Science.gov

Sample records for active space debris

  1. Activities on space debris in U.S.

    NASA Astrophysics Data System (ADS)

    Johnson, Nicholas L.

    2001-10-01

    In the U.S. space debris activities are addressed at all government levels, from the Executive Office of the President to the individual federal agencies to specialized centers, laboratories, organizations, and research groups. U.S. Space Policy specifically challenges government agencies to seek to minimize the creation of space debris and to promote debris minimization practices, both domestically and internationally. A set of space debris mitigation standard practices has been developed and adopted by relevant U.S. government agencies, and their application by the commercial aerospace community is highly encouraged. A growing number of U.S. government agencies have issued their own space debris mitigation policies, directives, regulations, and standards. Space debris research, including the definition and modeling of the current and future near-Earth space environment and the development of debris protection technologies, is principally conducted by NASA and the Department of Defense. The U.S. Space Surveillance Network continues to provide the most complete and timely characterization of the population of space debris larger than 10 cm. During the past several years major advancements have been achieved in extending this environment definition in LEO to include particles as small as only a few millimeters. The inspection of returned spacecraft surfaces continues to shed light on the even smaller debris population. With improvements in computer technology, new and more capable programs have been and are being developed to solve a number of operational and research problems. Finally, the academic and industrial sectors of the U.S. are also increasing their participation in and contributions to space debris operations and research. The cooperation of spacecraft and launch vehicle developers and operators is essential to the U.S. objective of promoting the preservation of the space environment for future generations.

  2. Activities on Space Debris in U.S.

    NASA Technical Reports Server (NTRS)

    Johnson, Nicholas L.

    2001-01-01

    In the U.S. space debris activities are addressed at all government levels, from the Executive Office of the President to the individual federal agencies to specialized centers, laboratories, organizations, and research groups. U.S. Space Policy specifically challenges government agencies to seek to minimize the creation of space debris and to promote debris minimization practices both domestically and internationally. A set of space debris mitigation standard practices has been developed and adopted by relevant US government agencies, and their application by the commercial aerospace community is highly encouraged. A growing number of US government agencies have issued their own space debris mitigation policies, directives, regulations, and standards. Space debris research, including the definition and modeling of the current and future near-Earth space environment and the development of debris protection technologies, is principally conducted by NASA and the Department of Defense. The U.S. Space Surveillance Network continues to provide the most complete and timely characterization of the population of space debris larger than 10 cm. During the past several years major advancements have been achieved in extending this environment definition in LEO to include particles as small as only a few millimeters. The inspection of returned spacecraft surfaces continues to shed light on the even smaller debris population. With improvements in computer technology, new and more capable programs have been and are being developed to solve a number of operational and research problems. Finally, the academic and industrial sectors of the U.S. are also increasing their participation in and contributions to space debris operations and research. The cooperation of satellite and launch vehicle developers and operators is essential to the U.S. objective of promoting the preservation of the space environment for future generations.

  3. Canada s activities on space debris mitigation technologies

    NASA Astrophysics Data System (ADS)

    Nikanpour, D.

    The threat of space debris to space activities is exponentially rising. Canada, as a space-faring nation having significant investment in space and astronauts participating in space missions, has recognized the risks arising from it and has been active as a participant in understanding and mitigate the problem. Since 1992, Canada has been involved with the creation of a sub-committee on space debris under the government's Interdepartmental Committee on Space (ICS) to deal with the policy and international cooperation on space debris. On the research front, Canadian Space Agency (CSA) has been coordinating the related researches within Canada. This paper outlines the major Canadian research activities on space debris and mitigation technologies along with CSA's future plan on the subject. Canadian research activities on space debris are in 3 major areas: (1) Measurement and modeling of space debris: The work has been led by the CSA (Space Technologies) with participations from research institutes and universities. The experiments cover the analysis and computational modeling of the space debris flux at orbital altitudes of interest for space activities. (2) Space debris mitigation: The technology for mitigating space debris is of key research interest and measures have been taken in the design and launch of LEO earth observation spacecraft, such as RADARSAT. RADARSAT-1, launched in 1995 and still operating, was one of the first commercial spacecraft to consider the effect of orbital debris in its design. Not only was the spacecraft designed to withstand a possible impact on orbit, and not be a source of debris from latches and tie-down mechanisms, but the launch of RADARSAT-1 was also delayed by 25 seconds in a very tight launch window, to avoid a possible impact on orbit. The design for the follow-on RADARSAT-2 spacecraft includes features to protect its Synthetic Aperture Radar (SAR) antenna against possible impact damage due to space debris as well as include

  4. Russian space agency activities on the problem of technogenic space debris

    NASA Astrophysics Data System (ADS)

    Blagun, V. P.; Kulik, S. V.; Lukyashchenko, V. I.

    1999-01-01

    In this paper the main directions and the major results of the activities on the problem of technogenic near-earth space (NES) orbital debris are discussed. With regard to monitoring the NES debris environment, the following issues are considered: the catalogue of space objects which includes objects in the geostationary ring, orbital debris models, and ground- and space-based observations. For the protection of spacecraft and Space Station from debris particles multilayer and other shields are used, as well as avoidance manoeuvres. Important issues are the determination of the location of impacts and restoration of the station wall tightness. The BUFFER program has been developed for the risk assessment of impacts of orbital debris particles with the Space Station. Measures are taken to reduce technogenic pollution of NES which include those to prevent launch vehicles and spacecraft explosions. Special attention is placed on the safe utilization of the geostationary orbit. From the results of these studies regulatory documents are issued.

  5. Space Shuttle Debris Transport

    NASA Technical Reports Server (NTRS)

    Gomez, Reynaldo J., III

    2010-01-01

    This slide presentation reviews the assessment of debris damage to the Space Shuttle, and the use of computation to assist in the space shuttle applications. The presentation reviews the sources of debris, a mechanism for determining the probability of damaging debris impacting the shuttle, tools used, eliminating potential damaging debris sources, the use of computation to assess while inflight damage, and a chart showing the applications that have been used on increasingly powerful computers simulate the shuttle and the debris transport.

  6. Active space debris removal by a hybrid propulsion module

    NASA Astrophysics Data System (ADS)

    DeLuca, L. T.; Bernelli, F.; Maggi, F.; Tadini, P.; Pardini, C.; Anselmo, L.; Grassi, M.; Pavarin, D.; Francesconi, A.; Branz, F.; Chiesa, S.; Viola, N.; Bonnal, C.; Trushlyakov, V.; Belokonov, I.

    2013-10-01

    During the last 40 years, the mass of the artificial objects in orbit increased quite steadily at the rate of about 145 metric tons annually, leading to a total tally of approximately 7000 metric tons. Now, most of the cross-sectional area and mass (97% in LEO) is concentrated in about 4600 intact objects, i.e. abandoned spacecraft and rocket bodies, plus a further 1000 operational spacecraft. Simulations and parametric analyses have shown that the most efficient and effective way to prevent the outbreak of a long-term exponential growth of the catalogued debris population would be to remove enough cross-sectional area and mass from densely populated orbits. In practice, according to the most recent NASA results, the active yearly removal of approximately 0.1% of the abandoned intact objects would be sufficient to stabilize the catalogued debris in low Earth orbit, together with the worldwide adoption of mitigation measures. The candidate targets for removal would have typical masses between 500 and 1000 kg, in the case of spacecraft, and of more than 1000 kg, in the case of rocket upper stages. Current data suggest that optimal active debris removal missions should be carried out in a few critical altitude-inclination bands. This paper deals with the feasibility study of a mission in which the debris is removed by using a hybrid propulsion module as propulsion unit. Specifically, the engine is transferred from a servicing platform to the debris target by a robotic arm so to perform a controlled disposal. Hybrid rocket technology for de-orbiting applications is considered a valuable option due to high specific impulse, intrinsic safety, thrust throttle ability, low environmental impact and reduced operating costs. Typically, in hybrid rockets a gaseous or liquid oxidizer is injected into the combustion chamber along the axial direction to burn a solid fuel. However, the use of tangential injection on a solid grain Pancake Geometry allows for more compact design of

  7. The INAF contribution to the ASI Space Debris program: observational activities.

    NASA Astrophysics Data System (ADS)

    Pupillo, G.; Salerno, E.; Bartolini, M.; Di Martino, M.; Mattana, A.; Montebugnoli, S.; Portelli, C.; Pluchino, S.; Schillirò, F.; Konovalenko, A.; Nabatov, A.; Nechaeva, M.

    Space debris are man made objects orbiting around Earth that pose a serious hazard for both present and future human activities in space. Since 2007 the Istituto Nazionale di Astrofisica (INAF) carried out a number of radar campaigns in the framework of the ASI ``Space Debris'' program. The observations were performed by using bi- and multi-static radars, composed of the INAF 32-m Italian radiotelescopes located at Medicina and Noto (used as receivers) and the 70-m parabolic antenna at Evpatoria (Ukraine) used as transmitter. The 32 m Ventspils antenna in Latvia also participated in the last campaign at the end of June 2010. Several kinds of objects in various orbital regions (radar calibrators, rocket upper stages, debris of different sizes) were observed and successfully detected. Some unknown objects were also discovered in LEO during the beam-park sessions. In this paper we describe some results of the INAF-ASI space debris research activity.

  8. An Introduction to Space Debris

    NASA Astrophysics Data System (ADS)

    Wright, David

    2008-04-01

    Space debris is any human-made object in orbit that no longer serves a useful purpose, including defunct satellites, discarded equipment and rocket stages, and fragments from the breakup of satellites and rocket stages. It is a concern because--due to its very high speed in orbit--even relatively small pieces can damage or destroy satellites in a collision. Since debris at high altitudes can stay in orbit for decades or longer, it accumulates as more is produced and the risk of collisions with satellites grows. Since there is currently no effective way to remove large amounts of debris from orbit, controlling the production of debris is essential for preserving the long-term use of space. Today there are 860 active satellites in orbit, supporting a wide range of civil and military uses. The 50 years of space activity since the launch of Sputnik 1 has also resulted in well over half a million pieces of orbiting debris larger than 1 cm in size. There are two main sources of space debris: (1) routine space activity and the accidental breakup of satellites and stages placed in orbit by such activity, and (2) the testing or use of destructive anti-satellite (ASAT) weapons that physically collide with satellites at high speed. The international community is attempting to reduce the first category by developing strict guidelines to limit the debris created as a result of routine space activities. However, the destruction of a single large spy satellite by an ASAT weapon could double the total amount of large debris in low earth orbit, and there are currently no international restrictions on these systems. This talk will give an introduction to what's in space, the origins of space debris, efforts to stem its growth, the threat it poses to satellites in orbit, and the long-term evolution of the debris population.

  9. Harpoon technology development for the active removal of space debris

    NASA Astrophysics Data System (ADS)

    Dudziak, Roger; Tuttle, Sean; Barraclough, Simon

    2015-08-01

    This paper presents the results of preliminary empirical testing and numerical modelling carried out to demonstrate the effectiveness of using a harpoon in an ADR application. Empirical testing involving the impact of blunt and conical shaped steel tips into 3 mm Al plate showed that the ballistic limit varies in proportion to the tip circumference, with conical shapes resulting in a higher relative ballistic limit due to the additional energy required for petaling. The creation of secondary debris was also monitored. It was found that blunt shapes created a plug during penetration as a result of shearing around the periphery of the projectile, whilst conical tips resulted in minor spalling and fragmentation. Preliminary oblique impact testing with conical and blunt tips showed that the ballistic limit increases with obliquity at a greater rate for blunt tips than conical ones. Impact testing of 3 mm Al plate with conical projectiles at low temperatures showed a more brittle fracture mode when compared with targets impacted at room temperature. As such, the fragmentation and spalling evident in room temperature targets was absent. The energy required to perforate the cooled plates also increased. Impact testing of Al panel obstructed with fixed heat pipes showed that the harpoon could successfully penetrate a target panel with such an obstruction due to shearing of the pipe flange. Testing of two lock on mechanisms showed that both a spring activated and integrated toggle could reliably open upon impact. This testing also used a tensile testing machine to show that both designs could withstand the force expected during deorbiting manoeuvres after impact with Al H/C panels. A parametric simulation comparing the diameter of conical tips with ballistic limits showed a good agreement with the predictions of De Marre's formula for normal impact. This suggests that the ballistic limit of plates impacted by conical projectiles can be successfully extrapolated with limited

  10. Space debris: modeling and detectability

    NASA Astrophysics Data System (ADS)

    Wiedemann, C.; Lorenz, J.; Radtke, J.; Kebschull, C.; Horstmann, A.; Stoll, E.

    2017-01-01

    High precision orbit determination is required for the detection and removal of space debris. Knowledge of the distribution of debris objects in orbit is necessary for orbit determination by active or passive sensors. The results can be used to investigate the orbits on which objects of a certain size at a certain frequency can be found. The knowledge of the orbital distribution of the objects as well as their properties in accordance with sensor performance models provide the basis for estimating the expected detection rates. Comprehensive modeling of the space debris environment is required for this. This paper provides an overview of the current state of knowledge about the space debris environment. In particular non-cataloged small objects are evaluated. Furthermore, improvements concerning the update of the current space debris model are addressed. The model of the space debris environment is based on the simulation of historical events, such as fragmentations due to explosions and collisions that actually occurred in Earth orbits. The orbital distribution of debris is simulated by propagating the orbits considering all perturbing forces up to a reference epoch. The modeled object population is compared with measured data and validated. The model provides a statistical distribution of space objects, according to their size and number. This distribution is based on the correct consideration of orbital mechanics. This allows for a realistic description of the space debris environment. Subsequently, a realistic prediction can be provided concerning the question, how many pieces of debris can be expected on certain orbits. To validate the model, a software tool has been developed which allows the simulation of the observation behavior of ground-based or space-based sensors. Thus, it is possible to compare the results of published measurement data with simulated detections. This tool can also be used for the simulation of sensor measurement campaigns. It is

  11. Space debris executive summary

    SciTech Connect

    Canavan, G.H.; Judd, O.; Naka, R.F.

    1996-09-01

    Spacecraft, boosters, and fragments are potential hazards to space vehicles, and it is argued that collisions between them could produce a cascade that could preclude activity in LEO in 25 to 50 years. That has generated pressure for constraints on military space operations, so the AF SAB performed a study of technical aspects of the debris problem. The Study was independent of the efforts of the Air Force Space Command (AFSPC) as well as those of and NASA Johnson Space Center (JSC), which is the principal advocate for cascades and constraints. Most work on space debris has been performed by AFSPC and JSC, so the Study was in part an assessment of their efforts, in which both have been cooperative. The Study identified the main disagreements and quantified their impacts. It resolved some issues and provided bounds for the rest. It treated radar and optical observations; launch, explosion, and decay rates; and the number and distribution of fragments from explosions and collisions. That made it possible to address hazard to manned spacecraft at low altitudes and the possibility of cascading at higher altitudes, both of which now appear less likely.

  12. Space debris detection and mitigation

    SciTech Connect

    Allahdadi, F.

    1993-01-01

    Space debris is defined as all useless man-made objects in space. This conference covers the following areas: debris detection, tracking, and surveillance; orbital debris analytical modeling; debris environment and safety issues; and orbital debris mitigation. Separate abstracts were prepared for 26 papers in this conference.

  13. Active Space Debris Removal using European Modified Launch Vehicle Upper Stages Equipped with Electrodynamic Tethers

    NASA Astrophysics Data System (ADS)

    Nasseri, Ali S.; Emanuelli, Matteo; Raval, Siddharth; Turconi, Andrea; Becker, Cristoph

    2013-08-01

    During the past few years, several research programs have assessed the current state and future evolution of the Low Earth Orbit region. These studies indicate that space debris density could reach a critical level such that there will be a continuous increase in the number of debris objects, primarily driven by debris-debris collision activity known as the Kessler effect. This cascade effect can be even more significant when intact objects as dismissed rocket bodies are involved in the collision. The majority of the studies until now have highlighted the urgency for active debris removal in the next years. An Active Debris Removal System (ADRS) is a system capable of approaching the debris object through a close-range rendezvous, establishing physical connection, stabilizing its attitude and finally de-orbiting the debris object using a type of propulsion system in a controlled manoeuvre. In its previous work, this group showed that a modified Fregat (Soyuz FG's 4th stage) or Breeze-M upper stage (Proton-M) launched from Plesetsk (Russian Federation) and equipped with an electro-dynamic tether (EDT) system can be used, after an opportune inclination's change, to de-orbit a Kosmos-3M second stage rocket body while also delivering an acceptable payload to orbit. In this paper, we continue our work on the aforementioned concept, presented at the 2012 Beijing Space Sustainability Conference, by comparing its performance to ADR missions using only chemical propulsion from the upper stage for the far approach and the de-orbiting phase. We will also update the EDT model used in our previous work and highlight some of the methods for creating physical contact with the object. Moreover, we will assess this concept also with European launch vehicles (Vega and Soyuz 2-1A) to remove space debris from space. In addition, the paper will cover some economic aspects, like the cost for the launches' operator in term of payload mass' loss at the launch. The entire debris removal

  14. Space Debris & its Mitigation

    NASA Astrophysics Data System (ADS)

    Kaushal, Sourabh; Arora, Nishant

    2012-07-01

    Space debris has become a growing concern in recent years, since collisions at orbital velocities can be highly damaging to functioning satellites and can also produce even more space debris in the process. Some spacecraft, like the International Space Station, are now armored to deal with this hazard but armor and mitigation measures can be prohibitively costly when trying to protect satellites or human spaceflight vehicles like the shuttle. This paper describes the current orbital debris environment, outline its main sources, and identify mitigation measures to reduce orbital debris growth by controlling these sources. We studied the literature on the topic Space Debris. We have proposed some methods to solve this problem of space debris. We have also highlighted the shortcomings of already proposed methods by space experts and we have proposed some modification in those methods. Some of them can be very effective in the process of mitigation of space debris, but some of them need some modification. Recently proposed methods by space experts are maneuver, shielding of space elevator with the foil, vaporizing or redirecting of space debris back to earth with the help of laser, use of aerogel as a protective layer, construction of large junkyards around international space station, use of electrodynamics tether & the latest method proposed is the use of nano satellites in the clearing of the space debris. Limitations of the already proposed methods are as follows: - Maneuvering can't be the final solution to our problem as it is the act of self-defence. - Shielding can't be done on the parts like solar panels and optical devices. - Vaporizing or redirecting of space debris can affect the human life on earth if it is not done in proper manner. - Aerogel has a threshold limit up to which it can bear (resist) the impact of collision. - Large junkyards can be effective only for large sized debris. In this paper we propose: A. The Use of Nano Tubes by creating a mesh

  15. Space Debris Environent Remediation Concepts

    NASA Astrophysics Data System (ADS)

    Klinkrad, H.; Johnson, N. L.

    2009-03-01

    Long-term projections of the space debris environment indicate that even drastic measures, such as an immediate, complete halt of launch and release activities, will not result in a stable environment of man-made space objects. Collision events between already existing space hardware will within a few decades start to dominate the debris population, and result in a net increase of the space debris population, also at sizes which may cause further catastrophic collisions. A collisional cascading may ultimately lead to a run-away situation ("Kessler syndrome"), with no further possibility of human intervention.The International Academy of Astronautics (IAA) has been investigating the status and the stability of the space debris environment in several studies by first looking into space traffic management possibilities, and then investigating means of mitigating the creation of space debris. In an on-going activity, an IAA study group looks into methods of active space debris environment remediation. In contrast to the former mitigation study, the current activity concentrates on the active removal of large objects, such as defunct spacecraft, orbital stages, and mission-related objects, which serve as a latent mass reservoir that fuels initial castastrophic collisions and later collisional cascading. The paper will outline different mass removal concepts, e.g. based on directed energy, tethers (momentum exchange or electro-dynamic), aerodynamic drag augmentation, solar sails, auxiliary propulsion units, retarding surfaces, or on-orbit capture. Apart from physical principles of the proposed concepts, their applicability to different orbital regimes, and their effectiveness concerning mass removal efficiency will be discussed.

  16. Space Tourism: Orbital Debris Considerations

    NASA Astrophysics Data System (ADS)

    Mahmoudian, N.; Shajiee, S.; Moghani, T.; Bahrami, M.

    2002-01-01

    Space activities after a phase of research and development, political competition and national prestige have entered an era of real commercialization. Remote sensing, earth observation, and communication are among the areas in which this growing industry is facing competition and declining government money. A project like International Space Station, which draws from public money, has not only opened a window of real multinational cooperation, but also changed space travel from a mere fantasy into a real world activity. Besides research activities for sending man to moon and Mars and other outer planets, space travel has attracted a considerable attention in recent years in the form of space tourism. Four countries from space fairing nations are actively involved in the development of space tourism. Even, nations which are either in early stages of space technology development or just beginning their space activities, have high ambitions in this area. This is worth noting considering their limited resources. At present, trips to space are available, but limited and expensive. To move beyond this point to generally available trips to orbit and week long stays in LEO, in orbital hotels, some of the required basic transportations, living requirements, and technological developments required for long stay in orbit are already underway. For tourism to develop to a real everyday business, not only the price has to come down to meaningful levels, but also safety considerations should be fully developed to attract travelers' trust. A serious hazard to space activities in general and space tourism in particular is space debris in earth orbit. Orbiting debris are man-made objects left over by space operations, hazardous to space missions. Since the higher density of debris population occurs in low earth orbit, which is also the same orbit of interest to space tourism, a careful attention should be paid to the effect of debris on tourism activities. In this study, after a

  17. Space debris detection

    NASA Astrophysics Data System (ADS)

    Eather, Robert H.

    1992-12-01

    A feasibility study on the possibility of detecting less than or = 10 cm space debris using a large-aperture ground-based telescope (with an intensified CCD detector) was completed, showing that detection should be possible. A detector system was designed and built, and installed on the 2.54 m WRDC telescope at Wright Patterson AFB. Bad seeing conditions in the Dayton area prevented the expected debris detection. Subsequently, a small 40 cm telescope was built and operated from the Haystack Observatory (Groton, MA). Known objects were used to test pointing and acquisition procedures, and the system was then shipped to Rattlesnake Observatory (Richland, WA) for participation in the ODERAC's debris calibration experiment from the Space Shuttle. This experiment failed, and our instrument has been stored at Rattlesnake in anticipation of a new ODERAC's flight in late 1993.

  18. Dynamics analysis and GNC design of flexible systems for space debris active removal

    NASA Astrophysics Data System (ADS)

    Benvenuto, Riccardo; Salvi, Samuele; Lavagna, Michèle

    2015-05-01

    Active debris removal is one of current hot spots in space research, necessary for space exploitation durability. Different techniques have been proposed for this challenging task, among them the use of throw-nets and tow-tethers seems promising: that opens new challenges for Guidance Navigation and Control (GNC) design, especially whenever flexible connections are involved. Via numerical simulations using a multi-body dynamics simulation tool developed at Politecnico di Milano - Department of Aerospace Science and Technology, this paper shows that tethered-net systems are a promising technology to capture and remove space debris and discusses the main difficulties that are likely to take place during capture and disposal phases, particularly from a GNC point of view.

  19. Space Debris Hazard Evaluation

    NASA Technical Reports Server (NTRS)

    Davison, Elmer H.; Winslow, Paul C., Jr.

    1961-01-01

    The hazard to space vehicles from natural space debris has been explored. A survey of the available information pertinent to this problem is presented. The hope is that this presentation gives a coherent picture of the knowledge to date in terms of the topic covered. The conclusion reached is that a definite hazard exists but that it can only be poorly assessed on the basis of present information. The need for direct measurement of this hazard is obvious, and some of the problems involved in making these direct measurements have been explored.

  20. Space Debris Mitigation CONOPS Development

    DTIC Science & Technology

    2013-06-01

    manmade orbital debris and that they existed in cloud clusters sometimes 1000 km along track (Mulholland and Veillet, 2004). 6 Although many...space debris. Orbital debris is herein defined as “any man-made Earth-orbiting object which is non-functional with no reasonable expectation of...Mission (SMM or Solar Max) and the Hubble Space Telescope (HST)…[and] Orbital Debris Collector (ODC) and the Momentum Stage Impact Detector (MOM

  1. Space debris, remarks on current legal issues

    NASA Astrophysics Data System (ADS)

    Kerrest, Armel

    2001-10-01

    A legal definition of space debris must take into consideration its consequences on the legal status of the object. For the purpose of mitigation of space debris at the time of the launch, any object launched in outer pace will turn sooner or later into a space debris. For liability purposes, a definition of a "space object " is more useful that the notion of "space debris". It must be sure that every space debris is considered as a space objet according to the liability convention. At the end and certainly a more difficult issue is the qualification of a space object as a space debris when it will be technically feasible to remove it. The question of the property of the debris or object should be important. States are responsible and liable for space debris. According to article VI and VII of the Outer Space Treaty, they must authorise and control any national space activity and make sure these activities will not be conducted against the law. In the case of an accident and excepting the use of nuclear power sources, the main problem lies on damage in outer space to other spacecraft. In that case, the victim must prove a fault. According with the lack of precise rules it should be difficult. It should be necessary to precise the law applicable to space debris. At the domestic level, rules must be taken to prevent space debris through an assessment of risk within the licensing process. At the international level, the principle of an obligation to mitigate debris should be clearly accepted. Some general rules should be useful to avoid breach of competition between commercial actors. The adoption of a clear and precise code of conduct should be of great help because it would determine the good launching States' behaviour and greatly helps the judge appreciating the proof of a fault in case of an accident.

  2. RS-34 Phoenix In-Space Propulsion System Applied to Active Debris Removal Mission

    NASA Technical Reports Server (NTRS)

    Esther, Elizabeth A.; Burnside, Christopher G.

    2014-01-01

    In-space propulsion is a high percentage of the cost when considering Active Debris Removal mission. For this reason it is desired to research if existing designs with slight modification would meet mission requirements to aid in reducing cost of the overall mission. Such a system capable of rendezvous, close proximity operations, and de-orbit of Envisat class resident space objects has been identified in the existing RS-34 Phoenix. RS-34 propulsion system is a remaining asset from the de-commissioned United States Air Force Peacekeeper program; specifically the pressure-fed storable bi-propellant Stage IV Post Boost Propulsion System. The National Aeronautics and Space Administration (NASA) Marshall Space Flight Center (MSFC) gained experience with the RS-34 propulsion system on the successful Ares I-X flight test program flown in the Ares I-X Roll control system (RoCS). The heritage hardware proved extremely robust and reliable and sparked interest for further utilization on other potential in-space applications. Subsequently, MSFC has obtained permission from the USAF to obtain all the remaining RS-34 stages for re-use opportunities. The MSFC Advanced Concepts Office (ACO) was commissioned to lead a study for evaluation of the Rocketdyne produced RS-34 propulsion system as it applies to an active debris removal design reference mission for resident space object targets including Envisat. Originally designed, the RS-34 Phoenix provided in-space six-degrees-of freedom operational maneuvering to deploy payloads at multiple orbital locations. The RS-34 Concept Study lead by sought to further understand application for a similar orbital debris design reference mission to provide propulsive capability for rendezvous, close proximity operations to support the capture phase of the mission, and deorbit of single or multiple large class resident space objects. Multiple configurations varying the degree of modification were identified to trade for dry mass optimization and

  3. Benefits of Active Debris Removal on the LEO Debris Population

    NASA Astrophysics Data System (ADS)

    Maniwa, Kazuaki; Hanada, Toshiya; Kawamoto, Satomi

    Since the launch of Sputnik, orbital debris population continues to increase due to ongoing space activities, on-orbit explosions, and accidental collisions. In the future, a great deal of fragments can be expected to be created by explosions and collisions. In spite of prevention of satellite and rocket upper stage explosions and other mitigation measures, debris population in low Earth orbit may not be stabilized. To better limit the growth of the future debris population, it is necessary to remove the existing debris actively. This paper studies about the effectiveness of active debris removal in low Earth orbit where the collision rate with and between space debris is high. This study does not consider economic problems, but investigates removing debris which may stabilize well the current debris population based on the concept of Japan Aerospace Exploration Agency.

  4. Space debris mitigation measures in India

    NASA Astrophysics Data System (ADS)

    Adimurthy, V.; Ganeshan, A. S.

    2006-02-01

    The Indian Space Research Organization (ISRO) recognizes the importance of the current space debris scenario, and the impact it has on the effective utilization of space technology for the improvement in the quality of life on the Earth. ISRO is committed to effective management of the threats due to space debris. Towards this commitment ISRO works on different aspects of space debris, including the debris mitigation measures. This paper highlights the activities and achievements in the implementation of the mitigation measures. ISRO successfully designed and developed a propellant venting system for implementation in the existing upper stage of India's Polar Satellite Launch Vehicle (PSLV), which uses Earth-storable liquid propellants. GSLV also employs passivation of the Cryogenic Upper Stage at the end of its useful mission. ISRO's communication satellites in GSO are designed with adequate propellant margins for re-orbiting at the end of their useful life to a higher graveyard orbit. A typical successful operation in connection with INSAT-2C is described. ISRO developed its debris environmental models and software to predict the close approach of any of the debris to the functional satellites. The software are regularly used for the debris risk management of the orbiting spacecraft and launch vehicles. ISRO recognizes the role of international cooperation in the debris mitigation measures and actively contributes to the efforts of the Inter-Agency Space Debris Coordination Committee (IADC) and United Nations Committee on the Peaceful Uses of Outer Space (UNCOPUOS).

  5. Remote Maneuver of Space Debris Using Photon Pressure for Active Collision Avoidance

    NASA Astrophysics Data System (ADS)

    Smith, C.

    2014-09-01

    The Space Environment Research Corporation (SERC) is a consortium of companies and research institutions that have joined together to pursue research and development of technologies and capabilities that will help to preserve the orbital space environment. The consortium includes, Electro Optics Systems (Australia), Lockheed Martin Australia, Optus Satellite Systems (Australia), The Australian national University, RMIT University, National Institute of Information and Communications Technology (NICT, Japan) as well as affiliates from NASA Ames and ESA. SERC is also the recipient of and Australian Government Cooperative Research Centre grant. SERC will pursue a wide ranging research program including technologies to improve tracking capability and capacity, orbit determination and propagation algorithms, conjunction analysis and collision avoidance. All of these technologies will contribute to the flagship program to demonstrate active collision avoidance using photon pressure to provide remote maneuver of space debris. This project joins of the proposed NASA Lightforce concept with infrastructure and capabilities provided by SERC. This paper will describe the proposed research and development program to provide an on-orbit demonstration within the next five years for remote maneuver of space debris.

  6. Formation Flying Guidance for Space Debris Observation, Manipulation and Capture

    NASA Astrophysics Data System (ADS)

    Peters, Thomas V.

    This article provides a brief overview of the space debris population, debris attitude dynamics, technologies for debris removal, followed by a more in-depth discussion of robotic arm based capture of debris. Guidance aspects of active debris removal missions are discussed. Mission phases for active debris removal missions are rendezvous, inspection, attitude synchronization and capture and de-tumbling. The need for attitude synchronization is driven by recent observations of Envisat which exhibits a fairly high rotation rate.

  7. Space debris modeling at NASA

    NASA Astrophysics Data System (ADS)

    Johnson, Nicholas L.

    2001-10-01

    Since the Second European Conference on Space Debris in 1997, the Orbital Debris Program Office at the NASA Johnson Space Center has undertaken a major effort to update and improve the principal software tools employed to model the space debris environment and to evaluate mission risks. NASA's orbital debris engineering model, ORDEM, represents the current and near-term Earth orbital debris population from the largest spacecraft to the smallest debris in a manner which permits spacecraft engineers and experimenters to estimate the frequency and velocity with which a satellite may be struck by debris of different sizes. Using expanded databases and a new program design, ORDEM2000 provides a more accurate environment definition combined with a much broader array of output products in comparison with its predecessor, ORDEM96. Studies of the potential long-term space debris environment are now conducted with EVOVLE 4.0, which incorporates significant advances in debris characterization and breakup modeling. An adjunct to EVOLVE 4.0, GEO EVOLVE has been created to examine debris issues near the geosynchronous orbital regime. In support of NASA Safety Standard (NSS) 1740.14, which establishes debris mitigation guidelines for all NASA space programs, a set of evaluation tools called the Debris Assessment Software (DAS) is specifically designed for program offices to determine whether they are in compliance with NASA debris mitigation guidelines. DAS 1.5 has recently been completed with improved WINDOWS compatibility and graphics functions. DAS 2.0 will incorporate guideline changes in a forthcoming revision to NSS 1740.14. Whereas DAS contains a simplified model to calculate possible risks associated with satellite reentries, NASA's higher fidelity Object Reentry Survival Analysis Tool (ORSAT) has been upgraded to Version 5.0. With the growing awareness of the potential risks posed by uncontrolled satellite reentries to people and property on Earth, the application of

  8. LDEF meteoroid and debris special investigation group investigations and activities at the Johnson Space Center

    NASA Technical Reports Server (NTRS)

    See, Thomas H.; Warren, Jack L.; Zolensky, Michael E.; Sapp, Clyde A.; Bernhard, Ronald P.; Dardano, Claire B.

    1995-01-01

    Since the return of the Long Duration Exposure Facility (LDEF) in January, 1990, members of the Meteoroid and Debris Special Investigation Group (M&D SIG) at the Johnson Space Center (JSC) in Houston, Texas have been examining LDEF hardware in an effort to expand the knowledge base regarding the low-Earth orbit (LEO) particulate environment. In addition to the various investigative activities, JSC is also the location of the general Meteoroid & Debris database. This publicly accessible database contains information obtained from the various M&D SIG investigations, as well as limited data obtained by individual LDEF Principal Investigators. LDEF exposed approximately 130 m(exp 2) of surface area to the LEO particulate environment, approximately 15.4 m(exp 2) of which was occupied by structural frame components (i.e., longerons and intercoastals) of the spacecraft. The data reported here was obtained as a result of detailed scans of LDEF intercoastals, 68 of which reside at JSC. The limited amount of data presently available on the A0178 thermal control blankets was reported last year and will not be reiterated here. The data presented here are limited to measurements of crater diameters and their frequency of occurrence (i.e., flux).

  9. An active time-optimal control for space debris deorbiting via geomagnetic field

    NASA Astrophysics Data System (ADS)

    Amiri Atashgah, M. A.; Gazerpour, Hamid; Lavaei, Abolfazl; Zarei, Yaser

    2017-02-01

    This paper is concerned with an approach for active removing of space debris by electrodynamic tether (EDT) systems in a time-optimal maneuver. In this regard, a collector-emitter system is comprised of the insulated EDT in order to generate the required electric current over a virtual circuit once the induced electric current is adopted as control force producer. To this end, a simulation program is initially developed, during which dynamic and mathematical models of the EDT as well as the geomagnetic field are encompassed, respectively. This toolset is first utilized for prediction of orbital characteristics during the deorbit process; and subsequently, using the direct transcription method, the time-optimal problem is well solved. The efficacy of the suggested technique is verified through extensive simulations once all hard constraints of the underlying problem are well satisfied. In short, while the altitude varies from 1413 to 200 km, the optimized deorbit time would reduce about 17 days.

  10. Lightweight Shield Against Space Debris

    NASA Technical Reports Server (NTRS)

    Redmon, John W., Jr.; Lawson, Bobby E.; Miller, Andre E.; Cobb, W. E.

    1992-01-01

    Report presents concept for lightweight, deployable shield protecting orbiting spacecraft against meteoroids and debris, and functions as barrier to conductive and radiative losses of heat. Shield made in four segments providing 360 degree coverage of cylindrical space-station module.

  11. Modeling and control of a space robot for active debris removal

    NASA Astrophysics Data System (ADS)

    Dubanchet, Vincent; Saussié, David; Alazard, Daniel; Bérard, Caroline; Peuvédic, Catherine Le

    2015-06-01

    Space access and satellites lifespan are increasingly threatened by the great amount of debris in Low Earth Orbits. Among the many solutions proposed in the literature so far, the emphasis is put here on a robotic arm mounted on a "chaser" satellite to capture massive debris, such as dead satellites or launch vehicle upper stages. The modeling and control of such systems are investigated throughout the paper. Dynamic models rely on an adapted Newton-Euler algorithm, and control algorithms are based on the fixed-structure H_{&infty}; synthesis, recently implemented in an efficient Matlab toolbox. The main goal is to efficiently track a target point on the debris while using PD-like controllers to reduce computational burden. The fixed-structure H_{∞} framework proves to be a suitable tool to design a reduced-order robust controller that catches up with external disturbances and is simultaneously compatible with current space processors capabilities.

  12. Modelling of space debris and meteoroids

    NASA Astrophysics Data System (ADS)

    Mandeville, J. C.; Alby, F.

    1997-05-01

    Since several years, CNES has undertaken studies in the field of debris and meteoroids since the knowledge of this environment is of prime importance for space activities and will be a growing concern in the future. In the frame of this study, the main available models concerning space debris and meteoroids have been analysed: origin, principle of modelization, limits and evolution as a function of time. A reference model has been choosen and evaluated through comparisons with available data, coming from in flight experiments such as LDEF, EURECA, MIR and HUBBLE. This work will lead in the future to improve the models, particularly for the small size debris.

  13. Optical surveys for space debris

    NASA Astrophysics Data System (ADS)

    Schildknecht, Thomas

    2007-01-01

    Space debris—man-made non-functional objects of all sizes in near-Earth space—has been recognized as an increasing threat for current and future space operations. The debris population in near-Earth space has therefore been extensively studied during the last decade. Information on objects at altitudes higher than about 2,000 km is, however, still comparatively sparse. Debris in this region is best detected by surveys utilizing optical telescopes. Moreover, the instruments and the applied observation techniques, as well as the processing methods, have many similarities with those used in optical surveys for ‘astronomical’ objects like near-Earth objects (NEOs). The present article gives a general introduction to the problem of space debris, presents the used observation and processing techniques emphasizing the similarities and differences compared to optical surveys for NEOs, and reviews the results from optical surveys for space debris in high-altitude Earth orbits. Predictions on the influence of space debris on the future of space research and space astronomy in particular are reported as well.

  14. Space debris studies in Japan

    NASA Astrophysics Data System (ADS)

    Toda, Susumu; Yasaka, Tetsuo

    1993-08-01

    The Space Debris Study Group of the Japan Society for Aeronautical and Space Sciences was established in September 1990 and the Interim Report was published in January 1992. The group has five subgroups: Observation, Cause, Modeling, Protection, and Social Impact. It intends to promote an awareness for the problem and put together related researches, to define the urgently needed activity area by first describing the present situation in each engineering field and then summarizing on-going respective researches. It is expected that sound technological base line understandings to the problem are to be attained at various institutions. International cooperations are indispensable, and Japanese efforts should be focused on those which do not duplicate but are complementary to achievements in other countries. Some of the results obtained by the group are presented and several examples of individual researches are summarized.

  15. The ESA Space Debris Mitigation Handbook 2002

    NASA Astrophysics Data System (ADS)

    Klinkrad, H.; Beltrami, P.; Hauptmann, S.; Martin, C.; Sdunnus, H.; Stokes, H.; Walker, R.; Wilkinson, J.

    2004-01-01

    The ESA Space Debris Mitigation Handbook 2002 was jointly produced by an industrial consortium and ESA, under an ESA contract. The Handbook is a non-regulatory, self-standing document, providing technical information in support of European debris mitigation standards. The necessity of debris mitigation is illustrated in the context of historic launch activities and operational practices, which led to the current debris environment, with corresponding collision flux levels. Based on detailed population evolution models, this initial population is analyzed with respect to its growth and stability under different traffic assumptions. The implementation of debris mitigation measures, in particular the de-orbiting of spacecraft and upper stages, is shown to reduce the debris growth to an acceptable level within a few decades. The risk on ground due to re-entering space objects, its assessment, and its control is also analyzed. For on-orbit systems, collision risk reduction by avoidance manoeuvres, and passive protection by shielding is outlined. ESA's Handbook also compares recommended debris mitigation and risk reduction practices proposed by several other space agencies. The Handbook will be available at the begin of 2003.

  16. The ESA Space Debris Mitigation Handbook 2002

    NASA Astrophysics Data System (ADS)

    Klinkrad, H.; Beltrami, P.; Hauptmann, S.; Martin, C.; Sdunnus, H.; Stokes, H.; Walker, R.; Wilkinson, J.

    The ESA Space Debris Mitigation Handbook 2002 was jointly produced by an industrial consortium and ESA, under an ESA contract. The Handbook is a non-regulatory, self-standing document, providing technical information in support of European debris mitigation standards. The necessity of debris mitigation is illustrated in the context of historic launch activities and operational practices, which led to the current debris environment, with corresponding collision flux levels. Based on detailed population evolution models, this initial population is analysed with respect to its growth and stability under different traffic assumptions. The implementation of debris mitigation measures, in particular the de-orbiting of spacecraft and upper stages, is shown to reduce the debris growth to an acceptable level within a few decades. The risk on ground due to re-entering space objects, its assessment, and its control is also analysed. For on-orbit systems, collision risk reduction by avoidance manoeuvres, and passive protection by shielding is outlined. ESA's Handbook also compares recommended debris mitigation and risk reduction practices proposed by several other space agencies. The Handbook will be available by the end of 2002.

  17. Operational support to collision avoidance activities by ESA's space debris office

    NASA Astrophysics Data System (ADS)

    Braun, V.; Flohrer, T.; Krag, H.; Merz, K.; Lemmens, S.; Bastida Virgili, B.; Funke, Q.

    2016-09-01

    The European Space Agency's (ESA) Space Debris Office provides a service to support operational collision avoidance activities. This support currently covers ESA's missions Cryosat-2, Sentinel-1A and -2A, the constellation of Swarm-A/B/C in low-Earth orbit (LEO), as well as missions of third-party customers. In this work, we describe the current collision avoidance process for ESA and third-party missions in LEO. We give an overview on the upgrades developed and implemented since the advent of conjunction summary messages (CSM)/conjunction data messages (CDM), addressing conjunction event detection, collision risk assessment, orbit determination, orbit and covariance propagation, process control, and data handling. We pay special attention to the effect of warning thresholds on the risk reduction and manoeuvre rates, as they are established through risk mitigation and analysis tools, such as ESA's Debris Risk Assessment and Mitigation Analysis (DRAMA) software suite. To handle the large number of CDMs and the associated risk analyses, a database-centric approach has been developed. All CDMs and risk analysis results are stored in a database. In this way, a temporary local "mini-catalogue" of objects close to our target spacecraft is obtained, which can be used, e.g., for manoeuvre screening and to update the risk analysis whenever a new ephemeris becomes available from the flight dynamics team. The database is also used as the backbone for a Web-based tool, which consists of the visualization component and a collaboration tool that facilitates the status monitoring and task allocation within the support team as well as communication with the control team. The visualization component further supports the information sharing by displaying target and chaser motion over time along with the involved uncertainties. The Web-based solution optimally meets the needs for a concise and easy-to-use way to obtain a situation picture in a very short time, and the support for

  18. ESA Technologies for Space Debris Remediation

    NASA Astrophysics Data System (ADS)

    Wormnes, K.; Le Letty, R.; Summerer, L.; Schonenborg, R.; Dubois-Matra, O.; Luraschi, E.; Cropp, A.; Krag, H.; Delaval, J.

    2013-08-01

    Space debris is an existing and growing problem for space operations. Studies show that for a continued use of LEO, 5 - 10 large and strategically chosen debris need to be removed every year. The European Space Agency (ESA) is actively pursuing technologies and systems for space debris removal under its Clean Space initiative. This overview paper describes the activities that are currently ongoing at ESA and that have already been completed. Additionally it outlines the plan for the near future. The technologies under study fall in two main categories corresponding to whether a pushing or a pulling manoeuvre is required for the de-orbitation. ESA is studying the option of using a tethered capture system for controlled de-orbitation through pulling where the capture is performed using throw-nets or alternatively a harpoon. The Agency is also studying rigid capture systems with a particular emphasis on tentacles (potentially combined with a robotic arm). Here the de-orbitation is achieved through a push-manoeuvre. Additionally, a number of activities will be discussed that are ongoing to develop supporting technologies for these scenarios, or to develop systems for de-orbiting debris that can be allowed to re-enter in an uncontrolled manner. The short term goal and main driver for the current technology developments is to achieve sufficient TRL on required technologies to support a potential de-orbitation mission to remove a large and strategically chosen piece of debris.

  19. Space Telescopes and Orbital Debris

    NASA Astrophysics Data System (ADS)

    Seitzer, Patrick

    2009-01-01

    Almost 12,000 artificial objects orbiting the Earth are currently in the public catalog of orbital elements maintained by the USAF. Only a small fraction of them are operational satellites. The remainder is satellites whose missions have ended, rocket bodies, and parts and debris from larger parent objects. And the catalog only contains the biggest and brightest of the objects in orbit. The Low Earth Orbit (LEO) regime where most of this population concentrates is also a regime of incredible interest to astronomers, since it is where flagship missions such as the Hubble Space Telescope and other Great Observatories operate. I'll review the current state of knowledge of the orbital debris population, how it has grown with time, and how this environment could affect current and future space telescopes. There are mitigation measures which many spacecraft operators have adopted which can control the growth of the debris population. Orbital debris research at the University of Michigan is funded by NASA's Orbital Debris Program Office, Johnson Space Center, Houston, Texas.

  20. Space Debris Detection and Analysis

    DTIC Science & Technology

    1994-02-28

    7F AD-A282 012 PL.-TR-94-206 Space Debris Detection and Analysis Robert H. Eather Ron Siewert Keo Consultants 27 Irving St. Brookline MA 02146 28...PERFORMING ORGANIZATION REPORT NUMBER Keo Consultants 27 Irving St. Brookline MA 02146 9. SPONSORINGI MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING

  1. Comparison of space debris estimates

    SciTech Connect

    Canavan, G.H.; Judd, O.P.; Naka, R.F.

    1996-10-01

    Debris is thought to be a hazard to space systems through impact and cascading. The current environment is assessed as not threatening to defense systems. Projected reductions in launch rates to LEO should delay concerns for centuries. There is agreement between AFSPC and NASA analyses on catalogs and collision rates, but not on fragmentation rates. Experiments in the laboratory, field, and space are consistent with AFSPC estimates of the number of fragments per collision. A more careful treatment of growth rates greatly reduces long-term stability issues. Space debris has not been shown to be an issue in coming centuries; thus, it does not appear necessary for the Air Force to take additional steps to mitigate it.

  2. HEO space debris orbit predictions.

    NASA Astrophysics Data System (ADS)

    Gregorowicz, Dorota; Pospieszynski, Remigiusz; Golembiewska, Justyna; Wnuk, Edwin

    2012-07-01

    HEO (Highly Elliptical Orbit) satellites are objects with an elliptic orbit with a low-altitude perigee and a high-altitude apogee. Perigee mainly cross the LEO orbits and apogee reaches regions above GEO orbits. Number of satellites on the orbits are old racket bodies and other space debris. Most of HEO objects has the eccentricity more than 0.7. Many trackable objects are included in the NORAD TLE Catalogue but much more small debris exist which we could not track. Objects on as highly elliptical orbit are very danger for satellites in LEO region because of increasing velocity near the perigee. In order to calculate the trajectory of space debris we have to take into account force model consisting of geopotential, luni-solar effects, solar radiation pressure and for objects with low-altitude of perigee, atmospheric drag. This last perturbation is very important to calculate orbits with high accuracy but also one of the hardest to predict. Many atmospheric space debris objects parameters should be taken into account in this case, but we do not have sufficient data from observations, in particular S/M (area-to-mass) ratio. Fortunately we have some archival data for some debris included in TLE Catalogue, which are very helpful to estimate the approximate value of the parameter. In this paper we present the results of calculations of orbit predictions for short and medium time span (up to several weeks). We tried to designate the S/M parameter for some HEO objects from archival data from the TLE Catalogue and predict its orbital elements for several weeks. With better knowledge about approximate mean value of the S/M parameter we are able to improve the accuracy of predicted orbits.

  3. Space Debris: Its Causes and Management

    NASA Technical Reports Server (NTRS)

    Johnson, Nicholas L.

    2002-01-01

    Orbital debris is internationally recognized as an environmental issue which needs to be addressed today to preserve near-Earth space for future generations. All major space agencies are committed to mitigating the growth of the debris environment. Many commercial space system operators have responded positively to orbital debris mitigation principles and recommendations. Orbital debris mitigation measures are most cost-effective if included in the design development phase.

  4. Orbiting space debris: Dangers, measurement and mitigation

    NASA Astrophysics Data System (ADS)

    McNutt, Ross T.

    1992-06-01

    Space debris is a growing environmental problem. Accumulation of objects in earth orbit threatens space systems through the possibility of collisions and runaway debris multiplication. The amount of debris in orbit is uncertain due to the lack of information on the population of debris between 1 and 10 centimeters diameter. Collisions with debris even smaller than 1 cm can be catastrophic due to the high orbital velocities involved. Research efforts are under way at NASA, United States Space Command and the Air Force Phillips Laboratory to detect and catalog the debris population in near-earth space. Current international and national laws are inadequate to control the proliferation of space debris. Space debris is a serious problem with large economic, military, technical and diplomatic components. Actions need to be taken now to: determine the full extent of the orbital debris problem; accurately predict the future evolution of the debris population; decide the extent of the debris mitigation procedures required; implement these policies on a global basis via an international treaty. Action must be initiated now, before the loss of critical space systems such as the space shuttle or the space station.

  5. Orbiting space debris: Dangers, measurement, and mitigation

    NASA Astrophysics Data System (ADS)

    McNutt, Ross T.

    1992-01-01

    Space debris is a growing environmental problem. Accumulation of objects in Earth orbit threatens space systems through the possibility of collisions and runaway debris multiplication. The amount of debris in orbit is uncertain due to the lack of information on the population of debris between 1 and 10 centimeters diameter. Collisions with debris even smaller than 1 cm can be catastrophic due to the high orbital velocities involved. Research efforts are under way at NASA, Unites States Space Command and the Air Force Phillips Laboratory to detect and catalog the debris population in near-Earth space. Current international and national laws are inadequate to control the proliferation of space debris. Space debris is a serious problem with large economic, military, technical, and diplomatic components. Actions need to be taken now for the following reasons: determine the full extent of the orbital debris problem; accurately predict the future evolution of the debris population; decide the extent of the debris mitigation procedures required; implement these policies on a global basis via an international treaty. Action must be initiated now, before the the loss of critical space systems such as the Space Shuttle or the Space Station.

  6. The application of lidar in detecting space debris

    NASA Astrophysics Data System (ADS)

    Wang, Yang; Wang, Qianqian

    2008-12-01

    The accumulation of space debris is expected to present an increasing threat to orbital aerostat. To develop and use space resource continually and in security the detecting technology for space debris has to be improved. The paper firstly introduces the concept of space debris and their common detection means, and then introduces the application of lidar in detecting the space debris. Comparing with conventional optical observation systems lidar adopts active detecting mode, without the limitation of illumination and with a long detecting distance. It also can measure range and speed of targets. Comparing with microwave radar the beam of lidar is narrow and it has great orientation precision and resolving power. To satisfy detecting small-sized debris in long distance and big area the paper proposes the composite method to detect the space debris which uses millimeter wave radar and optic equipment. It firstly uses millimeter wave with long distance and big view field to confirm the position of debris in long distance. And then it uses optical system with high resolving and anti-jamming power for accurate orientation and identification. It also measure the distance, angle and speed exactly of debris. The study in theory indicates this composite method can complete the detecting and orientation and achieve the distance, angle and speed of the space debris more than 10cm range beyond 150km.

  7. Space Shuttle Solid Rocket Booster Debris Assessment

    NASA Technical Reports Server (NTRS)

    Kendall, Kristin; Kanner, Howard; Yu, Weiping

    2006-01-01

    The Space Shuttle Columbia Accident revealed a fundamental problem of the Space Shuttle Program regarding debris. Prior to the tragedy, the Space Shuttle requirement stated that no debris should be liberated that would jeopardize the flight crew and/or mission success. When the accident investigation determined that a large piece of foam debris was the primary cause of the loss of the shuttle and crew, it became apparent that the risk and scope of - damage that could be caused by certain types of debris, especially - ice and foam, were not fully understood. There was no clear understanding of the materials that could become debris, the path the debris might take during flight, the structures the debris might impact or the damage the impact might cause. In addition to supporting the primary NASA and USA goal of returning the Space Shuttle to flight by understanding the SRB debris environment and capability to withstand that environment, the SRB debris assessment project was divided into four primary tasks that were required to be completed to support the RTF goal. These tasks were (1) debris environment definition, (2) impact testing, (3) model correlation and (4) hardware evaluation. Additionally, the project aligned with USA's corporate goals of safety, customer satisfaction, professional development and fiscal accountability.

  8. Recent Developments in Space Debris Mitigation Policy and Practices

    NASA Technical Reports Server (NTRS)

    Johnson, Nicholas L.

    2006-01-01

    In recent years, emphasis has shifted from national efforts to control the space debris population to international ones. Here, too, great progress has been made, most notably by the Inter-Agency Space Debris Coordination Committee (IADC) and the Committee on the Peaceful Uses of Outer Space (COPUOS) of the United Nations. Today, a firm international consensus is rapidly building on the principal space debris mitigation measures. The IADC is an association of the space agencies of ten countries (China, France, Germany, India, Italy, Japan, Russia, Ukraine, the United Kingdom, and the United States) and the European Space Agency, representing 17 countries of which four (France, Germany, Italy, and the United Kingdom) are also full IADC members. At the 17th meeting of the IADC in October 1999, a new Action Item (AI 17.2) was adopted to develop a set of consensus space debris mitigation guidelines. The purpose of the activity was to identify the most valuable space debris mitigation measures and to reach an international agreement on common directives. The IADC Space Debris Mitigation Guidelines (www.iadc-online.org/index.cgi?item=docs_pub) were formally adopted in October 2002 during the Second World Space Congress in Houston, Texas. Two years later a companion document, entitled Support to the IADC Space Debris Mitigation Guidelines, was completed to provide background and clarification for the guidelines.

  9. Space debris measurement program at Phillips Laboratory

    NASA Technical Reports Server (NTRS)

    Dao, Phan D.; Mcnutt, Ross T.

    1992-01-01

    Ground-based optical sensing was identified as a technique for measuring space debris complementary to radar in the critical debris size range of 1 to 10 cm. The Phillips Laboratory is building a staring optical sensor for space debris measurement and considering search and track optical measurement at additional sites. The staring sensor is implemented in collaboration with Wright Laboratory using the 2.5 m telescope at Wright Patterson AFB, Dayton, Ohio. The search and track sensor is designed to detect and track orbital debris in tasked orbits. A progress report and a discussion of sensor performance and search and track strategies will be given.

  10. Development of the Space Debris Sensor (SDS)

    NASA Technical Reports Server (NTRS)

    Hamilton, Joe; Liou, J. -C.; Anz-Meador, P.; Matney, M.; Christiansen, E.

    2017-01-01

    Debris Resistive/Acoustic Grid Orbital Navy-NASA Sensor (DRAGONS) is an impact sensor designed to detect and characterize collisions with small orbital debris: from 50 microns to greater than 1millimeter debris size detection; Characterizes debris size, speed, direction, and density. The Space Debris Sensor (SDS) is a flight demonstration of DRAGONS on the International Space Station: Approximately 1 square meter of detection area facing the ISS velocity vector; Minimum two year mission on Columbus External Payloads Facility (EPF); Minimal obstruction from ISS hardware; Development is nearing final checkout and integration with the ISS; Current launch schedule is SpaceX13, about September 2017, or SpaceX14, about Jan 2018.

  11. Active Debris Removal Using Modified Launch Vehicle Upper Stages

    NASA Astrophysics Data System (ADS)

    Nasseri, S. Ali; Emanuelli, Matteo; Raval, Siddharth; Turconi, Andrea

    2013-09-01

    During the past few years, several research programs have assessed the current state and future evolution of space debris in the Low Earth Orbit region. These studies indicate that space debris density could reach a critical level such that there will be a continuous increase in the number of debris objects, primarily driven by debris-debris collision activity known as the Kessler effect. These studies also highlight the urgency for active debris removal.An Active Debris Removal System (ADRS) is capable of approaching the debris object through a close-range rendezvous, stabilizing its attitude, establishing physical contact, and finally de-orbiting the debris object. The de-orbiting phase could be powered by propulsion systems such as chemical rockets or electrodynamic tether (EDT) systems.The aim of this project is to model and evaluate a debris removal mission in which an adapted rocket upper stage, equipped with an electrodynamic tether (EDT) system, is employed for de-orbiting a debris object. This ADRS package is installed initially as part of a launch vehicle on a normal satellite deployment mission, and a far-approach manoeuvre will be required to align the ADRS' orbit with that of the target debris. We begin by selecting a suitable target debris and launch vehicle, and then proceed with modelling the entire debris removal mission from launch to de-orbiting of the target debris object using Analytical Graphic Inc.'s Systems Tool Kit (STK).

  12. Development of the Space Debris Sensor (SDS)

    NASA Technical Reports Server (NTRS)

    Hamilton, J.; Liou, J.-C.; Anz-Meador, P. D.; Corsaro, B.; Giovane, F.; Matney, M.; Christiansen, E.

    2017-01-01

    The Space Debris Sensor (SDS) is a NASA experiment scheduled to fly aboard the International Space Station (ISS) starting in 2018. The SDS is the first flight demonstration of the Debris Resistive/Acoustic Grid Orbital NASA-Navy Sensor (DRAGONS) developed and matured at NASA Johnson Space Center's Orbital Debris Program Office. The DRAGONS concept combines several technologies to characterize the size, speed, direction, and density of small impacting objects. With a minimum two-year operational lifetime, SDS is anticipated to collect statistically significant information on orbital debris ranging from 50 microns to 500 microns in size. This paper describes the features of SDS and how data from the ISS mission may be used to update debris environment models. Results of hypervelocity impact testing during the development of SDS and the potential for improvement on future sensors at higher altitudes will be reviewed.

  13. Space debris: Assessing risk and responsibility

    NASA Astrophysics Data System (ADS)

    Bradley, Andrew M.; Wein, Lawrence M.

    2009-05-01

    We model the orbital debris environment by a set of differential equations with parameter values that capture many of the complexities of existing three-dimensional simulation models. We compute the probability that a spacecraft gets destroyed in a collision during its operational lifetime, and then define the sustainable risk level as the maximum of this probability over all future time. Focusing on the 900- to 1000-km altitude region, which is the most congested portion of low Earth orbit, we find that - despite the initial rise in the level of fragments - the sustainable risk remains below 10-3 if there is high (>98%) compliance to the existing 25-year postmission deorbiting guideline. We quantify the damage (via the number of future destroyed operational spacecraft) generated by past and future space activities. We estimate that the 2007 FengYun 1C antisatellite weapon test represents ≈1% of the legacy damage due to space objects having a characteristic size of ⩾10 cm, and causes the same damage as failing to deorbit 2.6 spacecraft after their operational life. Although the political and economic issues are daunting, these damage estimates can be used to help determine one-time legacy fees and fees on future activities (including deorbit noncompliance), which can deter future debris generation, compensate operational spacecraft that are destroyed in future collisions, and partially fund research and development into space debris mitigation technologies. Our results need to be confirmed with a high-fidelity three-dimensional model before they can provide the basis for any major decisions made by the space community.

  14. Reflectance Spectra of Space Debris in GEO

    NASA Astrophysics Data System (ADS)

    Schildknecht, T.; Vannanti, A.; Krag, H.; Erd, C.

    The space debris environment in the Geostationary Earth Orbit (GEO) region is mostly investigated by means of optical surveys. Such surveys revealed a considerable amount of debris in the size range of 10 centimeter to one meter. Some of these debris exhibit particularly high area-to-mass ratios as derived from the evolution of their orbits. In order to understand the nature and eventually the origin of these objects, observations allowing to derive physical characteristics like size, shape and material are required. Information on the shape and the attitude motion of a debris piece may be obtained by photometric light curves. The most promising technique to investigate the surface material properties is reflectance spectroscopy. This paper discusses preliminary results obtained from spectrometric observations of space debris in GEO. The observations were acquired at the 1-meter ESA Space Debris Telescope (ESASDT) on Tenerife with a low-resolution spectrograph in the wavelength range of 450-960 nm. The target objects were space debris of different types with brightness as small as magnitude 15. Some simple-shaped, intact "calibration objects" with known surface materials like the MSG-2 satellites were also observed. The spectra show shape variations expected to be caused by the different physical properties of the objects. The determination of the possible materials is still in a preliminary phase. Limitations of the acquisition process of the spectra and the subsequent analysis are discussed. Future steps planned for a better characterization of the debris from the observed data are briefly outlined.

  15. An adaptive strategy for active debris removal

    NASA Astrophysics Data System (ADS)

    White, Adam E.; Lewis, Hugh G.

    2014-04-01

    Many parameters influence the evolution of the near-Earth debris population, including launch, solar, explosion and mitigation activities, as well as other future uncertainties such as advances in space technology or changes in social and economic drivers that effect the utilisation of space activities. These factors lead to uncertainty in the long-term debris population. This uncertainty makes it difficult to identify potential remediation strategies, involving active debris removal (ADR), that will perform effectively in all possible future cases. Strategies that cannot perform effectively, because of this uncertainty, risk either not achieving their intended purpose, or becoming a hindrance to the efforts of spacecraft manufactures and operators to address the challenges posed by space debris. One method to tackle this uncertainty is to create a strategy that can adapt and respond to the space debris population. This work explores the concept of an adaptive strategy, in terms of the number of objects required to be removed by ADR, to prevent the low Earth orbit (LEO) debris population from growing in size. This was demonstrated by utilising the University of Southampton’s Debris Analysis and Monitoring Architecture to the Geosynchronous Environment (DAMAGE) tool to investigate ADR rates (number of removals per year) that change over time in response to the current space environment, with the requirement of achieving zero growth of the LEO population. DAMAGE was used to generate multiple Monte Carlo projections of the future LEO debris environment. Within each future projection, the debris removal rate was derived at five-year intervals, by a new statistical debris evolutionary model called the Computational Adaptive Strategy to Control Accurately the Debris Environment (CASCADE) model. CASCADE predicted the long-term evolution of the current DAMAGE population with a variety of different ADR rates in order to identify a removal rate that produced a zero net

  16. A Comparison of ESA and NASA Space Debris Models

    NASA Astrophysics Data System (ADS)

    Hauptmann, S.

    1996-12-01

    NASA recently developed a new orbital debris environment model for spacecraft design and observations in low earth orbit. This model has been implemented at ESA/ESTEC in an application which is able to assess debris flux distributions according to target and impactor orbital parameters as well as the directional dependencies of the impactor fluxes. In this paper, the following three models are compared: the above mentioned NASA model, the ESA MASTER Analyst Application, developed under ESA/ESOC contract in 1995 and the current NASA space debris reference model, which was developed in 1989. The conceptual designs of the three models are discussed and their quantitative predictions are compared for various target orbit characteristics, including more detailed analysis of the orbits of ERS-1, LDEF and ISSA (International Space Station Alpha). It is shown in particular that considerable discrepancies of more than one order of magnitude exist between the predictions of the different models in the region of sub-mm sized particles as well as for diameters greater than 1cm. Refined predictions of the debris flux given by the different models taking into account the orientation of the surface are investigated in the case of LDEF and ISSA. For further information on ESA and NASA space debris modelling activities have a look at the following sites:

    • Space Debris Activities at ESOC
    • Modelling the Space Environment at ESTEC
    • UNO Office of Outer Space Affairs
    • NASA-JSC Space Science Branch

  17. Space debris removal system using a small satellite

    NASA Astrophysics Data System (ADS)

    Nishida, Shin-Ichiro; Kawamoto, Satomi; Okawa, Yasushi; Terui, Fuyuto; Kitamura, Shoji

    2009-07-01

    Since the number of satellites in Earth orbit is steadily increasing, space debris will eventually pose a serious problem to near-Earth space activities if left unchecked, and so effective measures to mitigate it are becoming urgent. Equipping new satellites with an end-of-life de-orbit or orbital lifetime reduction capability could be an effective means of reducing the amount of debris by reducing the probability of the collisions between objects. On the other hand, the active removal of space debris and the retrieval of failed satellites by spacecraft are other possible measures. The Institute of Aerospace Technology, Japan Aerospace Exploration Agency (JAXA), is studying a micro-satellite system for active space debris removal, and is examining the applicability of electro-dynamic tether (EDT) technology as its high efficiency orbital transfer system. A small EDT package provides a possible means for lowering the orbits of objects without the need for propellant. Capture is indispensable for the retrieval of large space debris objects, and we propose a flexible robot arm for this purpose. This paper discusses a space debris removal satellite system and describes the development status of prototypes of the EDT package and a new robot arm for capturing non-cooperative targets.

  18. The Economics of the Control of the Space Debris Environment

    NASA Astrophysics Data System (ADS)

    Wiedemann, Carsten; Flegel, Sven; Mockel, Marek; Gelhaus, Johannes; Braun, Vitali; Kebschull, Christopher; Kreisel, Jorg; Metz, Manuel; Vorsmann, Peter

    2013-08-01

    It is investigated whether cost estimation can be used as an instrument to support the selection of suitable space debris mitigation or remediation measures. Several long-term simulations of the evolution of the future space debris environment are combined with cost estimation. The costs of damages to satellites are compared to the costs of measures like post mission disposal (PMD) and active debris removal (ADR). As a parameter variation the damage costs are estimated based on two different approaches. It is shown that the cost estimations are in a reasonable order of magnitude which allows cost-benefit comparisons for different scenarios.

  19. Analyzing costs of space debris mitigation methods

    NASA Astrophysics Data System (ADS)

    Wiedemann, C.; Krag, H.; Bendisch, J.; Sdunnus, H.

    The steadily increasing number of space objects poses a considerable hazard to all kinds of spacecraft. To reduce the risks to future space missions different debris mitigation measures and spacecraft protection techniques have been investigated during the last years. However, the economic efficiency has not been considered yet in this context. This economical background is not always clear to satellite operators and the space industry. Current studies have the objective to evaluate the mission costs due to space debris in a business as usual (no mitigation) scenario compared to the missions costs considering debris mitigation. The aim i an estimation of thes time until the investment in debris mitigation will lead to an effective reduction of mission costs. This paper presents the results of investigations on the key problems of cost estimation for spacecraft and the influence of debris mitigation and shielding on cost. The shielding of a satellite can be an effective method to protect the spacecraft against debris impact. Mitigation strategies like the reduction of orbital lifetime and de- or re-orbit of non-operational satellites are methods to control the space debris environment. These methods result in an increase of costs. In a first step the overall costs of different types of unmanned satellites are analyzed. The key problem is, that it is not possible to provide a simple cost model that can be applied to all types of satellites. Unmanned spacecraft differ very much in mission, complexity of design, payload and operational lifetime. It is important to classify relevant cost parameters and investigate their influence on the respective mission. The theory of empirical cost estimation and existing cost models are discussed. A selected cost model is simplified and generalized for an application on all operational satellites. In a next step the influence of space debris on cost is treated, if the implementation of mitigation strategies is considered.

  20. Development of high precision laser measurement to Space Debris and Applications in SHAO

    NASA Astrophysics Data System (ADS)

    Zhang, Zhongping; Chen, Juping; Xiong, Yaoheng; Han, Xingwei

    2016-07-01

    Artificial space debris has become the focus during the space exploration because of producing the damage for the future active spacecrafts and high precision measurement for space debris are required for debris surveillance and collision avoidance. Laser ranging technology is inherently high accurate and will play an important role in precise orbit determination, accurate catalog of space debris. Shanghai Astronomical Observatory (SHAO) of CAS, has been developing the technology of laser measurement to space debris for several years. According to characteristics of laser echoes from space debris and the experiences of relevant activities, high repetition rate, high power laser system and low dark noise APD detector with high quantum efficiency and high transmissivity of narrow bandwidth spectral filter are applied to laser measurement to space debris in SHAO. With these configurations, great achievements of laser measurement to space debris are made with hundreds of passes of laser data from space debris in the distance between 500km and 2500km with Radar Cross Section (RCS) of more than 10 m^{2} to less than 0.5m^{2} at the measuring precision of less than 1m (RMS). For better application of laser ranging technology, Chinese Space Debris Observation network, consisting of Shanghai, Changchun and Kunming station, has been preliminary developed and the coordinated observation has been performed to increase the measuring efficiency for space debris. It is referred from data that laser ranging technology can be as the essential high accuracy measurement technology in the study of space debris.

  1. Optical Detection of Space Debris Using a Large Achromatic Coronagraph

    DTIC Science & Technology

    1988-01-01

    34Exploter 46 Meteoroid Bumper Experiment: Earth orbital debris interpretation", in "Properties and Interactions of Interplanetary Dust", Astrophy- sics and...communication, 9th Sacramento Peak Workshop on Coronal Structure, 17-21th August. Su, S. Y.: 1986, " Orbital Debris Environement resulting from Future Activities...in Space", Adv. Sp. Res., 6, 7, 109. Taff, L. G., Jonuskis, D. M.: 1986, "Results and Analysis of a bi-telescopic Sur- vey of low Altitude Orbital

  2. Space Debris Alert System for Aviation

    NASA Astrophysics Data System (ADS)

    Sgobba, Tommaso

    2013-09-01

    Despite increasing efforts to accurately predict space debris re-entry, the exact time and location of re-entry is still very uncertain. Partially, this is due to a skipping effect uncontrolled spacecraft may experience as they enter the atmosphere at a shallow angle. Such effect difficult to model depends on atmospheric variations of density. When the bouncing off ends and atmospheric re-entry starts, the trajectory and the overall location of surviving fragments can be precisely predicted but the time to impact with ground, or to reach the airspace, becomes very short.Different is the case of a functional space system performing controlled re-entry. Suitable forecasts methods are available to clear air and maritime traffic from hazard areas (so-called traffic segregation).In US, following the Space Shuttle Columbia accident in 2003, a re-entry hazard areas location forecast system was putted in place for the specific case of major malfunction of a Reusable Launch Vehicles (RLV) at re-entry. The Shuttle Hazard Area to Aircraft Calculator (SHAAC) is a system based on ground equipment and software analyses and prediction tools, which require trained personnel and close coordination between the organization responsible for RLV operation (NASA for Shuttle) and the Federal Aviation Administration. The system very much relies on the operator's capability to determine that a major malfunction has occurred.This paper presents a US pending patent by the European Space Agency, which consists of a "smart fragment" using a GPS localizer together with pre- computed debris footprint area and direct broadcasting of such hazard areas.The risk for aviation from falling debris is very remote but catastrophic. Suspending flight over vast swath of airspace for every re-entering spacecraft or rocket upper stage, which is a weekly occurrence, would be extremely costly and disruptive.The Re-entry Direct Broadcasting Alert System (R- DBAS) is an original merging and evolution of the Re

  3. Overview of the space debris environment

    NASA Astrophysics Data System (ADS)

    Meshishnek, M. J.

    1995-03-01

    There is a component of the space environment that is man-made pollution, termed 'space debris' it exists at all inclinations and, primarily, at altitudes of roughly 350 km to 2000 km. The size of this debris ranges from several meters to a fraction of a micrometer in diameter, and the particle distribution follows an inverse power law, with the smaller size component far exceeding that of the larger. Debris is composed primarily of alumina from solid rocket motor exhausts, aluminum from spacecraft structures, and zinc and titanium oxides from thermal control coatings. The accepted model of the space debris environment is that of Kessler et al., a complex model that predicts the number of particles that will impact a surface as a function of altitude, inclination, solar cycle, and particle diameter, as well as their collision velocities. Recent data from LDEF has demonstrated both the accuracy and shortcomings of the Kessler model. Measured debris impactor fluxes are in good agreement with the model for ram surfaces. However, predictions of the model for other surfaces of a spacecraft are less accurate, most notably for the wake or trailing side. While the Kessler model is appropriate for long-term, average flux predictions, spatial-temporal impact fluxes measured on LDEF dramatically illustrated the presence of strong debris clouds that do not dissipate quickly in space and will encounter an orbiting spacecraft cyclically and repeatedly over its lifetime. LDEF data has also indicated the presence of debris in elliptical orbits, a fact not predicted by the Kessler model. This fact is responsible for the discrepancy between measured impact fluxes and predictions on trailing edge surfaces.

  4. Instability of the Current Space Debris Population in Low Earth Orbit

    NASA Astrophysics Data System (ADS)

    Maniwa, Kazuaki; Hanada, Toshiya; Kawamoto, Satomi

    Since the launch of Sputnik, orbital debris population continues to increase due to ongoing space activities, on-orbit explosions, and accidental collisions. In the future, it is expected that a great deal of fragments will be created by explosions and collisions. Thus, the number of space debris may increase exponentially (Kessler Syndrome). This paper analyzes the Kessler Syndrome using the Low Earth Orbital Debris Environmental Evolutionary Model (LEODEEM) developed at Kyushu University with collaboration from JAXA. The purpose of the study aims at understanding the issues related to space environment conservation. The results provide effective conditions of Active Debris Removal which is one of the space debris mitigation procedures.

  5. ICAN: A novel laser architecture for space debris removal

    NASA Astrophysics Data System (ADS)

    Soulard, Rémi; Quinn, Mark N.; Tajima, Toshiki; Mourou, Gérard

    2014-12-01

    The development of a fiber based laser architecture will enable novel applications in environments which have hitherto been impossible due to size, efficiency and power of traditional systems. Such a new architecture has been developed by the International Coherent Amplification Network (ICAN) project. Here we present an analysis of utilizing an ICAN laser for the purpose of tracking and de-orbiting hyper-velocity space debris. With an increasing number of new debris from collisions of active, derelict and new payloads in orbit, there is a growing danger of runaway debris impacts. Due to its compactness and efficiency, it is shown that space-based operation would be possible. For different design parameters such as fiber array size, it is shown that the kHz repetition rate and kW average power of ICAN would be sufficient to de-orbit small 1-10 cm debris within a single instance via laser ablation.

  6. From Asteroids to Space Debris

    NASA Astrophysics Data System (ADS)

    Benkhaldoun, Zouhair; Moon, Hong-Kyu; Daassou, Ahmed; Park, Jang-Hyun; Lazrek, Mohamed

    2016-01-01

    Since 2011, Oukaimeden Observatory (OUCA) has become one of the active NEO search facilities in the word. Its discovery statistics shows that the MOSS (Morocco Oukaimeden Sky Survey) project received credits for more than 2,145 new designations, including 3 NEOs and 4 comets. Its excellent astro-climactic characteristics are partly behind the success. The average number of observable nights is around 280 nights per year, while median seeing is 0.8-0.9 arcsec. We completed construction of a new telescope at the site in March 2015. It is Optical Wide-field Patrol (OWL) facility designed and built by Korea Space Science Institute (KASI). The primary objective of this facility is to monitor national space assets of Korea; either wide-field imaging- or fast data acquisition- capabilities enable the 0.5m telescope to conduct observation programs to catalog and follow-up various transient events in the night sky. We present the seeing condition, the OWL system and preliminary results obtained at OWL@Oukaimeden during the past several months.

  7. Orbital debris research at NASA Johnson Space Center, 1986-1988

    NASA Technical Reports Server (NTRS)

    Reynolds, Robert C.; Potter, Andrew E., Jr.

    1989-01-01

    Research on orbital debris has intensified in recent years as the number of debris objects in orbit has grown. The population of small debris has now reached the level that orbital debris has become an important design factor for the Space Station. The most active center of research in this field has been the NASA Lyndon B. Johnson Space Center. Work is being done on the measurement of orbital debris, development of models of the debris population, and development of improved shielding against hypervelocity impacts. Significant advances have been made in these areas. The purpose of this document is to summarize these results and provide references for further study.

  8. Rates inferred from the space debris catalog

    SciTech Connect

    Canavan, G.H.

    1996-08-01

    Collision and fragmentation rates are inferred from the AFSPC space debris catalog and compare with estimates from other treatments. The collision rate is evaluated without approximation. The fragmentation rate requires additional empirical assessments. The number of fragments per collision is low compared to analytic and numerical treatments, is peaked low, and falls rapidly with altitude.

  9. An Assessment of the Current LEO Debris Environment and the Need for Active Debris Removal

    NASA Technical Reports Server (NTRS)

    Liou, Jer-Chyi

    2010-01-01

    The anti-satellite test on the Fengun-1 C weather satellite in early 2007 and the collision between Iridium 33 and Cosmos 2251 in 2009 dramatically altered the landscape of the human-made orbital debris environment in the low Earth orbit (LEO). The two events generated approximately 5500 fragments large enough to be tracked by the U.S. Space Surveillance Network. Those fragments account for more than 60% increase to the debris population in LEO. However, even before the ASAT test, model analyses already indicated that the debris population (for those larger than 10 cm) in LEO had reached a point where the population would continue to increase, due to collisions among existing objects, even without any future launches. The conclusion implies that as satellites continue to be launched and unexpected breakup events continue to occur, commonly-adopted mitigation measures will not be able to stop the collision-driven population growth. To remediate the debris environment in LEO, active debris removal must be considered. This presentation will provide an updated assessment of the debris environment after the Iridium 33/Cosmos 2251 collision, an analysis of several future environment projections based on different scenarios, and a projection of collision activities in LEO in the near future. The need to use active debris removal to stabilize future debris environment will be demonstrated and the effectiveness of various active debris removal strategies will be quantified.

  10. Laser Remote Maneuver of Space Debris at the Space Environment Research Center

    NASA Astrophysics Data System (ADS)

    Bold, M.

    2016-09-01

    Active satellites have the ability to maneuver to avoid collision with other space objects. Unfortunately the majority of objects in space are debris objects that do not have the ability to maneuver. In the future the population of debris objects will grow and the probability of collision will increase. This paper will provide details on plans to use a ground based laser with uplink adaptive optics compensation to apply photon pressure to debris objects and maneuver them out of harm's way. This work is ongoing at the Space Environment Research Centre at Mt. Stromlo Australia with collaborative efforts from Lockheed Martin, Electro-Optics Systems Inc. and the Australian National University.

  11. Laser remote maneuver of space debris at the Space Environment Research Centre

    NASA Astrophysics Data System (ADS)

    Bold, Matthew M.

    2016-09-01

    Active satellites have the ability to maneuver to avoid collision with other space objects. Unfortunately the majority of objects in space are debris objects that do not have the ability to maneuver. In the future the population of debris objects will grow and the probability of collision will increase. This paper will provide details on plans to use a ground based laser with uplink adaptive optics compensation to apply photon pressure to debris objects and maneuver them out of harm's way. This work is ongoing at the Space Environment Research Centre at Mt. Stromlo Australia with collaborative efforts from Lockheed Martin, Electro-Optics Systems Inc. and the Australian National University.

  12. Charging of space debris in the LEO and GEO regions

    NASA Astrophysics Data System (ADS)

    Sen, Abhijit; Tiwari, Sanat Kumar

    The near exponential rise of space debris at the satellite orbital altitudes (particularly in the low earth orbit (LEO) region) and the risk they pose for space assets is a source of major concern for all nations engaged in space activities. Considerable efforts are therefore being expended into accurate modeling and tracking of these objects and various ideas for the safe removal of these debris are being explored. The debris objects are likely to acquire a large amount of charge since they are typically found in a plasma environment - such as the earth’s ionospheric plasma in the LEO region (100 kms to 1000 kms) and the radiation belts in the geosynchronous orbit (GEO) region. The consequent flow of electron and ion currents on them lead to the accumulation of a large amount of surface charge and the development of a surface potential on these objects. The influence of the plasma environment on the dynamics and charging of the debris is a relatively unexplored area of Space Situational Awareness (SSA) and Space Debris (SD) research and can be potentially important for the accurate prediction of the long-term evolution of debris orbits and their collision probabilities with other space objects. In this paper we will report on the charging of space debris under a variety of orbital conditions in the LEO and GEO regions using both analytic and particle-in-cell (PIC) modeling. The analytic estimates are obtained using refined Orbit Motion Limited (OML) modeling while the simulation studies are carried out using the SPIS code [1]. In the GEO region account is taken of charging due to photoemission processes as well as energetic beam charging. The PIC approach enables us to study charging of irregularly shaped debris objects as well as differential charging on objects that are composed of patches of conducting and insulated regions. The dynamical consequences of the debris charging on their orbital trajectories and rotational characteristics will be discussed. [1] J

  13. Orbiting Debris: a Space Environmental Problem. Background Paper

    NASA Technical Reports Server (NTRS)

    1990-01-01

    Artificial debris, deposited in a multitude of orbits about the Earth as the result of the exploration and use of the space environment, poses a growing hazard to future space operations. Unless nations sharply reduce the amount of orbital debris they produce, future space activites could suffer loss of capability, loss of income, and even loss of life as a result of collisions between spacecraft and debris. This background paper discusses the sources of debris and how they can be greatly reduced.

  14. From Asteroids to Space Debris

    NASA Astrophysics Data System (ADS)

    Benkhaldoun, Zouhair; Moon, Hong-Kyu; Daassou, Ahmed; Jang-Hyun, Park; Lazrek, Mohamed

    2015-08-01

    Since 2011, the Oukaimeden Observatory (OUCA) located on the mountains of the Moroccan High Atlas has become one of the successful contributors in asteroid discovery in the world. The discovery statistics of the MOSS (Morocco Oukaimeden Sky Survey) telescope represents more than 2145 new designations to date for their credits. Its discoveries include three new NEOs and four new comets. The exceptional astro-climatic conditions in terms not only of number of clear nights, but also of atmospheric seeing are partly behind this success. Indeed the average number of observable nights is around 280 nights per year, while the average seeing is about 0.8 to 0.9 arcsec.In the meanwhile, the OUCA achieved construction and installation of a new facility in March 2015. It is a compact, 0.5 m aperture fast optics robotic telescope designed and implemented by the Optical Wide-field Patrol (OWL) team of Korea Astronomy and Space Science Institute (KASI). The primary object of the OWL project is to monitor national space-based assets, howevr either wide-field imaging- or fast data acquisition- capabilities enable to undertake observational program to catalog and follow-up various transient events in the night sky. We will brief future plan for this joint project between the OUCA and KASI.Our presentation aims to share the details of instrumentation implemented and cooperation opportunities it can arouse within the community for the data analysis and interpretation.

  15. Orbiting Space Debris: Dangers, Measurement and Mitigation

    DTIC Science & Technology

    1992-01-01

    objects are released in orbit. One notorious experiment which resulted in a significant amount of debris is known as the Westford Needles Experiment. In...thousands of small metallic needles in order to reflect radio signals.8 These needles were to be 8 Carl Christol, The Modern International Law of Outer...experiment succeeded in deploying the needles . To date Air Force Space Command has cataloged only 170 of these needles .9 They are extremely difficult to

  16. Autonomous space processor for orbital debris

    NASA Technical Reports Server (NTRS)

    Ramohalli, Kumar; Marine, Micky; Colvin, James; Crockett, Richard; Sword, Lee; Putz, Jennifer; Woelfle, Sheri

    1991-01-01

    The development of an Autonomous Space Processor for Orbital Debris (ASPOD) was the goal. The nature of this craft, which will process, in situ, orbital debris using resources available in low Earth orbit (LEO) is explained. The serious problem of orbital debris is briefly described and the nature of the large debris population is outlined. The focus was on the development of a versatile robotic manipulator to augment an existing robotic arm, the incorporation of remote operation of the robotic arms, and the formulation of optimal (time and energy) trajectory planning algorithms for coordinated robotic arms. The mechanical design of the new arm is described in detail. The work envelope is explained showing the flexibility of the new design. Several telemetry communication systems are described which will enable the remote operation of the robotic arms. The trajectory planning algorithms are fully developed for both the time optimal and energy optimal problems. The time optimal problem is solved using phase plane techniques while the energy optimal problem is solved using dynamic programming.

  17. Space Debris Laser Ranging at Graz

    NASA Astrophysics Data System (ADS)

    Kirchner, Georg; Koidl, Franz; Kucharski, Daniel; Ploner, Martin; Riede, Wolfgang; Voelker, Uwe; Buske, Ivo; Friedrich, Fabian; Baur, Oliver; Krauss, Sandro; Wirnsberger, Harald

    2013-08-01

    The Graz Satellite Laser Ranging (SLR) station usually measures distances to retro-reflector equipped satellites with an accuracy of few millimetres, using short laser pulses with 10 ps pulse width, a low energy of 400 μJ, and a repetition rate of 2 kHz. To test laser ranging possibilities to space debris, we installed two stronger lasers (a diode-pumped 25 mJ / 1 kHz / 10 ns / 532 nm laser, exchanged later to a flash lamp pumped 150 mJ / 100 Hz / 3 ns / 532 nm laser) - both on loan from DLR / German Aerospace Centre Stuttgart -, and built lownoise single-photon detection units. With this configuration, we successfully tracked ≈ 100 passes of almost 50 different space debris targets, in distances between 600 km and up to more than 2500 km, with radar cross sections from > 15 m2 down to < 0.3 m2 , and measured their distances with an average accuracy of 0.7 m (10 ns laser) resp. ≈ 0.5 m (3 ns laser) RMS. The resulting data will be used to calculate improved orbits of the tracked debris objects, and to compare them with radar-based TLE (two-line element) orbits. As demonstration experiment, here we provide findings for ENVISAT normal point analysis. As a next step, we plan to additionally taking pointing information into account. Potentially, the joint analysis of both ranges and orientation angles further improves space debris orbit accuracy. Orbit determination and prediction was done with the GEODYN software package. In addition, we successfully tested a 'bi-static' mode: Graz fired laser pulses to ENVISAT; while Graz detected photons reflected from the retro-reflector, the Swiss SLR station Zimmerwald detected the photons diffusely reflected from the satellite body.

  18. Laser space debris removal: now, not later

    NASA Astrophysics Data System (ADS)

    Phipps, Claude R.

    2015-02-01

    Small (1-10cm) debris in low Earth orbit (LEO) are extremely dangerous, because they spread the breakup cascade depicted in the movie "Gravity." Laser-Debris-Removal (LDR) is the only solution that can address both large and small debris. In this paper, we briefly review ground-based LDR, and discuss how a polar location can dramatically increase its effectiveness for the important class of sun-synchronous orbit (SSO) objects. No other solutions address the whole problem of large ( 1000cm, 1 ton) as well as small debris. Physical removal of small debris (by nets, tethers and so on) is impractical because of the energy cost of matching orbits. We also discuss a new proposal which uses a space-based station in low Earth orbit (LEO), and rapid, head-on interaction in 10- 40s rather than 4 minutes, with high-power bursts of 100ps, 355nm pulses from a 1.5m diameter aperture. The orbiting station employs "heat-capacity" laser mode with low duty cycle to create an adaptable, robust, dualmode system which can lower or raise large derelict objects into less dangerous orbits, as well as clear out the small debris in a 400-km thick LEO band. Time-average laser optical power is less than 15kW. The combination of short pulses and UV wavelength gives lower required energy density (fluence) on target as well as higher momentum coupling coefficient. This combination leads to much smaller mirrors and lower average power than the ground-based systems we have considered previously. Our system also permits strong defense of specific assets. Analysis gives an estimated cost of about 1k each to re-enter most small debris in a few months, and about 280k each to raise or lower 1-ton objects by 40km. We believe it can do this for 2,000 such large objects in about four years. Laser ablation is one of the few interactions in nature that propel a distant object without any significant reaction on the source.

  19. Probabilistic Modeling of Space Shuttle Debris Impact

    NASA Technical Reports Server (NTRS)

    Huyse, Luc J.; Asce, M.; Waldhart, Chris J.; Riha, David S.; Larsen, Curtis E.; Gomez, Reynaldo J.; Stuart, Phillip C.

    2007-01-01

    On Feb 1, 2003, the Shuttle Columbia was lost during its return to Earth. As a result of the conclusion that debris impact caused the damage to the left wing of the Columbia Space Shuttle Vehicle (SSV) during ascent, the Columbia Accident Investigation Board recommended that an assessment be performed of the debris environment experienced by the SSV during ascent. A flight rationale based on probabilistic assessment is used for the SSV return-to-flight. The assessment entails identifying all potential debris sources, their probable geometric and aerodynamic characteristics, and their potential for impacting and damaging critical Shuttle components. A probabilistic analysis tool, based on the SwRI-developed NESSUS probabilistic analysis software, predicts the probability of impact and damage to the space shuttle wing leading edge and thermal protection system components. Among other parameters, the likelihood of unacceptable damage depends on the time of release (Mach number of the orbiter) and the divot mass as well as the impact velocity and impact angle. A typical result is visualized in the figures below. Probability of impact and damage, as well as the sensitivities thereof with respect to the distribution assumptions, can be computed and visualized at each point on the orbiter or summarized per wing panel or tile zone.

  20. Space debris hazard to defense systems

    SciTech Connect

    Canavan, G.H.

    1996-05-01

    Natural and man-made debris are argued to present hazards to space systems, but recent data indicate that at low altitudes, the impact rates from small particles may have been overestimated by an order of magnitude. At high altitudes, small particles only present an impact hazard to large satellites; they would not support a cascade. Large particles would apparently produce a cascade only on time scales of centuries or millennia. Radar and optical data should be capable of resolving these uncertainties, but their observations are, as yet, inconsistent. While independent analytic and numerical estimates of collision and cascade rates agree, given consistent inputs, different groups produced significantly different estimates of debris growth rates. This note examines the basis for these discrepancies.

  1. Research on Optical Observation for Space Debris

    NASA Astrophysics Data System (ADS)

    Sun, R. Y.

    2015-01-01

    Space debris has been recognized as a serious danger for operational spacecraft and manned spaceflights. Discussions are made in the methods of high order position precision and high detecting efficiency for space debris, including the design of surveying strategy, the extraction of object centroid, the precise measurement of object positions, the correlation and catalogue technique. To meet the needs of detecting space objects in the GEO (Geosynchronous Orbit), and prevent the saturation of CCD pixels with a long exposure time, a method of stacking a series of short exposure time images is presented. The results demonstrate that the saturation of pixels is eliminated effectively, and the SNR (Signal Noise Ratio) is increased by about 3.2 times, the detection ability is improved by about 2.5 magnitude when 10 seriate images are stacked, and the accuracy is reliable to satisfy the requirement by using the mean plate parameters for the astronomical orientation. A method combined with the geometrical morphology identification and linear correlation is adopted for the data calibration of IADC (Inter-Agency Space Debris Coordination Committee) AI23.4. After calibration, 139 tracklets are acquired, in which 116 tracklets are correlated with the catalogue. The distributions of magnitude, semi-major axis, inclination, and longitude of ascending node are obtained as well. A new method for detecting space debris in images is presented. The algorithm sets the gate around the image of objects, then several criterions are introduced for the object detection, at last the object position in the frame is obtained by the barycenter method and a simple linear transformation. The tests demonstrate that this technique is convenient for application, and the objects in image can be detected with a high centroid precision. In the observations of space objects, the shutter of camera is often removed, and the smear noise is ineluctable. Based on the differences of the geometry between the

  2. Rotating Space Debris Tracking Based on The Orbit-Attitude Coordinated Control

    NASA Astrophysics Data System (ADS)

    Wang, Shuquan; Zhu, Lingchao

    2016-07-01

    This paper investigates the rotating space debris tracking problem. Active capturing and removal of space debris are challenging because the space debris is noncoorperating. The scenario considered is that a rotating space debris is the target to be captured by a spacecraft with a robotic arm. One rough approach is to capture the space debris with a strong arm then detumble the rotation of the whole system using the attitude control system on board. In this way the arm and the spacecraft have to be strong enough to withstand the impact caused by the relative orbital and attitude motions. Another way is to at first track the motion of the characterized surface, which should be easier to capture, of the debris. Then the robotic arm is engaged to capture the debris. In this way, the impact applied on the robotic arm is greatly reduced such that the possibility of causing new debris is also reduced. The orbit-attitude coordinated controller is developed to track the motion of the space debris. The controller is assymptotically stable without considering the boundness of the control efforts. The stability in the situation of bounded control inputs is analyzed. Analytical criterion for a successful tracking is obtained in the situation that rotational motion of the space debris is percession.

  3. Autonomous Space Processor for Orbital Debris (ASPOD)

    NASA Technical Reports Server (NTRS)

    Ramohalli, Kumar; Mitchell, Dominique; Taft, Brett

    1992-01-01

    A project in the Advanced Design Program at the University of Arizona is described. The project is named the Autonomous Space Processor for Orbital Debris (ASPOD) and is a Universities Space Research Association (USRA) sponsored design project. The development of ASPOD and the students' abilities in designing and building a prototype spacecraft are the ultimate goals of this project. This year's focus entailed the development of a secondary robotic arm and end-effector to work in tandem with an existent arm in the removal of orbital debris. The new arm features the introduction of composite materials and a linear drive system, thus producing a light-weight and more accurate prototype. The main characteristic of the end-effector design is that it incorporates all of the motors and gearing internally, thus not subjecting them to the harsh space environment. Furthermore, the arm and the end-effector are automated by a control system with positional feedback. This system is composed of magnetic and optical encoders connected to a 486 PC via two servo-motor controller cards. Programming a series of basic routines and sub-routines allowed the ASPOD prototype to become more autonomous. The new system is expected to perform specified tasks with a positional accuracy of 0.5 cm.

  4. Autonomous Space Processor for Orbital Debris (ASPOD)

    NASA Astrophysics Data System (ADS)

    Ramohalli, Kumar; Mitchell, Dominique; Taft, Brett

    A project in the Advanced Design Program at the University of Arizona is described. The project is named the Autonomous Space Processor for Orbital Debris (ASPOD) and is a Universities Space Research Association (USRA) sponsored design project. The development of ASPOD and the students' abilities in designing and building a prototype spacecraft are the ultimate goals of this project. This year's focus entailed the development of a secondary robotic arm and end-effector to work in tandem with an existent arm in the removal of orbital debris. The new arm features the introduction of composite materials and a linear drive system, thus producing a light-weight and more accurate prototype. The main characteristic of the end-effector design is that it incorporates all of the motors and gearing internally, thus not subjecting them to the harsh space environment. Furthermore, the arm and the end-effector are automated by a control system with positional feedback. This system is composed of magnetic and optical encoders connected to a 486 PC via two servo-motor controller cards. Programming a series of basic routines and sub-routines allowed the ASPOD prototype to become more autonomous. The new system is expected to perform specified tasks with a positional accuracy of 0.5 cm.

  5. RemoveDEBRIS: An in-orbit active debris removal demonstration mission

    NASA Astrophysics Data System (ADS)

    Forshaw, Jason L.; Aglietti, Guglielmo S.; Navarathinam, Nimal; Kadhem, Haval; Salmon, Thierry; Pisseloup, Aurélien; Joffre, Eric; Chabot, Thomas; Retat, Ingo; Axthelm, Robert; Barraclough, Simon; Ratcliffe, Andrew; Bernal, Cesar; Chaumette, François; Pollini, Alexandre; Steyn, Willem H.

    2016-10-01

    Since the beginning of the space era, a significant amount of debris has progressively been generated. Most of the objects launched into space are still orbiting the Earth and today these objects represent a threat as the presence of space debris incurs risk of collision and damage to operational satellites. A credible solution has emerged over the recent years: actively removing debris objects by capturing them and disposing of them. This paper provides an update to the mission baseline and concept of operations of the EC FP7 RemoveDEBRIS mission drawing on the expertise of some of Europe's most prominent space institutions in order to demonstrate key active debris remove (ADR) technologies in a low-cost ambitious manner. The mission will consist of a microsatellite platform (chaser) that ejects 2 CubeSats (targets). These targets will assist with a range of strategically important ADR technology demonstrations including net capture, harpoon capture and vision-based navigation using a standard camera and LiDAR. The chaser will also host a drag sail for orbital lifetime reduction. The mission baseline has been revised to take into account feedback from international and national space policy providers in terms of risk and compliance and a suitable launch option is selected. A launch in 2017 is targeted. The RemoveDEBRIS mission aims to be one of the world's first in-orbit demonstrations of key technologies for active debris removal and is a vital prerequisite to achieving the ultimate goal of a cleaner Earth orbital environment.

  6. The Space Debris Crisis: Time for an International Treaty

    DTIC Science & Technology

    2011-03-23

    1978, Dr. Donald J. Kessler, later Chief of NASA‟s Orbital Debris Program Office, predicted an increase in space debris, beyond a critical tipping...travel at speeds up to 17,500 mph, fast enough for a relatively small piece of orbital debris to damage a satellite or a spacecraft. There are 500,000...while 10 cm objects are likely to cause catastrophic satellite break-ups.”18 NASA Chief Scientist for Orbital Debris Nicholas Johnson observed non

  7. Is It Time for Space Debris Reduction Capabilities?

    DTIC Science & Technology

    2009-04-01

    thrown into a range of orbits of varying altitudes).3 Thus, it appears the space debris problem is increasing. With this increase in orbital debris , we...and geostationary orbit (the fixed point over equator providing widest coverage of Earth).4 Spacecraft and orbital debris travelling in low earth...all orbital debris up to an altitude of 800 km in two years” for about $100 to 200M.98 The team also recommended a technical demonstration study to

  8. Automated image analysis for space debris identification and astrometric measurements

    NASA Astrophysics Data System (ADS)

    Piattoni, Jacopo; Ceruti, Alessandro; Piergentili, Fabrizio

    2014-10-01

    The space debris is a challenging problem for the human activity in the space. Observation campaigns are conducted around the globe to detect and track uncontrolled space objects. One of the main problems in optical observation is obtaining useful information about the debris dynamical state by the images collected. For orbit determination, the most relevant information embedded in optical observation is the precise angular position, which can be evaluated by astrometry procedures, comparing the stars inside the image with star catalogs. This is typically a time consuming process, if done by a human operator, which makes this task impractical when dealing with large amounts of data, in the order of thousands images per night, generated by routinely conducted observations. An automated procedure is investigated in this paper that is capable to recognize the debris track inside a picture, calculate the celestial coordinates of the image's center and use these information to compute the debris angular position in the sky. This procedure has been implemented in a software code, that does not require human interaction and works without any supplemental information besides the image itself, detecting space objects and solving for their angular position without a priori information. The algorithm for object detection was developed inside the research team. For the star field computation, the software code astrometry.net was used and released under GPL v2 license. The complete procedure was validated by an extensive testing, using the images obtained in the observation campaign performed in a joint project between the Italian Space Agency (ASI) and the University of Bologna at the Broglio Space center, Kenya.

  9. Space Transportation System Liftoff Debris Mitigation Process Overview

    NASA Technical Reports Server (NTRS)

    Mitchell, Michael; Riley, Christopher

    2011-01-01

    Liftoff debris is a top risk to the Space Shuttle Vehicle. To manage the Liftoff debris risk, the Space Shuttle Program created a team with in the Propulsion Systems Engineering & Integration Office. The Shutt le Liftoff Debris Team harnesses the Systems Engineering process to i dentify, assess, mitigate, and communicate the Liftoff debris risk. T he Liftoff Debris Team leverages off the technical knowledge and expe rtise of engineering groups across multiple NASA centers to integrate total system solutions. These solutions connect the hardware and ana lyses to identify and characterize debris sources and zones contribut ing to the Liftoff debris risk. The solutions incorporate analyses sp anning: the definition and modeling of natural and induced environmen ts; material characterizations; statistical trending analyses, imager y based trajectory analyses; debris transport analyses, and risk asse ssments. The verification and validation of these analyses are bound by conservative assumptions and anchored by testing and flight data. The Liftoff debris risk mitigation is managed through vigilant collab orative work between the Liftoff Debris Team and Launch Pad Operation s personnel and through the management of requirements, interfaces, r isk documentation, configurations, and technical data. Furthermore, o n day of launch, decision analysis is used to apply the wealth of ana lyses to case specific identified risks. This presentation describes how the Liftoff Debris Team applies Systems Engineering in their proce sses to mitigate risk and improve the safety of the Space Shuttle Veh icle.

  10. Space Debris in the neighborhood of the ISS

    NASA Astrophysics Data System (ADS)

    Sampaio, Jarbas; Vilhena de Moraes, Rodolpho; Celestino, Claudia C.; Fiorilo de Melo, Cristiano

    2016-07-01

    The International Space Station (ISS) is a great opportunity to use a research platform in space. An international partnership of space agencies provides the operation of the ISS since 2000. The ISS is in Low Earth Orbits, in the same region of most of the space debris orbiting the planet. In this way, several studies are important to preserve the operability of the space station and operational artificial satellites, considering the increasing number of distinct objects in the space environment offering collision risks. In this work, the orbital dynamics of space debris are studied in the neighborhood of the ISS - International Space Station. The results show that the collision risk of space debris with the ISS is high and purposes to avoid these events are necessary. Solutions for the space debris mitigation are considered.

  11. In-situ Observations of Space Debris at ESA

    NASA Astrophysics Data System (ADS)

    Drolshagen, G.

    Information on the small size (millimetre or smaller) space debris and meteoroid population in space can only be obtained by in-situ detectors or the analysis of retrieved hardware. Past, ongoing and planned ESA activities in this field are presented. In 1996 the GORID impact detector was launched into a geostationary orbit on-board the Russian Express-2 telecommunication satellite. This impact ionisation detector had a sensor surface of 0.1 m2. Until July 2002 when the spacecraft was shut down it recorded more than 3000 impacts in the micrometre size range. Inter alia, GORID measured numerous clusters of events, believed to result from debris clouds, and indicated that debris fluxes in GEO are larger than predicted by present models. Another in-situ detector, DEBIE-1, was launched in October 2001 and is operating on-board the small technology satellite PROBA in a low polar orbit. It has two sensors, each of 0.01m2 size, pointing in different directions. A second detector of this type, DEBIE-2 with 3 sensors, is ready for flight on the EuTEF carrier (external payload to ISS). The data from GORID and DEBIE-1 are stored on-line in EDID (European Detector Impact Database). Post-flight impact analyses of retrieved hardware provide detailed information on the encountered meteoroid and debris fluxes over a large range of sizes. ESA initiated several analyses in the past ((EURECA, Hubble Space Telescope (HST) solar arrays). The most recent impact analysis was performed for the HST solar arrays retrieved in March 2002. Measured crater sizes in solar cells ranged from about 1 micron to 7 mm. A total of 175 complete penetrations of the 0.7 mm thick arrays were observed. A chemical analysis of impact residues allowed the distinction between space debris and natural meteoroids. Space debris was found to dominate for sizes smaller than 10 microns and larger than about 1 mm. For intermediate sizes impacts are mainly from meteoroids. Results of the analysis and comparisons with

  12. International Space Station: Meteoroid/Orbital Debris Survivability and Vulnerability

    NASA Technical Reports Server (NTRS)

    Graves, Russell

    2000-01-01

    This slide presentation reviews the surviability and vulnerability of the International Space Station (ISS) from the threat posed by meteoroid and orbital debris. The topics include: (1) Space station natural and induced environments (2) Meteoroid and orbital debris threat definition (3) Requirement definition (4) Assessment methods (5) Shield development and (6) Component vulnerability

  13. Orbital Debris: the Growing Threat to Space Operations

    NASA Technical Reports Server (NTRS)

    Johnson, Nicholas L.

    2010-01-01

    For nearly 50 years the amount of man-made debris in Earth orbit steadily grew, accounting for about 95% of all cataloged space objects over the past few decades. The Chinese anti-satellite test in January 2007 and the accidental collision of two spacecraft in February 2009 created more than 4000 new cataloged debris, representing an increase of 40% of the official U.S. Satellite Catalog. The frequency of collision avoidance maneuvers for both human space flight and robotic operations is increasing along with the orbital debris population. However, the principal threat to space operations is driven by the smaller and much more numerous uncataloged debris. Although the U.S. and the international aerospace communities have made significant progress in recognizing the hazards of orbital debris and in reducing or eliminating the potential for the creation of new debris, the future environment is expected to worsen without additional corrective measures.

  14. Space Shuttle Systems Engineering Processes for Liftoff Debris Risk Mitigation

    NASA Technical Reports Server (NTRS)

    Mitchell, Michael; Riley, Christopher

    2011-01-01

    This slide presentation reviews the systems engineering process designed to reduce the risk from debris during Space Shuttle Launching. This process begins the day of launch from the tanking to the vehicle tower clearance. Other debris risks (i.e., Ascent, and micrometeoroid orbital debit) are mentioned) but are not the subject of this presentation. The Liftoff debris systems engineering process and an example of how it works are reviewed (i.e.,STS-119 revealed a bolt liberation trend on the Fixed Service Structure (FSS) 275 level elevator room). The process includes preparation of a Certification of Flight Readiness (CoFR) that includes (1) Lift-off debris from previous mission dispositioned, (2) Flight acceptance rationale has been provided for Lift-off debris sources/causes (3) Lift-off debris mission support documentation, processes and tools are in place for the up-coming mission. The process includes a liftoff debris data collection that occurs after each launch. This includes a post launch walkdown, that records each liftoff debris, and the entry of the debris into a database, it also includes a review of the imagery from the launch, and a review of the instrumentation data. There is also a review of the debris transport analysis process, that includes temporal and spatial framework and a computational fluid dynamics (CFD) analysis. which incorporates a debris transport analyses (DTA), debris materials and impact tests, and impact analyses.

  15. Matched Template Signal Processing for Continuous Wave Laser Tracking of Space Debris

    NASA Astrophysics Data System (ADS)

    Raj, S.; Ward, R.; Roberts, L.; Fleddermann, R.; Francis, S.; McClellend, D.; Shaddock, D.; Smith, C.

    2016-09-01

    The build up of space junk in Earth's orbit space is a growing concern as it shares the same orbit as many currently active satellites. As the number of objects increase in these orbits, the likelihood of collisions between satellites and debris will increase [1]. The eventual goal is to be able to maneuver space debris to avoid such collisions. We at SERC aim to accomplish this by using ground based laser facilities that are already being used to track space debris orbit. One potential method to maneuver space debris is using continuous wave lasers and applying photon pressure on the debris and attempt to change the orbit. However most current laser ranging facilities operates using pulsed lasers where a pulse of light is sent out and the time taken for the pulse to return back to the telescope is measured after being reflected by the target. If space debris maneuvering is carried out with a continuous wave laser then two laser sources need to be used for ranging and maneuvering. The aim of this research is to develop a laser ranging system that is compatible with the continuous wave laser; using the same laser source to simultaneously track and maneuver space debris. We aim to accomplish this by modulating the outgoing laser light with pseudo random noise (PRN) codes, time tagging the outgoing light, and utilising a matched filter at the receiver end to extract the various orbital information of the debris.

  16. Stochastic modeling of hypervelocity impacts in attitude propagation of space debris

    NASA Astrophysics Data System (ADS)

    Sagnières, Luc B. M.; Sharf, Inna

    2017-02-01

    Bombardment of orbital debris and micrometeoroids on active and inoperative satellites is becoming an increasing threat to space operations and has significant consequences on space missions. Concerns with orbital debris have led agencies to start developing debris removal missions and knowing a target's rotational parameters ahead of time is crucial to the eventual success of such a mission. A new method is proposed, enabling the inclusion of hypervelocity impacts into spacecraft attitude propagation models by considering the transfer of angular momentum from collisions as a stochastic jump process. Furthermore, the additional momentum transfer due to ejecta created during these hypervelocity impacts, an effect known as momentum enhancement, is considered. In order to assess the importance of collisions on attitude propagation, the developed model is applied to two pieces of space debris by using impact fluxes from ESA's Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) model.

  17. Development of Harpoon System for Capturing Space Debris

    NASA Astrophysics Data System (ADS)

    Reed, Jame; Barraclough, Simon

    2013-08-01

    Active removal of large space debris has been identified as a key activity to control the growth in the debris population and to limit the risk to active satellites. Astrium is developing technologies to enable such a mission, including a harpoon capture system. The harpoon is simple, compact and lightweight. Since the capture is fast (typically <0.5s) it is relatively insensitive to the dynamic state of the target and orbital dynamics, simplifying the mission design. The harpoon system is designed to attach to the target whilst also minimising damage. The harpoon consists of a set of barbs to robustly hold the target, a crushable section to absorb excess impact energy, and a tether to connect to the chaser vehicle. The baseline firing system uses compressed gas, although a simpler one-shot system has also been designed. To understand how a harpoon could be applicable to active debris removal an on-ground prototype and test-rig has been developed for trials with real structural elements of satellites and rocket bodies. Testing has demonstrated the feasibility of the concept and this paper describes the results as well as the next steps. A number of design variants are also proposed which could simplify the system design of an ADR mission.

  18. Space Debris and the Cost of Space Operations

    NASA Astrophysics Data System (ADS)

    Ailor, William; Womack, James; Peterson, Glenn; Murrell, Elisha

    2010-09-01

    The increased costs due to space debris of maintaining satellite constellations in sun-synchronous orbits at 850 km from 2010 to 2030 were examined for 1) a small constellation of government-owned satellites, 2) a medium-sized constellation of commercial satellites, and 3) large constellation of commercial satellites. Impacts of debris of 1mm diameter were assumed to degrade solar panel performance, 1cm objects damaged solar panels or terminated the satellite, and impact of a 10cm or larger object would terminate the satellite’s operation. Flux density projections were used to estimate the number of times a satellite would be impacted by objects of each size. The study determined the number of launches required to maintain each constellation for the 20-year period. The cost of maintaining the constellations increased by between 5%(government) and 26%(large commercial).

  19. Object Recognition Method of Space Debris Tracking Image Sequence

    NASA Astrophysics Data System (ADS)

    Chen, Zhang; Yi-ding, Ping

    2016-07-01

    In order to strengthen the capability of space debris detection, the automated optical observation becomes more and more popular. Thus, the fully unattended automatic object recognition is urgently needed to study. As the open-loop tracking, which guides the telescope only with the historical orbital elements, is a simple and robust way to track space debris, based on the analysis on the point distribution characteristics of object's open-loop tracking image sequence in the pixel space, this paper has proposed to use the cluster identification method for the automatic space debris recognition, and made a comparison on the three kinds of different algorithms.

  20. Space Shuttle Main Engine Debris Testing Methodology and Impact Tolerances

    NASA Technical Reports Server (NTRS)

    Gradl, Paul R.; Stephens, Walter

    2005-01-01

    In the wake of the Space Shuttle Columbia disaster every effort is being made to determine the susceptibility of Space Shuttle elements to debris impacts. Ice and frost debris is formed around the aft heat shield closure of the orbiter and liquid hydrogen feedlines. This debris has been observed to liberate upon lift-off of the shuttle and presents potentially dangerous conditions to the Space Shuttle Main Engine. This paper describes the testing done to determine the impact tolerance of the Space Shuttle Main Engine nozzle coolant tubes to ice strikes originating from the launch pad or other parts of the shuttle.

  1. Operational Impact of Improved Space Tracking on Collision Avoidance in the Future LEO Space Debris Environment

    NASA Astrophysics Data System (ADS)

    Sibert, D.; Borgeson, D.; Peterson, G.; Jenkin, A.; Sorge, M.

    2010-09-01

    Even if global space policy successfully curtails on orbit explosions and ASAT demonstrations, studies indicate that the number of debris objects in Low Earth Orbit (LEO) will continue to grow solely from debris on debris collisions and debris generated from new launches. This study examines the threat posed by this growing space debris population over the next 30 years and how improvements in our space tracking capabilities can reduce the number of Collision Avoidance (COLA) maneuvers required keep the risk of operational satellite loss within tolerable limits. Particular focus is given to satellites operated by the Department of Defense (DoD) and Intelligence Community (IC) in Low Earth Orbit (LEO). The following debris field and space tracking performance parameters were varied parametrically in the experiment to study the impact on the number of collision avoidance maneuvers required: - Debris Field Density (by year 2009, 2019, 2029, and 2039) - Quality of Track Update (starting 1 sigma error ellipsoid) - Future Propagator Accuracy (error ellipsoid growth rates - Special Perturbations in 3 axes) - Track Update Rate for Debris (stochastic) - Track Update Rate for Payloads (stochastic) Baseline values matching present day tracking performance for quality of track update, propagator accuracy, and track update rate were derived by analyzing updates to the unclassified Satellite Catalog (SatCat). Track update rates varied significantly for active payloads and debris and as such we used different models for the track update rates for military payloads and debris. The analysis was conducted using the System Effectiveness Analysis Simulation (SEAS) an agent based model developed by the United States Air Force Space Command’s Space and Missile Systems Center to evaluate the military utility of space systems. The future debris field was modeled by The Aerospace Corporation using a tool chain which models the growth of the 10cm+ debris field using high fidelity

  2. High Energy Laser for Space Debris Removal

    SciTech Connect

    Barty, C; Caird, J; Erlandson, A; Beach, R; Rubenchik, A

    2009-10-30

    The National Ignition Facility (NIF) and Photon Science Directorate at Lawrence Livermore National Laboratory (LLNL) has substantial relevant experience in the construction of high energy lasers, and more recently in the development of advanced high average power solid state lasers. We are currently developing new concepts for advanced solid state laser drivers for the Laser Inertial Fusion Energy (LIFE) application, and other high average power laser applications that could become central technologies for use in space debris removal. The debris population most readily addressed by our laser technology is that of 0.1-10 cm sized debris in low earth orbit (LEO). In this application, a ground based laser system would engage an orbiting target and slow it down by ablating material from its surface which leads to reentry into the atmosphere, as proposed by NASA's ORION Project. The ORION concept of operations (CONOPS) is also described in general terms by Phipps. Key aspects of this approach include the need for high irradiance on target, 10{sup 8} to 10{sup 9} W/cm{sup 2}, which favors short (i.e., picoseconds to nanoseconds) laser pulse durations and high energy per pulse ({approx} > 10 kJ). Due to the target's orbital velocity, the potential duration of engagement is only of order 100 seconds, so a high pulse repetition rate is also essential. The laser technology needed for this application did not exist when ORION was first proposed, but today, a unique combination of emerging technologies could create a path to enable deployment in the near future. Our concepts for the laser system architecture are an extension of what was developed for the National Ignition Facility (NIF), combined with high repetition rate laser technology developed for Inertial Fusion Energy (IFE), and heat capacity laser technology developed for military applications. The 'front-end' seed pulse generator would be fiber-optics based, and would generate a temporally, and spectrally tailored

  3. Space Debris Removal Using Multi-Mission Modular Spacecraft

    NASA Astrophysics Data System (ADS)

    Savioli, L.; Francesconi, A.; Maggi, F.; Olivieri, L.; Lorenzini, E.; Pardini, C.

    2013-08-01

    The study and development of ADR missions in LEO have become an issue of topical interest to the attention of the space community since the future space flight activities could be threatened by collisional cascade events. This paper presents the analysis of an ADR mission scenario where modular remover kits are employed to de-orbit some selected debris in SSO, while a distinct space tug performs the orbital transfers and rendezvous manoeuvres, and installs the remover kits on the client debris. Electro-dynamic tether and electric propulsion are considered as de-orbiting alternatives, while chemical propulsion is employed for the space tug. The total remover mass and de-orbiting time are identified as key parameters to compare the performances of the two de-orbiting options, while an optimization of the ΔV required to move between five selected objects is performed for a preliminary design at system level of the space tug. Final controlled re-entry is also considered and performed by means of a hybrid engine.

  4. Application of femtosecond laser range finder in space debris monitoring

    NASA Astrophysics Data System (ADS)

    Yuan, Jiang; Ji, Rongyi; Zhou, Weihu

    2016-11-01

    The space-based long-distance ranging of space debris will help to avoid collision. Compared with radar and telescope, the infrared binocular monitoring system can track and range space debris quickly. Because the measurement range is related to the baseline length, two cameras are placed on different satellites. Due to the lack of rigid connection between satellites, femtosecond laser ranging is used to measure the attitude of the camera.

  5. Procedures for analysis of debris relative to Space Shuttle systems

    NASA Technical Reports Server (NTRS)

    Kim, Hae Soo; Cummings, Virginia J.

    1993-01-01

    Debris samples collected from various Space Shuttle systems have been submitted to the Microchemical Analysis Branch. This investigation was initiated to develop optimal techniques for the analysis of debris. Optical microscopy provides information about the morphology and size of crystallites, particle sizes, amorphous phases, glass phases, and poorly crystallized materials. Scanning electron microscopy with energy dispersive spectrometry is utilized for information on surface morphology and qualitative elemental content of debris. Analytical electron microscopy with wavelength dispersive spectrometry provides information on the quantitative elemental content of debris.

  6. Space traffic hazards from orbital debris mitigation strategies

    NASA Astrophysics Data System (ADS)

    Smirnov, N. N.; Kiselev, A. B.; Smirnova, M. N.; Nikitin, V. F.

    2015-04-01

    The paper gives coverage of recent advances in mathematical modeling of long term orbital debris evolution within the frames of continua approach. Under the approach the evolution equations contain a number of source terms responsible for the variations of quantities of different fractions of orbital debris population due to fragmentations and collisions. Mechanisms of hypervelocity collisions of debris fragments with pressurized vessels are investigated. The spacecraft shield honeycomb concept is suggested based on principles of impact energy conversion and redistribution and consumption by destroyable structures. The paper is devoted to the 100th anniversary of the founder of space debris research in Moscow State University Prof. G.A. Tyulin.

  7. Membrane based thermoelectric sensor array for space debris detection

    NASA Astrophysics Data System (ADS)

    Haenschke, Frank; Kessler, Ernst; Ihring, Andreas; Bunte, Karl Dietrich; Herbst, Christian; Mohaupt, Matthias; Fichna, Torsten; Hagedorn, Daniel; Meyer, Hans-Georg

    2014-06-01

    As manmade space debris in the low earth orbit becomes an increasing risk to space missions, which could even result in total mission loss, it has become even more critical to have detailed knowledge of the properties of these particles like the mass, the velocity and the trajectory. In this paper, we present a newly designed, highly sensitive impact detector array with 16 pixels for space debris analysis. The thermopile sensor array, which was developed in the project, consists of 16 miniaturized multi-junction thermopile sensors made by modern thin-film technology on Si wafers. Each thermopile sensor consists of 100 radially arranged junction pairs formed from evaporated antimony and bismuth thin films. The centrally located active (hot) junctions comprise the active area of 1 mm². The output e.m.f. of the sensor is proportional to the temperature difference between the active and the reference junctions. The thermopile requires no cooling and no bias voltage or current for operation. It generates no 1/f noise but only the thermal resistance (Nyquist) noise. The sensor can be used for DC and low frequency AC measurements. The impact energy of micro sized particles is measured by a calorimetric principle. This means that the kinetic energy of the particle is converted into heat by hitting the absorbing foil, which is glued on the surface of the membrane area. This setup in combination with a preceded velocity detector allows the measurement of the most interesting particle quantities mass, velocity and trajectory.

  8. Characterization of Space Shuttle Ascent Debris Aerodynamics Using CFD Methods

    NASA Technical Reports Server (NTRS)

    Murman, Scott M.; Aftosmis, Michael J.; Rogers, Stuart E.

    2005-01-01

    An automated Computational Fluid Dynamics process for determining the aerodynamic Characteristics of debris shedding from the Space Shuttle Launch Vehicle during ascent is presented. This process uses Cartesian fully-coupled, six-degree-of-freedom simulations of isolated debris pieces in a Monte Carlo fashion to produce models for the drag and crossrange behavior over a range of debris shapes and shedding scenarios. A validation of the Cartesian methods against ballistic range data for insulating foam debris shapes at flight conditions, as well as validation of the resulting models, are both contained. These models are integrated with the existing shuttle debris transport analysis software to provide an accurate and efficient engineering tool for analyzing debris sources and their potential for damage.

  9. Object oriented studies into artificial space debris

    NASA Technical Reports Server (NTRS)

    Adamson, J. M.; Marshall, G.

    1988-01-01

    A prototype simulation is being developed under contract to the Royal Aerospace Establishment (RAE), Farnborough, England, to assist in the discrimination of artificial space objects/debris. The methodology undertaken has been to link Object Oriented programming, intelligent knowledge based system (IKBS) techniques and advanced computer technology with numeric analysis to provide a graphical, symbolic simulation. The objective is to provide an additional layer of understanding on top of conventional classification methods. Use is being made of object and rule based knowledge representation, multiple reasoning, truth maintenance and uncertainty. Software tools being used include Knowledge Engineering Environment (KEE) and SymTactics for knowledge representation. Hooks are being developed within the SymTactics framework to incorporate mathematical models describing orbital motion and fragmentation. Penetration and structural analysis can also be incorporated. SymTactics is an Object Oriented discrete event simulation tool built as a domain specific extension to the KEE environment. The tool provides facilities for building, debugging and monitoring dynamic (military) simulations.

  10. Orbital debris environment as measured at the Mir space station

    NASA Astrophysics Data System (ADS)

    Maag, Carl R.; Deshpande, Sunil P.; Stevenson, Tim J.; Mitzen, Paul S.

    1996-10-01

    A new European Space Agency (ESA) flight instrument attached to the exterior of the MIR Space Station is providing a better understanding of the effects of the space environment. The instrument was designed to measure, real time, the impacts and trajectory of hypervelocity particles, the atomic oxygen flux and contamination deposition/effects during the course of the mission. The ESA mission, EuroMir'95, began in September 1995 and was completed in March 1996. Active data from the momentum detectors have reconfirmed the existence of an orbital debris cloud. The mission also allowed for an EVA which returned passive materials to Earth for subsequent laboratory analyses. The early results of this experiment suggest the existence of one reasonable size cloud of small size debris particles with momenta in the range of 4E-11 kg-m/s to 5E-10 kg-m/s. These data are considered quite germane due to the similarity in orbital altitude and inclination of the Mir and Alpha Space Stations.

  11. Final design of a space debris removal system

    NASA Technical Reports Server (NTRS)

    Carlson, Erika; Casali, Steve; Chambers, Don; Geissler, Garner; Lalich, Andrew; Leipold, Manfred; Mach, Richard; Parry, John; Weems, Foley

    1990-01-01

    The objective is the removal of medium sized orbital debris in low Earth orbits. The design incorporates a transfer vehicle and a netting vehicle to capture the medium size debris. The system is based near an operational space station located at 28.5 degrees inclination and 400 km altitude. The system uses ground based tracking to determine the location of a satellite breakup or debris cloud. This data is unloaded to the transfer vehicle, and the transfer vehicle proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit, where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground, and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take about six months. The system is designed to allow for a 30 degree inclination change on the outgoing and incoming trips of the transfer vehicle.

  12. Space debris tracking at San Fernando laser station

    NASA Astrophysics Data System (ADS)

    Catalán, M.; Quijano, M.; Pazos, A.; Martín Davila, J.; Cortina, L. M.

    2016-12-01

    For years to come space debris will be a major issue for society. It has a negative impact on active artificial satellites, having implications for future missions. Tracking space debris as accurately as possible is the first step towards controlling this problem, yet it presents a challenge for science. The main limitation is the relatively low accuracy of the methods used to date for tracking these objects. Clearly, improving the predicted orbit accuracy is crucial (avoiding unnecessary anti-collision maneuvers). A new field of research was recently instituted by our satellite laser ranging station: tracking decommissioned artificial satellites equipped with retroreflectors. To this end we work in conjunction with international space agencies which provide increasing attention to this problem. We thus proposed to share our time-schedule of use of the satellite laser ranging station for obtaining data that would make orbital element predictions far more accurate (meter accuracy), whilst maintaining our tracking routines for active satellites. This manuscript reports on the actions carried out so far.

  13. Orbit propagation using semi-analytical theory and its applications in space debris field

    NASA Astrophysics Data System (ADS)

    Dutt, Pooja; Anilkumar, A. K.

    2017-02-01

    Lifetime estimation of space objects is very important for space debris related studies including mitigation studies and manoeuvre designs. It is essential to have a fast and accurate lifetime prediction tool for studies related to long term evolution of space debris environment. This paper presents the details of the Orbit Prediction using Semi-Analytic Theory (OPSAT) used for lifetime estimation of space objects. It uses BFGS Quasi-Newton algorithm to minimize least square error on apogee and perigee altitudes of a given TLE set to estimate ballistic coefficient (BC). This BC is used for future orbit prediction. OPSAT is evaluated for long term and short term orbit prediction using TLE data. It has been used for identification of potential candidate for active debris removal (ADR) and future projection of space debris environment with ADR.

  14. Space program: Space debris a potential threat to Space Station and shuttle

    NASA Technical Reports Server (NTRS)

    Schwartz, Stephen A.; Beers, Ronald W.; Phillips, Colleen M.; Ramos, Yvette

    1990-01-01

    Experts estimate that more than 3.5 million man-made objects are orbiting the earth. These objects - space debris - include whole and fragmentary parts of rocket bodies and other discarded equipment from space missions. About 24,500 of these objects are 1 centimeter across or larger. A 1-centimeter man-made object travels in orbit at roughly 22,000 miles per hour. If it hit a spacecraft, it would do about the same damage as would a 400-pound safe traveling at 60 miles per hour. The Government Accounting Office (GAO) reviews NASA's plans for protecting the space station from debris, the extent and precision of current NASA and Defense Department (DOD) debris-tracking capabilities, and the extent to which debris has already affected shuttle operations. GAO recommends that the space debris model be updated, and that the findings be incorporated into the plans for protecting the space station from such debris. GAO further recommends that the increased risk from debris to the space shuttle operations be analyzed.

  15. Applied Astronomy: An Optical Survey for Space Debris at GEO

    NASA Technical Reports Server (NTRS)

    Seitzer, Patrick; Barker, Edwin S.; Abercromby, K.; Rodriquez, H.

    2007-01-01

    A viewgraph is presented to discuss space debris at Geosynchronous Earth Orbit (GEO). The topics include: 1) Syncom1 launched February 14, 1963 Failed on orbit insertion 1st piece of GEO debris!; 2) Example of recent GEO payload: XM-2 Rock satellite for direct broadcast radio; 3) MODEST Michigan Orbital DEbrisSurvey Telescope the telescope formerly known as the Curtis-Schmidt; 4) GEO Debris Survey; 5) Examples of Detections; 6) Brightness Variations Common; 7) Observed Angular Rates; 8) Two Populations at GEO; 9) High Area-to-Mass Ratio Material (A/M); 10) Examples of MLI; 11) Examples of MLI Release in LEO; 12) Liou & Weaver (2005) models; 13) ESA 1-m Telescope Survey; 14) Two Telescopes March 2007 Survey and Follow-up; 15) Final Eccentricity; and 16) How control Space Debris?

  16. Mission concept and autonomy considerations for active Debris removal

    NASA Astrophysics Data System (ADS)

    Peters, Susanne; Pirzkall, Christoph; Fiedler, Hauke; Förstner, Roger

    2016-12-01

    Over the last 60 years, Space Debris has become one of the main challenges for the safe operation of satellites in low Earth orbit. To address this threat, guidelines that include a limited debris release during normal operations, minimization of the potential for on-orbit break-ups and post mission disposal have begun to be implemented. However, for the long-term, the amount of debris will still increase due to fragments created by collisions of objects in space. The active removal of space debris of at least five large objects per years is therefore recommended, but not yet included in those guidelines. Even though various technical concepts have been developed over the last years, the question on how to make them reliable and safe or how to finance such mission has not been answered. This paper addresses the first two topics. With Space Debris representing an uncooperative and possibly tumbling target, close proximity becomes absolutely critical, especially when an uninterrupted connection to the ground station is not ensured. This paper therefore defines firstly a mission to remove at least five large objects and secondly introduces a preliminary autonomy concept fitted for this mission.

  17. Micrometeoroid and Orbital Debris Environments for the International Space Station

    DTIC Science & Technology

    2007-12-15

    Baseline micrometeoroid and orbital debris fluence estimates for spacecraft in low Earth orbit (LEO) are provided. For these calculations, an orbit similar to that of the International Space Station (ISS) is used.

  18. Orbital Dynamics of Space Debris around operational artificial satellites

    NASA Astrophysics Data System (ADS)

    Sampaio, Jarbas

    2016-07-01

    The increasing number of space debris, orbiting the Earth justifies and requires more efforts to observe and track them to avoid collisions among them and the earth's satellites. In this way, several studies are important to preserve the operability of the artificial satellites. In this work, the orbital dynamics of space debris are studied in the neighborhood of operational artificial satellites. The results show that the collision risks between these objects is high and solutions to avoid these events are necessary.

  19. Tracking Debris Shed by a Space-Shuttle Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Stuart, Phillip C.; Rogers, Stuart E.

    2009-01-01

    The DEBRIS software predicts the trajectories of debris particles shed by a space-shuttle launch vehicle during ascent, to aid in assessing potential harm to the space-shuttle orbiter and crew. The user specifies the location of release and other initial conditions for a debris particle. DEBRIS tracks the particle within an overset grid system by means of a computational fluid dynamics (CFD) simulation of the local flow field and a ballistic simulation that takes account of the mass of the particle and its aerodynamic properties in the flow field. The computed particle trajectory is stored in a file to be post-processed by other software for viewing and analyzing the trajectory. DEBRIS supplants a prior debris tracking code that took .15 minutes to calculate a single particle trajectory: DEBRIS can calculate 1,000 trajectories in .20 seconds on a desktop computer. Other improvements over the prior code include adaptive time-stepping to ensure accuracy, forcing at least one step per grid cell to ensure resolution of all CFD-resolved flow features, ability to simulate rebound of debris from surfaces, extensive error checking, a builtin suite of test cases, and dynamic allocation of memory.

  20. Engineering Challenges for Active Debris Removal

    NASA Technical Reports Server (NTRS)

    Liou, Jer-Chyi

    2011-01-01

    Recent modeling studies on the instability of the debris population in the low Earth orbit (LEO) region and the collision between Iridium 33 and Cosmos 2251 have underlined the need for active debris removal. A 2009 analysis by the NASA Orbital Debris Program Office shows that, in order to maintain the LEO debris population at a constant level for the next 200 years, an active debris removal of about five objects per year is needed. The targets identified for removal are those with the highest mass and collision probability products in the environment. Many of these objects are spent upper stages with masses ranging from 1 to more than 8 metric tons, residing in several altitude regions and concentrated in about 10 inclination bands. To remove five of those objects on a yearly basis, in a cost-effective manner, represents many challenges in engineering, technology development, and operations. This paper outlines a conceptual end-to-end debris removal operation, including launch, precision tracking, rendezvous, stabilization (of the tumbling targets), capture, and deorbit of the targets; and highlights major challenges associated with the operations. Pros and cons of several proposed removal techniques are also evaluated.

  1. The Platform Design of Space-based Optical Observations of Space Debris

    NASA Astrophysics Data System (ADS)

    Bing-er, Chen; Jian-ning, Xiong

    2017-01-01

    The basic method to design a platform for the space-based optical observations of space debris is introduced. The observation schemes of GEO (geosynchronous equatorial orbit) and LEO (low Earth orbit) debris are given respectively, including the orbital parameters of platforms and the pointing of telescopes, etc. The debris studied here are all taken from the foreign catalog. According to the real orbits of space debris, the observational results of different schemes are simulated. By studying the single platform, the optimal observing altitude for the GEO debris and the optimal telescope's deflection angles at different altitudes for the LEO debris are given. According to these, the multi-platform observation networks are designed. By analyzing the advantages and disadvantages of different schemes, it can provide a reference for the application of space-based optical observations of space debris

  2. Laser system for space debris cleaning

    NASA Astrophysics Data System (ADS)

    Rubenchik, A. M.; Erlandson, A. C.; Liedahl, D.

    2012-07-01

    Starting with intensity requirements for producing efficient ablation thrust, then applying orbital mechanics and taking beam transport into account, we have determined the laser pulse energy and the number of pulses required for removing orbital debris. Our calculations show that a ground-based, diode-pumped, gas-cooled multi-slab laser, that uses only modest extensions of existing technology, would be capable of removing most small debris from low-earth orbit, when used with a 3-m-diameter beam director. Such a laser would also be capable of moving large debris into orbits that avoid high-value satellites and of even removing large debris from orbit, by illuminating the debris over several encounters. The laser design we propose uses diode-pumped, Nd:glass, gas-cooled amplifiers with 25-cm square apertures. When operating at the laser fundamental wavelength of 1054 nm, each beamline would produce ˜ 8kJ/4ns pulses at 15 Hz. Two such beamlines, combined using established polarization-combining methods, would be sufficient for orbital debris cleaning. Alternatively, when operating at the second harmonic of 527 nm, each beamline would produce ˜ 7 kJ/4 ns pulses. Due to reduced beam divergence and a smaller beam diameter at the debris, a single harmonically-converted beamline can be useful. We estimate that the first-of-a-kind beamline could be deployed within 4-5 years of project start at a cost of 100-150M. Later beamlines would require less development and engineering costs and would have substantially lower overall cost.

  3. Active Debris Removal System Based on Polyurethane Foam

    NASA Astrophysics Data System (ADS)

    Rizzitelli, Federico; Valdatta, Marcelo; Bellini, Niccolo; Candini Gian, Paolo; Rastelli, Davide; Romei, Fedrico; Locarini, Alfredo; Spadanuda, Antonio; Bagassi, Sara

    2013-08-01

    Space debris is an increasing problem. The exponential increase of satellite launches in the last 50 years has determined the problem of space debris especially in LEO. The remains of past missions are dangerous for both operative satellites and human activity in space. But not only: it has been shown that uncontrolled impacts between space objects can lead to a potentially dangerous situation for civil people on Earth. It is possible to reach a situation of instability where the big amount of debris could cause a cascade of collisions, the so called Kessler syndrome, resulting in the infeasibility of new space missions for many generations. Currently new technologies for the mitigation of space debris are under study: for what concerning the removal of debris the use of laser to give a little impulse to the object and push it in a graveyard orbit or to be destroyed in the atmosphere. Another solution is the use of a satellite to rendezvous with the space junk and then use a net to capture it and destroy it in the reentry phase. In a parallel way the research is addressed to the study of deorbiting solutions to prevent the formation of new space junk. The project presented in this paper faces the problem of how to deorbit an existing debris, applying the studies about the use of polyurethane foam developed by Space Robotic Group of University of Bologna. The research is started with the Redemption experiment part of last ESA Rexus program. The foam is composed by two liquid components that, once properly mixed, trig an expansive reaction leading to an increase of volume whose entity depends on the chemical composition of the two starting components. It is possible to perform two kind of mission: 1) Not controlled removal: the two components are designed to react producing a low density, high expanded, spongy foam that incorporates the debris. The A/m ratio of the debris is increased and in this way also the ballistic parameter. As a consequence, the effect of

  4. Research on Long-Term Orbit Propagation for Space Debris in LEO

    NASA Astrophysics Data System (ADS)

    Peng, Keke; Pang, Baojun; Xiao, Weike

    2013-08-01

    Space debris long-term orbit propagation is one of the main problems for the space debris environment models. The evolution of space debris in low Earth orbit (LEO) is determined by a complex interplay of different perturbations. The aim of this paper is to investigate the long-term effects of the most dominating perturbations: Earth geopotential effects, atmospheric drag, luni-solar perturbations and solar radiation pressure. The atmospheric drag is the major non-gravitational perturbation in LEO. This article provides an average method of numerical integration on one revolution for rotating and stationary atmosphere, and then one can make use of various atmospheric densities to calculate the orbital evolution. Using this method, we have analyzed the effects of rotating and stationary atmospheric drag perturbation on orbital lifetime. The results show the effects of solar activity and geomagnetic index on orbital evolution are obvious. The lifetime difference in rotating atmosphere is mostly depending on inclinations of space debris.

  5. Attitude coordination of multiple spacecraft for space debris surveillance

    NASA Astrophysics Data System (ADS)

    Felicetti, Leonard; Emami, M. Reza

    2017-03-01

    This paper discusses the attitude coordination of a formation of multiple spacecraft for space debris surveillance. Off-the-shelf optical sensors and reaction wheels, with limited field of view and control torque, respectively, are considered to be used onboard the spacecraft for performing the required attitude maneuvers to detect and track space debris. The sequence of attitude commands are planned by a proposed algorithm, which allows for a dynamic team formation, as well as performing suitable maneuvers to eventually point towards the same debris. A control scheme based on the nonlinear state dependent Riccati equation is designed and applied to the space debris surveillance mission scenario, and its performance is compared with those of the classic linear quadratic regulator and quaternion feedback proportional derivative controllers. The viability and performance of the coordination algorithm and the controllers are validated through numerical simulations.

  6. NASA's Long-term Debris Environment and Active Debris Removal Modeling Activities

    NASA Technical Reports Server (NTRS)

    Liou, J.-C.

    2009-01-01

    This slide presentation reviews the modeling activities for modeling of the long-term debris environment, the updated assessments of the environment, and the necessity to model the effectiveness of the technologies aimed at the removal of orbital debris. The model being used is named a LEO to GEO environment debris (LEGEND). It is a high fidelity three dimensional numerical simulation model with the capability to treat objects individually. It uses a Monte Carlo approach and a collision probability evaluation algorithm to simulate future satellite breakups and the growth of the debris populations.

  7. Autonomous space processor for orbital debris

    NASA Technical Reports Server (NTRS)

    1990-01-01

    This work continues to develop advanced designs toward the ultimate goal of a Get Away Special to demonstrate economical removal of orbital debris using local resources in orbit. The fundamental technical feasibility was demonstrated in 1988 through theoretical calculations, quantitative computer animation, a solar focal point cutter, a robotic arm design, and a subscale model. Last year improvements were made to the solar cutter and the robotic arm. Also performed last year was a mission analysis that showed the feasibility of retrieving at least four large (greater than 1500-kg) pieces of debris. Advances made during this reporting period are the incorporation of digital control with the existing placement arm, the development of a new robotic manipulator arm, and the study of debris spin attenuation. These advances are discussed here.

  8. Autonomous space processor for orbital debris

    NASA Technical Reports Server (NTRS)

    Ramohalli, Kumar; Campbell, David; Marine, Micky; Saad, Mohamad; Bertles, Daniel; Nichols, Dave

    1990-01-01

    Advanced designs are being continued to develop the ultimate goal of a GETAWAY special to demonstrate economical removal of orbital debris utilizing local resources in orbit. The fundamental technical feasibility was demonstrated in 1988 through theoretical calculations, quantitative computer animation, a solar focal point cutter, a robotic arm design and a subcase model. Last year improvements were made to the solar cutter and the robotic arm. Also performed last year was a mission analysis which showed the feasibility of retrieve at least four large (greater than 1500 kg) pieces of debris. Advances made during this reporting period are the incorporation of digital control with the existing placement arm, the development of a new robotic manipulator arm, and the study of debris spin attenuation. These advances are discussed.

  9. The Platform Design of Space-based Optical Observations of Space Debris

    NASA Astrophysics Data System (ADS)

    Chen, B. R.; Xiong, J. N.

    2016-03-01

    The basic design method of the platform for the space-based optical observations of space debris is introduced. The observation schemes of GEO (geosynchronous equatorial orbit) and LEO (low Earth orbit) debris are given respectively, including orbital parameters of platforms and pointing of telescopes, etc. Debris studied here is all from foreign catalog. According to the real orbit of space debris, the observational results of different schemes are simulated. By studying single platform, the optimal observing altitude for GEO debris and the optimal telescope's deflection angles at different altitudes for LEO debris are given. According to these, multi-platforms observation networks are designed. By analyzing the advantages and disadvantages of each scheme, it can provide reference for the application of space-based optical debris observation.

  10. Orbiting Space Debris: Dangers, Measurement and Mitigation

    DTIC Science & Technology

    1992-06-01

    sure how many undetectable particles the fragmentation of a satellite creates. Actual ground-based tesis have been conducted in an attempt to...conducted by the Jet Propulsion Laboratory lo measure the presence of 0.2 lo 0.5 cm and 0.5 to 2 cm sized debris. The Areclbo radar in Puerto Rico

  11. EISCAT Space Debris during the IPY- A 5000-Hour Campaign

    NASA Astrophysics Data System (ADS)

    Markkanen, J.; Jehn, R.; Krag, H.

    2009-03-01

    During the International Polar Year (IPY) in 2007-2009, EISCAT measured space debris at its Svalbard radar (ESR, latitude 78.2°N), simultaneously with the standard ionospheric measurement. From the 239 000 events which were recorded in 5060 hours only a "Quality Set" (QS) was extracted for further analysis. The QS essentially consists of 101 complete 24-hour beam park debris measurements, between 13 Mar 2007 and 10 Feb 2008, and contains about 95 000 events. The data provide a relatively dense sampling of the debris environment above ESR in the first year following the Chinese ASAT event, in January 2007. The QS is freely available in the web.

  12. Large craters on the meteoroid and space debris impact experiment

    NASA Technical Reports Server (NTRS)

    Humes, Donald H.

    1991-01-01

    The distribution around the Long Duration Exposure Facility (LDEF) of 532 large craters in the Al plates from the Meteoroid and Space Debris Impact Experiment (S0001) is discussed along with 74 additional large craters in Al plates donated to the Meteoroid and Debris Special Investigation Group by other LDEF experimenters. The craters are 0.5 mm in diameter and larger. Crater shape is discussed. The number of craters and their distribution around the spacecraft are compared with values predicted with models of the meteoroid environment and the manmade orbital debris environment.

  13. A modelling of ejecta as a space debris source

    NASA Astrophysics Data System (ADS)

    Bariteau, Muriel; Mandeville, Jean-Claude

    2001-10-01

    When a micro-debris or a micrometeoroid impacts a spacecraft surface, secondary particles, called ejecta, are produced. These ejecta can contributes to a modification of the debris environment: either locally by the occurrence of secondary impacts on the components of complex and large space structures, or at great distances by the formation of a population of small orbital debris. This paper describes, firstly, the ejecta production, and secondly, their lifetime and orbit propagation. Then, the repartition of ejecta in LEO is given. Results describing the ejecta number as a function of size and altitude are presented.

  14. A multi-spacecraft formation approach to space debris surveillance

    NASA Astrophysics Data System (ADS)

    Felicetti, Leonard; Emami, M. Reza

    2016-10-01

    This paper proposes a new mission concept devoted to the identification and tracking of space debris through observations made by multiple spacecraft. Specifically, a formation of spacecraft has been designed taking into account the characteristics and requirements of the utilized optical sensors as well as the constraints imposed by sun illumination and visibility conditions. The debris observations are then shared among the team of spacecraft, and processed onboard of a "hosting leader" to estimate the debris motion by means of Kalman filtering techniques. The primary contribution of this paper resides on the application of a distributed coordination architecture, which provides an autonomous and robust ability to dynamically form spacecraft teams once the target has been detected, and to dynamically build a processing network for the orbit determination of space debris. The team performance, in terms of accuracy, readiness and number of the detected objects, is discussed through numerical simulations.

  15. Engineering and Technology Challenges for Active Debris Removal

    NASA Technical Reports Server (NTRS)

    Liou, Jer-Chyi

    2011-01-01

    After more than fifty years of space activities, the near-Earth environment is polluted with man-made orbital debris. The collision between Cosmos 2251 and the operational Iridium 33 in 2009 signaled a potential collision cascade effect, also known as the "Kessler Syndrome", in the environment. Various modelling studies have suggested that the commonly-adopted mitigation measures will not be sufficient to stabilize the future debris population. Active debris removal must be considered to remediate the environment. This paper summarizes the key issues associated with debris removal and describes the technology and engineering challenges to move forward. Fifty-four years after the launch of Sputnik 1, satellites have become an integral part of human society. Unfortunately, the ongoing space activities have left behind an undesirable byproduct orbital debris. This environment problem is threatening the current and future space activities. On average, two Shuttle window panels are replaced after every mission due to damage by micrometeoroid or orbital debris impacts. More than 100 collision avoidance maneuvers were conducted by satellite operators in 2010 to reduce the impact risks of their satellites with respect to objects in the U.S. Space Surveillance Network (SSN) catalog. Of the four known accident collisions between objects in the SSN catalog, the last one, collision between Cosmos 2251 and the operational Iridium 33 in 2009, was the most significant. It was the first ever accidental catastrophic destruction of an operational satellite by another satellite. It also signaled the potential collision cascade effect in the environment, commonly known as the "Kessler Syndrome," predicted by Kessler and Cour-Palais in 1978 [1]. Figure 1 shows the historical increase of objects in the SSN catalog. The majority of the catalog objects are 10 cm and larger. As of April 2011, the total objects tracked by the SSN sensors were more than 22,000. However, approximately 6000 of

  16. Laser ranging system and measurement analysis for space debris with high repetition rate

    NASA Astrophysics Data System (ADS)

    Wu, Zhibo; Zhang, Haifeng; Meng, Wendong; Li, Pu; Deng, Huarong; Tang, Kai; Ding, Renjie; Zhang, Zhongping

    2016-01-01

    Laser measurement technology is inherently high accurate and will play an important role in precise orbit determination, accurate catalog, surveillance to space debris. Shanghai Astronomical Observatory (SHAO) has been developing the technology of laser measurement to space debris for several years. Based on the first successful laser ranging measurement to space debris in country, by applying one new set of high power 532nm wavelength laser system with 200Hz repetition rate, and adopting low dark noise APD detector with high quantum efficiency and high transmissivity of narrow bandwidth spectral filter, SHAO have achieved hundreds of passes of laser data from space debris in 2014, and the measured objects with distance between 500km and 2200km, Radar Cross Section (RCS) of >10m2 to <0.5m2 at the precision of <1m RMS for small RCS targets ,and the success rate of measured passes of up to 80%. The results show that laser ranging technology in China can routinely measure space debris and provide enough measurement data with high accuracy to space debris applications and researches such as surveillance activities in the future.

  17. Active removal of orbital debris by induced hypervelocity impact of injected dust grains

    NASA Astrophysics Data System (ADS)

    Ganguli, G.; Crabtree, C.; Velikovich, A.; Rudakov, L.; Chappie, S.

    2014-02-01

    Collisions of an active satellite with a small (1mm - cm) untrackable orbital debris can be mission ending. It has been recently established that we are at the tipping point for collisional cascade of larger objects to exponential growth of small orbital debris. This will make access to near-Earth space hazardous without first clearing the existing debris from this region. We present a concept for elimination of small debris by deploying micron scale dust to artificially enhance the drag on the debris. The key physics that makes this technique viable is the possibility of large momentum boost realized through hypervelocity dust/debris collision. By deploying high mass density micron scale dust in a narrow altitude band temporarily it is possible to artificially enhance drag on debris spread over a very large volume and force rapid reentry. The injected dust will also reenter the atmosphere leaving no permanent residue in space.

  18. Space Debris Radar Experiments at the Medicina VLBI Dish

    NASA Astrophysics Data System (ADS)

    Pupillo, G.; Montebugnoli, S.; Di Martino, M.; Salerno, E.; Bartolini, M.; Pluchino, S.; Schilliro, F.; Anselmo, L.; Portelli, C.; Konovalenko, A.; Nabatov, A.

    2009-03-01

    In 2007 three space debris detection tests were performed in the framework of a monitoring program carried out by the Istituto Nazionale di Astrofisica - INAF - in collaboration with the Italian Space Agency - ASI. The observations were made by using the bistatic radar technique. The INAF 32 m radiotelescope located at Medicina (Bologna, Italy) was used as receiver whereas the Ukrainian 70 m parabolic antenna located at Evpatoria was utilized as transmitter. The aim of the experiment was to test the sensitivity of the Medicina-Evpatoria radar system in space debris detection, and to validate and optimize the hardware setup. Measurements were mainly carried out on inactive satellites and catalogued space debris. However the search for new fragments in LEO was also performed during the campaign. This paper reports on results of these observations.

  19. Particle swarm optimization based space debris surveillance network scheduling

    NASA Astrophysics Data System (ADS)

    Jiang, Hai; Liu, Jing; Cheng, Hao-Wen; Zhang, Yao

    2017-02-01

    The increasing number of space debris has created an orbital debris environment that poses increasing impact risks to existing space systems and human space flights. For the safety of in-orbit spacecrafts, we should optimally schedule surveillance tasks for the existing facilities to allocate resources in a manner that most significantly improves the ability to predict and detect events involving affected spacecrafts. This paper analyzes two criteria that mainly affect the performance of a scheduling scheme and introduces an artificial intelligence algorithm into the scheduling of tasks of the space debris surveillance network. A new scheduling algorithm based on the particle swarm optimization algorithm is proposed, which can be implemented in two different ways: individual optimization and joint optimization. Numerical experiments with multiple facilities and objects are conducted based on the proposed algorithm, and simulation results have demonstrated the effectiveness of the proposed algorithm.

  20. Assessment Study of Small Space Debris Removal by Laser Satellites

    NASA Technical Reports Server (NTRS)

    Choi, Sang H.; Papa, Richard S.

    2011-01-01

    Space debris in Earth orbit poses significant danger to satellites, humans in space, and future space exploration activities. In particular, the increasing number of unidentifiable objects, smaller than 10 cm, presents a serious hazard. Numerous technologies have been studied for removing unwanted objects in space. Our approach uses a short wavelength laser stationed in orbit to vaporize these small objects. This paper discusses the power requirements for space debris removal using lasers. A short wavelength laser pumped directly or indirectly by solar energy can scan, identify, position, and illuminate the target, which will then be vaporized or slow down the orbital speed of debris by laser detonation until it re-enters the atmosphere. The laser-induced plasma plume has a dispersive motion of approximately 105 m/sec with a Lambertian profile in the direction of the incoming beam [1-2]. The resulting fast ejecting jet plume of vaporized material should prevent matter recombination and condensation. If it allows any condensation of vaporized material, the size of condensed material will be no more than a nanoscale level [3]. Lasers for this purpose can be indirectly pumped by power from an array of solar cells or directly pumped by the solar spectrum [4]. The energy required for vaporization and ionization of a 10 cm cube ( 2700 gm) of aluminum is 87,160 kJ. To remove this amount of aluminum in 3 minutes requires a continuous laser beam power of at least 5.38 MW under the consideration of 9% laser absorption by aluminum [5] and 5% laser pumping efficiency. The power needed for pumping 5.38 MW laser is approximately 108 MW, which can be obtained from a large solar array with 40% efficiency solar cells and a minimal area of 450 meters by 450 meters. This solar array would collect approximately 108 MW. The power required for system operation and maneuvering can be obtained by increasing solar panel size. This feasibility assessment covers roughly the power requirement

  1. Development and Flight Demonstration of Space Debris Monitor (SDM)

    NASA Astrophysics Data System (ADS)

    Kitazawa, Yukihito; Hanada, Toshiya; Matsumoto, Haruhisa; Kobayashi, Masanori; Sakurai, Akira; Yasaka, Tetsuo; Funakoshi, Kunihiro; Hasegawa, Sunao; Akahoshi, Yasuhiro; Kimoto, Yugo; Okudaira, Osamu; Kamiya, Koki; Nakamura, Maki

    2016-07-01

    The space debris monitor (SDM) is a large-area impact sensor for in situ measurements of micro-meteoroids and space debris of the sub-millimeter to millimeter size in the near-Earth space environment. These meteoroid and debris particles are very small to be detected by ground-based observations (radars and optical telescopes) but are sufficiently large to cause serious damage to spacecraft equipment in the low Earth orbit region. The nominal detection area of the SDM is 0.1 m^2 (0.35 m × 0.3 m), but its dimensions can be easily modified to accommodate different SDM constraints. The SDM is made from a flexible printed circuit, which is produced from a thin film of a nonconductive material (such as polyimide) on which thin conductive stripes are formed in parallel. The stripe width is approximately 50 μm, and the spatial separation is approximately 100 μm, as shown in Figure 1. When a micro-debris particle with an effective diameter near to or larger than the spatial separation of the stripes (here approximately 100 μm) collides with the sensor film at a velocity sufficient to penetrate it, one or more of the stripes are cut and become nonconductive. Debris impacts can thus be detected by monitoring the electrical conductivity (resistivity) of the stripes. This sensor system can measure the size of the incident micro-debris particles by detecting the number of severed stripes. The measurement concept is registered as a patent in many countries. The first SDM was launched with HTV-5 on August 19, 2015 and represented the world's first micro-debris measurement demonstration experiment to be conducted on the ISS using the concept of conductive (resistive) strip lines for real-time debris detection.

  2. Operational Implementation of Space Debris Mitigation Procedures

    NASA Astrophysics Data System (ADS)

    Gicquel, Anne-Helene; Bonaventure, Francois

    2013-08-01

    During the spacecraft lifetime, Astrium supports its customers to manage collision risks alerts from the Joint Space Operations Center (JSpOC). This was previously done with hot-line support and a manual operational procedure. Today, it is automated and integrated in QUARTZ, the Astrium Flight Dynamics operational tool. The algorithms and process details for this new 5- step functionality are provided in this paper. To improve this functionality, some R&D activities such as the study of dilution phenomenon and low relative velocity encounters are going on. Regarding end of life disposal, recent operational experiences as well as studies results are presented.

  3. Space Debris Attitude Simulation - IOTA (In-Orbit Tumbling Analysis)

    NASA Astrophysics Data System (ADS)

    Kanzler, R.; Schildknecht, T.; Lips, T.; Fritsche, B.; Silha, J.; Krag, H.

    Today, there is little knowledge on the attitude state of decommissioned intact objects in Earth orbit. Observational means have advanced in the past years, but are still limited with respect to an accurate estimate of motion vector orientations and magnitude. Especially for the preparation of Active Debris Removal (ADR) missions as planned by ESA's Clean Space initiative or contingency scenarios for ESA spacecraft like ENVISAT, such knowledge is needed. The In-Orbit Tumbling Analysis tool (IOTA) is a prototype software, currently in development within the framework of ESA's “Debris Attitude Motion Measurements and Modelling” project (ESA Contract No. 40000112447), which is led by the Astronomical Institute of the University of Bern (AIUB). The project goal is to achieve a good understanding of the attitude evolution and the considerable internal and external effects which occur. To characterize the attitude state of selected targets in LEO and GTO, multiple observation methods are combined. Optical observations are carried out by AIUB, Satellite Laser Ranging (SLR) is performed by the Space Research Institute of the Austrian Academy of Sciences (IWF) and radar measurements and signal level determination are provided by the Fraunhofer Institute for High Frequency Physics and Radar Techniques (FHR). Developed by Hyperschall Technologie Göttingen GmbH (HTG), IOTA will be a highly modular software tool to perform short- (days), medium- (months) and long-term (years) propagation of the orbit and attitude motion (six degrees-of-freedom) of spacecraft in Earth orbit. The simulation takes into account all relevant acting forces and torques, including aerodynamic drag, solar radiation pressure, gravitational influences of Earth, Sun and Moon, eddy current damping, impulse and momentum transfer from space debris or micro meteoroid impact, as well as the optional definition of particular spacecraft specific influences like tank sloshing, reaction wheel behaviour

  4. Characterization of the Space Shuttle Ascent Debris using CFD Methods

    NASA Technical Reports Server (NTRS)

    Murman, Scott M.; Aftosmis, Michael J.; Rogers, Stuart E.

    2005-01-01

    After video analysis of space shuttle flight STS-107's ascent showed that an object shed from the bipod-ramp region impacted the left wing, a transport analysis was initiated to determine a credible flight path and impact velocity for the piece of debris. This debris transport analysis was performed both during orbit, and after the subsequent re-entry accident. The analysis provided an accurate prediction of the velocity a large piece of foam bipod ramp would have as it impacted the wing leading edge. This prediction was corroborated by video analysis and fully-coupled CFD/six degree of freedom (DOF) simulations. While the prediction of impact velocity was accurate enough to predict critical damage in this case, one of the recommendations of the Columbia Accident Investigation Board (CAIB) for return-to-flight (RTF) was to analyze the complete debris environment experienced by the shuttle stack on ascent. This includes categorizing all possible debris sources, their probable geometric and aerodynamic characteristics, and their potential for damage. This paper is chiefly concerned with predicting the aerodynamic characteristics of a variety of potential debris sources (insulating foam and cork, nose-cone ablator, ice, ...) for the shuttle ascent configuration using CFD methods. These aerodynamic characteristics are used in the debris transport analysis to predict flight path, impact velocity and angle, and provide statistical variation to perform risk analyses where appropriate. The debris aerodynamic characteristics are difficult to determine using traditional methods, such as static or dynamic test data, due to the scaling requirements of simulating a typical debris event. The use of CFD methods has been a critical element for building confidence in the accuracy of the debris transport code by bridging the gap between existing aerodynamic data and the dynamics of full-scale, in-flight events.

  5. User's Manual for Space Debris Surfaces (SD_SURF)

    NASA Technical Reports Server (NTRS)

    Elfer, N. C.

    1996-01-01

    A unique collection of computer codes, Space Debris Surfaces (SD_SURF), have been developed to assist in the design and analysis of space debris protection systems. SD_SURF calculates and summarizes a vehicle's vulnerability to space debris as a function of impact velocity and obliquity. An SD_SURF analysis will show which velocities and obliquities are the most probable to cause a penetration. This determination can help the analyst select a shield design which is best suited to the predominant penetration mechanism. The analysis also indicates the most suitable parameters for development or verification testing. The SD_SURF programs offer the option of either FORTRAN programs and Microsoft EXCEL spreadsheets and macros. The FORTRAN programs work with BUMPERII version 1.2a or 1.3 (Cosmic released). The EXCEL spreadsheets and macros can be used independently or with selected output from the SD_SURF FORTRAN programs.

  6. Improving the precision of astrometry for space debris

    SciTech Connect

    Sun, Rongyu; Zhao, Changyin; Zhang, Xiaoxiang

    2014-03-01

    The data reduction method for optical space debris observations has many similarities with the one adopted for surveying near-Earth objects; however, due to several specific issues, the image degradation is particularly critical, which makes it difficult to obtain precise astrometry. An automatic image reconstruction method was developed to improve the astrometry precision for space debris, based on the mathematical morphology operator. Variable structural elements along multiple directions are adopted for image transformation, and then all the resultant images are stacked to obtain a final result. To investigate its efficiency, trial observations are made with Global Positioning System satellites and the astrometry accuracy improvement is obtained by comparison with the reference positions. The results of our experiments indicate that the influence of degradation in astrometric CCD images is reduced, and the position accuracy of both objects and stellar stars is improved distinctly. Our technique will contribute significantly to optical data reduction and high-order precision astrometry for space debris.

  7. NASA's Space Environments and Effects (SEE) Program: Meteoroid and Orbital Debris Lesson Plan.

    ERIC Educational Resources Information Center

    National Aeronautics and Space Administration, Washington, DC.

    The study of the natural space environment and its effects on spacecraft is one of the most important and least understood aspects of spacecraft design. The Space Environments and Effects (SEE) Program prepared the Meteoroids and Orbital Debris Lesson Plan, a SEE-focused high school curriculum to engage students in creative activities that will…

  8. Autonomous space processor for orbital debris

    NASA Technical Reports Server (NTRS)

    Ramohalli, Kumar; Campbell, David; Brockman, Jeff P.; Carter, Bruce; Donelson, Leslie; John, Lawrence E.; Marine, Micky C.; Rodina, Dan D.

    1989-01-01

    This work continues to develop advanced designs toward the ultimate goal of a GETAWAY SPECIAL to demonstrate economical removal of orbital debris utilizing local resources in orbit. The fundamental technical feasibility was demonstrated last year through theoretical calculations, quantitative computer animation, a solar focal point cutter, a robotic arm design and a subscale model. During this reporting period, several improvements are made in the solar cutter, such as auto track capabilities, better quality reflectors and a more versatile framework. The major advance has been in the design, fabrication and working demonstration of a ROBOTIC ARM that has several degrees of freedom. The functions were specifically tailored for the orbital debris handling. These advances are discussed here. Also a small fraction of the resources were allocated towards research in flame augmentation in SCRAMJETS for the NASP. Here, the fundamental advance was the attainment of Mach numbers up to 0.6 in the flame zone and a vastly improved injection system; the current work is expected to achieve supersonic combustion in the laboratory and an advanced monitoring system.

  9. Need for a network of observatories for space debris dynamical and physical characterization

    NASA Astrophysics Data System (ADS)

    Piergentili, Fabrizio; Santoni, Fabio; Castronuovo, Marco; Portelli, Claudio; Cardona, Tommaso; Arena, Lorenzo; Sciré, Gioacchino; Seitzer, Patrick

    2016-01-01

    Space debris represents a major concern for space missions since the risk of impact with uncontrolled objects has increased dramatically in recent years. Passive and active mitigation countermeasures are currently under consideration but, at the base of any of such corrective actions is the space debris continuous monitoring through ground based surveillance systems.At the present, many space agencies have the capability to get optical measurements of space orbiting objects mainly relaying on single observatories. The recent research in the field of space debris, demonstrated how it is possible to increase the effectiveness of optical measurements exploitation by using joint observations of the same target from different sites.The University of Rome "La Sapienza", in collaboration with Italian Space Agency (ASI), is developing a scientific network of observatories dedicated to Space Debris deployed in Italy (S5Scope at Rome and SPADE at Matera) and in Kenya at the Broglio Space Center in Malindi (EQUO). ASI founded a program dedicated to space debris, in order to spread the Italian capability to deal with different aspects of this issue. In this framework, the University of Rome is in charge of coordinating the observatories network both in the operation scheduling and in the data analysis. This work describes the features of the observatories dedicated to space debris observation, highlighting their capabilities and detailing their instrumentation. Moreover, the main features of the scheduler under development, devoted to harmonizing the operations of the network, will be shown. This is a new system, which will autonomously coordinate the observations, aiming to optimize results in terms of number of followed targets, amount of time dedicated to survey, accuracy of orbit determination and feasibility of attitude determination through photometric data.Thus, the authors will describe the techniques developed and applied (i) to implement the multi-site orbit

  10. Active Debris Removal: Current Status of Activities in CNES

    NASA Astrophysics Data System (ADS)

    Bonnal, Christophe; Ruault, Jean-Marc; Desjean, Marie-Christine

    2013-08-01

    Most of the ongoing studies led at worldwide level, mainly through IADC Actions, conclude that in order to keep a stable Low Earth Orbit environment in the coming decades, it may be necessary to retrieve some 5 to 10 large objects annually. These operations, known as Active Debris Removal (ADR), raise a huge amount of difficulties in numerous domains: political, legal, insurance, defense, financing and, last but not least, technical questions. The current paper aims at reviewing the current status of the ADR activities led by CNES both at National and Multi-lateral level. The first question which is raised is that of the high level requirements to be applied. What are the requirements coming from the operators; do we want to stabilize the environment, decrease it or could we accept some increase over the years; when do we have to act; can we baseline random reentry of such large objects or do we have to stick to controlled destructive reentries?… There may not yet be clear answers to these points, so efforts at international level are required. The second part of the paper deals with the potential solutions at system level. Numerous possibilities can be identified, depending on the size of the launcher and of the strategy selected to de-orbit the debris. Large space tugs visiting some 10 debris or small dedicated chasers launched as piggyback are among the solutions which have been traded. The currently preferred solution is described in details. The third part of the paper is devoted to the chaser-debris operations themselves, following five key functions; - the long range rendezvous, - the short range rendezvous up to contact, - the mechanical interfacing of the debris, - its control by the chaser, when required, - the de-orbiting maneuver itself. For each of these functions, the current status of available technologies is described, enabling the identification of the most critical ones requiring additional R&T effort and subsequent demonstrations. Among them

  11. Effects of Low Activity Solar Cycle on Orbital Debris Lifetime

    NASA Technical Reports Server (NTRS)

    Cable, Samual B.; Sutton, Eric K.; Lin, chin S.; Liou, J.-C.

    2011-01-01

    Long duration of low solar activity in the last solar minimum has an undesirable consequence of extending the lifetime of orbital debris. The AFRL TacSat-2 satellite decommissioned in 2008 has finally re-entered into the atmosphere on February 5th after more than one year overdue. Concerning its demise we have monitored its orbital decay and monthly forecasted Tacsat-2 re-entry since September 2010 by using the Orbital Element Prediction (OEP) model developed by the AFRL Orbital Drag Environment program. The model combines estimates of future solar activity with neutral density models, drag coefficient models, and an orbit propagator to predict satellite lifetime. We run the OEP model with solar indices forecast by the NASA Marshall Solar Activity Future Estimation model, and neutral density forecast by the MSIS-00 neutral density model. Based on the two line elements in 2010 up to mid September, we estimated at a 50% confidence level TacSat-2's re-entry time to be in early February 2011, which turned out to be in good agreement with Tacsat-2's actual re-entry date. The potential space weather effects of the coming low activity solar cycle on satellite lifetime and orbital debris population are examined. The NASA long-term orbital debris evolutionary model, LEGEND, is used to quantify the effects of solar flux on the orbital debris population in the 200-600 km altitude environment. The results are discussed for developing satellite orbital drag application product.

  12. Active debris removal of multiple priority targets

    NASA Astrophysics Data System (ADS)

    Braun, Vitali; Lüpken, A.; Flegel, S.; Gelhaus, J.; Möckel, M.; Kebschull, C.; Wiedemann, C.; Vörsmann, P.

    2013-05-01

    Today's space debris environment shows major concentrations of objects within distinct orbital regions for nearly all size regimes. The most critical region is found at orbital altitudes near 800 km with high declinations. Within this region many satellites are operated in so called sun-synchronous orbits (SSO). Among those, there are Earth observation, communication and weather satellites. Due to the orbital geometry in SSO, head-on encounters with relative velocities of about 15 km/s are most probable and would thus result in highly energetic collisions, which are often referred to as catastrophic collisions, leading to the complete fragmentation of the participating objects. So called feedback collisions can then be triggered by the newly generated fragments, thus leading to a further population increase in the affected orbital region. This effect is known as the Kessler syndrome.Current studies show that catastrophic collisions are not a major problem today, but will become the main process for debris generation within the SSO region in the near future, even without any further launches. In order to avoid this effect, objects with a major impact on collisional cascading have to be actively removed from the critical region after their end of life. Not having the capability to perform an end-of-life maneuver in order to transfer to a graveyard orbit or to de-orbit, many satellites and rocket bodies would have to be de-orbited within a dedicated mission. In such a mission, a service satellite would perform a de-orbit maneuver, after having docked to a specific target.In this paper, chemical and electric propulsion systems were analysed with the main focus on removing multiple targets within one single mission. The targets were chosen from a previously defined priority list in order to enhance the mission efficiency. Total mission time, ΔV and system mass were identified as key parameters to allow for an evaluation of the different concepts. It was shown that it

  13. EDDE, ElectroDynamic Debris Eliminator: New Frontiers in Space Traffic Management

    NASA Astrophysics Data System (ADS)

    Pearson, Jerome; Levin, Eugene; Oldson, John; Carroll, Joseph

    2010-09-01

    The ElectroDynamic Debris Eliminator(EDDE) is a solar-powered propellantless space vehicle that can change its altitude by hundreds of kilometers per day and its orbital plane by degrees per day. It can thrust constantly, producing hundreds of kilometers per second delta-V in years of active maneuvering. A dozen EDDE vehicles could remove all of the 2,500 dangerous debris objects over 2 kg from LEO orbits in less than 7 years and make LEO much safer for the operational spacecraft. To support operations of new kinds of space vehicles like EDDE, space traffic management must be taken to a new level, because these vehicles have to constantly maneuver between the orbits of multiple operational satellites and debris objects, making the space traffic picture very dynamic. Flight tests are planned to demonstrate orbit changes and to evaluate and improve tracking, navigation and control methods.

  14. Evaluation of a satellite constellation for active debris removal

    NASA Astrophysics Data System (ADS)

    Sahara, Hironori

    2014-12-01

    This paper analyzes an example of a three-dimensional constellation of debris removal satellites and proposes an effective constellation using a delta-V analysis that discusses the advisability of rendezvousing satellites with space debris. Lambert's Equation was used to establish a means of analysis to construct a constellation of debris removal satellites, which has a limit of delta-V injection by evaluating the amount of space debris that can be rendezvoused by a certain number of removal satellite. Consequently, we determine a constellation of up to 38 removal satellites for debris removal, where the number of space debris rendezvoused by a single removal satellite is not more than 25, removing up to 584 pieces of debris total. Even if we prepare 38 removal satellites in their respective orbits, it is impossible to remove all of the space debris. Although many removal satellites, over 100 for example, can remove most of the space debris, this method is economically disproportionate. However, we can also see the removal satellites are distributed nearly evenly. Accordingly, we propose a practical two-stage strategy. The first stage is to implement emergent debris removal with the 38 removal satellites. When we find a very high probability of collision between a working satellite and space debris, one of the removal satellites in the constellation previously constructed in orbit initiates a maneuver of emergent debris removal. The second stage is a long-term space debris removal strategy to suppress the increase of space debris derived from collisions among the pieces of space debris. The constellation analyzed in this paper, which consists of the first 38 removal satellites, can remove half of the over 1000 dangerous space debris among others, and then the constellation increases the number of the following removal satellites in steps. At any rate, an adequate orbital configuration and constellation form is very important for both space debris removal and

  15. Active debris removal: Recent progress and current trends

    NASA Astrophysics Data System (ADS)

    Bonnal, Christophe; Ruault, Jean-Marc; Desjean, Marie-Christine

    2013-04-01

    According to all available findings at international level, the Kessler syndrome, increase of the number of space debris in Low Earth Orbits due to mutual collisions, appears now to be a fact, triggered mainly by several major break-ups in orbit which occurred since 2007. The time may have come to study how to clean this fundamentally useful orbital region in an active way. CNES has studied potential solutions for more than 12 years! The paper aims at reviewing the current status of these activities. The high level requirements are fundamental, and have to be properly justified. The working basis, as confirmed through IADC studies consists in the removal of 5-10 integer objects from the overcrowded orbits, spent upper stages or old satellites, as identified by NASA. The logic of CNES activities consider a stepped approach aiming at progressively gaining the required Technological Readiness Level on the features required for Active Debris Removal which have not yet been demonstrated in orbit. The rendezvous with a non-cooperative, un-prepared, tumbling debris is essential. Following maturation gained with Research and Technology programs, a set of small orbital demonstrators could enable a confidence high enough to perform a full end to end demonstration performing the de-orbiting of a large debris and paving the way for the development of a first generation operational de-orbiter. The internal CNES studies, led together by the Toulouse Space Centre and the Paris Launcher Directorate, have started in 2008 and led to a detailed System Requirements Document used for the Industrial studies. Three industrial teams did work under CNES contract during 2011, led by Thales Alenia Space, Bertin Technologies and Astrium Space Transportation, with numerous sub-contractors. Their approaches were very rich, complementary, and innovative. The second phase of studies began mid-2012. Some key questions nevertheless have to be resolved, and correspond generally to current IADC

  16. Impacts of nuclear power sources on space debris

    SciTech Connect

    Grinberg, Eduard I.; Doschatov, Vitali V.; Nikolaev, Vadim S.; Sokolov, Nikolai A.; Nazarenko, Andrei I.; Usov, Veniamin A.

    1997-01-10

    The paper presents some results of efforts dealing with computational analyses of probability of impact of nuclear power sources (NPS) on space debris (SD), destruction of the NPS structure on the impacts, change in orbital parameters as a result of the NPS impact and reentry.

  17. The Space Shuttle Columbia Preservation Project - The Debris Loan Process

    NASA Technical Reports Server (NTRS)

    Thurston, Scott; Comer, Jim; Marder, Arnold; Deacon, Ryan

    2005-01-01

    The purpose of this project is to provide a process for loan of Columbia debris to qualified researchers and technical educators to: (1) Aid in advanced spacecraft design and flight safety development (2) Advance the study of hypersonic re-entry to enhance ground safety. (3) Train and instruct accident investigators and (4) Establish an enduring legacy for Space Shuttle Columbia and her crew.

  18. Harnessing Adaptive Optics for Space Debris Collision Mitigation

    NASA Astrophysics Data System (ADS)

    Zovaro, A.; Bennet, F.; Copeland, M.; Rigaut, F.; d'Orgeville, C.; Grosse, D.

    2016-09-01

    Human kind's continued use of space depends upon minimising the build-up of debris in low Earth-orbit (LEO). Preventing collisions between satellites and debris is essential given that a single collision can generate thousands of new debris objects. However, in-orbit manoeuvring of satellites is extremely expensive and shortens their operational life. Adjusting the orbits of debris objects instead of satellites would shift the responsibility of collision avoidance away from satellite operators altogether, thereby offering a superior solution. The Research School of Astronomy and Astrophysics at the Australian National University, partnered with Electro Optic Systems (EOS) Space Systems, Lockheed Martin Corporation and the Space Environment Research Centre (SERC) Limited, are developing the Adaptive Optics Tracking and Pushing (AOTP) system. AOTP will be used to perturb the orbits of debris objects using photon pressure from a 10 kW IR laser beam launched from the 1.8 m telescope at Mount. Stromlo Observatory, Australia. Initial simulations predict that AOTP will be able to displace debris objects 10 cm in size by up to 100 m with several overhead passes. An operational demonstrator is planned for 2019. Turbulence will distort the laser beam as it propagates through the atmosphere, resulting in a lower photon flux on the target and reduced pointing accuracy. To mitigate these effects, adaptive optics (AO) will be used to apply wavefront correction to the beam prior to launch. A unique challenge in designing the AO system arises from the high slew rate needed to track objects in LEO, which in turn requires laser guide star AO for satisfactory wavefront correction. The optical design and results from simulations of estimated performance of AOTP will be presented. In particular, design considerations associated with the high-power laser will be detailed.

  19. Space borne photometry perturbations from solar light scatterd by debris

    NASA Astrophysics Data System (ADS)

    Mandeville, Jean-Claude; Perrin, Jean-Marie; Vuillemin, André

    2001-10-01

    We study the possible impairment of the solar light scattered by small debris, measured by high photometric quality instrument, during space borne observations. We compute the contribution of the fragments released on orbit by the host satellite and of the debris already present in the background. Preliminary results show that these spurious fluxes can reach the level of the collected Zodiacal Light: there are the main components of the noise level which affect the scientific signal. On the future, threats on high sensitivity photometric missions should rise with the increasing launches of satellite constellations if no legislation controls the design of satellites.

  20. Threats to U.S. National Security Interests in Space: Orbital Debris Mitigation and Removal

    DTIC Science & Technology

    2014-01-08

    platforms in space from collisions with orbital debris . Some experts maintain the population growth of debris in space will be primarily driven by catastrophic collisions that are likely to occur every five to nine years.

  1. Eliminating Space Debris: Applied Technology and Policy Prescriptions, Fall 2007 - Project 07-02

    DTIC Science & Technology

    2008-01-01

    DEBRIS POPULATION: 2007 ORBITAL DEBRIS EVENTS .................................. 21 Anti-satellite Missile Test (China...48 DOMESTIC POLICY: U.S. ORBITAL DEBRIS GUIDELINES...tackling the problems associated with orbital debris and remediation of the space environment. The lack of any existing elimination (clean-up) mechanism

  2. Modeling the long-term evolution of space debris

    DOEpatents

    Nikolaev, Sergei; De Vries, Willem H.; Henderson, John R.; Horsley, Matthew A.; Jiang, Ming; Levatin, Joanne L.; Olivier, Scot S.; Pertica, Alexander J.; Phillion, Donald W.; Springer, Harry K.

    2017-03-07

    A space object modeling system that models the evolution of space debris is provided. The modeling system simulates interaction of space objects at simulation times throughout a simulation period. The modeling system includes a propagator that calculates the position of each object at each simulation time based on orbital parameters. The modeling system also includes a collision detector that, for each pair of objects at each simulation time, performs a collision analysis. When the distance between objects satisfies a conjunction criterion, the modeling system calculates a local minimum distance between the pair of objects based on a curve fitting to identify a time of closest approach at the simulation times and calculating the position of the objects at the identified time. When the local minimum distance satisfies a collision criterion, the modeling system models the debris created by the collision of the pair of objects.

  3. The International Space Station and the Space Debris Environment: 10 Years On

    NASA Astrophysics Data System (ADS)

    Johnson, Nicholas

    2009-03-01

    For just over a decade the International Space Station (ISS), the most heavily protected vehicle in Earth orbit, has weathered the space debris environment well. Numerous hypervelocity impact features on the surface of ISS caused by small orbital debris and meteoroids have been observed. In addition to typical impacts seen on the large solar arrays, craters have been discovered on windows, hand rails, thermal blankets, radiators, and even visiting logistics modules. None of these impacts have resulted in any degradation of the operation or mission of the ISS. Inadvertently and deliberately, the ISS has also been the source of space debris, although these objects typically exhibit very short orbital lifetimes.

  4. Projectile Shape Effects Analysis for Space Debris Impact

    NASA Astrophysics Data System (ADS)

    Shiraki, Kuniaki; Yamamoto, Tetsuya; Kamiya, Takeshi

    2002-01-01

    (JEM IST), has a manned pressurized module used as a research laboratory on orbit and planned to be attached to the International Space Station (ISS). Protection system from Micrometeoroids and orbital debris (MM/OD) is very important for crew safety aboard the ISS. We have to design a module with shields attached to the outside of the pressurized wall so that JEM can be protected when debris of diameter less than 20mm impact on the JEM wall. In this case, the ISS design requirement for space debris protection system is specified as the Probability of No Penetration (PNP). The PNP allocation for the JEM is 0.9738 for ten years, which is reallocated as 0.9814 for the Pressurized Module (PM) and 0.9922 for the Experiment Logistics Module-Pressurized Section (ELM-PS). The PNP is calculated with Bumper code provided by NASA with the following data inputs to the calculation. (1) JEM structural model (2) Ballistic Limit Curve (BLC) of shields pressure wall (3) Environmental conditions: Analysis type, debris distribution, debris model, debris density, Solar single aluminum plate bumper (1.27mm thickness). The other is a Stuffed Whipple shield with its second bumper composed of an aluminum mesh, three layers of Nextel AF62 ceramic fabric, and four layers of Kevlar 710 fabric with thermal isolation material Multilayer Insulation (MLI) in the bottom. The second bumper of Stuffed Whipple shields is located at the middle between the first bumper and the 4.8 mm-thick pressurized wall. with Two-Stage Light Gas Gun (TSLGG) tests and hydro code simulation already. The remaining subject is the verification of JEM debris protection shields for velocities ranging from 7 to 15 km/sec. We conducted Conical Shaped Charge (CSC) tests that enable hypervelocity impact tests for the debris velocity range above 10 km/sec as well as hydro code simulation. because of the jet generation mechanism. It is therefore necessary to analyze and compensate the results for a solid aluminum sphere, which

  5. Space Debris Optical Observation System in JAXA/IAT

    NASA Astrophysics Data System (ADS)

    Nakajima, A.; Kurosaki, H.; Fukaya, T.

    For the development of the optical observation technologies for space debris, Institute of Aerospace Technology(IAT) of JAXA has prepared two small optical observation facilities of LEO and GEO debris detections. LEO debris tracking facility is located at HQ of JAXA, Tokyo, with a 35cm telescope onboard the 3-axis tracking mount system, GEO debris observation facility is located at Nyukasa-yama mountain in Nagano Prefecture. A 35cm Newtonian optical telescope with 2K2K CCD camera and a 25cm BRC optical telescope with 4K4K CCD camera are supported on each equatorial mount system. The latter facility is under construction and will be operated within this autumn. The altitude of this site is 1,860m and the optical environment will be adequate for detecting faint objects. One of the most important study item in our R&D is to develop an automatic small size GEO debris detection software. In usual case, a long exposure time is necessary to detect a faint object by accumulating weak light energy during the time. On the contrary, short exposure observation is necessary for GEO debris detection to avoid the influence of the fixed star streaks image. We have proposed a stacking method for detecting a noise-level faint GEO debris by accumulating the signals of a number of images, for example, a hundred frames. By applying the stacking method for asteroid survey observation, 21st magnitude asteroid can be detected by using this small telescope. Another research item is to develop a high-speed read/write CCD camera. High efficiency back illuminated 1K1K and 2K2K CCD cameras were developed and 4K4K CCD camera is under testing. The read/write time of the 4K4K CCD camera is about 10 seconds, which is cooled by a sterling engine refrigerator. This paper introduces the JAXA's facilities for LEO and GEO space debris observation and describes some developing technologies and evaluated results.

  6. The impact of the atmospheric model and of the space weather data on the dynamics of clouds of space debris

    NASA Astrophysics Data System (ADS)

    Petit, Alexis; Lemaitre, Anne

    2016-06-01

    New tools are necessary to deal with more than hundred thousands of space debris, thus our aim is to develop software able to propagate numerous trajectories and manage collisions or fragmentations. Specifically in low orbits Earth, gravity and atmospheric drag are the two main forces that affect the dynamics of the artificial satellites or space debris. NIMASTEP, the local orbit propagator, initially designed for high altitudes, has been adapted to low altitude orbits. To study the future debris environment, we propose a suitable model of space weather and we compare three different atmospheric density models (Jacchia-Bowman 2008, DTM-2013, and TD-88) able to propagate with accuracy and efficiency a large population of space debris on long time scales. We compare the results in different altitudes and during the reentry regime; we show, with a ballistic coefficient constant, a trend to underestimate or overestimate the decrease of the semi-major axis, specifically during the periods of high solar activity. We parallelize our software and use the calculation power of a computing cluster, we propagate a huge cloud of debris and we show that its global evolution is in agreement with the observations on several years.

  7. Electromagnetic absorption properties of spacecraft and space debris

    NASA Astrophysics Data System (ADS)

    Micheli, D.; Santoni, F.; Giusti, A.; Delfini, A.; Pastore, R.; Vricella, A.; Albano, M.; Arena, L.; Piergentili, F.; Marchetti, M.

    2017-04-01

    Aim of the work is to present a method to evaluate the electromagnetic absorption properties of spacecraft and space debris. For these objects, the radar detection ability depends mainly on volume, shape, materials type and other electromagnetic reflecting behaviour of spacecraft surface components, such as antennas or thermal blankets, and of metallic components in space debris. The higher the electromagnetic reflection coefficient of such parts, the greater the radar detection possibility. In this research an electromagnetic reverberation chamber is used to measure the absorption cross section (ACS) of four objects which may represent space structure operating components as well as examples of space debris: a small satellite, a composite antenna dish, a Thermal Protection System (TPS) tile and a carbon-based composite missile shell. The ACS mainly depends on geometrical characteristics like apertures, face numbers and bulk porosity, as well as on the type of the material itself. The ACS, which is an electromagnetic measurement, is expressed in squared meters and thus can be compared with the objects geometrical cross section. A small ACS means a quite electromagnetic reflective tendency, which is beneficial for radar observations; on the contrary, high values of ACS indicate a strong absorption of the electromagnetic field, which in turn can result a critical hindering of radar tracking.

  8. Real Time Polarization Light Curves for Space Debris and Satellites

    NASA Astrophysics Data System (ADS)

    Stryjewski, J.; Hand, D.; Tyler, D.; Murali, S.; Roggemann, M.; Peterson, N.

    2010-09-01

    In recent years there as been a lot of interest in using the time history of re_ected solar light (light curves) from satellites and space debris as a means of determining shape and material composition. Most of these studies used time series analysis in an attempt to classify objects while some have used multi-spectral or spectroscopic approaches. One of the difficulties that most of these approaches had was the lack of high fidelity shape and material modeling. Here we present a high fidelity modeling approach that correctly describes the shape, material and dynamics of space objects. Furthermore, this model, in real time, correctly models reflection, emission, glint and polarization effects. We use this model to show how detection of polarization effects can help characterize both satellites and space debris. Polarization approaches have an advantage over spectroscopic or intensity based method because polarization is unaffected by the atmosphere. We present a comparison of polarization approaches for the analysis of space debris and satellites and discuss the advantages of being able to do these calculations in real time.

  9. National Standard of the Russian Federation for Space Debris Mitigation

    NASA Astrophysics Data System (ADS)

    Loginov, S.; Yakovlev, M.; Mikhailov, M.; Popkova, L.

    2009-03-01

    Normative and technical document that define requirements for the mitigation of human-produced near-earth space pollution develops in Russian Federation.NATIONAL STANDARD of the Russian Federation GOST R 52925-2008 «SPACE TECHNOLOGY ITEMS. General Requirements on Space Systems for the Mitigation of Human-Produced near-Earth Space Pollution» was approved in 2008 and entered into force since 1st January of 2009. Requirements of this standard harmonized with requirements of «UN SPACE DEBRIS MITIGATION GUIDELINESÈ»This standard consists of six parts:- Scope;- References to Standards;- Terms & Definitions;- Abbreviations;- General Provisions;- General Requirements on Space Systems for the Mitigation of Human-Produced near-Earth Space Pollution.

  10. A Numerical Approach to Estimate the Ballistic Coefficient of Space Debris from TLE Orbital Data

    NASA Technical Reports Server (NTRS)

    Narkeliunas, Jonas

    2016-01-01

    Low Earth Orbit (LEO) is full of space debris, which consist of spent rocket stages, old satellites and fragments from explosions and collisions. As of 2009, more than 21,000 orbital debris larger than 10 cm are known to exist], and while it is hard to track anything smaller than that, the estimated population of particles between 1 and 10 cm in diameter is approximately 500,000, whereas small as 1 cm exceeds 100 million. These objects orbit Earth with huge kinetic energies speeds usually exceed 7 kms. The shape of their orbit varies from almost circular to highly elliptical and covers all LEO, a region in space between 160 and 2,000 km above sea level. Unfortunately, LEO is also the place where most of our active satellites are situated, as well as, International Space Station (ISS) and Hubble Space Telescope, whose orbits are around 400 and 550 km above sea level, respectively.This poses a real threat as debris can collide with satellites and deal substantial damage or even destroy them.Collisions between two or more debris create clouds of smaller debris, which are harder to track and increase overall object density and collision probability. At some point, the debris density couldthen reach a critical value, which would start a chain reaction and the number of space debris would grow exponentially. This phenomenon was first described by Kessler in 1978 and he concluded that it would lead to creation of debris belt, which would vastly complicate satellite operations in LEO. The debris density is already relatively high, as seen from several necessary debris avoidance maneuvers done by Shuttle, before it was discontinued, and ISS. But not all satellites have a propulsion system to avoid collision, hence different methods need to be applied. One of the proposed collision avoidance concepts is called LightForce and it suggests using photon pressure to induce small orbital corrections to deflect debris from colliding. This method is very efficient as seen from

  11. Laser Ranging on Space Debris with the Changchun SLR Station

    NASA Astrophysics Data System (ADS)

    Liu, Chengzhi

    2015-08-01

    The Changchun SLR station has upgraded to track space debris in 2014. The system operates with a 60mJ/10ns/500Hz 532.0nm laser (M2<1.5) and an optical camera for closed-loop tracking. With this configuration, 466 passes of 224 different space debris targets were obtained during 19 terminator sessions, each about 1.5h. Target distances are between 460 km and 1800 km, with RCS (radar cross sections) from >15 m2 down to <1.0 m2. Measured range had an average precision of about 1.0 m RMS. The system can be conveniently operated by one person. The presentation will introduce the technical developments and the observation results obtained. By analyzing the laser range data, range residual of about 1~2 meters is obtained.

  12. A space debris simulation facility for spacecraft materials evaluation

    NASA Technical Reports Server (NTRS)

    Taylor, Roy A.

    1987-01-01

    A facility to simulate the effects of space debris striking an orbiting spacecraft is described. This facility was purchased in 1965 to be used as a micrometeoroid simulation facility. Conversion to a Space Debris Simulation Facility began in July 1984 and it was placed in operation in February 1985. The facility consists of a light gas gun with a 12.7-mm launch tube capable of launching 2.5-12.7 mm projectiles with a mass of 4-300 mg and velocities of 2-8 km/sec, and three target tanks of 0.067 m, 0.53 a m and 28.5 a m. Projectile velocity measurements are accomplished via pulsed X-ray, laser diode detectors, and a Hall photographic station. This facility is being used to test development structural configurations and candidate materials for long duration orbital spacecraft. A summary of test results are also described.

  13. Momentum Transfer by Laser Ablation of Irregularly Shaped Space Debris

    SciTech Connect

    Liedahl, Duane A.; Libby, Stephen B.; Rubenchik, Alexander

    2010-10-08

    Proposals for ground-based laser remediation of space debris rely on the creation of appropriately directed ablation-driven impulses to either divert the fragment or drive it into an orbit with a perigee allowing atmospheric capture. For a spherical fragment, the ablation impulse is a function of the orbital parameters and the laser engagement angle. If, however, the target is irregularly shaped and arbitrarily oriented, new impulse effects come into play. Here we present an analysis of some of these effects.

  14. Momentum Transfer by Laser Ablation of Irregularly Shaped Space Debris

    SciTech Connect

    Liedahl, D A; Libby, S B; Rubenchik, A

    2010-02-04

    Proposals for ground-based laser remediation of space debris rely on the creation of appropriately directed ablation-driven impulses to either divert the fragment or drive it into an orbit with a perigee allowing atmospheric capture. For a spherical fragment, the ablation impulse is a function of the orbital parameters and the laser engagement angle. If, however, the target is irregularly shaped and arbitrarily oriented, new impulse effects come into play. Here we present an analysis of some of these effects.

  15. Orbital Debris: A Chronology

    NASA Technical Reports Server (NTRS)

    Portree, Davis S. F. (Editor); Loftus, Joseph P., Jr. (Editor)

    1999-01-01

    This chronology covers the 37-year history of orbital debris concerns. It tracks orbital debris hazard creation, research, observation, experimentation, management, mitigation, protection, and policy. Included are debris-producing, events; U.N. orbital debris treaties, Space Shuttle and space station orbital debris issues; ASAT tests; milestones in theory and modeling; uncontrolled reentries; detection system development; shielding development; geosynchronous debris issues, including reboost policies: returned surfaces studies, seminar papers reports, conferences, and studies; the increasing effect of space activities on astronomy; and growing international awareness of the near-Earth environment.

  16. Laser measurements to space debris from Graz SLR station

    NASA Astrophysics Data System (ADS)

    Kirchner, Georg; Koidl, Franz; Friederich, Fabian; Buske, Ivo; Völker, Uwe; Riede, Wolfgang

    2013-01-01

    In order to test laser ranging possibilities to space debris objects, the Satellite Laser Ranging (SLR) Station Graz installed a frequency doubled Nd:YAG pulse laser with a 1 kHz repetition rate, a pulse width of 10 ns, and a pulse energy of 25 mJ at 532 nm (on loan from German Aerospace Center Stuttgart - DLR). We developed and built low-noise single-photon detection units to enable laser ranging to targets with inaccurate orbit predictions, and adapted our standard SLR software to include a few hundred space debris targets. With this configuration, we successfully tracked - within 13 early-evening sessions of each about 1.5 h - 85 passes of 43 different space debris targets, in distances between 600 km and up to more than 2500 km, with radar cross sections from >15 m2 down to <0.3 m2, and measured their distances with an average precision of about 0.7 m RMS.

  17. Space Station: Delays in dealing with space debris may reduce safety and increase costs

    NASA Astrophysics Data System (ADS)

    1992-06-01

    The majority of NASA's current designs for protecting the space station and crew from debris are outdated and its overall debris protection strategy is insufficient. NASA's contractors have designed the station using a 1984 model of the space environment that is obsolete, significantly underestimating the increasing amount of debris that the station will encounter during its 30-year lifetime. In February 1992, NASA directed its space centers to incorporate an updated 1991 model into their designs. However, the agency has not yet made critical decisions on how to implement this change. Preliminary evaluations show that incorporating the 1991 model using currently established safety criteria could entail a major redesign of some components, with significant cost impact and schedule delays. NASA's overall protection strategy for space debris is insufficient. While NASA has concentrated its protection on shielding the space station from small debris and plans to augment this initial shielding in orbit, it has not yet developed designs or studied the cost and operational impact of augmenting its protection with additional shielding. Further, current designs do not provide the capability of warning or protecting the crew from imminent collision with mid-size debris. Finally, although some capabilities exist for maneuvering the station away from large debris, the agency lacks collision-avoidance plans and debris-tracking equipment. In developing a comprehensive strategy to protect the station from the more severe debris environment, NASA cannot avoid some difficult decisions. These decisions involve tradeoffs between how much the agency is willing to pay to protect the station, the schedule delays it may incur, and the risk to station safety it is willing to accept. It is important that these decisions be made before NASA completes its critical design reviews in early 1993. At that time key designs will be made final and manufacturing will begin. Without a comprehensive

  18. Meteoroid and space debris impacts in grazing-incidence telescopes

    NASA Astrophysics Data System (ADS)

    Carpenter, J. D.; Wells, A.; Abbey, A. F.; Ambrosi, R. M.

    2008-06-01

    Context: Micrometeoroid or space debris impacts have been observed in the focal planes of the XMM-Newton and Swift-XRT (X-ray Telescope) X-ray observatories. These impacts have resulted in damage to, and in one case the failure of, focal-plane Charge-Coupled Device (CCDs) detectors. Aims: We aim to quantify the future risks of focal-plane impacts in present and future X-ray observatories. Methods: We present a simple model for the propagation of micrometeoroids and space debris particles into telescopes with grazing-incidence X-ray optics, which is based on the results of previous investigations into grazing-incidence hypervelocity impacts by microscopic particles. We then calculate micrometeoroid and space debris fluxes using the Micrometeoroid and Space Debris Terrestrial Environment Reference model (MASTER2005). The risks of future focal-plane impact events in three present (Swift-XRT, XMM-Newton, and Chandra) and two future (SIMBOL-X and XEUS) X-ray observatories are then estimated on the basis of the calculated fluxes and the model for particle propagation. Results: The probabilities of at least one impact occurring in the Swift-XRT, XMM-Newton, and Chandra focal planes, in a one year period from the time of writing in November 2007 are calculated to be ~5% and ~50% and ~3%. First-order predictions of the impact rates expected for the future SIMBOL-X and XEUS X-ray observatories yield probabilities for at least one focal-plane impact, during nominal 5-year missions, of more than 94% and 99%, respectively. Conclusions: The propagation of micrometeoroids and space debris particles into the focal planes of X-ray telescopes is highest for Wolter optics with the largest collecting areas and the lowest grazing angles. Telescopes in low-Earth orbits encounter enhanced particle fluxes compared with those in higher orbits and a pointing avoidance strategy for certain directions can reduce the risk of impacts. Future X-ray observatories, with large collecting areas and

  19. Debris Mitigation as a Component of Space Traffic Management

    NASA Astrophysics Data System (ADS)

    Kemper Force, M.

    2012-01-01

    The necessity of a traffic management in space is a consequence of our "free use" of it over the past fifty years, during which certain orbits have accumulated a significant amount of debris that may, in the future, threaten the feasibility of their use. This paper encapsulates the primary issues involved in the concept of space traffic management through basic questions, using as a case study the recent alarm caused by two close-misses of the ISS in one week, in order to guide the reader to an understanding of the current need for a space traffic management regime. The paper will describe the fundamental elements of space traffic management, including the tracking of objects, conjunction assessment, collision avoidance and orbital mechanics to understand why Earth-bound systems cannot be extrapolated to space. The paper will then focus on the primary concern of space debris, the acceptance and use of current guidelines in light of the existing corpus juris spatialis and international law, positing that the guidelines may soon develop into a customary norm. The paper will conclude that the latest close calls with the ISS demonstrate we cannot count on the mere vastness of space to reduce the probability of collisions with space objects. Despite the significant political, technical and economic challenges recognized by the International Space University Final Report of 2007, the International Academy of Astronautics' Cosmic Study of 2006 and the IAASS An ICAO for Space?, there is a need for a system to obviate the looming peril before governments and investors will sign on to a comprehensive program which limits their "free" use of space.

  20. Characterizing the Space Debris Environment with a Variety of SSA Sensors

    NASA Astrophysics Data System (ADS)

    Stansbery, Eugene

    Damaging space debris spans a wide range of sizes and altitudes. Therefore no single method or sensor can fully characterize the space debris environment. Space debris researchers use a variety of radars and optical telescopes to characterize the space debris environment in terms of number, altitude, and inclination distributions. Some sensors, such as phased array radars, are designed to search a large volume of the sky and can be instrumental in detecting new breakups and cataloging and precise tracking of relatively large debris. For smaller debris sizes more sensitivity is needed which can be provided, in part, by large antenna gains. Larger antenna gains, however, produce smaller fields of view. Statistical measurements of the debris environment with less precise orbital parameters result. At higher altitudes, optical telescopes become the more sensitive instrument and present their own measurement difficulties. Space Situational Awareness, or SSA, is concerned with more than the number and orbits of satellites. SSA also seeks to understand such parameters as the function, shape, and compo-sition of operational satellites. Similarly, debris researchers are seeking to characterize similar parameters for space debris to improve our knowledge of the risks debris poses to operational satellites as well as determine sources of debris for future mitigation. This paper will discuss different sensor and sensor types and the role that each plays in fully characterizing the space debris environment.

  1. Characterizing the Space Debris Environment with a Variety of SSA Sensors

    NASA Technical Reports Server (NTRS)

    Stansbery, Eugene G.

    2010-01-01

    Damaging space debris spans a wide range of sizes and altitudes. Therefore no single method or sensor can fully characterize the space debris environment. Space debris researchers use a variety of radars and optical telescopes to characterize the space debris environment in terms of number, altitude, and inclination distributions. Some sensors, such as phased array radars, are designed to search a large volume of the sky and can be instrumental in detecting new breakups and cataloging and precise tracking of relatively large debris. For smaller debris sizes more sensitivity is needed which can be provided, in part, by large antenna gains. Larger antenna gains, however, produce smaller fields of view. Statistical measurements of the debris environment with less precise orbital parameters result. At higher altitudes, optical telescopes become the more sensitive instrument and present their own measurement difficulties. Space Situational Awareness, or SSA, is concerned with more than the number and orbits of satellites. SSA also seeks to understand such parameters as the function, shape, and composition of operational satellites. Similarly, debris researchers are seeking to characterize similar parameters for space debris to improve our knowledge of the risks debris poses to operational satellites as well as determine sources of debris for future mitigation. This paper will discuss different sensor and sensor types and the role that each plays in fully characterizing the space debris environment.

  2. Analysis of debris from Spacelab Space Life Sciences-1

    NASA Technical Reports Server (NTRS)

    Caruso, S. V.; Rodgers, E. B.; Huff, T. L.

    1992-01-01

    Airborne microbiological and particulate contamination generated aboard Spacelab modules is a potential safety hazard. In order to shed light on the characteristics of these contaminants, microbial and chemical/particulate analyses were performed on debris vacuumed from cabin and avionics air filters in the Space Life Sciences-1 (SLS-1) module of the Space Transportation System 40 (STS-40) mission 1 month after landing. The debris was sorted into categories (e.g., metal, nonmetal, hair/fur, synthetic fibers, food particles, insect fragments, etc.). Elemental analysis of particles was done by energy dispersive analysis of x rays (metals) and Fourier transform infrared spectroscopy (nonmetals). Scanning electron micrographs were done of most particles. Microbiological samples were grown on R2A culture medium and identified. Clothing fibers dominated the debris by volume. Other particles, all attributed to the crew, resulted from abrasions and impacts during missions operations (e.g., paint chips, plastic, electronic scraps and clothing fibers). All bacterial species identified are commonly found in the atmosphere or on the human body. Bacillus sp. was the most frequently seen bacterium. One of the bacterial species, Enterobacter agglomerans, could cause illness in crew members with depressed immune systems.

  3. Using Lasers in Space: Laser Orbital Debris Removal and Asteroid Deflection

    DTIC Science & Technology

    2000-12-01

    Orbital debris in tow-Earth orbit ranging in size from 1 to 10 centimeters (cm) in diameter, poses a significant problem for space vehicles. While...ablate or vaporize the surface of orbital debris , thereby producing enough cumulative thrust to cause debris to reenter the atmosphere. One laser facility...favorable in comparison with the typical costs OR SPACECRAFT OPERATIONS. Orbital debris is not the only form of space junk that is deleterious to the Earth

  4. Adaptive control for space debris removal with uncertain kinematics, dynamics and states

    NASA Astrophysics Data System (ADS)

    Huang, Panfeng; Zhang, Fan; Meng, Zhongjie; Liu, Zhengxiong

    2016-11-01

    As the Tethered Space Robot is considered to be a promising solution for the Active Debris Removal, a lot of problems arise in the approaching, capturing and removing phases. Particularly, kinematics and dynamics parameters of the debris are unknown, and parts of the states are unmeasurable according to the specifics of tether, which is a tough problem for the target retrieval/de-orbiting. This work proposes a full adaptive control strategy for the space debris removal via a Tethered Space Robot with unknown kinematics, dynamics and part of the states. First we derive a dynamics model for the retrieval by treating the base satellite (chaser) and the unknown space debris (target) as rigid bodies in the presence of offsets, and involving the flexibility and elasticity of tether. Then, a full adaptive controller is presented including a control law, a dynamic adaption law, and a kinematic adaption law. A modified controller is also presented according to the peculiarities of this system. Finally, simulation results are presented to illustrate the performance of two proposed controllers.

  5. Hubble Space Telescope Observations of the HD 202628 Debris Disk

    NASA Technical Reports Server (NTRS)

    Krist, John E.; Stapelfeldt, Karl R.; Bryden, Geoffrey; Plavchan, Peter

    2012-01-01

    A ring-shaped debris disk around the G2V star HD 202628 (d = 24.4 pc) was imaged in scattered light at visible wavelengths using the coronagraphic mode of the Space Telescope Imaging Spectrograph on the Hubble Space Telescope. The ring is inclined by approx.64deg from face-on, based on the apparent major/minor axis ratio, with the major axis aligned along PA = 130deg. It has inner and outer radii (> 50% maximum surface brightness) of 139 AU and 193 AU in the northwest ansae and 161 AU and 223 AU in the southeast ((Delta)r/r approx. = 0.4). The maximum visible radial extent is approx. 254 AU. With a mean surface brightnesses of V approx. = 24 mag arcsec.(sup -2), this is the faintest debris disk observed to date in reflected light. The center of the ring appears offset from the star by approx.28 AU (deprojected). An ellipse fit to the inner edge has an eccentricity of 0.18 and a = 158 AU. This offset, along with the relatively sharp inner edge of the ring, suggests the influence of a planetary-mass companion. There is a strong similarity with the debris ring around Fomalhaut, though HD 202628 is a more mature star with an estimated age of about 2 Gyr. We also provide surface brightness limits for nine other stars in our study with strong Spitzer excesses around which no debris disks were detected in scattered light (HD 377, HD 7590, HD 38858, HD 45184, HD 73350, HD 135599, HD 145229, HD 187897, and HD 201219).

  6. Active Polarimetry for Orbital Debris Identification

    NASA Astrophysics Data System (ADS)

    Pasqual, M.; Cahoy, C.

    We present the results of polarimetric measurements that may help remotely identify orbital debris fragments, thereby extending current space surveillance capabilities. A bench-top polarimeter (wavelength 1064 nm) was used to experimentally determine the polarimetric Bidirectional Reflectance Distribution Function (BRDF) of several common spacecraft materials and coatings, including glossy white paint, matte black paint, black Kapton®, silver Teflon®, aluminum, and titanium. Analysis of these measurements allowed us to estimate each material's Mueller matrix and associated polarimetric properties as a function of the incident angle and (bistatic) in-plane scatter angle. Results revealed notable trends in the materials' polarimetric signatures. Specifically, the materials exhibited mostly weak diattenuation (D < 0.5) in all scatter directions, except for Kapton® and the two paints (D > 0.5 in the forward scatter direction). In terms of retardance (R), silver Teflon® exhibited a finite range of values (R = 30 to 120º) in all directions, while the other materials acted as mirrors (R = 180º) in the back scatter direction and had the full range of behavior (R = 0 to 180º) in the forward scatter direction. Finally, in terms of depolarization power (Delta), glossy white paint was a nearly perfect depolarizer (Delta = 1) in the back scatter direction, but sharply lost depolarization power (Delta = 0) at specular reflection. All other materials were mostly weak depolarizers (Delta < 0.5) in all scatter directions. These experimental findings may be used to develop requirements for a polarimetric laser radar that can interrogate debris fragments, identify their constituent materials, and infer their masses and other characteristics of interest.

  7. The International Space Station and the Space Debris Environment: 10 Years On

    NASA Technical Reports Server (NTRS)

    Johnson, Nicholas; Klinkrad, Heiner

    2009-01-01

    For just over a decade the International Space Station (ISS), the most heavily protected vehicle in Earth orbit, has weathered the space debris environment well. Numerous hypervelocity impact features on the surface of ISS caused by small orbital debris and meteoroids have been observed. In addition to typical impacts seen on the large solar arrays, craters have been discovered on windows, hand rails, thermal blankets, radiators, and even a visiting logistics module. None of these impacts have resulted in any degradation of the operation or mission of the ISS. Validating the rate of small particle impacts on the ISS as predicted by space debris environment models is extremely complex. First, the ISS has been an evolving structure, from its original 20 metric tons to nearly 300 metric tons (excluding logistics vehicles) ten years later. Hence, the anticipated space debris impact rate has grown with the increasing size of ISS. Secondly, a comprehensive visual or photographic examination of the complete exterior of ISS has never been accomplished. In fact, most impact features have been discovered serendipitously. Further complications include the estimation of the size of an impacting particle without knowing its mass, velocity, and angle of impact and the effect of shadowing by some ISS components. Inadvertently and deliberately, the ISS has also been the source of space debris. The U.S. Space Surveillance Network officially cataloged 65 debris from ISS from November 1998 to November 2008: from lost cameras, sockets, and tool bags to intentionally discarded equipment and an old space suit. Fortunately, the majority of these objects fall back to Earth quickly with an average orbital lifetime of less than two months and a maximum orbital lifetime of a little more than 15 months. The cumulative total number of debris object-years is almost exactly 10, the equivalent of one piece of debris remaining in orbit for 10 years. An unknown number of debris too small to be

  8. Impact of the New Optimal Rules for Arbitration of Disputers Relating to Space Debris Controversies

    NASA Astrophysics Data System (ADS)

    Force, Melissa K.

    2013-09-01

    The mechanisms and procedures for settlement of disputes arising from space debris collision damage, such as that suffered by the Russian Cosmos and US Iridium satellites in 2009, are highly political, nonbinding and unpredictable - all of which contributes to the uncertainty that increases the costs of financing and insuring those endeavors that take place in near-Earth space, especially in Low Earth Orbit. Dispute settlement mechanisms can be found in the 1967 Outer Space Treaty, which provides for consultations in cases involving potentially harmful interference with activities of States parties, and in the 1972 Liability Convention which permits but does not require States - not non-governmental entities - to pursue claims in a resolution process that is nonbinding (unless otherwise agreed.) There are soft- law mechanisms to control the growth of space debris, such as the voluntary 2008 United Nations Space Debris Mitigation Guidelines, and international law and the principles of equity and justice generally provide reparation to restore a person, State or organization to the condition which would have existed if damage had not occurred, but only if all agree to a specific tribunal or international court; even then, parties may be bound by the result only if agreed and enforcement of the award internationally remains uncertain. In all, the dispute resolution process for damage resulting from inevitable future damage from space debris collisions is highly unsatisfactory. However, the Administrative Council of the Permanent Court of Arbitration's recently adopted Optional Rules for the Arbitration of Disputes Relating to Outer Space Activities are, as of yet, untested, and this article will provide an overview of the process, explore the ways in which they fill in gaps in the previous patchwork of systems and analyze the benefits and shortcomings of the new Outer Space Optional Rules.

  9. Target selection and comparison of mission design for space debris removal by DLR's advanced study group

    NASA Astrophysics Data System (ADS)

    van der Pas, Niels; Lousada, Joao; Terhes, Claudia; Bernabeu, Marc; Bauer, Waldemar

    2014-09-01

    Space debris is a growing problem. Models show that the Kessler syndrome, the exponential growth of debris due to collisions, has become unavoidable unless an active debris removal program is initiated. The debris population in LEO with inclination between 60° and 95° is considered as the most critical zone. In order to stabilize the debris population in orbit, especially in LEO, 5 to 10 objects will need to be removed every year. The unique circumstances of such a mission could require that several objects are removed with a single launch. This will require a mission to rendezvous with a multitude of objects orbiting on different altitudes, inclinations and planes. Removal models have assumed that the top priority targets will be removed first. However this will lead to a suboptimal mission design and increase the ΔV-budget. Since there is a multitude of targets to choose from, the targets can be selected for an optimal mission design. In order to select a group of targets for a removal mission the orbital parameters and political constraints should also be taken into account. Within this paper a number of the target selection criteria are presented. The possible mission targets and their order of retrieval is dependent on the mission architecture. A comparison between several global mission architectures is given. Under consideration are 3 global missions of which a number of parameters are varied. The first mission launches multiple separate deorbit kits. The second launches a mother craft with deorbit kits. The third launches an orbital tug which pulls the debris in a lower orbit, after which a deorbit kit performs the final deorbit burn. A RoM mass and cost comparison is presented. The research described in this paper has been conducted as part of an active debris removal study by the Advanced Study Group (ASG). The ASG is an interdisciplinary student group working at the DLR, analyzing existing technologies and developing new ideas into preliminary

  10. Collision risk investigation for an operational spacecraft caused by space debris

    NASA Astrophysics Data System (ADS)

    Zhang, Binbin; Wang, Zhaokui; Zhang, Yulin

    2017-04-01

    The collision probability between an operational spacecraft and a population of space debris is investigated. By dividing the 3-dimensional operational space of the spacecraft into several space volume cells (SVC) and proposing a boundary selection method to calculate the collision probability in each SVC, the distribution of the collision risk, as functions of the time, the orbital height, the declination, the impact elevation, the collision velocity, etc., can be obtained. Thus, the collision risk could be carefully evaluated over a time span for the general orbital configurations of the spacecraft and the space debris. As an application, the collision risk for the Tiangong-2 space laboratory caused by the cataloged space debris is discussed and evaluated. Results show that most of the collision threat comes from the front left and front right in Tiangong-2's local, quasi-horizontal plane. And the collision probability will also accumulate when Tiangong-2 moves to the largest declinations (about {±} 42°). As a result, the manned space activities should be avoided at those declinations.

  11. One active debris removal control system design and error analysis

    NASA Astrophysics Data System (ADS)

    Wang, Weilin; Chen, Lei; Li, Kebo; Lei, Yongjun

    2016-11-01

    The increasing expansion of debris presents a significant challenge to space safety and sustainability. To address it, active debris removal, usually involving a chaser performing autonomous rendezvous with targeted debris to be removed is a feasible solution. In this paper, we explore a mid-range autonomous rendezvous control system based on augmented proportional navigation (APN), establishing a three-dimensional kinematic equation set constructed in a rotating coordinate system. In APN, feedback control is applied in the direction of line of sight (LOS), thus analytical solutions of LOS rate and relative motion are expectedly obtained. To evaluate the effectiveness of the control system, we adopt Zero-Effort-Miss (ZEM) in this research as the index, the uncertainty of which is directly determined by that of LOS rate. Accordingly, we apply covariance analysis (CA) method to analyze the propagation of LOS rate uncertainty. Consequently, we find that the accuracy of the control system can be verified even with uncertainty and the CA method is drastically more computationally efficient compared with nonlinear Monte-Carlo method. Additionally, to justify the superiority of the system, we further discuss more simulation cases to show the robustness and feasibility of APN proposed in the paper.

  12. In-space technology development: Atomic oxygen and orbital debris effects

    NASA Technical Reports Server (NTRS)

    Visentine, James T.; Potter, Andrew E., Jr.

    1989-01-01

    Earlier Shuttle flight experiments have shown atomic oxygen within the orbital environment can interact with many materials to produce surface recession and mass loss and combine catalytically with other constituents to generate visible and infrared glows. In addition to these effects, examinations of returned satellite hardware have shown many spacecraft materials are also susceptible to damage from high velocity impacts with orbital space debris. These effects are of particular concern for large, multi-mission spacecraft, such as Space Station and SDI operational satellites, that will operate in low-Earth orbit (LEO) during the late 1990's. Not only must these spacecraft include materials and exterior coatings that are resistant to atomic oxygen surface interactions, but these materials must also provide adequate protection against erosion and pitting that could result from numerous impacts with small particles (less than 100 microns) of orbital space debris. An overview of these concerns is presented, and activities now underway to develop materials and coatings are outlined that will provide adequate atomic protection for future spacecraft. The report also discusses atomic oxygen and orbital debris flight experiments now under development to expand our limited data base, correlate ground-based measurments with flight results, and develop an orbital debris collision warning system for use by future spacecraft.

  13. Development of in-situ Space Debris Detector

    NASA Astrophysics Data System (ADS)

    Bauer, Waldemar; Romberg, O.; Wiedemann, C.; Drolshagen, G.; Vörsmann, P.

    2014-11-01

    Due to high relative velocities, collisions of spacecraft in orbit with Space Debris (SD) or Micrometeoroids (MM) can lead to payload degradation, anomalies as well as failures in spacecraft operation, or even loss of mission. Flux models and impact risk assessment tools, such as MASTER (Meteoroid and Space Debris Terrestrial Environment Reference) or ORDEM (Orbital Debris Engineering Model), and ESABASE2 or BUMPER II are used to analyse mission risk associated with these hazards. Validation of flux models is based on measured data. Currently, as most of the SD and MM objects are too small (millimeter down to micron sized) for ground-based observations (e.g. radar, optical), the only available data for model validation is based upon retrieved hardware investigations e.g. Long Duration Exposure Facility (LDEF), Hubble Space Telescope (HST), European Retrievable Carrier (EURECA). Since existing data sets are insufficient, further in-situ experimental investigation of the SD and MM populations are required. This paper provides an overview and assessment of existing and planned SD and MM impact detectors. The detection area of the described detectors is too small to adequately provide the missing data sets. Therefore an innovative detection concept is proposed that utilises existing spacecraft components for detection purposes. In general, solar panels of a spacecraft provide a large area that can be utilised for in-situ impact detection. By using this method on several spacecraft in different orbits the detection area can be increased significantly and allow the detection of SD and MM objects with diameters as low as 100 μm. The design of the detector is based on damage equations from HST and EURECA solar panels. An extensive investigation of those panels was performed by ESA and is summarized within this paper. Furthermore, an estimate of the expected sensitivity of the patented detector concept as well as examples for its implementation into large and small

  14. Small craters on the meteoroid and space debris impact experiment

    NASA Technical Reports Server (NTRS)

    Humes, Donald H.

    1995-01-01

    Examination of 9.34 m(exp 2) of thick aluminum plates from the Long Duration Exposure Facility (LDEF) using a 25X microscope revealed 4341 craters that were 0.1 mm in diameter or larger. The largest was 3 mm in diameter. Most were roughly hemispherical with lips that were raised above the original plate surface. The crater diameter measured was the diameter at the top of the raised lips. There was a large variation in the number density of craters around the three-axis gravity-gradient stabilized spacecraft. A model of the near-Earth meteoroid environment is presented which uses a meteoroid size distribution based on the crater size distribution on the space end of the LDEF. An argument is made that nearly all the craters on the space end must have been caused by meteoroids and that very few could have been caused by man-made orbital debris. However, no chemical analysis of impactor residue that will distinguish between meteoroids and man-made debris is yet available. A small area (0.0447 m(exp 2)) of one of the plates on the space end was scanned with a 200X microscope revealing 155 craters between 10 micron and 100 micron in diameter and 3 craters smaller than 10 micron. This data was used to extend the size distribution of meteoroids down to approximately 1 micron. New penetration equations developed by Alan Watts were used to relate crater dimensions to meteoroid size. The equations suggest that meteoroids must have a density near 2.5 g/cm(exp 3) to produce craters of the shape found on the LDEF. The near-Earth meteoroid model suggests that about 80 to 85 percent of the 100 micron to 1 mm diameter craters on the twelve peripheral rows of the LDEF were caused by meteoroids, leaving 15 to 20 percent to be caused by man-made orbital debris.

  15. Small craters on the meteoroid and space debris impact experiment

    NASA Astrophysics Data System (ADS)

    Humes, Donald H.

    1995-02-01

    Examination of 9.34 m(exp 2) of thick aluminum plates from the Long Duration Exposure Facility (LDEF) using a 25X microscope revealed 4341 craters that were 0.1 mm in diameter or larger. The largest was 3 mm in diameter. Most were roughly hemispherical with lips that were raised above the original plate surface. The crater diameter measured was the diameter at the top of the raised lips. There was a large variation in the number density of craters around the three-axis gravity-gradient stabilized spacecraft. A model of the near-Earth meteoroid environment is presented which uses a meteoroid size distribution based on the crater size distribution on the space end of the LDEF. An argument is made that nearly all the craters on the space end must have been caused by meteoroids and that very few could have been caused by man-made orbital debris. However, no chemical analysis of impactor residue that will distinguish between meteoroids and man-made debris is yet available. A small area (0.0447 m(exp 2)) of one of the plates on the space end was scanned with a 200X microscope revealing 155 craters between 10 micron and 100 micron in diameter and 3 craters smaller than 10 micron. This data was used to extend the size distribution of meteoroids down to approximately 1 micron. New penetration equations developed by Alan Watts were used to relate crater dimensions to meteoroid size. The equations suggest that meteoroids must have a density near 2.5 g/cm(exp 3) to produce craters of the shape found on the LDEF. The near-Earth meteoroid model suggests that about 80 to 85 percent of the 100 micron to 1 mm diameter craters on the twelve peripheral rows of the LDEF were caused by meteoroids, leaving 15 to 20 percent to be caused by man-made orbital debris.

  16. Confronting Space Debris: Strategies and Warnings from Comparable Examples Including Deepwater Horizon

    DTIC Science & Technology

    2010-01-01

    and Space Administration’s (NASA’s) chief scientist for orbital debris , "[T]he current orbital debris environment poses a real, albeit low level...would cause catastrophic failure of that satellite. This monograph presents a new way of thinking about the orbital debris problem. It should be of

  17. Debris mitigation measures by satellite design and operational methods - Findings from the DLR space debris End-to-End Service

    NASA Astrophysics Data System (ADS)

    Sdunnus, H.; Beltrami, P.; Janovsky, R.; Koppenwallner, G.; Krag, H.; Reimerdes, H.; Schäfer, F.

    Debris Mitigation has been recognised as an issue to be addressed by the space faring nations around the world. Currently, there are various activities going on, aiming at the establishment of debris mitigation guidelines on various levels, reaching from the UN down to national space agencies. Though guidelines established on the national level already provide concrete information how things should be done (rather that specifying what should be done or providing fundamental principles) potential users of the guidelines will still have the need to explore the technical, management, and financial implications of the guidelines for their projects. Those questions are addressed by the so called "Space Debris End-to-End Service" project, which has been initiated as a national initiative of the German Aerospace Centre (DLR). Based on a review of already existing mitigation guidelines or guidelines under development and following an identification of needs from a circle of industrial users the "End-to-End Service Gu idelines" have been established for designer and operators of spacecraft. The End-to-End Service Guidelines are based on requirements addressed by the mitigation guidelines and provide recommendations how and when the technical consideration of the mitigation guidelines should take place. By referencing requirements from the mitigation guidelines, the End-to-End Service Guidelines address the consideration of debris mitigation measures by spacecraft design and operational measures. This paper will give an introduction to the End-to-End Service Guidelines. It will focus on the proposals made for mitigation measures by the S/C system design, i.e. on protective design measures inside the spacecraft and on design measures, e.g. innovative protective (shielding) systems. Furthermore, approaches on the analytical optimisation of protective systems will be presented, aiming at the minimisation of shield mass under conservation of the protective effects. On the

  18. Image processing improvement for optical observations of space debris with the TAROT telescopes

    NASA Astrophysics Data System (ADS)

    Thiebaut, C.; Theron, S.; Richard, P.; Blanchet, G.; Klotz, A.; Boër, M.

    2016-07-01

    CNES is involved in the Inter-Agency Space Debris Coordination Committee (IADC) and is observing space debris with two robotic ground based fully automated telescopes called TAROT and operated by the CNRS. An image processing algorithm devoted to debris detection in geostationary orbit is implemented in the standard pipeline. Nevertheless, this algorithm is unable to deal with debris tracking mode images, this mode being the preferred one for debris detectability. We present an algorithm improvement for this mode and give results in terms of false detection rate.

  19. Orbital Debris

    NASA Technical Reports Server (NTRS)

    Kessler, D. J. (Compiler); Su, S. Y. (Compiler)

    1985-01-01

    Earth orbital debris issues and recommended future activities are discussed. The workshop addressed the areas of environment definition, hazards to spacecraft, and space object management. It concluded that orbital debris is a potential problem for future space operations. However, before recommending any major efforts to control the environment, more data are required. The most significant required data are on the population of debris smaller than 4 cm in diameter. New damage criteria are also required. When these data are obtained, they can be combined with hypervelocity data to evaluate the hazards to future spacecraft. After these hazards are understood, then techniques to control the environment can be evaluated.

  20. Kent in space: Cosmic dust to space debris

    NASA Astrophysics Data System (ADS)

    McDonnell, J. A. M.

    1994-10-01

    The dusty heritage of the University of Kent's Space Group commenced at Jodrell Bank, Cheshire, U.K., the home of the largest steerable radio telescope. While Professor Bernard Lovell's 250 ft. diameter telescope was used to command the U.S. deep space Pioneer spacecraft, Professor Tony McDonnell, as a research student in 1960, was developing a space dust detector for the US-UK Ariel program. It was successful. With a Ph.D. safely under the belt, it seemed an inevitable step to go for the next higher degree, a B.T.A.] Two years with NASA at Goddard Space Flight Center, Greenbelt, provided excellent qualifications for such a graduation ('Been to America'). A spirited return to the University of Kent at Canterbury followed, to one of the green field UK University sites springing from the Robbins Report on Higher Education. Swimming against the current of the brain drain, and taking a very considerable reduction in salary, it was with some disappointment that he found that the UK Premier Harold Wilson's 'white-hot technological revolution' never quite seemed to materialize in terms of research funding] Research expertise, centered initially on cosmic dust, enlarged to encompass planetology during the Apollo program, and rightly acquired international acclaim, notching up a history of space missions over 25 years. The group now comprises 38 people supported by four sources: the government's Research Councils, the University, the Space Agencies and Industry. This paper describes the thrust of the group's Research Plan in Space Science and Planetology; not so much based on existing international space missions, but more helping to shape the direction and selection of space missions ahead.

  1. An improved astrometric calibration technique for space debris observation

    NASA Astrophysics Data System (ADS)

    Sun, Rong-Yu; Zhao, Chang-Yin; Lu, Yao

    2016-02-01

    An optical survey is the main technique for detecting space debris. Due to the specific characteristics of observation, the pointing errors and tracking errors of the telescope as well as image degradation may be significant, which make it difficult for astrometric calibration. Here we present an improved method that corrects the pointing and tracking errors, and measures the image position precisely. The pipeline is tested on a number of CCD images obtained from a 1-m telescope administered by Xinjiang Astronomical Observatory while observing a GPS satellite. The results show that the position measurement error of the background stars is around 0.1 pixel, while the time cost for a single frame is about 7.5 s; hence the reliability and accuracy of our method are demonstrated. In addition, our method shows a versatile and feasible way to perform space debris observation utilizing non-dedicated telescopes, which means more sensors could be involved and the ability to perform surveys could be improved.

  2. The Predicted Growth of the Low Earth Orbit Space Debris Environment: An Assessment of Future Risk for Spacecraft

    NASA Technical Reports Server (NTRS)

    Krisko, Paula H.

    2007-01-01

    Space debris is a worldwide-recognized issue concerning the safety of commercial, military, and exploration spacecraft. The space debris environment includes both naturally occuring meteoroids and objects in Earth orbit that are generated by human activity, termed orbital debris. Space agencies around the world are addressing the dangers of debris collisions to both crewed and robotic spacecraft. In the United States, the Orbital Debris Program Office at the NASA Johnson Space Center leads the effort to categorize debris, predict its growth, and formulate mitigation policy for the environment from low Earth orbit (LEO) through geosynchronous orbit (GEO). This paper presents recent results derived from the NASA long-term debris environment model, LEGEND. It includes the revised NASA sodium potassium droplet model, newly corrected for a factor of two over-estimation of the droplet population. The study indicates a LEO environment that is already highly collisionally active among orbital debris larger than 1 cm in size. Most of the modeled collision events are non-catastrophic (i.e., They lead to a cratering of the target, but no large scale fragmentation.). But they are potentially mission-ending, and take place between impactors smaller than 10 cm and targets larger than 10 cm. Given the small size of the impactor these events would likely be undetectable by present-day measurement means. The activity continues into the future as would be expected. Impact rates of about four per year are predicted by the current study within the next 30 years, with the majority of targets being abandoned intacts (spent upper stages and spacecraft). Still, operational spacecraft do show a small collisional activity, one that increases over time as the small fragment population increases.

  3. Approaches to dealing with meteoroid and orbital debris protection on the Space Station

    NASA Technical Reports Server (NTRS)

    Kessler, Donald J.

    1990-01-01

    Viewgraphs and discussion on approaches to dealing with meteoroid and orbital debris protection on the space station are presented. The National Space Policy of February, 1988, included the following: 'All sectors will seek to minimize the creation of space debris. Design and operations of space tests, experiments, and systems will strive to minimize or reduce accumulation of space debris consistent with mission requirements and cost effectiveness.' The policy also tasked the National Security Council, which established an Interagency Group, which in turn produced an Interagency Report. NASA and DoD tasks to establish a joint plan to determine techniques to measure the environment, and techniques to reduce the environment are addressed. Topics covered include: orbital debris environment, meteoroids, orbital debris population, cataloged earth satellite population, USSPACECOM cataloged objects, and orbital debris radar program.

  4. Analysis of Space Station Operations in the Space Debris Environment.

    DTIC Science & Technology

    1984-12-01

    THESIS Presented to the Faculty of the School of Engineering of the Air Force Institute of Technology Air University In Partial Fulfillment of the...The 1983 TRW Space Log listed fourteen nations involved in sponsoring launches (32:120). As nations develop their technology , it is logical that...incentives to develop technology , forming a positive loop as indicated by the causal diagram. Again, the American and Russian space programs verify this

  5. Active Debris Removal mission design in Low Earth Orbit

    NASA Astrophysics Data System (ADS)

    Martin, Th.; Pérot, E.; Desjean, M.-Ch.; Bitetti, L.

    2013-03-01

    Active Debris Removal (ADR) aims at removing large sized intact objects ― defunct satellites, rocket upper-stages ― from space crowded regions. Why? Because they constitute the main source of the long-term debris environment deterioration caused by possible future collisions with fragments and worse still with other intact but uncontrolled objects. In order to limit the growth of the orbital debris population in the future (referred to as the Kessler syndrome), it is now highly recommended to carry out such ADR missions, together with the mitigation measures already adopted by national agencies (such as postmission disposal). At the French Space Agency, CNES, and in the frame of advanced studies, the design of such an ADR mission in Low Earth Orbit (LEO) is under evaluation. A two-step preliminary approach has been envisaged. First, a reconnaissance mission based on a small demonstrator (˜500 kg) rendezvousing with several targets (observation and in-flight qualification testing). Secondly, an ADR mission based on a larger vehicle (inherited from the Orbital Transfer Vehicle (OTV) concept) being able to capture and deorbit several preselected targets by attaching a propulsive kit to these targets. This paper presents a flight dynamics level tradeoff analysis between different vehicle and mission concepts as well as target disposal options. The delta-velocity, times, and masses required to transfer, rendezvous with targets and deorbit are assessed for some propelled systems and propellant less options. Total mass budgets are then derived for two end-to-end study cases corresponding to the reconnaissance and ADR missions mentioned above.

  6. Active Debris Removal and the Challenges for Environment Remediation

    NASA Technical Reports Server (NTRS)

    Liou, J. C.

    2012-01-01

    Recent modeling studies on the instability of the debris population in the low Earth orbit (LEO) region and the collision between Iridium 33 and Cosmos 2251 have underlined the need for active debris removal. A 2009 analysis by the NASA Orbital Debris Program Office shows that, in order to maintain the LEO debris population at a constant level for the next 200 years, an active debris removal of about five objects per year is needed. The targets identified for removal are those with the highest mass and collision probability products in the environment. Many of these objects are spent upper stages with masses ranging from 1 to more than 8 metric tons, residing in several altitude regions and concentrated in about 7 inclination bands. To remove five of those objects on a yearly basis, in a cost-effective manner, represents many challenges in technology development, engineering, and operations. This paper outlines the fundamental rationale for considering active debris removal and addresses the two possible objectives of the operations -- removing large debris to stabilize the environment and removing small debris to reduce the threat to operational spacecraft. Technological and engineering challenges associated with the two different objectives are also discussed.

  7. Adaptive Optics for Satellite Imaging and Space Debris Ranging

    NASA Astrophysics Data System (ADS)

    Bennet, F.; D'Orgeville, C.; Price, I.; Rigaut, F.; Ritchie, I.; Smith, C.

    Earth's space environment is becoming crowded and at risk of a Kessler syndrome, and will require careful management for the future. Modern low noise high speed detectors allow for wavefront sensing and adaptive optics (AO) in extreme circumstances such as imaging small orbiting bodies in Low Earth Orbit (LEO). The Research School of Astronomy and Astrophysics (RSAA) at the Australian National University have been developing AO systems for telescopes between 1 and 2.5m diameter to image and range orbiting satellites and space debris. Strehl ratios in excess of 30% can be achieved for targets in LEO with an AO loop running at 2kHz, allowing the resolution of small features (<30cm) and the capability to determine object shape and spin characteristics. The AO system developed at RSAA consists of a high speed EMCCD Shack-Hartmann wavefront sensor, a deformable mirror (DM), and realtime computer (RTC), and an imaging camera. The system works best as a laser guide star system but will also function as a natural guide star AO system, with the target itself being the guide star. In both circumstances tip-tilt is provided by the target on the imaging camera. The fast tip-tilt modes are not corrected optically, and are instead removed by taking images at a moderate speed (>30Hz) and using a shift and add algorithm. This algorithm can also incorporate lucky imaging to further improve the final image quality. A similar AO system for space debris ranging is also in development in collaboration with Electro Optic Systems (EOS) and the Space Environment Management Cooperative Research Centre (SERC), at the Mount Stromlo Observatory in Canberra, Australia. The system is designed for an AO corrected upward propagated 1064nm pulsed laser beam, from which time of flight information is used to precisely range the target. A 1.8m telescope is used for both propagation and collection of laser light. A laser guide star, Shack-Hartmann wavefront sensor, and DM are used for high order

  8. The shape effect of space debris on recoil impulse by pulsed laser ablation

    NASA Astrophysics Data System (ADS)

    Wang, Chenglin; Zhang, Yan; Wang, Kunpeng

    2016-10-01

    Removing space debris by high-energy pulsed laser may be the most effective way to mitigate the threat posed by the increasing space debris. Laser ablation of a thin surface layer causes recoil impulse, which will lower the orbit perigee of space debris and accelerate the atmospheric capture. When the laser beam vertically irradiates a flat debris, it requires a certain laser fluence to reach the optimal impulse coupling, and the recoil impulse is parallel to the laser beam. However, the incident laser fluence varies in different parts of a non-flat surface. We have taken the shape effect into account to propose a numerical method of calculating the recoil impulse. Taking cylinder debris as the target, we have compared the recoil impulse in different laser fluences through simulation experiments, which implies that a higher laser fluence than the optimal one is needed to obtain a larger recoil impulse for irregularly shaped space debris.

  9. The geocentric particulate distribution: Cometary, asteroidal, or space debris?

    NASA Technical Reports Server (NTRS)

    Mcdonnell, J. A. M.; Ratcliff, P. R.

    1992-01-01

    Definition of the Low Earth Orbit (LEO) particulate environment has been refined considerably with the analysis of data from NASA's Long Duration Exposure Facility (LDEF). Measurements of the impact rates from particulates ranging from sub-micron to millimetres in dimension and, especially, information on their directionality has permitted new scrunity of the sources of the particulates. Modelling of the dynamics of both bound (Earth orbital) and unbound (hyperbolic interplanetary) particulates intercepting LDEF's faces leads to the conclusion that the source is dominantly interplanetary for particle dimensions of greater than some 5 microns diameter; however the anisotropy below this dimension demands lower velocities and is compatible with an orbital component. Characteristics of the LDEF interplanetary component are compatible with familiar meteoroid sources and deep space measurements. Understanding of the orbital component which exceeds the interplanetary flux by a factor of 4 is less clear; although the very small particulates in orbit have been associated with space debris (Lawrance and Brownlee, 1986) this data conflicts with other measurements (McDonnell, Carey and Dixon, 1984) at the same epoch. By analysis of trajectories approaching the Earth and its atmosphere, we have shown that a significant contribution could be captured by aerocapture, i.e., atmospheric drag, from either asteroidal or cometary sources; such enhancement is unlikely however to provide the temporal and spatial fluctuations observed by the LDEF Interplanetary Dust Experiment (Mullholland et al. 1992). A further new mechanism is also examined, that of aerofragmentation capture, where an atmospheric grazing trajectory, which would not normally lead to capture, leads to fragmentation by thermal or mechanical shock; the microparticulates thus created can be injected in large numbers, but only into short-lifetime orbits. The concentration in one particular orbit plane, could explain the

  10. Re-entry aerodynamics derived from space debris trajectory analysis

    NASA Astrophysics Data System (ADS)

    Crowther, R.

    1992-05-01

    This paper considers the technique of orbital analysis as a means of determining the ill-defined gas-surface interaction between spacecraft and atmospheric molecules in low earth orbit. The interaction is a major uncertainty in trajectory predictions for a body moving within an atmosphere. The rate of change of the orbital period of a debris object, the uncontrolled Salyut 7/Kosmos 1686 space station, is analyzed in order to determine the free molecular drag coefficient. The results are compared with theoretical values for the drag coefficient calculated using a complex representation of the vehicle configuration and motion and applying the Monte Carlo Test Particle method. Results suggest a nature of re-emission very close to the classical diffuse, totally accommodated case was occurring at the surface of the debris object as it approached re-entry. However, the determined drag coefficient and therefore the derived interaction are found to be very sensitive to the neutral density and therefore the atmospheric model used in the analysis.

  11. NASA's Marshall Space Flight Center Recent Studies and Technology Developments in the Area of SSA/Orbital Debris

    NASA Technical Reports Server (NTRS)

    Wiegmann, Bruce M.; Hovater, Mary; Kos, Larry

    2012-01-01

    NASA/MSFC has been investigating the various aspects of the growing orbital debris problem since early 2009. Data shows that debris ranging in size from 5 mm to 10 cm presents the greatest threat to operational spacecraft today. Therefore, MSFC has focused its efforts on small orbital debris. Using off-the-shelf analysis packages, like the ESA MASTER software, analysts at MSFC have begun to characterize the small debris environment in LEO to support several spacecraft concept studies and hardware test programs addressing the characterization, mitigation, and ultimate removal, if necessary, of small debris. The Small Orbital Debris Active Removal (SODAR) architectural study investigated the overall effectiveness of removing small orbital debris from LEO using a low power, space-based laser. The Small Orbital Debris Detection, Acquisition, and Tracking (SODDAT) conceptual technology demonstration spacecraft was developed to address the challenges of in-situ small orbital debris environment classification including debris observability and instrument requirements for small debris observation. Work is underway at MSFC in the areas of hardware and testing. By combining off the shelf digital video technology, telescope lenses, and advanced video image FPGA processing, MSFC is building a breadboard of a space based, passive orbital tracking camera that can detect and track faint objects (including small debris, satellites, rocket bodies, and NEOs) at ranges of tens to hundreds of kilometers and speeds in excess of 15 km/sec,. MSFC is also sponsoring the development of a one-of-a-kind Dynamic Star Field Simulator with a high resolution large monochrome display and a custom collimator capable of projecting realistic star images with simple orbital debris spots (down to star magnitude 11-12) into a passive orbital detection and tracking system with simulated real-time angular motions of the vehicle mounted sensor. The dynamic star field simulator can be expanded for multiple

  12. NASAs Marshall Space Flight Center Recent Studies and Technology Developments in the Area of SSA/Orbital Debris

    NASA Astrophysics Data System (ADS)

    Wiegman, B.; Hovater, M.; Kos, L.

    2012-09-01

    NASA/MSFC has been investigating the various aspects of the growing orbital debris problem since early 2009. Data shows that debris ranging in size from 5 mm to 10 cm presents the greatest threat to operational spacecraft today. Therefore, MSFC has focused its efforts on small orbital debris. Using off-the-shelf analysis packages, like the ESA MASTER software, analysts at MSFC have begun to characterize the small debris environment in LEO to support several spacecraft concept studies and hardware test programs addressing the characterization, mitigation, and ultimate removal, if necessary, of small debris. The Small Orbital Debris Active Removal (SODAR) architectural study investigated the overall effectiveness of removing small orbital debris from LEO using a low power, space-based laser. The Small Orbital Debris Detection, Acquisition, and Tracking (SODDAT) conceptual technology demonstration spacecraft was developed to address the challenges of in-situ small orbital debris environment classification including debris observability and instrument requirements for small debris observation. Work is underway at MSFC in the areas of hardware and testing. By combining off the shelf digital video technology, telescope lenses, and advanced video image FPGA processing, MSFC is building a breadboard of a space based, passive orbital tracking camera that can detect and track faint objects (including small debris, satellites, rocket bodies, and NEOs) at ranges of tens to hundreds of kilometers and speeds in excess of 15 km/sec,. MSFC is also sponsoring the development of a one-of-a-kind Dynamic Star Field Simulator with a high resolution large monochrome display and a custom collimator capable of projecting realistic star images with simple orbital debris spots (down to star magnitude 11-12) into a passive orbital detection and tracking system with simulated real-time angular motions of the vehicle mounted sensor. The dynamic star field simulator can be expanded for multiple

  13. On the effects of solar storms to the decaying orbital space debris

    SciTech Connect

    Herdiwijaya, Dhani; Rachman, Abdul

    2014-03-24

    Any man-made object in Earth's orbit that no longer serves a useful purpose is classified as orbital debris. Debris objects come from a variety of sources. The majority is related to satellite fragmentation. Other major sources of debris are propulsion systems, and fragmentation of spent upper stages, payload and mission related debris. Serious concern about orbital debris has been growing. Knowledge of the future debris environment is important to both satellite designers, and mission planners, who need to know what hazards a satellite might encounter during the course of its mission. Therefore, it is important to know how much debris is in orbit, where it is located, and when it will decay. The debris environment is complex and dynamically evolving. Objects of different shape and size behave differently in orbit. The geoeffectiveness space environments include solar flux at 10.7 cm, solar energetic particles flux or speed, solar wind flow pressure, electric field, and geomagnetic indices. We study the decaying orbital debris from Tracking and Impact Prediction (TIP) messages in conjuction with geoeffectiveness space environments through time epoch correlation. We found that the decaying and reentry orbital debris are triggered by space environment enhancement within at least one week before reentry. It is not necessary a transient or high energetic and severe solar storm events are needed in decaying processes. We propose that the gradual enhancement processes of space environment will cause satellite surface charging due to energetic electron and enhance drag force.

  14. ROGER a potential orbital space debris removal system

    NASA Astrophysics Data System (ADS)

    Starke, Juergen; Bischof, Bernd; Foth, W.-O.; -J., J.; Günther

    The previous activities in the field of On Orbit Servicing studied in the 1990's included in partic-ular the capability of vehicles in GEO to capture and support satellites (mainly communication satellites) to enable repair and continuation of operations, and finally the controlled transfer the target into a permanent graveyard orbit. The specific capture tools for these applications were mostly based on robotic systems to capture and fix the target under specific dynamic constraints (e.g. slowly tumbling target) without damage, and to allow the stabilization, re-orientation and potential repair of the target and subsequent release or transport to the final disposal orbit. Due to the drastically increasing number of debris particularly in the Low Earth Orbits (SSO) the active debris removal is now necessary to counteract to the predicted debris production cascade (Kessler Syndrome), which means the pollution of the total sphere in low earth orbit and not only the SSO area. In most of the debris congresses it was recommended to start removal with the still integrated systems as soon as possible. In the case of large debris objects, the soft capture system can be replaced by a simpler and robust system able to operate from a safe distance to the target and flexible enough to capture and hold different types of targets such as deactivated and/or defective satellites, upper stages and big fragments. These nominally non -cooperative targets might be partially destroyed by the capture process, but the production of additional debris shall be avoided. A major argument for the commercial applications is a multi-target mission potential, which is possible at GEO because the transfer propellant requirement to the disposal orbit and the return to the orbit of the next potential target is relative low (orbits with similar inclination and altitude). The proposed ROGER system is designed as a spacecraft with rendezvous capabilities including inspection in the vicinity of the

  15. Deployment dynamics of tethered-net for space debris removal

    NASA Astrophysics Data System (ADS)

    Shan, Minghe; Guo, Jian; Gill, Eberhard

    2017-03-01

    A tethered-net is a promising method for space debris capturing. However, its deployment dynamics is complex because of the flexibility, and its dependency of the deployment parameters is insufficiently understood. To investigate the deployment dynamics of tethered-net, four critical deployment parameters, namely maximum net area, deployment time, traveling distance and effective period are identified in this paper, and the influence of initial deployment conditions on these four parameters is investigated. Besides, a comprehensive study on a model for the tethered-net based on absolute nodal coordinates formulation (ANCF) is provided. Simulations show that the results based on the ANCF modeling method present a good agreement with that based on the conventional mass-spring modeling method. Moreover, ANCF model is capable of describing the flexibility between two nodes on the net. However, it is more computationally expensive.

  16. Numerical simulation of space debris impacts on the Whipple shield

    NASA Astrophysics Data System (ADS)

    Katayama, M.; Toda, S.; Kibe, S.

    1997-06-01

    The authors carried out three series of experimental tests of the first bumper perforation and main wall cratering processes directly caused by three types of projectiles with about 2, 4 and 7 km s -1 impact velocities but comparable initial kinetic energies, by using three different accelerators (one-stage powder gun, two-stage light-gas gun and rail gun), for the purpose of investigating space debris hypervelocity impacts onto single-walled Whipple bumper shields [1]. In the present study, after reviewing the numerical simulation method of hydrocode for both Eulerian and Lagrangian descriptions, a number of parametric numerical simulation analyses using multiple material Eulerian methods were performed in order to optimize the material properties of bumper and main wall materials through comparison with experimental results of single target impacts by the projectiles. In particular, the material data on the dynamic fracture phenomena are discussed in detail in the first part. Then a couple of numerical calculations using the interactive Lagrangian rezoning method to simulate the overall impact process against the single walled Whipple shield were performed and compared with the corresponding experimental results. Both results indicated fairly good agreement with each other. Moreover, it was demonstrated that the present method is helpful and efficient in understanding the impact phenomena and fracture mechanism in the space debris hypervelocity impact problem. Finally the multiple material Eulerian method was applied to the same problems modeled by the interactive Lagrangian rezoning method used previously, because the former is much easier to use for almost all users, although it is more diffusive and unclear of material boundaries than the latter. Those two kinds of numerical results also indicated fairly good agreements with each other.

  17. L'ADROIT - A spaceborne ultraviolet laser system for space debris clearing

    NASA Astrophysics Data System (ADS)

    Phipps, Claude R.

    2014-11-01

    Small (1-10 cm) debris in low Earth orbit (LEO) are extremely dangerous, because they spread the breakup cascade. Pulsed laser active debris removal using laser ablation jets on target is the most cost-effective way to re-enter the small debris. No other solutions address the whole problem of large ( 100 cm, 1 t) as well as small debris. Physical removal of small debris (by nets, tethers and so on) is uneconomical because of the energy cost of matching orbits. In this paper, we present a completely new proposal relative to our earlier work. This new approach uses rapid, head-on interaction in 10-40 s rather than 4 minutes, using 20-40 kW bursts of 100 ps, 355 nm UV pulses from a 1.5 m diameter aperture on a space-based station in LEO. The station employs “heat-capacity” laser mode with low duty cycle to create an adaptable, robust, dual-mode system which can lower or raise large derelict objects into less dangerous orbits, as well as clear out the small debris in a 400-km thick LEO band. Time-average laser optical power is less than 15 kW. The combination of short pulses and UV wavelength gives lower required fluence on target as well as higher momentum coupling coefficient. An orbiting system can have short range because of high interaction rate deriving from its velocity through the debris field. This leads to much smaller mirrors and lower average power than the ground-based systems we have considered previously. Our system also permits strong defense of specific assets. Analysis gives an estimated cost less than 1 k each to re-enter most small debris in a few months, and about 280 k each to raise or lower 1-ton objects by 40 km. We believe it can do this for 2000 such large objects in about four years. Laser ablation is one of the few interactions in nature that propel a distant object without any significant reaction on the source.

  18. Controlling the Growth of Future LEO Debris Populations with Active Debris Removal

    NASA Technical Reports Server (NTRS)

    Liou, J.-C.; Johnson, N. L.; Hill, N. M.

    2008-01-01

    Active debris removal (ADR) was suggested as a potential means to remediate the low Earth orbit (LEO) debris environment as early as the 1980s. The reasons ADR has not become practical are due to its technical difficulties and the high cost associated with the approach. However, as the LEO debris populations continue to increase, ADR may be the only option to preserve the near-Earth environment for future generations. An initial study was completed in 2007 to demonstrate that a simple ADR target selection criterion could be developed to reduce the future debris population growth. The present paper summarizes a comprehensive study based on more realistic simulation scenarios, including fragments generated from the 2007 Fengyun-1C event, mitigation measures, and other target selection options. The simulations were based on the NASA long-term orbital debris projection model, LEGEND. A scenario, where at the end of mission lifetimes, spacecraft and upper stages were moved to 25-year decay orbits, was adopted as the baseline environment for comparison. Different annual removal rates and different ADR target selection criteria were tested, and the resulting 200-year future environment projections were compared with the baseline scenario. Results of this parametric study indicate that (1) an effective removal strategy can be developed based on the mass and collision probability of each object as the selection criterion, and (2) the LEO environment can be stabilized in the next 200 years with an ADR removal rate of five objects per year.

  19. Comparison between ASI, CNES and JAXA CCD analysis software for optical space debris monitoring

    NASA Astrophysics Data System (ADS)

    Paolillo, Fabrizio; Laas-Bourez, Myrtille; Yanagisawa, Toshifumi; Cappelletti, Chantal; Graziani, Filippo; Vidal, Bruno

    Since nineties Italian Space Agency (ASI), Centre National d'Etudes Spatiales CNES and Japan Aerospace Exploration Agency (JAXA) play an important role in Inter-Agency Space Debris Coordination Committee (IADC) activities. Respectively the Group of Astrodynamics of Uni-versity Sapienza of Rome (GAUSS), TAROT team (Télescope a Action Rapide pour les Objets Transitoires) and Institute of Aerospace Technology (IAT), participate in optical space debris monitoring activities (WG1 at IADC ) with the following facilities: 1. SpaDE observatory of ASI/GAUSS in Collepardo (Fr.), country-regionplaceItaly. 2. TAROT observatories of CNES: one in Chili (ESO LA Silla) and one in placecountry-regionFrance (Observatoire de la Côte d'Azur, at Calern). 3. Nyukasayama Observatory of IAT/JAXA, country-regionplaceJapan. Due to the large amount of data collected during the IADC coordinated observation campaigns and the autonomous campaigns, these research groups developed three different software for image processing automation and for the correlation of the detected objects with the catalogue. Using these software the three different observatories are improving the knowledge of the space debris population, in particular in the so-called geostationary belt (AI23.4 IADC International 2007 optical observation campaigns in higher Earth orbits and AI23.2 Investigation of high A/m ratio debris in higher Earth orbits), but they use different space debris monitoring techniques. With the aim to improve CCD analysis capabilities of each research group, during the 27th IADC meeting ASI, CNES and JAXA started a cooperation in this field on the comparison between the image processing software. The objectives of this activity are: 1. Test of ASI, CNES and JAXA CCD analysis software on real images taken in the 3 dif-ferent observation strategies (each observatory uses a particular objects extraction pro-cedure). 2. Results comparison: number of bad detection, number of good detection, processing

  20. KSC ice/frost/debris assessment for space shuttle mission STS-29R

    NASA Technical Reports Server (NTRS)

    Stevenson, Charles G.; Katnik, Gregory N.; Higginbotham, Scott A.

    1989-01-01

    An ice/frost/debris assessment was conducted for Space Shuttle Mission STS-29R. Debris inspections of the flight elements and launch pad are performed before and after launch. Ice/frost conditions on the external tank are assessed by the use of computer programs, nomographs, and infrared scanner data during cryogenic loading of the vehicle followed by an on-pad visual inspection. High speed photography is analyzed after launch to identify ice/debris sources and evaluate potential vehicle damage. The ice/frost/debris conditions of Mission STS-29R and their effect on the Space Shuttle Program are documented.

  1. Ice/frost/debris assessment for space shuttle mission STS-27R, December 2, 1988

    NASA Technical Reports Server (NTRS)

    Katnik, Gregory N.; Higginbotham, Scott A.

    1989-01-01

    An Ice/Frost/Debris assessment was conducted for Space Shuttle Mission STS-27R. Debris inspections of the flight elements and launch pad are performed before and after launch. Ice/frost conditions are assessed by the use of computer programs, nomographs, and infrared scanner data during cryogenic loading of the vehicle followed by an on-pad visual inspection. High speed photography is viewed after launch to identify ice/debris sources and evaluate potential vehicle damage. The Ice/Frost/Debris conditions of Mission STS-27R and their effect on the Space Shuttle Program are documented.

  2. Ice/frost/debris assessment for space shuttle Mission STS-32 (61-C)

    NASA Technical Reports Server (NTRS)

    Stevenson, Charles G.; Katnik, Gregory N.; Speece, Robert F.

    1986-01-01

    An Ice/Frost/Debris assessment was conducted for Space Shuttle Mission STS-32 (61-C). This assessment begins with debris inspections of the flight elements and launch facilities before and after launch. Ice/Frost formations are calculated during cryogenic loading of the external tank followed by an on-pad assessment of the Shuttle vehicle and pad at T-3 hours in the countdown. High speed films are reviewed after launch to identify Ice/Frost/Debris sources and investigate potential vehicle damage. The Ice/Frost/Debris conditions and their effects on the Space Shuttle are documented.

  3. Ice/frost/debris assessment for space shuttle mission STS-26R

    NASA Technical Reports Server (NTRS)

    Stevenson, Charles G.; Katnik, Gregory N.; Higginbotham, Scott A.

    1988-01-01

    An Ice/Frost/Debris Assessment was conducted for Space Shuttle Mission STS-26R. Debris inspections of the flight elements and launch pad are performed before and after launch. Ice/Frost conditions are assessed by use of computer programs, nomographs, and infrared scanner data during cryogenic loading of the vehicle followed by an on-pad visual inspection. High speed photography is viewed after launch to identify ice/debris sources and evaluate potential vehicle damage. The Ice/Frost/Debris conditions of Mission 26R and their effect on the Space Shuttle Program is documented.

  4. KSC ice/frost/debris assessment for Space Shuttle Mission STS-30R

    NASA Technical Reports Server (NTRS)

    Stevenson, Charles G.; Katnik, Gregory N.; Higginbotham, Scott A.

    1989-01-01

    An ice/frost/debris assessment was conducted for Space Shuttle Mission STS-30R. Debris inspections of the flight elements and launch pad are performed before and after launch. Ice/frost conditions on the external tank are assessed by the use of computer programs, nomographs, and infrared scanner data during cryogenic loading of the vehicle followed by an on-pad visual inspection. High speed photography is analyzed after launch to identify ice/debris sources and evaluate potential vehicle damage. The ice/frost/debris conditions of Mission STS-30R and their overall effect on the Space Shuttle Program is documented.

  5. NASA Now: Technology: Orbital Debris -- Man-made Objects in Space

    NASA Video Gallery

    Nicholas Johnson is chief scientist for the Orbital Debris Office at NASA’s Johnson Space Center in Houston. The office monitors nearly 22,000 objects in space every single day to keep astronauts...

  6. NASA Now Minute: Technology: Orbital Debris -- Man-made Objects in Space

    NASA Video Gallery

    Nicholas Johnson is chief scientist for the Orbital Debris Office atNASA’s Johnson Space Center in Houston. The office monitors nearly 22,000objects in space every single day to keep astronauts...

  7. Microbiological analysis of debris from Space Transportation System (STS)-55 Spacelab D-2

    NASA Technical Reports Server (NTRS)

    Huff, T. L.

    1994-01-01

    Filter debris from the Spacelab module D-2 of STS-55 was analyzed for microbial contamination. Debris from cabin and avionics filters was collected by Kennedy Space Center personnel on May 8, 1993, 2 days postflight. Debris weights were similar to those of previous Spacelab missions. Approximately 5.1E+5 colony forming units per gram of debris were enumerated from the cabin and avionics filter debris, respectively. these numbers were similar in previous missions for which the entire contents were analyzed without sorting of the material. Bacterial diversity was small compared to previous missions, with no gram negative bacteria isolated. Only one bacterial species, Corynebacterium pseudodiphtheriticum, was not isolated previously by the laboratory from Spacelab debris. This organism is a normal inhabitant of the pharynx. A table listing all species of bacteria isolated by the laboratory from previous Spacelab air filters debris collection is provided.

  8. Demonstration designs for the remediation of space debris from the International Space Station

    NASA Astrophysics Data System (ADS)

    Ebisuzaki, Toshikazu; Quinn, Mark N.; Wada, Satoshi; Piotrowski, Lech Wiktor; Takizawa, Yoshiyuki; Casolino, Marco; Bertaina, Mario E.; Gorodetzky, Philippe; Parizot, Etienne; Tajima, Toshiki; Soulard, Rémi; Mourou, Gérard

    2015-07-01

    We present here designs for a staged implementation of an orbiting debris remediation system comprised of a super-wide field-of-view telescope (EUSO) and a novel high efficiency fibre-based laser system (CAN). Initial proof of concept stages will operate from the International Space Station (ISS) where the EUSO telescope has been designed for operation as a detector of ultra-high energy cosmic rays. Equipped with 2.5 m optics and a field of view of ±30°, the EUSO telescope can also be utilised for the detection of high velocity fragmentation debris in orbit near the ISS. Further tracking, characterisation and remediation are to be performed by a CAN laser system operating in tandem with the EUSO telescope. For full scale versions of both instruments, the range of the detection/removal operation can be as large as 100 km. Utilising a step-by-step approach of increasing scale we present an analysis of implementation of: 1) Proof of principle demonstration of the detection by a mini-EUSO and operation of 100-fibre CAN laser technology as an ISS based prototype, 2) Technical demonstrator of debris-removal that consists of the EUSO telescope for the detection and a 10,000 fibre CAN laser for tracking and impulse delivery for debris re-entry, and 3) A free-flyer mission dedicated to debris remediation in a polar orbit with the altitude near 800 km. The integration of the two novel technologies aboard the ISS amounts to a novel approach as an immediate response to the serious space debris problem with the existing platform of ISS.

  9. Impact of high-risk conjunctions on Active Debris Removal target selection

    NASA Astrophysics Data System (ADS)

    Lidtke, Aleksander A.; Lewis, Hugh G.; Armellin, Roberto

    2015-10-01

    Space debris simulations show that if current space launches continue unchanged, spacecraft operations might become difficult in the congested space environment. It has been suggested that Active Debris Removal (ADR) might be necessary in order to prevent such a situation. Selection of objects to be targeted by ADR is considered important because removal of non-relevant objects will unnecessarily increase the cost of ADR. One of the factors to be used in this ADR target selection is the collision probability accumulated by every object. This paper shows the impact of high-probability conjunctions on the collision probability accumulated by individual objects as well as the probability of any collision occurring in orbit. Such conjunctions cannot be predicted far in advance and, consequently, not all the objects that will be involved in such dangerous conjunctions can be removed through ADR. Therefore, a debris remediation method that would address such events at short notice, and thus help prevent likely collisions, is suggested.

  10. An Assessment of Potential Detectors to Monitor the Man-made Orbital Debris Environment. [space debris

    NASA Technical Reports Server (NTRS)

    Reynolds, R. C.; Ruck, G. T.

    1983-01-01

    Observations using NORAD radar showed that man made debris exceeds the natural environment for large objects. For short times (a few days to a few weeks) after solid rocket motor (SRM) firings in LEO, man made debris in the microparticle size range also appears to exceed the meteoroid environment. The properties of the debris population between these size regimes is currently unknown as there has been no detector system able to perform the required observations. The alternatives for obtaining data on this currently unobserved segment of the population are assessed.

  11. Orbit Prediction Tool for Different Classes of Space Debris Orbits

    NASA Astrophysics Data System (ADS)

    Wnuk, Edwin; Wytrzyszczak, Iwona; Golembiewska, Justyna; Klinkrad, Heiner

    There are two aspects of the orbital evolution of space debris: the long-term evolution and the short-term prediction of individual object orbits. In the case of the long-term evolution (years or tens of years time span) general characteristics (e.g. total number of objects, spa-tial distribution and density) of a future space environment are predicted with the use of a relatively simple theory of motion for statistical analysis of future orbits of a large number of objects -a cloud of particles". In the short-term orbital evolution of space debris objects, as considered in this paper, future positions and velocities of individual objects are calculated for a few days or a few weeks time span. A much more sophisticated theory of satellite motion is applied in this case. The paper presents the orbital prediction tool that uses an analytical and semi-analytical theories of satellite motion. The force model includes all important perturbing factors: geopotential effects with arbitrary degree and order spherical harmonic coefficients taken into account, luni-solar attractions, solar radiation pressure and atmospheric drag. The analytical theory of motion is of the second order and is not sensitive to singularities for small eccentricities and small inclinations. A new algorithm for the transformation between mean and osculating elements for the second order theory is applied. Predicted positions of a satel-lite on a given level of accuracy are calculated only with the use of terms that essentially influence on predicted satellite orbit, all other terms are omitted. The number of terms in for-mulas for perturbations, and thus complexity of the theory, depends on the defined level of accuracy and the type of orbit. In practice, we create a dynamical model for a given class of satellite orbit. Geopotential and luni-solar perturbations are calculated in the two following steps. In the first step, values of secular terms and all amplitudes of periodic terms are calculated

  12. Space debris observational test with the Medicina-Evpatoria bistatic radar.

    NASA Astrophysics Data System (ADS)

    Pupillo, G.; Bartolini, M.; Cevolani, G.; Di Martino, M.; Falkovich, I.; Konovalenko, A. A.; Malevinskij, S.; Montebugnoli, S.; Nabatov, A.; Pluchino, S.; Salerno, E.; Schillirò, F.; Zoni, L.

    In the framework of the space debris monitoring program of the Italian Space Agency (ASI), the Italian Institute of Radioastronomy (IRA), the Turin Astronomical Observatory (OATO) and the Ukrainian Institute of Radioastronomy performed a space debris observational test by using the Medicina-Evpatoria bistatic radar. Several kinds of objects orbiting in LEO, MEO, GEO and HEO were selected as target in order to validate the hardware setup and new observational techniques. Echoes coming from small space debris were detected with an extremely high signal to noise ratio as well as still unknown orbiting objects were presumably discovered during the observations.

  13. Space Debris-de-Orbiting by Vaporization Impulse using Short Pulse Laser

    SciTech Connect

    Early, J; Bibeau, C; Claude, P

    2003-09-16

    Space debris constitutes a significant hazard to low earth orbit satellites and particularly to manned spacecraft. A quite small velocity decrease from vaporization impulses is enough to lower the perigee of the debris sufficiently for atmospheric drag to de-orbit the debris. A short pulse (picosecond) laser version of the Orion concept can accomplish this task in several years of operation. The ''Mercury'' short pulse Yb:S-FAP laser being developed at LLNL for laser fusion is appropriate for this task.

  14. UniSat-5: a space-based optical system for space debris monitoring

    NASA Astrophysics Data System (ADS)

    Di Roberto, Riccardo; Cappelletti, Chantal

    2012-07-01

    Micro-satellite missions, thanks to the miniaturization process of electronic components, now have a broader range of applications. Gauss Group at School of Aerospace Engineering has been a pioneer in educational micro-satellites, namely with UNISAT and EDUSAT missions. Moreover it has been long involved in space debris related studies, such as optical observations as well as mitigation. A new project is under development for a compact digital imaging system. The purpose will be in situ observation of space debris on board Unisat-5 micro-satellite. One of the key elements of observing on orbit is that many atmospheric phenomena would be avoided, such as diffraction and EM absorption. Hence images would gain more contrast and solar spectral irradiance would be higher for the whole visible spectrum Earlier limitations of power and instrument size prevented the inclusion of these payloads in educational satellite missions. The system is composed of an optical tube, a camera, C band and S band transceivers and two antennas. The system is independent from the rest of the spacecraft. The optical tube is a Schmidt-Cassegrain reflector, and the magnitude limit is 13. The camera is equipped with a panchromatic 5Mpix sensor, capable of direct video streaming, as well as local storage of recorded images. The transceivers operate on ISM 2.4GHz and 5 GHz Wi-Fi bands, and they provide stand-alone communication capabilities to the payload, and Unisat-5 OBDH can switch between the two. Both transceivers are connected to their respective custom-designed patch antenna. The ground segment is constituted of a high gain antenna dish, which will use the same transceiver on board the spacecraft as the feed, in order to establish a TCP/IP wireless link. Every component of this system is a consumer grade product. Therefore price reduction of cutting edge imaging technology now allows the use of professional instruments, that combined with the new wireless technology developed for

  15. Conceptualizing an economically, legally, and politically viable active debris removal option

    NASA Astrophysics Data System (ADS)

    Emanuelli, M.; Federico, G.; Loughman, J.; Prasad, D.; Chow, T.; Rathnasabapathy, M.

    2014-11-01

    It has become increasingly clear in recent years that the issue of space debris, particularly in low-Earth orbit, can no longer be ignored or simply mitigated. Orbital debris currently threatens safe space flight for both satellites and humans aboard the International Space Station. Additionally, orbital debris might impact Earth upon re-entry, endangering human lives and damaging the environment with toxic materials. In summary, orbital debris seriously jeopardizes the future not only of human presence in space, but also of human safety on Earth. While international efforts to mitigate the current situation and limit the creation of new debris are useful, recent studies predicting debris evolution have indicated that these will not be enough to ensure humanity's access to and use of the near-Earth environment in the long-term. Rather, active debris removal (ADR) must be pursued if we are to continue benefiting from and conducting space activities. While the concept of ADR is not new, it has not yet been implemented. This is not just because of the technical feasibility of such a scheme, but also because of the host of economic, legal/regulatory, and political issues associated with debris remediation. The costs of ADR are not insignificant and, in today's restrictive fiscal climate, are unlikely/to be covered by any single actor. Similarly, ADR concepts bring up many unresolved questions about liability, the protection of proprietary information, safety, and standards. In addition, because of the dual use nature of ADR technologies, any venture will necessarily require political considerations. Despite the many unanswered questions surrounding ADR, it is an endeavor worth pursuing if we are to continue relying on space activities for a variety of critical daily needs and services. Moreover, we cannot ignore the environmental implications that an unsustainable use of space will imply for life on Earth in the long run. This paper aims to explore some of these

  16. SRT as a receiver in a bistatic radar space debris configuration

    NASA Astrophysics Data System (ADS)

    Pisanu, T.; Concu, R.; Gaudiomonte, F.; Marongiu, P.; Melis, A.; Serra, G.; Urru, E.; Valente, G.; Portelli, C.; Muntoni, G.; Bianchi, G.; Comoretto, G.; Dolce, F.; Paoli, J.; Reali, M.; Villadei, W.

    2016-08-01

    Space debris is becoming a very important and urgent problem for present and future space activities. For that reason many public and private Institutions in the world are being involved in order to monitor and control the debris population increase and to understand which facilities can be used for improving the surveillance and tracking capabilities. In this framework in 2014 we performed some preliminary observations in a beam parking, CW mode and a bistatic configuration, with a transmitter of 4 kW of the Italian Air Force and the SRT (Sardinia Radio Telescope) a 64 meters radiotelescope used as a receiver. We performed the observations in P band at 410 MHz, receiving the signal diffused from some debris of different sizes and distances in LEO orbit, in order to understand the performances and capabilities of the system. In this article we will describe the results of this observations campaign, the simulation work done for preparing it, the RCS (radar cross section) observed, the level of the received signals, the Doppler measurements, and the work we are doing for developing a new and higher performing digital back end, able to process the data received.

  17. Prospects for Observing Space Debris with Solar Coronagraphs

    DTIC Science & Technology

    1994-04-07

    mode designed to detect orbital debris . II 4- Coronagraph -2or -2- /• -. 0.001 s -4- -6. . . . . . -3 -2 -1 0 1 Log a (cm) Figure 1. Per-pixel signal...velocities of orbital debris and the typical direction and fast transit times of nearby particles under strong wind conditions, or random and nonlinear

  18. Orbital evolution of space debris due to aerodynamic forces

    NASA Astrophysics Data System (ADS)

    Crowther, R.

    1993-08-01

    The concepts used in the AUDIT (Assessment Using Debris Impact Theory) debris modelling suite are introduced. A sensitivity analysis is carried out to determine the dominant parameters in the modelling process. A test case simulating the explosion of a satellite suggest that at the parent altitude there is a greater probability of collision with more massive fragments.

  19. Space Shuttle and Launch Pad Lift-Off Debris Transport Analysis: SRB Plume-Driven

    NASA Technical Reports Server (NTRS)

    West, Jeff; Strutzenberg, Louis; Dougherty, Sam; Radke, Jerry; Liever, Peter

    2007-01-01

    This paper discusses the Space Shuttle Lift-Off model developed for potential Lift-Off Debris transport. A critical Lift-Off portion of the flight is defined from approximately 1.5 sec after SRB Ignition up to 'Tower Clear', where exhaust plume interactions with the Launch Pad occur. A CFD model containing the Space Shuttle and Launch Pad geometry has been constructed and executed. The CFD model works in conjunction with a debris particle transport model and a debris particle impact damage tolerance model. These models have been used to assess the effects of the Space Shuttle plumes, the wind environment, their interactions with the Launch Pad, and their ultimate effect on potential debris during Lift-Off. Emphasis in this paper is on potential debris that might be caught by the SRB plumes.

  20. Finite element analysis of space debris removal by high-power lasers

    NASA Astrophysics Data System (ADS)

    Xue, Li; Jiang, Guanlei; Yu, Shuang; Li, Ming

    2015-08-01

    With the development of space station technologies, irradiation of space debris by space-based high-power lasers, can locally generate high-temperature plasmas and micro momentum, which may achieve the removal of debris through tracking down. Considered typical square-shaped space debris of material Ti with 5cm×5cm size, whose thermal conductivity, density, specific heat capacity and emissivity are 7.62W/(m·°C), 4500kg/m3, 0.52J/(kg·°C) and 0.3,respectively, based on the finite element analysis of ANSYS, each irradiation of space debris by high-power lasers with power density 106W/m2 and weapons-grade lasers with power density 3000W/m2 are simulated under space environment, and the temperature curves due to laser thermal irradiation are obtained and compared. Results show only 2s is needed for high-power lasers to make the debris temperature reach to about 10000K, which is the threshold temperature for plasmas-state conversion. While for weapons-grade lasers, it is 13min needed. Using two line elements (TLE), and combined with the coordinate transformation from celestial coordinate system to site coordinate system, the visible period of space debris is calculated as 5-10min. That is, in order to remove space debris by laser plasmas, the laser power density should be further improved. The article provides an intuitive and visual feasibility analysis method of space debris removal, and the debris material and shape, laser power density and spot characteristics are adjustable. This finite element analysis method is low-cost, repeatable and adaptable, which has an engineering-prospective applications.

  1. Measure short separation for space debris based on radar angle error measurement information

    NASA Astrophysics Data System (ADS)

    Zhang, Yao; Wang, Qiao; Zhou, Lai-jian; Zhang, Zhuo; Li, Xiao-long

    2016-11-01

    With the increasingly frequent human activities in space, number of dead satellites and space debris has increased dramatically, bring greater risks to the available spacecraft, however, the current widespread use of measuring equipment between space target has a lot of problems, such as high development costs or the limited conditions of use. To solve this problem, use radar multi-target measure error information to the space, and combining the relationship between target and the radar station point of view, building horizontal distance decoding model. By adopting improved signal quantization digit, timing synchronization and outliers processing method, improve the measurement precision, satisfies the requirement of multi-objective near distance measurements, and the using efficiency is analyzed. By conducting the validation test, test the feasibility and effectiveness of the proposed methods.

  2. A Parametric Study on Using Active Debris Removal to Stabilize the Future LEO Debris Environment

    NASA Technical Reports Server (NTRS)

    Liou, J.C.

    2010-01-01

    Recent analyses of the instability of the orbital debris population in the low Earth orbit (LEO) region and the collision between Iridium 33 and Cosmos 2251 have reignited the interest in using active debris removal (ADR) to remediate the environment. There are; however, monumental technical, resources, operational, legal, and political challenges in making economically viable ADR a reality. Before a consensus on the need for ADR can be reached, a careful analysis of the effectiveness of ADR must be conducted. The goal is to demonstrate the feasibility of using ADR to preserve the future environment and to guide its implementation to maximize the benefit-cost ratio. This paper describes a comprehensive sensitivity study on using ADR to stabilize the future LEO debris environment. The NASA long-term, orbital debris evolutionary model, LEGEND, is used to quantify the effects of many key parameters. These parameters include (1) the starting epoch of ADR implementation, (2) various target selection criteria, (3) the benefits of collision avoidance maneuvers, (4) the consequence of targeting specific inclination or altitude regimes, (5) the consequence of targeting specific classes of vehicles, and (6) the timescale of removal. Additional analyses on the importance of postmission disposal and how future launches might affect the requirements to stabilize the environment are also included.

  3. Dodging Bullets: The Threat of Space Debris to U.S. National Security

    DTIC Science & Technology

    2010-06-11

    have orbited, or are currently orbiting, the Earth. According to a recent 2009 request for information for orbital debris removal by the Defense...international mitigation guidelines to reduce the growth of orbital debris and begin, if possible, to diminish current amounts in order to keep space...

  4. On-orbit monitoring of near-Earth space debris across the size spectrum

    NASA Astrophysics Data System (ADS)

    Mulholland, John-Derral; Kessler, Donald J.; Mandeville, Jean-Claude; Oliver, John P.; Stevenson, Tim J.

    2001-10-01

    Near-Earth space debris is a mixture of cosmic particles and manmade trash. The LDEF Interplanetary Dust Experiment was to monitor natural dust, as a followup to Explorer 46 (MTS), but analysis of the precisely-timed impact data showed that the overwhelming majority of the particles of submicron to millimeter size at ordinary satellite distances (300-500 km) are manmade, often concentrated in clouds of hundreds of kilometers dimension. At speeds of 10 km/sec and more, these objects represent hazards to useful and expensive spacecraft, manned or robotic. Protective measures are mandatory. Unhappily, there is an information gap between what shield and mission designers know and what they need to know. There is a paucity of measured data (the only real world) on the size, spatial and temporal domains of space debris. For size, there are serious gaps in our knowledge in the 1 μm to 1.5 mm range. Spatially, there are few data beyond 500 km. For the size range recorded by LDEF/IDE, there was extreme temporal fluctuation over short time scales during the period of active recording. There is surely long-term secular change also, but this is a principal crux of the problem: we do not know, because the debris environment has not been measured seriously since LDEF. We suggest that the solution is a "Debris Technology Satellite" (DTS) in the spirit of MTS, with a Sun-synchronous, perigee around 500 km, apogee 2000 km, for a duration of 10 years. Its instrument complement would include several complementary instruments to cover the size range from submicron to centimeter.

  5. Assessing the IADC Space Debris Mitigation Guidelines: A Case for Ontology-based Data Management

    NASA Astrophysics Data System (ADS)

    Walls, R.; Gaylor, D.; Reddy, V.; Furfaro, R.; Jah, M.

    2016-09-01

    As the population of man-made debris orbiting the Earth increases, so does the risk of damaging collisions. The Inter-Agency Space Debris Coordination Committee (IADC) has issued space debris mitigation guidelines including a key recommendation that before mission's end, spacecraft should move far enough from GEO so as not to be an operational hazard to other objects in active missions. It can be extremely difficult to determine if a spacecraft or operator is in compliance with this guideline, as it requires prediction of future actions based upon many data types. Furthermore, there has been no comprehensive assessment of the adequacy or validity of the IADC recommendations. The EU strives for a Code of Conduct in space, the United Nations-Committee On Peaceful Uses of Outer Space (UN-COPUOS) strives for guidelines to ensure the Long Term Sustainability of Space Activities (LTSSA), the FAA is concerned with Space Traffic Management (STM), etc. If rules, policies, guidelines, and laws are put in place, how can any entity know who and what is adhering to them, when we don't even know how to quantify and assess behavior of space objects? The University of Arizona aims to address this salient issue. As part of its new Space Object Behavioral Sciences (SOBS) initiative, the University of Arizona is developing an ontology-based system to support integration, use, and sharing of space domain data. As a first use-case, we will test the system's ability to assess compliance with the IADC recommendation to move beyond GEO at the end of a mission as well as the adequacy and validity of recommendations. We describe the relevant data types gathered for this use-case, present a prototype ontology, and outline methods for combining semantic analysis with astrodynamics modeling. Without loss of generality, we present this method as an approach that will form the foundation of SOBS and be used to address pressing challenges in Space Situational Awareness (SSA), Orbital Safety

  6. Pulsed laser interactions with space debris: Target shape effects

    SciTech Connect

    Liedahl, D. A.; Rubenchik, A.; Libby, S. B.; Nikolaev, S.; Phipps, C. R.

    2013-05-24

    Among the approaches to the proposed mitigation and remediation of the space debris problem is the de-orbiting of objects in low Earth orbit through irradiation by ground-based high-intensity pulsed lasers. Laser ablation of a thin surface layer causes target recoil, resulting in the depletion of orbital angular momentum and accelerated atmospheric re-entry. However, both the magnitude and direction of the recoil are shape dependent, a feature of the laser-based remediation concept that has received little attention. Since the development of a predictive capability is desirable, we have investigated the dynamical response to ablation of objects comprising a variety of shapes. We derive and demonstrate a simple analytical technique for calculating the ablation-driven transfer of linear momentum, emphasizing cases for which the recoil is not exclusively parallel to the incident beam. For the purposes of comparison and contrast, we examine one case of momentum transfer in the low-intensity regime, where photon pressure is the dominant momentum transfer mechanism, showing that shape and orientation effects influence the target response in a similar, but not identical, manner. As a result, we address the related problem of target spin and, by way of a few simple examples, show how ablation can alter the spin state of a target, which often has a pronounced effect on the recoil dynamics.

  7. Pulsed laser interactions with space debris: Target shape effects

    DOE PAGES

    Liedahl, D. A.; Rubenchik, A.; Libby, S. B.; ...

    2013-05-24

    Among the approaches to the proposed mitigation and remediation of the space debris problem is the de-orbiting of objects in low Earth orbit through irradiation by ground-based high-intensity pulsed lasers. Laser ablation of a thin surface layer causes target recoil, resulting in the depletion of orbital angular momentum and accelerated atmospheric re-entry. However, both the magnitude and direction of the recoil are shape dependent, a feature of the laser-based remediation concept that has received little attention. Since the development of a predictive capability is desirable, we have investigated the dynamical response to ablation of objects comprising a variety of shapes.more » We derive and demonstrate a simple analytical technique for calculating the ablation-driven transfer of linear momentum, emphasizing cases for which the recoil is not exclusively parallel to the incident beam. For the purposes of comparison and contrast, we examine one case of momentum transfer in the low-intensity regime, where photon pressure is the dominant momentum transfer mechanism, showing that shape and orientation effects influence the target response in a similar, but not identical, manner. As a result, we address the related problem of target spin and, by way of a few simple examples, show how ablation can alter the spin state of a target, which often has a pronounced effect on the recoil dynamics.« less

  8. Space Debris Symposium (A6.) Measurements and Space Surveillance (1.): Measurements of the Small Particle Debris Cloud from the 11 January, 2007 Chinese Anti-satellite Test

    NASA Technical Reports Server (NTRS)

    Matney, Mark J.; Stansbery, Eugene; J.-C Liou; Stokely, Christopher; Horstman, Matthew; Whitlock, David

    2008-01-01

    On January 11, 2007, the Chinese military conducted a test of an anti-satellite (ASAT) system, destroying their own Fengyun-1C spacecraft with an interceptor missile. The resulting hypervelocity collision created an unprecedented number of tracked debris - more than 2500 objects. These objects represent only those large enough for the US Space Surveillance Network (SSN) to track - typically objects larger than about 5-10 cm in diameter. There are expected to be even more debris objects at sizes too small to be seen and tracked by the SSN. Because of the altitude of the target satellite (865 x 845 km orbit), many of the debris are expected to have long orbital lifetimes and contribute to the orbital debris environment for decades to come. In the days and weeks following the ASAT test, NASA was able to use Lincoln Laboratory s Haystack radar on several occasions to observe portions of the ASAT debris cloud. Haystack has the capability of detecting objects down to less than one centimeter in diameter, and a large number of centimeter-sized particles corresponding to the ASAT cloud were clearly seen in the data. While Haystack cannot track these objects, the statistical sampling procedures NASA uses can give an accurate statistical picture of the characteristics of the debris from a breakup event. For years computer models based on data from ground hypervelocity collision tests (e.g., the SOCIT test) and orbital collision experiments (e.g., the P-78 and Delta-180 on-orbit collisions) have been used to predict the extent and characteristics of such hypervelocity collision debris clouds, but until now there have not been good ways to verify these models in the centimeter size regime. It is believed that unplanned collisions of objects in space similar to ASAT tests will drive the long-term future evolution of the debris environment in near-Earth space. Therefore, the Chinese ASAT test provides an excellent opportunity to test the models used to predict the future debris

  9. Large craters on the meteoroid and space debris impact experiment

    NASA Technical Reports Server (NTRS)

    Humes, Donald H.

    1992-01-01

    Examination of 29.37 sq m of thick aluminum plates from the LDEF, which were exposed to the meteoroid and man-made orbital debris environments for 5.8 years, revealed 606 craters that were 0.5 mm in diameter or larger. Most were nearly hemispherical. There was a large variation in the number density of craters around the three axis gravity gradient stabilized spacecraft. A new model of the near-Earth meteoroid environment gives good agreement with the crater fluxes measured on the fourteen faces of the LDEF. The man-made orbital debris model of Kessler, which predicts that 16 pct. of the craters would be caused by man-made debris, is plausible. No chemical analyses of impactor residue that will distinguish between meteoroids and man-made debris is yet available.

  10. Charging of Space Debris and Their Dynamical Consequences

    DTIC Science & Technology

    2016-01-08

    particle beams associated with solar flares. The PIC approach has also been used to study differential charging of debris objects that are composed of...gravitational and solar radiation pressure effects and hence may have a negligible influence on orbital calculations. However the debris charge can give...photoemission effects as well as due to the impact of energetic charged particle beams associated with solar flares. The PIC approach has also been

  11. A digital panoramic polarimeter for study of space debris and near Earth asteroids

    NASA Astrophysics Data System (ADS)

    Vidmachenko, A. P.; Delets, A. S.; Nevodovskiy, P. V.; Andruk, V. M.

    2003-12-01

    Meteorites, asteroids, and other space object (natural and artificial debris), moving in the vicinity of the Earth orbit, are very dangerous both for life on the Earth, and the Earth existence. Polarimetric method for study of near Earth asteroid and space debris is very efficient for their registrations on the background of the sky, the determination their optical and physical parameters. In MAO of NASU is has been created a polarimetric complex "Digital polarimeter", capable to execute these problems.

  12. Upgrade of DRAMA-ESA's Space Debris Mitigation Analysis Tool Suite

    NASA Astrophysics Data System (ADS)

    Gelhaus, Johannes; Sanchez-Ortiz, Noelia; Braun, Vitali; Kebschull, Christopher; de Oliveira, Joaquim Correia; Dominguez-Gonzalez, Raul; Wiedemann, Carsten; Krag, Holger; Vorsmann, Peter

    2013-08-01

    One decade ago ESA started the dev elopment of the first version of the software tool called DRAMA (Debris Risk Assessment and Mitigation Analysis) to enable ESA space programs to assess their compliance with the recommendations in the European Code of Conduct for Space Debris Mitigation. This tool was maintained, upgraded and extended during the last year and is now a combination of five individual tools, each addressing a different aspect of debris mitigation. This paper gives an overview of the new DRAMA software in general. Both, the main tools ARES, OSCAR, MIDAS, CROC and SARA will be discussed and the environment used by DRAMA will be explained shortly.

  13. Combined orbit determination of space debris using SLR and optical data

    NASA Astrophysics Data System (ADS)

    Chen, Juping

    2016-07-01

    This paper presents the combined orbit determination analysis by using the laser ranging data and optical angle direction data of space debris collected from Shanghai and Changchun SLR systems and optical tracking telescopes of Purple Mountain Observatory respectively during December 2015 to January 2016. It is shown that laser ranging is a good supplement for ground-based radar and optical telescopes system for space debris tracking. When the laser data is used for the orbit determination of LEO debris objects, the orbit determination and prediction accuracy will be improved in less than 3 days and help to avoid unnecessary anti-collision maneuvers for spacecrafts on orbit.

  14. Review of uncertainty sources affecting the long-term predictions of space debris evolutionary models

    NASA Astrophysics Data System (ADS)

    Dolado-Perez, J. C.; Pardini, Carmen; Anselmo, Luciano

    2015-08-01

    Since the launch of Sputnik-I in 1957, the amount of space debris in Earth's orbit has increased continuously. Historically, besides abandoned intact objects (spacecraft and orbital stages), the primary sources of space debris in Earth's orbit were (i) accidental and intentional break-ups which produced long-lasting debris and (ii) debris released intentionally during the operation of launch vehicle orbital stages and spacecraft. In the future, fragments generated by collisions are expected to become a significant source as well. In this context, and from a purely mathematical point of view, the orbital debris population in Low Earth Orbit (LEO) should be intrinsically unstable, due to the physics of mutual collisions and the relative ineffectiveness of natural sink mechanisms above~700 km. Therefore, the real question should not be "if", but "when" the exponential growth of the space debris population is supposed to start. From a practical point of view, and in order to answer the previous question, since the end of the 1980's several sophisticated long-term debris evolutionary models have been developed. Unfortunately, the predictions performed with such models, in particular beyond a few decades, are affected by considerable uncertainty. Such uncertainty comes from a relative important number of variables that being either under the partial control or completely out of the control of modellers, introduce a variability on the long-term simulation of the space debris population which cannot be captured with standard Monte Carlo statistics. The objective of this paper is to present and discuss many of the uncertainty sources affecting the long-term predictions done with evolutionary models, in order to serve as a roadmap for the uncertainty and the statistical robustness analysis of the long-term evolution of the space debris population.

  15. Active Debris Removal - A Grand Engineering Challenge for the Twenty-First Century

    NASA Technical Reports Server (NTRS)

    Liou, Jer-Chyi

    2010-01-01

    The collision between Iridium 33 and Cosmos 2251 in 2009 underlined the potential of an ongoing collision cascade effect (the Kessler Syndrome ) in the near-Earth orbital debris environment. A 2006 NASA analysis of the instability of the debris population in the low Earth orbit (LEO, the region below 2000 km altitude) shows that the environment has reached a point where the debris population will continue to increase in the next 200 years, even without any future launches. The increase is driven by fragments generated via collisions among existing objects in LEO. In reality, the situation will be worse than this prediction because satellite launches will continue and unexpected major breakups may continue to occur. Mitigation measures commonly adopted by the international space community (such as the 25-year rule) will help, but will be insufficient to stop the population growth. To better preserve the near-Earth space environment for future generations, active debris removal (ADR) should be considered. The idea of active debris removal is not new. However, due to the monumental technical, resource, operational, legal, and political challenges associated with removing objects from orbit, it has not yet been widely considered feasible. The recent major breakup events and the environment modeling efforts have certainly reignited the interest in using active debris removal to remediate the environment. This trend is further highlighted by the National Space Policy of the United States of America, released by the White House in June 2010, where the President explicitly directs NASA and the Department of Defense to pursue research and development of technology and techniques, to mitigate and remove on-orbit debris, reduce hazards, and increase understanding of the current and future debris environment. A 2009 modeling study by the NASA Orbital Debris Program Office has shown that, in order to maintain the LEO debris population at a constant level for the next 200 years

  16. Detection of Space-debris Using Space-Based Integrated Detection and Image Processing System

    NASA Astrophysics Data System (ADS)

    Azzazy, M.; Justice, J.

    2014-09-01

    Detection and cataloguing of space-debris is paramount to satellite operations. Space debris vary in size from very small objects 10-4 m2 to large objects approximately > 1 m2. The detection of small debris using earth-based telescopes and detection systems present a great challenge; long integration time, and large blur due to atmospheric turbulence. Space-based detection systems are usually expensive and have limited image processing capabilities to detect and track space debris. In this paper we describe the development of a relatively inexpensive space-based integrated sensor/processor that allows the detection of objects as small as 10-4 m2 at 50 km range (equivalent to star magnitude 10). The sensor noise floor is equivalent to star magnitude 12. The sensor field of regard is 60°x120°. The elevation field of regard is covered by two 25 mega-pixel focal plane arrays, each with 4 cm aperture covering 30 degrees field of view. A gimbal is then used to scan the sensor in the azimuthal direction. The sensor frame rate to cover the full field of regard is 10 frames/sec. The FPA outputs are processed onboard to register the images, remove background stars, identify the debris, and determine their coordinate and sidereal motion relative to the camera frame of reference. Image registration: rotation and translation to sub-pixel level was achieved using Radon transformation and fast Fourier transform techniques. The image registration algorithm was optimized to run on an FPGA. Star background is then removed from the registered images and the location and sidereal motion of the debris are then determined. The image processing system uses stars with magnitudes between 5 and 7 along with a look-up table map of the sky to convert the debris coordinate system to an inertial coordinate system which is then transmitted to the ground. A high fidelity simulation model has been developed and used to guide and test the image processing algorithms. The high fidelity simulation

  17. Eddy Currents applied to de-tumbling of space debris: feasibility analysis, design and optimization aspects

    NASA Astrophysics Data System (ADS)

    Ortiz Gómez, Natalia; Walker, Scott J. I.

    Existent studies on the evolution of the space debris population show that both mitigation measures and active debris removal methods are necessary in order to prevent the current population from growing. Active debris removal methods, which require contact with the target, show complications if the target is rotating at high speeds. Observed rotations go up to 50 deg/s combined with precession and nutation motions. “Natural” rotational damping in upper stages has been observed for some debris objects. This phenomenon occurs due to the eddy currents induced by the Earth’s magnetic field in the predominantly conductive materials of these man made rotating objects. The idea presented in this paper is to submit the satellite to an enhanced magnetic field in order to subdue it and damp its rotation, thus allowing for its subsequent de-orbiting phase. The braking method that is proposed has the advantage of avoiding any kind of mechanical contact with the target. A deployable structure with a magnetic coil at its end is used to induce the necessary braking torques on the target. This way, the induced magnetic field is created far away from the chaseŕs main body avoiding undesirable effects on its instruments. This paper focuses on the overall design of the system and the parameters considered are: the braking time, the power required, the mass of the deployable structure and the magnetic coil system, the size of the coil, the materials selection and distance to the target. The different equations that link all these variables together are presented. Nevertheless, these equations lead to several variables which make it possible to approach the engineering design as an optimization problem. Given that only a few variables remain, no sophisticated numerical methods are called for, and a simple graphical approach can be used to display the optimum solutions. Some parameters are open to future refinements as the optimization problem must be contemplated globally in

  18. Laser-based space debris removal: design guidelines for coherent coupling power transmission

    NASA Astrophysics Data System (ADS)

    Kästel, Jürgen; Speiser, Jochen

    2016-10-01

    Space debris presents an increasing threat to the lifetime of commercial and military space assets. Laser-based space debris removal systems could potentially mitigate this threat by targeting debris objects in the cm-range. In order to reach this goal a minimum fluence of a few J/cm² on the debris object and a pulse repetition rate of several 10 Hz are necessary. These requirements can be met by coupling 1000-2000 independent 10 J laser sources coherently and employing a sending telescope with a diameter of 5 m. We analyze which parameters are critical to the effectiveness of the transmission system and deduce design guidelines. In particular the effects of non-optimum filling factors, secondary mirror size, emitter intensity distribution and phase jitter of the individual emitters are discussed and compared.

  19. Space debris removal using a high-power ground-based laser

    SciTech Connect

    Monroe, D.K.

    1993-12-31

    The feasibility and practicality of using a ground-based laser (GBL) to remove artificial space debris is examined. Physical constraints indicate that a reactor-pumped laser (RPL) may be best suited for this mission, because of its capabilities for multimegawatt output long run-times, and near-diffraction-limited initial beams. Simulations of a laser-powered debris removal system indicate that a 5-MW RPL with a 10-meter-diameter beam director and adaptive optics capabilities can deorbit 1-kg debris from space station altitudes. Larger debris can be deorbited or transferred to safer orbits after multiple laser engagements. A ground-based laser system may be the only realistic way to access and remove some 10,000 separate objects, having velocities in the neighborhood of 7 km/sec, and being spatially distributed over some 10{sup 10} km{sup 3} of space.

  20. Validated simulator for space debris removal with nets and other flexible tethers applications

    NASA Astrophysics Data System (ADS)

    Gołębiowski, Wojciech; Michalczyk, Rafał; Dyrek, Michał; Battista, Umberto; Wormnes, Kjetil

    2016-12-01

    In the context of active debris removal technologies and preparation activities for the e.Deorbit mission, a simulator for net-shaped elastic bodies dynamics and their interactions with rigid bodies, has been developed. Its main application is to aid net design and test scenarios for space debris deorbitation. The simulator can model all the phases of the debris capturing process: net launch, flight and wrapping around the target. It handles coupled simulation of rigid and flexible bodies dynamics. Flexible bodies were implemented using Cosserat rods model. It allows to simulate flexible threads or wires with elasticity and damping for stretching, bending and torsion. Threads may be combined into structures of any topology, so the software is able to simulate nets, pure tethers, tether bundles, cages, trusses, etc. Full contact dynamics was implemented. Programmatic interaction with simulation is possible - i.e. for control implementation. The underlying model has been experimentally validated and due to significant gravity influence, experiment had to be performed in microgravity conditions. Validation experiment for parabolic flight was a downscaled process of Envisat capturing. The prepacked net was launched towards the satellite model, it expanded, hit the model and wrapped around it. The whole process was recorded with 2 fast stereographic camera sets for full 3D trajectory reconstruction. The trajectories were used to compare net dynamics to respective simulations and then to validate the simulation tool. The experiments were performed on board of a Falcon-20 aircraft, operated by National Research Council in Ottawa, Canada. Validation results show that model reflects phenomenon physics accurately enough, so it may be used for scenario evaluation and mission design purposes. The functionalities of the simulator are described in detail in the paper, as well as its underlying model, sample cases and methodology behind validation. Results are presented and

  1. Methodology of design and analysis of external walls of space station for hypervelocity impacts by meteoroids and space debris

    NASA Technical Reports Server (NTRS)

    Batla, F. A.

    1986-01-01

    The development of criteria and methodology for the design and analysis of Space Station wall elements for collisions with meteoroids and space debris at hypervelocities is discussed. These collisions will occur at velocities of 10 km/s or more and can be damaging to the external wall elements of the Space Station. The wall elements need to be designed to protect the pressurized modules of the Space Station from functional or structural failure due to these collisions at hypervelocities for a given environment and population of meteoroids and space debris. The design and analysis approach and the associated computer program presented is to achieve this objective, including the optimization of the design for a required overall probability of no penetration. The approach is based on the presently available experimental and actual data on meteoroids and space debris flux and damage assessments and the empirical relationships resulting from the hypervelocity impact studies in laboratories.

  2. A Review of the Recent NASA Long-Term Orbital Debris Environment Projection and Active Debris Removal Modeling Activities

    NASA Technical Reports Server (NTRS)

    Liou, J.C.

    2009-01-01

    The NASA Orbital Debris Program Office (ODPO) developed a high fidelity debris evolutionary model, LEGEND (a LEO-to-GEO Environment Debris model), in 2004 to enhance its capability to better model the near-Earth environment. LEGEND can mimic the growth of the historical debris population and project it into the future based on user-defined scenarios. The first major LEGEND study concluded that even without any future launches, the LEO population would continue to increase due to mutual collisions among existing objects. In reality, the increase will be worse than this prediction because of ongoing satellite launches and unexpected major breakups. Even with a full implementation of the commonly-adopted mitigation measures, the LEO population growth is inevitable. To preserve the near-Earth environment for future generations, active debris removal (ADR) must be considered. A follow-up LEGEND ADR study was completed recently. The main results indicate that (1) the mass and collision probability of each object can be used to establish an effective removal selection criterion and (2) a removal rate of 5 objects per year is sufficient to stabilize the LEO environment. Due to the limitation of removal techniques, however, different target selection criteria (in size, altitude, inclination, etc.) may be more practical. A careful evaluation of the effectiveness of different proposed techniques must be carried out to maximize the long-term benefit to the environment.

  3. Optical and In-situ Debris Measurements under Collaboration with Space Weather Science and Education

    NASA Astrophysics Data System (ADS)

    Hanada, Toshiya; Matsumoto, Haruhisa; Yoshikawa, Akimasa; Yanagisawa, Toshifumi; Kitazawa, Yukihito

    Kyushu University established International Centre for Space Weather Science and Education, shortly ICSWSE, in April 2012. The ICSWSE is leading two major research areas. One is magnetized environment of the Earth, and the other is space debris environment. Now, the ICSWSE fuses these two major research areas into one new project to contribute to the protection of space environment and space situational awareness. The ICSWSE has already established a technical and human network under the MAGnetic Data Acquisition System / Circum pan Pacific Magnetometer Array (MAGDAS/CPMN) project. Now, the ICSWSE is willing to establish a measurement network for space debris using small-aperture optical telescopes and small satellite constellation under the technical and human network, being named DEBris Data Acquisition System (DEBDAS). The telescopes are well organized to be robotically and remotely controlled, including sophisticated image processing techniques and orbit estimation software. The satellites are conducting in-situ measurements of micron-size debris using an easy-to-operate new sensor developed at JAXA. Data acquired from the systems will be analyzed and modeled in a manner coupled with space weather science to provide a better understanding of the present and future space debris environment. The ICSWSE also aims at education for practical astronomy and space engineering at Kyushu University, collaborative measurements in combination between robotic telescopes and small satellites, space environmental awareness and space science, including debris generation and resulting environment. Practical astronomy provides you with planning and observation, processing and detection, and origin identification. Space engineering provides you with small satellite design, production, and operation.

  4. Preliminary Results from Reflectance Spectroscopy Observations of Space Debris in GEO

    NASA Astrophysics Data System (ADS)

    Vananti, A.; Schidknecht, T.; Krag, H.; Erd, C.

    2009-03-01

    The space debris environment in the Geostationary Earth Orbit (GEO) region is mostly investigated using optical telescopes. The detection of the objects and the determination of their orbits are based on optical observations. However, for a better characterization of the environment it would be necessary to know the shape and the material of the objects. The area-to-mass ratio can be estimated from orbit determinations. In some rare case additional information can be derived from photometric measurements. A possible technique to investigate the material type of the debris is the reflectance spectroscopy. This paper discusses preliminary results obtained from spectrometric observations of orbital space debris. The observations were acquired at the 1-meter ESA Space Debris Telescope (ESASDT) on Tenerife with a low-resolution spectrograph in the wavelength range of 450-960 nm. The observed objects are space debris in GEO orbits with brightness as small as magnitude 16. The spectra show shape variations expected to be caused by the different physical properties of the objects. The determination of the material and of the type of object is still in a preliminary phase. Limitations of the acquisition process of the spectra and the subsequent analysis are discussed. Future steps planned for a better characterization of the debris from the observed data are briefly outlined.

  5. A laser-optical system to re-enter or lower low Earth orbit space debris

    NASA Astrophysics Data System (ADS)

    Phipps, Claude R.

    2014-01-01

    Collisions among existing Low Earth Orbit (LEO) debris are now a main source of new debris, threatening future use of LEO space. Due to their greater number, small (1-10 cm) debris are the main threat, while large (>10 cm) objects are the main source of new debris. Flying up and interacting with each large object is inefficient due to the energy cost of orbit plane changes, and quite expensive per object removed. Strategically, it is imperative to remove both small and large debris. Laser-Orbital-Debris-Removal (LODR), is the only solution that can address both large and small debris. In this paper, we briefly review ground-based LODR, and discuss how a polar location can dramatically increase its effectiveness for the important class of sun-synchronous orbit (SSO) objects. With 20% clear weather, a laser-optical system at either pole could lower the 8-ton ENVISAT by 40 km in about 8 weeks, reducing the hazard it represents by a factor of four. We also discuss the advantages and disadvantages of a space-based LODR system. We estimate cost per object removed for these systems. International cooperation is essential for designing, building and operating any such system.

  6. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray F11

    NASA Technical Reports Server (NTRS)

    1990-01-01

    LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray F11 The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks at the right end of the upper tray flange and at the center of the lower and left tray flanges have changed slightly to an off-white color. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The vertical streaks observed on the right debris panel in the flight photograph are no longer visible since the blue sky reflection is not present. Debris from other experiments, significantly degraded during the mission, are visible on the lower experiment tray sidewall at its intersection with the right tray sidewall. A larger piece is located in the upper right corner on the right debris panel. Other experiment debris, visible as dark specks, can be seen at the intersection of the debris panel outer edges and the tray sidewalls. The light band along the sides and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  7. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray E11

    NASA Technical Reports Server (NTRS)

    1990-01-01

    LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray E11 The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks at the left end of the lower tray flange and at the center of the upper and right tray flanges have changed slightly to an off-white color. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The vertical streaks observed on the debris panels in the flight photograph are no longer visible since the blue sky reflection is not present. Debris from other experiments, significantly degraded during the mission, are visible on the lower experiment tray sidewall at its intersection with the lower edge of the debris panels. Other experiment debris, visible as dark specks, can be seen at the intersection of the debris panel outer edges and the tray sidewalls. The light band along the sides and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  8. Observing orbital debris using space-based telescopes. I - Mission orbit considerations

    NASA Technical Reports Server (NTRS)

    Reynolds, Robert C.; Talent, David L.; Vilas, Faith

    1989-01-01

    In this paper, mission orbit considerations are addressed for using the Space Shuttle as a telescope platform for observing man-made orbital debris. Computer modeling of various electrooptical systems predicts that such a space-borne system will be able to detect particles as small as 1-mm diameter. The research is meant to support the development of debris- collision warning sensors through the acquisition of spatial distribution and spectral characteristics for debris and testing of detector combinations on a shuttle-borne telescopic experiment. The technique can also be applied to low-earth-orbit-debris environment monitoring systems. It is shown how the choice of mission orbit, season of launch, and time of day of launch may be employed to provide extended periods of favorable observing conditions.

  9. Space debris removal by ground-based lasers: main conclusions of the European project CLEANSPACE.

    PubMed

    Esmiller, Bruno; Jacquelard, Christophe; Eckel, Hans-Albert; Wnuk, Edwin

    2014-11-01

    Studies show that the number of debris in low Earth orbit is exponentially growing despite future debris release mitigation measures considered. Specifically, the already existing population of small and medium debris (between 1 cm and several dozens of cm) is today a concrete threat to operational satellites. A ground-based laser solution which can remove, at low expense and in a nondestructive way, hazardous debris around selected space assets appears as a highly promising answer. This solution is studied within the framework of the CLEANSPACE project which is part of the FP7 space program. The overall CLEANSPACE objective is: to propose an efficient and affordable global system architecture, to tackle safety regulation aspects, political implications and future collaborations, to develop affordable technological bricks, and to establish a roadmap for the development and the future implantation of a fully functional laser protection system. This paper will present the main conclusions of the CLEANSPACE project.

  10. Space debris removal using a high-power ground-based laser

    SciTech Connect

    Monroe, D.K.

    1993-08-01

    The feasibility of utilizing a ground-based laser without an orbital mirror for space debris removal is examined. Technical issues include atmospheric transmission losses, adaptive-optics corrections of wavefront distortions, laser field of view limitations, and laser-induced impulse generation. The physical constraints require a laser with megawatt output, long run-time capability, and wavelength with good atmospheric transmission characteristics. It is found that a 5-MW reactor-pumped laser can deorbit debris having masses of the order of one kilogram from orbital altitudes to be used by Space Station Freedom. Debris under one kilogram can be deorbited after one pass over the laser site, while larger debris can be deorbited or transferred to alternate orbits after multiple passes over the site.

  11. Lessons Learned from Natural Space Debris in Heliocentric Orbit: An Analogue for Hazardous Debris in Earth Orbit

    NASA Astrophysics Data System (ADS)

    Russell, C. T.; Wei, Hanying; Connors, Martin; Lai, Hairong; Delzanno, Gian Luca

    there is a spread of the IFE rate around the descending node, indicating that the co-orbiting materials have significant dispersion about the asteroid’s orbit. In summary, orbiting debris in orbits intersecting at high speeds can destroy itself quite efficiently, but with a long timescale. In deep space, this process is a step on the path between the asteroidal source population and the creation of solar system dust. This may be true for Earth-orbiting debris as well.

  12. Operational Impact of Improved Space Tracking on Collision Avoidance in the Future LEO Space Debris Environment

    DTIC Science & Technology

    2010-09-01

    objects at the time of closest approach. Keywords: Orbital Debris , Conjunction, Collision Avoidance, Future Debris Field Report Documentation Page...critical satellites can suddenly be lost in a collision. Large spikes in the tracked orbital debris population associated with this collision, the...perform the analysis required for this study, an up-to-date orbital debris model with associated predictions of the future debris field was required. The

  13. Bi-objective optimization of a multiple-target active debris removal mission

    NASA Astrophysics Data System (ADS)

    Bérend, Nicolas; Olive, Xavier

    2016-05-01

    The increasing number of space debris in Low-Earth Orbit (LEO) raises the question of future Active Debris Removal (ADR) operations. Typical ADR scenarios rely on an Orbital Transfer Vehicle (OTV) using one of the two following disposal strategies: the first one consists in attaching a deorbiting kit, such as a solid rocket booster, to the debris after rendezvous; with the second one, the OTV captures the debris and moves it to a low-perigee disposal orbit. For multiple-target ADR scenarios, the design of such a mission is very complex, as it involves two optimization levels: one for the space debris sequence, and a second one for the "elementary" orbit transfer strategy from a released debris to the next one in the sequence. This problem can be seen as a Time-Dependant Traveling Salesman Problem (TDTSP) with two objective functions to minimize: the total mission duration and the total propellant consumption. In order to efficiently solve this problem, ONERA has designed, under CNES contract, TOPAS (Tool for Optimal Planning of ADR Sequence), a tool that implements a Branch & Bound method developed in previous work together with a dedicated algorithm for optimizing the "elementary" orbit transfer. A single run of this tool yields an estimation of the Pareto front of the problem, which exhibits the trade-off between mission duration and propellant consumption. We first detail our solution to cope with the combinatorial explosion of complex ADR scenarios with 10 debris. The key point of this approach is to define the orbit transfer strategy through a small set of parameters, allowing an acceptable compromise between the quality of the optimum solution and the calculation cost. Then we present optimization results obtained for various 10 debris removal scenarios involving a 15-ton OTV, using either the deorbiting kit or the disposal orbit strategy. We show that the advantage of one strategy upon the other depends on the propellant margin, the maximum duration allowed

  14. Passive optical detection of submillimeter and millimeter size space debris in low Earth orbit

    NASA Astrophysics Data System (ADS)

    Gruntman, Mike

    2014-12-01

    Understanding of the space debris environment and accuracy of its observation-validated models are essential for optimal design and safe operation of satellite systems. Existing ground-based optical telescopes and radars are not capable of observing debris smaller than several millimeters in size. A new experimental and instrumental approach - the space-based Local Orbital Debris Environment (LODE) detector - aims at in situ measuring of debris with sizes from 0.2-10 mm near the satellite orbit. The LODE concept relies on a passive optical photon-counting time-tagging imaging system detecting solar photons (in the visible spectral range) reflected by debris crossing the sensor field of view. In contrast, prior feasibility studies of space-based optical sensors considered frame detectors in the focal plane. The article describes the new experimental concept, discusses top-level system parameters and design tradeoffs, outlines an approach to identifying and extracting rare debris detection events from the background, and presents an example of performance characteristics of a LODE sensor with a 6-cm diameter aperture. The article concludes with a discussion of possible sensor applications on satellites.

  15. The first velocity space image of a planetary debris disc orbiting a white dwarf

    NASA Astrophysics Data System (ADS)

    Manser, Christopher James

    2015-12-01

    Since the first ESS meeting, dusty debris discs at white dwarfs have been firmly established as signposts of evolved planetary systems. We have identified a small number of systems where the circumstellar dust is accompanied by gas. The emission lines from these gaseous components are tracers of dynamic activity in these remnant planetary environments, and provide unparalleled insight into the formation and evolution of the debris discs, and into the properties of the parent planetesimals.Here we present the twelve years of spectroscopy of the prototypical gas disc at SDSS J1228+1040, revealing a spectacular long-term evolution in the morphology of the emission line profiles. Using Doppler tomography, we constructed an image of the gaseous disc in velocity space, and show that the observations are consistent with the precession of a fixed intensity pattern on a period of 27 ± 3 years. We speculate that the underlying cause of this dynamical activity is either a young, not fully circularised disc, or a perturbation of a previously stable and quiescent disc.

  16. Implementation of National Space Policy on US Air Force End of Life Operations and Orbital Debris Mitigation

    DTIC Science & Technology

    2012-06-01

    the orbital debris problem in Low Earth Orbit (LEO). Therefore current EOL plans are written largely with the aim of reducing long-lasting debris that...Space Command policies for mitigation of orbital debris , this paper details several considerations for writing operational EOL plans, with special...assess and minimize orbital debris released during and after EOL satellite passivation by accidental explosions, by intentional breakup and due to on

  17. An active debris removal parametric study for LEO environment remediation

    NASA Astrophysics Data System (ADS)

    Liou, J.-C.

    2011-06-01

    Recent analyses on the instability of the orbital debris population in the low Earth orbit (LEO) region and the collision between Iridium 33 and Cosmos 2251 have reignited interest in using active debris removal (ADR) to remediate the environment. There are, however, monumental technical, resource, operational, legal, and political challenges in making economically viable ADR a reality. Before a consensus on the need for ADR can be reached, a careful analysis of its effectiveness must be conducted. The goal is to demonstrate the need and feasibility of using ADR to better preserve the future environment and to explore different operational options to maximize the benefit-to-cost ratio. This paper describes a new sensitivity study on using ADR to stabilize the future LEO debris environment. The NASA long-term orbital debris evolutionary model, LEGEND, is used to quantify the effects of several key parameters, including target selection criteria/constraints and the starting epoch of ADR implementation. Additional analyses on potential ADR targets among the existing satellites and the benefits of collision avoidance maneuvers are also included.

  18. Statistical Analysis of Micrometeoroid and Space Debris Impacts on the Space Station "Salyut-4"

    NASA Astrophysics Data System (ADS)

    Rebrikov, V. N.

    2009-03-01

    It is common to consider the flow of micrometeoroids and space debris (MM/SD) as the Poisson one when calculating risks for spaceship [1]. However even the first studies of the near Earth space with the aid of spaceships where sensors of particle registrations have been set allow us to suppose that registered streams have very complex features [2-3].The objective of this work is the statistical analysis of MM/SD registration data onboard station "Salut-4" and specification of their distribution models in the near Earth. As initial data we used results of studies performed on stations "Salyut-4" and obtained with the help of the control system. This system was used for detecting of the MM/SD impacts and consisted of condenser sensors (CS) and an electronic device.

  19. Design of a shuttle-based space debris telescope

    NASA Technical Reports Server (NTRS)

    Richardson, E. H.; Talent, D. L.; Tritsch, C. L.; Vilas, F.

    1990-01-01

    A 1.6-meter diameter f/0.95 all-reflecting telescope was designed to observe orbital debris particles as small as 1 mm from the shuttle payload bay. The telescope was specified to have a flat focal surface without the imposition of refractive elements. Two design configurations involving three mirrors were evaluated - a reflective Schmidt-Cassegrain and a modified Paul corrector. The Paul system was found to be more compact and appropriate for this application.

  20. Estimation of debris dispersion due to a space vehicle breakup during reentry

    NASA Astrophysics Data System (ADS)

    Reyhanoglu, Mahmut; Alvarado, Juan

    2013-05-01

    This paper studies the problem of the estimation of the extent of the airspace containing falling debris due to a space vehicle breakup. A precise propagation of debris to the ground is not practical for many reasons. There is insufficient knowledge of the initial state vector, ambient wind conditions, and the key parameters including the ballistic coefficients. In addition, propagation of all debris pieces to the ground would require extensive computer time. In this paper, a covariance propagation method is introduced for the estimation of debris dispersion due to a space vehicle breakup. The falling debris is simulated, and the data are analyzed to derive the probability of debris evolution in different altitude layers over time. The concept of positional probability ellipsoids is employed for the visualization of the results. Through a case study, it is shown that while the results of the covariance propagation method are in close agreement with those of the Monte Carlo method, the covariance propagation method is much more computationally efficient than the Monte Carlo method.

  1. A computational model for assessing high-velocity debris impact in space applications

    NASA Astrophysics Data System (ADS)

    Bergh, M.; Garcia, V.

    2017-01-01

    Man-made space debris is dominating the background meteorite environment with a growing debris population leading to increased collision risks for satellites, especially in the low Earth orbit and geostationary orbit protected environments. Here we present a computational model for estimating the effect of hypervelocity impact from debris particles on non-shielded propellant and pressurant tanks. Eulerian hydrocode simulation is utilised to model firstly penetration and shock wave formation in the propellant and secondly subsequent detonation wave propagation and interaction with the tank wall. Furthermore, reactive molecular dynamics is used to estimate the risk of detonation in a liquid hydrazine layer. We present simulations of a 3.5 mm aluminium spherical debris particle at a velocity of 14 km/s relative to a hydrazine tank. We find that the degree of damage is strongly dependent on tank temperature and hence on the satellite thermal configuration at its end of life.

  2. The bistatic radar capabilities of the Medicina radiotelescopes in space debris detection and tracking

    NASA Astrophysics Data System (ADS)

    Montebugnoli, S.; Pupillo, G.; Salerno, E.; Pluchino, S.; di Martino, M.

    2010-03-01

    An accurate measurement of the position and trajectory of the space debris fragments is of primary importance for the characterization of the orbital debris environment. The Medicina Radioastronomical Station is a radio observation facility that is here proposed as receiving part of a ground-based space surveillance system for detecting and tracking space debris at different orbital regions (from Low Earth Orbits up to Geostationary Earth Orbits). The proposed system consists of two bistatic radars formed by the existing Medicina receiving antennas coupled with appropriate transmitters. This paper focuses on the current features and future technical development of the receiving part of the observational setup. Outlines of possible transmitting systems will also be given together with the evaluation of the observation strategies achievable with the proposed facilities.

  3. Spin period and attitude of satellites and space debris measured by using photometry

    NASA Astrophysics Data System (ADS)

    Shakun, Leonid; Koshkin, Nikolay; Korobeynikova, Elena; Strakhova, Svetlana; Melikyants, Seda; Ryabov, Andrey

    2016-07-01

    Photometry is an essential method for studying of the properties of the proper rotation of satellites and space debris. The observation method with high time resolution is used in the Odessa astronomical observatory for observations of artificial satellites. This method provides the measuring of the orbital motion and the proper rotation of satellites. Worth note, that the time resolution of the light curve and the accuracy of positioning in time of the details in the light curve are more important for the interpretation of the brightness variations than the precise measuring of the brightness. The rapid photometry allows not only registering of the flashes caused by mirror surfaces of structure satellite elements but also determining the indicatrix of the corresponding structure satellite element. This principal change of the photometric quality allows significant improving the interpretation of the satellites' light curves. We obtained a large amount of the photometric observations sequences of the satellites with time resolution 0.02 sec on the 50 cm telescope during last 11 years. We used this data for determination of the rotational parameters of several space objects. We present the method and results of the data analysis for the inactive satellites such as Envisat, Cbers-2B, Topex and other. Each of them changes its rotational parameters in its own way. For some satellites, the rotation period increases, for other it decreases. The rotation axis also change their orientation in space. The obtained information about rotation characteristics can be used for the precise numerical models of the satellite orbital motion and for the future Active Debris Removal missions.

  4. The mechanics of motorised momentum exchange tethers when applied to active debris removal from LEO

    SciTech Connect

    Caldecott, Ralph; Kamarulzaman, Dayangku N. S.; Kirrane, James P.; Cartmell, Matthew P.; Ganilova, Olga A.

    2014-12-10

    The concept of momentum exchange when applied to space tethers for propulsion is well established, and a considerable body of literature now exists on the on-orbit modelling, the dynamics, and also the control of a large range of tether system applications. The authors consider here a new application for the Motorised Momentum Exchange Tether by highlighting three key stages of development leading to a conceptualisation that can subsequently be developed into a technology for Active Debris Removal. The paper starts with a study of the on-orbit mechanics of a full sized motorised tether in which it is shown that a laden and therefore highly massasymmetrical tether can still be forced to spin, and certainly to librate, thereby confirming its possible usefulness for active debris removal (ADR). The second part of the paper concentrates on the modelling of the centripetal deployment of a symmetrical MMET in order to get it initialized for debris removal operations, and the third and final part of the paper provides an entry into scale modelling for low cost mission design and testing. It is shown that the motorised momentum exchange tether offers a potential solution to the removal of large pieces of orbital debris, and that dynamic methodologies can be implemented to in order to optimise the emergent design.

  5. The mechanics of motorised momentum exchange tethers when applied to active debris removal from LEO

    NASA Astrophysics Data System (ADS)

    Caldecott, Ralph; Kamarulzaman, Dayangku N. S.; Kirrane, James P.; Cartmell, Matthew P.; Ganilova, Olga A.

    2014-12-01

    The concept of momentum exchange when applied to space tethers for propulsion is well established, and a considerable body of literature now exists on the on-orbit modelling, the dynamics, and also the control of a large range of tether system applications. The authors consider here a new application for the Motorised Momentum Exchange Tether by highlighting three key stages of development leading to a conceptualisation that can subsequently be developed into a technology for Active Debris Removal. The paper starts with a study of the on-orbit mechanics of a full sized motorised tether in which it is shown that a laden and therefore highly massasymmetrical tether can still be forced to spin, and certainly to librate, thereby confirming its possible usefulness for active debris removal (ADR). The second part of the paper concentrates on the modelling of the centripetal deployment of a symmetrical MMET in order to get it initialized for debris removal operations, and the third and final part of the paper provides an entry into scale modelling for low cost mission design and testing. It is shown that the motorised momentum exchange tether offers a potential solution to the removal of large pieces of orbital debris, and that dynamic methodologies can be implemented to in order to optimise the emergent design.

  6. Three Dimension Position of Space Debris with Laser Ranging and Optical Astrometry

    NASA Astrophysics Data System (ADS)

    Yu, Y.; Li, Y.; Mao, Y. D.; Cao, J. J.; Tang, Z. H.; Zhang, Z. P.

    2015-10-01

    According to the principles of space debris orbit determination, its success rate and reliability will be improved if the celestial coordinates are known at the time of the laser ranging. The method of determining the 3D location of space debris by laser ranging and optical astrometry is presented. A test platform is established by installing a photographic equipment on the 60cm satellite laser ranging telescope system of the Shanghai Astronomical Observatory. Experimental observations are carried out and the satellite Ajisai is chosen as the target. The results show this method is feasible and the angle measurement accuracy of the satellite Ajisai is about 5 arc second.

  7. Mitigation Policy Scenario of Space Debris Threat Related with National Security

    NASA Astrophysics Data System (ADS)

    Herdiansyah, Herdis; Frimawaty, Evy; Munir, Ahmad

    2016-02-01

    The development of air space recently entered a new phase, when the space issues correlated with the future of a country. In past time, the space authorization was related with advancing technology by many space mission and various satellite launchings, or it could be said that who ruled technology will rule the space. Therefore, the numerous satellites in the space could be a threat for the countries which are mainly located in the path of the satellite, especially in the equatorial region including Indonesia. This study aims to create a policy scenario in mitigating the threat of space debris. The results showed that although space debris was not threatened national security for now, but the potential and its impact on the future potentially harmful. The threats of orbit circulation for some experts considered as a threat for national security, because its danger potential which caused by space debris could significantly damage the affected areas. However, until now Indonesia has no comprehensive mitigation strategy for space matters although it has been ratified by the United Nations Convention.

  8. Application of multi-agent coordination methods to the design of space debris mitigation tours

    NASA Astrophysics Data System (ADS)

    Stuart, Jeffrey; Howell, Kathleen; Wilson, Roby

    2016-04-01

    The growth in the number of defunct and fragmented objects near to the Earth poses a growing hazard to launch operations as well as existing on-orbit assets. Numerous studies have demonstrated the positive impact of active debris mitigation campaigns upon the growth of debris populations, but comparatively fewer investigations incorporate specific mission scenarios. Furthermore, while many active mitigation methods have been proposed, certain classes of debris objects are amenable to mitigation campaigns employing chaser spacecraft with existing chemical and low-thrust propulsive technologies. This investigation incorporates an ant colony optimization routing algorithm and multi-agent coordination via auctions into a debris mitigation tour scheme suitable for preliminary mission design and analysis as well as spacecraft flight operations.

  9. Space Debris Surfaces (Computer Code): Probability of No Penetration Versus Impact Velocity and Obliquity

    NASA Technical Reports Server (NTRS)

    Elfer, N.; Meibaum, R.; Olsen, G.

    1995-01-01

    A unique collection of computer codes, Space Debris Surfaces (SD_SURF), have been developed to assist in the design and analysis of space debris protection systems. SD_SURF calculates and summarizes a vehicle's vulnerability to space debris as a function of impact velocity and obliquity. An SD_SURF analysis will show which velocities and obliquities are the most probable to cause a penetration. This determination can help the analyst select a shield design that is best suited to the predominant penetration mechanism. The analysis also suggests the most suitable parameters for development or verification testing. The SD_SURF programs offer the option of either FORTRAN programs or Microsoft-EXCEL spreadsheets and macros. The FORTRAN programs work with BUMPERII. The EXCEL spreadsheets and macros can be used independently or with selected output from the SD_SURF FORTRAN programs. Examples will be presented of the interaction between space vehicle geometry, the space debris environment, and the penetration and critical damage ballistic limit surfaces of the shield under consideration.

  10. A history of meteoroid and orbital debris impacts on the Space Shuttle

    NASA Astrophysics Data System (ADS)

    Hyde, J. L.; Christiansen, E. L.; Bernhard, R. P.; Kerr, J. H.; Lear, D. M.

    2001-10-01

    This paper describes observations and analyses of meteoroid and debris impact damage on the Space Shuttle Orbiter. NASA's Space Transportation System Orbiter has been in service since 1981. The reusable nature of the orbiter necessitates post-flight inspection and repair of exterior thermal protection system surfaces. Since 1992, post flight inspections have included an assessment of meteoroid/debris impacts in selected areas of the vehicle. Hypervelocity impact sites are identified post-flight on the crew module windows, payload bay door radiators, payload bay door exterior insulation and wing leading edge surfaces and subjected to sample collection and analysis. One product of the analyses is determination of impactor source (meteoroid or orbital debris) by scanning electron microscope (SEM) energy dispersive X-ray analysis (EDXA) of residual impactor materials recovered from the impact site.

  11. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray F10

    NASA Technical Reports Server (NTRS)

    1990-01-01

    LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray F10 The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks at the right end of the upper tray flange and at the center of the bottom and left tray flanges have changed slightly to an off-white color. The green tint on the two (2) debris panels is a by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. A light colored irregular shaped vertical streak is seen on the right debris panel. The light band across the top and bottom edges of the panels is caused by light reflecting from the tray sidewalls.

  12. Active debris removal GNC challenges over design and required ground validation

    NASA Astrophysics Data System (ADS)

    Colmenarejo, Pablo; Avilés, Marcos; di Sotto, Emanuele

    2015-06-01

    Because of the exponential growth of space debris, the access to space in the medium-term future is considered as being seriously compromised, particularly within LEO polar Sun-synchronous orbits and within geostationary orbits. The active debris removal (ADR) application poses new and challenging requirements on: first, the new required Guidance, Navigation and Control (GNC) technologies and, second, how to validate these new technologies before being applied in real missions. There is no doubt about the strong safety and collision risk aspects affecting the real operational ADR missions. But it shall be considered that even ADR demonstration missions will be affected by significant risk of collision during the demonstration, and that the ADR GNC systems/technologies to be used shall be well mature before using/demonstrating them in space. Specific and dedicated on-ground validation approaches, techniques and facilities are mandatory. The different ADR techniques can be roughly catalogued in three main groups (rigid capture, non-rigid capture and contactless). All of them have a strong impact on the GNC system of the active vehicle during the capture/proximity phase and, particularly, during the active vehicle/debris combo control phase after capture and during the de-orbiting phase. The main operational phases on an ADR scenario are: (1) ground controlled phase (ADR vehicle and debris are far), (2) fine orbit synchronization phase (ADR vehicle to reach debris ±V-bar), (3) short range phase (along track distance reduction till 10-100 s of metres), (4) terminal approach/capture phase and (5) de-orbiting. While phases 1-3 are somehow conventional and already addressed in detail during past/on-going studies related to rendezvous and/or formation flying, phases 4-5 are very specific and not mature in terms of GNC needed technologies and HW equipment. GMV is currently performing different internal activities and ESA studies/developments related to ADR mission, GNC and

  13. Autonomous shooting at middle size space debris objects from space-based APT laser systems

    NASA Astrophysics Data System (ADS)

    Gambi, J. M.; García del Pino, M. L.

    2017-02-01

    This paper is motivated by the need of removing middle size space debris objects. It deals with the problem of increasing the pointing accuracy while shooting at these objects by means of autonomous space-based APT systems endowed with very narrow laser beams. It is shown that shooting at these objects with these systems is the one single ballistic problem that becomes singular in space. This means that the shooting direction that is to be implemented by any of these systems to reach an object at a given instant can only be hopefully implemented after the object has been previously reached. Thus, the problem becomes backwards recurrent with no end for any object-system configuration, except when the LOS direction remains constant for some period of time. It is also shown that the implementation of the point-ahead angles from the data acquired prior to the respective shootings is essential to keep accuracy. In fact, one single omission during the action may cause errors larger than the size of the objects. As a consequence, we find that there is only one way for an autonomous system to minimize the pointing errors: any shooting sequence to any of these objects must be started when the transverse component of the relative velocity of the object with respect to the system is zero (actually, as close to zero as possible).

  14. Catalogue of space objects and events as a powerful tool for scientific researches on space debris

    NASA Astrophysics Data System (ADS)

    Agapov, V.; Stepanyants, V.; Tuchin, A.; Khutorovsky, Z.

    Wide work on developing and maintenance of the Catalogue of scientific information on space objects and events is continuing at the Keldysh Institute of Applied Mathematics. The work is making in cooperation with Russian company "Space information analytical systems" (KIA Systems). Powerful software tool is developed by now including:- informational core (relational database in RDBMS Oracle 8i environment)with special tools for automatic initial processing and systematization ofdata- software complex for orbital modeling and space objects and eventsdynamical catalogue maintenance- special information - analytical software Informational core covers wide spectrum of data needed for following purposes:- full-scale and high quality modeling of object's motion in near-Earth space(orbital and measurement data, solar flux and geomagnetic indices, Earthrotation parameters etc.)- determination of various events parameters (launches, manoeuvres,fragmentations etc.)- analysis of space debris sources- studying long-term orbital evolution (over several years or tens of years)- other The database is storing huge volume of data including:- optical measurements- TLEs- information about all space launches took place since 1957- information about space missions and programs- manoeuvres- fragmentations- launch sequences for typical orbital insertions- various characteristics for orbital objects (payloads, stages, fragments)- officially released UN and ITU registration data- other By now there are records storing in informational core for more than 28000 orbital objects (both catalogued and not), about all orbital launch attempts since 04.10.1957 (including failed ones), more than 30millions records of orbital information (TLEs, state vectors, polynomial data), more than 200000 optical measurements (normal places) for GEO region objects, calculated data on more than 14 millions of close approaches had taken place during last five years and other data. Software complex for orbital

  15. Laser Ranging for Effective and Accurate Tracking of Space Debris in Low Earth Orbits

    NASA Astrophysics Data System (ADS)

    Blanchet, Guillaume; Haag, Herve; Hennegrave, Laurent; Assemat, Francois; Vial, Sophie; Samain, Etienne

    2013-08-01

    The paper presents the results of preliminary design options for an operational laser ranging system adapted to the measurement of the distance of space debris. Thorough analysis of the operational parameters is provided with identification of performance drivers and assessment of enabling design options. Results from performance simulation demonstrate how the range measurement enables improvement of the orbit determination when combined with astrometry. Besides, experimental results on rocket-stage class debris in LEO were obtained by Astrium beginning of 2012, in collaboration with the Observatoire de la Côte d'Azur (OCA), by operating an experimental laser ranging system supported by the MéO (Métrologie Optique) telescope.

  16. Preface: Advances in asteroid and space debris science and technology - Part 2

    NASA Astrophysics Data System (ADS)

    Vasile, Massimiliano

    2016-04-01

    Asteroids and space debris represent a significant hazard for space and terrestrial assets; at the same time asteroids represent also an opportunity. In recent years it has become clear that the increasing population of space debris could lead to catastrophic consequences in the near term. The Kessler syndrome (where the density of objects in orbit is high enough that collisions could set off a cascade) is more realistic than when it was first proposed in 1978. Although statistically less likely to occur, an asteroid impact would have devastating consequences for our planet. Although an impact with a large (∼10 km) to medium (∼300 m) sized, or diameter, asteroid is unlikely, still it is not negligible as the recent case of the asteroid Apophis has demonstrated. Furthermore impacts with smaller size objects, between 10 m and 100 m diameter, are expected to occur more frequently and hence are, proportionally, equally dangerous for humans and assets on Earth and in space.

  17. Preface: Advances in Asteroid and Space Debris Science and Technology - Part 1

    NASA Astrophysics Data System (ADS)

    Vasile, Massimiliano

    2015-08-01

    Asteroids and space debris represent a significant hazard for space and terrestrial assets; at the same time asteroids represent also an opportunity. In recent years it has become clear that the increasing population of space debris could lead to catastrophic consequences in the near term. The Kessler syndrome (where the density of objects in orbit is high enough that collisions could set off a cascade) is more realistic than when it was first proposed in 1978. Although statistically less likely to occur, an asteroid impact would have devastating consequences for our planet. While an impact with a large (∼10 km) to medium (∼300 m) sized, or diameter, asteroid is unlikely, still it is not negligible as the recent case of the asteroid Apophis has demonstrated. Furthermore impacts with smaller size objects, between 10 m to 100 m diameter, are expected to occur more frequently and hence are, proportionally, equally dangerous for humans and assets on Earth and in space.

  18. Results of Space Debris Survey Observations on Highly-Eccentric MEO Orbits

    NASA Astrophysics Data System (ADS)

    Hinze, Andreas; Schildknecht, T.; Flohrer, T.; Krag, H.

    2013-08-01

    Optical surveys for space debris in high-altitude orbits have been conducted since more than ten years. First observation strategies and processing techniques were successfully developed for the geostationary ring (GEO). The observations scenarios were adjusted for observations in the geostationary transfer orbit (GTO) and in the medium Earth orbit (MEO). After the already investigated circular MEO orbits of the GPS and GLONASS constellations the Astronomical Institute of the University of Bern (AIUB) developed survey and follow-up strategies for the systematically search of space debris in highly-eccentric orbits in the MEO region, in particular in Molniya-type orbits. Several breakup events and deliberate fragmentations are known to have taken place in such orbits. The AIUB performed several survey campaigns between January 2013 and April 2013 to search for debris objects in this MEO region. The optical observations were conducted in the framework of an ESA study using ESA's Space Debris Telescope (ESASDT) the 1-m Zeiss telescope located at the Optical Ground Station (OGS) at the Teide Observatory at Tenerife, Spain. The results from the different observation campaigns will be presented.

  19. Space Shuttle and Launch Pad Computational Fluid Dynamics Model for Lift-off Debris Transport Analysis

    NASA Technical Reports Server (NTRS)

    Dougherty, Sam; West, Jeff; Droege, Alan; Wilson, Josh; Liever, Peter; Slaby, Matthew

    2006-01-01

    This paper discusses the Space Shuttle Lift-off CFD model developed for potential Lift-off Debris transport for return-to-flight. The Lift-off portion of the flight is defined as the time starting with tanking of propellants until tower clear, approximately T0+6 seconds, where interactions with the launch pad cease. A CFD model containing the Space Shuttle and launch Pad geometry has been constructed and executed. Simplifications required in the construction of the model are presented and discussed. A body-fitted overset grid of up to 170 million grid points was developed which allowed positioning of the Vehicle relative to the Launch Pad over the first six seconds of Climb-Out. The CFD model works in conjunction with a debris particle transport model and a debris particle impact damage tolerance model. These models have been used to assess the interactions of the Space Shuttle plumes, the wind environment, and their interactions with each other and the Launch Pad and their ultimate effect on potential debris during Lift-off.

  20. Debris Disk Science Enabled by a Probe-scale Space Coronagraph Mission

    NASA Astrophysics Data System (ADS)

    Stapelfeldt, Karl R.; Trauger, J. T.; Krist, J. E.

    2010-01-01

    Debris disks are the signposts of planetary systems: collisions between rocky/icy parent bodies maintain debris dust around main sequence stars against losses to radiation pressure and P-R drag. Debris disk structures show the location of asteroid/Kuiper belts around nearby stars, and reflect dynamical interactions with local extrasolar planets. Only 17 debris disks with high optical depth have been spatially resolved to date in scattered light images made with the Hubble Space Telescope and ground-based adaptive optics. Hundreds more with lower optical depth have been identified among nearby stars through far-IR photometry with the Spitzer Space Telescope, and more should follow in the next few years from Herschel. The most capable means for imaging this larger disk population is a next-generation coronagraphic instrument on a 1.5m class optical space telescope. Utilizing high-contrasat imaging simulations validated by laboratory demonstrations on the JPL High Contrast Imaging Testbed, we show that such a mission will be capable of imaging Kuiper disk structures down to the 10 zodi level, and exozodiacal dust down to the 1 zodi level, around a major sample of nearby stars. This performance goes well beyond what is about to be achieved with upcoming extreme adaptive optics systems or the ALMA array, and thus provides the best path for imaging exploration of planetary systems in the solar neighborhood.

  1. Study the Space Debris Impact in the Early Stages of the Nano-Satellite Design

    NASA Astrophysics Data System (ADS)

    Mahdi, Mohammed Chessab

    2016-12-01

    The probability of KufaSat collisions with different sizes of orbital debris and with other satellites which operating in the same orbit during orbital lifetime was determined. Apogee/Perigee Altitude History was used to graph apogee and perigee altitudes over KufaSat lifetime. The required change in velocity for maneuvers necessary to reentry atmospheric within 25 years was calculated. The prediction of orbital lifetime of KufaSat using orbital parameters and engineering specifications as inputs to the Debris Assessment Software (DAS) was done, it has been verified that the orbital lifetime will not be more than 25 years after end of mission which is compatible with recommendation of Inter-Agency Space Debris Coordination Committee (IADC).

  2. Quantifying and Improving International Space Station Survivability Following Orbital Debris Penetration

    NASA Technical Reports Server (NTRS)

    Williamsen, Joel; Evans, Hilary; Bohl, Bill; Evans, Steven; Parker, Nelson (Technical Monitor)

    2001-01-01

    The increase of the orbital debris environment in low-earth orbit has prompted NASA to develop analytical tools for quantifying and lowering the likelihood of crew loss following orbital debris penetration of the International Space Station (ISS). NASA uses the Manned Spacecraft and Crew Survivability (MSCSurv) computer program to simulate the events that may cause crew loss following orbital debris penetration of ISS manned modules, including: (1) critical cracking (explosive decompression) of the module; (2) critical external equipment penetration (such as hydrazine and high pressure tanks); (3) critical internal system penetration (guidance, control, and other vital components); (4) hazardous payload penetration (furnaces, pressure bottles, and toxic substances); (5) crew injury (from fragments, overpressure, light flash, and temperature rise); (6) hypoxia from loss of cabin pressure; and (7) thrust from module hole causing high angular velocity (occurring only when key Guidance, Navigation, and Control (GN&C) equipment is damaged) and, thus, preventing safe escape vehicle (EV) departure. MSCSurv is also capable of quantifying the 'end effects' of orbital debris penetration, such as the likelihood of crew escape, the probability of each module depressurizing, and late loss of station control. By quantifying these effects (and their associated uncertainties), NASA is able to improve the likelihood of crew survivability following orbital debris penetration due to improved crew operations and internal designs.

  3. Failure Analysis in Space: International Space Station (ISS) Starboard Solar Alpha Rotary Joint (SARJ) Debris Analysis

    NASA Technical Reports Server (NTRS)

    Long, V. S.; Wright, M. C.; McDanels, S. J.; Lubas, D.; Tucker, B.; Marciniak, P. J.

    2010-01-01

    This slide presentation reviews the debris analysis of the Starboard Solar Alpha Rotary Joint (SARJ), a mechanism that is designed to keep the solar arrays facing the sun. The goal of this was to identify the failure mechanism based on surface morphology and to determine the source of debris through elemental and particle analysis.

  4. Laser ranging with the MéO telescope to improve orbital accuracy of space debris

    NASA Astrophysics Data System (ADS)

    Hennegrave, L.; Pyanet, M.; Haag, H.; Blanchet, G.; Esmiller, B.; Vial, S.; Samain, E.; Paris, J.; Albanese, D.

    2013-05-01

    Improving orbital accuracy of space debris is one of the major prerequisite to performing reliable collision prediction in low earth orbit. The objective is to avoid false alarms and useless maneuvers for operational satellites. This paper shows how laser ranging on debris can improve the accuracy of orbit determination. In March 2012 a joint OCA-Astrium team had the first laser echoes from space debris using the MéO (Métrologie Optique) telescope of the Observatoire de la Côte d'Azur (OCA), upgraded with a nanosecond pulsed laser. The experiment was conducted in full compliance with the procedures dictated by the French Civil Aviation Authorities. To perform laser ranging measurement on space debris, the laser link budget needed to be improved. Related technical developments were supported by implementation of a 2J pulsed laser purchased by ASTRIUM and an adapted photo detection. To achieve acquisition of the target from low accuracy orbital data such as Two Lines Elements, a 2.3-degree field of view telescope was coupled to the original MéO telescope 3-arcmin narrow field of view. The wide field of view telescope aimed at pointing, adjusting and acquiring images of the space debris for astrometry measurement. The achieved set-up allowed performing laser ranging and angular measurements in parallel, on several rocket stages from past launches. After a brief description of the set-up, development issues and campaigns, the paper discusses added-value of laser ranging measurement when combined to angular measurement for accurate orbit determination. Comparison between different sets of experimental results as well as simulation results is given.

  5. MEO and LEO space debris optical observations at Crimean Observatory: first experience and future perspectives.

    NASA Astrophysics Data System (ADS)

    Rumyantsev, Vasilij; Biryukov, Vadim; Agapov, Vladimir; Molotov, Igor

    The near Earth space observation group of Crimean Observatory is performing the regular op-tical monitoring of space debris at GEO region within framework of the International Scientific Optical Network (ISON). During last years we also paid attention to objects on lower orbits due to increasing interest to LEO and MEO regions caused by several catastrophic events happened in the recent past. Optical observations provide high quality information about position and physical properties of space debris at LEO and MEO so they can be considered as another source of data comple-mentary to traditional radar measurements. We will discuss our observations of fragments from Briz-M upper stage (object 28944) and Block-DM ullage motor (25054) explosions. Results of observation of USA-193 debris will be presented. Then we will focus on observations and some photometric properties of FengYun 1C debris as well as Cosmos 2251 and Iridium 33 fragments. Radar cross-section versus optical photometry will be compared. Moreover, estimates of orbital parameters as well as area-to-mass ratio for some observed objects will be given. Most of our observations which we discuss in the paper represent just the first attempt to investigate capabilities of our optical system to observe MEO and LEO objects. But these results are very promising and show good perspectives for the future. We will briefly describe future perspectives of our optical observations of space debris and other objects in MEO and LEO region after the new wide-field telescopes will be put into operation.

  6. Status of CNES optical observations of space debris in geostationary orbit

    NASA Astrophysics Data System (ADS)

    Alby, F.; Deguine, B.; Escane, I.

    Ground observation of space debris in geostationary orbit (GEO) or close to it is not feasible with radar facilities. Optical systems using a telescope and a CCD camera are effective solutions for such a GEO survey because objects remain fixed with report to the Earth. The photons can be cumulated during the exposure time, thus allowing observing faint objects. CNES has been studying and developing such systems for several years with two main objectives: first to develop systems able to detect debris in the vicinity of the geostationary orbit for statistical evaluation of the population, secondly to develop a tool to accurately determine the orbits: these activities are led in the frame of two projects called Tarot and Rosace. On one hand, the capability of detecting small objects in geostationary orbit was demonstrated during previous studies using a large Schmidt telescope. Now, the software has been transferred on a smaller telescope called Tarot. This telescope has the advantage to be automatic with a real time processing capability and can be remotely controlled. Moreover, its large field of view enables a systematic survey of the geostationary region to detect uncatalogued objects. Beside the detection function, a step by step orbit determination function is implemented. This function is necessary to find again the same object a few minutes or a few hours later. On the other hand, Rosace was designed as a low cost accurate orbit determination system for on-station geostationary satellites. The main application is the calibration of the classical tracking systems. The other objectives are to provide redundancy to existing facilities, to track failed satellites or to monitor co-located satellites. The first operational use is now foreseen in the frame of the Stentor project. This paper presents the main characteristics of both systems, the principle of their image processing software, their development status and the main results obtained. Finally, perspectives

  7. On the connection of permafrost and debris flow activity in Austria

    NASA Astrophysics Data System (ADS)

    Huber, Thomas; Kaitna, Roland

    2016-04-01

    Debris flows represent a severe hazard in alpine regions and typically result from a critical combination of relief energy, water, and sediment. Hence, besides water-related trigger conditions, the availability of abundant sediment is a major control on debris flows activity in alpine regions. Increasing temperatures due to global warming are expected to affect periglacial regions and by that the distribution of alpine permafrost and the depth of the active layer, which in turn might lead to increased debris flow activity and increased interference with human interests. In this contribution we assess the importance of permafrost on documented debris flows in the past by connecting the modeled permafrost distribution with a large database of historic debris flows in Austria. The permafrost distribution is estimated based on a published model approach and mainly depends of altitude, relief, and exposition. The database of debris flows includes more than 4000 debris flow events in around 1900 watersheds. We find that 27 % of watersheds experiencing debris flow activity have a modeled permafrost area smaller than 5 % of total area. Around 7 % of the debris flow prone watersheds have an area larger than 5 %. Interestingly, our first results indicate that watersheds without permafrost experience significantly less, but more intense debris flow events than watersheds with modeled permafrost occurrence. Our study aims to contribute to a better understanding of geomorphic activity and the impact of climate change in alpine environments.

  8. Impulse calculation and characteristic analysis of space debris by pulsed laser ablation

    NASA Astrophysics Data System (ADS)

    Wang, Chenglin; Zhang, Yan; Wang, Kunpeng

    2016-11-01

    Ablation by high-energy pulsed laser provides recoil impulse that results in the de-orbiting and atmospheric re-entry of space debris, which may be the best method of clearing space debris in the size range of 1-10 cm. Both the magnitude and direction of the recoil impulse depend on the shape and orientation of the target and serve as the foundation for studying orbital evolution and evaluating removal effects. However, how to calculate the recoil impulse and analyze the features of recoil impulse have not received sufficient attention in the literature. Based on certain assumed conditions, a general numerical method is proposed to calculate the recoil impulse of free motion debris under a set of laser pulses. Selecting cylindrical debris as the research target, we derive an analytical method to calculate the ablation-driven impulse. Moreover, the characteristics of single impulses changing over time and the total impulse are examined using analytical expressions. Finally, simulation experiments are conducted to validate both the numerical and analytical methods.

  9. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray B11

    NASA Technical Reports Server (NTRS)

    1990-01-01

    LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray B11 The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks at the left end of the lower tray flange and at the center of the upper and right tray flanges have changed slightly to an off-white color. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The dark streaks observed on the right debris panel in the flight photograph are no longer visible since the blue sky reflection is not present. However, the light irregular shaped discoloration observed on the left debris panel starting near the center of the left edge is clearly seen. The light band along the sides and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  10. Hypervelocity impact facility for simulating materials exposure to impact by space debris

    NASA Technical Reports Server (NTRS)

    Rose, M. F.; Best, S.; Chaloupka, T.; Stephens, B.; Crawford, G.

    1993-01-01

    As a result of man's venturing into space, the local debris contributed by his presence exceeds, at some orbital altitudes, that of the natural component. Man's contribution ranges from fuel residue to large derelect satellites that weigh many kilograms. Current debris models are able to predict the growth of the problem and suggest that spacecraft must employ armor or bumper shields for some orbital altitudes now, and that, the problem will become worse as a function of time. The practical upper limit to the velocity distribution is on the order of 40 km/s and is associated with the natural environment. The maximum velocity of the man-made component is in the 14-16 km/s range. The Long Duration Exposure Facility (LDEF) has verified that the 'high probability of impact' particles are in the microgram to milligram range. These particles can have significant effects on coatings, insulators, and thin metallic layers. The surface of thick materials becomes pitted and the local debris component is enhanced by ejecta from the debris spectrum in a controlled environment. The facility capability is discussed in terms of drive geometry, energetics, velocity distribution, diagnostics, and projectile/debris loading. The facility is currently being used to study impact phenomena on Space Station Freedom's solar array structure, other solar array materials, potential structural materials for use in the station, electrical breakdown in the space environment, and as a means of clarifying or duplicating the impact phenomena on the LDEF surfaces. The results of these experiments are described in terms of the mass/velocity distribution incident on selected samples, crater dynamics, and sample geometry.

  11. Streak detection and analysis pipeline for space-debris optical images

    NASA Astrophysics Data System (ADS)

    Virtanen, Jenni; Poikonen, Jonne; Säntti, Tero; Komulainen, Tuomo; Torppa, Johanna; Granvik, Mikael; Muinonen, Karri; Pentikäinen, Hanna; Martikainen, Julia; Näränen, Jyri; Lehti, Jussi; Flohrer, Tim

    2016-04-01

    We describe a novel data-processing and analysis pipeline for optical observations of moving objects, either of natural (asteroids, meteors) or artificial origin (satellites, space debris). The monitoring of the space object populations requires reliable acquisition of observational data, to support the development and validation of population models and to build and maintain catalogues of orbital elements. The orbital catalogues are, in turn, needed for the assessment of close approaches (for asteroids, with the Earth; for satellites, with each other) and for the support of contingency situations or launches. For both types of populations, there is also increasing interest to detect fainter objects corresponding to the small end of the size distribution. The ESA-funded StreakDet (streak detection and astrometric reduction) activity has aimed at formulating and discussing suitable approaches for the detection and astrometric reduction of object trails, or streaks, in optical observations. Our two main focuses are objects in lower altitudes and space-based observations (i.e., high angular velocities), resulting in long (potentially curved) and faint streaks in the optical images. In particular, we concentrate on single-image (as compared to consecutive frames of the same field) and low-SNR detection of objects. Particular attention has been paid to the process of extraction of all necessary information from one image (segmentation), and subsequently, to efficient reduction of the extracted data (classification). We have developed an automated streak detection and processing pipeline and demonstrated its performance with an extensive database of semisynthetic images simulating streak observations both from ground-based and space-based observing platforms. The average processing time per image is about 13 s for a typical 2k-by-2k image. For long streaks (length >100 pixels), primary targets of the pipeline, the detection sensitivity (true positives) is about 90% for

  12. Image Restoration Based on Statistic PSF Modeling for Improving the Astrometry of Space Debris

    NASA Astrophysics Data System (ADS)

    Sun, Rongyu; Jia, Peng

    2017-04-01

    Space debris is a special kind of fast-moving, near-Earth objects, and it is also considered to be an interesting topic in time-domain astronomy. Optical survey is the main technique for observing space debris, which contributes much to the studies of space environment. However, due to the motion of registered objects, image degradation is critical in optical space debris observations, as it affects the efficiency of data reduction and lowers the precision of astrometry. Therefore, the image restoration in the form of deconvolution can be applied to improve the data quality and reduction accuracy. To promote the image processing and optimize the reduction, the image degradation across the field of view is modeled statistically with principal component analysis and the efficient mean point-spread function (PSF) is derived from raw images, which is further used in the image restoration. To test the efficiency and reliability, trial observations were made for both low-Earth orbital and high-Earth orbital objects. The positions of all targets were measured using our novel approach and compared with the reference positions. The performance of image restoration employing our estimated PSF was compared with several competitive approaches. The proposed image restoration outperformed the others so that the influence of image degradation was distinctly reduced, which resulted in a higher signal-to-noise ratio and more precise astrometric measurements.

  13. Approximate expressions of mean eddy current torque acted on space debris

    NASA Astrophysics Data System (ADS)

    Lin, Hou-yuan; Zhao, Chang-yin

    2017-02-01

    Rotational state of space debris will be influenced by eddy current torque which is produced by the conducting body rotating within the geomagnetic field. Former expressions of instantaneous torque established in body-fixed coordinate system will change in space during rotation due to the variation of the coordinate system. In order to further investigate the evolution of the rotation of space debris subjected to the eddy current torque, approximate expressions of mean eddy current torque in inertial coordinate system are obtained from the average of the Euler dynamics equations under the assumption that two of the principal moments of inertia of the space debris are similar. Then the expressions are verified through numerical simulation, in which the orientation of the averaged variation of angular momentum is in agreement with the torque from the expressions, which is on an identical plane with magnetic field and the angular momentum. The torque and the averaged variation of the angular momentum have the same evolution trend during rotation in spite of minor deviations of their values.

  14. Development of a New Type Sensor for In-Situ Space Debris Measurement

    NASA Astrophysics Data System (ADS)

    Kitazawa, Y.; Sakurai, A.; Yasaka, T.; Kunihiro, F.; Hanada, T.; Hasegawa, S.; Matsumotom H.

    Space debris environment models are used for debris impact risk assessments for spacecraft. The comparison of representative models revealed that there is large difference in the flux value of the size range from a hundred micrometers to several millimeters. The uncertainty of models is caused by the lack of measurement data. Although the large size objects (larger than several cm) can be detected by grand based observations, and small size debris (smaller than hundred micrometers) is measured by spacecraft surface inspections, the size range of hundred micrometers to several millimeters cannot be detected by ground observations and cannot get enough data from spacecraft surface inspections. On the other hand, importance of measurement of these large particles has been increased especially in the engineering viewpoints (e.g. space system design and operations). The in-situ measurement data are useful for; 1) verifications of space debris environment models, 2) verifications of space debris environment evolution models, 3) real time detection and evaluation of the influences on space environment by unexpected events, such as explosions on an orbit (ex. ASAT ( Anti-Satellite Test) and satellites collisions). Authors have been developing the in-situ measurement sensor to detect dust particles ranging from a hundred micrometers to several millimeters. Since spatial density of this size range of debris is low, the sensor must have a large detection area, while the sensor is required to be low in mass, low in power, robust, and low in telemetry requirements. The sensor consists of multitudes of thin and conductive strips which are formed with fine pitch on a thin film of nonconductive material. A dust particle impact is detected when one or more strips are severed by the impact hole. It is simple to produce and use and requires almost no calibration as it is essentially a digital system. Features of the sensor are; 1) Simple mechanism, 2) High reliability (sensing

  15. Morphology of meteoroid and space debris craters on LDEF metal targets

    NASA Technical Reports Server (NTRS)

    Love, S. G.; Brownlee, D. E.; King, N. L.; Hoerz, F.

    1994-01-01

    We measured the depths, average diameters, and circularity indices of over 600 micrometeoroid and space debris craters on various metal surfaces exposed to space on the Long Duration Exposure Facility (LDEF) satellite, as a test of some of the formalisms used to convert the diameters of craters on space-exposed surfaces into penetration depths for the purpose of calculating impactor sizes or masses. The topics covered include the following: targe materials orientation; crater measurements and sample populations; effects of oblique impacts; effects of projectile velocity; effects of crater size; effects of target hardness; effects of target density; and effects of projectile properties.

  16. Morphology of meteoroid and space debris craters on LDEF metal targets

    NASA Astrophysics Data System (ADS)

    Love, S. G.; Brownlee, D. E.; King, N. L.; Hoerz, F.

    1994-03-01

    We measured the depths, average diameters, and circularity indices of over 600 micrometeoroid and space debris craters on various metal surfaces exposed to space on the Long Duration Exposure Facility (LDEF) satellite, as a test of some of the formalisms used to convert the diameters of craters on space-exposed surfaces into penetration depths for the purpose of calculating impactor sizes or masses. The topics covered include the following: targe materials orientation; crater measurements and sample populations; effects of oblique impacts; effects of projectile velocity; effects of crater size; effects of target hardness; effects of target density; and effects of projectile properties.

  17. Sensitivity analysis of a space-based multi-band infrared imager for GEO belt debris study

    NASA Astrophysics Data System (ADS)

    Murray-Krezan, Jeremy

    2016-05-01

    Thousands of space objects in the Earth orbital-region known as the GEO belt are categorized as debris. Relatively little is known about the thousands of space debris objects. Remote sensing techniques offer the only viable opportunity to learn more about these objects. In this paper an analysis is performed for observations using a hypothetical space-based multi-band infrared instrument to measure characteristics of GEO belt space debris. The purpose of this study is to understand the limitations of such an instrument and sensing modality for studying GEO belt space debris. Although certain aspects of this study are analytical, the results are anchored with results from the NASA-WISE experiments.

  18. MDD3-EMI's Upcoming Meteoroid and Space Debris Detector Experiment Onboard Russian Spektr-R Satellite

    NASA Astrophysics Data System (ADS)

    Schimmerohn, Martin; Schafer, Frank; Lomakin, Ilya; Willemsen, Philip

    2009-03-01

    The Ernst-Mach-Institut (EMI) is currently developing its next meteoroid and space debris detector experiment, referred to as MDD3, which will be integrated onboard the Russian Spektr-R satellite. Taking this flight opportunity supported by the German Aerospace Center, MDD3 will be operated in a highly elliptical orbit, allowing for in-situ measurements of impact events in various Earth orbit particle environments. The detector system is equipped with several sensors, thus contributing to both the on-orbit verification of a robust impact detection system and the enhancement of knowledge about micrometeoroid and space debris populations. This paper addresses scientific and technical aspects of the MDD3 mission in a general overview. The status of MDD3 implementation, as well as facts on the Spektr-R mission and orbit environment are outlined for background information.

  19. Design of a secondary debris containment shield for large space structures

    NASA Technical Reports Server (NTRS)

    Schonberg, William P.; Taylor, Roy A.

    1989-01-01

    All long-duration spacecraft are susceptible to impacts by meteoroids and pieces of orbiting space debris. Such impacts are expected to occur at extremely high speeds and can damage internal and external flight-critical systems of spacecraft. An effective mechanism is developed to protect external spacecraft subsystems against damage by ricochet particles formed during such impacts. Equations and design procedures for protective shield panels are developed based on observed ricochet phenomena and calculated ricochet particle sizes and speeds. Panel dimensions are shown to be strongly dependent on their inclination and on their distribution around a spacecraft module. It is concluded that obliquity effects of high-speed impacts must be considered in the design of any structure exposed to the meteoroid and space debris environment.

  20. US Space Situational Awareness activities

    NASA Astrophysics Data System (ADS)

    Butler, Stephen, , Col; Hand, Kelly; Smith, Bradley, , Col

    A new ESA Programme on Space Situational Awareness (SSA) has been approved during the ESA Council at Ministerial level in November 2008. A preparatory phase is in progress, covering the timeframe 2009 -2012. It concentrates on the architectural design of the SSA System, its governance and data policy, as well as on the provision of precursor services based on the federation of existing National and European assets. A continuation of the SSA programme will be proposed at the next Ministerial Council for the years 2012 and onwards. The SSA Preparatory Programme covers three distinct segments, namely: -Space Surveillance and Tracking of artificial objects orbiting the Earth -Space Weather -Near Earth Objects Each of the above segments has a strong relation with Science and is supported by specific RD Programmes at National, EC and ESA levels. In this paper, the scientific aspects of the three SSA Segments are outlined and the following main topics developed: • Space Surveillance: statistical models of the evolution of the space debris population in Earth-bound orbits, study of active mitigation measures, impact analysis, tracking and char-acterisation principles based on radar and optical techniques. • Space Weather: awareness of the natural space environment, detection and forecasting of space weather effects and interferences, analysis of appropriate ground and space-based sensors for the monitoring of the Sun, the solar wind, the radiation belts, the magnetosphere and the ionosphere. • Near Earth Objects (NEOs): methods for determination of physical characteristics of newly discovered objects, study of appropriate sensors based on radar and optical techniques, iden-tification and ranking of collision risks of NEOs with the Earth, study of possible mitigation measures (e.g. Don Quichotes project). The research topics undertaken during the preparatory programme, as well as those foreseen during the next phase, possibly with a strong international cooperation

  1. Observations of the orbital debris complex by the Midcourse Space Experiment (MSX) satellite

    NASA Technical Reports Server (NTRS)

    Vilas, Faith; Anz-Meador, Phillip; Talent, Dave

    1997-01-01

    The midcourse space experiment (MSX) provides the opportunity to observe debris at multiple, simultaneous wavelengths, or in conjunction with other sensors and prior data sets. The instruments onboard MSX include an infrared telescope, an infrared interferometer, a visible telescope, an ultraviolet telescope and a spectroscopic imager. The spacecraft carries calibration spheres for instrument calibration and atmospheric drag studies. The experimental program, the implementation aspects, the data reduction techniques and the preliminary results are described.

  2. Modeling the space debris environment with MASTER-2009 and ORDEM2010

    NASA Astrophysics Data System (ADS)

    Flegel, Sven Kevin; Krisko, Paula; Gelhaus, Johannes; Wiedemann, Carsten; Moeckel, Marek; Krag, Holger; Klinkrad, Heiner; Xu, Yu-Lin; Horstman, Matthew; Matney, Mark; Vörsmann, Peter

    The two software tools MASTER-2009 and ORDEM2010 are the ESA and NASA reference software tools respectively which describe the earth's debris environment. The primary goal of both programs is to allow users to estimate the object flux onto a target object for mission planning. The current paper describes the basic distinctions in the model philosophies. At the core of each model lies the method by which the object environment is established. Cen-tral to this process is the role played by the results from radar/telescope observations or impact fluxes on surfaces returned from earth orbit. The ESA Meteoroid and Space Debris Terrestrial Environment Reference Model (MASTER) is engineered to give a realistic description of the natural and the man-made particulate environment of the earth. Debris sources are simulated based on detailed lists of known historical events such as fragmentations or solid rocket motor firings or through simulation of secondary debris such as impact ejecta or the release of paint flakes from degrading spacecraft surfaces. The resulting population is then validated against historical telescope/radar campaigns using the ESA Program for Radar and Optical Observa-tion Forecasting (PROOF) and against object impact fluxes on surfaces returned from space. The NASA Orbital Debris Engineering Model (ORDEM) series is designed to provide reliable estimates of orbital debris flux on spacecraft and through telescope or radar fields-of-view. Central to the model series is the empirical nature of the input populations. These are derived from NASA orbital debris modeling but verified, where possible, with measurement data from various sources. The latest version of the series, ORDEM2010, compiles over two decades of data from NASA radar systems, telescopes, in-situ sources, and ground tests that are analyzed by statistical methods. For increased understanding of the application ranges of the two programs, the current paper provides an overview of the two

  3. Mantle Debris in Giant Impacts: Parameter-Space Study and Scaling Laws

    NASA Astrophysics Data System (ADS)

    Gabriel, Travis; Reufer, Andreas; Jackson, Alan P.; Asphaug, Erik

    2016-10-01

    Collisions between similar-sized planetesimals are prevalent throughout the early stages of the formation of the Solar System. N-body dynamics simulations commonly employed to understand planetary evolution depend on parameterized disruption/accretion criteria in order to consider the diversity of outcomes of these collisions. Additionally, understanding the debris from collisions is essential in tracing the source regions of volatiles, placing constraints on collisional grinding, and explaining the formation of small solar system bodies. We describe the transport of mantle material through debris production in giant impacts using a large database of SPH hydrocode simulations. We then develop new scaling laws that accurately capture the production of diverse debris products found in giant impacts with a range of relative velocities up to a few times the mutual escape velocity and a complete range of impact geometries. At typical impact angles it is found that giant impacts are significantly less erosive than suggested by existing scaling laws. This discrepancy grows with impact velocity and the impactor-to-target mass ratio, and thus it grows with the kinetic energy of the system. Our database spans a wide parameter space of pre-impact initial conditions, and includes chondritic and icy, chondritic material representative of the bulk abundances in the inner and outer solar system respectively. Implications for this new understanding in debris production through giant impacts are discussed.

  4. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray G04

    NASA Technical Reports Server (NTRS)

    1990-01-01

    LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray G04 The Space Debris Impact Experiment con sist of a three sixteenth (3/16) of an inch thick chromic anodized aluminum panel mounted in a three (3) inch deep LDEF experiment tray. The side of the plate exposed to the LDEF interior is painted with Chemglaze Z-306 flat black paint over a Chemglaze #9924 wash primer. The panels are attached to the aluminum tray structure with non-magnetic stainless steel fasteners. The panel coatings, a thin layer of chromic anodize facing out and the Chemglaze Z-306 black paint facing the LDEF interior, contribute significantly to thermal control of the LDEF spacecraft. The photograph was taken in SAEF II at the KSC after the experiment was removed from the LDEF. The light pink tint of the debris panel is a by-product of the chromic anodize coating pro cess and not attributed to contamination and/or exposure to the space environment. A brown stain is located in the lower right corner of the tray.

  5. Simulation of the space debris environment in LEO using a simplified approach

    NASA Astrophysics Data System (ADS)

    Kebschull, Christopher; Scheidemann, Philipp; Hesselbach, Sebastian; Radtke, Jonas; Braun, Vitali; Krag, H.; Stoll, Enrico

    2017-01-01

    Several numerical approaches exist to simulate the evolution of the space debris environment. These simulations usually rely on the propagation of a large population of objects in order to determine the collision probability for each object. Explosion and collision events are triggered randomly using a Monte-Carlo (MC) approach. So in many different scenarios different objects are fragmented and contribute to a different version of the space debris environment. The results of the single Monte-Carlo runs therefore represent the whole spectrum of possible evolutions of the space debris environment. For the comparison of different scenarios, in general the average of all MC runs together with its standard deviation is used. This method is computationally very expensive due to the propagation of thousands of objects over long timeframes and the application of the MC method. At the Institute of Space Systems (IRAS) a model capable of describing the evolution of the space debris environment has been developed and implemented. The model is based on source and sink mechanisms, where yearly launches as well as collisions and explosions are considered as sources. The natural decay and post mission disposal measures are the only sink mechanisms. This method reduces the computational costs tremendously. In order to achieve this benefit a few simplifications have been applied. The approach of the model partitions the Low Earth Orbit (LEO) region into altitude shells. Only two kinds of objects are considered, intact bodies and fragments, which are also divided into diameter bins. As an extension to a previously presented model the eccentricity has additionally been taken into account with 67 eccentricity bins. While a set of differential equations has been implemented in a generic manner, the Euler method was chosen to integrate the equations for a given time span. For this paper parameters have been derived so that the model is able to reflect the results of the numerical MC

  6. Physical simulation of the long-term dynamic action of a plasma beam on a space debris object

    NASA Astrophysics Data System (ADS)

    Shuvalov, Valentin A.; Gorev, Nikolai. B.; Tokmak, Nikolai A.; Kochubei, Galina S.

    2017-03-01

    A methodology is developed for physical (laboratory) simulation of the long-term dynamic action of plasma beam high-energy ions on a space debris object with the aim of removing it to a lower orbit followed by its burning in the Earth's atmosphere. The methodology is based on the use of a criterion for the equivalence of two plasma beam exposure regimes (in the Earth' ionosphere and in laboratory conditions) and an accelerated test procedure in what concerns space debris object material sputtering and space debris object erosion by a plasma beam in the Earth's ionosphere. The space debris coating material (blanket thermal insulation) sputtering yield and normal and tangential momentum transfer coefficients are determined experimentally as a function of the ion energy and the ion beam incidence angle.

  7. The Challenge of Orbital Debris

    NASA Technical Reports Server (NTRS)

    Matney, Mark

    2012-01-01

    Since the dawn of the Space Age more than 50 years ago, humans have been launching objects into the space environment faster than they have been removed by active means or natural decay. This has led to a proliferation of debris -- derelict satellites, discarded rocket upper stages, and pieces from satellite breakups -- in Earth orbit, especially in well-used orbital regimes. This talk will summarize the current knowledge of the debris environment and describe plans to address the challenges orbital debris raises for the future usability of near-Earth space. The talk will be structured around 4 categories: Measurements, Modeling, Shielding, and Mitigation. This will include discussions of the long-term prognosis of debris growth (i.e., the "Kessler Syndrome") as well as plans for active debris removal.

  8. French space activities

    NASA Technical Reports Server (NTRS)

    Blanc, R.

    1982-01-01

    The four main points of research and development of space programs by France are explained. The National Center of Space Studies is discussed, listing the missions of the Center and describing the activities of the staff.

  9. An optical survey for space debris on highly eccentric and inclined MEO orbits

    NASA Astrophysics Data System (ADS)

    Silha, J.; Schildknecht, T.; Hinze, A.; Flohrer, T.; Vananti, A.

    2017-01-01

    Optical surveys for space debris in high-altitude orbits have been conducted since more than ten years. Originally these efforts concentrated mainly on the geostationary region (GEO). Corresponding observation strategies, processing techniques and cataloguing approaches have been developed and successfully applied. The ESA GEO surveys, e.g., resulted in the detection of a significant population of small-size debris and later in the discovery of high area-to-mass ratio objects in GEO-like orbits. Comparably less experience (both, in terms of practical observation and strategy definition) is available for eccentric orbits that (at least partly) are in the MEO region, in particular for the Molniya-type orbits. Different survey and follow-up strategies for searching space debris objects in highly-eccentric MEO orbits, and to acquire orbits which are sufficiently accurate to catalog such objects and to maintain their orbits over longer time spans were developed. Simulations were performed to compare the performance of different survey and cataloguing strategies. Eventually, optical observations were conducted in the framework of an ESA study using ESA's Space Debris Telescope (ESASDT) the 1-m Zeiss telescope located at the Optical Ground Station (OGS) at the Teide Observatory at Tenerife, Spain. Thirteen nights of surveys of Molniya-type orbits were performed between January and August 2013. Eventually 255 surveys were performed during these thirteen nights corresponding to about 47 h of observations. In total 30 uncorrelated faint objects were discovered. On average one uncorrelated object was found every 100 min of observations. Some of these objects show a considerable brightness variation and have a high area-to-mass ratio as determined in the orbit estimation process.

  10. Comparing long-term projections of the space debris environment to real world data - Looking back to 1990

    NASA Astrophysics Data System (ADS)

    Radtke, Jonas; Stoll, Enrico

    2016-10-01

    Long-term projections of the space debris environment are commonly used to assess the trends within different scenarios for the assumed future development of spacefaring. General scenarios investigated include business-as-usual cases in which spaceflight is performed as today and mitigation scenarios, assuming the implementation of Space Debris Mitigation Guidelines at different advances or the effectiveness of more drastic measures, such as active debris removal. One problem that always goes along with the projection of a system's behaviour in the future is that affecting parameters, such as the launch rate, are unpredictable. It is common to look backwards and re-model the past in other fields of research. This is a rather difficult task for spaceflight as it is still quite young, and furthermore mostly influenced by drastic politic changes, as the break-down of the Soviet Union in the end of the 1980s. Furthermore, one major driver of the evolution of the number of on-orbit objects turn out to be collisions between objects. As of today, these collisions are, fortunately, very rare and therefore, a real-world-data modelling approach is difficult. Nevertheless, since the end of the cold war more than 20 years of a comparably stable evolution of spaceflight activities have passed. For this study, this period is used in a comparison between the real evolution of the space debris environment and that one projected using the Institute of Space System's in-house tool for long-term assessment LUCA (Long-Term Utility for Collision Analysis). Four different scenarios are investigated in this comparison; all of them have the common starting point of using an initial population for 1st May 1989. The first scenario, which serves as reference, is simply taken from MASTER-2009. All launch and mission related objects from the Two Line Elements (TLE) catalogue and other available sources are included. All events such as explosion and collision events have been re-modelled as

  11. An International Environmental Agreement for space debris mitigation among asymmetric nations

    NASA Astrophysics Data System (ADS)

    Singer, Michael J.; Musacchio, John T.

    2011-01-01

    We investigate how ideas from the International Environmental Agreement (IEA) literature can be applied to the problem of space debris mitigation. Space debris pollution is similar to other international environmental problems in that there is a potential for a "tragedy of the commons" effect: individual nations bear all the cost of their mitigation measures but share only a fraction of the benefit. As a consequence, nations have a tendency to underinvest in mitigation. Coalitions of nations, brought together by IEAs, have the potential to lessen the tragedy of the commons effect by pooling the costs and benefits of mitigation. This work brings together two recent modeling advances: (i) a game theoretic model for studying the potential gains from IEA cooperation between nations with asymmetric costs and benefits, (ii) an orbital debris model that gives the societal cost that specific actions, such as failing to deorbit an inactive spacecraft, have on the environment. We combine these two models with empirical launch-share data for a "proof of concept" of an IEA for a single mitigation measure—deorbiting spacecraft at the end of operational lifetime. Simulations of empirically derived and theoretical launch distributions among nations suggest the possibility that voluntary coalitions can provide significant deorbiting gains relative to nations acting in the absence of an IEA agreement.

  12. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray E07

    NASA Technical Reports Server (NTRS)

    1990-01-01

    LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray E07 The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks at the center of the upper tray flange and at each end of the bottom tray flange are an off-white or light tan color. Paint on the clamp block located at the center of the lower tray flange has been exposed to a greater atomic oxygen flux than paint on the clamp block located at the center of the left flange and appears to be less contaminated and therefore brighter. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The streaks on the debris panels in the flight photographs are almost invisible since the blue sky reflection is not present. The light band along the sides and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  13. Research and Development on In-Situ Measurement Sensors for Micro-Meteoroid and Small Space Debris at JAXA

    NASA Astrophysics Data System (ADS)

    Kitazawa, Yukihito; Matsumoto, Haruhisa; Okudaira, Osamu; Kimoto, Yugo; Hanada, Toshiya; Akahoshi, Yasuhiro; Pauline, Faure; Sakurai, Akira; Funakoshi, Kunihiro; Yasaka, Testuo

    2015-04-01

    The history of Japanese R&D into in-situ sensors for micro-meteoroid and orbital debris (MMOD) measurements is neither particularly long nor short. Research into active sensors started for the meteoroid observation experiment on the HITEN (MUSES-A) satellite of ISAS/JAXA launched in 1990, which had MDC (Munich Dust Counter) on-board sensors for micro meteoroid measurement. This was a collaboration between Technische Universität München and ISAS/JAXA. The main purpose behind the start of passive sensor research was SOCCOR, a late 80's Japan-US mission that planned to capture cometary dust and return to the Earth. Although this mission was canceled, the research outcomes were employed in a JAXA micro debris sample return mission using calibrated aerogel involving the Space Shuttle and the International Space Station. There have been many other important activities apart from the above, and the knowledge generated from them has contributed to JAXA's development of a new type of active dust sensor. JAXA and its partners have been developing a simple in-situ active dust sensor of a new type to detect dust particles ranging from a hundred micrometers to several millimeters. The distribution and flux of the debris in the size range are not well understood and is difficult to measure using ground observations. However, it is important that the risk caused by such debris is assessed. In-situ measurement of debris in this size range is useful for 1) verifying meteoroid and debris environment models, 2) verifying meteoroid and debris environment evolution models, and 3) the real time detection of explosions, collisions and other unexpected orbital events. Multitudes of thin, conductive copper strips are formed at a fine pitch of 100 um on a film 12.5 um thick of nonconductive polyimide. An MMOD particle impact is detected when one or more strips are severed by being perforated by such an impact. This sensor is simple to produce and use and requires almost no calibration as

  14. The New Space Debris Mitigation (SDM 4.0) Long Term Evolution Code

    NASA Astrophysics Data System (ADS)

    Rossi, A.; Anselmo, L.; Pardini, C.; Jehn, R.; Valsecchi, G. B.

    2009-03-01

    The main new features in the Space Debris Mitigation long-term analysis program (SDM) recently upgraded to Version 4.0 are described. They include new or upgraded orbital propagators, two new collision probability algorithms, upgraded mitigation scenarios and new post-processing routines. The results of a set of simulations of the long term evolution of the Low Earth Orbit (LEO) environment are decribed. A No Future Launches, a Business as Usual and a Mitigated scenario are simulated, showing the need to adopt all the feasible proposed mitigation measures, in order to reduce the proliferation of orbiting debris. In particular, the mitigation measures proposed in this study appear capable of strongly reducing the growth of the 10 cm and larger population, but not enough to fully stabilize critical regions, such as the shell in the 800-1000 km altitude range.

  15. Meteoroid/orbital debris impact damage predictions for the Russian space station MIR

    NASA Technical Reports Server (NTRS)

    Christiansen, E. L.; Hyde, J. L.; Lear, D.

    1997-01-01

    Components of the Mir space station have been exposed to the meteoroid/orbital debris (M/OD) environment for up to 11 years. During this period, no M/OD impact perforation of the pressure shell of the manned modules were reported. The NASA standard M/OD analysis code BUMPER was used to predict the probability of M/OD impact damage to various components of Mir. The analysis indicates a 1 in 2.2 chance that a M/OD impact would have caused a penetration resulting in a pressure leak of the Mir modules since its launch up to the February 1997. For the next five years, the estimated odds become 1 in 3. On an annual basis, penetration risks are 60 percent higher, on the average, in the next five years due to the larger size of Mir and the growth in the orbital debris population.

  16. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray A06

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dots on clamp blocks at the centers of the experiment tray top and right flanges are now a light tan while the dot on the clamp block at the left end of the lower flange appears to have changed little in color. The experiment tray flanges and lower sidewall appear discolored with a light tan stain. The Space Debris Impact Experiment consists of two (2) three sixteenth (3/16th) inch thick chromic anodized aluminum panels mounted in a three (3) inch deep peripheral LDEF experiment tray. The side of the panels exposed to the LDEF interior are painted black with Chemglaze Z-306 flat black paint over a Chemglaze 9924 wash primer. The panels are attached to the aluminum tray structure with non-magnetic stainless steel fasteners. The panel coatings, a thin layer of chromic anodize facing out and the Chemglaze Z-306 black paint facing the LDEF interior, contribute significantly to thermal control of the LDEF spacecraft. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The finger prints along the center edges of the debris panels that were observed in the flight photograph are still visible. The vertical streaks seen on the debris panels appear the same as on the prelaunch photograph. The black unit located on the right panel is a keel camera target used during berthing of the LDEF. The color of the stripes and the tip of the vertical rod appear darker than in the prelaunch photograph. The light band along the right side and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  17. Implementation of an open-scenario, long-term space debris simulation approach

    NASA Astrophysics Data System (ADS)

    Stupl, J.; Nelson, B.; Faber, N.; Perez, A.; Carlino, R.; Yang, F.; Henze, C.; Karacalioglu, A.; O'Toole, C.; Swenson, J.

    This paper provides a status update on the implementation of a flexible, long-term space debris simulation approach. The motivation is to build a tool that can assess the long-term impact of various options for debris-remediation, including the LightForce space debris collision avoidance scheme. State-of-the-art simulation approaches that assess the long-term development of the debris environment use either completely statistical approaches, or they rely on large time steps in the order of several (5-15) days if they simulate the positions of single objects over time. They cannot be easily adapted to investigate the impact of specific collision avoidance schemes or de-orbit schemes, because the efficiency of a collision avoidance maneuver can depend on various input parameters, including ground station positions, space object parameters and orbital parameters of the conjunctions and take place in much smaller timeframes than 5-15 days. For example, LightForce only changes the orbit of a certain object (aiming to reduce the probability of collision), but it does not remove entire objects or groups of objects. In the same sense, it is also not straightforward to compare specific de-orbit methods in regard to potential collision risks during a de-orbit maneuver. To gain flexibility in assessing interactions with objects, we implement a simulation that includes every tracked space object in LEO, propagates all objects with high precision, and advances with variable-sized time-steps as small as one second. It allows the assessment of the (potential) impact of changes to any object. The final goal is to employ a Monte Carlo approach to assess the debris evolution during the simulation time-frame of 100 years and to compare a baseline scenario to debris remediation scenarios or other scenarios of interest. To populate the initial simulation, we use the entire space-track object catalog in LEO. We then use a high precision propagator to propagate all objects over the

  18. An optical survey for space debris on highly eccentric and inclined MEO orbits

    NASA Astrophysics Data System (ADS)

    Schildknecht, Thomas; Flohrer, Tim; Hinze, Andreas; Vananti, Alessandro; Silha, Jiri

    Optical surveys for space debris in high-altitude orbits have been conducted since more than fifteen years. Originally these efforts concentrated mainly on the geostationary ring (GEO) and its close region. Corresponding observation strategies, processing techniques and cataloguing approaches have been developed and successfully applied. The ESA GEO surveys, e.g., resulted in the detection of a significant population of small-size debris and later in the discovery of high area-to-mass ratio objects in GEO-like orbits. The observation scenarios were successively adapted to survey the geostationary transfer orbit (GTO) region; and surveys to search for debris in the medium Earth orbit (MEO) region of the global navigation satellite constellations were successfully conducted. Comparably less experience (both, in terms of practical observation and strategy definition) is available for eccentric orbits that (at least partly) are in the MEO region, in particular for the Molniya-type orbits. Several breakup events and deliberate fragmentations are known to have taken place in such orbits. Survey and follow-up strategies for searching space debris objects in highly-eccentric MEO orbits, and to acquire orbits which are sufficiently accurate to catalogue such objects and to maintain their orbits over longer time spans were developed and, eventually, optical observations were conducted in the framework of an ESA study using ESA' Space Debris Telescope (ESASDT) the 1-m Zeiss telescope located at the Optical Ground Station (OGS) at the Teide Observatory at Tenerife, Spain. Thirteen nights of surveys of Molniya-type orbits was performed between January and August 2013. A basic survey consisted of observing a single geocentric field for 10 minutes. If a faint object was found, follow-up observations were performed during the same night to ensure a save rediscovery of the object during the next nights. Additional follow-up observations to maintain the orbits of these newly

  19. Space-based application of the CAN laser to LIDAR and orbital debris remediation

    NASA Astrophysics Data System (ADS)

    Quinn, M. N.; Jukna, V.; Ebisuzaki, T.; Dicaire, I.; Soulard, R.; Summerer, L.; Couairon, A.; Mourou, G.

    2015-10-01

    Development of pulsed lasers for space-based science missions entail many additional challenges compared to terrestrial experiments. For systems requiring short pulses ≪1 ns with energies >100 mJ and fast repetition rates >10 kHz there are currently few if no laser architectures capable of operating with high electrical efficiency >20% and have good system stability. The emergence of a mulit-channel fiber-based Coherent-Amplifying-Network or CAN laser potentially enables such capability for space based missions. Here in this article we present an analysis of two such missions scaling up in pulse energy from ≈100 mJ for a supercontinuum LIDAR application utilising atmospheric filamentation to the higher energy demands needed for space debris remediation requiring ≈10 J pulses. This scalability of the CAN laser provides pathways for development of the core science and technology where many new novel space applications can be made possible.

  20. Implementation of an Open-Scenario, Long-Term Space Debris Simulation Approach

    NASA Technical Reports Server (NTRS)

    Nelson, Bron; Yang Yang, Fan; Carlino, Roberto; Dono Perez, Andres; Faber, Nicolas; Henze, Chris; Karacalioglu, Arif Goktug; O'Toole, Conor; Swenson, Jason; Stupl, Jan

    2015-01-01

    This paper provides a status update on the implementation of a flexible, long-term space debris simulation approach. The motivation is to build a tool that can assess the long-term impact of various options for debris-remediation, including the LightForce space debris collision avoidance concept that diverts objects using photon pressure [9]. State-of-the-art simulation approaches that assess the long-term development of the debris environment use either completely statistical approaches, or they rely on large time steps on the order of several days if they simulate the positions of single objects over time. They cannot be easily adapted to investigate the impact of specific collision avoidance schemes or de-orbit schemes, because the efficiency of a collision avoidance maneuver can depend on various input parameters, including ground station positions and orbital and physical parameters of the objects involved in close encounters (conjunctions). Furthermore, maneuvers take place on timescales much smaller than days. For example, LightForce only changes the orbit of a certain object (aiming to reduce the probability of collision), but it does not remove entire objects or groups of objects. In the same sense, it is also not straightforward to compare specific de-orbit methods in regard to potential collision risks during a de-orbit maneuver. To gain flexibility in assessing interactions with objects, we implement a simulation that includes every tracked space object in Low Earth Orbit (LEO) and propagates all objects with high precision and variable time-steps as small as one second. It allows the assessment of the (potential) impact of physical or orbital changes to any object. The final goal is to employ a Monte Carlo approach to assess the debris evolution during the simulation time-frame of 100 years and to compare a baseline scenario to debris remediation scenarios or other scenarios of interest. To populate the initial simulation, we use the entire space

  1. Active Removal of Large Debris: System Approach of Desorbiting Concepts and Technological Issues

    NASA Astrophysics Data System (ADS)

    Couzin, Patrice; Rembala, Richard; Teti, Frank; Bakouche, Charles; Billot, Carole

    2013-08-01

    The threat induced by large space debris, dead satellites or rocket bodies, in Low Earth Orbit has been identified years ago. A first part of the Orbital Transfer Vehicle (OTV) study was dedicated to identify mission architectures that can fulfil the objective to eliminate the necessary number of critical debris. Those potential solutions and architectures have been compared taking into account cost considerations. The present paper reports the first results of the OTV step2 study funded by CNES that addresses different solutions for large debris removal. It compares different desorbiting concepts from selected single to multiple debris complying with the Space Law, i.e. able to ensure controlled re entries. Different capture options are presented, including sensors needs and an analysis of the problems posed by different solutions. The overall performances of the concepts are compared, showing the adequacy, the limits of each solutions and application domains.

  2. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray C07

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks at the center of the upper tray flange and at each end of the bottom tray flange are an off-white or light tan color. Paint on the clamp blocks located at each end of the lower tray flange has been exposed to a greater atomic oxygen flux than paint on the upper flange clamp block and appears to be less contaminated and therefore brighter. The pink and the greenish-gray tints on the two (2) debris panels are a by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The two (2) white spots in the lower left quadrant of the left debris panel appear to be debris impact craters. The light band along the right side and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  3. A new stochastic impressionistic low Earth model of the space debris scenario

    NASA Astrophysics Data System (ADS)

    Ananthasayanam, M. R.; Anilkumar, A. K.; Subba Rao, P. V.

    2006-10-01

    A new Stochastic IMPressionistic Low Earth (SIMPLE) model of the space debris environment using a stochastic approach is presented in this paper. The present approach and philosophy are similar to that utilized for evolving the international standard or other reference atmospheres. Presently, this model describes the debris scenario up to an altitude of 2000 km and with eccentricity less than 0.2 thus covering about 75% of the large space debris objects catalogued in USSPACECOM two line element (TLE) sets. Two types of models one called 'gross' provides insight into the physical process by characterizing the distribution of the number density ' n', eccentricity ' e', and the ballistic coefficient ' B' of objects over the whole of the LEO region for all inclinations put together as also separately. The other called 'local' model characterizes the distribution of ' e' and ' B' of the debris across suitable local altitude and perigee bins useful for mission analysis and risk assessment for spacecraft designers interested in specific altitude or perigee height bins and inclination bands. The number density ' n' in all the gross models can be represented in terms of a mixture of Laplace distributions. The SIMPLE model with much less parameters than in ORDEM96 captures closely all the peak fragment densities without loss of accuracy at other altitudes. The distribution of ' e' and the ' B' in each and every gross and local model can be represented by suitable lognormal distributions. Qualitatively the parameters of the ' n' and ' e' distributions in the gross and the local models exhibit statistically quasi-equilibrium state (though quantitatively the fragment density is varying all over) across the time period from 1999 to 2002 and hence an average is recommended as the model value. Since, the parameters of ' B' show large variations or trend in their values derived from the TLE data sets, the latest year 2002 value is suggested as a reference in the model. Lastly some

  4. Progress in development of the Russian scientific optical network for space debris research

    NASA Astrophysics Data System (ADS)

    Molotov, I.; Agapov, V.; Guseva, I.; Kornienko, G.; Volvach, A.; Ibragimov, M.; Vlasjuk, V.; Kiladze, R.; Zalles, O.; Sukhov, P.

    The Pulkovo cooperation of optical observers PULCOO collaborates with the 8 FSU observatories along 110 degree of longitude to conduct out the observations of space debris and asteroids The 10 telescopes were equipped with CCD cameras and GPS-receivers provided with software for CCD frame processing and ephemeris support 2 6-m ZTSh in Nauchny 32-cm ZA-320 and 22-cm SR-220 in Pulkovo 60-cm Zeiss-600 in Maidanak 1-m Zeiss-1000 in Zelenchuk 40-cm double Zeiss astrograph in Ussuriysk 40-cm double Zeiss astrograph in Abastumani 60-cm RK-600 in Mayaki 70-cm AZT-8 in Chuguev 1-m Zeiss-1000 in Simeiz Few observing campaigns of GEO region were carried out in collaboration with ESOC for searching and tracking of the unknown objects More than 60 000 measurements of PULCOO and European telescopes were collected and processed at Space Debris Data Base in KIAM Ballistic Center of Russian Academy of Science that allowed to find about 170 GEO objects that are absent in public distributed orbital data and to fix their orbital elements Including the 50 small-sized fragments of space debris that were discovered in areas predicted using Pulkovo Laplace motion theory 1 Some of these faint GEO fragments are tracked during few hundred day period The trial observations were arranged in Tarija Bolivia The test GEO survey demonstrated the high performances of new SR-220 in Nauchny 300 square degrees hour 100 detection of catalogued objects up to 15 star magnitude Two more such telescopes were ordered for future usage in Far East and Moldova The research was supported

  5. Considering the collision probability of Active Debris Removal missions

    NASA Astrophysics Data System (ADS)

    Lidtke, Aleksander A.; Lewis, Hugh G.; Armellin, Roberto; Urrutxua, Hodei

    2017-02-01

    Active Debris Removal (ADR) methods are being developed due to a growing concern about the congestion on-orbit and sustainability of spaceflight. This study examined the probability of an on-orbit collision between an ADR target, whilst being de-orbited, and all the objects in the public catalogue published by the US Strategic Command. Such a collision could have significant effects because the target is likely to be located in a densely populated orbital regime and thus follow-on collisions could take place. Six impulsive and three low-thrust example ADR mission trajectories were screened for conjunctions. Extremely close conjunctions were found to result in as much as 99% of the total accumulated collision probability. The need to avoid those conjunctions is highlighted, which raises concerns about ADR methods that do not support collision avoidance. Shortening the removal missions, at an expense of more ΔV and so cost, will also lower their collision probability by reducing the number of conjunctions that they will experience.

  6. Space construction activities

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The Center for Space Construction at the University of Colorado at Boulder was established in 1988 as a University Space Engineering Research Center. The mission of the Center is to conduct interdisciplinary engineering research which is critical to the construction of future space structures and systems and to educate students who will have the vision and technical skills to successfully lead future space construction activities. The research activities are currently organized around two central projects: Orbital Construction and Lunar Construction. Summaries of the research projects are included.

  7. LISK-BROOM: Clearing near-Earth space debris in 4 years using a 20-kW, 530-nm repetitively pulsed laser

    SciTech Connect

    Phipps, C.R.; Michaelis, M.M.

    1994-10-01

    When space debris forced a change of plan for a recent US Space Shuttle mission, it finally reached the point of broad awareness. Almost a million pieces of debris have been generated by 35 years of spaceflight, and now threaten some long-term space missions. This problem can best a be solved by causing space debris items to re-enter and burn up in the atmosphere on a computed trajectory. Illumination of the objects by a repetitively-pulsed laser will easily produce a laser-ablation jet providing the impulse to de-orbit the object. For reasons we will discuss, we propose the use of a ground-based laser system, atmospheric-turbulence compensating beam director, computer and high resolution detection system to solve this problem. A laser of just 2OkW average power and state-of-the-art detection capabilities could clear near-Earth space below 1100km altitude of all space debris larger than 1 cm but less massive than 100kg in about 4 years. The LISK-BROOM laser would be located near the Equator above 5km elevation [e.g., the Uhuru site on Kilimanjarol, minimizing turbulence correction and absorption of the 530-nm wavelength laser beam. LISK-BROOM is a special case of Laser Impulse Space Propulsion (LISP), by which objects are propelled in space by the ablation jet due to a distant laser. We will also discuss active beam phase error correction during passage through the atmosphere and the object detection system which are necessary.

  8. Quantifying Space Environment Interactions with Debris Objects using Observation Data Fusion Techniques

    DTIC Science & Technology

    2014-09-22

    lightcurves , it is also used for follow-up observations of space debris objects and for satellite laser ranging. This restricted the observation time available...the last column of Table 2.1. 4.2 Detailed Analysis of Sample Lightcurves Lightcurves of Meteosat 9 (05049B) The Meteosat 9 satellite with Cospar number...Astra 1D satellite (94070A) is operational and 3-axis stabilized. It is of box-wing shape. Three lightcurves of the object are displayed in Figure

  9. Autonomous space processor for orbital debris advanced design project in support of solar system exploration

    NASA Astrophysics Data System (ADS)

    Ramohalli, Kumar; Mitchell, Dominique; Taft, Brett; Chinnock, Paul; Kutz, Bjoern

    This paper is regarding a project in the Advanced Design Program at the University of Arizona. The project is named the Autonomous Space Processor for Orbital Debris (ASPOD) and is a NASA/Universities Space Research Association (USRA) sponsored design project. The development of ASPOD and the students' abilities in designing and building a prototype spacecraft are the ultimate goals of this project. This year's focus entailed the development of a secondary robotic arm and end-effector to work in tandem with an existent arm in the removal of orbital debris. The new arm features the introduction of composite materials and a linear drive system, thus producing a light-weight and more accurate prototype. The main characteristic of the end-effector design is that it incorporates all of the motors and gearing internally, thus not subjecting them to the harsh space environment. Furthermore, the arm and the end-effector are automated by a control system with positional feedback. This system is composed of magnetic and optical encoders connected to a 486 PC via two servo-motor controller cards. Programming a series of basic routines and sub-routines has allowed the ASPOD prototype to become more autonomous. The new system is expected to perform specified tasks with a positional accuracy of 0.5 cm.

  10. Autonomous space processor for orbital debris advanced design project in support of solar system exploration

    NASA Technical Reports Server (NTRS)

    Ramohalli, Kumar; Mitchell, Dominique; Taft, Brett; Chinnock, Paul; Kutz, Bjoern

    1992-01-01

    This paper is regarding a project in the Advanced Design Program at the University of Arizona. The project is named the Autonomous Space Processor for Orbital Debris (ASPOD) and is a NASA/Universities Space Research Association (USRA) sponsored design project. The development of ASPOD and the students' abilities in designing and building a prototype spacecraft are the ultimate goals of this project. This year's focus entailed the development of a secondary robotic arm and end-effector to work in tandem with an existent arm in the removal of orbital debris. The new arm features the introduction of composite materials and a linear drive system, thus producing a light-weight and more accurate prototype. The main characteristic of the end-effector design is that it incorporates all of the motors and gearing internally, thus not subjecting them to the harsh space environment. Furthermore, the arm and the end-effector are automated by a control system with positional feedback. This system is composed of magnetic and optical encoders connected to a 486 PC via two servo-motor controller cards. Programming a series of basic routines and sub-routines has allowed the ASPOD prototype to become more autonomous. The new system is expected to perform specified tasks with a positional accuracy of 0.5 cm.

  11. Stabilization and parameter identification of tumbling space debris with bounded torque in postcapture

    NASA Astrophysics Data System (ADS)

    Zhang, Teng; Yue, Xiaokui; Ning, Xin; Yuan, Jianping

    2016-06-01

    This paper presents a new control scheme for the problem of a space robot after capturing an unknown tumbling target, such as space debris. Robotic capturing the target may destabilize the base of spacecraft and control torque is bounded which would affect the performance of attitude control system. To stabilize the base with bounded torque in postcapture scenario, a new control scheme which utilizes the control torque to balance angular momentum and motion of the manipulator to compensate limitation of the torque, is proposed. Considering uncertainties of the target, parameter identification technique for tumbling target with linear momentum is utilized to correct parameters of the controller. To verify validity and feasibility of the proposed concept, a planar space robot capturing small, medium and large target with or without linear momentum is studied. The results show that the whole system is stabilized finally and all the inertial parameters of the target converge to their real values.

  12. An Electric Propulsion "Shepherd" for Active Debris Removal that Utilizes Ambient Gas as Propellant

    NASA Technical Reports Server (NTRS)

    Matney, Mark J.

    2013-01-01

    There is a growing consensus among the space debris technical community that limiting the long ]term growth of debris in Low-Earth Orbit (LEO) requires that space users limit the accumulation of mass in orbit. This is partially accomplished by mitigation measures for current and future LEO systems, but there is now interest in removing mass that has already accumulated in LEO from more than 50 years of space activity (termed "Active Debris Removal", or ADR). Many ADR proposals face complex technical issues of how to grapple with uncooperative targets. Some researchers have suggested the use of conventional ion thrusters to gently "blow" on objects to gradually change their orbits, without ever having to come into physical contact with the target. The chief drawback with these methods is the cost per object removed. Typically, a space "tug" or an ion-drive "shepherd" can only remove a few objects per mission due to limited propellant. Unless a costeffective way that removes tens of objects per mission can be found, it is not clear that any of the ideas so far proposed will be economically viable. In this paper, a modified version of the ion-drive "shepherd" is proposed that uses ambient atmospheric gases in LEO as propellant for the ion drives. This method has the potential to greatly extend the operational lifetime of an ADR mission, as the only mission limit is the lifetime of the components of the satellite itself, not on its fuel supply. An ambient-gas ion-drive "shepherd" would the local atmospheric drag on an object by ionizing and accelerating the ambient gas the target would have encountered anyway, thereby hastening its decay. Also, the "shepherd" satellite itself has a great deal of flexibility to maneuver back to high altitude and rendezvous with its next target using the ion drive not limited by fuel supply. However, the amount of available ambient gas is closely tied to the altitude of the spacecraft. It may be possible to use a "hybrid" approach that

  13. An Electric Propulsion "Shepherd" for Active Debris Removal that Utilizes Ambient Gas as Propellant

    NASA Technical Reports Server (NTRS)

    Matney, Mark

    2013-01-01

    There is a growing consensus among the space debris technical community that limiting the long-term growth of debris in Low-Earth Orbit (LEO) requires that space users limit the accumulation of mass in orbit. This is partially accomplished by mitigation measures for current and future LEO systems, but there is now interest in removing mass that has already accumulated in LEO from more than 50 years of space activity (termed "Active Debris Removal", or ADR). Many ADR proposals face complex technical issues of how to grapple with uncooperative targets. Some researchers have suggested the use of conventional ion thrusters to gently "blow" on objects to gradually change their orbits, without ever having to come into physical contact with the target. The chief drawback with these methods is the cost per object removed. Typically, a space "tug" or an ion-drive "shepherd" can only remove a few objects per mission due to limited propellant. Unless a cost-effective way that removes tens of objects per mission can be found, it is not clear that any of the ideas so far proposed will be economically viable. In this paper, a modified version of the ion-drive "shepherd" is proposed that uses ambient atmospheric gases in LEO as propellant for the ion drives. This method has the potential to greatly extend the operational lifetime of an ADR mission, as the only mission limit is the lifetime of the components of the satellite itself, not on its fuel supply. An ambient-gas ion-drive "shepherd" would enhance the local atmospheric drag on an object by ionizing and accelerating the ambient gas the target would have encountered anyway, thereby hastening its decay. Also, the "shepherd" satellite itself has a great deal of flexibility to maneuver back to high altitude and rendezvous with its next target using the ion drive not limited by fuel supply. However, the amount of available ambient gas is closely tied to the altitude of the spacecraft. It may be possible to use a "hybrid

  14. Hypervelocity impact facility for simulating materials exposure to impact by space debris

    NASA Astrophysics Data System (ADS)

    Rose, M. Frank; Best, S. G.; Chaloupka, T.; Stephens, B.

    1992-06-01

    The Space Power Institute at Auburn University has constructed an electromagnetically driven particle accelerator for simulating the effects of space debris on the materials for use in advanced spacecraft. The facility consists of a capacitively driven accelerator section, a drift tube and a specimen impact chamber. The drift tube is sufficiently long that all electrical activity has ceased prior to impact in the specimen chamber. The impact chamber is large enough to allow a wide range of specimen geometries, ranging from small coupons to active portions of advanced spacecraft. The electric drive for the accelerator consists of a 67 kJ, 50 k capacitor bank arranged in a low inductance configuration. The bank is discharged through an aluminum armature/plastic ablator plate/projectile load in roughly 1.2 microsec. The evaporation of the ablaitor plate produces an expanding gas slug, mostly H2, traveling at a velocity of some 60 km/sec. Because of the pressure and local density, the expanding gas cloud accelerates projectiles due to plasma drag. To date, we have utilized projectiles consisting of 100 micron SiC, 100 and 400 micron Al2O3, 100 and 145 micron olivines. Since many particles are accelerated in a given experiment, there is a range of velocities for each shot as well as some particle breakup. Advanced diagnostics techniques allow determination of impact coordinates, velocity, and approximate size for as many as 50 individual impacts in a given experiment. We routinely measure velocities in the range 1-15 km/sec. We have used this facility to study a variety of impact generated phenomena on coated surfaces, both paint and plastic, thermal blanket material, solar cell arrays, and optical materials such as glass and quartz lenses. The operating characteristics of the gun, the advanced diagnostic scheme, and the results of studies of crater morphology are described in detail. Projectile residue analysis, as a function of impact velocity for the materials listed

  15. Hypervelocity impact facility for simulating materials exposure to impact by space debris

    NASA Technical Reports Server (NTRS)

    Rose, M. Frank; Best, S. G.; Chaloupka, T.; Stephens, B.

    1992-01-01

    The Space Power Institute at Auburn University has constructed an electromagnetically driven particle accelerator for simulating the effects of space debris on the materials for use in advanced spacecraft. The facility consists of a capacitively driven accelerator section, a drift tube and a specimen impact chamber. The drift tube is sufficiently long that all electrical activity has ceased prior to impact in the specimen chamber. The impact chamber is large enough to allow a wide range of specimen geometries, ranging from small coupons to active portions of advanced spacecraft. The electric drive for the accelerator consists of a 67 kJ, 50 k capacitor bank arranged in a low inductance configuration. The bank is discharged through an aluminum armature/plastic ablator plate/projectile load in roughly 1.2 microsec. The evaporation of the ablaitor plate produces an expanding gas slug, mostly H2, traveling at a velocity of some 60 km/sec. Because of the pressure and local density, the expanding gas cloud accelerates projectiles due to plasma drag. To date, we have utilized projectiles consisting of 100 micron SiC, 100 and 400 micron Al2O3, 100 and 145 micron olivines. Since many particles are accelerated in a given experiment, there is a range of velocities for each shot as well as some particle breakup. Advanced diagnostics techniques allow determination of impact coordinates, velocity, and approximate size for as many as 50 individual impacts in a given experiment. We routinely measure velocities in the range 1-15 km/sec. We have used this facility to study a variety of impact generated phenomena on coated surfaces, both paint and plastic, thermal blanket material, solar cell arrays, and optical materials such as glass and quartz lenses. The operating characteristics of the gun, the advanced diagnostic scheme, and the results of studies of crater morphology are described in detail. Projectile residue analysis, as a function of impact velocity for the materials listed

  16. Assessment of the effects of space debris and meteoroids environment on the Space Station solar array assembly

    NASA Technical Reports Server (NTRS)

    Nahra, Henry K.

    1988-01-01

    The methodology used to assess the probability of no impact of space debris and meteoroids on a spacecraft structure is applied to the Space Station solar array assembly. Starting with space debris and meteoroid flux models, the projected surface area of the solar cell string circuit of the solar array panel and the mast longeron, and the design lifetime, the possibility of no impact on the solar mast and solar cell string circuits was determined as a function of particle size. The probability of no impact on the cell string circuits was used to derive the probability of no open circuit panel. The probability of meeting a certain power requirement at the end of the design lifetime was then calculated as a function of impacting particle size. Coupled with a penetration and damage models/correlations which relate the particle size to penetration depth and damage, the results of this analysis can be used to determine the probability of meeting the lower power requirement given a degree of redundancy, and the probability of no impact on the solar array mast.

  17. Assessment of the effects of space debris and meteoroids environment on the space station solar array assembly

    NASA Technical Reports Server (NTRS)

    Nahra, Henry K.

    1988-01-01

    The methodology used to assess the probability of no impact of space debris and meteoroids on a spacecraft structure is applied to the Space Station solar array assembly. Starting with the space debris and meteoroids flux models, the projected surface area of the solar cell string circuit of the solar array panel and the mast longeron, and the design lifetime, the possibility of no impact on the solar array mast and solar cell string circuits was determined as a function of particle size. The probability of no impact on the cell string circuits was used to derive the probability of no open circuit panel. The probability of meeting a certain power requirement at the end of the design lifetime was then calculated as a function of impacting particle size. Coupled with a penetration and damage models/correlations which relate the particle size to the penetration depth and damage, the results of this analysis can be used to determine the probability of meeting the lower power requirement given a degree of redundancy, and the probability of no impact on the solar array mast.

  18. Active Debris Removal - A Grand Engineering Challenge for the Twenty-First Century

    NASA Technical Reports Server (NTRS)

    Liou, J.-C.

    2011-01-01

    The collision between Iridium 33 and Cosmos 2251 in 2009 has reignited interest in using active debris removal to remediate the near-Earth orbital debris environment. A recent NASA study shows that, in order to stabilize the environment in the low Earth orbit (LEO) region for the next 200 years, active debris removal of about five large and massive (1 to more than 8 metric tons) objects per year is needed. To develop the capability to remove five of those objects per year in a cost-effective manner truly represents a grand challenge in engineering and technology development.

  19. A new stochastic impressionistic low earth (SIMPLE) engineering model of the space debris scenario

    NASA Astrophysics Data System (ADS)

    Ananthasayanam, M.; Anilkumar, A.; Subba Rao, P.

    A new stochastic approach is presented in this paper for the modeling of the space debris environment. The approach and the philosophy that has been adopted is similar to that utilized for evolving the International Standard or other various Reference Atmospheres. The bases for the present model are the following observations. The space debris environment is a randomly evolving dynamical process. The joint probability distribution function and the statistics of the various characteristics based on the observed data at various times can be used to model the debris environment. The description should be close to the mean over appropriate space and time and within the ranges of the variations of the data. Further the model should have a balance between accuracy and simplicity and have the smallest possible number of parameters. Also the model should have easy mathematical tractability for further simulations, analysis of the environment and the estimation of collision probabilities and be able to assimilate newer data and adaptively change the model parameters with the passage of time. The present model being impressionistic in nature, we call it SIMPLE denoting Stochastic Impressionistic Low Earth, model. This model is presently up to an altitude of 2000 km and eccentricity less than 0.2 and thus encompasses about 75% of the large objects catalogued in NORAD Two Line Element (TLE) sets. SIMPLE describes the marginal probability distributions with a tertiary mixture of Laplace distributions for the number of fragments in terms of the altitude and perigee height and Lognormal for the distribution of eccentricity and ballistic coefficient. The model parameters for the characteristics are provided extensively for various altitudes and inclination bands similar to ORDEM96 and somewhat in line with the style for the various reference atmospheres . The number of parameter values is quite less than in ORDEM96 for description of altitude or perigee distributions and the model

  20. Pay Me Now or Pay Me More Later: Start the Development of Active Orbital Debris Removal Now

    NASA Astrophysics Data System (ADS)

    McKnight, D.

    2010-09-01

    time it takes for the actions to reap benefits. Additionally, if the growth of the lethal hazard grows faster than anticipated it may be necessary to replace some satellites, execute large object removal, and perform medium debris (i.e. lethal fragments) sweeping operations. The sooner the community starts to remove large derelict objects, the more likely satellite damage will be minimized and the less likely that medium debris sweeping will have to be implemented. While the research is focused on starting debris removal, the ensemble of observations reinforces the need to continue to push for as close to 100% compliance to debris mitigation guidelines as possible. This analysis is unique in its pragmatic application of advanced probability concepts, merging of space hazard assessments with space insurance thresholds, and the use of general risk management concepts on the orbital debris hazard control process. It is hoped that this paper provides an impetus for spacefaring organizations to start to actively pursue development and deployment of debris removal solutions and policies.

  1. Active debris removal: Aspects of trajectories, communication and illumination during final approach

    NASA Astrophysics Data System (ADS)

    Deloo, J. A. F.; Mooij, E.

    2015-12-01

    The aim of this research is to investigate a debris-remediation technique where a chaser performs a rendezvous with the debris, establishes a rigid-link connection, and actively de-orbits the debris. ESA's satellite Envisat has been used as a design case. The research assessed passive safety aspects of the final-approach manoeuvres by analysing the resulting trajectories after thrust inhibit. Next, the research explored the possibility for continuous ground communication by considering the chain of European space tracking (ESTRACK) ground stations (located mainly in Europe). Furthermore, obstruction of the communication signal by the target was studied. Last, the research studies the illumination conditions encountered by the chaser, where obscuration of the Sun by the target was taken into account. Each of these elements are studied for the final approach only. In the topic of passive safety, the results confirm that manoeuvres on H-bar are passively unsafe, and indicate this also for the fly-around manoeuvres along the natural orbital motion. It can be concluded from the communication analysis that the maximum duration of the uninterrupted window varies between 22 and 32 min, using the chain of core ESTRACK ground stations. However, the study on communication blockage shows that frequent communication gaps can occur, with the longest gaps being in the order of one minute in duration. In the field of illumination, it can be concluded that correct target illumination and sensor visibility cannot be guaranteed. Furthermore, the average solar-array area available during final approach varies between 35% and 75%, due to both incorrect pointing of the solar array by the chaser and obscuration by the target.

  2. System, Apparatus, and Method for Active Debris Removal

    NASA Technical Reports Server (NTRS)

    Griffith, Sr., Anthony D. (Inventor); Kohli, Rajiv (Inventor); Burns, Susan H. (Inventor); Damico, Stephen J. (Inventor); Gruber, David J. (Inventor); Hickey, Christopher J. (Inventor); Lee, David E. (Inventor); Robinson, Travis M. (Inventor); Smith, Jason T. (Inventor); Spehar, Peter T. (Inventor)

    2017-01-01

    Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

  3. GEO space debris flux determination based on earth-fixed coordinate system

    NASA Astrophysics Data System (ADS)

    Dongfang, Wang; Baojun, Pang; Weike, Xiao

    2017-01-01

    An analysis is performed on the space debris flux determination of geosynchronous (GEO) orbit based on earth-fixed coordinate system. As part of the examination, flux contribution from different components of space debris is presented here in order to clarify the linkage between orbital characteristic and resulting flux distribution. The analysis of GEO flux determination based on earth-fixed coordinate system reveals several new insights: 1) Near the GEO equatorial plane, average flux mainly centralizes in two azimuth ranges: the higher priority one, local azimuth close to±90°, mainly contributed from objects with relatively larger inclination; the lower priority one, local azimuth close to 0°, mainly contributed from objects with relatively smaller inclination. 2) Impact flux against geostationary satellites is not unified by longitude. Longitude-dependent flux determination based on earth-fixed frame reveals that impact flux against geostationary satellite near the geopotential wells (105°W and 75°E longitude zones) is about two to three times larger than average. 3) The comparison of flux determination against certain targets based on earth-fixed coordinate system and inertially-fixed coordinate system shows significant difference.

  4. Optical observations of space debris in GEO and in highly-eccentric orbits

    NASA Astrophysics Data System (ADS)

    Schildknecht, T.; Musci, R.; Ploner, M.; Beutler, G.; Flury, W.; Kuusela, J.; de Leon Cruz, J.; de Fatima Dominguez Palmero, L.

    2004-01-01

    The space debris population in low Earth orbits (LEO) has been extensively studied during the last decade and reasonable models covering all size ranges were produced. Information on the distribution of objects in the geostationary ring (GEO), however, is still comparatively sparse. Until quite recently the population of man-made objects in GEO had to be inferred solely from the about 900 continuously tracked objects and the modeling of the two explosions known to have occurred in GEO. Optical observations from the last two years performed with ESA's 1-m telescope at the Teide observatory in Tenerife changed the situation substantially. A hitherto unknown but significant population of small-size objects with diameters as small as ten centimeters has been detected in GEO. Objects in highly-eccentric orbits crossing the GEO region, in particular objects in geostationary transfer orbits (GTO), also contribute to the density of space debris in GEO. This family is even less well known than the GEO population, although many explosion events were reported in this orbital region. The paper will summarize recent results from the ESA GEO survey and describe the techniques and first results of a trial GTO survey.

  5. Optical Observations of Space Debris with a global network of robotic telescopes

    NASA Astrophysics Data System (ADS)

    Laas-Bourez, Myrtille; Coward, David; Klotz, Alain; Boer, Michel

    The two TAROTs (Télescopes a Action Rapide pour les Objets Transitoires; Rapid Response ` Telescopes for Transient Objects) are fully robotic optical observatories with optimized observa-tion scheduling, data processing and archiving. In 2008, a new algorithm based on morpholog-ical mathematic was implemented in the standard pipeline. The method works by correlating measurements of the same object on successive images and provides very imprecise detection and false alarm rates. We have improved the algorithm and present the optimized version in this paper. With show that the efficiency and quality of the geostationary orbit survey is drastically improved. We find false detection and non-detection rates near zero. In this paper, we provide an overview of an international network of robotic optical telescopes that now includes the two TAROTs, a new Australian facility, the 1-m Zadko Telescope, and two other French telescopes. This robotic telescope networks offer simplicity in managing data, facilities and optimizes the potential science output for the individual instruments. In relation to space debris , the network will allow the Zadko Telescope to participate in a satellite and space debris tracking program. The network will potentially access 100% of all geostationary belt objects, provide accurate satellites positions and track low Earth orbit objects.

  6. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray F01

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks around the perifery of the experiment tray show the results of contamination and exposure to the space environment. The variation in color, from off-white along the top flange to brown at other locations, is attributed to variations in the atomic oxygen flux intensity. A surface exposed to a higher intensity of atomic oxygen flux will have less contamination due to the scrubbing or cleaning action that occurs when the atomic oxygen molecules impact that surface. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The dark vertical streaks seen on the left debris panel in the flight photographs are still visi- ble, but are much lighter since the blue sky reflection is not present. The same can be said for the two (2) discolorations, they are still visible but much lighter. The light band along the sides and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  7. Report on orbital debris

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The success of space endeavors depends upon a space environment sufficiently free of debris to enable the safe and dependable operation of spacecraft. An environment overly cluttered with debris would threaten the ability to utilize space for a wide variety of scientific, technological, military, and commercial purposes. Man made space debris (orbital debris) differs from natural meteoroids because it remains in earth orbit during its lifetime and is not transient through the space around the Earth. The orbital debris environment is considered. The space environment is described along with sources of orbital debris. The current national space policy is examined, along with ways to minimize debris generation and ways to survive the debris environment. International efforts, legal issues and commercial regulations are also examined.

  8. Space debris orbit prediction errors using bi-static laser observations. Case study: ENVISAT

    NASA Astrophysics Data System (ADS)

    Wirnsberger, Harald; Baur, Oliver; Kirchner, Georg

    2015-06-01

    Large and massive space debris objects - such as abandoned satellites and upper stages - in the Low Earth Orbit (LEO) segment pose an increasing threat to all space faring nations. For collision avoidance measures or the removal of these objects, the quality of orbit predictions is one of the most relevant issues. Laser ranging has the potential to significantly contribute to the reliability and accuracy of orbit predictions. The benefit of "conventional" two-way laser ranges for this purpose has recently been demonstrated. For the first time, in this contribution we focus on bi-static laser observations - a new observation type for orbit determination and prediction. Our investigations deal with orbit predictions of the defunct ENVISAT satellite. In order to compensate for the sparseness of "conventional" tracking data, we found that the concept of bi-static laser observations improves the prediction accuracy by one order of magnitude compared to the results based on two-way laser ranges only.

  9. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray B02

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks around the perifery of the experiment tray show the results of contamination and exposure to the space environment. The variation in color, from tan along the top flange to brown at other locations, is attributed to variations in the atomic oxygen flux intensity. A surface exposed to a higher intensity of atomic oxygen flux will have less contamination due to the scrubbing or cleaning action that occurs when the atomic oxygen molecules impact that surface. The pink and the greenish-gray tints on the two (2) debris panels are a by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environ ment. The light band along the sides and across the bottom of the panels is caused by light reflecting from the tray sidewalls.

  10. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray E01

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clamp blocks around the periphery of the experiment tray show the results of contamination and exposure to the space environment. The variation in color, from off-white along the top flange to brown at other locations, is attributed to variations in the atomic oxygen flux intensity. A surfaces exposed to a higher intensity of atomic oxygen flux will have less contamination due to the scrubbing or cleaning action that occurs when the atomic oxygen molecules impact that surface. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The light band along the bottom of the panels is caused by light reflecting from the tray sidewalls.

  11. Earth's gravity gradient and eddy currents effects on the rotational dynamics of space debris objects: Envisat case study

    NASA Astrophysics Data System (ADS)

    Gómez, Natalia Ortiz; Walker, Scott J. I.

    2015-08-01

    The space debris population has grown rapidly over the last few decades with the consequent growth of impact risk between current objects in orbit. Active Debris Removal (ADR) has been recommended to be put into practice by several National Agencies in order to remove objects that pose the biggest risk for the space community. The most immediate target that is being considered for ADR by the European Space Agency is the Earth-observing satellite Envisat. In order to safely remove such a massive object from its orbit, a capturing process followed by a controlled reentry is necessary. However, current ADR methods that require physical contact with the target have limitations on the maximum angular momentum that can be absorbed and a de-tumbling phase prior to the capturing process may be required. Therefore, it is of utmost importance for the ADR mission design to be able to predict accurately how the target will be rotating at the time of capture. This article analyses two perturbations that affect an object in Low Earth Orbit (LEO), the Earth's gravity gradient and the eddy currents induced by the Earth's magnetic field. The gravity gradient is analysed using the equation of conservation of total energy and a graphical method is presented to understand the expected behaviour of any object under the effect of this perturbation. The eddy currents are also analysed by studying the total energy of the system. The induced torque and the characteristic time of decay are presented as a function of the object's magnetic tensor. In addition, simulations were carried out for the Envisat spacecraft including the gravity gradient perturbation as well as the eddy currents effect using the International Geomagnetic Reference Field IGRF-11 to model the Earth's magnetic field. These simulations show that the combined effect of these two perturbations is a plausible explanation for the rotational speed decay observed between April 2013 and September 2013.

  12. Orbital Debris Quarterly News, Vol. 13, No. 2

    NASA Technical Reports Server (NTRS)

    Liou, J.-C. (Editor); Shoots, Debi (Editor)

    2009-01-01

    Topics include: debris clouds left by satellite collision; debris flyby near the International Space Station; and break-up of an ullage motor from a Russian Proton launch vehicle. Findings from the analysis of the STS-126 Shuttle Endeavour window impact damage are provided. Abstracts from the NASA Orbital Debris program office are presented and address a variety of topics including: Reflectance Spectra Comparison of Orbital Debris, Intact Spacecraft, and Intact Rocket Bodies in the GEO Regime; Shape Distribution of Fragments From Microsatellite Impact Tests; Micrometeoroid and Orbital Debris Threat Mitigation Techniques for the Space Shuttle Orbiter; Space Debris Environment Remediation Concepts; and, In Situ Measurement Activities at the NASA Orbital Debris Program Office. Additionally, a Meeting Report is provided for the 12 meeting of the NASA/DoD Orbital Debris Working Group.

  13. Orbital Debris Research at NASA

    NASA Technical Reports Server (NTRS)

    Stansbery, Eugene G.

    2009-01-01

    The United States has one of the most active programs of research of the orbital debris environment in the world. Much of the research is conducted by NASA s Orbital Debris Program Office at the Johnson Space Center. Past work by NASA has led to the development of national space policy which seeks to limit the growth of the debris population and limit the risk to spacecraft and humans in space and on the Earth from debris. NASA has also been instrumental in developing consistent international policies and standards. Much of NASA's efforts have been to measure and characterize the orbital debris population. The U.S. Department of Defense tracks and catalogs spacecraft and large debris with it's Space Surveillance Network while NASA concentrates on research on smaller debris. In low Earth orbit, NASA has utilized short wavelength radars such as Haystack, HAX, and Goldstone to statistically characterize the population in number, size, altitude, and inclination. For higher orbits, optical telescopes have been used. Much effort has gone into the understanding and removal of observational biases from both types of measurements. NASA is also striving to understand the material composition and shape characteristics of debris to assess these effects on the risk to operational spacecraft. All of these measurements along with data from ground tests provide the basis for near- and long-term modeling of the environment. NASA also develops tools used by spacecraft builders and operators to evaluate spacecraft and mission designs to assess compliance with debris standards and policies which limit the growth of the debris environment.

  14. First astrometric observations of space debris with the MéO telescope

    NASA Astrophysics Data System (ADS)

    Laas-Bourez, Myrtille; Wailliez, Sébastien; Deleflie, Florent; Klotz, Alain; Albanese, Dominique; Saba, Nathalie

    2012-02-01

    The MéO (for Métrologie Optique) telescope is the Satellite and Lunar Laser Ranging (SLR) dedicated telescope of Observatoire de la Côte d'Azur (France) located at plateau de Calern. The telescope uses an altazimuth mount. The motorization of the mount has a capability of 6 deg/s allowing the follow up of Low Earth Orbits (LEO) satellites, as well as Medium Earth Orbits (MEO) and geostationary (GEO) satellites, and the Moon. The telescope has a primary mirror of 1.54 m. It uses a Nasmyth focus equipped with an EMCCD camera. The telescope field of view, defined by the equivalent focal length and the size of the camera, is currently 3.4 arcmin × 3.4 arcmin.Space debris observation with an optical telescope ideally requires a large field of view, accurate pointing, a fast slew rate, a high sensitivity, accurate astrometric positions, and a precise method for orbit propagation. The challenge is to obtain accurate orbits for all debris without compromising the field of view. The MéO telescope has a larger diameter than the ones habitually used for space debris tracking. It should improve the current accuracy of observations in the GEO region. For LEO, such sensitivity should allow observations of small pieces of debris at low altitudes.This paper presents the preliminary experiments carried out to benefit from the high astrometric quality of the instrument, namely the method developed to extract and to compute the astrometric positions of LEO and MEO satellites, as a test of the capabilities of such an instrument (very small field of view, but large aperture) for space debris tracking. Furthermore, we analyse the ability of MéO to keep track of an object for which only a preliminary orbit (computed by the Laplace method from previous observations) is known, so that high precision measurements can be obtained and the object can be catalogued with an updated orbit.The feasibility of our astrometric methods was tested throughout 2010. This paper presents the methods

  15. FIVE DEBRIS DISKS NEWLY REVEALED IN SCATTERED LIGHT FROM THE HUBBLE SPACE TELESCOPE NICMOS ARCHIVE

    SciTech Connect

    Soummer, Rémi; Perrin, Marshall D.; Pueyo, Laurent; Choquet, Élodie; Chen, Christine; Golimowski, David A.; Brendan Hagan, J.; Moerchen, Margaret; N'Diaye, Mamadou; Wolff, Schuyler; Debes, John; Hines, Dean C.; Mittal, Tushar; Rajan, Abhijith; Schneider, Glenn

    2014-05-10

    We have spatially resolved five debris disks (HD 30447, HD 35841, HD 141943, HD 191089, and HD 202917) for the first time in near-infrared scattered light by reanalyzing archival Hubble Space Telescope (HST)/NICMOS coronagraphic images obtained between 1999 and 2006. One of these disks (HD 202917) was previously resolved at visible wavelengths using the HST/Advanced Camera for Surveys. To obtain these new disk images, we performed advanced point-spread function subtraction based on the Karhunen-Loève Image Projection algorithm on recently reprocessed NICMOS data with improved detector artifact removal (Legacy Archive PSF Library And Circumstellar Environments (LAPLACE) Legacy program). Three of the disks (HD 30447, HD 35841, and HD 141943) appear edge-on, while the other two (HD 191089 and HD 202917) appear inclined. The inclined disks have been sculpted into rings; in particular, the disk around HD 202917 exhibits strong asymmetries. All five host stars are young (8-40 Myr), nearby (40-100 pc) F and G stars, and one (HD 141943) is a close analog to the young Sun during the epoch of terrestrial planet formation. Our discoveries increase the number of debris disks resolved in scattered light from 19 to 23 (a 21% increase). Given their youth, proximity, and brightness (V = 7.2-8.5), these targets are excellent candidates for follow-up investigations of planet formation at visible wavelengths using the HST/Space Telescope Imaging Spectrograph coronagraph, at near-infrared wavelengths with the Gemini Planet Imager and Very Large Telescope/SPHERE, and at thermal infrared wavelengths with the James Webb Space Telescope NIRCam and MIRI coronagraphs.

  16. Catastrophe on the Horizon: A Scenario-Based Future Effect of Orbital Space Debris

    DTIC Science & Technology

    2010-04-01

    4 Reducing and Clearing Orbital Debris ……….....................................................................................5...impact it could have on our society and the world. This research is intended to identify some potential futures as a result from orbital debris and...Network (SSN), managed by US Strategic Command), which provides radar data on spacecraft trajectories.9 As the amount of orbital debris continues to

  17. LightForce Photon-Pressure Collision Avoidance: Efficiency Assessment on an Entire Catalogue of Space Debris

    NASA Technical Reports Server (NTRS)

    Stupl, Jan Michael; Faber, Nicolas; Foster, Cyrus; Yang Yang, Fan; Levit, Creon

    2013-01-01

    The potential to perturb debris orbits using photon pressure from ground-based lasers has been confirmed by independent research teams. Two useful applications of this scheme are protecting space assets from impacts with debris and stabilizing the orbital debris environment, both relying on collision avoidance rather than de-orbiting debris. This paper presents the results of a new assessment method to analyze the efficiency of the concept for collision avoidance. Earlier research concluded that one ground based system consisting of a 10 kW class laser, directed by a 1.5 m telescope with adaptive optics, can prevent a significant fraction of debris-debris collisions in low Earth orbit. That research used in-track displacement to measure efficiency and restricted itself to an analysis of a limited number of objects. As orbit prediction error is dependent on debris object properties, a static displacement threshold should be complemented with another measure to assess the efficiency of the scheme. In this paper we present the results of an approach using probability of collision. Using a least-squares fitting method, we improve the quality of the original TLE catalogue in terms of state and co-state accuracy. We then calculate collision probabilities for all the objects in the catalogue. The conjunctions with the highest risk of collision are then engaged by a simulated network of laser ground stations. After those engagements, the perturbed orbits are used to re-assess the collision probability in a 20 minute window around the original conjunction. We then use different criteria to evaluate the utility of the laser-based collision avoidance scheme and assess the number of base-line ground stations needed to mitigate a significant number of high probability conjunctions. Finally, we also give an account how a laser ground station can be used for both orbit deflection and debris tracking.

  18. The Orbital Debris Problem and the Challenges for Environment Remediation

    NASA Technical Reports Server (NTRS)

    Liou, J.-C.

    2013-01-01

    Orbital debris scientists from major international space agencies, including JAXA and NASA, have worked together to predict the trend of the future environment. A summary presentation was given to the United Nations in February 2013. The orbital debris population in LEO will continue to increase. Catastrophic collisions will continue to occur every 5 to 9 years center dot To limit the growth of the future debris population and to better protect future spacecraft, active debris removal, should be considered.

  19. Comparison of different methods to compute a preliminary orbit of Space Debris using radar observations

    NASA Astrophysics Data System (ADS)

    Ma, Hélène; Gronchi, Giovanni F.

    2014-07-01

    We advertise a new method of preliminary orbit determination for space debris using radar observations, which we call Infang †. We can perform a linkage of two sets of four observations collected at close times. The context is characterized by the accuracy of the range ρ, whereas the right ascension α and the declination δ are much more inaccurate due to observational errors. This method can correct α, δ, assuming the exact knowledge of the range ρ. Considering no perturbations from the J 2 effect, but including errors in the observations, we can compare the new method, the classical method of Gibbs, and the more recent Keplerian integrals method. The development of Infang is still on-going and will be further improved and tested.

  20. Space Debris Conjunction Risk Assessment for the ATV-Jules Verne Mission

    NASA Astrophysics Data System (ADS)

    Delavault, S.; Dupuis, G.; Perrachon, P.

    2009-03-01

    This paper focuses on the collision risk assessment, between ATV and space debris, managed in ATV-CC at CNES during phasing to docking and de-orbit phases. First, the methods and results of middle and short term mission analyses are detailed. The effects of the two fragmentation events which occurred shortly before and after the launch (the US ASAT on USA 193 and the natural fragmentation of the Russian satellite COSMOS 2421) have been evaluated using models and data from GRAVES and USSTRATCOM catalogues. The results showed a important impact on the foreseen conjunction rate. Second, the operational procedure of the conjunction management is described. The operational organization within ATV-CC teams and with the international partners is also presented. Then, a statement of the operational conjunction management is done, showing a good consistency level with the predictions. Eventually this led to 3 avoidance events (but only one avoidance maneuver).

  1. Micrometeoroid and Orbital Debris Threat Mitigation Techniques for the Space Shuttle Orbiter

    NASA Astrophysics Data System (ADS)

    Hyde, James L.; Christiansen, Eric L.; Lear, Dana M.; Kerr, Justin H.

    2009-03-01

    An overview of significant Micrometeoroid and Orbital Debris (MMOD) impacts on the Payload Bay Door radiators, wing leading edge reinforced carbon-carbon panels and crew module windows will be presented, along with a discussion of the techniques NASA has implemented to reduce the risk from MMOD impacts. The concept of "Late Inspection" of the Nose Cap and Wing Leading Edge (WLE) Reinforced Carbon Carbon (RCC) regions will be introduced. An alternative mated attitude with the International Space Station (ISS) on shuttle MMOD risk will also be presented. The significant threat mitigation effect of these two techniques will be demonstrated. The wing leading edge impact detection system, on-orbit repair techniques and disabled vehicle contingency plans will also be discussed.

  2. Analysis of Particulate and Fiber Debris Samples Returned from the International Space Station

    NASA Technical Reports Server (NTRS)

    Perry, Jay L.; Coston, James E.

    2014-01-01

    During the period of International Space Station (ISS) Increments 30 and 31, crewmember reports cited differences in the cabin environment relating to particulate matter and fiber debris compared to earlier experience as well as allergic responses to the cabin environment. It was hypothesized that a change in the cabin atmosphere's suspended particulate matter load may be responsible for the reported situation. Samples were collected and returned to ground-based laboratories for assessment. Assessments included physical classification, optical microscopy and photographic analysis, and scanning electron microscopy (SEM) evaluation using energy dispersive X-ray spectrometry (EDS) methods. Particular points of interest for assessing the samples were for the presence of allergens, carbon dioxide removal assembly (CDRA) zeolite dust, and FGB panel fibers. The results from the physical classification, optical microscopy and photographic analysis, and SEM EDS analysis are presented and discussed.

  3. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray D06

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph, taken prior to removal of the experiment trays from the LDEF, again shows a significant difference in the color of the paint dots on the experiment tray clamp blocks. The direction and intensity of the artifical light source has caused hot spots and reflections that tend to wash-out the brown stain on the aluminum structure. The Space Debris Impact Experiment panels have a clean washed-out look that is attributed to the lighting. The center panel has a pink tint and the end panel has a green tint as they appeared in the pre-launch photograph. The finger prints seen on the flight photograph are not visible but a faint shadow of the palm print can be seen. With the change in direction of the light source, the panel serial numbers and the location of impacts can not be determined.

  4. Analysis of the 2007 Chinese ASAT Test and the Impact of its Debris on the Space Environment

    NASA Astrophysics Data System (ADS)

    Kelso, T.

    On 2007 January 11, the People's Republic of China conducted a successful direct-ascent ASAT test against one of their own defunct polar-orbiting weather satellites. The test produced at least 1,337 pieces of debris large enough to be routinely tracked by the US Space Surveillance Network and the NASA Orbital Debris Program Office estimated it generated over 35,000 pieces of debris down to 1 centimeter in size. While this event captured worldwide attention in the weeks and months after the test was revealed, much of the information provided in the press was inaccurate or misleading and did not appear to be based on scientific analysis of the data available to the public. In order to help the public and key policy makers more fully understand the nature of the event and its impact on the existing satellite population, the Center for Space Standards & Innovation developed a series of animations, images, and graphical analyses to more clearly portray this event and provide a factual foundation for the subsequent debate. Those materials were all made publicly available via the Internet without restriction and have appeared in numerous publications. This paper will summarize the primary areas of analysis of this event, to include a confirmation of the basic facts initially reported in Aviation Week & Space Technology, a visualization of the initial spread of the debris cloud in the first couple of hours after the attack, analysis of the impact of the debris on the LEO space environment including the number of satellites potentially affected and the increase in the number of conjunctions, a look at the current debris environment, and an assessment of the orbital lifetimes that shows that these impacts will last not for years but for centuries. The visualization techniques used to portray these analyses played a substantial role in helping the scientific community to quickly and easily convey important aspects of this event to policy makers and the public at large.

  5. Optimal planning of LEO active debris removal based on hybrid optimal control theory

    NASA Astrophysics Data System (ADS)

    Yu, Jing; Chen, Xiao-qian; Chen, Li-hu

    2015-06-01

    The mission planning of Low Earth Orbit (LEO) active debris removal problem is studied in this paper. Specifically, the Servicing Spacecraft (SSc) and several debris exist on near-circular near-coplanar LEOs. The SSc should repeatedly rendezvous with the debris, and de-orbit them until all debris are removed. Considering the long-duration effect of J2 perturbation, a linear dynamics model is used for each rendezvous. The purpose of this paper is to find the optimal service sequence and rendezvous path with minimum total rendezvous cost (Δv) for the whole mission, and some complex constraints (communication time window constraint, terminal state constraint, and time distribution constraint) should be satisfied meanwhile. Considering this mission as a hybrid optimal control problem, a mathematical model is proposed, as well as the solution method. The proposed approach is demonstrated by a typical active debris removal problem. Numerical experiments show that (1) the model and solution method proposed in this paper can effectively address the planning problem of LEO debris removal; (2) the communication time window constraint and the J2 perturbation have considerable influences on the optimization results; and (3) under the same configuration, some suboptimal sequences are equivalent to the optimal one since their difference in Δv cost is very small.

  6. High-Power Amplifier Compatible Internally Sensed Optical Phased Array for Space Debris Tracking and Maneuvering

    NASA Astrophysics Data System (ADS)

    Roberts, L.; Francis, S.; Sibley, P.; Ward, R.; Smith, C.; McClelland, D.; Shaddock, D.

    2016-09-01

    Optical phased arrays (OPAs) provide a way to scale optical power beyond the capabilities of conventional CW lasers via coherent beam combination. By stabilising the relative output phase of multiple spatially separate lasers, OPAs form a coherent optical wavefront in the far field. Since the phase of each laser can be controlled independently, OPAs also have the ability to manipulate the distribution of optical power in the far field, and therefore may provide the capability to compensate for atmospheric turbulence. Combined with their inherent scalability and high power handling capabilities, OPAs are a promising technology for CW space debris ranging and manoeuvring. The OPA presented here is unique in its ability to sense the phase of each laser internally, without requiring any external sampling optics between it and the telescope. This allows the internally sensed OPA to be constructed entirely within fibre, utilising high-power fiber amplifiers to scale optical power beyond the limits of any conventional single lasers. The total power that can be delivered by each emitter in the OPA is limited only by the onset of stimulated Brillouin scattering, a non-linear effect that clamps the amount of power that can be delivered through a fiber waveguide. A three element internally sensed OPA developed at the Australian National University has been demonstrated to coherently combine three commercial 15 Watt fiber amplifiers with an output phase stability of one 200th of a wavelength. We have also demonstrated the ability to dynamically manipulate the distribution of optical power in the far-field at a bandwidth of up to 10 kHz. Since the OPA's control system is implemented using field-programmable gate-array technology, the system may be scaled beyond 100 emitters, potentially reaching the kilowatt level optical powers required to perturb the orbit of space debris.

  7. Experimental technique to simulate orbital-debris impact on space shields at impact velocities over 10 km/s

    SciTech Connect

    Chhabildas, L.C.; Boslough, M.B.

    1992-01-01

    With the development of a new HyperVelocity Launcher, HVL, at Sandia, it is now possible to perform experiments over the velocity range of 7 to 12 km/s. This velocity range has not been previously accessible for gram-size plates. This meets the requisite mass-velocity criteria established for the orbital debris environment. In this paper, the technique employed to launch thin flier plates to velocities not previously accessible on a two-stage light-gas gun is reported. In particular, this technique has been used on a two-stage light-gas gun to launch nominally 0.5 to 1.0-mm thick aluminum, titanium, and magnesium flier plates intact to velocities up to 12.2 km/s. Since the mass-velocity capability of the newly developed HVL meets the average specifications of the space debris environment, it is expected to be a useful tool to evaluate the effects of debris impact on space structures and debris shields. Examples of a plate impact i.e., orbital debris impact on a thin Whipple shield are presented in this paper.

  8. Experimental technique to simulate orbital-debris impact on space shields at impact velocities over 10 km/s

    SciTech Connect

    Chhabildas, L.C.; Boslough, M.B.

    1992-12-31

    With the development of a new HyperVelocity Launcher, HVL, at Sandia, it is now possible to perform experiments over the velocity range of 7 to 12 km/s. This velocity range has not been previously accessible for gram-size plates. This meets the requisite mass-velocity criteria established for the orbital debris environment. In this paper, the technique employed to launch thin flier plates to velocities not previously accessible on a two-stage light-gas gun is reported. In particular, this technique has been used on a two-stage light-gas gun to launch nominally 0.5 to 1.0-mm thick aluminum, titanium, and magnesium flier plates intact to velocities up to 12.2 km/s. Since the mass-velocity capability of the newly developed HVL meets the average specifications of the space debris environment, it is expected to be a useful tool to evaluate the effects of debris impact on space structures and debris shields. Examples of a plate impact i.e., orbital debris impact on a thin Whipple shield are presented in this paper.

  9. Research and Development on In-Situ Measurement Sensors for Micro-Meteoroid and Small Space Debris at JAXA

    NASA Astrophysics Data System (ADS)

    Kitazawa, Y.; Matsumoto, H.; Okudaira, O.; Kimoto, Y.; Hanada, T.; Faure, P.; Akahoshi, Y.; Hattori, M.; Karaki, A.; Sakurai, A.; Funakoshi, K.; Yasaka, T.

    2013-08-01

    The Japan Aerospace Exploration Agency (JAXA) has been conducting R&D into in-situ sensors for measuring micro-meteoroid and small-sized debris (MMSD) since the 1980s. Research into active sensors started with the meteoroid observation experiment conducted using the HITEN (MUSES-A) satellite that ISAS/JAXA launched in 1990. The main purpose behind the start of passive collector research was SOCCER, a late-80s Japan-US mission that was designed to capture cometary dust and then return to the Earth. Although this mission was cancelled, the research outcomes were employed in a JAXA mission for the return of MMSD samples using calibrated aerogel and involving the space shuttle and the International Space Station. Many other important activities have been undertaken as well, and the knowledge they have generated has contributed to JAXA's development of a new type of active dust sensor. This paper reports on the R&D conducted at JAXA into in-situ MMSD measurement sensors.

  10. Cost estimation for the active debris removal of multiple priority targets

    NASA Astrophysics Data System (ADS)

    Braun, Vitali; Wiedemann, Carsten; Schulz, Eugen

    The increasing number of space debris objects, especially in distinct low Earth orbit (LEO) altitudes between 600 and 1000 km, leads to an increase in the potential collision risk between the objects and threatens active satellites in that region. Several recent studies show that active debris removal (ADR) has to be performed in order to prevent a collisional cascading effect, also known as the Kessler syndrome. In order to stabilize the population growth in the critical LEO region, a removal of five prioritized objects per year has been recognized as a significant figure. Various proposals are addressing the technical issues for ADR missions, including the de-orbiting of objects by means of a service satellite using a chemical or an electric propulsion system. The servicer would rendezvous with a preselected target, perform a docking maneuver and then provide a de-orbit burn to transfer the target on a trajectory where it re-enters the Earth’s atmosphere within a given time frame. In this paper the technical aspects are complemented by a cost estimation model, focusing on multi target missions, which are based on a service satellite capable of de-orbiting more than one target within a single mission. The cost model for ADR includes initial development cost, production cost, launch cost and operation cost as well as the modelling of the propulsion system of the servicer. Therefore, different scenarios are defined for chemical and electric propulsion systems as applied to multi target missions, based on a literature review of concepts currently being under discussion. The costs of multi target missions are compared to a scenario where only one target is removed. Also, the results allow to determine an optimum number of objects to be removed per mission and provide numbers which can be used in future studies, e.g. those related to ADR cost and benefit analyses.

  11. Optical Observation, Image-processing, and Detection of Space Debris in Geosynchronous Earth Orbit

    NASA Astrophysics Data System (ADS)

    Oda, H.; Yanagisawa, T.; Kurosaki, H.; Tagawa, M.

    2014-09-01

    We report on optical observations and an efficient detection method of space debris in the geosynchronous Earth orbit (GEO). We operate our new Australia Remote Observatory (ARO) where an 18 cm optical telescope with a charged-coupled device (CCD) camera covering a 3.14-degree field of view is used for GEO debris survey, and analyse datasets of successive CCD images using the line detection method (Yanagisawa and Nakajima 2005). In our operation, the exposure time of each CCD image is set to be 3 seconds (or 5 seconds), and the time interval of CCD shutter open is about 4.7 seconds (or 6.7 seconds). In the line detection method, a sufficient number of sample objects are taken from each image based on their shape and intensity, which includes not only faint signals but also background noise (we take 500 sample objects from each image in this paper). Then we search a sequence of sample objects aligning in a straight line in the successive images to exclude the noise sample. We succeed in detecting faint signals (down to about 1.8 sigma of background noise) by applying the line detection method to 18 CCD images. As a result, we detected about 300 GEO objects up to magnitude of 15.5 among 5 nights data. We also calculate orbits of objects detected using the Simplified General Perturbations Satellite Orbit Model 4(SGP4), and identify the objects listed in the two-line-element (TLE) data catalogue publicly provided by the U.S. Strategic Command (USSTRATCOM). We found that a certain amount of our detections are new objects that are not contained in the catalogue. We conclude that our ARO and detection method posse a high efficiency detection of GEO objects despite the use of comparatively-inexpensive observation and analysis system. We also describe the image-processing specialized for the detection of GEO objects (not for usual astronomical objects like stars) in this paper.

  12. Space debris tracking based on fuzzy running Gaussian average adaptive particle filter track-before-detect algorithm

    NASA Astrophysics Data System (ADS)

    Torteeka, Peerapong; Gao, Peng-Qi; Shen, Ming; Guo, Xiao-Zhang; Yang, Da-Tao; Yu, Huan-Huan; Zhou, Wei-Ping; Zhao, You

    2017-02-01

    Although tracking with a passive optical telescope is a powerful technique for space debris observation, it is limited by its sensitivity to dynamic background noise. Traditionally, in the field of astronomy, static background subtraction based on a median image technique has been used to extract moving space objects prior to the tracking operation, as this is computationally efficient. The main disadvantage of this technique is that it is not robust to variable illumination conditions. In this article, we propose an approach for tracking small and dim space debris in the context of a dynamic background via one of the optical telescopes that is part of the space surveillance network project, named the Asia-Pacific ground-based Optical Space Observation System or APOSOS. The approach combines a fuzzy running Gaussian average for robust moving-object extraction with dim-target tracking using a particle-filter-based track-before-detect method. The performance of the proposed algorithm is experimentally evaluated, and the results show that the scheme achieves a satisfactory level of accuracy for space debris tracking.

  13. JUPITER AFTER THE 2009 IMPACT: HUBBLE SPACE TELESCOPE IMAGING OF THE IMPACT-GENERATED DEBRIS AND ITS TEMPORAL EVOLUTION

    SciTech Connect

    Hammel, H. B.; Wong, M. H.; Noll, K.; Clarke, J. T.; De Pater, I.; Fletcher, L. N.; Orton, G. S.; Yanamandra-Fisher, P. A.; Hueso, R.; Perez-Hoyos, S.; Sanchez-Lavega, A.; Simon-Miller, A. A.

    2010-06-01

    We report Hubble Space Telescope images of Jupiter during the aftermath of an impact by an unknown object in 2009 July. The 2009 impact-created debris field evolved more slowly than those created in 1994 by the collision of the tidally disrupted comet D/Shoemaker-Levy 9 (SL9). The slower evolution, in conjunction with the isolated nature of this single impact, permits a more detailed assessment of the altitudes and meridional motion of the debris than was possible with SL9. The color of the 2009 debris was markedly similar to that seen in 1994, thus this dark debris is likely to be Jovian material that is highly thermally processed. The 2009 impact site differed from the 1994 SL9 sites in UV morphology and contrast lifetime; both are suggestive of the impacting body being asteroidal rather than cometary. Transport of the 2009 Jovian debris as imaged by Hubble shared similarities with transport of volcanic aerosols in Earth's atmosphere after major eruptions.

  14. Jupiter After the 2009 Impact: Hubble Space Telescope Imaging of the Impact-Generated Debris and Its Temporal Evolution

    NASA Technical Reports Server (NTRS)

    Hammel, H. B.; Wong, M. H.; Clarke, J. T.; de Pater, I.; Fletcher, L. N.; Hueso, R.; Noll, K.; Orton, G. S.; Perez-Hoyos, S.; Sanchez-Lavega, A.; Simon-Miller, A. A.; Yanamandra-Fisher, P. A.

    2010-01-01

    We report Hubble Space Telescope images of Jupiter during the aftermath of an impact by an unknown object in 2009 July, The 2009 impact-created debris field evolved more slowly than those created in 1994 by the collision of the tidally disrupted comet D/Shoemaker-Levy 9 (SL9). The slower evolution, in conjunction with the isolated nature of this single impact, permits a more detailed assessment of the altitudes and meridional motion of the debris than was possible with SL9. The color of the 2009 debris was markedly similar to that seen in 1994, thus this dark debris is likely to be Jovian material that is highly thermally processed. The 2009 impact site differed from the 1994 SL9 sites in UV morphology and contrast lifetime; both are suggestive of the impacting body being asteroidal rather than cometary. Transport of the 2009 Jovian debris as imaged by Hubble shared similarities with transport of volcanic aerosols in Earth's atmosphere after major eruptions.

  15. First results of functioning of the Ukraine-China Telescope Network on Space Debris Observations

    NASA Astrophysics Data System (ADS)

    Shulga, A. V.; Kozyrev, E. S.; Sibiryakova, E. S.; Koshkin, N. I.; Blagodyr, Ya. T.; Epishev, V. P.; Blagodyr, Ya. T.; Epishev, V. P.; Mao, Yi; Li, Y.; Chen, Zh.; Tang, Zh.

    2010-05-01

    Substantial growth of space debris (SD) on the near-Earth orbits is caused by increasing launch number of the Earth artificial satellites (EAS). Leading space countries assign considerable efforts and contributions for creation, maintenance and development of space control systems (SCS). Effective work of SCS is achieved by usage of radio and optical means based both on the ground and space. Control system of space environment (CSSE) developed by National Space Agency is working in Ukraine. CSSE provides space tracking of up to 300 objects and supplies information about them to customers. Usage of optical telescopes belonging to Ukrainian research institutes and universities of Ministry of Education and Science (MES) is a prospective way to enlarge number of information sources about the SD at low orbits (less than 2500 km) for CSSE. The network of the MES telescopes has a perspective in international cooperation in particular with People's Republic of China. Ukraine and China are members of the Interagency Coordinating Committee on Space Debris; and in accordance with the resolution of the United Nations General Assembly #61/11, they are responsible for collection and distribution of data on SD. This project is directed towards creation of the first Ukrainian-Chinese network of optical telescopes for observations of the SD on the low orbits. The telescopes are equipped with the short focus objectives and sensitive TV CCD Watec cameras. A list of telescope features, such as an institution name, telescope abbreviation, focal length, f-number, field of view are given below: 1) RI NAO, FRT, 85 mm, 1.8, 4.2° x 3.2°; 2) RI AOONU, KT-50, 250 mm, 2.5, 1.5° x 1.1°; 3) AOLNU, TPL1M, 250 mm, 2.5, 1.5° x 1.1°; 4) LSRUNU, TPL1M, 85 mm, 1.5, 4.2° x3.2°; 5) ShAO, TV,85 mm, 1.8, 4.2° x 3.2°. An original method of TV observations of the low orbit objects with a static telescope was tested at all the telescopes. This method was developed and successfully used in RI NAO in

  16. The estimation of space debris distribution by Kharkiv incoherent scatter radar data

    NASA Astrophysics Data System (ADS)

    Cherniak, Iurii

    Currently in near space are a large number of artificial origin objects. Among them are operable spacecrafts and the so-called "space debris". The Kharkiv radar is a sole incoherent scatter instrument on the middle latitudes of European region. The radar located near Kharkiv, Ukraine (geographic coordinates: 49.6N, 36.3E, geomagnetic coordinates: 45.7N, 117.8E). This powerful radar facility operates with 100-m zenith parabolic antenna at 158 MHz with peak transmitted power 2.0 MW, and can registered scattering of electromagnetic waves from small volumes (about ten square centimeters at distance 500 km). During the ionosphere parameters measurement by incoherent scatter radar are received different radar signals, different by nature from the signal, incoherent scattered ionosphere plasma. The paper presents the results of data analysis of several measurements cycles. It was obtained the distribution characteristics of the radar reflections from objects on Earth orbit. There are two main peak reflections appearance intensity at distances 800 km and 1000 km. Two other peaks at the altitude of 600 km and 1400 km. It is from distance above 1700 km the number of reflections is insignificant. Based on the experimental data was constructed height-temporal distribution of reflection signals. The total analysis time was about 200 hours. The intensity of reflections and their peak distances not significantly changed during day. The average number of observed reflections per day was about 500.

  17. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray B01

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The postflight photograph was taken in the SAEF II at KSC prior to experiment removal from the LDEF. The originally white paint dot on clampblocks around the perifery of the experiment tray show the results of contamination and exposure to the space environment. The variation in color, from off-white along the top flange to different shades of brown at other locations, is attributed to variations in the atomic oxygen flux intensity. Surfaces exposed to a higher atomic oxygen flux will have less contamination due to the scrubbing or cleaning action of the atomic oxygen molecule impacting that surface. The pink and the greenish-gray tints on the two (2) debris panels are by-product of the chromic anodize coating process and not attributed to contamination and/or exposure to the space environment. The light bands along the bottom and the left and right edges of the panels are caused by lights reflecting from the tray sidewalls. The two (2) small mounds seen on the panel on the left are manufacturing defects that existed prior to flight.

  18. Cosmic dust and micro-debris measurements on the MIR space station

    NASA Astrophysics Data System (ADS)

    Mandeville, J. C.; Bariteau, M.

    2001-01-01

    During the last ten years, investigation of impact features found on material retrieved from low earth orbit, after exposure to space for a long period of time, has provided us with a great deal of data on the particulate environment, either natural or man-made. Between 1987 and 1997, several detection devices have been deployed outside the Russian MIR space station. Passive sensors are composed primarily of stacked thin metal foils (gold and aluminum). Depending on the size of the particles, they are either decelerated or fragmented upon high velocity impact. The size of holes or impact craters give information on the size or shape of the impacting particles. Samples have been retrieved for laboratory analysis. In addition, solar cells from a solar array retrieved by a Shuttle-MIR mission have been searched for impact craters. Comparison with data from LDEF, and HST provides insight in the long-term evolution of small particle population and in the debris environment of a permanently manned station. Several samples show evidence of secondary impact cratering: an attempt is made to locate the origin of primary impact sites. Some results about the possible origin of the impactors are provided by the chemical identification of particle remnants inside the craters.

  19. Ballistic limit regression analysis for Space Station Freedom meteoroid and space debris protection system

    NASA Technical Reports Server (NTRS)

    Jolly, William H.

    1992-01-01

    Relationships defining the ballistic limit of Space Station Freedom's (SSF) dual wall protection systems have been determined. These functions were regressed from empirical data found in Marshall Space Flight Center's (MSFC) Hypervelocity Impact Testing Summary (HITS) for the velocity range between three and seven kilometers per second. A stepwise linear least squares regression was used to determine the coefficients of several expressions that define a ballistic limit surface. Using statistical significance indicators and graphical comparisons to other limit curves, a final set of expressions is recommended for potential use in Probability of No Critical Flaw (PNCF) calculations for Space Station. The three equations listed below represent the mean curves for normal, 45 degree, and 65 degree obliquity ballistic limits, respectively, for a dual wall protection system consisting of a thin 6061-T6 aluminum bumper spaced 4.0 inches from a .125 inches thick 2219-T87 rear wall with multiple layer thermal insulation installed between the two walls. Normal obliquity is d(sub c) = 1.0514 v(exp 0.2983 t(sub 1)(exp 0.5228). Forty-five degree obliquity is d(sub c) = 0.8591 v(exp 0.0428) t(sub 1)(exp 0.2063). Sixty-five degree obliquity is d(sub c) = 0.2824 v(exp 0.1986) t(sub 1)(exp -0.3874). Plots of these curves are provided. A sensitivity study on the effects of using these new equations in the probability of no critical flaw analysis indicated a negligible increase in the performance of the dual wall protection system for SSF over the current baseline. The magnitude of the increase was 0.17 percent over 25 years on the MB-7 configuration run with the Bumper II program code.

  20. Space safety trajectory optimization and debris analysis using ASTOS at ESA

    NASA Astrophysics Data System (ADS)

    Ortega, Guillermo; Blasco, Ana; Weikert, Sven

    This paper describes the coupling of the space trajectory optimization software ASTOS with a tool for splashdown analysis of separated spacecraft stages and debris called DARS (Destructive Analysis for Re-entry Spacecraft), and a Risk Analysis Module called RAM. ASTOS is a main reference tool for space trajectory optimization at ESA. It is also used to compute demise and break up of rocket stages and re-entry vehicles and analyze the risk to populated areas. ASTOS software is a simulation and optimization environment to compute optimal trajectories for a variety of complex multi-phase optimal control problems. It consists of fast and powerful optimization programs, PROMIS, CAMTOS, SOCS and TROPIC, that handle large and highly discretized problems, a user interface with multiple plot capability, and GISMO, an integrated graphical iteration monitor to review the optimization process and plot the state and control histories at intermediate steps during the optimization. The optimization programs used by ASTOS use Non-Linear Programming (NLP) mathematical solvers like NPSOL, SLSQP, SLLSQP, and SNOPT. These solvers use Sequential Quadratic Programming (SQP) mathematical algorithms to find the solution of the non-linear programming problems in trajectory optimization. ASTOS comprises an extensive model library, which allows launcher and re-entry spacecraft trajectory optimization without programming work. DARS considers not only a stage break-up, but also ablation and melting of the fragments, taking diverse materials and shapes into account. The paper discusses hazard due to stage and debris impact, considering the ESA launchers and re-entry vehicles as examples. Previous approaches for the impact point calculation during trajectory optimization are presented. Subsequently the results of these approaches are compared to DARS results. This paper shows that ASTOS and the DARS and RAM extensions can calculate impact points with satisfactory accuracy and calculation time

  1. First astrometric observations with the MéO telescope in view of space debris observations

    NASA Astrophysics Data System (ADS)

    Laas-Bourez, Myrtille; Deleflie, Florent; Klotz, Alain; Albanese, Dominique; Samain, Etienne

    The MéO (for "Métrologie Optique") telescope is the Satellite and Lunar Laser Ranging dedicated telescope of Observatoire de la Côte d'Azur (France), and located at "plateau de Calern" (43,7546336886111 N 6,9215750911111 E 1323,3480 U). The telescope is pointed by an altazimu-tale mount. The motorization, with a typical velocity of 5 deg/s allows to follow LEO satellites (from an altitude of 400 kilometers), as well as MEO and GEO satellites, and the Moon. The telescope has an aperture of 1.54m. It has Nasmyth focus equipped with an EMCCD camera. The field of view, defined by the equivalent focal length and the size of the camera, is actually 3 arcmin x 3 arcmin. The paper aims at presenting two methods that we will be developing to observe LEO and MEO satellites, and give very precise astrometrical positions in view of testing the capabilities of such an instrument to track space debris. In particular, the greater diameter than the ones usually used for space debris tracking should improve the current accu-racy of the observations within in the GEO region. In the LEO region, such a diameter should allow to observe trailing satellites with a high magnitude (to be quantified). The first method is "stellar reference" -based. It consists in identifying stars on the images sky background and in using an astrometrical catalog to calibrate the passage relations between image coordinates and celestial coordinates. The main difficulty comes from the possible lack of catalogued stars on every image, to exactly identify, for each track, the original epoch and positions of stellar trails. The second method is "telescope referenced" -based. It consists in relying the opto-mechanical chain of the telescope to assign the theoretical value read in the ephemeris file as the center of the images. So, we can calibrate the field blind. The difficulty consists hence in estimating the accuracy of pointing of the telescope. The feasibility of these two methods was demonstrated in

  2. Study on the eddy current damping of the spin dynamics of space debris from the Ariane launcher upper stages

    NASA Astrophysics Data System (ADS)

    Praly, N.; Hillion, M.; Bonnal, C.; Laurent-Varin, J.; Petit, N.

    2012-07-01

    This paper addresses the topic of damping of the spin dynamics of a spatial debris orbiting around the Earth. Such debris, which can consist of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as their conducting non-ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important effect which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we present a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell's equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm's law, we show how one can obtain a partial differential equation with Neumann's boundary conditions problem that, once solved, e.g. through a finite elements method, yields the values of induced currents and braking torques. The case of a depleted upper stage of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of typical orbit of space debris are treated.

  3. Autonomous space processor for orbital debris removal and flame augmentation additives in scramjets for the National Aerospace Plane

    NASA Technical Reports Server (NTRS)

    1988-01-01

    This is a brief description of the USRA-sponsored design project at the University of Arizona. Approximately eighty-percent of this effort was spent pursuing a novel engineering concept for the in-situ processing of orbital debris utilizing resources available in low Earth orbit (LEO); the other twenty-percent was devoted to discovering innovative additives for the anchoring of supersonic combustion zones that find direct use in the Aerospace Plane that is expected to use scramjets. The seriousness of the orbital debris problem is briefly described. Available 'solutions' are outlined from the literature. The engineering design is briefly mentioned, with an emphasis on the positive aspects of the space environment that should be used in an economical approach. The aspects of operating in microgravity, vacuum, and in utilizing solar energy are mentioned. A quantitative computer animation was developed to provide design data. Three specific dead spacecraft were identified for an initial cleanup mission. The design concept, which includes a solar processor, remote arm manipulators, and the gradual processing of the debris, is also described. This is followed by a description of hardware construction. Operation and actual processing of simulated debris parts (aluminum, for now) are demonstrated in the NASP task, construction of the new design for measuring the radiation from the key free radicals (as enhanced by the additives) is described. Immediate (1988) and long-range (through 1992) future plans are shown to clearly indicate the full engineering design strategy in the light of the national space program thrusts.

  4. Power Beaming, Orbital Debris Removal, and Other Space Applications of a Ground Based Free Electron Laser

    DTIC Science & Technology

    2010-03-01

    power beaming to satellites, the removal of orbital debris , laser illumination of objects within the solar system for scientific study, and...frequency of accesses between a satellite and one or more ground stations for multiple orbital profiles. FEL illumination of orbital debris is modeled to

  5. Contrasting mass-wasting activity in two debris flow-dominated catchments of the Venosta Valley/Vinschgau (Italy): 1945-2014

    NASA Astrophysics Data System (ADS)

    Lazzarini, Simone; Brardinoni, Francesco; Draganits, Erich; Cavalli, Marco

    2015-04-01

    combines zones with colluvial transport regimes with areas in which fluvial transport prevails, whereas Plaies is essentially dominated by mass-wasting processes strongly controlled by the dynamics of the overhanging Ortler Glacier. Further, Cengles is a supply-limited system, since there the occurrence of debris flows is strongly controlled by in-channel sediment evacuation and recharge cycles that interact with the overcoming of variable hydrometeorological thresholds. In contrast, Plaies is a transport-limited resulting from the almost unlimited availability of loose, mainly glacigenic material that can be mobilized. The debris-flow activity in Plaies is strongly controlled by a combination of hydrometeorological forcing and glacier dynamics. This work is part of SedAlp (www.sedalp.eu), a project funded through the Alpine Space Programme.

  6. Assessment and Management of the Risks of Debris Hits During Space Station EVAs

    NASA Technical Reports Server (NTRS)

    Pate-Cornell, Elisabeth; Sachon, Marc

    1997-01-01

    economies of scale that could be gained from a two-branch manufacturing line (space and deep sea). Of course, the space suit would need to be space qualified. Some of the problems in adopting one of the hard suits were first that the testing had to be completed, and second that it required additional storage space. The decision was made not to develop a hard suit in time for the construction and operation of the ISS. Instead, to improve the safety of the current suit, it was decided to reinforce the soft parts of the shuttle EMU with KEVLAR linings to strengthen it against debris impacts. Test results, however, show that this advanced suit design has little effect on the penetration characteristics.

  7. LDEF (Postflight), S0001 : Space Debris Impact Experiment, Tray H05

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The Space Debris Impact Experiment con sists of a three sixteenth (3/16) of an inch thick chromic anodized aluminum panel mounted in a three (3) inch deep LDEF experiment tray. The side of the plate exposed to the LDEF interior is painted with Chemglaze Z-306 flat black paint over a Chemglaze 9924 wash primer. The panels are attached to the aluminum tray structure with non-magnetic stainless steel fasteners. The panel coatings, a thin layer of chromic anodize facing out and the Chemglaze Z-306 black paint facing the LDEF interior, contribute significantly to thermal control of the LDEF spacecraft. The postflight photograph was taken in SAEF II at the KSC after the experiment was removed from the LDEF. A brown discoloration can be seen on the upper tray flange and a lighter discol oration on the lower tray flange not covered by the experiment tray clamp blocks. Irregular shaped tan discolorations are also visible on the experiment tray sidewall with a darker stain in the right tray corners

  8. Solution of the flyby problem for large space debris at sun-synchronous orbits

    NASA Astrophysics Data System (ADS)

    Baranov, A. A.; Grishko, D. A.; Medvedevskikh, V. V.; Lapshin, V. V.

    2016-05-01

    the paper considers the flyby problem related to large space debris (LSD) objects at low earth orbits. The data on the overall dimensions of known last and upper stages of launch vehicles makes it possible to single out five compact groups of such objects from the NORAD catalog in the 500-2000 km altitude interval. The orbits of objects of each group have approximately the same inclinations. The features of the mutual distribution of the orbital planes of LSD objects in the group are shown in a portrait of the evolution of deviations of the right ascension of ascending nodes (RAAN). In the case of the first three groups (inclinations of 71°, 74°, and 81°), the straight lines of relative RAAN deviations of object orbits barely intersect each other. The fourth (83°) and fifth (97°-100°) LSD groups include a considerable number of objects whose orbits are described by straight lines (diagonals), which intersect other lines many times. The use of diagonals makes it possible to significantly reduce the temporal and total characteristic velocity expenditures required for object flybys, but it complicates determination of the flyby sequence. Diagonal solutions can be obtained using elements of graph theory. A solution to the flyby problem is presented for the case of group 5, formed of LSD objects at sun-synchronous orbits.

  9. Experimental modeling of impact of space dust and debris on flying vehicles and their components

    NASA Astrophysics Data System (ADS)

    Khristoforov, B. D.

    2011-06-01

    For modeling the space dust and debris effect on flying vehicles, an investigation of the low-velocity impact of corundum and tungsten powders, accelerated by explosion, with particle size up to 50 microns on steel and duralumin targets was carried out. Also studied was the impact of sewing needles against metal and dielectric barriers, antimeteor shield models, and duralumin containers with hard materials, gunpowder, and explosives. At impact of powders at velocities of up to 2 km/s and needles at a velocity of up to 0.5 km/s against metals, the channels arose with lengths greater than 100 and 50 diameters of a striker. At impact of needles, the containers with hard explosive materials were destroyed because of ignition of their contents, and containers with plastic explosive were punched through, and no burning occurred. The energy, released at destruction of plexiglas blocks and containers with hard materials, many times exceeded the impact energy due to release of the elastic energy stored in them.

  10. Conceptual design of an Orbital Debris Defense System

    NASA Technical Reports Server (NTRS)

    Bedillion, Erik; Blevins, Gary; Bohs, Brian; Bragg, David; Brown, Christopher; Casanova, Jose; Cribbs, David; Demko, Richard; Henry, Brian; James, Kelly

    1994-01-01

    Man made orbital debris has become a serious problem. Currently NORAD tracks over 7000 objects in orbit and less than 10 percent of these are active payloads. Common estimates are that the amount of debris will increase at a rate of 10 percent per year. Impacts of space debris with operational payloads or vehicles is a serious risk to human safety and mission success. For example, the impact of a 0.2 mm diameter paint fleck with the Space Shuttle Challenger window created a 2 mm wide by 0.6 mm deep pit. The cost to replace the window was over $50,000. A conceptual design for a Orbital Debris Defense System (ODDS) is presented which considers a wide range of debris sizes, orbits and velocities. Two vehicles were designed to collect and remove space debris. The first would attach a re-entry package to de-orbit very large debris, e.g. inactive satellites and spent upper stages that tend to break up and form small debris. This vehicle was designed to contain several re-entry packages, and be refueled and resupplied with more re-entry packages as needed. The second vehicle was designed to rendezvous with and capture debris ranging from 10 cm to 2 m. Due to tracking limitations, no technically feasible method for collecting debris below 10 cm in size could be devised; it must be accomplished through international regulations which reduce the accumulation of space debris.

  11. Conceptual design of an Orbital Debris Defense System

    NASA Astrophysics Data System (ADS)

    Bedillion, Erik; Blevins, Gary; Bohs, Brian; Bragg, David; Brown, Christopher; Casanova, Jose; Cribbs, David; Demko, Richard; Henry, Brian; James, Kelly

    1994-08-01

    Man made orbital debris has become a serious problem. Currently NORAD tracks over 7000 objects in orbit and less than 10 percent of these are active payloads. Common estimates are that the amount of debris will increase at a rate of 10 percent per year. Impacts of space debris with operational payloads or vehicles is a serious risk to human safety and mission success. For example, the impact of a 0.2 mm diameter paint fleck with the Space Shuttle Challenger window created a 2 mm wide by 0.6 mm deep pit. The cost to replace the window was over $50,000. A conceptual design for a Orbital Debris Defense System (ODDS) is presented which considers a wide range of debris sizes, orbits and velocities. Two vehicles were designed to collect and remove space debris. The first would attach a re-entry package to de-orbit very large debris, e.g. inactive satellites and spent upper stages that tend to break up and form small debris. This vehicle was designed to contain several re-entry packages, and be refueled and resupplied with more re-entry packages as needed. The second vehicle was designed to rendezvous with and capture debris ranging from 10 cm to 2 m. Due to tracking limitations, no technically feasible method for collecting debris below 10 cm in size could be devised; it must be accomplished through international regulations which reduce the accumulation of space debris.

  12. Orbital Debris: A Policy Perspective

    NASA Technical Reports Server (NTRS)

    Johnson, Nicholas L.

    2007-01-01

    A viewgraph presentation describing orbital debris from a policy perspective is shown. The contents include: 1) Voyage through near-Earth Space-animation; 2) What is Orbital Debris?; 3) Orbital Debris Detectors and Damage Potential; 4) Hubble Space Telescope; 5) Mir Space Station Solar Array; 6) International Space Station; 7) Space Shuttle; 8) Satellite Explosions; 9) Satellite Collisions; 10) NASA Orbital Debris Mitigation Guidelines; 11) International Space Station Jettison Policy; 12) Controlled/Uncontrolled Satellite Reentries; 13) Return of Space Objects; 14) Orbital Debris and U.S. National Space Policy; 15) U.S Government Policy Strategy; 16) Bankruptcy of the Iridium Satellite System; 17) Inter-Agency Space Debris Coordination Committee (IADC); 18) Orbital Debris at the United Nations; 19) Chinese Anti-satellite System; 20) Future Evolution of Satellite Population; and 21) Challenge of Orbital Debris

  13. Space station integrated wall damage and penetration damage control. Task 5: Space debris measurement, mapping and characterization system

    NASA Technical Reports Server (NTRS)

    Lempriere, B. M.

    1987-01-01

    The procedures and results of a study of a conceptual system for measuring the debris environment on the space station is discussed. The study was conducted in two phases: the first consisted of experiments aimed at evaluating location of impact through panel response data collected from acoustic emission sensors; the second analyzed the available statistical description of the environment to determine the probability of the measurement system producing useful data, and analyzed the results of the previous tests to evaluate the accuracy of location and the feasibility of extracting impactor characteristics from the panel response. The conclusions were that for one panel the system would not be exposed to any event, but that the entire Logistics Module would provide a modest amount of data. The use of sensors with higher sensitivity than those used in the tests could be advantageous. The impact location could be found with sufficient accuracy from panel response data. The waveforms of the response were shown to contain information on the impact characteristics, but the data set did not span a sufficient range of the variables necessary to evaluate the feasibility of extracting the information.

  14. Dating of ancient debris fan complexes from Lantau Island, Hong Kong: The potential relationship between landslide activity and climate change

    NASA Astrophysics Data System (ADS)

    Sewell, R. J.; Wong, J.; Wang, N.

    2013-12-01

    Debris fan complexes along mountain range fronts are known to be sensitive indicators of changes in hydrological conditions and hence may serve as a proxy for climate change. We have obtained fifty-two Optically Stimulated Luminescence (OSL) ages from debris fan complexes at five sites bordering the coastal foothills of western Lantau Island, Hong Kong. The debris fan complexes generally comprise an upper sequence of dominantly loose, gravelly colluvium and alluvium representing mainly debris flood deposits, and a lower sequence of dominantly cohesive, bouldery colluvium representing debris flow deposits. The age data from the debris fan complexes suggest three main periods of accumulation: <5,000 yr BP, 8,000 - 15,000 yr BP, and 20,000 - 40,000 yr BP. The youngest two periods appear to be dominated by debris flood deposition, whereas the older period is dominated mainly by debris flow deposition. We hypothesize that immediately prior to the Last Glacial Maximum (LGM, i.e. 21,000 yr BP), the climate was cool and dry. Upland areas were probably devoid of vegetation, providing favorable conditions for sediment production in source areas. These debris-laden source areas are likely to have been mobilized en masse during periodic intense rainstorm activity leading to accumulation of thick debris lobes along the coastal foothills. During post-LGM, the climate was warmer and more humid. Pluvial conditions predominated; forests occupied the upland source areas, leading to possibly reduced sediment yields, more frequent flash floods and deposition of debris dominated by debris flood. Compared with recent studies on the weathering and erosion history of the Pearl River Delta, our landslide age data suggest a potential link between increased landslide activity and intensification of the Asian Monsoon during the Early Holocene to Middle Holocene.

  15. Impact of the 2008 Wenchuan earthquake in China on subsequent long-term debris flow activities in the epicentral area

    NASA Astrophysics Data System (ADS)

    Zhang, S.; Zhang, L. M.

    2017-01-01

    The 2008 Wenchuan earthquake triggered the largest number of landslides among the recent strong earthquake events around the world. The loose landslide materials were retained on steep terrains and deep gullies. In the period from 2008 to 2015, numerous debris flows occurred during rainstorms along the Provincial Road 303 (PR303) near the epicentre of the earthquake, causing serious damage to the reconstructed highway. Approximately 5.24 × 106 m3 of debris-flow sediment was deposited shortly after the earthquake. This paper evaluates the evolution of the debris flows that occurred after the Wenchuan earthquake, which helps understand long-term landscape evolution and cascading effects in regions impacted by mega earthquakes. With the aid of a GIS platform combined with field investigations, we continuously tracked movements of the loose deposit materials in all the debris flow gullies along an 18 km reach of PR303 and the characteristics of the regional debris flows during several storms in the past seven years. This paper presents five important aspects of the evolution of debris flows: (1) supply of debris flow materials; (2) triggering rainfall; (3) initiation mechanisms and types of debris flows; (4) runout characteristics; and (5) elevated riverbed due to the deposited materials from the debris flows. The hillslope soil deposits gradually evolved into channel deposits and the solid materials in the channels moved towards the ravine mouth. Accordingly, channelized debris flows became dominant gradually. Due to the decreasing source material volume and changes in debris flow characteristics, the triggering rainfall tends to increase from 30 mm h- 1 in 2008 to 64 mm h- 1 in 2013, and the runout distance tends to decrease over time. The runout materials blocked the river and elevated the riverbed by at least 30 m in parts of the study area. The changes in the post-seismic debris flow activity can be categorized into three stages, i.e., active, unstable, and

  16. ON THE DETECTION AND TRACKING OF SPACE DEBRIS USING THE MURCHISON WIDEFIELD ARRAY. I. SIMULATIONS AND TEST OBSERVATIONS DEMONSTRATE FEASIBILITY

    SciTech Connect

    Tingay, S. J.; Wayth, R. B.; Hurley-Walker, N.; Kennewell, J.; Arcus, W.; Bhat, N. D. R.; Emrich, D.; Herne, D.; Kudryavtseva, N.; Lynch, M.; Ord, S. M.; Waterson, M.; Kaplan, D. L.; McKinley, B.; Briggs, F.; Bell, M.; Gaensler, B. M.; Smith, C.; Zhang, K.; Barnes, D. G.; and others

    2013-10-01

    The Murchison Widefield Array (MWA) is a new low-frequency interferometric radio telescope, operating in the benign radio frequency environment of remote Western Australia. The MWA is the low-frequency precursor to the Square Kilometre Array (SKA) and is the first of three SKA precursors to be operational, supporting a varied science mission ranging from the attempted detection of the Epoch of Reionization to the monitoring of solar flares and space weather. In this paper we explore the possibility that the MWA can be used for the purposes of Space Situational Awareness (SSA). In particular we propose that the MWA can be used as an element of a passive radar facility operating in the frequency range 87.5-108 MHz (the commercial FM broadcast band). In this scenario the MWA can be considered the receiving element in a bi-static radar configuration, with FM broadcast stations serving as non-cooperative transmitters. The FM broadcasts propagate into space, are reflected off debris in Earth orbit, and are received at the MWA. The imaging capabilities of the MWA can be used to simultaneously detect multiple pieces of space debris, image their positions on the sky as a function of time, and provide tracking data that can be used to determine orbital parameters. Such a capability would be a valuable addition to Australian and global SSA assets, in terms of southern and eastern hemispheric coverage. We provide a feasibility assessment of this proposal, based on simple calculations and electromagnetic simulations, that shows that the detection of sub-meter size debris should be possible (debris radius of >0.5 m to ∼1000 km altitude). We also present a proof-of-concept set of observations that demonstrate the feasibility of the proposal, based on the detection and tracking of the International Space Station via reflected FM broadcast signals originating in southwest Western Australia. These observations broadly validate our calculations and simulations. We discuss some

  17. On the Detection and Tracking of Space Debris Using the Murchison Widefield Array. I. Simulations and Test Observations Demonstrate Feasibility

    NASA Astrophysics Data System (ADS)

    Tingay, S. J.; Kaplan, D. L.; McKinley, B.; Briggs, F.; Wayth, R. B.; Hurley-Walker, N.; Kennewell, J.; Smith, C.; Zhang, K.; Arcus, W.; Bhat, N. D. R.; Emrich, D.; Herne, D.; Kudryavtseva, N.; Lynch, M.; Ord, S. M.; Waterson, M.; Barnes, D. G.; Bell, M.; Gaensler, B. M.; Lenc, E.; Bernardi, G.; Greenhill, L. J.; Kasper, J. C.; Bowman, J. D.; Jacobs, D.; Bunton, J. D.; deSouza, L.; Koenig, R.; Pathikulangara, J.; Stevens, J.; Cappallo, R. J.; Corey, B. E.; Kincaid, B. B.; Kratzenberg, E.; Lonsdale, C. J.; McWhirter, S. R.; Rogers, A. E. E.; Salah, J. E.; Whitney, A. R.; Deshpande, A.; Prabu, T.; Udaya Shankar, N.; Srivani, K. S.; Subrahmanyan, R.; Ewall-Wice, A.; Feng, L.; Goeke, R.; Morgan, E.; Remillard, R. A.; Williams, C. L.; Hazelton, B. J.; Morales, M. F.; Johnston-Hollitt, M.; Mitchell, D. A.; Procopio, P.; Riding, J.; Webster, R. L.; Wyithe, J. S. B.; Oberoi, D.; Roshi, A.; Sault, R. J.; Williams, A.

    2013-10-01

    The Murchison Widefield Array (MWA) is a new low-frequency interferometric radio telescope, operating in the benign radio frequency environment of remote Western Australia. The MWA is the low-frequency precursor to the Square Kilometre Array (SKA) and is the first of three SKA precursors to be operational, supporting a varied science mission ranging from the attempted detection of the Epoch of Reionization to the monitoring of solar flares and space weather. In this paper we explore the possibility that the MWA can be used for the purposes of Space Situational Awareness (SSA). In particular we propose that the MWA can be used as an element of a passive radar facility operating in the frequency range 87.5-108 MHz (the commercial FM broadcast band). In this scenario the MWA can be considered the receiving element in a bi-static radar configuration, with FM broadcast stations serving as non-cooperative transmitters. The FM broadcasts propagate into space, are reflected off debris in Earth orbit, and are received at the MWA. The imaging capabilities of the MWA can be used to simultaneously detect multiple pieces of space debris, image their positions on the sky as a function of time, and provide tracking data that can be used to determine orbital parameters. Such a capability would be a valuable addition to Australian and global SSA assets, in terms of southern and eastern hemispheric coverage. We provide a feasibility assessment of this proposal, based on simple calculations and electromagnetic simulations, that shows that the detection of sub-meter size debris should be possible (debris radius of >0.5 m to ~1000 km altitude). We also present a proof-of-concept set of observations that demonstrate the feasibility of the proposal, based on the detection and tracking of the International Space Station via reflected FM broadcast signals originating in southwest Western Australia. These observations broadly validate our calculations and simulations. We discuss some

  18. Environmental Impact Assessment and Space Activities

    NASA Astrophysics Data System (ADS)

    Viikari, L.

    these developments in way or another. In addition to national EIA regulations, there are also international agreements on EIA (i.a. the Espoo Convention) which establish their own EIA systems. In international law of outer space, environmental impact assessment is, however, not a well-established tool. The UN space treaties were drafted during a time when such consideratio ns were still not among the highest ranking items on national agendas. Therefore, these instruments fail to contain provisions regarding impact assessment, and also rest of the environmental content found in them is rather modest. The nearest equivalent to any impact assessment is contained in the Outer Space Treaty Article IX, namely the requirement of prior consultations in case of planned space activity or experiment that might cause "potentially harmful interference" with space activities of other St ates Parties. There also exist some applicable provisions on national level, such as the requirement of "formal assessment" on NASA programs of "[orbital] debris generation potential and debris mitigation options" in NASA Policy for Limiting Orbital Debris Generation (Art. 1.b). Also the national legislation of some space faring countries provides at least for the supply of some kind of information assessing the possible environmental consequences of proposed space activities. For instance, the Russian Statute on Lisencing Space Operations requires that for obtaining a license for space operation in the Russian Federation, the applicant has to supply, i.a. "documents confirming the safety of space operations (including ecological, fire and explosion safety) and the reliability of space equipment'"(Art.5.h). However, such provisions are obviously not enough for ensuring effective international regulation of the issue. The goal of this paper is to consider the usefulness of international environmental impact assessment for space activities. The space environment, however, is a unique arena in many ways

  19. Small Orbital Debris Mitigation Mission Architecture

    NASA Technical Reports Server (NTRS)

    Wiegmann, Bruce M.

    2011-01-01

    Small orbital debris in LEO (1-10 cm in size) presents a clear and present danger to operational LEO spacecraft. This debris field has dramatically increased (nearly doubled) in recent years following the Chinese ASAT Test in 2007 and the Iridium/Cosmos collision in 2009. Estimates of the number of small debris have grown to 500,000 objects after these two events; previously the population was 300,000 objects. These small, untracked debris objects (appproximately 500,000) outnumber the larger and tracked objects (appproximately 20,000) by a factor 25 to 1. Therefore, the risk of the small untracked debris objects to operational spacecraft is much greater than the risk posed by the larger and tracked LEO debris objects. A recent study by The Aerospace Corporation found that the debris environment will increase the costs of maintaining a constellation of government satellites by 5%, a constellation of large commercial satellites by 11%, and a constellation of factory built satellites by 26% from $7.6 billion to $9.57 billion. Based upon these facts, the NASA Marshall Space Flight Center (MSFC) Advanced Concepts Office (ACO) performed an architecture study on Small Orbital Debris Active Removal (SODAR) using a space-based nonweapons- class laser satellite for LEO debris removal. The goal of the SODAR study was to determine the ability of a space-based laser system to remove the most pieces of debris (1 cm to 10 cm, locations unknown), in the shortest amount of time, with the fewest number of spacecraft. The ESA developed MASTER2005 orbital debris model was used to probabilistically classify the future debris environment including impact velocity, magnitude, and directionality. The study ground rules and assumptions placed the spacecraft into a high inclination Low Earth Orbit at 800 km as an initial reference point. The architecture study results found that a spacecraft with an integrated forward-firing laser is capable of reducing the small orbital debris flux within

  20. Analysis of the Long-term Area-to-mass Ratio Variation of Space Debris

    NASA Astrophysics Data System (ADS)

    Herzog, J.; Schildknecht, T.

    2012-09-01

    The internal catalogue of space debris objects maintained by the Astronomical Institute of the University of Bern (AIUB), contains many objects with observations over long time spans. They are observed regularly with ESA's 1-meter telescopes in Tenerife (Spain), AIUB's 1-meter telescope ZIMLAT and 30-centimeter telescope ZimSMART in Zimmerwald near Bern (Switzerland). We analysed Area-to-Mass ratio (AMR) variations of 10 objects for which observations covering a time span of one year or more were available. The mean AMR values ranges from 0.02 square meter per kilogram to 30 square meter per kilogram. The class of Low Area-to-Mass ratio objects (LAMR) with AMR values lower than 1 square meter per kilogram is covered as well as the class of High Area-to-Mass ratio objects (HAMR). Although the observations were post-processed, the same approach as in the routine processing was used: observation arcs as long as possible are fit with a constant AMR value. As a consequence, the AMR values are averaged over these intervals. Also, the individual arc lengths are varying and intervals are overlapping, because observations used in previous orbit determinations are used again. If adding results in poor fits, the oldest observations are taken off until the requirements for a ``good orbit' are fulfilled. The procedure acts as a low-pass filter and only AMR value variations with low frequencies may be determined. For this small sample, the LAMR objects do not show any significant AMR value variation, the mean AMR values are constant within the estimated uncertainties. In contrast, some of the HAMR objects show significant variations of the AMR values.

  1. International Space Station environmental microbiome - microbial inventories of ISS filter debris.

    PubMed

    Venkateswaran, Kasthuri; Vaishampayan, Parag; Cisneros, Jessica; Pierson, Duane L; Rogers, Scott O; Perry, Jay

    2014-01-01

    Despite an expanding array of molecular approaches for detecting microorganisms in a given sample, rapid and robust means of assessing the differential viability of the microbial cells, as a function of phylogenetic lineage, remain elusive. A propidium monoazide (PMA) treatment coupled with downstream quantitative polymerase chain reaction (qPCR) and pyrosequencing analyses was carried out to better understand the frequency, diversity, and distribution of viable microorganisms associated with debris collected from the crew quarters of the International Space Station (ISS). The cultured bacterial counts were more in the ISS samples than cultured fungal population. The rapid molecular analyses targeted to estimate viable population exhibited 5-fold increase in bacterial (qPCR-PMA assay) and 25-fold increase in microbial (adenosine triphosphate assay) burden than the cultured bacterial population. The ribosomal nucleic acid-based identification of cultivated strains revealed the presence of only four to eight bacterial species in the ISS samples, however, the viable bacterial diversity detected by the PMA-pyrosequencing method was far more diverse (12 to 23 bacterial taxa) with the majority consisting of members of actinobacterial genera (Propionibacterium, Corynebacterium) and Staphylococcus. Sample fractions not treated with PMA (inclusive of both live and dead cells) yielded a great abundance of highly diverse bacterial (94 to 118 taxa) and fungal lineages (41 taxa). Even though deep sequencing capability of the molecular analysis widened the understanding about the microbial diversity, the cultivation assay also proved to be essential since some of the spore-forming microorganisms were detected only by the culture-based method. Presented here are the findings of the first comprehensive effort to assess the viability of microbial cells associated with ISS surfaces, and correlate differential viability with phylogenetic affiliation.

  2. A Parametric Study on Using Active Debris Removal for LEO Environment Remediation

    NASA Technical Reports Server (NTRS)

    2010-01-01

    Recent analyses on the instability of the orbital debris population in the low Earth orbit (LEO) region and the collision between Iridium 33 and Cosmos 2251 have reignited the interest in using active debris removal (ADR) to remediate the environment. There are; however, monumental technical, resource, operational, legal, and political challenges in making economically viable ADR a reality. Before a consensus on the need for ADR can be reached, a careful analysis of its effectiveness must be conducted. The goal is to demonstrate the need and feasibility of using ADR to better preserve the future environment and to guide its implementation to maximize the benefit-to-cost ratio. This paper describes a new sensitivity study on using ADR to stabilize the future LEO debris environment. The NASA long-term orbital debris evolutionary model, LEGEND, is used to quantify the effects of several key parameters, including target selection criteria/constraints and the starting epoch of ADR implementation. Additional analyses on potential ADR targets among the currently existing satellites and the benefits of collision avoidance maneuvers are also included.

  3. Interactions of the space debris environment with mega constellations-Using the example of the OneWeb constellation

    NASA Astrophysics Data System (ADS)

    Radtke, Jonas; Kebschull, Christopher; Stoll, Enrico

    2017-02-01

    Recently, several announcements have been published to deploy satellite constellations into Low Earth Orbit (LEO) containing several hundred to thousands of rather small sized objects. The purpose of these constellations is to provide a worldwide internet coverage, even to the remotest areas. Examples of these mega-constellations are one from SpaceX, which is announced to comprise of about 4000 satellites, the Norwegian STEAM network, which is told to contain 4257 satellites, and the OneWeb constellation, which forms one of the smaller constellations with 720 satellites. As example constellation, OneWeb has been chosen. From all announced constellation, OneWeb by far delivered most information, both in regards to constellation design and their plans to encounter space debris issues, which is the reason why it has been chosen for these analyses. In this paper, at first an overview of the planned OneWeb constellation setup is given. From this description, a mission life-cycle is deduced, splitting the complete orbital lifetime of the satellites into four phases. Following, using ESA-MASTER, for each of the mission phases the flux on both single constellations satellites and the complete constellation are performed and the collision probabilities are derived. The focus in this analysis is set on catastrophic collisions. This analysis is then varied parametrically for different operational altitudes of the constellation as well as different lifetimes with different assumptions for the success of post mission disposal (PMD). Following the to-be-expected mean number of collision avoidance manoeuvres during all active mission phases is performed using ARES from ESA's DRAMA tool suite. The same variations as during the flux analysis are considered. Lastly the characteristics of hypothetical OneWeb satellite fragmentation clouds, calculated using the NASA Breakup model, are described and the impact of collision clouds from OneWeb satellites on the constellation itself is

  4. Holocene activity of an alpine debris-flow catchment: does climate control erosion rate variability?

    NASA Astrophysics Data System (ADS)

    Savi, S.; Norton, K. P.; Brardinoni, F.; Akçar, N.; Kubik, P.; Picotti, V.; Schlunegger, F.

    2012-12-01

    The Zielbach catchment is located in the central-eastern Italian Alps. It covers an area of ca. 40 km2 and is characterized by fluvial sediment transport along the main drainage basin, and by the supply of sediment through debris flows, derived from a ca. 10 km2 tributary catchment. A debris-flow database demonstrates that nowadays this latter tributary dominates the sediment budget of the entire Zielbach. In this study, we analyze modern and paleo-erosion rates of the catchment through the application of the cosmogenic nuclides technique. For modern erosion rate, samples of river-born sand were taken from the main river and tributaries along the entire drainage system, while paleo-erosion rates are calculated thanks to cores' samples, which were collected on the alluvial fan and which were likewise dated based on 14C measurements of organic matter. Results obtained from the modern drainage system reveal the spatial erosion rate variability that characterizes the catchment nowadays (values ranging from 2.6 to 0.15 mm/yr). This spatial pattern is characterized by a generally increasing trend of 10Be values where hillslope contributions predominate and by a decreasing concentration trend where sediment has been supplied by debris flows. Results obtained from the cores allow the reconstruction of the Zielbach Holocene evolution and the assignment of the climate role on the temporal erosion rate variability (values ranging between 21 and 0.43 mm/yr). 14C concentrations of organic material collected from the core material indicate a lowermost age of 10'000 yr at ca. 35 m depth. The sedimentary fabric of the deposits indicates that the fan is built up by alternation of alluvial and debris-flow deposits, where the latter ones dominate in volumes. The stratigraphic architecture also infers that alluvial deposits correspond to periods of low activity of the debris-flow catchment. Most important, however, paleo-erosion rates indicate a decreasing trend for the debris

  5. A regional reconstruction of debris-flow activity in the Northern Calcareous Alps, Austria

    NASA Astrophysics Data System (ADS)

    Procter, Emily; Bollschweiler, Michelle; Stoffel, Markus; Neumann, Mathias

    2011-09-01

    Dendrogeomorphic dating of historical debris-flow events is a highly valuable tool for improving historical records in the field of natural hazard management. Previous dendrogeomorphic investigations generally have focused on case studies of single torrents; however, regional investigations may offer a more accurate reconstruction of regional patterns of activity and therefore may have an advantage over individual cases. The aim of the study is to provide a regional reconstruction of debris-flow events for a site in the Northern Calcareous Alps of western Austria (Gamperdonatal, Vorarlberg) and to document spatial and temporal morphological changes in individual and neighboring torrents. Analysis of 442 trees (268 Pinus mugo ssp. uncinata, 164 Picea abies, and 10 Abies alba) allowed identification of 579 growth disturbances corresponding to 63 debris-flow events since A.D. 1839. The majority of growth disturbances were in the form of growth suppression or release (76%) owing to the nature of both the deposited material and the process characteristics. Regional patterns of event frequency indicated a paucity of activity in the early to mid-twentieth century and increased activity since A.D. 1948, whereby large events were followed by subsequent years of continued activity of smaller magnitude. Patterns of frequency could be attributed primarily to spatiotemporal changes in channel morphology, but may also be reflective of changes in transport conditions within the valley. This study provides the first regional investigation in the Austrian Alps and contributes to the documentation of tree responses to geomorphic disturbances in calcareous material.

  6. Canadian space robotic activities

    NASA Astrophysics Data System (ADS)

    Sallaberger, Christian; Space Plan Task Force, Canadian Space Agency

    The Canadian Space Agency has chosen space robotics as one of its key niche areas, and is currently preparing to deliver the first flight elements for the main robotic system of the international space station. The Mobile Servicing System (MSS) is the Canadian contribution to the international space station. It consists of three main elements. The Space Station Remote Manipulator System (SSRMS) is a 7-metre, 7-dof, robotic arm. The Special Purpose Dextrous Manipulator (SPDM), a smaller 2-metre, 7-dof, robotic arm can be used independently, or attached to the end of the SSRMS. The Mobile Base System (MBS) will be used as a support platform and will also provide power and data links for both the SSRMS and the SPDM. A Space Vision System (SVS) has been tested on Shuttle flights, and is being further developed to enhance the autonomous capabilities of the MSS. The CSA also has a Strategic Technologies in Automation and Robotics Program which is developing new technologies to fulfill future robotic space mission needs. This program is currently developing in industry technological capabilities in the areas of automation of operations, autonomous robotics, vision systems, trajectory planning and object avoidance, tactile and proximity sensors, and ground control of space robots. Within the CSA, a robotic testbed and several research programs are also advancing technologies such as haptic devices, control via head-mounted displays, predictive and preview displays, and the dynamic characterization of robotic arms. Canada is also now developing its next Long Term Space Plan. In this context, a planetary exploration program is being considered, which would utilize Canadian space robotic technologies in this new arena.

  7. Diversity and Activity of Communities Inhabiting Plastic Debris in the North Pacific Gyre.

    PubMed

    Bryant, Jessica A; Clemente, Tara M; Viviani, Donn A; Fong, Allison A; Thomas, Kimberley A; Kemp, Paul; Karl, David M; White, Angelicque E; DeLong, Edward F

    2016-01-01

    Marine plastic debris has become a significant concern in ocean ecosystems worldwide. Little is known, however, about its influence on microbial community structure and function. In 2008, we surveyed microbial communities and metabolic activities in seawater and on plastic on an oceanographic expedition through the "great Pacific garbage patch." The concentration of plastic particles in surface seawater within different size classes (2 to 5 mm and >5 mm) ranged from 0.35 to 3.7 particles m(-3) across sampling stations. These densities and the particle size distribution were consistent with previous values reported in the North Pacific Ocean. Net community oxygen production (NCP = gross primary production - community respiration) on plastic debris was positive and so net autotrophic, whereas NCP in bulk seawater was close to zero. Scanning electron microscopy and metagenomic sequencing of plastic-attached communities revealed the dominance of a few metazoan taxa and a diverse assemblage of photoautotrophic and heterotrophic protists and bacteria. Bryozoa, Cyanobacteria, Alphaproteobacteria, and Bacteroidetes dominated all plastic particles, regardless of particle size. Bacteria inhabiting plastic were taxonomically distinct from the surrounding picoplankton and appeared well adapted to a surface-associated lifestyle. Genes with significantly higher abundances among plastic-attached bacteria included che genes, secretion system genes, and nifH genes, suggesting enrichment for chemotaxis, frequent cell-to-cell interactions, and nitrogen fixation. In aggregate, our findings suggest that plastic debris forms a habitat for complex microbial assemblages that have lifestyles, metabolic pathways, and biogeochemical activities that are distinct from those of free-living planktonic microbial communities. IMPORTANCE Marine plastic debris is a growing concern that has captured the general public's attention. While the negative impacts of plastic debris on oceanic macrobiota

  8. Diversity and Activity of Communities Inhabiting Plastic Debris in the North Pacific Gyre

    PubMed Central

    Bryant, Jessica A.; Clemente, Tara M.; Viviani, Donn A.; Fong, Allison A.; Thomas, Kimberley A.; Kemp, Paul; Karl, David M.; White, Angelicque E.

    2016-01-01

    ABSTRACT Marine plastic debris has become a significant concern in ocean ecosystems worldwide. Little is known, however, about its influence on microbial community structure and function. In 2008, we surveyed microbial communities and metabolic activities in seawater and on plastic on an oceanographic expedition through the “great Pacific garbage patch.” The concentration of plastic particles in surface seawater within different size classes (2 to 5 mm and >5 mm) ranged from 0.35 to 3.7 particles m−3 across sampling stations. These densities and the particle size distribution were consistent with previous values reported in the North Pacific Ocean. Net community oxygen production (NCP = gross primary production − community respiration) on plastic debris was positive and so net autotrophic, whereas NCP in bulk seawater was close to zero. Scanning electron microscopy and metagenomic sequencing of plastic-attached communities revealed the dominance of a few metazoan taxa and a diverse assemblage of photoautotrophic and heterotrophic protists and bacteria. Bryozoa, Cyanobacteria, Alphaproteobacteria, and Bacteroidetes dominated all plastic particles, regardless of particle size. Bacteria inhabiting plastic were taxonomically distinct from the surrounding picoplankton and appeared well adapted to a surface-associated lifestyle. Genes with significantly higher abundances among plastic-attached bacteria included che genes, secretion system genes, and nifH genes, suggesting enrichment for chemotaxis, frequent cell-to-cell interactions, and nitrogen fixation. In aggregate, our findings suggest that plastic debris forms a habitat for complex microbial assemblages that have lifestyles, metabolic pathways, and biogeochemical activities that are distinct from those of free-living planktonic microbial communities. IMPORTANCE Marine plastic debris is a growing concern that has captured the general public’s attention. While the negative impacts of plastic debris on

  9. Electron microscope observations of impact crater debris amongst contaminating particulates on materials surfaces exposed in space in low-Earth orbit

    NASA Technical Reports Server (NTRS)

    Murr, L. E.; Rivas, J. M.; Quinones, S.; Niou, C.-S.; Advani, A. H.; Marquez, B.

    1993-01-01

    Debris particles extracted from a small sampling region on the leading edge of the Long Duration Exposure Facility (LDEF) spacecraft have been examined by analytical transmission electron microscopy and the elemental frequency observed by energy-dispersive X-ray spectrometry and compared with upper atmosphere (Earth) particle elemental frequency and the average elemental compositions of interplanetary dust particles. A much broader elemental distribution was observed for the exposed spacecraft surface debris milieu. Numerous metal microfragment analyses, particularly aluminum and stainless steel, were compared with scanning electron microscope observations-of impact crater features, and the corresponding elemental spectra on selected LDEF aluminium tray clamps and stainless steel bolts. The compositions and melt features for these impact craters and ejecta have been shown to be consistent with microcrystalline debris fragments in the case of aluminum, and these observations suggest an ever changing debris milieu on exposed surfaces for space craft and space system materials.

  10. Orbital Debris and NASA's Measurement Program

    NASA Astrophysics Data System (ADS)

    Africano, J. L.; Stansbery, E. G.

    2002-05-01

    Since the launch of Sputnik in 1957, the number of manmade objects in orbit around the Earth has dramatically increased. The United States Space Surveillance Network (SSN) tracks and maintains orbits on over nine thousand objects down to a limiting diameter of about ten centimeters. Unfortunately, active spacecraft are only a small percentage ( ~ 7%) of this population. The rest of the population is orbital debris or ``space junk" consisting of expended rocket bodies, dead payloads, bits and pieces from satellite launches, and fragments from satellite breakups. The number of these smaller orbital debris objects increases rapidly with decreasing size. It is estimated that there are at least 130,000 orbital debris objects between one and ten centimeters in diameter. Most objects smaller than 10 centimeters go untracked! As the orbital debris population grows, the risk to other orbiting objects, most importantly manned space vehicles, of a collision with a piece of debris also grows. The kinetic energy of a solid 1 cm aluminum sphere traveling at an orbital velocity of 10 km/sec is equivalent to a 400 lb. safe traveling at 60 mph. Fortunately, the volume of space in which the orbiting population resides is large, collisions are infrequent, but they do occur. The Space Shuttle often returns to earth with its windshield pocked with small pits or craters caused by collisions with very small, sub-millimeter-size pieces of debris (paint flakes, particles from solid rocket exhaust, etc.), and micrometeoroids. To get a more complete picture of the orbital-debris environment, NASA has been using both radar and optical techniques to monitor the orbital debris environment. This paper gives an overview of the orbital debris environment and NASA's measurement program.

  11. Multibody dynamics driving GNC and system design in tethered nets for active debris removal

    NASA Astrophysics Data System (ADS)

    Benvenuto, Riccardo; Lavagna, Michèle; Salvi, Samuele

    2016-07-01

    Debris removal in Earth orbits is an urgent issue to be faced for space exploitation durability. Among different techniques, tethered-nets present appealing benefits and some open points to fix. Former and latter are discussed in the paper, supported by the exploitation of a multibody dynamics tool. With respect to other proposed capture mechanisms, tethered-net solutions are characterised by a safer capturing distance, a passive angular momentum damping effect and the highest flexibility to unknown shape, material and attitude of the target to interface with. They also allow not considering the centre of gravity alignment with thrust axis as a constraint, as it is for any rigid link solution. Furthermore, the introduction of a closing thread around the net perimeter ensures safer and more reliable grasping and holding. In the paper, a six degrees of freedom multibody dynamics simulator is presented: it was developed at Politecnico di Milano - Department of Aerospace Science and Technologies - and it is able to describe the orbital and attitude dynamics of tethered-nets systems and end-bodies during different phases, with great flexibility in dealing with different topologies and configurations. Critical phases as impact and wrapping are analysed by simulation to address the tethered-stack controllability. It is shown how the role of contact modelling is fundamental to describe the coupled dynamics: it is demonstrated, as a major novel contribution, how friction between the net and a tumbling target allows reducing its angular motion, stabilizing the system and allowing safer towing operations. Moreover, the so-called tethered space tug is analysed: after capture, the two objects, one passive and one active, are connected by the tethered-net flexible link, the motion of the system being excited by the active spacecraft thrusters. The critical modes prevention during this phase, by means of a closed-loop control synthesis is shown. Finally, the connection between

  12. An Efficient Optical Observation Ground Network is the Fundamental basis for any Space Based Debris Observation Segment

    NASA Astrophysics Data System (ADS)

    Cibin, L.; Chiarini, M.; Annoni, G.; Milani, A.; Bernardi, F.; Dimare, L.; Valsecchi, G.; Rossi, A.; Ragazzoni, R.; Salinari, P.

    2013-08-01

    A matter which is strongly debated in the SSA Community, concerns the observation of Space Debris from Space [1]. This topic has been preliminary studied by our Team for LEO, MEO and GEO orbital belts, allowing to remark a fundamental concept, residing in the fact that to be suitable to provide a functionality unavailable from ground in a cost to performance perspective, any Space Based System must operate in tight collaboration with an efficient Optical Ground Observation Network. In this work an analysis of the different functionalities which can be implemented with this approach for every orbital belt is illustrated, remarking the different achievable targets in terms of population size as a function of the observed orbits. Further, a preliminary definition of the most interesting missions scenarios, together with considerations and assessments on the observation strategy and P/L characteristics are presented.

  13. The flux of meteoroids and orbital space debris striking satellites in low earth orbit

    NASA Technical Reports Server (NTRS)

    Laurance, M. R.; Brownlee, D. E.

    1986-01-01

    Results are presented from an analysis of 331 craters in the 0.09-250 micron size range found in the solid aluminum thermal control louvers of the Solar Maximum Mission spacecraft, distinguishing between natural meteoroid impacts and those of orbital spacecraft debris. The time-averaged flux and size distribution of both particle types over the 10 to the -13th to 10 to the -7th g mass range are directly determined.

  14. Overview of the Inter Agency Debris Committee protection manual

    NASA Astrophysics Data System (ADS)

    Meshcheryakov, S. A.; Lambert, M.; Stokes, H.; Christiansen, E.; Kibe, S.

    2001-10-01

    Man's enthusiasm for exploring space has resulted in the launch of many payloads over the years, leading to the creation of a man-made orbital blanket of debris around the Earth in addition to the meteoroid hazard. Risk analysis studies have indicated space debris or meteoroids impact damages can have a wide range of effects on spacecraft. The primary objective of the Protection Manual (PM) is to capture results of interchange and cooperative activities among members of the Protection Working Group of the Interagency Space Debris Coordination Committee (IADC). The PM provides the framework that allows comparable meteoroid/orbital debris (M/OD) risk assessments between member agencies. In particular, the PM provides a standard methodology for meteoroid/debris risk assessments, a mean to cross-calibrate risk assessment tools, documentation of reliable ballistic limit equations, procedures and results used to calibrate member hypervelocity impact test facilities, and description of validation activities for hypervelocity impact simulation codes.

  15. ISIS: an In-Situ Impact Sensor for space debris monitoring

    NASA Astrophysics Data System (ADS)

    Porfilio, M.; Graziani, F.

    At the School of Aerospace Engineering of the University of Rome "La Sapienza", an In-Situ Impact Sensor system for space debris monitoring (called ISIS) has been designed and developed. The system is ready to launch and a test mission is forecasted on-board the UNISAT-2 microsatellite (foreseen launch window: July- December 2002). The device is based on a number of piezoelectric patches to be located on the external surface of a spacecraft; the system could detect both "small" particles directly impact ing on the patches and "greater" objects colliding the host satellite structure. How "small" or "great" the particle can be is to be investigated through hypervelocity impact tests and comparisons with flight data collected during on-orbit experiments. More in detail, ISIS consists of a number of couples of piezoelectric sensors, analogical boards (ABs) and a digital board (DB) hosting a microcontroller (°C); the patches of the same couple should be placed close to each other, so being exposed to same environment and disturbances. Hence, the signals from the two sensors can be subtracted in order to most easily detect small particles that eventually impacted one of the patches' surface. The ABs are devoted to amplification of the sensors signal; they receive, from the DB, the thresholds which the signals must be compared with; when a threshold is overcome, an interrupt signal is sent to the °C; the signals themselves are sent to the DB through another dedicated line. The system "brain" is a 8051 family °C; both the °C and the memory are only devoted to ISIS; in such a way, the system is quite independent on the peculiar spacecraft electronic architecture. Of course the ISIS °C must interface with the main satellite computer both to receive commands from the ground station and to transmit the collected data, so a certain amount of software must be programmed on the main spacecraft computer. ISIS will experience the first flight test on board the UNISAT-2

  16. The altitude effect on the climatic factors controlling debris flows activation: the Marderello Torrent case study

    NASA Astrophysics Data System (ADS)

    Palladino, Michela; Turconi, Laura; Savio, Gabriele; Tropeano, Domenico

    2015-04-01

    The left Cenischia valley includes some of the best known alpine basins prone to debris flow in Northwestern Italian Alps. In particular, in the Marderello catchment (6,6 km²), a left tributary of the Cenischia river, 31 important debris flood/flow events occurred during the last one hundred years. According to the chronicles of the last three centuries, events with significant volumes are on the average liable to take place every 3-4 years, whereas minor events may occur even twice per year. Due to the high frequency of activations, the site is of relevant interest for monitoring purposes. Since the early nineties, the CNR IRPI equipped the Marderello basin with meteorological monitoring devices. The rainfall monitoring network consists of four rain gauges, placed at different elevations, between 800 m a.s.l. and 2854 m a.s.l. Other meteorological data (air moisture and temperature, atmospheric pressure, wind speed and direction) are provided by three stations located at 3150, 2150 and 830 m a.s.l. The main objective of the monitoring is the investigation of the triggering conditions for debris flows initiation. In the scientific literature the prediction of debris flows is often tackled by the use of empirical methods, based on the analysis of past activation and related rainfall triggering conditions. The effectiveness of these methods strictly depends on the representativeness of the meteorological monitoring stations used to collect the data. In complex orography sites, as the Alpine catchments are, the remarkable elevation gaps between the source areas of debris flows and the rain gauges position make it difficult to identify the triggering rainfall. To attain more reliable results, the elevation effect must be considered. In fact, elevation influences the precipitation in terms of cumulative values and, as a result of the temperature gradient, it controls the nature of the precipitation (rain/snow). In the present study we use the rainfall and temperature

  17. The long-term effects of the micrometeoroid and orbital debris environments on materials used in space

    NASA Technical Reports Server (NTRS)

    Cour-Palais, Burton G.

    1989-01-01

    The long-term effects of the orbital debris and micrometeoroid environments on materials that are current candidates for use on space vehicles are discussed. In addition, the limits of laboratory testing to determine these effects are defined and the need for space-based data is delineated. The impact effects discussed are divided into primary and secondary surfaces. Primary surfaces are those that are subject to erosion, pitting, the degradation and delamination of optical coatings, perforation of atomic oxygen erosion barriers, vapor coating of optics and the production of secondary ejecta particles. Secondary surfaces are those that are affected by the result of the perforation of primary surfaces, for example, vapor deposition on electronic components and other sensitive equipment, and the production of fragments with damage potential to internal pressurized elements. The material properties and applications that are required to prevent or lessen the effects described, are defined.

  18. About possibilities of clearing near-Earth space from dangerous debris by a spaceborne laser system with an autonomous cw chemical HF laser

    SciTech Connect

    Avdeev, A V; Bashkin, A S; Katorgin, Boris I; Parfen'ev, M V

    2011-07-31

    The possibility of clearing hazardous near-Earth space debris using a spaceborne laser station with a large autonomous cw chemical HF laser is substantiated and the requirements to its characteristics (i.e., power and divergence of laser radiation, pulse duration in the repetitively pulsed regime, repetition rate and total time of laser action on space debris, necessary to remove them from the orbits of the protected spacecrafts) are determined. The possibility of launching the proposed spaceborne laser station to the orbit with the help of a 'Proton-M' carrier rocket is considered. (laser applications)

  19. Orbital debris: A technical assessment

    NASA Technical Reports Server (NTRS)

    Gleghorn, George; Asay, James; Atkinson, Dale; Flury, Walter; Johnson, Nicholas; Kessler, Donald; Knowles, Stephen; Rex, Dietrich; Toda, Susumu; Veniaminov, Stanislav

    1995-01-01

    To acquire an unbiased technical assessment of (1) the research needed to better understand the debris environment, (2) the necessity and means of protecting spacecraft against the debris environment, and (3) potential methods of reducing the future debris hazard, NASA asked the National Research Council to form an international committee to examine the orbital debris issue. The committee was asked to draw upon available data and analyses to: characterize the current debris environment, project how this environment might change in the absence of new measures to alleviate debris proliferation, examine ongoing alleviation activities, explore measures to address the problem, and develop recommendations on technical methods to address the problems of debris proliferation.

  20. Geosynchronous Large Debris Reorbiter: Challenges and Prospects

    NASA Astrophysics Data System (ADS)

    Schaub, Hanspeter; Moorer, Daniel F.

    2012-06-01

    An elegant solution is proposed to an old problem of how to remove expired or malfunctioning satellites from the geosynchronous belt. Previous "space-tug" concepts describe a scenario where one craft (the tug) docks with another (debris) and then boosts that object to a super-synchronous orbit. The most challenging aspect of these concepts is the very complex proximity operations to an aging, possibly rotating and, probably, non-cooperative satellite. Instead, the proposed method uses an elegant blend of electrostatic charge control and low-thrust propulsion to avoid any contact requirement. The Geosynchronous Large Debris Reorbiter (GLiDeR) uses active charge emission to raise its own absolute potential to 10's of kilovolts and, in addition, directs a stream of charged particles at the debris to increase its absolute potential. In a puller configuration the opposite polarity of the debris creates an attractive force between the GLiDeR and the debris. Pusher configurations are feasible as well. Next, fuel-efficient micro-thrusters are employed to gently move the reorbiter relative to the debris, and then accelerate the debris out of its geosynchronous slot and deposit it in a disposal orbit. Preliminary analysis shows that a 1000 kg debris object can be re-orbited over two-four months. During the reorbit phase the separation distance is held nominally fixed without physical contact, even if the debris is tumbling, by actively controlling the charge transfer between the reorbiter and the debris. Numerical simulations are presented illustrating the expected performance, taking into account also the solar radiation pressure.

  1. Space Shuttle Debris Impact Tool Assessment Using the Modern Design of Experiments

    NASA Technical Reports Server (NTRS)

    DeLoach, Richard; Rayos, Elonsio M.; Campbell, Charles H.; Rickman, Steven L.; Larsen, Curtis E.

    2007-01-01

    Complex computer codes are used to estimate thermal and structural reentry loads on the Shuttle Orbiter induced by ice and foam debris impact during ascent. Such debris can create cavities in the Shuttle Thermal Protection System. The sizes and shapes of these cavities are approximated to accommodate a code limitation that requires simple "shoebox" geometries to describe the cavities -- rectangular areas and planar walls that are at constant angles with respect to vertical. These approximations induce uncertainty in the code results. The Modern Design of Experiments (MDOE) has recently been applied to develop a series of resource-minimal computational experiments designed to generate low-order polynomial graduating functions to approximate the more complex underlying codes. These polynomial functions were then used to propagate cavity geometry errors to estimate the uncertainty they induce in the reentry load calculations performed by the underlying code. This paper describes a methodological study focused on evaluating the application of MDOE to future operational codes in a rapid and low-cost way to assess the effects of cavity geometry uncertainty.

  2. Development of a New Type Sensor for Micrometeoroid and Space Debris In-Situ Measurement at JAXA

    NASA Astrophysics Data System (ADS)

    Kitazawa, Y.; Sakurai, A.; Yasaka, T.; Funakoshi, K.; Hanada, T.; Matsumoto, H.

    2009-04-01

    Several sensor systems are being designed to monitor large (larger than 100 μm) hypervelocity particles in space. Because of the low spatial density of these large particles, the candidate sensor systems must have a large detection area, while the constraints of a space environment deployment require that these systems be low in mass, low in power, robust and low telemetry requirements. On the other hand importance of measurement of these large particles has been increased especially in engineering viewpoints (e.g. space system design and operations). The in-situ measurement data are useful for; 1) verifications of meteoroid and debris environment models, 2) verifications of meteoroid and debris environment evolution models, 3) real time detection of unexpected events, such as explosions on an orbit (Ex. ASAT: Anti Satellite Test). JAXA has been developing a simple in-situ sensor to detect dust particles ranging from a hundred micrometers to several millimeters. Multitudes of thin, conductive strips are formed with fine pitch on a thin film of nonconductive material. A dust particle impact is detected when one or more strips are severed by the impact hole. It is simple to produce and use and requires almost no calibration as it is essentially a digital system. Features of the sensor are; 1) Simple mechanism, 2) High reliability (sensing ability), 3) Flexible configuration (easy to make a large-size sensor and no restrictions of size and/or form), 4) No need to perform many hypervelocity impact experiments (Calibration shots), 5) Measurement of change of the usable area of a sensor is possible correctly, 6) Low weight, low power and low cost, 7) Excellent extendibility for measure additional parameters (the impact location, the impact velocity and direction of the particle).

  3. Coordinated Observations of Space Debris as Optimisation Problem of Inter-Dependent Metrics

    NASA Astrophysics Data System (ADS)

    Sciotti, M.; Charlish, A.

    2013-08-01

    Optimal allocation of sensor resources is addressed in this paper in the frame of space surveillance application. Inspiration is taken from the optimal management of multi-functional sensors and netted surveillance sensors, for which the Sensor Management problem is often addressed as a Markov Decision Process. This approach allows determining the optimal decision at each discrete time instant by quantifying the expected payoff coming from the selected action. An action might be the assignment of the i -th surveillance task to the m -th sensor in the network ('tasking'), the selection of the i -th task at the k -th time slot ('scheduling'), or the activation of a specific sensor configuration for the completion of the i -th task ('resource allocation'). The common objective is the maximization of the global reward coming from the selected sequence of actions over a finite or infinite time horizon. This leads to a sequence of coordinated observations carried out by the sensor(s), which are determined statically or dynamically by the Sensor Manager. In this paper, the allocation of space surveillance resources is analysed as a management problem for sensor(s) with finite resources. The proposed allocation is driven by the operational requirements for space objects cataloguing, such as the object population coverage and the track accuracy. A sequential resource allocation strategy is formulated in order to cope with such inter-dependent, concurring performance metrics. The approach can be also extended to multiple sensors with different performance or nature. Promising results are demonstrated over a phased array radar case study.

  4. ISODEX: An entry point for developing countries into space activities

    NASA Astrophysics Data System (ADS)

    Skinner, Mark Andrew

    2015-08-01

    Several threads current in the community of international space actors have led to calls at UN COPUOS Scientific & Technical Sub-Committee meetings for enhancing the scientific information available on man-made space objects, whilst fostering international space object data sharing. Growing awareness of the problems of space debris proliferation and space traffic management, especially amongst developing countries and non-traditional space faring nations, have fueled their desires to become involved in the areas of space object tracking, utilizing relatively modest astronomical instrumentation. Additionally, several commercial satellite operators, members of the Satellite Data Association, have called for augmentation of the information available from existing catalogs. This confluence of factors has led to an international discussion, at the UN and elsewhere, of the possibility of creating a clearing-house for parties willing to share data on space objects, with a working title of the “International Space Object Data Exchange” (ISODEX). We discuss the ideas behind this concept, how it might be implemented, and it might enhance the public’s knowledge of space activities, as well as providing an entry point into space for developing countries.

  5. Evidence for enhanced debris flow activity in the Northern Calcareous Alps since the 1980s (Plansee, Austria)

    NASA Astrophysics Data System (ADS)

    Dietrich, Andreas; Krautblatter, Michael

    2016-04-01

    From 1950 to 2011 almost 80.000 people lost their lives through the occurrence of debris flow events (Dowling and Santi, 2014). Debris flows occur in all alpine regions due to intensive rainstorms and mobilisable loose debris. Due to their susceptible lithology, the Northern Calcareous Alps are affected by a double digit number of major hazard events per year. Some authors hypothesised a relation between an increasing frequency of heavy rainstorms and an increasing occurrence of landslides in general (Beniston and Douglas, 1996) and debris flows in special (Pelfini and Santilli, 2008), but yet there is only limited evidence. The Plansee catchment in the Ammergauer Alps consists of intensely jointed Upper Triassic Hauptdolomit lithology and therefore shows extreme debris flow activity. To investigate this activity in the last decades, the temporal and spatial development of eight active debris flow fans is examined with GIS and field mapping. The annual rates since the late 1940s are inferred accurately by using aerial photos from 1947, 1952, 1971, 1979, 1987, 2000 and 2010. These rates are compared to the mean Holocene/Lateglacial debris flow volume derived from the most prominent cone. The contact with the underlying till is revealed by electrical resistivity tomography (ERT). It shows that the mean annual debris flow volume has increased there by a factor of 10 from 1947-1952 (0.23 ± 0.07 10³m³/yr) to 1987-2000 (2.41 ± 0.66 10³m³/yr). A similar trend can be seen on all eight fans: mean post-1980 rates exceed pre-1980 rates by a factor of more than three. This increasing debris flow activity coincides with an enhanced rainstorm (def. 35 mm/d) frequency recorded at the nearest meteorological station. Since 1921 the frequency of heavy rainstorms has increased there on average by 10% per decade. Recent debris flow rates are also 2-3 times higher compared to mean Holocene/Lateglacial rates. Furthermore, we state a strong correlation between the non

  6. Vulnerability of Space Station Freedom Modules: A Study of the Effects of Module Perforation on Crew and Equipment. Volume 2; Analytical Modeling of Internal Debris Cloud Effects

    NASA Technical Reports Server (NTRS)

    Schonberg, William P.; Davenport, Quint

    1995-01-01

    In this part of the report, a first-principles based model is developed to predict the overpressure and temperature effects of a perforating orbital debris particle impact within a pressurized habitable module. While the effects of a perforating debris particles on crew and equipment can be severe, only a limited number of empirical studies focusing on space vehicles have been performed to date. Traditionally, crew loss or incapacitation due to a perforating impact has primarily been of interest to military organizations and as such have focused on military vehicles and systems. The module wall considered in this study is initially assumed to be a standard Whippletype dual-wall system in which the outer wall protects the module and its inhabitants by disrupting impacting particles. The model is developed in a way such that it sequentially characterizes the phenomena comprising the impact event, including the initial impact, the creation and motion of a debris cloud within the dual-wall system, the impact of the debris cloud on the inner wall, the creation and motion of the debris cloud that enters the module interior, and the effects of the debris cloud within the module on module pressure and temperature levels. This is accomplished through the application of elementary shock physics and thermodynamic theory.

  7. Space weather activities in Europe

    NASA Astrophysics Data System (ADS)

    Wimmer-Schweingruber, R. F.

    The Sun has long been understood as a source of energy for mankind. Only in the more modern times has it also been seen as a source of disturbances in the space environment of the Earth, but also of the other planets and the heliosphere. Space weather research had an early start in Europe with investigations of Birkeland, Fitzgerald and Lodge, ultimately leading to an understanding of geomagnetic storms and their relation to the Sun. Today, European space weather activities range from the study of the Sun, through the inner heliosphere, to the magnetosphere, ionosphere, atmosphere, down to ground level effects. We will give an overview of European space weather activities and focus on the chain of events from Sun to Earth.

  8. Selection of a Propulsion System for Jason-CS in Order to Fulfil Space Debris Mitigation Requirements for ESA Project

    NASA Astrophysics Data System (ADS)

    Barthen, Bjoern; Beck, Jan; Duske, Norbert; Francis, Richard; Koeble, Klaus-Peter

    2013-08-01

    For two decades, the mission Topex-Poseidon and its successor mission Jason/Ocean Surface Topography Mission provide satellite data for the analysis of sea topography, wave heights and wind speeds. For the continuation of service mission Jason-CS, ESA's choice to rely on the CryoSat-2 platform design permits re-use of a well established product and proven processes. An industrial consortium led by Astrium GmbH has built the satellite CryoSat-2 which for over three years successfully provides altimeter measurements of the polar ice cap thickness evolutions. This platform is perfectly suited for accommodation of the Jason-CS instruments. Unlike CryoSat-2, Jason-CS is required to perform a post-mission disposal according to the Requirements for Space Debris Mitigation for ESA Projects. This paper discusses different technologies in terms of efficiency, feasibility and accommodation, aiming at minimizing necessary spacecraft design modifications.

  9. Severe Impingement of Lumbar Disc Replacements Increases the Functional Biological Activity of Polyethylene Wear Debris

    PubMed Central

    Baxter, Ryan M.; MacDonald, Daniel W.; Kurtz, Steven M.; Steinbeck, Marla J.

    2013-01-01

    Background: Wear, oxidation, and particularly rim impingement damage of ultra-high molecular weight polyethylene total disc replacement components have been observed following surgical revision. However, neither in vitro testing nor retrieval-based evidence has shown the effect(s) of impingement on the characteristics of polyethylene wear debris. Thus, we sought to determine (1) differences in polyethylene particle size, shape, number, or biological activity that correspond to mild or severe rim impingement and (2) in an analysis of all total disc replacements, regardless of impingement classification, whether there are correlations between the extent of regional damage and the characteristics of polyethylene wear debris. Methods: The extent of dome and rim damage was characterized for eleven retrieved polyethylene cores obtained at revision surgery after an average duration of implantation of 9.7 years (range, 4.6 to 16.1 years). Polyethylene wear debris was isolated from periprosthetic tissues with use of nitric acid and was imaged with use of environmental scanning electron microscopy. Subsequently, particle size, shape, number, biological activity, and chronic inflammation scores were determined. Results: Grouping of particles by size ranges that represented high biological relevance (<0.1 to 1-μm particles), intermediate biological relevance (1 to 10-μm particles), and low biological relevance (>10-μm particles) revealed an increased volume fraction of particles in the <0.1 to 1-μm and 1 to 10-μm size ranges in the mild-impingement cohort as compared with the severe-impingement cohort. The increased volume fractions resulted in a higher specific biological activity per unit particle volume in the mild-impingement cohort than in the severe-impingement cohort. However, functional biological activity, which is normalized by particle volume (mm3/g of tissue), was significantly higher in the severe-impingement cohort. This increase was due to a larger volume

  10. Orbital debris and near-Earth environmental management: A chronology

    NASA Technical Reports Server (NTRS)

    Portree, David S. F.; Loftus, Joseph P., Jr.

    1993-01-01

    This chronology covers the 32-year history of orbital debris and near-Earth environmental concerns. It tracks near-Earth environmental hazard creation, research, observation, experimentation, management, mitigation, protection, and policy-making, with emphasis on the orbital debris problem. Included are the Project West Ford experiments; Soviet ASAT tests and U.S. Delta upper stage explosions; the Ariane V16 explosion, U.N. treaties pertinent to near-Earth environmental problems, the PARCS tests; space nuclear power issues, the SPS/orbital debris link; Space Shuttle and space station orbital debris issues; the Solwind ASAT test; milestones in theory and modeling the Cosmos 954, Salyut 7, and Skylab reentries; the orbital debris/meteoroid research link; detection system development; orbital debris shielding development; popular culture and orbital debris; Solar Max results; LDEF results; orbital debris issues peculiar to geosynchronous orbit, including reboost policies and the stable plane; seminal papers, reports, and studies; the increasing effects of space activities on astronomy; and growing international awareness of the near-Earth environment.

  11. Orbital debris and near-Earth environmental management: A chronology

    NASA Astrophysics Data System (ADS)

    Portree, David S. F.; Loftus, Joseph P., Jr.

    1993-12-01

    This chronology covers the 32-year history of orbital debris and near-Earth environmental concerns. It tracks near-Earth environmental hazard creation, research, observation, experimentation, management, mitigation, protection, and policy-making, with emphasis on the orbital debris problem. Included are the Project West Ford experiments; Soviet ASAT tests and U.S. Delta upper stage explosions; the Ariane V16 explosion, U.N. treaties pertinent to near-Earth environmental problems, the PARCS tests; space nuclear power issues, the SPS/orbital debris link; Space Shuttle and space station orbital debris issues; the Solwind ASAT test; milestones in theory and modeling the Cosmos 954, Salyut 7, and Skylab reentries; the orbital debris/meteoroid research link; detection system development; orbital debris shielding development; popular culture and orbital debris; Solar Max results; LDEF results; orbital debris issues peculiar to geosynchronous orbit, including reboost policies and the stable plane; seminal papers, reports, and studies; the increasing effects of space activities on astronomy; and growing international awareness of the near-Earth environment.

  12. In Situ Measurement Activities at the Nasa Orbital Debris Program Office

    NASA Technical Reports Server (NTRS)

    Liou, J.-C.; Burchell, M.; Corsaro, R.; Drolshagen, G.; Giovane, F.; Pisacane, V.; Stansbery, E.

    2009-01-01

    The NASA Orbital Debris Program Office has been involved in the development of several particle impact instruments since 2003. The main objective of this development is to eventually conduct in situ measurements to better characterize the small (millimeter or smaller) orbital debris and micrometeoroid populations in the near-Earth environment. In addition, the Office also supports similar instrument development to define the micrometeoroid and lunar secondary ejecta environment for future lunar exploration activities. The instruments include impact acoustic sensors, resistive grid sensors, fiber optic displacement sensors, and impact ionization sensors. They rely on different mechanisms and detection principles to identify particle impacts. A system consisting of these different sensors will provide data that are complimentary to each other, and will provide a better description of the physical and dynamical properties (e.g., size, mass, and impact speed) of the particles in the environment. Details of several systems being considered by the Office and their intended mission objectives are summarized in this paper.

  13. Climatic controls on debris-flow activity and sediment aggradation: The Del Medio fan, NW Argentina

    NASA Astrophysics Data System (ADS)

    Savi, Sara; Schildgen, Taylor F.; Tofelde, Stefanie; Wittmann, Hella; Scherler, Dirk; Mey, Jürgen; Alonso, Ricardo N.; Strecker, Manfred R.

    2016-12-01

    In the Central Andes, several studies on alluvial terraces and valley fills have linked sediment aggradation to periods of enhanced sediment supply. However, debate continues over whether tectonic or climatic factors are most important in triggering the enhanced supply. The Del Medio catchment in the Humahuaca Basin (Eastern Cordillera, NW Argentina) is located within a transition zone between subhumid and arid climates and hosts the only active debris-flow fan within this intermontane valley. By combining 10Be analyses of boulder and sediment samples within the Del Medio catchment, with regional morphometric measurements of nearby catchments, we identify the surface processes responsible for aggradation in the Del Medio fan and their likely triggers. We find that the fan surface has been shaped by debris flows and channel avulsions during the last 400 years. Among potential tectonic, climatic, and autogenic factors that might influence deposition, our analyses point to a combination of several favorable factors that drive aggradation. These are in particular the impact of occasional abundant rainfall on steep slopes in rock types prone to failure, located in a region characterized by relatively low rainfall amounts and limited transport capacity. These characteristics are primarily associated with the climatic transition zone between the humid foreland and the arid orogen interior, which creates an imbalance between sediment supply and sediment transfer. The conditions and processes that drive aggradation in the Del Medio catchment today may provide a modern analog for the conditions and processes that drove aggradation in other nearby tributaries in the past.

  14. Debris flow evolution and the activation of an explosive hydrothermal system; Te Maari, Tongariro, New Zealand

    NASA Astrophysics Data System (ADS)

    Procter, J. N.; Cronin, S. J.; Zernack, A. V.; Lube, G.; Stewart, R. B.; Nemeth, K.; Keys, H.

    2014-10-01

    Analysis of the pre- and post-eruption topography, together with observations of the avalanche deposition sequence, yields a triggering mechanism for the 6 August 2012 eruption of Upper Te Maari. The avalanche was composed of a wedge of c. 683 000-774 000 m3 of coarse breccia, spatter and clay-rich tuffs and diamictons which slid from the western flanks of the Upper Te Maari Crater, the failure plane is considered to be a hydrothermally altered clay layer. This landslide led to a pressure drop of up to 0.5 MPa, enough to generate an explosive eruption from the hydrothermal system below, which had been activated over the months earlier by additional heat and gas from a shallow intrusion. The landslide transformed after c. 700 m into a clay-rich cohesive debris flow, eroding soils from steep, narrow stretches of channel, before depositing on intermediate broad flatter reaches. After each erosive reach, the debris flow contained greater clay and mud contents and became more mobile. At c. 2 km flow distance, however, the unsaturated flow stopped, due to a lack of excess pore pressure. This volume controlled flow deposited thick, steep sided lobes behind an outer levee, accreting inward and upward to form a series of curved surface ridges.

  15. Debris Flow Architecture and Processes in Offshore Trinidad: Implications for basin fill in tectonically active margins

    NASA Astrophysics Data System (ADS)

    Moscardelli, L.; Wood, L.; Mann, P.

    2004-12-01

    The eastern continental margin of Trinidad is situated along the tectonically active oblique converging southeastern boundary of the Caribbean and South American plates and proximal to the Orinoco Delta. Factors that have contributed to gravitational instabilities in the shelf edge include high sedimentation accumulation rates, high frequency sea-level fluctuations during the Quaternary, frequent earthquakes and the abundance of methane hydrate. This volatile mix of factors favor the formation of episodic gravity induced deposits that have affected thousands of square kilometers of the deep marine environment. Debris flows are the predominant type of gravity induced deposits in the area. Multiple episodes of debris flow occurrence have been identified using nearly 10,000 square kilometers of three-dimensional seismic data that cover the entire eastern margin. Units can reach up to 250 meters in thickness and occur over 100's of kilometer square areas. Maps that have been generated for the uppermost flow show significant basal scour, up to 33 meters deep generated during passage of the flow. Scours also show divergent patterns in map view indicating changes in the flow conditions. Flow scour erosional shadows around prominent seafloor mud volcanoes preserving evacuated strata on the downslope side of these obstructions. Internal architecture shows high amplitude discontinuous and chaotic seismic facies, and stacked thrust imbricates association with compressional bends in the flow path. The scale and occurrence frequency of these features suggest that they may form a significant threat to submarine installations and possibly generate tsunamigenic waves that can threaten shipping and coastal communities.

  16. De-Orbiting of Space Debris by Means of a Towering Cable and a Single Thruster Spaceship: Whiplash and Tail Wagging Effects

    NASA Astrophysics Data System (ADS)

    da Cruz Pacheco, Gabriel Felippe; Carpentier, Benjamin; Petit, Nicolas

    2013-08-01

    This papers exposes two difficulties that are likely to take place during the towing of a space debris. These effects, which could trouble de-orbitation strategies, are visible on simple simulations based on a model of coupled rigid-bodies dynamics. We name them tail wagging and whiplash effects, respectively.

  17. Frequency analysis of the non-principal-axis rotation of uniaxial space debris in circular orbit subjected to gravity-gradient torque

    NASA Astrophysics Data System (ADS)

    Lin, Hou-Yuan; Zhao, Chang-Yin; Zhang, Ming-Jiang

    2016-03-01

    The non-principal-axis rotational motion of uniaxial space debris can be decomposed into periodic motions associated with two frequencies: the polhode frequency of the space debris rotating around the symmetry axis, and the tumbling frequency of the symmetry axis rotating around the angular momentum. To determine from optical measurements the rotational motion of upper rocket stages in circular orbits subjected to gravity-gradient torque, the evolutions of these two frequencies need to be analyzed. Taking into account only the long-term changes in the long-period variables, the differential equations of the non-principal axis rotational motion of the uniaxial space debris are averaged and reduced, from which the evolutions of the polhode and tumbling frequencies are then obtained analytically. The theoretical results are verified by numerical simulations of the diffuse reflection model. The frequencies in the variation of the reflected light intensity in the simulation are analyzed using the frequency map analysis (FMA) method. Errors of these results are found to be less than 1%. Based on the theoretical expressions, the rotational state of the uniaxial space debris can be estimated in the simulation without any prior information except the orbital parameters. A series of state variables are estimated, including the ratio of the moments of inertia about the transverse axis and the symmetry axis, the instantaneous rotation velocity, the orientation of the angular momentum, and the precession cone of the symmetry axis.

  18. Long-term explosive degassing and debris flow activity at West Mata submarine volcano

    NASA Astrophysics Data System (ADS)

    Dziak, R. P.; Bohnenstiehl, D. R.; Baker, E. T.; Matsumoto, H.; Caplan-Auerbach, J.; Embley, R. W.; Merle, S. G.; Walker, S. L.; Lau, T.-K.; Chadwick, W. W.

    2015-03-01

    West Mata is a 1200 m deep submarine volcano where explosive boninite eruptions were observed in 2009. The acoustic signatures from the volcano's summit eruptive vents Hades and Prometheus were recorded with an in situ (~25 m range) hydrophone during ROV dives in May 2009 and with local (~5 km range) moored hydrophones between December 2009 and August 2011. The sensors recorded low frequency (1-40 Hz), short duration explosions consistent with magma bubble bursts from Hades, and broadband, 1-5 min duration signals associated with episodes of fragmentation degassing from Prometheus. Long-term eruptive degassing signals, recorded through May 2010, preceded a several month period of declining activity. Degassing episodes were not recorded acoustically after early 2011, although quieter effusive eruption activity may have continued. Synchronous optical measurements of turbidity made between December 2009 and April 2010 indicate that turbidity maxima resulted from occasional south flank slope failures triggered by the collapse of accumulated debris during eruption intervals.

  19. Extravehicular Mobility Unit Penetration Probability from Micrometeoroids and Orbital Debris: Revised Analytical Model and Potential Space Suit Improvements

    NASA Technical Reports Server (NTRS)

    Chase, Thomas D.; Splawn, Keith; Christiansen, Eric L.

    2007-01-01

    The NASA Extravehicular Mobility Unit (EMU) micrometeoroid and orbital debris protection ability has recently been assessed against an updated, higher threat space environment model. The new environment was analyzed in conjunction with a revised EMU solid model using a NASA computer code. Results showed that the EMU exceeds the required mathematical Probability of having No Penetrations (PNP) of any suit pressure bladder over the remaining life of the program (2,700 projected hours of 2 person spacewalks). The success probability was calculated to be 0.94, versus a requirement of >0.91, for the current spacesuit s outer protective garment. In parallel to the probability assessment, potential improvements to the current spacesuit s outer protective garment were built and impact tested. A NASA light gas gun was used to launch projectiles at test items, at speeds of approximately 7 km per second. Test results showed that substantial garment improvements could be made, with mild material enhancements and moderate assembly development. The spacesuit s PNP would improve marginally with the tested enhancements, if they were available for immediate incorporation. This paper discusses the results of the model assessment process and test program. These findings add confidence to the continued use of the existing NASA EMU during International Space Station (ISS) assembly and Shuttle Operations. They provide a viable avenue for improved hypervelocity impact protection for the EMU, or for future space suits.

  20. Drainage basin morphometry controls on the active depositional area of debris flow fans

    NASA Astrophysics Data System (ADS)

    Mihir, Monika; Wasklewicz, Thad; Malamud, Bruce

    2015-04-01

    A majority of the research on understanding the connection between alluvial fans and drainage basins to date has focused on coarse-scale relations between total fan area and drainage basin area. Here we take a new approach where we assess relationships between active fan depositional area and drainage basin morphometry using 52 debris flow fans (32 from the White Mountains and 20 from the Inyo Mountains) on the eastern side of Owens Valley, California, USA. The boundaries for fans, drainage basin and active depositional areas were delineated from 10m digital elevation models and 1 m aerial photographs. We examined the relationships between the normalised active depositional area of the fan (Afad/Af, where Afad is the fan active depositional area and Af the entire fan area) and the following four variables for drainage basin: (i) area (Adb), (ii) total stream length (Ls), (iii) relief (BHH), (iv) roughness (R). We find a statistically significant (r2 > 0.40) inverse power-law relationship between recent sediment contribution to the fan and drainage basin area (Afad/Af = 0.29Adb-0.167) drainage network length (Afad/Af = 0.39Ls-0.161) and basin relief (Afad/Af = 3.90BHH-0.401), and a statistically weak (r2 = 0.22) inverse power law with basin roughness (Afad/Af = 0.32R0.5441). Drainage basin size combined with other morphometric variables may largely determine efficiency in sediment transport and delivery to the fan surface. A large proportion of the total fan area of smaller fans are flooded by debris flow indicating less sediment storage in the drainage basins and greater efficiency in sediment delivery. The findings signify the importance of coarse-scale relationships to both long- and short-term fan evolution.

  1. Extravehicular activity space suit interoperability

    NASA Astrophysics Data System (ADS)

    Skoog, A. Ingemar; McBarron, James W.; Severin, Guy I.

    1995-10-01

    The European Agency (ESA) and the Russian Space Agency (RKA) are jointly developing a new space suit system for improved extravehicular activity (EVA) capabilities in support of the MIR Space Station Programme, the EVA Suit 2000. Recent national policy agreements between the U.S. and Russia on planned cooperations in manned space also include joint extravehicular activity (EVA). With an increased number of space suit systems and a higher operational frequency towards the end of this century an improved interoperability for both routine and emergency operations is of eminent importance. It is thus timely to report the current status of ongoing work on international EVA interoperability being conducted by the Committee on EVA Protocols and Operations of the International Academy of Astronautics initialed in 1991. This paper summarises the current EVA interoperability issues to be harmonised and presents quantified vehicle interface requirements for the current U.S. Shuttle EMU and Russian MIR Orlan DMA and the new European/Russian EVA Suit 2000 extravehicular systems. Major critical/incompatible interfaces for suits/mothercraft of different combinations arc discussed, and recommendations for standardisations given.

  2. Active debris multi-removal mission concept based on hybrid propulsion

    NASA Astrophysics Data System (ADS)

    Tadini, P.; Tancredi, U.; Grassi, M.; Anselmo, L.; Pardini, C.; Francesconi, A.; Branz, F.; Maggi, F.; Lavagna, M.; DeLuca, L. T.; Viola, N.; Chiesa, S.; Trushlyakov, V.; Shimada, T.

    2014-10-01

    During the last 40 years, the mass of the artificial objects in orbit increased quite steadily at the rate of about 145 metric tons annually, leading to about 7000 metric tons. Most of the cross-sectional area and mass (97% in low Earth orbit) is concentrated in about 4500 intact abandoned objects plus a further 1000 operational spacecraft. Analyses have shown that the most effective mitigation strategy should focus on the disposal of objects with larger cross-sectional area and mass from densely populated orbits. Recent NASA results have shown that the worldwide adoption of mitigation measures in conjunction with active yearly removal of approximately 0.2-0.5% of the abandoned objects would stabilize the debris population. Targets would have typical masses between 500 and 1000 kg in the case of spacecraft, and of more than 1000 kg for rocket upper stages. In the case of Cosmos-3M second stages, more than one object is located nearly in the same orbital plane. This provides the opportunity of multi-removal missions, more suitable for yearly removal rate and cost reduction needs. This paper deals with the feasibility study of a mission for the active removal of large abandoned objects in low Earth orbit. In particular, a mission is studied in which the removal of two Cosmos-3M second stages, that are numerous in low Earth orbit, is considered. The removal system relies on a Chaser spacecraft which performs rendezvous maneuvers with the two targets. The first Cosmos-3M stage is captured and an autonomous de-orbiting kit, carried by the Chaser, is attached to it. The de-orbiting kit includes a Hybrid Propulsion Module, which is remotely ignited to perform stage disposal and controlled reentry after Chaser separation. Then, the second Cosmos-3M stage is captured and, in this case, the primary propulsion system of the Chaser is used for the disposal of the mated configuration. Critical mission aspects and related technologies are investigated at a preliminary level. In

  3. The Space Shuttle Program Pre-Flight Meteoroid and Orbital Debris Risk/Damage Predictions and Post-Flight Damage Assessments

    NASA Technical Reports Server (NTRS)

    Levin, George M.; Christiansen, Eric L.

    1997-01-01

    The pre-flight predictions and postflight assessments carried out in relation to a series of Space Shuttle missions are reviewed, and data are presented for the meteoroid and orbital debris damage observed on the Hubble Space Telescope during the 1994 Hubble repair mission. Pre-flight collision risk analyses are carried out prior to each mission, and in the case of an unacceptable risk, the mission profile is altered until the risk is considered to be acceptable. The NASA's BUMPER code is used to compute the probability of damage from debris and meteoroid particle impacts based on the Poisson statistical model for random events. The penetration probability calculation requires information concerning the geometry of the critical systems, the penetration resistance and mission profile parameters. Following each flight, the orbiter is inspected for meteoroid and space debris damage. The emphasis is on areas such as the radiator panels, the windows and the reinforced carbon-carbon structures on the leading wing edges and on the nose cap. The contents of damage craters are analyzed using a scanning electron microscope to determine the nature and origin of the impactor. Hypervelocity impact tests are often performed to simulate the observed damage and to estimate the nature of the damaging particles. The number and type of damage observed provides information concerning the orbital debris environment.

  4. Protection of Space Vehicles from Micrometeoroid/Orbital Debris (MMOD) Damages

    NASA Technical Reports Server (NTRS)

    Barr, Stephanie

    2007-01-01

    As the environment that puts space vehicles at risk can never be eliminated, space vehicles must implement protection against the MMOD environment. In general, this protection has been implemented on a risk estimate basis, largely focused on estimates of impactor size and estimated flux. However, there is some uncertainty in applying these methods from data gathered in earth orbit to excursions outside. This paper discusses different past thresholds and processes of the past and suggests additional refinement or methods that could be used for future space endeavors.

  5. 14 CFR 417.211 - Debris analysis.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... TRANSPORTATION LICENSING LAUNCH SAFETY Flight Safety Analysis § 417.211 Debris analysis. (a) General. A flight safety analysis must include a debris analysis. For an orbital or suborbital launch, a debris analysis... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Debris analysis. 417.211 Section...

  6. 14 CFR 417.211 - Debris analysis.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... TRANSPORTATION LICENSING LAUNCH SAFETY Flight Safety Analysis § 417.211 Debris analysis. (a) General. A flight safety analysis must include a debris analysis. For an orbital or suborbital launch, a debris analysis... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Debris analysis. 417.211 Section...

  7. 14 CFR 417.211 - Debris analysis.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... TRANSPORTATION LICENSING LAUNCH SAFETY Flight Safety Analysis § 417.211 Debris analysis. (a) General. A flight safety analysis must include a debris analysis. For an orbital or suborbital launch, a debris analysis... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Debris analysis. 417.211 Section...

  8. 14 CFR 417.211 - Debris analysis.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... TRANSPORTATION LICENSING LAUNCH SAFETY Flight Safety Analysis § 417.211 Debris analysis. (a) General. A flight safety analysis must include a debris analysis. For an orbital or suborbital launch, a debris analysis... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Debris analysis. 417.211 Section...

  9. 14 CFR 417.211 - Debris analysis.