Science.gov

Sample records for 16-minute suborbital flight

  1. Liability and Insurance for Suborbital Flights

    NASA Astrophysics Data System (ADS)

    Masson-Zwaan, T.

    2012-01-01

    This paper analyzes and compares liability and liability insurance in the fields of aviation and spaceflight in order to propose solutions for a liability regime and insurance options for suborbital flights. Suborbital flights can be said to take place in the grey zone between air and space, between air law and space law, as well as between aviation insurance and space insurance. In terms of liability, the paper discusses air law and space law provisions in the fields of second and third party liability for damage to passengers and 'innocent bystanders' respectively, touching upon international treaties, national law and EU law, and on insurance to cover those risks. Although the insurance market is currently not ready to provide tailor-made products for operators of suborbital flights, it is expected to adapt rapidly once such flights will become reality. A hybrid approach will provide the best solution in the medium term.

  2. Suborbital Science Program: Dryden Flight Research Center

    NASA Technical Reports Server (NTRS)

    DelFrate, John

    2008-01-01

    This viewgraph presentation reviews the suborbital science program at NASA Dryden Flight Research Center. The Program Objectives are given in various areas: (1) Satellite Calibration and Validation (Cal/val)--Provide methods to perform the cal/val requirements for Earth Observing System satellites; (2) New Sensor Development -- Provide methods to reduce risk for new sensor concepts and algorithm development prior to committing sensors to operations; (3) Process Studies -- Facilitate the acquisition of high spatial/temporal resolution focused measurements that are required to understand small atmospheric and surface structures which generate powerful Earth system effects; and (4) Airborne Networking -- Develop disruption-tolerant networking to enable integrated multiple scale measurements of critical environmental features. Dryden supports the NASA Airborne Science Program and the nation in several elements: ER-2, G-3, DC-8, Ikhana (Predator B) & Global Hawk and Reveal. These are reviewed in detail in the presentation.

  3. Life-sciences research opportunities in commercial suborbital space flight

    NASA Astrophysics Data System (ADS)

    Shelhamer, Mark

    2014-11-01

    Commercial suborbital space flights will reach altitudes above 100 km, with 3-5 min of weightlessness bracketed by high-g launch and landing phases. The proposed frequency of these flights, and the large passenger population, present interesting opportunities for researchers in the life sciences. The characteristics of suborbital flight are between those of parabolic and orbital flights, opening up new scientific possibilities and easing the burden for obtaining access to 0g. There are several areas where these flights might be used for research in the life sciences: (1) operational research: preparation for “real” space flight, such as rehearsal of medical procedures, (2) applied research-to answer questions relevant to long-term space flight; (3) passenger health and safety-effects on passengers, relevant to screening and training; (4) basic research in physiological mechanisms-to address issues of fundamental science. We describe possible projects in each of these categories. One in particular spans several areas. Based on the anticipated suborbital flight profiles, observations from parabolic flight, and the wide range of fitness and experience levels of suborbital passengers, sensorimotor disturbances such as motion sickness and disorientation are major concerns. Protocols for pre-flight adaptation of sensorimotor responses might help to alleviate some of these problems, based on results from research in the initial flights. This would improve the passenger experience and add to the knowledge base relevant to space flight more generally.

  4. Sub-orbital flights, a starting point for space tourism

    NASA Astrophysics Data System (ADS)

    Gaubatz, William A.

    2002-07-01

    While there is a growing awareness and interest by the general public in space travel neither the market nor the infrastructure exist to make a commercial space tourism business an attractive risk venture. In addition there is much to be learned about how the general public will respond to space flights and what physiological and psychological needs must be met to ensure a pleasurable as well as adventurous experience. Sub-orbital flights offer an incremental approach to develop the market and the infrastructure, demonstrate the safety of space flight, obtain real flight information regarding the needs of general public passengers and demonstrate the profitability of space tourism. This paper will summarize some of the system, operations, and financial aspects of creating a sub-orbital space tourism business as a stepping-stone to public space travel. A sample business case will be reviewed and impacts of markets, operations and vehicle costs and lifetimes will be assessed.

  5. Towards Regulating Sub-Orbital Flights- An Uppdated EASA Approach

    NASA Astrophysics Data System (ADS)

    Marciacq, Jean-Bruno; Morier, Yves; Tomasello, Filippo; Erdelyi, Zsuzsanna; Gerhard, Michael

    2010-09-01

    The Treaty of the European Union allows for the development of common policies for all sectors of transport, including aviation, and its safety. To this end, the European legislator established in 2002 the European Aviation Safety Agency(EASA), located in Cologne, Germany, and gave it responsibility for the regulation of aviation safety, including airworthiness, air operations and Flight Crew Licensing. The Agency's remit has been since extended to Air Traffic Management(ATM) and Air Navigation Systems(ANS), as well as to Aerodromes Licensing. Annex 8 of the International Civil Aviation Organization(ICAO) to the Chicago Convention defines an aircraft as “any machine that can derive support in the atmosphere from the reactions of the air other than the reactions of the air against the earth’s surface”. Thus, Sub-orbital Aeroplanes(SoA) generating aerodynamic lift during the atmospheric part of their flight are considered to be aircraft. Therefore, their airworthiness, crews and operations are under the remit of EASA, which is currently preparing to fulfil its role in relation to civil suborbital flights, that is to certify SoAs and their operations. This paper is an update of the previous paper presented at the 3rd IAASS in Rome in October 2008 [31], presenting the approach proposed by EASA to accommodate sub-orbital flights into its regulatory system, from the perspectives of Sub-orbital Aeroplanes certification and their operation, including Air/Space Traffic Management, Flight Crew vs. Passengers Licensing, as well as Operators and Aerodromes vs. "Spaceports" licensing.

  6. Life Sciences Research and Development Opportunities During Suborbital Space Flight

    NASA Technical Reports Server (NTRS)

    Davis, Jeffrey R.

    2010-01-01

    Suborbital space platforms provide a unique opportunity for Space Life Sciences in the next few years. The opportunities include: physiological characterization of the first few minutes of space flight; evaluation of a wide-variety of medical conditions during periods of hyper and hypo-gravity through physiological monitoring; and evaluation of new biomedical and environmental health technologies under hyper and hypo-gravity conditions

  7. [Doctor, may I travel in space? Aeromedical considerations regarding commercial suborbital space flights].

    PubMed

    Haerkens, Marck H T M; Simons, Ries; Kuipers, André

    2011-01-01

    Within a few years, the first commercial operators will start flying passengers on suborbital flights to the verge of space. Medical data on the effects of space journeys on humans have mainly been provided by professional astronauts. There is very little research into the aeromedical consequences of suborbital flights for the health of untrained passengers. Low air pressure and oxygen tension can be compensated for by pressurising the spacecraft or pressure suit. Rapid changes in gravitational (G-)force pose ultimate challenges to cardiovascular adaptation mechanisms. Zero-gravity and G-force may cause motion sickness. Vibrations and noise during the flight may disturb communication between passengers and crew. In addition, the psychological impact of a suborbital flight should not be underestimated. There are currently no legal requirements available for medical examinations for commercial suborbital flights, but it seems justifiable to establish conditions for potential passengers' states of health.

  8. Neurovestibular considerations for sub-orbital space flight: A framework for future investigation.

    PubMed

    Karmali, Faisal; Shelhamer, Mark

    2010-01-01

    Commercial sub-orbital operators will soon offer the excitement of traveling to space to thousands of people. Based on previous experience in space flight and parabolic flight, sensorimotor disruptions in eye movements, postural stability, and motor coordination are likely in these travelers. Here we propose a framework for developing strategies to overcome these sensorimotor disruptions. We delineate how approaches should differ from those applied to orbital flight and between sub-orbital passengers and pilots based on differing frequency of flights and mission objectives. Sensorimotor adaptation is one strategy for overcoming disruptions; an important question is whether it occurs quickly enough to be of use during periods of reduced and enhanced gravity lasting less than five minutes. Data are presented showing that sensorimotor adaptation of the pitch vestibulo-ocular reflex during parabolic flight takes a few consecutive days of flying to overcome an initial disruption. We conclude with recommendations for operators and researchers to improve safety and comfort during sub-orbital operations. We recommend using parabolic flight as a tool for pre-adapting sub-orbital passengers, along with further research into the required quantity and timing of these pre-adaptation flights and the tasks conducted during these flights. Likewise, for sub-orbital pilots, we recommend emphasizing recency of experience.

  9. Neurovestibular Considerations for Sub-Orbital Space Flight: A Framework for Future Investigation

    PubMed Central

    Karmali, Faisal; Shelhamer, Mark

    2013-01-01

    Commercial sub-orbital operators will soon offer the excitement of traveling to space to thousands of people. Based on previous experience in space flight and parabolic flight, sensorimotor disruptions in eye movements, postural stability, and motor coordination are likely in these travelers. Here we propose a framework for developing strategies to overcome these sensorimotor disruptions. We delineate how approaches should differ from those applied to orbital flight and between sub-orbital passengers and pilots based on differing frequency of flights and mission objectives. Sensorimotor adaptation is one strategy for overcoming disruptions; an important question is whether it occurs quickly enough to be of use during periods of reduced and enhanced gravity lasting less than five minutes. Data are presented showing that sensorimotor adaptation of the pitch vestibulo-ocular reflex during parabolic flight takes a few consecutive days of flying to overcome an initial disruption. We conclude with recommendations for operators and researchers to improve safety and comfort during sub-orbital operations. We recommend using parabolic flight as a tool for pre-adapting sub-orbital passengers, along with further research into the required quantity and timing of these pre-adaptation flights and the tasks conducted during these flights. Likewise, for sub-orbital pilots, we recommend emphasizing recency of experience. PMID:20555165

  10. Results of the Second U.S. Manned Suborbital Space Flight, July 21, 1961

    NASA Technical Reports Server (NTRS)

    1961-01-01

    This document presents the results of the second United States manned suborbital space flight. The data and flight description presented form a continuation of the information provided at an open conference held under the auspices of the National Aeronautics and Space Administration, in cooperation with the National Institutes of Health and the National Academy of Sciences, at the U.S. Department of State Auditorium on June 6, 1961. The papers presented herein generally parallel the presentations of the first report and were prepared by the personnel of the NASA Manned Spacecraft Center in collaboration with personnel from other government agencies, participating industry, and universities. The second successful manned suborbital space flight on July 21, 1961, in which Astronaut Virgil I. Grissom was the pilot was another step in the progressive research, development, and training program leading to the study of man's capabilities in a space environment during manned orbital flight. Data and operational experiences gained from this flight were in agreement with and supplemented the knowledge obtained from the first suborbital flight of May 5, 1961, piloted by Astronaut Alan B. Shepard, Jr. The two recent manned suborbital flights, coupled with the unmanned research and development flights, have provided valuable engineering nd scientific data on which the program can progress. The successful active participation of the pilots, in much the same way as in the development and testing of high performance aircraft, has. greatly increased our confidence in giving man a significant role in future space flight activities. It is the purpose of this report to continue the practice of providing data to the scientific community interested in activities of this nature. Brief descriptions are presented of the Project Mercury spacecraft and flight plan. Papers are provided which parallel the presentations of data published for the first suborbital space flight. Additional

  11. NASA's Flight Opportunities Program: Matching Suborbital Research Payload Demand with Commercial Flight Supply

    NASA Astrophysics Data System (ADS)

    Mains, R.; Maclise, D.

    2012-12-01

    The Flight Opportunities Program (FOP) is designed to solicit, select and oversee the upgrade of research technology payloads to readiness status for integration onboard a range of commercial flight platforms including; parabolic aircraft, high-altitude balloons, and suborbital launch vehicles. Two key Program goals are: to identify, demonstrate and support research technology maturation of value to future NASA missions in space-like environments, and help stimulate the availability of new low-cost, frequent access to space by funding commercial flights. FOP is one of four key elements of a new suborbital endeavor that also includes: the research payload provider community, the flight service providers, and the spaceport service providers. Ongoing collaboration and coordination between them as well as within the FOP is essential, since there are 8 commercial flight providers on contract, with 5 of them now actively seeking flight payloads. The challenge of matching the readiness to fly of both payloads and flight platforms will be described and strategies for optimizing this presented. Ideally, a pipeline of payloads will be available to ensure that flight platforms can be optimally filled with compatible payloads. However, payloads need to fly soon after they are ready in order to conserve project resources and advance technologies. Several design and interface strategies will be described that can support efficient payload processing and help to optimize these matching challenges. The fundamental driver for payload proposal submission to the FOP is understandably the perceived return on investment to the research payload providers from participation. These projected benefits are most easily understood when a candidate researcher is able to review results from flight of a payload similar to what they might propose. To this end, an analysis of recent FOP research payload proposal categories will be presented along with top-level accomplishments from recent FOP

  12. Acquisition of a Biomedical Database of Acute Responses to Space Flight during Commercial Personal Suborbital Flights

    NASA Technical Reports Server (NTRS)

    Charles, John B.; Richard, Elizabeth E.

    2010-01-01

    There is currently too little reproducible data for a scientifically valid understanding of the initial responses of a diverse human population to weightlessness and other space flight factors. Astronauts on orbital space flights to date have been extremely healthy and fit, unlike the general human population. Data collection opportunities during the earliest phases of space flights to date, when the most dynamic responses may occur in response to abrupt transitions in acceleration loads, have been limited by operational restrictions on our ability to encumber the astronauts with even minimal monitoring instrumentation. The era of commercial personal suborbital space flights promises the availability of a large (perhaps hundreds per year), diverse population of potential participants with a vested interest in their own responses to space flight factors, and a number of flight providers interested in documenting and demonstrating the attractiveness and safety of the experience they are offering. Voluntary participation by even a fraction of the flying population in a uniform set of unobtrusive biomedical data collections would provide a database enabling statistical analyses of a variety of acute responses to a standardized space flight environment. This will benefit both the space life sciences discipline and the general state of human knowledge.

  13. Regulating private human suborbital flight at the international and European level: Tendencies and suggestions

    NASA Astrophysics Data System (ADS)

    Masson-Zwaan, Tanja; Moro-Aguilar, Rafael

    2013-12-01

    In the context of the FAST20XX project (Future High-Altitude High-Speed Transport) that started in 2009 under the 7th Framework Programme of the European Union (EU), the authors reexamined the legal status of private human suborbital flight, and researched whether it might be regulated as aviation or as spaceflight. International space law is ambiguous as to accommodating suborbital activities. While some provisions of the UN outer space treaties would seem to exclude them, generally there is not any explicit condition in terms of reaching orbit as a requirement for application. International air law presents equal difficulties in dealing with this activity. The classic definition of "aircraft" as contained in the Annexes to the Chicago Convention does not really encompass the kind of rocket-powered vehicles that are envisaged here. As a result, it is unclear whether the United Nations Committee on the Peaceful Uses of Outer Space (COPUOS), the International Civil Aviation Organization (ICAO), or both could be involved in an eventual international regulation of suborbital flight. In the absence of a uniform international regime, each state has the sovereign right to regulate human suborbital flights operating within its airspace. So far, two practical solutions have been realised or proposed, and will be analyzed. On the one hand, the USA granted power for regulation and licensing over private human suborbital flight to the Office of Commercial Space Transportation of the Federal Aviation Administration (FAA/AST). Subsequent regulations by the FAA have set out a series of requirements for companies that want to operate these flights, enabling a market to develop. On the other side of the Atlantic, both the European Space Agency (ESA) and a group of representatives of the European Aviation Safety Agency (EASA) of the European Union (EU) seem to rather regard this activity as aviation, potentially subject to the regulation and certification competences of EASA

  14. 14 CFR Appendix C to Part 417 - Flight Safety Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Flight Safety Analysis Methodologies and... Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown With a Wind Weighting... analysis required for the launch of an unguided suborbital launch vehicle flown with a wind...

  15. 14 CFR Appendix C to Part 417 - Flight Safety Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Flight Safety Analysis Methodologies and... Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown With a Wind Weighting... analysis required for the launch of an unguided suborbital launch vehicle flown with a wind...

  16. 14 CFR Appendix C to Part 417 - Flight Safety Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Flight Safety Analysis Methodologies and... Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown With a Wind Weighting... analysis required for the launch of an unguided suborbital launch vehicle flown with a wind...

  17. A Sub-Orbital Platform for Flight Tests of Small Space Capsules

    NASA Astrophysics Data System (ADS)

    Pereira, P. Moraes A. L., Jr.; Silva, C. R.; Villas Bôas, D. J.; Corrêa, F., Jr.; Miyoshi, J. H.; Loures da Costa, L. E.

    2002-01-01

    In the development of a small recoverable space capsule, flight tests using sub-orbital rockets are considered. For this test series, a platform for aerodynamic and thermal measurements as also for qualification tests of onboard sub-systems and equipment was specified and is actually under development. This platform, known as SARA Suborbital, is specified to withstand a sub-orbital flight with the high performance sounding rocket VS40 and to be recovered at the sea. To perform the testing program, a flight trajectory with adequate aeroballistic parameters, as for instance high velocities in dense atmosphere and average re-entry velocity, is considered. The testing program includes measurements of aerodynamic pressures and thermal characteristics, three- axis acceleration, acoustic pressure level inside the platform and vibration environment. Beside this, tests to characterise the performance of the data acquisition and transmission system, the micro-gravity environment and to qualify the recovery system will be carried out. During the return flight, the dynamics of parachutes deployment and platform water impact, as also rescue procedures will also be observed. The present article shows the concept of the platform, describes in detail the experiments, and concludes with a discussion on the flight trajectory and recovery procedure.

  18. Selection of artificial gravity by animals during suborbital rocket flights.

    PubMed

    Lange, K O; Belleville, R E; Clark, F C

    1975-06-01

    White rats selected preferred artificial gravity levels by locomotion in centrifuges consisting of two runways mounted in the nose of sounding rockets. Roll rate of the Aerobee 150A rocket was designed to produce an angular velocity of 45 r.p.m. during 5 min of free-fall, providing a gravity range range from 0.3 to 1.5 G depending on a subject's runway position. One animal was released at the high and one at the low gravity position in each flight. Animal positions were continuously recorded. Flight subjects were selected from about 100 trained animals adapted to the simulated launch environment for several months. In two flights excessive rollrates produced gravity ranges above the designed limits. In two other flights the desired range was produced. Locomotion patterns during these flights were similar. All four animals explored the entire available G-range. One rat settled at 0.4 G after 2 min; the others crossed the 1-G location in progressively narrower excursions and were near earth gravity at the end of the test period. Data were more varible than in laboratory tests above 1 G and the observation periods were necessarily few and short. Tentatively, however, the data suggest that normal earth-reared rats select earth gravity when available magnitudes include values above and below 1 B. Modification of gravity preference by prolonged exposure to higher or lower levels remains a possibility.

  19. Selection of artificial gravity by animals during suborbital rocket flights

    NASA Technical Reports Server (NTRS)

    Lange, K. O.; Belleville, R. E.; Clark, F. C.

    1975-01-01

    White rats selected preferred artificial gravity levels by locomotion in centrifuges consisting of two runways mounted in the nose of sounding rockets. Roll rate of the Aerobee 150A rocket was designed to produce an angular velocity of 45 rpm during 5 min of free-fall, providing a gravity range from 0.3 to 1.5 G depending on a subject's runway position. One animal was released at the high and one at the low gravity position in each flight. Animal positions were continuously recorded. Locomotion patterns during these flights were similar. All four animals explored the entire available G-range. One rat settled at 0.4 G after 2 min; the others crossed the 1-G location in progressively narrower excursions and were near earth gravity at the end of the test period. Tentatively, the data suggest that normal earth-reared rats select earth gravity when available magnitudes include values above and below 1 G. Modification of gravity preference by prolonged exposure to higher or lower levels remains a possibility.

  20. Development of a suborbital flight experiment for validating a satellite inertia identification method

    NASA Astrophysics Data System (ADS)

    Martinez, Gerardo; Inzunza-Ibarra, Marco; Ferrel, Ivann; Herrera, Brandi; Ma, Ou

    2011-06-01

    For three years, students at New Mexico State University have pursued flight experiments for validation of a newly developed inertia property identification algorithm. The robotics-based algorithm was developed and studied using computer simulations only. It has not been fully validated experimentally because of the difficulty to physically test full six degrees of freedom system dynamics in microgravity conditions on the ground. In the attempt to experimentally validate the algorithm, two experiments onboard NASA's C-9 microgravity flights have been performed. Although these flight experiments have been an invaluable experience, the zero-gravity environment desired to fully validate the algorithm has not yet been achieved. The full validation requires 6 DOF, a zero-gravity motion condition which is virtually inconceivable for ground-based testing or aircraft-based testing. Therefore, the student team is developing a suborbital experiment to further test the algorithm. The experiment has been scheduled to fly in the summer of 2011. This paper describes the activities of this suborbital flight project.

  1. Opportunities for research in space life sciences aboard commercial suborbital flights.

    PubMed

    Wagner, Erika B; Charles, John B; Cuttino, Charles Marsh

    2009-11-01

    The emergence of commercial suborbital spaceflight offers a wide range of new research and development opportunities for those in the space life sciences. Large numbers of diverse flyers, frequent re-flights, and flexible operations provide a fertile ground for both basic and applied science, as well as technology demonstrations. This commentary explores some of the unique features available to the space life science community and encourages engagement with commercial developers and operators during the design phase to help optimize platform designs and operations for future research.

  2. The " Daphnia" Lynx Mark I Suborbital Flight Experiment: Hardware Qualification at the Drop Tower Bremen

    NASA Astrophysics Data System (ADS)

    Knie, Miriam; Schoppmann, Kathrin; Eck, Hendrik; Ribeiro, Bernard Wolfschoon; Laforsch, Christian

    2016-06-01

    The Drop Tower Bremen, a ground-based facility enabling research under real microgravity conditions, is an excellent platform for testing new types of experimental hardware to ensure full performance when deployed in costly and rare flight opportunities such as suborbital flights. Here we describe the " Daphnia" experiment which will fly on XCOR Aerospace Lynx Mark I and our experience from the hardware tests with the catapult system at the drop tower. The aim of the " Daphnia" experiment is to obtain data on the biological performance of daphnids and predator-prey interactions in microgravity, which are important for the development of aquatic bioregenerative life support systems (BLSS). The experiment consists of two subunits: The first unit is dedicated to predator-prey interactions, where behavioural analysis should reveal if microgravity interfere with prey ( Daphnia) detection or feeding and therefore may interrupt the trophic cascade. The functioning of such an artificial food web is indispensable for a long-lasting BLSS suitable for long-duration manned space missions or Earth-based explorations to extreme habitats. The second unit is designed to investigate the impact of microgravity on gene expression and the cytoskeleton in Daphnia. Next to data collection, the real microgravity conditions at the drop tower have helped to identify the weak points of the " Daphnia" experimental hardware and lead to further improvement. Hence, the drop tower is ideal for testing new experimental hardware which is indispensable before the implementation in suborbital flights.

  3. NASA's Suborbital Missions Teach Engineering and Technology: Goddard Space Flight Center's Wallops Flight Facility

    NASA Technical Reports Server (NTRS)

    Winterton, Joyce L.

    2016-01-01

    A 50 minute-workshop based on NASA publicly available information will be conducted at the International Technology and Engineering Educator Association annual conference. Attendees will include middle and high school teachers and university teacher educators. Engineering and technology are essential to NASA's suborbital missions including sounding rockets, scientific balloon and airborne science. The attendees will learn how to include NASA information on these missions in their teaching.

  4. Reusable Suborbital Launch Vehicles: Modeling and Assessment of Global Changes Associated With High Flight Rates

    NASA Astrophysics Data System (ADS)

    Ross, M.

    2011-12-01

    Reusable Suborbital Launch Vehicles (RSLVs) are expected to play a large role in the space transport sector in coming decades, opening a new chapter in middle and upper atmospheric flight. RSLV flight rates of up to 1000 per year are forecast as early as 2025. While combustion emissions from each RSLV launch are small, less than 10 metric tons or less, the cumulative stratospheric emissions loading from RSLV flights could significantly exceed the loading from present day orbital launches. Recent GCM results suggest that black carbon (BC) emissions from hydrocarbon fueled rocket engines - including engine types planned for some RSLVs - are of particular interest because BC emitted by rockets could affect global direct radiative forcing and composition in the middle atmosphere to a much greater extent than other rocket emissions such as carbon dioxide and water. We present arguments and model results indicating that 1000 RSLV launches per year could regionally increase stratospheric BC by at least tens of percent over the background and change surface temperatures by over one degree. We also show how the new middle atmospheric measurement capabilities offered by RSLVs permit heretofore unavailable measurements of background stratospheric and mesospheric particle populations and an assessment of the buildup of RSLV exhaust particles during the time that RSLV flight rates are expected to surge (2015-2025).

  5. The Suborbital Particle Aggregation and Collision Experiment (SPACE): studying the collision behavior of submillimeter-sized dust aggregates on the suborbital rocket flight REXUS 12.

    PubMed

    Brisset, Julie; Heißelmann, Daniel; Kothe, Stefan; Weidling, René; Blum, Jürgen

    2013-09-01

    The Suborbital Particle Aggregation and Collision Experiment (SPACE) is a novel approach to study the collision properties of submillimeter-sized, highly porous dust aggregates. The experiment was designed, built, and carried out to increase our knowledge about the processes dominating the first phase of planet formation. During this phase, the growth of planetary precursors occurs by agglomeration of micrometer-sized dust grains into aggregates of at least millimeters to centimeters in size. However, the formation of larger bodies from the so-formed building blocks is not yet fully understood. Recent numerical models on dust growth lack a particular support by experimental studies in the size range of submillimeters, because these particles are predicted to collide at very gentle relative velocities of below 1 cm/s that can only be achieved in a reduced-gravity environment. The SPACE experiment investigates the collision behavior of an ensemble of silicate-dust aggregates inside several evacuated glass containers which are being agitated by a shaker to induce the desired collisions at chosen velocities. The dust aggregates are being observed by a high-speed camera, allowing for the determination of the collision properties of the protoplanetary dust analog material. The data obtained from the suborbital flight with the REXUS (Rocket Experiments for University Students) 12 rocket will be directly implemented into a state-of-the-art dust growth and collision model.

  6. The suborbital particle aggregation and collision experiment (SPACE): Studying the collision behavior of submillimeter-sized dust aggregates on the suborbital rocket flight REXUS 12

    NASA Astrophysics Data System (ADS)

    Brisset, Julie; Heißelmann, Daniel; Kothe, Stefan; Weidling, René; Blum, Jürgen

    2013-09-01

    The Suborbital Particle Aggregation and Collision Experiment (SPACE) is a novel approach to study the collision properties of submillimeter-sized, highly porous dust aggregates. The experiment was designed, built, and carried out to increase our knowledge about the processes dominating the first phase of planet formation. During this phase, the growth of planetary precursors occurs by agglomeration of micrometer-sized dust grains into aggregates of at least millimeters to centimeters in size. However, the formation of larger bodies from the so-formed building blocks is not yet fully understood. Recent numerical models on dust growth lack a particular support by experimental studies in the size range of submillimeters, because these particles are predicted to collide at very gentle relative velocities of below 1 cm/s that can only be achieved in a reduced-gravity environment. The SPACE experiment investigates the collision behavior of an ensemble of silicate-dust aggregates inside several evacuated glass containers which are being agitated by a shaker to induce the desired collisions at chosen velocities. The dust aggregates are being observed by a high-speed camera, allowing for the determination of the collision properties of the protoplanetary dust analog material. The data obtained from the suborbital flight with the REXUS (Rocket Experiments for University Students) 12 rocket will be directly implemented into a state-of-the-art dust growth and collision model.

  7. On-Board Entry Trajectory Planning Expanded to Sub-orbital Flight

    NASA Technical Reports Server (NTRS)

    Lu, Ping; Shen, Zuojun

    2003-01-01

    A methodology for on-board planning of sub-orbital entry trajectories is developed. The algorithm is able to generate in a time frame consistent with on-board environment a three-degree-of-freedom (3DOF) feasible entry trajectory, given the boundary conditions and vehicle modeling. This trajectory is then tracked by feedback guidance laws which issue guidance commands. The current trajectory planning algorithm complements the recently developed method for on-board 3DOF entry trajectory generation for orbital missions, and provides full-envelope autonomous adaptive entry guidance capability. The algorithm is validated and verified by extensive high fidelity simulations using a sub-orbital reusable launch vehicle model and difficult mission scenarios including failures and aborts.

  8. Analysis of low-density effects in suborbital flight of FAST20XX

    NASA Astrophysics Data System (ADS)

    Votta, Raffaele; Marini, Marco; Morsa, Luigi; Fels, Giorgio; Zuppardi, Gennaro; Schwanekamp, Tobias; Sippel, Martin

    2012-11-01

    The paper studies the high altitude effects to the future hypersonic/suborbital re-entry vehicle SpaceLiner developed in the framework of EC-funded FAST20XX project. Bridging functions have been developed and validated by means of DSMC calculations. The effects of rarefaction on global longitudinal aerodynamics of SpaceLiner in the range of altitude 65÷85 km have been pointed out by comparing to the aerodatabase in continuum regime conditions. DSMC computation has been done in the higher SpaceLiner altitude point confirming the bridging function results and providing heat transfer estimations.

  9. Results of the Second U.S. Manned Suborbital Space Flight, July 21, 1961

    DTIC Science & Technology

    1961-07-21

    SPACECRAFT AND FLIGHT PLAN FOR THE MERCURY -REDSTONE 4 FLIGHT .............................................................. 3 By Jercme B. Haammack... Mercury -Redstone Project Engineer, NASA Manned Spacecraft Center. 3. RESULTS OF TIlE MR-4 PREFLIGHT AND POSTFLIGHT MEDICAL EXAMI- NATION CONDUCTED ON... MERCURY -REDSTONF MISSIONS 3 AND 4 ................................................................... 23 By William K. Douglas, M.D., Astronaut Fi

  10. A fully-coupled implicit method for thermo-chemical nonequilibrium air at sub-orbital flight speeds

    NASA Technical Reports Server (NTRS)

    Park, Chul; Yoon, Seokkwan

    1989-01-01

    A CFD technique is described in which the finite-rate chemistry in thermal and chemical nonequilibrium air is fully and implicitly coupled with the fluid motion. Developed for use in the suborbital hypersonic flight speed range, the method accounts for nonequilibrium vibrational and electronic excitation and dissociation, but not ionization. The steady-state solution to the resulting system of equations is obtained by using a lower-upper factorization and symmetric Gauss-Seidel sweeping technique through Newton iteration. Inversion of the left-hand-side matrices is replaced by scalar multiplications through the use of the diagonal dominance algorithm. The code, named CENS2H (Compressible-Euler-Navier-Stokes Two-Dimensional Hypersonic), is fully vectorized and requires about 8.8 x 10 to the -5th sec per node point per iteration using a Cray X-MP computer. Converged solutions are obtained after about 2400 iterations. Sample calculations are made for a circular cylinder and a 10 percent airfoil at 5 deg angle of attack. The calculated cylinder flow field agrees with that obtained experimentally. The code predicts a 10 percent change in lift, drag, and pitching moment for the airfoil due to the thermochemical phenomena.

  11. NASA's Flight Opportunities Program

    NASA Video Gallery

    NASA's Flight Opportunities Program is facilitating low-cost access to suborbital space, where researchers can test technologies using commercially developed vehicles. Suborbital flights can quickl...

  12. Signal transduction in primary human T lymphocytes in altered gravity - results of the MASER-12 suborbital space flight mission.

    PubMed

    Tauber, Svantje; Hauschild, Swantje; Crescio, Claudia; Secchi, Christian; Paulsen, Katrin; Pantaleo, Antonella; Saba, Angela; Buttron, Isabell; Thiel, Cora Sandra; Cogoli, Augusto; Pippia, Proto; Ullrich, Oliver

    2013-05-07

    We investigated the influence of altered gravity on key proteins of T cell activation during the MASER-12 ballistic suborbital rocket mission of the European Space Agency (ESA) and the Swedish Space Cooperation (SSC) at ESRANGE Space Center (Kiruna, Sweden). We quantified components of the T cell receptor, the membrane proximal signaling, MAPK-signaling, IL-2R, histone modifications and the cytoskeleton in non-activated and in ConA/CD28-activated primary human T lymphocytes. The hypergravity phase during the launch resulted in a downregulation of the IL-2 and CD3 receptor and reduction of tyrosine phosphorylation, p44/42-MAPK phosphorylation and histone H3 acetylation, whereas LAT phosphorylation was increased. Compared to the baseline situation at the point of entry into the microgravity phase, CD3 and IL-2 receptor expression at the surface of non-activated T cells were reduced after 6 min microgravity. Importantly, p44/42-MAPK-phosphorylation was also reduced after 6 min microgravity compared to the 1g ground controls, but also in direct comparison between the in-flight μg and the 1g group. In activated T cells, the reduced CD3 and IL-2 receptor expression at the baseline situation recovered significantly during in-flight 1g conditions, but not during microgravity conditions. Beta-tubulin increased significantly after onset of microgravity until the end of the microgravity phase, but not in the in-flight 1g condition. This study suggests that key proteins of T cell signal modules are not severely disturbed in microgravity. Instead, it can be supposed that the strong T cell inhibiting signal occurs downstream from membrane proximal signaling, such as at the transcriptional level as described recently. However, the MASER-12 experiment could identify signal molecules, which are sensitive to altered gravity, and indicates that gravity is obviously not only a requirement for transcriptional processes as described before, but also for specific phosphorylation

  13. Signal transduction in primary human T lymphocytes in altered gravity – results of the MASER-12 suborbital space flight mission

    PubMed Central

    2013-01-01

    We investigated the influence of altered gravity on key proteins of T cell activation during the MASER-12 ballistic suborbital rocket mission of the European Space Agency (ESA) and the Swedish Space Cooperation (SSC) at ESRANGE Space Center (Kiruna, Sweden). We quantified components of the T cell receptor, the membrane proximal signaling, MAPK-signaling, IL-2R, histone modifications and the cytoskeleton in non-activated and in ConA/CD28-activated primary human T lymphocytes. The hypergravity phase during the launch resulted in a downregulation of the IL-2 and CD3 receptor and reduction of tyrosine phosphorylation, p44/42-MAPK phosphorylation and histone H3 acetylation, whereas LAT phosphorylation was increased. Compared to the baseline situation at the point of entry into the microgravity phase, CD3 and IL-2 receptor expression at the surface of non-activated T cells were reduced after 6 min microgravity. Importantly, p44/42-MAPK-phosphorylation was also reduced after 6 min microgravity compared to the 1g ground controls, but also in direct comparison between the in-flight μg and the 1g group. In activated T cells, the reduced CD3 and IL-2 receptor expression at the baseline situation recovered significantly during in-flight 1g conditions, but not during microgravity conditions. Beta-tubulin increased significantly after onset of microgravity until the end of the microgravity phase, but not in the in-flight 1g condition. This study suggests that key proteins of T cell signal modules are not severely disturbed in microgravity. Instead, it can be supposed that the strong T cell inhibiting signal occurs downstream from membrane proximal signaling, such as at the transcriptional level as described recently. However, the MASER-12 experiment could identify signal molecules, which are sensitive to altered gravity, and indicates that gravity is obviously not only a requirement for transcriptional processes as described before, but also for specific phosphorylation

  14. COBALT: Development of a Platform to Flight Test Lander GN&C Technologies on Suborbital Rockets

    NASA Technical Reports Server (NTRS)

    Carson, John M., III; Seubert, Carl R.; Amzajerdian, Farzin; Bergh, Chuck; Kourchians, Ara; Restrepo, Carolina I.; Villapando, Carlos Y.; O'Neal, Travis V.; Robertson, Edward A.; Pierrottet, Diego; Hines, Glenn D.; Garcia, Reuben

    2017-01-01

    The NASA COBALT Project (CoOperative Blending of Autonomous Landing Technologies) is developing and integrating new precision-landing Guidance, Navigation and Control (GN&C) technologies, along with developing a terrestrial fight-test platform for Technology Readiness Level (TRL) maturation. The current technologies include a third- generation Navigation Doppler Lidar (NDL) sensor for ultra-precise velocity and line- of-site (LOS) range measurements, and the Lander Vision System (LVS) that provides passive-optical Terrain Relative Navigation (TRN) estimates of map-relative position. The COBALT platform is self contained and includes the NDL and LVS sensors, blending filter, a custom compute element, power unit, and communication system. The platform incorporates a structural frame that has been designed to integrate with the payload frame onboard the new Masten Xodiac vertical take-o, vertical landing (VTVL) terrestrial rocket vehicle. Ground integration and testing is underway, and terrestrial fight testing onboard Xodiac is planned for 2017 with two flight campaigns: one open-loop and one closed-loop.

  15. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  16. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  17. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  18. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  19. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  20. The Suborbital Research Association: Using Suborbital Platforms for Scientific and Student Experiments

    NASA Astrophysics Data System (ADS)

    Pletser, V.; Migeotte, P. F.; Legros, J. C.; Deneyer, B.; Caron, R.

    2016-10-01

    The Suborbital Research Association (SRA), created in Brussels in June 2013, seeks to raise the awareness of the scientific community to the possibilities for scientific and technological research purposes offered by long suborbital trajectories, yielding several minutes of continuous microgravity at an attractive cost. The SRA, which is open to all forms of cooperation, has set its objectives: " to encourage, to assist, to facilitate and to promote suborbital scientific research; to give the necessary assistance, within the possibilities of the Association, to the practical realization of fundamental and applied scientific research in the suborbital environment, independently and in a complementary manner to existing structures; to organize or to participate in the organization of promotion events of scientific research in suborbital flights to the general public, the youth and the students." The first on-going project of the SRA is to organize a first scientific flight with the XCOR Lynx suborbital spaceplane in 2016 or 2017 to perform scientific and student experiments. A SRA Selection Committee evaluated 17 experiment proposals from six European countries and recommended ten experiments for this first flight: five scientific and technological experiments from European Scientists, a historical promotional experiment, and four student experiments from Belgian secondary schools. Further flights will be organised as soon as possible. The paper presents the SRA and put in context the proposed use of suborbital platforms for microgravity research. The selected experiments are further introduced.

  1. FASTRACK (TM): Parabolic and Suborbital Experiment Support Facility

    NASA Technical Reports Server (NTRS)

    Richards, Stephanie E. (Compiler); Levine, Howard G.; Romero, V.

    2016-01-01

    FASTRACK was developed by NASA Kennedy Space Center and Space Florida to provide capabilities to conduct frequent, affordable, and responsive flight opportunities for reduced gravity experiments, technology development, and hardware testing on suborbital vehicles and parabolic flights.

  2. Commercial Development Suborbital Rocket Program

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The enclosed report provides information on the sixth flight of the Consort suborbital rocket series. Consort 6 is currently scheduled for launch on February 19, 1993, with lift off at 11:00 a.m., Mountain Time. It will carry seven materials and biotechnology experiments, two accelerometer systems, a controller and battery packs in a module nearly 12 feet tall and weighing approximately 1,004 pounds. Consort 6 will reach an apogee of approximately 200 miles providing about 7 minutes of microgravity time. The entire mission, from launch to touchdown, is expected to last approximately 15 minutes. The Consort series is part of a unique suborbital rocket launch services program conducted by the Office of Advanced Concepts and Technology (OACT) in conjunction with its Centers for the Commercial Development of Space (CCDS). This service is managed through the Consortium for Materials Development in Space (CMDS), a CCDS based University of Alabama in Huntsville (UAH). at the This suborbital rocket program provides CCDS investigators with a microgravity environment to achieve commercial development objectives, or to test developmental hardware or techniques in preparation for orbital flights or additional follow-on work. Rocket and launch services for Consort 6, including use of the Starfire 1 launch vehicle, are provided by EER Systems Corporation. Integration of the payload into Starfire 1 will be handled by McDonnell Douglas Space Systems Company.

  3. The Undergraduate Student Instrument Project (USIP) - building the STEM workforce by providing exciting, multi-disciplinary, student-led suborbital flight projects.

    NASA Astrophysics Data System (ADS)

    Dingwall, B. J.

    2015-12-01

    NASA's Science Mission Directorate (SMD) recognizes that suborbital carriers play a vital role in training our country's future science and technology leaders. SMD created the Undergraduate Student Instrument Project (USIP) to offer students the opportunity to design, build, and fly instruments on NASA's unique suborbital research platforms. This paper explores the projects, the impact, and the lessons learned of USIP. USIP required undergraduate teams to design, build, and fly a scientific instrument in 18 months or less. Students were required to form collaborative multidisciplinary teams to design, develop and build their instrument. Teams quickly learned that success required skills often overlooked in an academic environment. Teams quickly learned to share technical information in a clear and concise manner that could be understood by other disciplines. The aggressive schedule required team members to hold each other accountable for progress while maintaining team unity. Unanticipated problems and technical issues led students to a deeper understanding of the need for schedule and cost reserves. Students exited the program with a far deeper understanding of project management and team dynamics. Through the process of designing and building an instrument that will enable new research transforms students from textbook learners to developers of new knowledge. The initial USIP project funded 10 undergraduate teams that flew a broad range of scientific instruments on scientific balloons, sounding rockets, commercial rockets and aircraft. Students were required to prepare for and conduct the major reviews that are an integral part of systems development. Each project conducted a Preliminary Design Review, Critical Design Review and Mission Readiness review for NASA officials and flight platform providers. By preparing and presenting their designs to technical experts, the students developed a deeper understanding of the technical and programmatic project pieces that

  4. A suborbital IMU test mission

    NASA Astrophysics Data System (ADS)

    Lawman, Adam; Straub, Jeremy; Kerlin, Scott

    2015-05-01

    This paper presents work conducted in preparation for a suborbital test flight to test an inertial measurement unit's (IMU's) ability to serve as a position determination mechanism in a GPS-denied environment. Because the IMU could potentially be used at several points during flight, it is not guaranteed that a GPS fix can be used to reset the IMU after the stresses of launch. Due to this, the specific goal of this work is to characterize whether a rocket launch disrupts the IMU-based position knowledge to the extent that it is unusable. This paper discusses preparations for a sub-orbital launch mission to this end. It include a description of the hardware and software used. A discussion of the data logging mechanism and the onboard and post-flight processing which is required to compare the GPS fixes and IMU-generated positions is also presented. Finally, the utility of an IMU capable of maintaining position awareness during launch is discussed.

  5. The New Commercial Suborbital Vehicles: An Opportunity for Scientific and Microgravity Research

    NASA Astrophysics Data System (ADS)

    Moro-Aguilar, Rafael

    2014-11-01

    As of 2013, a number of companies had announced their intention to start flying suborbital vehicles, capable of transporting people to high altitudes out of any airport or launch site, on a commercial and regular basis. According to several studies, a market for suborbital "space tourism" exists. Another very promising application of suborbital flight is scientific research. The present paper provides an overview of the potential of commercial suborbital flight for science, including microgravity research. Suborbital flight provides a much-needed intermediate-duration opportunity between research performed in Earth orbit and more affordable but shorter duration alternatives, such as drop towers and zero-g parabolic flights. Moreover, suborbital flight will be less expensive and more frequent than both orbital flight and sounding rockets, and it has the capability to fly into sub-orbit the researcher together with the payload, and thus enable on-site interaction with the experiment. In the United States, both the National Aeronautics and Space Administration (NASA) and a number of private institutions have already shown interest in conducting scientific experiments, particularly microgravity research, aboard these new platforms. Researchers who intend to participate in future suborbital flights as payload specialists will need training, given the physical challenges posed by the flight. Finally, suborbital researchers may also want to have a basic knowledge of the legal status that will apply to them as passengers of such flights.

  6. Suborbital Applications in Astronomy and Astrophysics

    NASA Technical Reports Server (NTRS)

    Unwin, Steve; Werner, Mike; Goldsmith, Paul

    2012-01-01

    Suborbital flights providing access to zero-g in a space environment - Demonstrating new technologies in a relevant environment. - Flight testing of individual elements of a constellation. - Raising the TRL of critical technologies for subsystems on future large missions High-altitude balloons (up to 10 kg payload) -Access to near-space for wavelengths not observable from the ground. -Raising the TRL of critical technologies for subsystems on future large missions. -UV Detector testing.

  7. Overview of the NASA Suborbital Program

    NASA Astrophysics Data System (ADS)

    Jones, W. Vernon

    2014-08-01

    The NASA Suborbital Program consists of Sounding Rocket and Balloon Projects managed, respectively, by the Heliophysics and Astrophysics Divisions of the Science Mission Directorate, which maintains “Program” Offices at the NASA Wallops Flight Facility. Suborbital missions have for several decades enabled investigations with significant results from relatively modest investments. Some have been competitive with orbital missions, while others have enabled orbital missions. NASA launches suborbital missions from sites established in the U.S. and around the world to meet investigators’ needs. A sea change in scientific ballooning occurred with the inauguration of 8 - 20 day flights around Antarctica in the early 1990’s. The U.S. National Science Foundation supports these circumpolar flights, which have been spectacularly successful with many investigations utilizing multiple flights of payloads that are recovered, refurbished, and reused to minimize life-cycle costs. The attainment of 25 - 32 day and 35 - 55 day flights in two and three circumnavigations, respectively, of the Antarctic continent has greatly increased expectations of scientific users. The 55-day Super-TIGER flight over Antarctica during the 2012-13 season broke the 42-day CREAM record during the 2004-05 season, as well as the 54-day super pressure balloon test flight in 2008-09. Qualification of super pressure flights to support 1000 kg science instruments for up to 100 days at 33 km have proceeded in parallel with plans to increase the altitude for less massive instruments requiring less atmospheric overburden. The nearly constant volume of super-pressure balloons allows stable altitude flights at non-polar latitudes. Long-duration flights in both polar and non-polar regions will confirm the important contributions that ballooning can make in traditional Astrophysics, Solar and Heliophysics, and Earth Science disciplines. With two comets approaching the sun in 2013-14, the Planetary Science

  8. Suborbital missions: The Joust

    NASA Technical Reports Server (NTRS)

    Ferguson, Bruce W.

    1991-01-01

    Joust 1 will carry a payload of 10 experiments. The experiments in the payload module will be mated with a service module containing accelerometers, avionics, a low gravity rate control system, and battery packs. This suborbital mission will last approximately 21 minutes, providing at least 13 minutes of microgravity time. The experiments are as follow: study into polymer membrane processes; polymer curing; plasma particle generation; automated generic bioprocessing apparatus; biomodule; thin films; materials dispersion apparatus; foam formation; electrodeposition process; and powdered materials processing.

  9. The Fastrack Suborbital Platform for Microgravity Applications

    NASA Technical Reports Server (NTRS)

    Levine, H. G.; Ball, J. E.; Shultz, D.; Odyssey, A.; Wells, H. W.; Soler, R. R.; Albino, S.; Meshberger, R. J.; Murdoch, T.

    2009-01-01

    The FASTRACK suborbital experiment platform has been developed to provide a capability for utilizing 2.5-5 minute microgravity flight opportunities anticipated from the commercial suborbital fleet (currently in development) for science investigations, technology development and hardware testing. It also provides "express rack" functionality to deliver payloads to ISS. FASTRACK fits within a 24" x 24" x 36" (61 cm x 61 cm x 91.4 cm) envelope and is capable of supporting either two single Middeck Locker Equivalents (MLE) or one double MLE configuration. Its overall mass is 300 lbs (136 kg), of which 160 lbs (72 kg) is reserved for experiments. FASTRACK operates using 28 VDC power or batteries. A support drawer located at the bottom of the structure contains all ancillary electrical equipment (including batteries, a conditioned power system and a data collection system) as well as a front panel that contains all switches (including remote cut-off), breakers and warning LEDs.

  10. Sub-orbital commercial human spaceflight and informed consent.

    PubMed

    Carminati, Maria-Vittoria; Griffith, Doug; Campbell, Mark R

    2011-02-01

    Commercial spaceflight is expected to rapidly develop in the near future. This will begin with sub-orbital missions and then progress to orbital flights. Technical informed consent of spaceflight participants is required by the commercial spaceflight operator for regulatory purposes. Additionally, though not required by regulation, the aerospace medicine professional involved in the medical screening of both spaceflight participants and crewmembers will be asked to assist operators in obtaining medical informed consent for liability purposes. The various federal and state regulations regarding informed consent for sub-orbital commercial spaceflight are evolving and are unfamiliar to most aerospace medical professionals and are reviewed and discussed.

  11. Medical certification for pilots of commercial suborbital spaceflights.

    PubMed

    2009-09-01

    The Aerospace Medical Association convened a Working Group on October 31, 2008, with the objective of preparing a position statement on medical certification for pilots of commercial suborbital flights. The discussion concerned two areas: medical standards and the content of the medical examination. The Working Group found that the current medical standards for the Federal Aviation Administration Class I certificate were reasonable for crews flying suborbital profiles. It further recommended that the medical examination include a history and physical examination as well as urinalysis, hemoglobin/hematocrit, hemoglobin A1c, and ECG.

  12. NASA's Suborbital Center of Excellence - reaching young minds and crafting the future

    NASA Astrophysics Data System (ADS)

    Cathey, H.; Hottman, S.; Hansen, K.

    The NASA Suborbital Center of Excellence is charting new territory. From an idea to promote science and engineering education and outreach, the Suborbital Center of Excellence is working toward the objective of increasing numbers of college graduates choosing a career in suborbital programs. Approaches to excite university students to want to pursue these careers through relevant and useful work experiences will be highlighted. Suborbital platforms include balloons, sounding rockets, research aircraft (manned and remotely piloted vehicles) and small satellites. Key components of this are the Suborbital Center of Excellence co-op program and the support of Engineering ``Capstone'' projects. A number of these projects and programs have been supported during the past year. Highlights of these student hands-on learning experiences will be presented. The projects have included diverse projects ranging from work on a power beaming demonstration and autonomous aircraft control logic to the development of light weight pressure vessels for balloon flights based on ULDB spin-off technology, and balloon drop sonde development. Preparing these future Scientists and Engineers involves the investment of time, energy, and resources. The Suborbital Center of Excellence is uniquely positioned to do this. Future programs and initiatives will be presented. The Suborbital Center of Excellence is evolving, meeting the needs to promote science and engineering education and outreach. Educational outreach initiatives for young children to university students will also be presented. These include hands-on experiments, demonstrations, and suborbital educational materials.

  13. 14 CFR 437.53 - Pre-flight and post-flight operations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... operations and systems in preparing a reusable suborbital rocket for flight at a launch site in the United States and returning the reusable suborbital rocket and any support equipment to a safe condition...

  14. 14 CFR 437.53 - Pre-flight and post-flight operations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... operations and systems in preparing a reusable suborbital rocket for flight at a launch site in the United States and returning the reusable suborbital rocket and any support equipment to a safe condition...

  15. 14 CFR 437.53 - Pre-flight and post-flight operations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... operations and systems in preparing a reusable suborbital rocket for flight at a launch site in the United States and returning the reusable suborbital rocket and any support equipment to a safe condition...

  16. 14 CFR 437.53 - Pre-flight and post-flight operations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... operations and systems in preparing a reusable suborbital rocket for flight at a launch site in the United States and returning the reusable suborbital rocket and any support equipment to a safe condition...

  17. 14 CFR 437.53 - Pre-flight and post-flight operations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... operations and systems in preparing a reusable suborbital rocket for flight at a launch site in the United States and returning the reusable suborbital rocket and any support equipment to a safe condition...

  18. Suborbital Research and Development Opportunities

    NASA Technical Reports Server (NTRS)

    Davis, Jeffrey R.

    2011-01-01

    This slide presentation reviews the new strategies for problem solving in the life sciences in the suborbital realm. Topics covered are: an overview of the space life sciences, the strategic initiatives that the Space Life Sciences organization engaged in, and the new business model that these initiatives were developed. Several opportunities for research are also reviewed.

  19. The Atsa Suborbital Observatory: An Observatory for a Commercial Suborbital Spacecraft

    NASA Astrophysics Data System (ADS)

    Vilas, F.; Sollitt, L. S.

    2012-12-01

    The advantages of astronomical observations made above Earth's atmosphere have long been understood: free access to spectral regions inaccessible from Earth (e.g., UV) or affected by the atmosphere's content (e.g., IR). Most robotic, space-based telescopes maintain large angular separation between the Sun and an observational target in order to avoid accidental damage to instruments from the Sun. For most astronomical targets, this possibility is easily avoided by waiting until objects are visible away from the Sun. For the Solar System objects inside Earth's orbit, this is never the case. Suborbital astronomical observations have over 50 years' history using NASA's sounding rockets and experimental space planes. Commercial suborbital spacecraft are largely expected to go to ~100 km altitude above Earth, providing a limited amount of time for astronomical observations. The unique scientific advantage to these observations is the ability to point close to the Sun: if a suborbital spacecraft accidentally turns too close to the Sun and fries an instrument, it is easy to land the spacecraft and repair the hardware for the next flight. Objects uniquely observed during the short observing window include inner-Earth asteroids, Mercury, Venus, and Sun-grazing comets. Both open-FOV and target-specific observations are possible. Despite many space probes to the inner Solar System, scientific questions remain. These include inner-Earth asteroid size and bulk density informing Solar System evolution studies and efforts to develop methods of mitigation against imminent impactors to Earth; chemistry and dynamics of Venus' atmosphere addressing physical phenomena such as greenhouse effect, atmospheric super-rotation and global resurfacing on Venus. With the Atsa Suborbital Observatory, we combine the strengths of both ground-based observatories and space-based observing to create a facility where a telescope is maintained and used interchangeably with both in-house facility

  20. The Advantages, Potentials and Safety of VTOL Suborbital Space Tourism Operations

    NASA Astrophysics Data System (ADS)

    Ridzuan Zakaria, N.; Nasrun, N.; Abu, J.; Jusoh, A.; Azim, L.; Said, A.; Ishak, S.; Rafidi Zakaria, N.

    2012-01-01

    Suborbital space tourism offers short-time zero gravity and Earth view from space to its customers, and a package that can offer the longest duration of zero- gravity and the most exciting Earth view from space to its customer can be considered a better one than the others. To increase the duration of zero gravity time involves the design and engineering of the suborbital vehicles, but to improve the view of Earth from space aboard a suborbital vehicle, involves more than just the design and engineering of the vehicle, but more on the location of where the vehicle operates. So far, most of the proposed operations of suborbital space tourism vehicles involve a flight to above 80km and less than 120km and taking-off and landing at the same location. Therefore, the operational location of the suborbital vehicle clearly determines the view of earth from space that will be available to its passengers. The proposed operational locations or spaceports usually are existing airports such as the airport at Curacao Island in the Caribbean or spaceport specially built at locations with economic interests such as Spaceport America in New Mexico or an airport that is going to be built, such as SpaceportSEA in Selangor, Malaysia. Suborbital vehicles operating from these spaceports can only offer limited views of Earth from space which is only few thousand kilometers of land or sea around their spaceports, and a clear view of only few hundred kilometers of land or sea directly below them, even though the views can be enhanced by the application of optical devices. Therefore, the view of some exotic locations such as a colorful coral reef, and phenomena such as a smoking volcano on Earth which may be very exciting when viewed from space will not be available on these suborbital tourism packages. The only possible way for the passengers of a suborbital vehicle to view such exotic locations and phenomena is by flying above or near them, and since it will not be economic and will be

  1. Overview Of Suborbital Human Transportation Concept Alpha

    NASA Astrophysics Data System (ADS)

    Adirim, H.; Pilz, N.; Marini, M.; Hendrick, P.; Schmid, M.; Behr, R.; Barth, T.; Tarfeld, F.; Wiegand, A.; Charbonnier, D.; Haya Ramos, R.; Steeland, J.; Mack, A.

    2011-05-01

    Within the EC co-funded project FAST20XX (Future high-Altitude high-Speed Transport 20XX), the European suborbital passenger transportation system concept ALPHA (Airplane Launched PHoenix Aircraft), which shall be based to a maximum extent on existing technologies and capabilities, is currently being investigated as collaborative project by a European consortium under coordination of ESA. The ALPHA concept incorporates an air-launch from a carrier aircraft, which shall be used as first stage. The ALPHA vehicle shall be capable of transporting up to four passengers plus one pilot to an altitude of at least 100 km. The ALPHA vehicle is a down-scaled version of the suborbital space transportation concept Hopper, which was already deeply investigated within the European FESTIP System Study and the German ASTRA program including the successfully flown experimental landing demonstrator Phoenix. This approach has allowed the use of existing aerodynamic vehicle data and has led to the adaptation of the external Hopper/Phoenix configuration for ALPHA. In FESTIP and ASTRA, the Hopper configuration showed sufficient stability margins. Due to the geometric similarity of the ALPHA and Hopper vehicles, a trimable and flyable configuration could be derived by means of ALPHA flight trajectory calculations. In its current configuration, the ALPHA vehicle has a length of ca. 9 m and a gross take-off mass of ca. 3.5 Mg. The launch, staging and separation of ALPHA shall be performed either as internal air-launch from the cargo bay of the carrier aircraft, as under-wing air-launch or as towed air-launch. After separation from the carrier aircraft, the ALPHA vehicle ignites its onboard rocket propulsion system. Since conventional liquid and solid propulsion did not seem suitable for ALPHA due to Their high cost, limited safety and toxicity, a low-cost, “green” and non-hazardous hybrid propulsion system based on liquid nitrous oxide in combination with a solid polymer fuel was

  2. External Payload Carrier (XPC) A Suborbital Research Platform

    NASA Technical Reports Server (NTRS)

    Schallhorn, Paul; Tatro, Chuck; Kutter, Bernard; Szatkowski, Gerald; Stopnitzky, Ben; Bulk, Tim

    2011-01-01

    This slide presentation details the concept of an External Payload Carrier (XPC), that can fly on ann unused Solid Rocket Booster (SRB) location on the Atlas V rocket to suborbital environment. The XPC can be used anytime there is sufficient excess lift capability available. The dimensions and possible uses of the XPC are reviewed. The completed Phase 1 study reviewed 57 variations, and arrived at three viable configurations, identified design baselines, subsystems and preliminary testing requirements. Phase II effort is planned to produce the preliminary design (i.e., PDR level), Systems Requirements Document (SRD), identify flight candidates, develop schedule and funding profiles, and identify the risk-reduction activities.

  3. Astrium suborbital spaceplane project: Demand analysis of suborbital space tourism

    NASA Astrophysics Data System (ADS)

    Le Goff, Thierry; Moreau, Antoine

    2013-12-01

    ASTRIUM is preparing the development of a safe and passenger friendly Suborbital Spaceplane, taking off and landing from a standard runway, powered by turbofans and using a rocket engine of proven design to reach 100 km altitude. This vehicle will be able to carry paying passengers to the edge of space and return them safely to their starting point. As a very new potentially adjacent B2C market, Astrium had decided at the beginning of this project to first conduct a full market analysis with the support of a worldwide survey based Research Company (IPSOS) in order to assess reality and credibility of this market. Two campaigns have been done, the first one in 2007 and the second one in 2010 after the international financial crisis. Last one has been also the opportunity to optimize quality of models by focusing in Asia region. This article describes the methodology used for this survey and unveils some results in term of size of this market and typology of the customers.

  4. Suborbital Reusable Launch Vehicles and Applicable Markets

    NASA Astrophysics Data System (ADS)

    Martin, J. C.; Law, G. W.

    2002-10-01

    The purpose of this report is to survey and characterize suborbital reusable launch vehicles (RLVs) in development, as well as to identify current and emerging suborbital market opportunities that these systems may enable. Over the past 30 years, NASA has accepted the burden of developing technologies that will enable cheaper access to orbital space, as evidenced by its past X-programs and the current Space Launch Initiative. Various private companies have also attempted, and are still attempting, to develop new RLV systems for orbital space applications. However, the large development costs of such systems, coupled with the downturn of the low Earth orbit market (e.g., Iridium, GlobalStar), have made private sector development of orbital RLV systems increasingly difficult at this time. Given these hurdles, many commercial space transportation companies have begun shifting focus toward suborbital market opportunities, for which the technical challenge is much lower and the cost of market entry less expensive.

  5. Suborbital commercial spaceflight crewmember medical issues.

    PubMed

    2011-04-01

    As directed by the Council of the Aerospace Medical Association, the Commercial Spaceflight Working Group has developed the following position paper concerning medical issues for commercial suborbital spaceflight crewmembers. This position paper has been approved by the AsMA Council to become a policy of the AsMA.

  6. 14 CFR 437.31 - Verification of operating area containment and key flight-safety event limitations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ...(a) to contain its reusable suborbital rocket's instantaneous impact point within an operating area... limits on the ability of the reusable suborbital rocket to leave the operating area; or (2) Abort... requirements of § 437.59 to conduct any key flight-safety event so that the reusable suborbital...

  7. 14 CFR 437.31 - Verification of operating area containment and key flight-safety event limitations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ...(a) to contain its reusable suborbital rocket's instantaneous impact point within an operating area... limits on the ability of the reusable suborbital rocket to leave the operating area; or (2) Abort... requirements of § 437.59 to conduct any key flight-safety event so that the reusable suborbital...

  8. 14 CFR 437.31 - Verification of operating area containment and key flight-safety event limitations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ...(a) to contain its reusable suborbital rocket's instantaneous impact point within an operating area... limits on the ability of the reusable suborbital rocket to leave the operating area; or (2) Abort... requirements of § 437.59 to conduct any key flight-safety event so that the reusable suborbital...

  9. 14 CFR 437.31 - Verification of operating area containment and key flight-safety event limitations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ...(a) to contain its reusable suborbital rocket's instantaneous impact point within an operating area... limits on the ability of the reusable suborbital rocket to leave the operating area; or (2) Abort... requirements of § 437.59 to conduct any key flight-safety event so that the reusable suborbital...

  10. 14 CFR 437.31 - Verification of operating area containment and key flight-safety event limitations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ...(a) to contain its reusable suborbital rocket's instantaneous impact point within an operating area... limits on the ability of the reusable suborbital rocket to leave the operating area; or (2) Abort... requirements of § 437.59 to conduct any key flight-safety event so that the reusable suborbital...

  11. 14 CFR 437.71 - Flight rules.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... rocket-powered flight, a permittee must confirm that all systems and operations necessary to ensure that... endanger the public. (c) A permittee may not operate a reusable suborbital rocket in a careless or reckless... operate a reusable suborbital rocket in areas designated in a Notice to Airmen under § 91.137, §...

  12. 14 CFR 437.71 - Flight rules.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... rocket-powered flight, a permittee must confirm that all systems and operations necessary to ensure that... endanger the public. (c) A permittee may not operate a reusable suborbital rocket in a careless or reckless... operate a reusable suborbital rocket in areas designated in a Notice to Airmen under § 91.137, §...

  13. 14 CFR 437.71 - Flight rules.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... rocket-powered flight, a permittee must confirm that all systems and operations necessary to ensure that... endanger the public. (c) A permittee may not operate a reusable suborbital rocket in a careless or reckless... operate a reusable suborbital rocket in areas designated in a Notice to Airmen under § 91.137, §...

  14. 14 CFR 437.71 - Flight rules.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... rocket-powered flight, a permittee must confirm that all systems and operations necessary to ensure that... endanger the public. (c) A permittee may not operate a reusable suborbital rocket in a careless or reckless... operate a reusable suborbital rocket in areas designated in a Notice to Airmen under § 91.137, §...

  15. 14 CFR 437.71 - Flight rules.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... rocket-powered flight, a permittee must confirm that all systems and operations necessary to ensure that... endanger the public. (c) A permittee may not operate a reusable suborbital rocket in a careless or reckless... operate a reusable suborbital rocket in areas designated in a Notice to Airmen under § 91.137, §...

  16. The XP spaceplane: A near term multi-purpose suborbital RLV

    NASA Astrophysics Data System (ADS)

    Lauer, Charles J.

    2007-06-01

    This paper will describe the history, technology and design features of the XP spaceplane being developed by Rocketplane Ltd. in Oklahoma. The XP is a four seat fighter-sized spaceplane that uses turbojets for takeoff and landing and a liquid oxygen/kerosene rocket engine for main propulsion during its ascent to a 100 km apogee suborbital space flight. The XP is intended to serve a variety of markets including suborbital tourist flights, intermediate duration microgravity research, remote sensing, astronomy, and microsatellite launch missions. Changes in vehicle configuration and flight profile for serving each of these markets will be described. The prototype XP will have its rollout ceremony at the end of 2007 and will begin test flights in early 2008. Commercial space flight operations are expected to begin in fall 2008 with tourist flights and microgravity research flights being the early customer base. The spaceplane's flight systems, safety systems, and operating procedures will be reviewed. In addition, key elements of the Rocketplane business and financial model will be discussed.

  17. PoSSUM: Polar Suborbital Science in the Upper Mesosphere

    NASA Astrophysics Data System (ADS)

    Reimuller, J. D.; Fritts, D. C.; Thomas, G. E.; Taylor, M. J.; Mitchell, S.; Lehmacher, G. A.; Watchorn, S. R.; Baumgarten, G.; Plane, J. M.

    2013-12-01

    Project PoSSUM (www.projectpossum.org) is a suborbital research project leveraging imaging and remote sensing techniques from Reusable Suborbital Launch Vehicles (rSLVs) to gather critical climate data through use of the PoSSUM Observatory and the PoSSUM Aeronomy Laboratory. An acronym for Polar Suborbital Science in the Upper Mesosphere, PoSSUM grew from the opportunity created by the Noctilucent Cloud Imagery and Tomography Experiment, selected by the NASA Flight Opportunities Program as Experiment 46-S in March 2012. This experiment will employ an rSLV (e.g. the XCOR Lynx Mark II) launched from a high-latitude spaceport (e.g. Eielson AFB, Alaska or Kiruna, Sweden) during a week-long deployment scheduled for July 2015 to address critical questions concerning noctilucent clouds (NLCs) through flights that transition the cloud layer where the clouds will be under direct illumination from the sun. The 2015 Project PoSSUM NLC campaign will use the unique capability of rSLVs to address key under-answered questions pertaining to NLCs. Specifically, PoSSUM will answer: 1) What are the small-scale dynamics of NLCs and what does this tell us about the energy and momentum deposition from the lower atmosphere? 2) What is the seasonal variability of NLCs, mesospheric dynamics, and temperatures? 3) Are structures observed in the OH layer coupled with NLC structures? 4) How do NLCs nucleate? and 5) What is the geometry of NLC particles and how do they stratify? Instrumentation will include video and still-frame visible cameras (PoSSUMCam), infrared cameras, a mesospheric temperatures experiment, a depolarization LiDAR, a mesospheric density and temperatures experiment (MCAT), a mesospheric winds experiment, and a meteoric smoke detector (MASS). The instrument suite used on PoSSUM will mature through subsequent campaigns to develop an integrated, modular laboratory (the ';PoSSUM Observatory') that will provide repeatable, low cost, in-situ NLC and aeronomy observations as well

  18. Commercial suborbital space tourism-proposal on passenger's medical selection

    NASA Astrophysics Data System (ADS)

    Kluge, Götz; Stern, Claudia; Trammer, Martin; Chaudhuri, Indra; Tuschy, Peter; Gerzer, Rupert

    2013-12-01

    Commercial human spaceflight has excellent economic and technical perspectives in the next decades. Passengers will be persons from a general population differing from culture, age, gender and health status. They all will have to withstand physical loads of spaceflight such as acceleration and deceleration forces, microgravity, vibration, noise and radiation. There is a necessity to mitigate all negative impacts on the passengers' health. Besides precautionary measures in construction and equipment, a diligent medical selection and pre-flight training is recommended. To ensure an easy and at the same time qualified selection procedure, it is necessary to define medical selection criteria and training methods. As experiences with suborbital spaceflight of private passengers are still few we recommend to implement in the beginning of this new era maximum safety standards. Having performed a satisfactory number of successful flights, some of the selection criteria and training sessions might be loosened or modified. This judicious approach is in the interest of the spaceflight participants as well as of the providing companies. As a guideline we propose a four step approach that allows a quick decision concerning the fitness of participants to fly as well as an intensive preparation of the passengers. For the first two steps positive experiences from medical screening and examination of professional pilots can be utilised. According to JAR-FCL 3 (Joint Aviation Requirements-Flight Crew Licensing, Chapter 3) a questionnaire with medical interview targeting the medical background of the respective person and including no-go criteria provides a first estimation for applicants and medical examiners whether there will be a chance to be accepted as a passenger. The second step of selection comprises the physical examination of the applicant adjusted to the professional pilot's examination procedure. As the physical challenges of the suborbital flight will exceed the impact

  19. The NASA Suborbital Program: A status review

    NASA Technical Reports Server (NTRS)

    Teeter, R.; Reynolds, B.

    1983-01-01

    The status of the NASA suborbital program is reviewed and its importance to astrophysical and geophysical programs is assessed. A survey of past scientific and developmental accomplishments, an examination of the trends in program costs, and an analysis of current and future program roles are included. The technical disciplines examined are primarily those of astronomy/astrophysics/solar physics and magnetospheric/ionospheric/ atmospheric physics.

  20. External Payload Carrier (XPC) - A Novel Platform for Suborbital Research

    NASA Technical Reports Server (NTRS)

    Schallhorn, Paul; Groves, Curtis; Tatro, Charles; Kutter, Bernard; Szatkowski, Gerald; Bulk, Tim; Pitchford, Brian

    2010-01-01

    ULA, SAS, and NASA LSP are examining a new platform for suborbital research utilizing the Atlas V Launch Vehicle. The new platform, XPC, fills a new niche within the suborbital realm Large Heavy Lift (approximately 1200 cubic feet, 5000 lb payload). It will not compete with the commercial suborbital launch sector. The XPC will utilize excess performance on Atlas V missions. The Preliminary Design phase is recently underway. The XPC team is soliciting input from potential users.

  1. Study of Waverider-based Point-to-Point Suborbital Rocketplane

    NASA Astrophysics Data System (ADS)

    Takama, Yoshiki; Ishimoto, Shinji

    As a high-speed manned transportation system in the future, point-to-point (P2P) suborbital rocketplane is currently studied in Japan Aerospace Exploration Agency (JAXA) space transportation mission directorate. The vehicle was designed on the basis of the concept of waverider allowing high L/D in hypersonic regime, which is required for longer flight range and smaller load factor. Compared with an ideal waverider, the designed P2P suborbital rocketplane has outer wings for the improvement of the low-speed aerodynamic performance, finite thickness in the leading edge for the reduction of the aerodynamic heating, and twin vertical tails for directional stability. The aerodynamic performance of the P2P vehicle was investigated through numerical simulation of both subsonic and hypersonic flows, and the baseline aerodynamic shape of the P2P vehicle was discussed. The L/D in the trim condition at hypersonic speed was 2.6.

  2. Flight Opportunities: Space Technology Mission Directorate

    NASA Technical Reports Server (NTRS)

    Van Dijk, Alexander

    2016-01-01

    Flight Opportunities enables maturation of new space technologies by funding access to commercially available space-relevant test environments. The program also supports capability development in the commercial suborbital and orbital small satellite launcher markets.

  3. The Design and Operation of Suborbital Low Cost and Low Risk Vehicle to the Edge of Space (SOLVES)

    NASA Astrophysics Data System (ADS)

    Ridzuan Zakaria, Norul; Nasrun, Nasri; Rashidy Zulkifi, Mohd; Izmir Yamin, Mohd; Othman, Jamaludin; Rafidi Zakaria, Norul

    2013-09-01

    and therefore it will be engineered for simple operation by trained passengers. However, for certification by aviation authorities the vehicle may be operational with 3 passengers and a pilot. A specific operation considered for SOLVES is navaloperation where the suborbital vehicle will be operating from a seaborne spaceport, probably a superyacht with spacepad for the vertical launching and landing of the vehicle. Such naval operation enables the vehicle to fly above exotic locations reachable by sea. SOLVES is also planned for further development into reusable rocket booster to carry small suborbiter to 160km from sea level, enables the passengers aboard the suborbiter to experience longer zero gravity time and more effective suborbital flight.

  4. Suborbital Research and Education Missions with Commercial Reusable Launch Vehicles

    NASA Astrophysics Data System (ADS)

    Rodway, K.; Nelson, A.; Voigt, J.

    2012-12-01

    Suborbital reusable launch vehicles (sRLV) will provide low-cost, flexible, and frequent access to space. In the case of XCOR's Lynx, the vehicle design and capabilities work well for hosting specially designed experiments that can be flown with a human-tended researcher or alone with the pilot on a unique mission on a customized flight trajectory. This new manned, reusable commercial platform will allow for repeated observations with a single instrument, but without the need to refurbish the vehicle between flights. In addition, the short turn-around means a researcher can do multiple observations, measurements, or targets. The vehicle is designed for multi-mission primary and secondary payload capabilities, including: in-cockpit experiments and instrumentation testing, externally mounted experiments, upper atmospheric sampling, and microsatellite launch. This vehicle takes off horizontally from a runway and will go into a powered ascent attaining Mach 2.9 maximum airspeed. After about three minutes and at approximately 58 km (190,000 ft) the engines are shutdown and the RLV then coasts upwards. The low gravity period (at or below 0.001go) begins soon after at 3.35 minutes and the microgravity period (at or below 10-6go) starts at 4.25 minutes. At approximately four and half minutes the vehicle reaches apogee of 100 km (328, 000 ft). After reentry and a Max-G force pullout of 4 g, the Lynx touches down on the takeoff runway after approximately 30 minutes.Typical Lynx Mark II flight profile

  5. Remote control video cameras on a suborbital rocket

    NASA Astrophysics Data System (ADS)

    Wessling, Francis C., Dr.

    1997-01-01

    Three video cameras were controlled in real time from the ground to a sub-orbital rocket during a fifteen minute flight from White Sands Missile Range in New Mexico. Telemetry communications with the rocket allowed the control of the cameras. The pan, tilt, zoom, focus, and iris of two of the camera lenses, the power and record functions of the three cameras, and also the analog video signal that would be sent to the ground was controlled by separate microprocessors. A microprocessor was used to record data from three miniature accelerometers, temperature sensors and a differential pressure sensor. In addition to the selected video signal sent to the ground and recorded there, the video signals from the three cameras also were recorded on board the rocket. These recorders were mounted inside the pressurized segment of the rocket payload. The lenses, lens control mechanisms, and the three small television cameras were located in a portion of the rocket payload that was exposed to the vacuum of space. The accelerometers were also exposed to the vacuum of space.

  6. Remote control video cameras on a suborbital rocket

    SciTech Connect

    Wessling, Francis C.

    1997-01-10

    Three video cameras were controlled in real time from the ground to a sub-orbital rocket during a fifteen minute flight from White Sands Missile Range in New Mexico. Telemetry communications with the rocket allowed the control of the cameras. The pan, tilt, zoom, focus, and iris of two of the camera lenses, the power and record functions of the three cameras, and also the analog video signal that would be sent to the ground was controlled by separate microprocessors. A microprocessor was used to record data from three miniature accelerometers, temperature sensors and a differential pressure sensor. In addition to the selected video signal sent to the ground and recorded there, the video signals from the three cameras also were recorded on board the rocket. These recorders were mounted inside the pressurized segment of the rocket payload. The lenses, lens control mechanisms, and the three small television cameras were located in a portion of the rocket payload that was exposed to the vacuum of space. The accelerometers were also exposed to the vacuum of space.

  7. 14 CFR 437.95 - Inspection of additional reusable suborbital rockets.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... suborbital rockets. 437.95 Section 437.95 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL... of an Experimental Permit § 437.95 Inspection of additional reusable suborbital rockets. A permittee may launch or reenter additional reusable suborbital rockets of the same design under the permit...

  8. 14 CFR 437.95 - Inspection of additional reusable suborbital rockets.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... suborbital rockets. 437.95 Section 437.95 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL... of an Experimental Permit § 437.95 Inspection of additional reusable suborbital rockets. A permittee may launch or reenter additional reusable suborbital rockets of the same design under the permit...

  9. 14 CFR 437.95 - Inspection of additional reusable suborbital rockets.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... suborbital rockets. 437.95 Section 437.95 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL... of an Experimental Permit § 437.95 Inspection of additional reusable suborbital rockets. A permittee may launch or reenter additional reusable suborbital rockets of the same design under the permit...

  10. 14 CFR 437.95 - Inspection of additional reusable suborbital rockets.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... suborbital rockets. 437.95 Section 437.95 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL... of an Experimental Permit § 437.95 Inspection of additional reusable suborbital rockets. A permittee may launch or reenter additional reusable suborbital rockets of the same design under the permit...

  11. 14 CFR 437.95 - Inspection of additional reusable suborbital rockets.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... suborbital rockets. 437.95 Section 437.95 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL... of an Experimental Permit § 437.95 Inspection of additional reusable suborbital rockets. A permittee may launch or reenter additional reusable suborbital rockets of the same design under the permit...

  12. Remote Sensing of PMCs with the Polar Suborbital Science in the Upper Mesosphere (PoSSUM) Lidar

    NASA Astrophysics Data System (ADS)

    Mitchell, S.; Thayer, J. P.; Reimuller, J. D.

    2013-12-01

    The Polar Suborbital Science in the Upper Mesosphere (PoSSUM) experiment is a modular observatory readily integrated into commercial manned Reusable Suborbital Launch Vehicles (RSLV) for aeronomy, remote sensing, solar physics, astronomy/astrophysics, and Earth observations. The proposed observatory, scheduled for deployment in July 2015, is being designed to operate onboard the XCOR Lynx and Virgin Galactic SpaceShipTwo vehicles. The observatory will enable unprecedented capabilities to dedicate low-cost suborbital campaigns for the study of the small-scale dynamics of polar mesospheric clouds (PMC) by obtaining imagery and remotely sensed data from apogee altitudes in excess of 100 km. A key component of the observatory is the PoSSUM Lidar, a Rayleigh/Mie backscatter lidar currently being designed at the University of Colorado at Boulder. The proposed instrument transmitter consists of a 532 nm linearly polarized laser coupled with conditioning and steering optics. The receiver employs a photon counting approach to detect the received optical signals backscattered from PMCs during flight operations. The design of the PoSSUM Lidar will be presented, including the unique challenges associated with developing a lidar instrument for operations onboard a RSLV. Initial simulation data will be explored, including a discussion of the expected science products output by the lidar, such as PMC height and density, as well as the potential for depolarization measurements to evaluate PMC asphericity.

  13. ASPS: American Suborbital Passenger System 2005

    NASA Astrophysics Data System (ADS)

    Wyczalek, Floyd A.

    1994-11-01

    With the evaporation of funding support for the National Aerospace Plane (NASP), realization of a single stage to orbit flight system has been deferred. With the resource down sizing of the NASP management and technical team, development of the NASP concept appears to be delayed beyond the year 2030. To fill this gap for shorter flight times to remote destinations over 8,000 km, it is now proposed to convert the existing NASA shuttle to a passenger configuration and air launch horizontally from a Boeing 747 aircraft as the first stage carrier after climb to launch altitude. This US Shuttle concept may permit the transport of 100 passengers to destinations 10,000 km distant during a flight duration of 90 minutes, and during flight durations of about 120 minutes to any commercial destination on the planet Earth. This long distance system takes advantage of the existing shuttle and Boeing 747 airframe and propulsion technology, and can be implemented within the next decade.

  14. Tracking the Relative Motion of Four Space Payloads Launched from a Sub-Orbital NASA Rocket

    NASA Technical Reports Server (NTRS)

    Bull, Barton; Martell, Hugh

    1999-01-01

    One problem, which is comparatively new in the field of GPS (Global Positioning System) applications, is the determination of the relative trajectories of space vehicles. Applications include the docking of spacecraft, collision avoidance in the area of space stations, and trajectory reconstruction of multiple payloads. The required precision in any of these applications will vary, according to the requirements of the task and abilities of GPS to cope with the environment and the dynamics. This paper describes the post-mission reconstruction of the relative trajectories of four GPS receivers attached to four payloads jettisoned from a Black Brant XII rocket. This vehicle was launched by the National Aeronautics and Space Administration (NASA) in January 1999 from the Poker Flats Research Range near Fairbanks, Alaska. The Black Brant XII is a sub-orbital rocket designed to carry payloads of 100 to 500 kg into the upper atmosphere. Flight time is generally in the order of 10 - 20 minutes.

  15. Pushing the Boundaries of X-ray Grating Spectroscopy in a Suborbital Rocket

    NASA Technical Reports Server (NTRS)

    McEntaffer, Randall L.; DeRoo, Casey; Schultz, Ted; Zhang, William W.; Murray, Neil J.; O'Dell, Stephen; Cash, Webster

    2013-01-01

    Developments in grating spectroscopy are paramount for meeting the soft X-ray science goals of future NASA X-ray Observatories. While developments in the laboratory setting have verified the technical feasibility of using off-plane reflection gratings to reach this goal, flight heritage is a key step in the development process toward large missions. To this end we have developed a design for a suborbital rocket payload employing an Off-Plane X-ray Grating Spectrometer. This spectrometer utilizes slumped glass Wolter-1 optics, an array of gratings, and a CCD camera. We discuss the unique capabilities of this design, the expected performance, the science return, and the perceived impact to future missions.

  16. The External Payload Carrier - A Suborbital Research Platform

    NASA Technical Reports Server (NTRS)

    Schallhorn, Paul; Tatro, Charles; Kutter, Bernard; Szatkowski, Gerald; Stopnitzky, Benny; Bulk, Tim; Pitchford, Brian

    2011-01-01

    High altitude, suborbital research payloads are typically restricted to small packages (in terms of both volume and mass) due to the delivery platform employed. Sounding rockets that normally provide these services have payload capacities which severely limit the size and scope of the research to be performed. A new research platform is currently in the early development phase for large (both volume and mass) payload microgravity suborbital payloads seeking access to these regimes. The EXternal Payload Carrier (XPC) utilizes an open solid rocket motor position on the Atlas V vehicle and aerodynamically mimics the outer contour of a solid rocket motor. This presentation will detail the current state of the design and capability of XPC for potential future users.

  17. Commercial suborbital reusable launch vehicles: ushering in a new era for turbopause exploration (Invited)

    NASA Astrophysics Data System (ADS)

    Smith, H. T.

    2013-12-01

    Multiple companies are in the process of developing commercial suborbital reusable launch vehicles (sRLV's). While these companies originally targeted space tourism as the primary customer base, it is rapidly becoming apparent that this dramatic increase in low cost access to space could provide revolutionary opportunities for scientific research, engineering/instrument development and STEM education. These burgeoning capabilities will offer unprecedented opportunities regarding access to space with frequent low-cost access to the region of space from the ground to the boundary of near-Earth space at ~100 km. In situ research of this region is difficult because it is too high for aircraft and balloons and yet too low for orbital satellites and spacecraft. However, this region is very significant because it represents the tenuous boundary of Earth's Atmosphere and Space. It contains a critical portion of the atmosphere where the regime transitions from collisional to non-collisional physics and includes complex charged and neutral particle interactions. These new launch vehicles are currently designed for manned and unmanned flights that reach altitudes up to 110 km for 5K-500K per flight with payload capacity exceeding 600 kg. Considering the much higher cost per flight for a sounding rocket with similar capabilities, high flight cadence, and guaranteed return of payload, commercial spacecraft has the potential to revolutionize access to near space. This unprecedented access to space allows participation at all levels of research, engineering, education and the public at large. For example, one can envision a model where students can conduct complete end to end projects where they design, build, fly and analyze data from individual research projects for thousands of dollars instead of hundreds of thousands. Our community is only beginning to grasp the opportunities and impactions of these new capabilities but with operational flights anticipated in 2014, it is

  18. Human Factors Engineering in Designing the Passengers' Cockpit of the Malaysian Commercial Suborbital Spaceplane

    NASA Astrophysics Data System (ADS)

    Ridzuan Zakaria, Norul; Mettauer, Adrian; Abu, Jalaluddin; Hassan, Mohd Roshdi; Ismail, Anwar Taufeek; Othman, Jamaluddin; Shaari, Che Zhuhaida; Nasron, Nasri

    2010-09-01

    The design of the passengers’ cabin or cockpit of commercial suborbital spaceplane is a new and exciting frontier in human factors engineering, which emphasizes on comfort and safety. There is a program to develop small piloted 3 seats commercial suborbital spaceplane by a group of Malaysians with their foreign partners, and being relatively small and due to its design philosophy, the spaceplane does not require a cabin, but only a cockpit for its 2 passengers. In designing the cockpit, human factors engineering and safety principles are given priority. The cockpit is designed with the intention to provide comfort and satisfaction to the passengers without compromising the safety, in such a way that there are passenger-view wide angled video camera to observe the passengers at all time in flight, “rear-view”, “under-the-floor-view” and “fuselage-view” video cameras for the passengers, personalized gauges and LCDs on the dashboard to provide vital and useful information during the flight to the passengers, and biomedical engineered products which not only entertain the passengers, but also provide important information on the passengers to the ground crews who are responsible in the comfort and safety of the passengers. The passenger-view video-camera, which record the passengers with Earth visible through the glass canopy as the background, not only provides live visual of the passengers for safety reason, but also provide the most preferred memorable video collection for the passengers, while other video cameras provide the opportunity to view at various angles from unique positions to both the passengers and the ground observers. The gauges and LCDs on the dashboard provide access to the passengers to information such as the gravity, orientation, rate of climb and flight profile of the spaceplane, graphical presentation of the spaceplane in flight, and live video from the onboard video cameras. There is also a control stick for each passenger to

  19. Study and Development of a Sub-Orbital Re-Entry Demonstrator

    NASA Astrophysics Data System (ADS)

    Savino, R.

    The Italian and European Space Agencies are supporting a research programme, developed in Campania region by a cluster of industries, research institutes and universities, on a low-cost re-entry capsule, able to return payloads from the ISS to Earth and/or to perform short-duration scientific missions in Low Earth Orbit (LEO). The ballistic capsule is characterized by a deployable, disposable "umbrella-like" heat shield that allows relatively small dimensions at launch and a sufficient exposed surface area in re-entry conditions, reducing the ballistic coefficient and leading to acceptable heat fluxes, mechanical loads and final descent velocity. ESA is supporting a preliminary study to develop a flight demonstrator of the capsule to be embarked as a secondary payload onboard a sub-orbital sounding rocket. The deployable thermal protection system concept may be applied to future science and robotic exploration mission requiring planetary entry and, possibly also to missions in the framework of Human Space flight, requiring planetary entry or re-entry. The technology offers also an interesting potential for aerobraking, aerocapture and for de-orbiting. This paper summarizes the results of these activities, which are being more and more refined as the work proceeds, including the definition and analysis of the mission scenario, the aerodynamic, aerothermodynamic, mechanical and structural analyses and the technical definition of avionics, instrumentation and main subsystems.

  20. Results of the First US Manned Orbital Space Flight

    NASA Technical Reports Server (NTRS)

    1962-01-01

    The results of the first United States manned orbital space flight conducted on February 20, 1962 are presented. The prelaunch activities, spacecraft description, flight operations, flight data, and postflight analyses presented form a continuation of the information previously published for the two United States manned suborbital space flights conducted on May 5, 1961, and July 21, 1961, respectively, by the National Aeronautics and Space Administration.

  1. Suborbital spaceplane optimization using non-stationary Gaussian processes

    NASA Astrophysics Data System (ADS)

    Dufour, Robin; de Muelenaere, Julien; Elham, Ali

    2014-10-01

    This paper presents multidisciplinary design optimization of a sub-orbital spaceplane. The optimization includes three disciplines: the aerodynamics, the structure and the trajectory. An Adjoint Euler code is used to calculate the aerodynamic lift and drag of the vehicle as well as their derivatives with respect to the design variables. A new surrogate model has been developed based on a non-stationary Gaussian process. That model was used to estimate the aerodynamic characteristics of the vehicle during the trajectory optimization. The trajectory of thevehicle has been optimized together with its geometry in order to maximize the amount of payload that can be carried by the spaceplane.

  2. Analysis of Satellite and Sub-Orbital Measurements

    NASA Technical Reports Server (NTRS)

    Gleason, James (Technical Monitor); Martin, Randall V.

    2004-01-01

    The objective of this project is to support the INTEX aircraft mission by developing experience in the integrated analysis of existing sub-orbital observations and satellite observations with numerical models. Specific tasks include providing guidance to INTEX by identifying discrepancies in satellite observations with (1) in situ measurements, (2) bottom-up emission inventories of nitrogen oxides and volatile organic compounds, and (3) model calculations of the export of pollution from North America to the global atmosphere. An important focus area is developing and improving bottom-up emission inventories by combining top-down and bottom-up information.

  3. Longitudinal stability analysis of a suborbital re-entry demonstrator for a deployable capsule

    NASA Astrophysics Data System (ADS)

    Iacovazzo, Michele; Carandente, Valerio; Savino, Raffaele; Zuppardi, Gennaro

    2015-01-01

    In the field of atmospheric re-entry technology several research and industrial projects are based on the design of deployable, umbrella-like Thermal Protection Systems (TPSs) and aero-brakes. These systems are made of flexible, high temperature resistant fabrics, folded at launch and deployed in space for de-orbit and re-entry operations. This technology is very promising for low cost research and industrial applications, but requires to be validated by experimental flight tests. The University of Naples "Federico II" is currently working on the development of different down-scaled technological demonstrators for this kind of capsule to be launched by different classes of sounding rockets. In the present work an aerodynamic longitudinal stability analysis for a possible, suborbital re-entry demonstrator, has been performed in continuum and rarefied regimes. The longitudinal stability behavior of the capsule, along the entire re-entry path, has been investigated in the whole range of angle of attack and, in particular, around the nominal and the reverse equilibrium re-entry attitudes (i.e. around 0° and 180°, respectively) to implement a proper re-entry strategy able not to compromise the effectiveness of the flying system.

  4. From suborbital space tourism to commercial personal spaceflight

    NASA Astrophysics Data System (ADS)

    Peeters, Walter

    2010-06-01

    Excellent essays have been recently published on the profitability and the future of space tourism. This paper is intended to supplement the considerations in this field and emphasizes the further potential evolution of commercial personal spaceflights. Indeed, based upon work done at the International Space University (ISU) the oligopolistic character of suborbital space tourism has been linked to marketing and product life cycle (PLC) considerations and has led to the thesis that space tourism as a profitable sector will require a follow-on strategy. Orbital space tourism, on one hand, could become an extension of the PLC but, on the other hand, it is assumed that point-to-point (P2P) commercial space transport will become the long term sustainable market. Without ignoring technical challenges, this paper will mainly concentrate on marketing and commercial aspects of personal spaceflight.

  5. Proliferating cells in suborbital tissue drive eye migration in flatfish.

    PubMed

    Bao, Baolong; Ke, Zhonghe; Xing, Jubin; Peatman, Eric; Liu, Zhanjiang; Xie, Caixia; Xu, Bing; Gai, Junwei; Gong, Xiaoling; Yang, Guimei; Jiang, Yan; Tang, Wenqiao; Ren, Daming

    2011-03-01

    The left/right asymmetry of adult flatfishes (Pleuronectiformes) is remarkable given the external body symmetry of the larval fish. The best-known change is the migration of their eyes: one eye migrates from one side to the other. Two extinct primitive pleuronectiformes with incomplete orbital migration have again attracted public attention to the mechanism of eye migration, a subject of speculation and research for over a century. Cranial asymmetry is currently believed to be responsible for eye migration. Contrary to that hypothesis, we show here that the initial migration of the eye is caused by cell proliferation in the suborbital tissue of the blind side and that the twist of frontal bone is dependent on eye migration. The inhibition of cell proliferation in the suborbital area of the blind side by microinjected colchicine was able to prevent eye migration and, thereafter, cranial asymmetry in juvenile Solea senegalensis (right sideness, Soleidae), Cynoglossus semilaevis (left sideness, Cynoglossidae), and Paralichthys olivaceus (left sideness, Paralichthyidae) with a bottom-dwelling lifestyle. Our results correct the current misunderstanding that eye migration is driven by the cranial asymmetry and simplify the explanation for broken left/right eye-symmetry. Our findings should help to focus the search on eye migration-related genes associated with cell proliferation. Finally, a novel model is proposed in this research which provides a reasonable explanation for differences in the migrating eye between, and sometimes within, different species of flatfish and which should aid in our overall understanding of eye migration in the ontogenesis and evolution of Pleuronectiformes.

  6. Combining Suborbital Measurements of Aerosol Optical Depth and Columnar Water Vapor for Satellite Sensor Validations in the CLAMS (Chesapeake Lighthouse and Aircraft Measurements for Satellites) Experiment, 2001

    NASA Astrophysics Data System (ADS)

    Redemann, J.; Schmid, B.; Livingston, J. M.; Russell, P. B.; Eilers, J. A.; Hobbs, P. V.; Kahn, R.; Smith, W. L.; Holben, B. N.; Rutledge, C. K.; Pitts, M. C.; Mishchenko, M. I.; Chowdhary, J.; Martins, J. V.; Plana-Fattori, A.; Charlock, T. P.

    2002-05-01

    As part of the Chesapeake Lighthouse and Aircraft Measurements for Satellites (CLAMS) experiment, July 10 - August 2, 2001, the 14-channel NASA Ames Airborne Tracking Sunphotometer (AATS-14) was operated successfully aboard the University of Washington Convair-580 during 10 research flights (~45 flight hours). The CLAMS campaign was a clear sky, shortwave (SW) closure campaign that entailed measurements from the Chesapeake Lighthouse research platform, several land sites, 6 research aircraft and the Terra satellite. CLAMS research goals included validation of satellite-based retrievals of aerosol properties, vertical profiles of radiative fluxes, temperature and water vapor. Suborbital measurements of aerosol optical depth (AOD) and columnar water vapor (CWV) were carried out at several AERONET sites and aboard five of the six airborne platforms using a variety of techniques. AATS-14 measures the direct solar beam transmission at 14 discrete wavelengths (354-1558 nm), yielding aerosol optical depth spectra and columnar water vapor. During coordinated flights of the UW Convair-580, AATS-14 measured full column aerosol optical depth spectra at exact Terra overpass time on at least 7 occasions. For five of these opportunities, AOD at 499nm was at or below 0.1. During Terra overpass on July 17, 2001, AATS-14 measured the largest AOD encountered during the entire experiment (~0.48 at 499nm), including a horizontal gradient in AOD of more than 0.1 over a distance of ~80 kilometers. We will illustrate how the spatially resolved measurements by AATS-14 and the temporally resolved AERONET measurements can be usefully combined for satellite validation purposes by constraining the small-scale aerosol variability off the US East coast. While the first part of this paper is focused on AATS-14 measurements, in the remainder of this paper we will show comparisons to other suborbital measurements obtained using (i) the AERONET sun/sky radiometer at the Chesapeake Lighthouse, (ii

  7. 14 CFR 437.25 - Flight test plan.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Flight test plan. 437.25 Section 437.25 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... reusable suborbital rocket. Operational Safety Documentation...

  8. 14 CFR 437.25 - Flight test plan.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Flight test plan. 437.25 Section 437.25 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... reusable suborbital rocket. Operational Safety Documentation...

  9. 14 CFR 437.25 - Flight test plan.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Flight test plan. 437.25 Section 437.25 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... reusable suborbital rocket. Operational Safety Documentation...

  10. 14 CFR 437.25 - Flight test plan.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Flight test plan. 437.25 Section 437.25 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... reusable suborbital rocket. Operational Safety Documentation...

  11. 14 CFR 437.25 - Flight test plan.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Flight test plan. 437.25 Section 437.25 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... reusable suborbital rocket. Operational Safety Documentation...

  12. Flight programs and X-ray optics development at MSFC

    NASA Astrophysics Data System (ADS)

    Gubarev, M.; Ramsey, B.; O'Dell, S.; Elsner, R.; Kilaru, K.; Atkins, C.; Swartz, D.; Gaskin, J.; Weisskopf, M.

    The X-ray astronomy group at the Marshall Space Flight Center (MSFC) is developing electroformed nickel/cobalt x-ray optics for suborbital and orbital experiments. Suborbital instruments include the Focusing X-ray Solar Imager (FOXSI) and Micro-X sounding rocket experiments and the HEROES balloon payload. Our current orbital program is the fabrication of mirror modules for the Astronomical Roentgen Telescope (ART) to be launched on board the Russian-German Spectrum Roentgen Gamma Mission (SRG). A second component of our work is the development of fabrication techniques and optical metrology to improve the angular resolution of thin-shell optics to the arcsecond-level.

  13. Auroral Spatial Structures Probe Sub-Orbital Mission Preliminary Results

    NASA Astrophysics Data System (ADS)

    Pratt, J.; Swenson, C.; Martineau, R. J.; Fish, C. S.; Conde, M.; Hampton, D.; Crowley, G.

    2015-12-01

    The NASA Auroral Spatial Structures Probe, 49.002, was launched January 28, 2015 from the Poker Flat Research Range into active aurora over the northern coast of Alaska. The primary objective of this mission was to determine the contribution of small spatial and temporal scale fluctuations of the electric fields to the larger-scale energy deposition processes associated with the aurora. The Auroral Spatial Structures Probe Sub-Orbital Mission consisted of a formation of 7 spacecraft (a main payload with 6 deployable sub-payloads) designed for multiple temporally spaced co-located measurements of electric and magnetic fields in the earth's ionosphere. The mission was able to make observations at a short time scale and small spatial scale convergence that is unobservable by either satellite or ground-based observations. The payloads included magnetometers, electric field double probes, and Langmuir probes as well as a sweeping impedance probe on the main payload. We present here preliminary results from the measurements taken that hint at the underlying spatial structure of the currents and energy deposition in the aurora. The Poynting flux derived from the observations is shown and implications are discussed in terms of the contribution of small spatial scale, rapid temporal scale fluctuations in the currents that deposit energy in the auroral region. Funding provided by NASA Grants NNX11AE23G and NNX13AN20A.

  14. Ultraviolet Instrumentation for the NASA Sub-orbital Program

    NASA Astrophysics Data System (ADS)

    Beasley, Matthew N.; Scowen, P.

    2009-01-01

    We present several sub-orbital projects that will provide good science, demonstrate technology suitable to space missions, and provide for the training of students at all levels. We have a pair of sounding rocket payloads that are designed to exploit otherwise inaccessible parameter space (wavelength, imaging resolution, spectral resolution) to answer particular questions about the nature of the local ISM and star formation in both the Milky Way and other nearby galaxies. This payload, currently in fabrication, will take images at 7 arcsecond resolution from 90 - 110 nm and can be configured for an emission line filter (103 nm) within that bandpass. This design is optimized for a very high launch rate. Targets are spread over the sky and refurbishment time between launches is very low. The other payload is to produce high resolution (R > 100,000) spectra of the interstellar medium of lithium-like oxygen, nitrogen, and carbon. In addition to sounding rockets, we present options for new balloon-borne instruments to use the advantages of high altitude pointed observations. The key features are the high resolution due to good intrinsic seeing over a wide field and very low background that allow measurements of low surface brightness objects. Our program will provide excellent scientific return, develop new instrumentation, and has a strong history of training students at the graduate and undergraduate levels.

  15. Airborne Microwave Observatory of Subcanopy and Subsurface (AirMOSS) Earth Venture Suborbital Mission Overview

    NASA Astrophysics Data System (ADS)

    Moghaddam, M.; Entekhabi, D.; Moorcroft, P. R.; Lou, Y.; Chapin, E.; Saatchi, S. S.; Reichle, R. H.; Crow, W. T.; Cuenca, R. H.; Tabatabaeenejad, A.; Shepson, P. B.; Hensley, S.; Hagimoto, Y.; Chen, R.; Milak, S.; Ali, A. A.; Hollinger, D. Y.

    2015-12-01

    AirMOSS was selected by NASA in 2010 as one of the first 5 Earth-Venture-Suborbital missions, with the goal of reducing the uncertainty of net ecosystem exchange (NEE) in north America through provision of high-resolution surface-to-depth profiles of soil moisture to land hydrology and ecosystem models. AirMOSS is accomplishing this goal by producing retrieved maps of so-called root zone soil moisture (RZSM) at approximately 100-m resolution for 9 biomes (10 sites) in north America, ranging from the boreal forests in Canada to the tropical rainforests in Costa Rica. RZSM has been hypothesized to account for 60% or more of the uncertainty in estimates of NEE. AirMOSS, currently in its final mission year, has acquired about 3 years of observations of RZSM at its study sites, with a total of 21 flight campaigns per year. Each flight campaign has included 2-3 flight dates. The RZSM maps have been retrieved from polarimetric synthetic aperture radar (SAR) instrument built by the Jet Propulsion Laboratory and flyign aboard a Gulfstream-3 airplane, operated by NASA Johnson Space Center. The estimation algorithms for deriving the RZSM maps have been matured throughout the mission, and have been shown to produce estimates of RZSM that are accurate to within 0.02-0.12 m3/m3 compared to in-situ validation data. The mission has also produced higher level RZSM products at hourly intervals, using land hydrology models, whose parameters are optimized using the AirMOSS snapshots. The ultimate product of the mission are the NEE estimates, generated not only for the mission study sites, but also upscaled to the entire scale of north America. These results are all under production, with the final mission products expected in May 2016. This presentation will give an overview of the mission, its products, and the main scientific findings. Several other papers in this session provide more details on each of the various aspects of the mission.

  16. Establishing a Regulatory Framework for the Development & Operations of Sub-Orbital & Orbital Aircraft (SOA) in the EU

    NASA Astrophysics Data System (ADS)

    Marciacq, Jean-Bruno; Tomasello, Filippo; Erdelyi, Zsuzsanna; Gerhard, Michael

    2013-09-01

    The Treaty of the European Union allows for the development of common policies for all sectors of transport, including aviation, and its safety. To this end, the European legislator established in 2002 the European Aviation Safety Agency (EASA), located in Cologne, Germany, and gave it responsibility for the regulation of aviation safety, successively encompassing airworthiness, air operations and Flight Crew Licensing (FCL), Air Traffic Management (ATM), Air Navigation Systems (ANS), as well as Aerodromes (ADR).The Annexes 6 and 8 of the International Civil Aviation Organization (ICAO) to the Chicago Convention define an aircraft as "any machine that can derive support in the atmosphere from the reactions of the air other than the reactions of the air against the earth's surface". The aerodynamic lift generated during the atmospheric part of the flight is commonly used to sustain and control the vehicle, that is to take-off, climb, pull-up, perform manoeuvres, fly back to the airport and land. Thus, Sub- orbital and Orbital Aircraft (SOA) are considered to be aircraft, as opposed to rockets which are symmetrical bodies not generating lift, and solely sustained by their rocket engine(s).Consequently, the regulation of SOA airworthiness, their crew, operations, insertion into the traffic and utilisation of aerodromes would in principle fall under the remit of EASA, which would have to fulfil its role of protection of the European citizens in relation to civil suborbital and orbital flights, that is to certify SOAs and their operations before they would be operated for Commercial Transport in the EU.Since EASA was first contacted by potential applicants in 2007, many projects have developed and the context has evolved. Thus, this paper intends to update the approach initially proposed at the 3rd IAASS in Rome in October 2008 and complemented at the 4th IAASS in Huntsville in May 2010 to accommodate sub-orbital and orbital aircraft into the EU regulatory system, and

  17. Monte Carlo simulations of the secondary neutron ambient and effective dose equivalent rates from surface to suborbital altitudes and low Earth orbit

    NASA Astrophysics Data System (ADS)

    El-Jaby, Samy; Richardson, Richard B.

    2015-07-01

    Occupational exposures from ionizing radiation are currently regulated for airline travel (<20 km) and for missions to low-Earth orbit (∼300-400 km). Aircrew typically receive between 1 and 6 mSv of occupational dose annually, while aboard the International Space Station, the area radiation dose equivalent measured over just 168 days was 106 mSv at solar minimum conditions. It is anticipated that space tourism vehicles will reach suborbital altitudes of approximately 100 km and, therefore, the annual occupational dose to flight crew during repeated transits is expected to fall somewhere between those observed for aircrew and astronauts. Unfortunately, measurements of the radiation environment at the high altitudes reached by suborbital vehicles are sparse, and modelling efforts have been similarly limited. In this paper, preliminary MCNPX radiation transport code simulations are developed of the secondary neutron flux profile in air from surface altitudes up to low Earth orbit at solar minimum conditions and excluding the effects of spacecraft shielding. These secondary neutrons are produced by galactic cosmic radiation interacting with Earth's atmosphere and are among the sources of radiation that can pose a health risk. Associated estimates of the operational neutron ambient dose equivalent, used for radiation protection purposes, and the neutron effective dose equivalent that is typically used for estimates of stochastic health risks, are provided in air. Simulations show that the neutron radiation dose rates received at suborbital altitudes are comparable to those experienced by aircrew flying at 7 to 14 km. We also show that the total neutron dose rate tails off beyond the Pfotzer maximum on ascension from surface up to low Earth orbit.

  18. Monte Carlo simulations of the secondary neutron ambient and effective dose equivalent rates from surface to suborbital altitudes and low Earth orbit.

    PubMed

    El-Jaby, Samy; Richardson, Richard B

    2015-07-01

    Occupational exposures from ionizing radiation are currently regulated for airline travel (<20 km) and for missions to low-Earth orbit (∼300-400 km). Aircrew typically receive between 1 and 6 mSv of occupational dose annually, while aboard the International Space Station, the area radiation dose equivalent measured over just 168 days was 106 mSv at solar minimum conditions. It is anticipated that space tourism vehicles will reach suborbital altitudes of approximately 100 km and, therefore, the annual occupational dose to flight crew during repeated transits is expected to fall somewhere between those observed for aircrew and astronauts. Unfortunately, measurements of the radiation environment at the high altitudes reached by suborbital vehicles are sparse, and modelling efforts have been similarly limited. In this paper, preliminary MCNPX radiation transport code simulations are developed of the secondary neutron flux profile in air from surface altitudes up to low Earth orbit at solar minimum conditions and excluding the effects of spacecraft shielding. These secondary neutrons are produced by galactic cosmic radiation interacting with Earth's atmosphere and are among the sources of radiation that can pose a health risk. Associated estimates of the operational neutron ambient dose equivalent, used for radiation protection purposes, and the neutron effective dose equivalent that is typically used for estimates of stochastic health risks, are provided in air. Simulations show that the neutron radiation dose rates received at suborbital altitudes are comparable to those experienced by aircrew flying at 7 to 14 km. We also show that the total neutron dose rate tails off beyond the Pfotzer maximum on ascension from surface up to low Earth orbit.

  19. Design, construction, test and field support of a containerless payload package for rocket flight. [electromagnetic heating and confinement

    NASA Technical Reports Server (NTRS)

    1977-01-01

    The performance of a device for electromagnetically heating and positioning containerless melts during space processing was evaluated during a 360 second 0-g suborbital sounding rocket flight. Components of the electromagnetic containerless processing package (ECPP), its operation, and interface with the rocket are described along with flight and qualification tests results.

  20. Suborbital Platforms as a Tool for a Symbiotic Relationship Between Scientists, Engineers, and Students

    NASA Technical Reports Server (NTRS)

    Chamberlin, Phillip C.

    2011-01-01

    Sounding rockets started in-situ space experimentation over 60 years ago with scientific experiments replacing warheads on captured V- 2 German rockets. Prior to this, and still today, suborbital platforms such as airplanes and high-altitude balloons have provided advantageous remote sensing observations advancing many areas of Earth and Space science. There is still a place for first-rate science in both stand-alone missions as well as providing complimentary measurements to the larger orbital missions. Along with the aforementioned science, the cost effectiveness and development times provided by sub-orbital platforms allows for perfect hands-on and first rate educational opportunities for undergraduate and graduate students. This talk will give examples and discuss the mutually beneficial opportunities that scientists and students obtain in development of suborbital missions. Also discussed will be how the next generation of space vehicles should help eliminate the number one obstacle to these programs - launch opportunities.

  1. 14 CFR Appendix D to Part 420 - Impact Dispersion Areas and Casualty Expectancy Estimate for an Unguided Suborbital Launch Vehicle

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Expectancy Estimate for an Unguided Suborbital Launch Vehicle D Appendix D to Part 420 Aeronautics and Space... LICENSE TO OPERATE A LAUNCH SITE Pt. 420, App. D Appendix D to Part 420—Impact Dispersion Areas and Casualty Expectancy Estimate for an Unguided Suborbital Launch Vehicle (a) Introduction (1) This...

  2. 14 CFR 440.11 - Duration of coverage for licensed launch, including suborbital launch, or permitted activities...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Duration of coverage for licensed launch, including suborbital launch, or permitted activities; modifications. 440.11 Section 440.11 Aeronautics and... Duration of coverage for licensed launch, including suborbital launch, or permitted...

  3. Tracking the Relative Motion of Four Space Payloads Launched from a Sub-Orbital NASA Rocket

    NASA Technical Reports Server (NTRS)

    Martell, Hugh; Bull, Barton

    1999-01-01

    One problem, which is comparatively new in the field of GPS applications, is the determination of the relative trajectories of space vehicles. Applications include the docking of spacecraft, collision avoidance in the area of space stations, and trajectory reconstruction of multiple payloads. The required precision in any of these applications will vary, according to the requirements of the task and abilities of GPS to cope with the environment and the dynamics. This paper describes the post-mission reconstruction of the relative trajectories of four GPS receivers attached to four payloads jettisoned from a Black Brant XII rocket. This vehicle was launched by the National Aeronautics and Space Administration (NASA) in January 1999 from the Poker Flats Research Range near Fairbanks, Alaska. The Black Brant XII is a sub-orbital rocket designed to carry payloads of 100 to 500 kg into the upper atmosphere. Flight time is generally in the order of 10-20 minutes. In this experiment, a GPS receiver and antenna was attached to each of the four payloads. One of the GPS receivers was assigned as the "base station", while the other 3 receivers were designated as remotes. GPS time, code and phase measurements were telemetered to a ground station for real-time processing and storage. The object of the mission was to re-compute the position and velocity of the remote units with respect to the base station during the launch phase and after the payloads separated. During the launch segment the 3 baseling distances between the 4 antennas are known from plans and are constant values until each payload is released. On the fly ambiguity determination was used to establish local coordinates from the base antenna to each of the other 3 GPS units during flight. Distance computations were made from the GPS-derived coordinates and compared to plan distances. Using this methodology an error analysis of the relative GPS accuracies has been presented and in addition a description given of the

  4. Three-dimensional Critical Wetting Experiment for Next-Gen Suborbital Flight

    NASA Astrophysics Data System (ADS)

    Collicott, Steven; Sharp, Lauren

    References: [1] Finn, R., "Capillary Surface Interfaces," Notices of the AMS, 46, No. 7, pp. 770-781, Aug., 1999. [2] Allen, J.S., Son, S.Y., Collicott, S.H., "Proton exchange membrane fuel cell (PEMFC) flow-field design for improved water management", Hdbk of Fuel Cell:, V5&6, Vielstich, W., Gasteiger, H.A., Yokokawa, H.(ed.). J country-regioncountry-regionWiley country-region& country-regionSons, country-regionUK, pp687-698, 2009. [3] Collicott, S. H., Weislogel, M. M., "Computing Existence and Stability of Capillary Surfaces using Surface Evolver," AIAA J, 42, pp. 289-295, Feb 2004. [4] Symons, E. P., Nussle, R. C., Abdalla, K. L., "Liquid Inflow to Initially Empty, Hemispher-ical Ended Cylinders During Weightlessness", NASA, TN-M628, 1968.

  5. Occupational Exposure to Ionizing Radiation for Crews of Suborbital Spacecraft: Questions and Answers

    DTIC Science & Technology

    2013-12-01

    Crewmembers, Ionizing Radiation, Galactic Cosmic Radiation, Solar Cosmic Radiation, Cancer Risk, Hereditary Risks, Radiation Exposure Limits Document is...higher altitudes. The dose to non-pregnant crewmembers could also have exceeded the recommended limit . A solar radiation alert system, developed by...Occupational Exposure to Ionizing Radiation for Crews of Suborbital Spacecraft : Questions & Answers Kyle Copeland Civil Aerospace Medical Institute

  6. Flexible imaging payload for real-time fluorescent biological imaging in parabolic, suborbital and space analog environments

    NASA Astrophysics Data System (ADS)

    Bamsey, Matthew T.; Paul, Anna-Lisa; Graham, Thomas; Ferl, Robert J.

    2014-10-01

    utilized to assess, in real-time, the response of plants to novel environments including various spaceflight analogs, including several parabolic flight environments as well as hypobaric plant growth chambers. Basic performance results obtained under these operational environments, as well as laboratory-based tests are described. The Flex Imager has also been designed to be compatible with emerging suborbital platforms.

  7. Growing Minority Student Interest in Earth and Space Science with Suborbital and Space-related Investigations

    NASA Astrophysics Data System (ADS)

    Austin, S. A.

    2009-12-01

    This presentation describes the transformative impact of student involvement in suborbital and Cubesat investigations under the MECSAT program umbrella at Medgar Evers College (MEC). The programs evolved from MUSPIN, a NASA program serving minority institutions. The MUSPIN program supported student internships for the MESSENGER and New Horizons missions at the Applied Physics Lab at John Hopkins University. The success of this program motivated the formation of smaller-scale programs at MEC to engage a wider group of minority students using an institutional context. The programs include an student-instrument BalloonSAT project, ozone investigations using sounding vehicles and a recently initiated Cubesat program involving other colleges in the City University of New York (CUNY). The science objectives range from investigations of atmospheric profiles, e.g. temperature, humidity, pressure, and CO2 to ozone profiles in rural and urban areas including comparisons with Aura instrument retrievals to ionospheric scintillation experiments for the Cubesat project. Through workshops and faculty collaborations, the evolving programs have mushroomed to include the development of parallel programs with faculty and students at other minority institutions both within and external to CUNY. The interdisciplinary context of these programs has stimulated student interest in Earth and Space Science and includes the use of best practices in retention and pipelining of underrepresented minority students in STEM disciplines. Through curriculum integration initiatives, secondary impacts are also observed supported by student blogs, social networking sites, etc.. The program continues to evolve including related student internships at Goddard Space Flight Center and the development of a CUNY-wide interdisciplinary team of faculty targeting research opportunities for undergraduate and graduate students in Atmospheric Science, Space Weather, Remote Sensing and Astrobiology primarily for

  8. Developing hybrid near-space technologies for affordable access to suborbital space

    NASA Astrophysics Data System (ADS)

    Badders, Brian David

    High power rockets and high altitude balloons are two near-space technologies that could be combined in order to provide access to the mesosphere and, eventually, suborbital space. This "rockoon" technology has been used by several large budget space programs before being abandoned in favor of even more expensive, albeit more accurate, ground launch systems. With the increased development of nano-satellites and atmospheric sensors, combined with rising interest in global atmospheric data, there is an increase in desire for affordable access to extreme altitudes that does not necessarily require the precision of ground launches. Development of hybrid near-space technologies for access to over 200k ft. on a small budget brings many challenges within engineering, systems integration, cost analysis, market analysis, and business planning. This research includes the design and simulation testing of all the systems needed for a safe and reusable launch system, the cost analysis for initial production, the development of a business plan, and the development of a marketing plan. This project has both engineering and scientific significance in that it can prove the space readiness of new technologies, raise their technology readiness levels (TRLs), expedite the development process, and also provide new data to the scientific community. It also has the ability to stimulate university involvement in the aerospace industry and help to inspire the next generation of workers in the space sector. Previous development of high altitude balloon/high power rocket hybrid systems have been undertaken by government funded military programs or large aerospace corporations with varying degrees of success. However, there has yet to be a successful flight with this type of system which provides access to the upper mesosphere in a university setting. This project will aim to design and analyze a viable system while testing the engineering process under challenging budgetary constraints. The

  9. New Platforms for Suborbital Astronomical Observations and In Situ Atmospheric Measurements: Spacecraft, Instruments, and Facilities

    NASA Astrophysics Data System (ADS)

    Rodway, K.; DeForest, C. E.; Diller, J.; Vilas, F.; Sollitt, L. S.; Reyes, M. F.; Filo, A. S.; Anderson, E.

    2014-12-01

    Suborbital astronomical observations have over 50 years' history using NASA's sounding rockets and experimental space planes. The new commercial space industry is developing suborbital reusable launch vehicles (sRLV's) to provide low-cost, flexible, and frequent access to space at ~100 km altitude. In the case of XCOR Aerospace's Lynx spacecraft, the vehicle design and capabilities work well for hosting specially designed experiments that can be flown with a human-tended researcher or alone with the pilot on a customized mission. Some of the first-generation instruments and facilities that will conduct solar observations on dedicated Lynx science missions include the SwRI Solar Instrument Pointing Platform (SSIPP) and Atsa Suborbital Observatory, as well as KickSat sprites, which are picosatellites for in situ atmospheric and solar phenomena measurements. The SSIPP is a demonstration two-stage pointed solar observatory that operates inside the Lynx cockpit. The coarse pointing stage includes the pilot in the feedback loop, and the fine stage stabilizes the solar image to achieve arcsecond class pointing. SSIPP is a stepping-stone to future external instruments that can operate with larger apertures and shorter wavelengths in the solar atmosphere. The Planetary Science Institute's Atsa Suborbital Observatory combines the strengths of ground-based observatories and space-based observing to create a facility where a telescope is maintained and used interchangeably with either in-house facility instruments or user-provided instruments. The Atsa prototype is a proof of concept, hand-guided camera that mounts on the interior of the Lynx cockpit to test target acquisition and tracking for human-operated suborbital astronomy. KickSat sprites are mass-producible, one inch printed circuit boards (PCBs) populated by programmable off the shelf microprocessors and radios for real time data transmission. The sprite PCBs can integrate chip-based radiometers, magnetometers

  10. Operations of Suborbital Research Platforms to Obtain Remote Sensing Data

    NASA Technical Reports Server (NTRS)

    Hines, Dennis O.

    2014-01-01

    The Armstrong Flight Research Center (AFRC) operates six highly modified aircraft in support the NASA science mission.These include two ER-2 aircraft, a DC-8, a G-III, and two Global Hawks. The NASA science missions demands that these aircraft be deployed around the globe while carrying a variety of science instruments. The ER-2 reconnaissance aircraft provides routine access to altitudes over 70,000 ft (20km) for large payloads and with an endurance of over 10hours. Recently the ER-2s have conducted convective storm research missions in the mid-western United States and supported the development of new instruments. The DC-8 is a four-engine jetliner that operates for up to 12 hours ataltitudes that range from the surface to 42,000 ft (13 km). Although its flight envelope is equivalent to conventional.

  11. CAMUI Type Hybrid Rocket as Small Scale Ballistic Flight Testbed

    NASA Astrophysics Data System (ADS)

    Nagata, Harunori; Uematsu, Tsutomu; Ito, Kenichi

    The authors have been developing CAMUI (Cascaded Multistage Impinging-jet) type hybrid rockets, explosive-flee small rocket motors. This is to downsize the scale of suborbital flight experiments on space related technology development. A key idea is a new fuel grain design to increase gasification rates of a solid fuels. By the new fuel grain design, the combustion gas repeatedly impinges on fuel surfaces to hasten the heat transfer to the fuel. Suborbital flight experiments by sounding rockets provide variety of test beds to accumulate basic technologies common to the next step of space development in Japan. By using hybrid rockets one can take the cost advantage of small-scale rocket experiments. This cost advantage improves robustness of space technology development projects by dispersion of risk.

  12. Flight project data book, 1991

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The Office of Space Science and Applications (OSSA) is responsible for planning, directing, executing, and evaluating that part of the overall NASA program that has as its goal the use of the unique characteristics of the space environment to conduct a scientific study of the universe, to solve practical problems on Earth, and to provide the scientific research foundation for expanding human presence beyond Earth into the solar system. OSSA manages the development of NASA's flight instrumentation for space science and applications including free flying spacecraft, Shuttle and Space Station payloads, and the suborbital sounding rockets, balloons, and aircraft programs. A summary is provided of future flight missions, including those approved and currently under development and those which appear in the OSSA strategic plan.

  13. Flight Project Data Book

    NASA Technical Reports Server (NTRS)

    1992-01-01

    The Office of Space Science and Applications (OSSA) is responsible for the overall planning, directing, executing, and evaluating that part of the overall NASA program that has the goal of using the unique characteristics of the space environment to conduct a scientific study of the universe, to understand how the Earth works as an integrated system, to solve practical problems on Earth, and to provide the scientific and technological research foundation for expanding human presence beyond Earth orbit into the solar system. OSSA guides its program toward leadership through its pursuit of excellence across the full spectrum of disciplines. OSSA pursues these goals through an integrated program of ground-based laboratory research and experimentation, suborbital flight of instruments on airplanes, balloons, and sounding rockets; flight of instruments and the conduct of research on the Shuttle/Spacelab system and on Space Station Freedom; and development and flight of automated Earth-orbiting and interplanetary spacecraft. The OSSA program is conducted with the participation and support of other Government agencies and facilities, universities throughout the United States, the aerospace contractor community, and all of NASA's nine Centers. In addition, OSSA operates with substantial international participation in many aspects of our Space Science and Applications Program. OSSA's programs currently in operation, those approved for development, and those planned for future missions are described.

  14. Suborbital Soft X-Ray Spectroscopy with Gaseous Electron Multipliers

    NASA Astrophysics Data System (ADS)

    Rogers, Thomas D.

    This thesis consists of the design, fabrication, and launch of a sounding rocket payload to observe the spectrum of the soft X-ray emission (0.1-1 keV) from the Cygnus Loop supernova remnant. This instrument, designated the Off-plane Grating Rocket for Extended Source Spectroscopy (OGRESS), was launched from White Sands Missile Range on May 2nd, 2015. The X-ray spectrograph incorporated a wire-grid focuser feeding an array of gratings in the extreme off-plane mount which dispersed the spectrum onto Gaseous Electron Multiplier (GEM) detectors. The gain characteristics of OGRESS's GEM detectors were fully characterized with respect to applied voltage and internal gas pressure, allowing operational settings to be optimized. The GEMs were optimized to operate below laboratory atmospheric pressure, allowing lower applied voltages, thus reducing the risk of both electrical arcing and tearing of the thin detector windows. The instrument recorded 388 seconds of data and found highly uniform count distributions over both detector faces, in sharp contrast to the expected thermal line spectrum. This signal is attributed to X-ray fluorescence lines generated inside the spectrograph. The radiation is produced when thermal ionospheric particles are accelerated into the interior walls of the spectrograph by the high voltages of the detector windows. A fluorescence model was found to fit the flight data better than modeled supernova spectra. Post-flight testing and analysis revealed that electrons produce distinct signal on the detectors which can also be successfully modeled as fluorescence emission.

  15. SPIDER: probing the early Universe with a suborbital polarimeter

    SciTech Connect

    Fraisse, A.A.; Chiang, H.C.; Ade, P.A.R.; Amiri, M.; Burger, B.; Davis, G.; Benton, S.J.; Bock, J.J.; Crill, B.P.; Doré, O.; Filippini, J.P.; Golwala, S.; Bond, J.R.; Farhang, M.; Bonetti, J.A.; Bryan, S.; Clark, C.N.; Contaldi, C.R.; Fissel, L.M.; Gandilo, N.N.; and others

    2013-04-01

    We evaluate the ability of SPIDER, a balloon-borne polarimeter, to detect a divergence-free polarization pattern (B-modes) in the cosmic microwave background (CMB). In the inflationary scenario, the amplitude of this signal is proportional to that of the primordial scalar perturbations through the tensor-to-scalar ratio r. We show that the expected level of systematic error in the SPIDER instrument is significantly below the amplitude of an interesting cosmological signal with r = 0.03. We present a scanning strategy that enables us to minimize uncertainty in the reconstruction of the Stokes parameters used to characterize the CMB, while accessing a relatively wide range of angular scales. Evaluating the amplitude of the polarized Galactic emission in the SPIDER field, we conclude that the polarized emission from interstellar dust is as bright or brighter than the cosmological signal at all SPIDER frequencies (90 GHz, 150 GHz, and 280 GHz), a situation similar to that found in the ''Southern Hole.'' We show that two ∼ 20-day flights of the SPIDER instrument can constrain the amplitude of the B-mode signal to r < 0.03 (99% CL) even when foreground contamination is taken into account. In the absence of foregrounds, the same limit can be reached after one 20-day flight.

  16. Consort 1 flight results: a synopsis

    NASA Technical Reports Server (NTRS)

    Wessling, F. C.; Lundquist, C. A.; Maybee, G. W.

    1990-01-01

    Consort 1 was the first low gravity materials processing payload to be launched by a commercially licensed rocket in the U.S.A. It carried six experiments which operated as planned during approx. 7 min of suborbital, low gravity flight (10(-5) g) and were returned in excellent condition to the investigators within 4 h of launch. Nearly 150 physical samples supported by measurements and photographs made during the flight were obtained for analysis. In addition to the experimental data returned, the success of Consort 1 demonstrated the ability of industry, working with university centers and government agencies, to rapidly prepare and launch payloads. A brief description of the rocket flight and payload configuration is given. Experiment objectives and methods are described and preliminary results and conclusions are presented.

  17. Ares I-X: First Flight of a New Generation

    NASA Technical Reports Server (NTRS)

    Davis, Stephan R.; Askins, Bruce R.

    2010-01-01

    The Ares I-X suborbital development flight test demonstrated NASA s ability to design, develop, launch and control a new human-rated launch vehicle (Figure 14). This hands-on missions experience will provide the agency with necessary skills and insights regardless of the future direction of space exploration. The Ares I-X team, having executed a successful launch, will now focus on analyzing the flight data and extracting lessons learned that will be used to support the development of future vehicles.

  18. Flight Programs and X-ray Optics Development at MSFC

    NASA Technical Reports Server (NTRS)

    Gubarev, M.; Ramsey, B.; O'Dell, S. L.; Elsner, R.; Kilaru, K.; Atkins, C.; Swartz, D.; Gaskin, J.; Weisskopf, Martin

    2012-01-01

    The X-ray astronomy group at the Marshall Space Flight Center is developing electroformed nickel/cobalt x-ray optics for suborbital and orbital experiments. Suborbital instruments include the Focusing X-ray Solar Imager (FOXSI) and Micro-X sounding rocket experiments and the HERO balloon payload. Our current orbital program is the fabrication of a series of mirror modules for the Astronomical Roentgen Telescope (ART) to be launched on board the Russian-German Spectrum Roentgen Gamma Mission (SRG.) The details and status of these various programs are presented. A second component of our work is the development of fabrication techniques and optical metrology to improve the angular resolution of thin shell optics to the arcsecond-level. The status of these x-ray optics technology developments is also presented.

  19. Point-to-point sub-orbital space tourism: Some initial considerations

    NASA Astrophysics Data System (ADS)

    Webber, Derek

    2010-06-01

    Several public statements have been made about the possible, or even likely, extension of initial sub-orbital space tourism operations to encompass point-to-point travel. It is the purpose of this paper to explore some of the basic considerations for such a plan, in order to understand both its merits and its problems. The paper will discuss a range of perspectives, from basic physics to market segmentation, from ground segment logistics to spacecraft design considerations. It is important that these initial considerations are grasped before more detailed planning and design takes place.

  20. 14 CFR 417.233 - Analysis for an unguided suborbital launch vehicle flown with a wind weighting safety system.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... vehicle flown with a wind weighting safety system. 417.233 Section 417.233 Aeronautics and Space... with a wind weighting safety system. For each launch of an unguided suborbital launch vehicle flown with a wind weighting safety system, in addition to the other requirements in this subpart outlined...

  1. 14 CFR 417.233 - Analysis for an unguided suborbital launch vehicle flown with a wind weighting safety system.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... vehicle flown with a wind weighting safety system. 417.233 Section 417.233 Aeronautics and Space... with a wind weighting safety system. For each launch of an unguided suborbital launch vehicle flown with a wind weighting safety system, in addition to the other requirements in this subpart outlined...

  2. 14 CFR 417.233 - Analysis for an unguided suborbital launch vehicle flown with a wind weighting safety system.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... vehicle flown with a wind weighting safety system. 417.233 Section 417.233 Aeronautics and Space... with a wind weighting safety system. For each launch of an unguided suborbital launch vehicle flown with a wind weighting safety system, in addition to the other requirements in this subpart outlined...

  3. 14 CFR 417.233 - Analysis for an unguided suborbital launch vehicle flown with a wind weighting safety system.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... vehicle flown with a wind weighting safety system. 417.233 Section 417.233 Aeronautics and Space... with a wind weighting safety system. For each launch of an unguided suborbital launch vehicle flown with a wind weighting safety system, in addition to the other requirements in this subpart outlined...

  4. 14 CFR 417.233 - Analysis for an unguided suborbital launch vehicle flown with a wind weighting safety system.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... vehicle flown with a wind weighting safety system. 417.233 Section 417.233 Aeronautics and Space... with a wind weighting safety system. For each launch of an unguided suborbital launch vehicle flown with a wind weighting safety system, in addition to the other requirements in this subpart outlined...

  5. 14 CFR Appendix D to Part 420 - Impact Dispersion Areas and Casualty Expectancy Estimate for an Unguided Suborbital Launch Vehicle

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... Expectancy Estimate for an Unguided Suborbital Launch Vehicle D Appendix D to Part 420 Aeronautics and Space... LICENSE TO OPERATE A LAUNCH SITE Pt. 420, App. D Appendix D to Part 420—Impact Dispersion Areas and... vehicle stages on maps in accordance with paragraph (b)(2). ER19Oc00.113 (d) Evaluate the...

  6. 14 CFR Appendix D to Part 420 - Impact Dispersion Areas and Casualty Expectancy Estimate for an Unguided Suborbital Launch Vehicle

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Expectancy Estimate for an Unguided Suborbital Launch Vehicle D Appendix D to Part 420 Aeronautics and Space... LICENSE TO OPERATE A LAUNCH SITE Pt. 420, App. D Appendix D to Part 420—Impact Dispersion Areas and... vehicle stages on maps in accordance with paragraph (b)(2). ER19Oc00.113 (d) Evaluate the...

  7. Suborbital Reusable Launch Vehicles as an Opportunity to Consolidate and Calibrate Ground Based and Satellite Instruments

    NASA Astrophysics Data System (ADS)

    Papadopoulos, K.

    2014-12-01

    XCOR Aerospace, a commercial space company, is planning to provide frequent, low cost access to near-Earth space on the Lynx suborbital Reusable Launch Vehicle (sRLV). Measurements in the external vacuum environment can be made and can launch from most runways on a limited lead time. Lynx can operate as a platform to perform suborbital in situ measurements and remote sensing to supplement models and simulations with new data points. These measurements can serve as a quantitative link to existing instruments and be used as a basis to calibrate detectors on spacecraft. Easier access to suborbital data can improve the longevity and cohesiveness of spacecraft and ground-based resources. A study of how these measurements can be made on Lynx sRLV will be presented. At the boundary between terrestrial and space weather, measurements from instruments on Lynx can help develop algorithms to optimize the consolidation of ground and satellite based data as well as assimilate global models with new data points. For example, current tides and the equatorial electrojet, essential to understanding the Thermosphere-Ionosphere system, can be measured in situ frequently and on short notice. Furthermore, a negative-ion spectrometer and a Faraday cup, can take measurements of the D-region ion composition. A differential GPS receiver can infer the spatial gradient of ionospheric electron density. Instruments and optics on spacecraft degrade over time, leading to calibration drift. Lynx can be a cost effective platform for deploying a reference instrument to calibrate satellites with a frequent and fast turnaround and a successful return of the instrument. A calibrated reference instrument on Lynx can make collocated observations as another instrument and corrections are made for the latter, thus ensuring data consistency and mission longevity. Aboard a sRLV, atmospheric conditions that distort remotely sensed data (ground and spacecraft based) can be measured in situ. Moreover, an

  8. Ares I-X: First Flight of a New Era

    NASA Technical Reports Server (NTRS)

    Davis, Stephen R.; Askins, Bruce R.

    2010-01-01

    Since 2005, NASA s Constellation Program has been designing, building, and testing the next generation of launch and space vehicles to carry humans beyond low-Earth orbit (LEO). The Ares Projects at Marshall Space Flight Center (MSFC) are developing the Ares I crew launch vehicle and Ares V cargo launch vehicle. On October 28, 2009, the first development flight test of the Ares I crew launch vehicle, Ares I-X, lifted off from a launch pad at Kennedy Space Center (KSC) on successful suborbital flight. Basing exploration launch vehicle designs on Ares I-X information puts NASA one step closer to full-up "test as you fly," a best practice in vehicle design. Although the final Constellation Program architecture is under review, the Ares I-X data and experience in vehicle design and operations can be applied to any launch vehicle. This paper presents the mission background as well as results and lessons learned from the flight.

  9. Data Management Challenges for Airborne NASA Earth Venture Sub-Orbital Investigations

    NASA Astrophysics Data System (ADS)

    Boyer, A.; Lindsley, C.; Wright, D.; Cook, R. B.; Santhana Vannan, S. K.

    2015-12-01

    The Oak Ridge National Laboratory (ORNL) Distributed Active Archive Center (DAAC) is developing technology infrastructure to archive airborne remote sensing observations from two of NASA's Earth Venture Sub-orbital Missions. The two missions are CARVE (Carbon in Arctic Reservoirs Vulnerability Experiment) and AirMOSS (Airborne Microwave Observatory of Subcanopy and Subsurface). These missions collected over 140 TB of data from extensive ground-based and airborne instruments. The metadata and documentation requirements necessary for proper archive and dissemination of such transect-based, and often 3-dimensional, airborne data are quite different from traditional field campaign data and satellite remote sensing data streams. Staff at the ORNL DAAC have developed a metadata and data infrastructure for airborne data that enables spatial or keyword-based search and discovery, integration of related satellite- or ground-based data sets, and subsetting and visualization tools for both CARVE and AirMOSS. Here we discuss challenges, progress, and lessons learned.

  10. Tracking the Relative Motion of Four Space Payloads Launched From a Sub-Orbital NASA Rocket

    NASA Technical Reports Server (NTRS)

    Martel, Hugh; Bull, Barton

    1999-01-01

    One problem, which is comparatively new in the field of GPS applications, is the determination of the relative trajectories of space vehicles. Applications include the docking of spacecraft, collision avoidance in the area of space stations, and trajectory reconstruction of multiple payloads. The required precision in any of these applications will vary, according to the requirements of the task and abilities of GPS to cope with the environment and the dynamics. This paper describes the post-mission reconstruction of the relative trajectories of four GPS receivers attached to four payloads jettisoned from a rocket in a sub-orbital NASA science mission. It is shown that the sub-decimetre level were achieved with single frequency GPS receivers.

  11. The opto-mechanical design of the sub-orbital local interstellar cloud experiment (SLICE)

    NASA Astrophysics Data System (ADS)

    Kane, Robert; Nell, Nicholas; Schultz, Ted; France, Kevin; Beasley, Matthew; Burgh, Eric; Bushinsky, Rachel; Hoadley, Keri

    2013-09-01

    We present the fabrication and testing of the Sub-orbital Local Interstellar Cloud Experiment (SLICE), a rocket-borne payload for ultraviolet astrophysics in the 1020 to 1070 Å bandpass. The SLICE optical system is composed of an ultraviolet-optimized telescope feeding a Rowland Circle spectrograph. The telescope is an 8-inch Classical Cassegrain operating at F/7, with Al optics overcoated with LiF for enhanced far-ultraviolet reflectivity. The holographically-ruled grating focuses light at an open-faced microchannel plate detector employing an opaque RbBr photocathode. In this proceeding, we describe the design trades and calibration issues confronted during the build-up of this payload. We place particular emphasis on the technical details of the design, modifications, construction, and alignment procedures for SLICE in order to provide a roadmap for the optimization of future ruggedized experiments for ultraviolet imaging and spectroscopy.

  12. Focal plane actuation for the development of a high resolution suborbital telescope

    NASA Astrophysics Data System (ADS)

    Duke Miller, Alex; Scowen, Paul A.; Veach, Todd

    2016-01-01

    We present a hexapod stabilized focal plane as the key instrument for a proposed suborbital balloon mission. Balloon gondolas currently achieve 1-2 arcsecond pointing error, but cannot correct for unavoidable jitter movements (~50μm at 20hz) caused by wind rushing over balloon surfaces, thermal variations, cryocoolers, and reaction wheels. The jitter causes image blur during exposures and is the limiting resolution of the system. To solve this, the hexapod system actuates the focal plane to counteract the jitter through real-time closed loop feedback from star-trackers. Removal of this final jitter term decreases pointing error by an order of magnitude and allows for true diffraction-limited observation. This boost in resolution will allow for Hubble-quality imaging for a fraction of the cost. Tip-tilt pointing systems have been used for these purposes in the past, but require additional optics and introduce multiple reflections. The hexapod system, rather, is compact and can be plugged into the focal point of nearly any configuration. The design also thermally isolates the hexapod from the cryogenic focal plane enabling the use of well-established non-cryogenic hexapod technology. High-resolution time domain multispectral imaging of the gas giant outer planets, especially in the UV range, is of particular interest to the planetary community, and a suborbital telescope with the hexapod stabilization in place would provide a wealth of new data. On an Antarctic ~100-day Long-Duration-Balloon mission the continued high-resolution imaging of gas giant storm systems would provide cloud formation and evolution data second to only a Flagship orbiter.

  13. The Texas space flight liability act and efficient regulation for the private commercial space flight era

    NASA Astrophysics Data System (ADS)

    Johnson, Christopher D.

    2013-12-01

    In the spring of 2011, the American state of Texas passed into law an act limiting the liability of commercial space flight entities. Under it, those companies would not be liable for space flight participant injuries, except in cases of intentional injury or injury proximately caused by the company's gross negligence. An analysis within the framework of international and national space law, but especially informed by the academic discipline of law and economics, discusses the incentives of all relevant parties and attempts to understand whether the law is economically "efficient" (allocating resources so as to yield maximum utility), and suited to further the development of the fledgling commercial suborbital tourism industry. Insights into the Texas law are applicable to other states hoping to foster commercial space tourism and considering space tourism related legislation.

  14. Zero Gravity Flights as the Most Effective Embryonic Operation for Planned Commercial Spaceport

    NASA Astrophysics Data System (ADS)

    Abu Samah, Shamsul Kamar; Ridzuan Zakaria, Norul; Nasrun, Nasri; Abu, Jalaluddin; Muszaphar Shukor, Dato'Sheikh

    2013-09-01

    From the experience gained by the management team of Spaceport Malaysia, a popular service that can be provided by a planned commercial spaceport in a country without existing space travel infrastructure are zero gravity flights. Zero gravity flights range from parabolic flights using aerobatic airplane to suborbital flights using rockets, and in the near future using suborbital rocketplanes. Therefore, zero gravity flights can be operated from a certified runway or planned for operation at a future commercial spaceport. With such range of operation, zero gravity flights provide a natural link between a low cost operation of small airplane to exclusive high profile operation of suborbital rocketplane, and this attracts the attention of individuals and organizations that are planning for the establishment of a commercial spaceport. This is the approach chosen by the planners and developers of Spaceport Malaysia. A significant factor in zero gravity flight is the zero gravity time, the period where the payload onboard the airplane or rocketplane will experience zero gravity. Based on the momentum of the airplane or rocketplane, the zero gravity time may vary from few seconds to few minutes and that determines the quality of the zero gravity flight. To achieve zero gravity, the airplane or rocketplane will fly with a steady velocity for a significant time as a gravity control flight, accelerate upwards with an angle producing hypergravity and perform parabolic flight with natural momentum producing zero gravity and followed by dive that will result in another hypergravity flight. 2 zero gravity platforms being considered for operation at and by Spaceport Malaysia are F-5E Tiger II and Airbus A300, since both platforms have been successfully used by a partner of Spaceport Malaysia in performing zero gravity flights. An F-5E fighter jet owned by Royal Malaysian Air Force is being planned to be converted into a zero gravity platform to be operated at and by Spaceport

  15. 14 CFR Appendix C to Part 417 - Flight Safety Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... population database for the region being evaluated or by estimating the current population using exponential population growth rate equations applied to the most current historical data available. The population...

  16. 14 CFR Appendix C to Part 417 - Flight Safety Analysis Methodologies and Products for an Unguided Suborbital Launch Vehicle Flown...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ...), through the licensing process, that an alternate method provides an equivalent level of fidelity. C417...; (iii) All location errors; and (iv) Launch azimuth and elevation. (2) Reference ellipsoidal Earth model, as follows— (i) Name of the Earth model employed; (ii) Semi-major axis; (iii) Semi-minor axis;...

  17. Focal plane actuation by hexapod for the development of a high-resolution suborbital telescope

    NASA Astrophysics Data System (ADS)

    Miller, Alexander D.; Scowen, Paul A.; Veach, Todd J.

    2016-07-01

    We present a prototype hexapod image stabilization system as the key instrument for a proposed suborbital balloon mission. The unique design thermally isolates an off-the-shelf non-cryogenic hexapod from a liquid nitrogen cooled focal plane, enabling its use in a cryogenic environment. Balloon gondolas currently achieve 1-2 arcsecond pointing error, but cannot correct for unavoidable jitter movements ( 20 micron amplitude at 20 Hz at the worst) caused by wind rushing over balloon surfaces, thermal variations, and vibrations from cryocoolers, and reaction wheels. The jitter causes image blur during exposures and limits the resolution of the system. Removal of this final jitter term decreases pointing error by an order of magnitude and allows for true diffraction-limited observation. Tip-tilt pointing systems have been used for these purposes in the past, but require additional optics and introduce multiple reflections. The hexapod system, rather, is compact and can be plugged into the focal point of nearly any configuration. For a 0.8m telescope the improvement in resolution by this system would provide 0.1" angular resolution at 300nm, which is comparable to Hubble for a fraction of the cost. On an actual balloon, the hexapod system would actuate the focal plane to counteract the jitter using position information supplied by guidestar cameras. However, in the lab, we instead simulate guide camera tracking, using a 1024 × 1024 e2v science-grade CCD to take long exposures of a target attached to an XY stage driven with the balloon jitter signal recorded during the STO mission. Further confirmation of the positional accuracy and agility of the hexapod is achieved using a laser and fast-sampling position-sensitive diode. High-resolution time domain multispectral imaging of the gas giants, especially in the UV range, is of particular interest to the planetary community, and a suborbital telescope with the hexapod stabilization in place would provide a wealth of new

  18. Upper-Stage Flight Experiment

    NASA Technical Reports Server (NTRS)

    Anderson, W. E.; Boxwell, R.; Crockett, D. V.; Ross, R.; Lewis, T.; McNeal, C.; Verdarame, K.

    1999-01-01

    For propulsion applications that require that the propellants are storable for long periods, have a high density impulse, and are environmentally clean and non-toxic, the best choice is a combination of high-concentration hydrogen peroxide (High Test Peroxide, or HTP) and a liquid hydrocarbon (LHC) fuel. The HTP/LHC combination is suitable for low-cost launch vehicles, space taxi and space maneuvering vehicles, and kick stages. Orbital Sciences Corporation is under contract with the NASA Marshall Space Flight Center in cooperation with the Air Force Research Lab to design, develop and demonstrate a new low-cost liquid upper stage based on HTP and JP-8. The Upper Stage Flight Experiment (USFE) focuses on key technologies necessary to demonstrate the operation of an inherently simple propulsion system with an innovative, state-of-the-art structure. Two key low-cost vehicle elements will be demonstrated - a 10,000 lbf thrust engine and an integrated composite tank structure. The suborbital flight test of the USFE is scheduled for 2001. Preceding the flight tests are two major series of ground tests at NASA Stennis Space Center and a subscale tank development program to identify compatible composite materials and to verify their compatibility over long periods of time. The ground tests include a thrust chamber development test series and an integrated stage test. This paper summarizes the results from the first phase of the thrust chamber development tests and the results to date from the tank material compatibility tests. Engine and tank configurations that meet the goals of the program are described.

  19. A Chimpanzee, 'Ham,' in the Biopack Couch for the MR-2 Flight

    NASA Technical Reports Server (NTRS)

    1961-01-01

    A three-year-old chimpanzee, named Ham, in the biopack couch for the MR-2 suborbital test flight. On January 31, 1961, a Mercury-Redstone launch from Cape Canaveral carried the chimpanzee 'Ham' over 640 kilometers down range in an arching trajectory that reached a peak of 254 kilometers above the Earth. The mission was successful and Ham performed his lever-pulling task well in response to the flashing light. NASA used chimpanzees and other primates to test the Mercury Capsule before launching the first American astronaut Alan Shepard in May 1961. The successful flight and recovery confirmed the soundness of the Mercury-Redstone systems.

  20. Strong coupling of Asian Monsoon and Antarctic climates on sub-orbital timescales

    NASA Astrophysics Data System (ADS)

    Chen, Shitao; Wang, Yongjin; Cheng, Hai; Edwards, R. Lawrence; Wang, Xianfeng; Kong, Xinggong; Liu, Dianbing

    2016-09-01

    There is increasing evidence that millennial-scale climate variability played an active role on orbital-scale climate changes, but the mechanism for this remains unclear. A 230Th-dated stalagmite δ18O record between 88 and 22 thousand years (ka) ago from Yongxing Cave in central China characterizes changes in Asian monsoon (AM) strength. After removing the 65°N insolation signal from our record, the δ18O residue is strongly anti-phased with Antarctic temperature variability on sub-orbital timescales during the Marine Isotope Stage (MIS) 3. Furthermore, once the ice volume signal from Antarctic ice core records were removed and extrapolated back to the last two glacial-interglacial cycles, we observe a linear relationship for both short- and long-duration events between Asian and Antarctic climate changes. This provides the robust evidence of a link between northern and southern hemisphere climates that operates through changes in atmospheric circulation. We find that the weakest monsoon closely associated with the warmest Antarctic event always occurred during the Terminations. This finding, along with similar shifts in the opal flux record, suggests that millennial-scale events play a key role in driving the deglaciation through positive feedbacks associated with enhanced upwelling and increasing CO2.

  1. Strong coupling of Asian Monsoon and Antarctic climates on sub-orbital timescales.

    PubMed

    Chen, Shitao; Wang, Yongjin; Cheng, Hai; Edwards, R Lawrence; Wang, Xianfeng; Kong, Xinggong; Liu, Dianbing

    2016-09-08

    There is increasing evidence that millennial-scale climate variability played an active role on orbital-scale climate changes, but the mechanism for this remains unclear. A (230)Th-dated stalagmite δ(18)O record between 88 and 22 thousand years (ka) ago from Yongxing Cave in central China characterizes changes in Asian monsoon (AM) strength. After removing the 65°N insolation signal from our record, the δ(18)O residue is strongly anti-phased with Antarctic temperature variability on sub-orbital timescales during the Marine Isotope Stage (MIS) 3. Furthermore, once the ice volume signal from Antarctic ice core records were removed and extrapolated back to the last two glacial-interglacial cycles, we observe a linear relationship for both short- and long-duration events between Asian and Antarctic climate changes. This provides the robust evidence of a link between northern and southern hemisphere climates that operates through changes in atmospheric circulation. We find that the weakest monsoon closely associated with the warmest Antarctic event always occurred during the Terminations. This finding, along with similar shifts in the opal flux record, suggests that millennial-scale events play a key role in driving the deglaciation through positive feedbacks associated with enhanced upwelling and increasing CO2.

  2. A Suborbital Payload for Soft X-ray Spectroscopy of Extended Sources

    NASA Astrophysics Data System (ADS)

    Oakley, Phillip Henry Howard

    This thesis details the intent, design and results of an X-ray suborbital rocket payload whose scientific target was the Cygnus Loop Supernova Remnant. The payload consists of wire grid collimators, off-plane gratings arrays and gaseous electron multiplier (GEM) detectors. The system was designed for measurements in the 17-107 Å bandpass with a resolution up to ∼ 60 (λ=Δλ). This instrument was christened the Extended X-ray Off-plane Spectrometer (EXOS) and was launched on a Terrier-Black Brant rocket on November 13th, 2009 from White Sands Missile Range and obtained 340 seconds of useable scientific data. The emission is dominated by O VII and O VIII, including the He-like O VII triplet at ∼22 Å. Another feature at ∼45 Å is composed primarily of Si XI and Si XII. The best-fit model to this spectrum is an equilibrium plasma model at a temperature of log(T) = 6.4 (0.23 keV).

  3. Strong coupling of Asian Monsoon and Antarctic climates on sub-orbital timescales

    PubMed Central

    Chen, Shitao; Wang, Yongjin; Cheng, Hai; Edwards, R. Lawrence; Wang, Xianfeng; Kong, Xinggong; Liu, Dianbing

    2016-01-01

    There is increasing evidence that millennial-scale climate variability played an active role on orbital-scale climate changes, but the mechanism for this remains unclear. A 230Th-dated stalagmite δ18O record between 88 and 22 thousand years (ka) ago from Yongxing Cave in central China characterizes changes in Asian monsoon (AM) strength. After removing the 65°N insolation signal from our record, the δ18O residue is strongly anti-phased with Antarctic temperature variability on sub-orbital timescales during the Marine Isotope Stage (MIS) 3. Furthermore, once the ice volume signal from Antarctic ice core records were removed and extrapolated back to the last two glacial-interglacial cycles, we observe a linear relationship for both short- and long-duration events between Asian and Antarctic climate changes. This provides the robust evidence of a link between northern and southern hemisphere climates that operates through changes in atmospheric circulation. We find that the weakest monsoon closely associated with the warmest Antarctic event always occurred during the Terminations. This finding, along with similar shifts in the opal flux record, suggests that millennial-scale events play a key role in driving the deglaciation through positive feedbacks associated with enhanced upwelling and increasing CO2. PMID:27605015

  4. H{sub 2} EXCITATION STRUCTURE ON THE SIGHTLINES TO {delta} SCORPII AND {zeta} OPHIUCI: FIRST RESULTS FROM THE SUB-ORBITAL LOCAL INTERSTELLAR CLOUD EXPERIMENT

    SciTech Connect

    France, Kevin; Nell, Nicholas; Kane, Robert; Green, James C.; Burgh, Eric B.

    2013-07-20

    We present the first science results from the Sub-orbital Local Interstellar Cloud Experiment (SLICE): moderate resolution 1020-1070 A spectroscopy of four sightlines through the local interstellar medium. High signal-to-noise (S/N) spectra of {eta} Uma, {alpha} Vir, {delta} Sco, and {zeta} Oph were obtained during a 2013 April 21 rocket flight. The SLICE observations constrain the density, molecular photoexcitation rates, and physical conditions present in the interstellar material toward {delta} Sco and {zeta} Oph. Our spectra indicate a factor of two lower total N(H{sub 2}) than previously reported for {delta} Sco, which we attribute to higher S/N and better scattered light control in the new SLICE observations. We find N(H{sub 2}) = 1.5 Multiplication-Sign 10{sup 19} cm{sup -2} on the {delta} Sco sightline, with kinetic and excitation temperatures of 67 and 529 K, respectively, and a cloud density of n{sub H} = 56 cm{sup -3}. Our observations of the bulk of the molecular sightline toward {zeta} Oph are consistent with previous measurements (N(H{sub 2}) Almost-Equal-To 3 Multiplication-Sign 10{sup 20} cm{sup -2} at T{sub 01}(H{sub 2}) = 66 K and T{sub exc} = 350 K). However, we detect significantly more rotationally excited H{sub 2} toward {zeta} Oph than previously observed. We infer a cloud density in the rotationally excited component of n{sub H} Almost-Equal-To 7600 cm{sup -3} and suggest that the increased column densities of excited H{sub 2} are a result of the ongoing interaction between {zeta} Oph and its environment; also manifest as the prominent mid-IR bowshock observed by WISE and the presence of vibrationally excited H{sub 2} molecules observed by the Hubble Space Telescope.

  5. The X-33 Flight Test Challenge

    NASA Technical Reports Server (NTRS)

    Borden, David; Ramiscal, Ermin; Howell, John

    1999-01-01

    Low cost access to space has eluded present launch system technologies. Our objective is to reduce the cost of putting a payload into space from $10,000 per pound to $1000 per pound. In July 1996, a cooperative agreement was initiated between the Lockheed Martin Skunk Works and NASA to help accomplish this goal. The X-33 is the first step in the process to make low cost space access a reality. The X-33 is a suborbital, hypersonic lifting body, proof of concept of a reusable launch vehicle. The X-33 flight test program will validate technologies such as a metallic thermal protection system, Linear Aerospike Engines, use of tanks and struts as fundamental structural elements, as well as quick turnaround time. Flight testing will begin in July 2000, with launches originating from Edwards Air Force Base and initial landings at Michael Army Airfield in Utah. Data collected from these flight tests will aid in the decision to build an economically viable single stage to orbit reusable launch vehicle. This paper will explore the technical challenges facing the X-33 Flight Test Team.

  6. B-SSIPP: A Miniature Solar Observatory for Rocket or Balloon Flight

    NASA Astrophysics Data System (ADS)

    DeForest, Craig; Laurent, Glenn Thomas; Diller, Jed; Brownsberger, Judy

    2016-05-01

    The Southwest Solar Instrument Pointing Package (SSIPP) is a miniature solar observatory for flight application. Conceived as a way to lower barriers to entry to spaceflight, SSIPP conditions a broadband solar beam for use by an IR, visible, or UV instrument on an optical table -- just as do ground-based observatories. The beam is conditioned by a closed-loop tip/tilt pointing system that can lock onto the Sun over a 20° cone of angles, and maintain arcsecond-class pointing from a dynamic flight platform. SSIPP was originally conceived as an instrument platform for the XCOR Lynx suborbital sportsrocket. It has been adapted for ballloon flight, incorporating a novel coarse pointing system that measures torsional pendulation in-flight to construct a stable pointing law on-the-fly. First flight is projected for June 2016 (shortly after SPD). We present status, major design elements, and future plans for the platform.

  7. Laser- and Radar-based Mission Concepts for Suborbital and Spaceborne Monitoring of Seismic Surface Waves

    SciTech Connect

    Foxall, W; Schultz, C A; Tralli, D M

    2004-09-21

    The development of a suborbital or spaceborne system to monitor seismic waves poses an intriguing prospect for advancing the state of seismology. This capability would enable an unprecedented global mapping of the velocity structure of the earth's crust, understanding of earthquake rupture dynamics and wave propagation effects, and event source location, characterization and discrimination that are critical for both fundamental earthquake research and nuclear non-proliferation applications. As part of an ongoing collaboration between LLNL and JPL, an advanced mission concept study assessed architectural considerations and operational and data delivery requirements, extending two prior studies by each organization--a radar-based satellite system (JPL) for earthquake hazard assessment and a feasibility study of space- or UAV-based laser seismometer systems (LLNL) for seismic event monitoring. Seismic wave measurement requirements include lower bounds on detectability of specific seismic sources of interest and wave amplitude accuracy for different levels of analysis, such as source characterization, discrimination and tomography, with a 100 {micro}m wave amplitude resolution for waves nominally traveling 5 km/s, an upper frequency bound based on explosion and earthquake surface displacement spectra, and minimum horizontal resolution (1-5 km) and areal coverage, in general and for targeted observations. For a radar system, corresponding engineering and operational factors include: Radar frequency (dictated by required wave amplitude measurement accuracy and maximizing ranging, Doppler or interferometric sensitivity), time sampling (maximum seismic wave frequency and velocity), and overall system considerations such as mass, power and data rate. Technical challenges include characterization of, and compensation for, phase distortion resulting from atmospheric and ionospheric perturbations and turbulence, and effects of ground scattering characteristics and seismic

  8. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided...

  9. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided...

  10. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided...

  11. Development of the x-ray camera for the OGRE sub-orbital rocket

    NASA Astrophysics Data System (ADS)

    Lewis, Matthew R. F.; Soman, Matthew R.; Holland, Andrew D.; Murray, Neil J.; Hall, David; Weatherill, Daniel P.; Tutt, James H.; McEntaffer, Randall L.; DeRoo, Casey T.; Schultz, Ted B.; Holland, Karen

    2016-08-01

    Current theories regarding the matter composition of the universe suggest that half of the expected baryonic matter is missing. One region this could be residing in is intergalactic filaments which absorb strongly in the X-ray regime. Present space based technology is limited when it comes to imaging at these wavelengths and so new techniques are required. The Off-Plane Grating Rocket Experiment (OGRE) aims to produce the highest resolution spectrum of the binary star system Capella, a well-known X-ray source, in the soft X-ray range (0.2keV to 2keV). This will be achieved using a specialised payload combining three low technology readiness level components placed on-board a sub-orbital rocket. These three components consist of an array of large format off-plane X-ray diffraction gratings, a Wolter Type 1 mirror made using single crystal silicon, and the use of EM-CCDs to capture soft X-rays. Each of these components have been previously reviewed with OGRE being the first project to utilise them in a space observation mission. This paper focuses on the EM-CCDs (CCD207-40 by e2v) that will be used and their optimisation with a camera purposely designed for OGRE. Electron Multiplying gain curves were produced for the back-illuminated devices at -80C. Further tests which will need to be carried out are discussed and the impact of the OGRE mission on future projects mentioned.

  12. Suborbital Intercept and Fragmentation of an Asteroid with Very Short Warning Time Scenario

    NASA Technical Reports Server (NTRS)

    Hupp, Ryan; DeWald, Spencer; Wie, Bong; Barbee, Brent W.

    2015-01-01

    Small near-Earth objects (NEOs) is approx. 50-150 m in size are far more numerous (hundreds of thousands to millions yet to be discovered) than larger NEOs. Small NEOs, which are mostly asteroids rather than comets, are very faint in the night sky due to their small sizes, and are, therefore, difficult to discover far in advance of Earth impact. Furthermore, even small NEOs are capable of creating explosions with energies on the order of tens or hundreds of megatons (Mt). We are, therefore, motivated to prepare to respond effectively to short warning time, small NEO impact scenarios. In this paper we explore the lower bound on actionable warning time by investigating the performance of notional upgraded Intercontinental Ballistic Missiles (ICBMs) to carry Nuclear Explosive Device (NED) payloads to intercept and disrupt a hypothetical incoming NEO at high altitudes (generally at least 2500 km above Earth). We conduct this investigation by developing optimal NEO intercept trajectories for a range of cases and comparing their performances. Our results show that suborbital NEO intercepts using Minuteman III or SM-3 IIA launch vehicles could achieve NEO intercept a few minutes prior to when the NEO would strike Earth. We also find that more powerful versions of the launch vehicles (e.g., total deltaV is approx. 9.5-11 km/s) could intercept incoming NEOs several hours prior to when the NEO would strike Earth, if launched at least several days prior to the time of intercept. Finally, we discuss a number of limiting factors and practicalities that affect whether the notional systems we describe could become feasible.

  13. Focal plane actuation to achieve ultra-high resolution on suborbital balloon payloads

    NASA Astrophysics Data System (ADS)

    Scowen, Paul A.; Miller, Alex; Challa, Priya; Veach, Todd; Groppi, Chris; Mauskopf, Phil

    2014-07-01

    Over the past few years there has been remarkable success flying imaging telescope systems suspended from suborbital balloon payload systems. These imaging systems have covered optical, ultraviolet, sub-­-millimeter and infrared passbands (i.e. BLAST, STO, SBI, Fireball and others). In recognition of these advances NASA is now considering ambitious programs to promote planetary imaging from high altitude at a fraction of the cost of similar fully orbital systems. The challenge with imaging from a balloon payload is delivering the full diffraction-­-limited resolution of the system from a moving payload. Good progress has been made with damping mechanisms and oscillation control to remove most macroscopic movement in the departures of the imaging focal plane from a static configuration, however a jitter component remains that is difficult to remove using external corrections. This paper reports on work to demonstrate in the laboratory the utility and performance of actuating a detector focal plane (of whatever type) to remove the final jitter terms using an agile hexapod design. The input to this demonstration is the jitter signal generated by the pointing system of a previously flown balloon mission (the Stratospheric Terahertz Observatory, STO). Our group has a mature jitter compensation system that thermally isolates the control head from the focal plane itself. This allows the hexapod to remain at ambient temperature in a vacuum environment with the focal plane cooled to cryogenic temperatures. Our lab design mounts the focal plane on the hexapod in a custom cryostat and delivers an active optical stimulus together with the corresponding jitter signal, using the actuation of the hexapod to correct for the departures from a static, stable configuration. We believe this demonstration will make the case for inclusion of this technological solution in future balloon-­-borne imaging systems requiring ultra-­-high resolution.

  14. Suborbital Asteroid Intercept and Fragmentation for Very Short Warning Time Scenarios

    NASA Technical Reports Server (NTRS)

    Hupp, Ryan; Dewald, Spencer; Wie, Bong; Barbee, Brent W.

    2015-01-01

    Small near-Earth objects (NEOs) 50150 m in size are far more numerous (hundreds of thousands to millions yet to be discovered) than larger NEOs. Small NEOs, which are mostly asteroids rather than comets, are very faint in the night sky due to their small sizes, and are, therefore, difficult to discover far in advance of Earth impact. However, even small NEOs are capable of creating explosions with energies on the order of tens or hundreds of megatons (Mt).We are, therefore, motivated to prepare to respond effectively to short warning time, small NEO impact scenarios. In this paper we explore the lower bound on actionable warning time by investigating the performance of notional upgraded Intercontinental Ballistic Missiles (ICBMs) to carry Nuclear Explosive Device (NED) payloads to intercept and disrupt a fictitious incoming NEO at high altitudes (generally, at least 2500 km above Earth). We conduct this investigation by developing optimal NEO intercept trajectories for a range of cases and comparing their performances.Our results show that suborbital NEO intercepts using Minuteman III or SM-3 IIA launch vehicles could achieve NEO intercept a few minutes prior to when the NEOwould strike Earth. We also find that more powerful versions of the launch vehicles (e.g., total V 9.511 kms) could intercept incoming NEOs over a day prior to when the NEO would strike Earth, if launched at least several days prior to the time of NEO intercept. Finally, we discuss a number of limiting factors and practicalities that affect whether the notional systems we describe could become feasible.

  15. Ares I-X Flight Test - The Future Begins Here

    NASA Technical Reports Server (NTRS)

    Davis, Stephan R.

    2008-01-01

    In less than two years, the National Aeronautics and Space Administration (NASA) will launch the Ares I-X mission. This will be the first flight of the Ares I crew launch vehicle, which, together with the Ares V cargo launch vehicle, will eventually send humans to the Moon, Mars, and beyond. As the countdown to this first Ares mission continues, personnel from across the Ares I-X Mission Management Office (MMO) are finalizing designs and fabricating vehicle hardware for an April 2009 launch. This paper will discuss the hardware and programmatic progress of the Ares I-X mission. Like the Apollo program, the Ares launch vehicles will rely upon extensive ground, flight, and orbital testing before sending the Orion crew exploration vehicle into space with humans on board. The first flight of Ares I, designated Ares I-X, will be a suborbital development flight test. Ares I-X gives NASA its first opportunity to gather critical data about the flight dynamics of the integrated launch vehicle stack; understand how to control its roll during flight; better characterize the severe stage separation environments that the upper stage engine will experience during future operational flights; and demonstrate the first stage recovery system. NASA also will begin modifying the launch infrastructure and fine-tuning ground and mission operations, as the agency makes the transition from the Space Shuttle to the Ares/Orion system.

  16. Flight Performance of the Inflatable Reentry Vehicle Experiment 3

    NASA Technical Reports Server (NTRS)

    Dillman, Robert; DiNonno, John; Bodkin, Richard; Gsell, Valerie; Miller, Nathanael; Olds, Aaron; Bruce, Walter

    2013-01-01

    The Inflatable Reentry Vehicle Experiment 3 (IRVE-3) launched July 23, 2012, from NASA Wallops Flight Facility (WFF) on a Black Brant XI suborbital sounding rocket and successfully performed its mission, demonstrating the survivability of a hypersonic inflatable aerodynamic decelerator (HIAD) in the reentry heating environment and also illustrating the effect of an offset center of gravity on the HIAD's lift-to-drag ratio. IRVE-3 was a follow-on to 2009's IRVE-II mission, which demonstrated exo-atmospheric inflation, reentry survivability - without significant heating - and the aerodynamic stability of a HIAD down to subsonic flight conditions. NASA Langley Research Center is leading the development of HIAD technology for use on future interplanetary and Earth reentry missions.

  17. The design and realisation of the IXV Mission Analysis and Flight Mechanics

    NASA Astrophysics Data System (ADS)

    Haya-Ramos, Rodrigo; Blanco, Gonzalo; Pontijas, Irene; Bonetti, Davide; Freixa, Jordi; Parigini, Cristina; Bassano, Edmondo; Carducci, Riccardo; Sudars, Martins; Denaro, Angelo; Angelini, Roberto; Mancuso, Salvatore

    2016-07-01

    The Intermediate eXperimental Vehicle (IXV) is a suborbital re-entry demonstrator successfully launched in February 2015 focusing on the in-flight demonstration of a lifting body system with active aerodynamic control surfaces. This paper presents an overview of the Mission Analysis and Flight Mechanics of the IXV vehicle, which comprises computation of the End-to-End (launch to splashdown) design trajectories, characterisation of the Entry Corridor, assessment of the Mission Performances through Monte Carlo campaigns, contribution to the aerodynamic database, analysis of the Visibility and link budget from Ground Stations and GPS, support to safety analyses (off nominal footprints), specification of the Centre of Gravity box, selection of the Angle of Attack trim line to be flown and characterisation of the Flying Qualities performances. An initial analysis and comparison with the raw flight data obtained during the flight will be discussed and first lessons learned derived.

  18. The mechanisms of orbital and suborbital-scale productivity variations in the Eastern Equatorial Pacific

    NASA Astrophysics Data System (ADS)

    Ivanova, E. V.; Beaufort, L.; Vidal, L.

    2009-04-01

    The Eastern Equatorial Pacific (EEP) is known to exhibit high seasonal, interannual (ENSO-like) and longer-term climatic variability with possible worldwide consequences, however, the origin of the suborbital-scale changes in the region is still enigmatic. The centennial to millennial scale variations in the foraminiferal-based MAT-derived SST, productivity index (FP index estimated as the total faunal portion of the three productivity-related planktic foraminiferal species) and coccolithophore-based quantitative productivity record are investigated over MIS 3 and three glacial-interglacial terminations in the IMAGES Core MD02-2529 off Costa Rica (8°12.5' N, 84° 07.5' W, w.d. 1619 m). The stratigraphic framework over three climatic cycles is based on the benthic d 18O record performed on C. wuellerstorfi, and on the published time-scale for last 90 ka (Leduc et al. 2007). The results of the study provide new insight on the mechanisms of productivity variations in the EEP. FP index and total planktic foraminiferal abundance increase concurrently with the previously established salinity raise (Leduc et al.2007) at six H-events (from H-6 to H-1) and at the Younger Dryas relative to the adjacent values. SST record does not show any consistent positive or negative correlation with H-events. The longer-lasting events of enhanced FP index values associate with all three terminations, whereas SST and the total portion of foraminiferal oligotrophic species increase by the end of terminations. The recurrent increase in bioproductivity during H-events may be interpreted in terms of intensified nutrients supply at the core site. At present, bioproductivity at site MD02-2529 is influenced by the seasonal cycle and associated shifts of the Costa Rica Dome and by propagation of eddies and filaments from the nearby coastal upwellings in the Panama Bight and Gulf of Papagayo with the Ekman drift. As these seasonal upwellings are known to be driven by coastal wind jets associated

  19. 14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... energy to reach any populated area in any direction from the launch point; or (2) A launch operator... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the...

  20. Planned Flight of the Terrestrial HIAD Orbital Reentry (THOR)

    NASA Technical Reports Server (NTRS)

    Dillman, Robert; Hughes, Stephen; DiNonno, John; Bodkin, Richard; White, Joseph; DelCorso, Joseph; Cheatwood, F. M.

    2014-01-01

    The Terrestrial HIAD Orbital Reentry (THOR) is planned for flight in 2016 as a secondary payload on an Orbital Sciences commercial resupply mission to the International Space Station. THOR will launch with its Hypersonic Inflatable Aerodynamic Decelerator (HIAD) stowed as a small cylinder between the second stage motor and the launch vehicle fairing. Once the Cygnus cargo vehicle has separated from the second stage, THOR will likewise separate, autonomously re-orient itself, perform a deorbit burn, then inflate the HIAD to a 3.5m diameter cone before atmospheric interface. THOR is a follow-on mission to the IRVE-3 flight test of 2012. The high energy of orbital reentry will allow THOR to demonstrate the performance of its improved, second-generation inflatable structure and flexible TPS materials, in a more energetic entry environment than previous suborbital test flights.This paper discusses the sequence of events planned to occur as part of the THOR mission. Specific topics will include the THOR mission concept, reentry vehicle design for the expected flight environment, the on-board sensors that will allow quantification of vehicle performance, and how we intend to retrieve the flight data from a reentry vehicle splashing down in international waters.

  1. A CubeSat for Calibrating Ground-Based and Sub-Orbital Millimeter-Wave Polarimeters

    NASA Astrophysics Data System (ADS)

    Johnson, Bradley

    2016-06-01

    We describe a low-cost, open-access, CubeSat-based calibration instrument that is designed to support ground-based and sub-orbital experiments searching for various polarization signals in the cosmic microwave background (CMB). All modern CMB polarization experiments require a robust calibration program that will allow the effects of instrument-induced signals to be mitigated during data analysis. A bright, compact, and linearly polarized astrophysical source with polarization properties known to adequate precision does not exist. Therefore, we designed a space-based millimeter-wave calibration instrument, called CalSat, to serve as an open-access calibrator, and this paper describes the results of our design study. The calibration source on board CalSat is composed of five "tones'" with one each at 47.1, 80.0, 140, 249 and 309 GHz. The five tones we chose are well matched to (i) the observation windows in the atmospheric transmittance spectra, (ii) the spectral bands commonly used in polarimeters by the CMB community, and (iii) The Amateur Satellite Service bands in the Table of Frequency Allocations used by the Federal Communications Commission. CalSat will be placed in a polar orbit allowing visibility from observatories in the Northern Hemisphere, such as Mauna~Kea in Hawaii and Summit Station in Greenland, and the Southern Hemisphere, such as the Atacama Desert in Chile and the South Pole. CalSat also will be observable by balloon-borne instruments launched from a range of locations around the world. This global visibility makes CalSat the only source that can be observed by all terrestrial and sub-orbital observatories, thereby providing a universal standard that permits comparison between experiments using appreciably different measurement approaches.

  2. A CubeSat for Calibrating Ground-Based and Sub-Orbital Millimeter-Wave Polarimeters (CalSat)

    NASA Astrophysics Data System (ADS)

    Johnson, Bradley R.; Vourch, Clement J.; Drysdale, Timothy D.; Kalman, Andrew; Fujikawa, Steve; Keating, Brian; Kaufman, Jon

    2015-10-01

    We describe a low-cost, open-access, CubeSat-based calibration instrument that is designed to support ground-based and sub-orbital experiments searching for various polarization signals in the cosmic microwave background (CMB). All modern CMB polarization experiments require a robust calibration program that will allow the effects of instrument-induced signals to be mitigated during data analysis. A bright, compact and linearly polarized astrophysical source with polarization properties known to adequate precision does not exist. Therefore, we designed a space-based millimeter-wave calibration instrument, called CalSat, to serve as an open-access calibrator, and this paper describes the results of our design study. The calibration source on board CalSat is composed of five “tones” with one each at 47.1, 80.0, 140, 249 and 309GHz. The five tones we chose are well matched to (i) the observation windows in the atmospheric transmittance spectra, (ii) the spectral bands commonly used in polarimeters by the CMB community and (iii) the Amateur Satellite Service bands in the Table of Frequency Allocations used by the Federal Communications Commission. CalSat would be placed in a polar orbit allowing visibility from observatories in the Northern Hemisphere, such as Mauna Kea in Hawaii and Summit Station in Greenland, and the Southern Hemisphere, such as the Atacama Desert in Chile and the South Pole. CalSat also would be observable by balloon-borne instruments launched from a range of locations around the world. This global visibility makes CalSat the only source that can be observed by all terrestrial and sub-orbital observatories, thereby providing a universal standard that permits comparison between experiments using appreciably different measurement approaches.

  3. A packet based, data driven telemetry system for autonomous experimental sub-orbital spacecraft

    SciTech Connect

    Kalibjian, J.R.

    1993-04-26

    A data driven telemetry system is described that responds to the rapid nature in which experimental satellite telemetry content is changed during the development process. It also meets the needs of a diverse experiment which the many phases of a mission may contain radically different types of telemetry data. The system emphasizes mechanisms for achieving high redundancy of critical data. A practical example of such an implementation, Brilliant Pebbles Flight Experiment Three (FE-3), is cited.

  4. Fluid Vessel Quantity Using Non-invasive PZT Technology Flight Volume Measurements Under Zero G Analysis

    NASA Technical Reports Server (NTRS)

    Garofalo, Anthony A

    2013-01-01

    The purpose of the project is to perform analysis of data using the Systems Engineering Educational Discovery (SEED) program data from 2011 and 2012 Fluid Vessel Quantity using Non-Invasive PZT Technology flight volume measurements under Zero G conditions (parabolic Plane flight data). Also experimental planning and lab work for future sub-orbital experiments to use the NASA PZT technology for fluid volume measurement. Along with conducting data analysis of flight data, I also did a variety of other tasks. I provided the lab with detailed technical drawings, experimented with 3d printers, made changes to the liquid nitrogen skid schematics, and learned how to weld. I also programmed microcontrollers to interact with various sensors and helped with other things going on around the lab.

  5. Fluid Vessel Quantity using Non-Invasive PZT Technology Flight Volume Measurements Under Zero G Analysis

    NASA Technical Reports Server (NTRS)

    Garofalo, Anthony A.

    2013-01-01

    The purpose of the project is to perform analysis of data using the Systems Engineering Educational Discovery (SEED) program data from 2011 and 2012 Fluid Vessel Quantity using Non-Invasive PZT Technology flight volume measurements under Zero G conditions (parabolic Plane flight data). Also experimental planning and lab work for future sub-orbital experiments to use the NASA PZT technology for fluid volume measurement. Along with conducting data analysis of flight data, I also did a variety of other tasks. I provided the lab with detailed technical drawings, experimented with 3d printers, made changes to the liquid nitrogen skid schematics, and learned how to weld. I also programmed microcontrollers to interact with various sensors and helped with other things going on around the lab.

  6. Technical Progress on the Ares I-X Flight Test

    NASA Technical Reports Server (NTRS)

    Davis, S.R.; Robinson, K.F.; Flynn, K.C.

    2008-01-01

    Ares I-X will be NASA's first test flight for a new human-rated launch vehicle since 1981, and the team is well on its way toward completing the vehicle's design and hardware fabrication for an April 2009 launch. This uncrewed suborbital development test flight gives NASA its first opportunities to: gather critical data about the flight dynamics of the integrated launch vehicle; understand how to control its roll during flight; better characterize the stage separation environments during future flight; and demonstrate the first stage recovery system. The Ares I-X Flight Test Vehicle (FTV) incorporates a mix of flight and mockup hardware. It is powered by a four-segment solid rocket booster, and will be modified to include a fifth, spacer segment; the upper stage, Orion crew exploration vehicle, and launch abort system are simulator hardware to make the FTV aerodynamically similar to the same size, shape, and weight of Ares I. The Ares IX first stage includes an existing Shuttle solid rocket motor and thrust vector control system controlled by an Ascent Thrust Vector Controller (ATVC) designed and built by Honeywell International. The avionics system will be tested in a dedicated System Integration Laboratory located at Lockheed Martin Space Systems (LMSS) in Denver, Colorado. The Upper Stage Simulator (USS) is made up of cylindrical segments that will be stacked and integrated at Kennedy Space Center (KSC) for launch. Glenn Research Center is already building these segments, along with their internal access structures. The active Roll Control System (RoCS) includes two thruster units harvested from Peacekeeper missiles. Duty cycle testing for RoCS was conducted, and fuel tanking and detanking tests will occur at KSC in early 2008. This important flight will provide valuable experience for the ground operations team in integrating, stacking, and launching Ares I. Data from Ares I-X will ensure the safety and reliability of America's newest launch vehicle.

  7. Understanding Flight

    SciTech Connect

    Anderson, David

    2001-01-31

    Through the years the explanation of flight has become mired in misconceptions that have become dogma. Wolfgang Langewiesche, the author of 'Stick and Rudder' (1944) got it right when he wrote: 'Forget Bernoulli's Theorem'. A wing develops lift by diverting (from above) a lot of air. This is the same way that a propeller produces thrust and a helicopter produces lift. Newton's three laws and a phenomenon called the Coanda effect explain most of it. With an understanding of the real physics of flight, many things become clear. Inverted flight, symmetric wings, and the flight of insects are obvious. It is easy to understand the power curve, high-speed stalls, and the effect of load and altitude on the power requirements for lift. The contribution of wing aspect ratio on the efficiency of a wing, and the true explanation of ground effect will also be discussed.

  8. A Space Based Internet Protocol System for Sub-Orbital Tracking and Control

    NASA Technical Reports Server (NTRS)

    Bull, Barton; Grant, Charles; Morgan, Dwayne; Streich, Ron; Bauer, Frank (Technical Monitor)

    2001-01-01

    Personnel from the Goddard Space Flight Center Wallops Flight Facility (GSFC/WFF) in Virginia are responsible for the overall management of the NASA Sounding Rocket Program. Payloads are generally in support of NASA's Space Science Enterprise's missions and return a variety of scientific data as well as providing a reasonably economical means of conducting engineering tests for instruments and devices used on satellites and other spacecraft. The fifteen types of sounding rockets used by NASA can carry payloads of various weights to altitudes from 50 km to more than 1,300 km. Launch activities are conducted not only from established missile ranges, but also from remote locations worldwide requiring mobile tracking and command equipment to be transported and set up at considerable expense. The advent of low earth orbit (LEO) commercial communications satellites provides an opportunity to dramatically reduce tracking and control costs of launch vehicles and Unpiloted Aerial Vehicles (UAVs) by reducing or eliminating this ground infrastructure. Additionally, since data transmission is by packetized Internet Protocol (IP), data can be received and commands initiated from practically any location. A low cost Commercial Off The Shelf (COTS) system is currently under development for sounding rockets which also has application to UAVs and scientific balloons. Due to relatively low data rate (9600 baud) currently available, the system will first be used to provide GPS data for tracking and vehicle recovery. Range safety requirements for launch vehicles usually stipulate at least two independent tracking sources. Most sounding rockets flown by NASA now carry GPS receivers that output position data via the payload telemetry system to the ground station. The Flight Modem can be configured as a completely separate link thereby eliminating requirement for tracking radar. The system architecture which integrates antennas, GPS receiver, commercial satellite packet data modem, and a

  9. Stream network analysis and geomorphic flood plain mapping from orbital and suborbital remote sensing imagery application to flood hazard studies in central Texas

    NASA Technical Reports Server (NTRS)

    Baker, V. R. (Principal Investigator); Holz, R. K.; Hulke, S. D.; Patton, P. C.; Penteado, M. M.

    1975-01-01

    The author has identified the following significant results. Development of a quantitative hydrogeomorphic approach to flood hazard evaluation was hindered by (1) problems of resolution and definition of the morphometric parameters which have hydrologic significance, and (2) mechanical difficulties in creating the necessary volume of data for meaningful analysis. Measures of network resolution such as drainage density and basin Shreve magnitude indicated that large scale topographic maps offered greater resolution than small scale suborbital imagery and orbital imagery. The disparity in network resolution capabilities between orbital and suborbital imagery formats depends on factors such as rock type, vegetation, and land use. The problem of morphometric data analysis was approached by developing a computer-assisted method for network analysis. The system allows rapid identification of network properties which can then be related to measures of flood response.

  10. Ares I-X Flight Test--The Future Begins Here

    NASA Technical Reports Server (NTRS)

    Davis, Stephan R.; Robinson, Kimberly F.

    2008-01-01

    In less than one year, the National Aeronautics and Space Administration (NASA) will launch the Ares I-X mission. This will be the first flight of the Ares I crew launch vehicle, which, together with the Ares V cargo launch vehicle, will send humans to the Moon and beyond. Personnel from the Ares I-X Mission Management Office (MMO) are finalizing designs and fabricating vehicle hardware for a 2009 launch. Ares I-X will be a suborbital development flight test that will gather critical data about the flight dynamics of the integrated launch vehicle stack; understand how to control its roll during flight; better characterize the severe stage separation environments that the upper stage engine will experience during future flights; and demonstrate the first stage recovery system. NASA also will modify the launch infrastructure and ground and mission operations. The Ares I-X Flight Test Vehicle (FTV) will incorporate flight and mockup hardware similar in mass and weight to the operational vehicle. It will be powered by a four-segment Solid Rocket Booster (SRB), which is currently in Shuttle inventory, and will include a fifth spacer segment and new forward structures to make the booster approximately the same size and weight as the five-segment SRB. The Ares I-X flight profile will closely approximate the flight conditions that the Ares I will experience through Mach 4.5, up to approximately 130,000 feet (39,600 meters (m)) and through maximum dynamic pressure ('Max Q') of approximately 800 pounds per square foot (38.3 kilopascals (kPa)). Data from the Ares I-X flight will support the Ares I Critical Design Review (CDR), scheduled for 2010. Work continues on Ares I-X design and hardware fabrication. All of the individual elements are undergoing CDRs, followed by a two-part integrated vehicle CDR in March and July 2008. The various hardware elements are on schedule to begin deliveries to Kennedy Space Center (KSC) in early September 2008. Ares I-X is the first step in

  11. Flight Simulation.

    DTIC Science & Technology

    1986-09-01

    PROCEEDINGS No.408 Flight Simulation DTIC !ELECTE NOVO505s ’ D -J DISTRIBUTION AND AVAILABILITY I I •k i nimy fle-"-- THE MISSION OF AGARI) The mission of...recherche. Ie d ~veloppement et lentrainement. Les objectifs du symposium de la commmission m~canique de vol de L’AGARD 6taient de fournir une description...tttbution Availjbiily CcodeS AvailI a.- d or Dist Spe~cial FLIGHT MECHANICS PANEL OFFICERS Chairman: Dr Ing. P.Hamcl Deputy Chairman: Dr Ing. A.Filisetti

  12. The Development of the Ares I-X Flight Test

    NASA Technical Reports Server (NTRS)

    Ess, Robert H.

    2008-01-01

    The National Aeronautics and Space Administration (NASA) Constellation Program (CxP) has identified a series of tests to provide insight into the design and development of the Ares I Crew Launch Vehicle (CLV) and the Orion Crew Exploration Vehicle (CEV). Ares I-X was created as the first suborbital development flight test to help meet CxP objectives. The Ares I-X flight vehicle is an early operational model of Ares, with specific emphasis on Ares I and ground operation characteristics necessary to meet Ares I-X flight test objectives. Ares I-X will encompass the design and construction of an entire system that includes the Flight Test Vehicle (FTV) and associated operations. The FTV will be a test model based on the Ares I design. Select design features will be incorporated in the FTV design to emulate the operation of the CLV in order to meet the flight test objectives. The operations infrastructure and processes will be customized for Ares I-X, while still providing data to inform the developers of the launch processing system for Ares/Orion. The FTV is comprised of multiple elements and components that will be developed at different locations. The components will be delivered to the launch/assembly site, Kennedy Space Center (KSC), for assembly of the elements and components into an integrated, flight-ready, launch vehicle. The FTV will fly a prescribed trajectory in order to obtain the necessary data to meet the objectives. Ares I-X will not be commanded or controlled from the ground during flight, but the FTV will be equipped with telemetry systems, a data recording capability and a flight termination system (FTS). The in-flight part of the test includes a trajectory to simulate maximum dynamic pressure during flight and perform a stage separation representative of the CLV. The in-flight test also includes separation of the Upper Stage Simulator (USS) from the First Stage and recovery of the First Stage. The data retrieved from the flight test will be analyzed

  13. Data Management Challenges for Airborne NASA Earth Venture Sub-Orbital (EVS-1) Investigations

    NASA Astrophysics Data System (ADS)

    Boyer, A.; Cook, R. B.; Santhana Vannan, S. K.

    2014-12-01

    The ORNL DAAC is developing a technology infrastructure to archive airborne remote sensing observations from two Earth System Science Pathfinder Missions. The two missions are CARVE: Carbon in Arctic Reservoirs Vulnerability Experiment and AirMOSS: Airborne Microwave Observatory of Subcanopy and Subsurface. The two missions are collecting over 140 TB of data from extensive ground-based and airborne instruments. The metadata and documentation requirements necessary for proper archive and dissemination of such transect-based, and often 3-dimensional, airborne data are quite different from the traditional field campaign and satellite remote sensing data streams. Staff at the ORNL DAAC are currently working with the CARVE and AirMOSS teams as well as investigating cyberinfrastructures from other DAACs to develop a metadata and data infrastructure for airborne data that will enable spatial, flight-line, or keyword-based search and discovery, integration as needed of related satellite- and ground-based data sets, and subsetting and visualization tools for both CARVE and AirMOSS. We discuss challenges, progress, and lessons learned.

  14. Scientific and Technical Publishing at Goddard Space Flight Center in Fiscal Year 1994

    NASA Technical Reports Server (NTRS)

    1994-01-01

    This publication is a compilation of scientific and technical material that was researched, written, prepared, and disseminated by the Center's scientists and engineers during FY94. It is presented in numerical order of the GSFC author's sponsoring technical directorate; i.e., Code 300 is the Office of Flight Assurance, Code 400 is the Flight Projects Directorate, Code 500 is the Mission Operations and Data Systems Directorate, Code 600 is the Space Sciences Directorate, Code 700 is the Engineering Directorate, Code 800 is the Suborbital Projects and Operations Directorate, and Code 900 is the Earth Sciences Directorate. The publication database contains publication or presentation title, author(s), document type, sponsor, and organizational code. This is the second annual compilation for the Center.

  15. The SERTS-97 Rocket Experiment on Study Activity on the Sun: Flight 36.167-GS on 1997 November 18

    NASA Technical Reports Server (NTRS)

    Swartz, Marvin; Condor, Charles E.; Davila, Joseph M.; Haas, J. Patrick; Jordan, Stuart D.; Linard, David L.; Miko, Joseph J.; Nash, I. Carol; Novello, Joseph; Payne, Leslie J.; Plummer, Thomas B.; Thomas, Roger J.; White, Larry A.; Brosius, Jeffrey W.; Thompson, William T.

    1999-01-01

    This paper describes mainly the 1997 version of the Solar EUV Rocket Telescope and Spectrograph (SERTS-97), a scientific experiment that operated on NASA's suborbital rocket flight 36.167-GS. Its function was to study activity on the Sun and to provide a cross calibration for the CDS instrument on the SOHO satellite. The experiment was designed, built, and tested by the Solar Physics Branch of the Laboratory for Astronomy and Solar Physics at the Goddard Space Flight Center (GSFC). Other essential sections of the rocket were built under the management of the Sounding Rockets Program Office. These sections include the electronics, timers, IGN despin, the SPARCS pointing controls, the S-19 flight course correction section, the rocket motors, the telemetry, ORSA, and OGIVE.

  16. Constellation's First Flight Test: Ares I-X

    NASA Technical Reports Server (NTRS)

    Davis, Stephan R.; Askins, Bruce R.

    2010-01-01

    On October 28, 2009, NASA launched Ares I-X, the first flight test of the Constellation Program that will send human beings to the Moon and beyond. This successful test is the culmination of a three-and-a-half-year, multi-center effort to design, build, and fly the first demonstration vehicle of the Ares I crew launch vehicle, the successor vehicle to the Space Shuttle. The suborbital mission was designed to evaluate the atmospheric flight characteristics of a vehicle dynamically similar to Ares I; perform a first stage separation and evaluate its effects; characterize and control roll torque; stack, fly, and recover a solid-motor first stage testing the Ares I parachutes; characterize ground, flight, and reentry environments; and develop and execute new ground hardware and procedures. Built from existing flight and new simulator hardware, Ares I-X integrated a Shuttle-heritage four-segment solid rocket booster for first stage propulsion, a spacer segment to simulate a five-segment booster, Peacekeeper axial engines for roll control, and Atlas V avionics, as well as simulators for the upper stage, crew module, and launch abort system. The mission leveraged existing logistical and ground support equipment while also developing new ones to accommodate the first in-line rocket for flying astronauts since the Saturn IB last flew from Kennedy Space Center (KSC) in 1975. This paper will describe the development and integration of the various vehicle and ground elements, from conception to stacking in KSC s Vehicle Assembly Building; hardware performance prior to, during, and after the launch; and preliminary lessons and data gathered from the flight. While the Constellation Program is currently under review, Ares I-X has and will continue to provide vital lessons for NASA personnel in taking a vehicle concept from design to flight.

  17. Cellular responses to low-gravity: Pilot studies on suborbital rockets and orbiting spacecraft

    NASA Technical Reports Server (NTRS)

    Lewis, Marian L.

    1993-01-01

    The allocated funding supported, in part, experiments conducted on two Consort sounding rockets and five Shuttle flights. The primary parameters investigated were signal transduction in response to various mediators, cellular differentiation and metabolism in microgravity, and effect of microgravity on cytoskeletal morphology. Achievements include: demonstration of effect of spaceflight on the actin cytoskeleton in mouse osteoblasts and frog cells; confirmation that the T cell receptor-mediated signal transduction pathway in T lymphocytes is not affected by low-gravity compared to non-TCR-mediated stimulation (Con-A) which classically does not promote proliferative response; indication that microgravity may allow separation of proliferative signaling and secretory function in lymphocytes; demonstration that T lymphocytes and bone cells utilized less glucose indicating a shift in metabolism and confirming Spacelab results with WI-38 cells which used significantly less glucose, during spaceflight; confirmation that activation of human splenic B cells with a number of different mediators is not affected during spaceflight; demonstration of increased prostaglandin synthesis during reduced bone cell growth suggesting an effect of microgravity on prostaglandin-induced mitogenesis. The funding contributed significantly to the database described above and resulted in submission of six collaborative abstracts in 1993 (five to the ASGSB Annual Meeting and one to the ASCB Annual Meeting). Two abstracts were presented at the 1992 ASGSB Annual Meeting in Tucson. In addition, several peer reviewed papers are being generated and data will be included as background in preparation of future proposals, which hopefully will allow us to continue this type of extremely productive collaborative research.

  18. Flight and Integrated Vehicle Testing: Laying the Groundwork for the Next Generation of Space Exploration Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Taylor, Jim

    2009-01-01

    Integrated vehicle testing will be critical to ensuring proper vehicle integration of the Ares I crew launch vehicle and Ares V cargo launch vehicle. The Ares Projects, based at Marshall Space Flight Center in Alabama, created the Flight and Integrated Test Office (FITO) as a separate team to ensure that testing is an integral part of the vehicle development process. As its name indicates, FITO is responsible for managing flight testing for the Ares vehicles. FITO personnel are well on the way toward assembling and flying the first flight test vehicle of Ares I, th Ares I-X. This suborbital development flight will evaluate the performance of Ares I from liftoff to first stage separation, testing flight control algorithms, vehicle roll control, separation and recovery systems, and ground operations. Ares I-X is now scheduled to fly in summer 2009. The follow-on flight, Ares I-Y, will test a full five-segment first stage booster and will include cryogenic propellants in the upper stage, an upper stage engine simulator, and an active launch abort system. The following flight, Orion 1, will be the first flight of an active upper stage and upper stage engine, as well as the first uncrewed flight of an Orion spacecraft into orbit. The Ares Projects are using an incremental buildup of flight capabilities prior to the first operational crewed flight of Ares I and the Orion crew exploration vehicle in 2015. In addition to flight testing, the FITO team will be responsible for conducting hardware, software, and ground vibration tests of the integrated launch vehicle. These efforts will include verifying hardware, software, and grou handling interfaces. Through flight and integrated testing, the Ares Projects will identify and mitigate risks early the United States prepares to take its next giant leaps to the Moon and beyond.

  19. Flight and Integrated Vehicle Testing: Laying the Groundwork for the Next Generation of Space Exploration Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Taylor, J. L.; Cockrell, C. E.

    2009-01-01

    Integrated vehicle testing will be critical to ensuring proper vehicle integration of the Ares I crew launch vehicle and Ares V cargo launch vehicle. The Ares Projects, based at Marshall Space Flight Center in Alabama, created the Flight and Integrated Test Office (FITO) as a separate team to ensure that testing is an integral part of the vehicle development process. As its name indicates, FITO is responsible for managing flight testing for the Ares vehicles. FITO personnel are well on the way toward assembling and flying the first flight test vehicle of Ares I, the Ares I-X. This suborbital development flight will evaluate the performance of Ares I from liftoff to first stage separation, testing flight control algorithms, vehicle roll control, separation and recovery systems, and ground operations. Ares I-X is now scheduled to fly in summer 2009. The follow-on flight, Ares I-Y, will test a full five-segment first stage booster and will include cryogenic propellants in the upper stage, an upper stage engine simulator, and an active launch abort system. The following flight, Orion 1, will be the first flight of an active upper stage and upper stage engine, as well as the first uncrewed flight of an Orion spacecraft into orbit. The Ares Projects are using an incremental buildup of flight capabilities prior to the first operational crewed flight of Ares I and the Orion crew exploration vehicle in 2015. In addition to flight testing, the FITO team will be responsible for conducting hardware, software, and ground vibration tests of the integrated launch vehicle. These efforts will include verifying hardware, software, and ground handling interfaces. Through flight and integrated testing, the Ares Projects will identify and mitigate risks early as the United States prepares to take its next giant leaps to the Moon and beyond.

  20. Bringing the Ocean into Finer Focus through the NASA COAST, HyspIRI, and OCEANIA Suborbital Missions

    NASA Astrophysics Data System (ADS)

    Palacios, S. L.; Guild, L. S.; Kudela, R. M.; Hooker, S. B.; Morrow, J. H.; Russell, P. B.; Livingston, J. M.; Negrey, K.; Torres-Perez, J. L.; Kacenelenbogen, M. S.

    2014-12-01

    High-quality ocean color measurements are needed to characterize water quality and phytoplankton functional types in the coastal zone. Accurate ocean color retrievals are often confounded by inadequacies in atmospheric correction. The recent NASA COAST, HyspIRI, and OCEANIA suborbital missions over Monterey Bay, CA have used novel instruments in a multi-sensor, multi-platform approach to collect above- and in-water measurements to better characterize ocean color through improvements in instrument dynamic range and attention to atmospheric correction. High-level objectives of these missions are to characterize the coastal ocean through end-to-end assessment of image acquisition, atmospheric correction, algorithm application, and sea-truth observations to improve vicarious calibration and validation of satellite ocean color products. We present results from COAST, HyspIRI, and OCEANIA to demonstrate the importance of coincident atmospheric and sea-truth measurements to improve atmospheric correction. Our specific objective was to conduct a sensitivity analysis of the atmospheric correction algorithm, Tafkaa, on Headwall Imaging Spectrometer data using input parameters of atmospheric aerosol optical depth spectra and column water vapor obtained from the Ames Airborne Tracking Sunphotometer (AATS-14) collected on the CIRPAS Twin Otter during COAST (2011). Use of the high dynamic-range, in-water Compact-Optical Profiling System (C-OPS) and above-water Coastal Airborne In-situ Radiometers (C-AIR) with matched wavelength channels enabled accurate observations of exact water-leaving radiance to use in validating imagery. Results from HyspIRI and OCEANIA (October 2013) flown on the NASA ER-2 and CIRPAS Twin Otter will be presented. Knowledge gained from these missions will improve vicarious calibration and validation of legacy (MODIS) and future (PACE & GEO-CAPE) satellite sensors to better characterize coastal ecosystems using ocean color observations.

  1. Orbital and suborbital variability in North Atlantic bottom water temperature obtained from deep-sea ostracod Mg/Ca ratios

    USGS Publications Warehouse

    Cronin, T. M.; Dwyer, G.S.; Baker, P.A.; Rodriguez-Lazaro, J.; DeMartino, D.M.

    2000-01-01

    Magnesium/calcium (Mg/Ca) ratios were measured in the deep-sea ostracod (Crustacea) genus Krithe from Chain core 82-24-4PC from the western mid-Atlantic Ridge (3427 m) in order to estimate ocean circulation and bottom water temperature (BWT) variability over the past 200,000 years. Mg/Ca ratios have been used as a paleothermometer because the ratios are controlled primarily by ambient water temperatures at the time the organism secretes its adult carapace. Over the past two glacial-interglacial cycles, Mg/Ca values oscillated between about 7 mmol/mol and 12 mmol/mol, equivalent to a BWT range of 0 to > 3.5??C. The lowest values were obtained on specimens from glacial marine isotope stages (MISs) 2, 4 and 6; the highest values were obtained from specimens from the early part of the Holocene interglacial (MIS 1), and also from MISs 5 and 7. These trends suggest that BWTs in the North Atlantic Ocean fluctuate over orbital time scales. Suborbital variability in Mg/Ca ratios and BWT was also observed for the past 100,000 years. Ratios rose from ~8 mmol/mol to ~10 mmol/mol (implying a BWT increase of ~1 to 3??C) during 14 Mg/Ca excursions. The highest ratios were found in Krithe dated at approximately 32, 36-38, 43, 48, 73, 85 and 93 ka. Although the age model for the Chain 82-24-4PC and temporal resolution do not allow precise correlation, some of these deep-sea bottom temperature excursions appear to correspond to Heinrich events recorded in other regions of the North Atlantic and perhaps Dansgaard-Oeschger interstadial events recorded in Greenland ice cores. If confirmed, this would support the hypothesis that millennial-scale oscillations of climate in the North Atlantic are capable of affecting global climate via thermohaline circulation changes. (C) 2000 Elsevier Science B.V.

  2. Mission Design and Analysis for Suborbital Intercept and Fragmentation of an Asteroid with Very Short Warning Time

    NASA Technical Reports Server (NTRS)

    Hupp, Ryan; DeWald, Spencer; Wie, Bong; Barbee, Brent W.

    2014-01-01

    Small near-Earth objects (NEOs) approximately 50-150 m in size are far more numerous (hundreds of thousands to millions yet to be discovered) than larger NEOs. Small NEOs, which are mostly asteroids rather than comets, are very faint in the night sky due to their small sizes, and are, therefore, difficult to discover far in advance of Earth impact. Furthermore, even small NEOs are capable of creating explosions with energies on the order of tens or hundreds of megatons (Mt). We are, therefore, motivated to prepare to respond effectively to short warning time, small NEO impact scenarios. In this paper we explore the lower bound on actionable warning time by investigating the performance of notional upgraded Intercontinental Ballistic Missiles (ICBMs) to carry Nuclear Explosive Device (NED) payloads to intercept and disrupt a hypothetical incoming NEO at high altitudes (generally at least 2500 km above Earth). We conduct this investigation by developing optimal NEO intercept trajectories for a range of cases and comparing their performances. Our results show that suborbital NEO intercepts using Minuteman III or SM-3 IIA launch vehicles could achieve NEO intercept a few minutes prior to when the NEO would strike Earth. We also find that more powerful versions of the launch vehicles (e.g., total delta V of approximately 9.5-11 km/s) could intercept incoming NEOs several hours prior to when the NEO would strike Earth, if launched at least several days prior to the time of intercept. Finally, we discuss a number of limiting factors and practicalities that affect whether the notional systems we describe could become feasible.

  3. Inter-linkages of SE Asian, Indian and Indonesian-Australian monsoonal subsystems on orbital and suborbital timescales

    NASA Astrophysics Data System (ADS)

    Holbourn, A. E.; Kuhnt, W.; Tada, R.; Murray, R. W.; Alvarez Zarikian, C. A.; Clemens, S. C.

    2014-12-01

    The SE Asian, Indian and Indonesian-Australian monsoonal subsystems are closely inter-linked, but show substantial differences in the spatial and temporal distribution of precipitation, mainly due to contrasting land-sea distribution and high latitude control. We explore changes in these subsystems in relation to high latitude climate variability on suborbital and orbital timescales, focusing on the last deglaciation and the long-term Miocene evolution. Our main proxies are δ18O and Mg/Ca based salinity and temperature reconstructions in combination with sedimentary and geochemical runoff signatures. Key issues are the synchroneity of monsoonal precipitation changes in relation to northern and southern hemisphere insolation and the response of individual subsystems to atmospheric CO2 and global ice volume variations. In contrast to northern hemisphere monsoonal records, the deglacial intensification of the Australian summer monsoon paralleled southern hemisphere climate evolution. We hypothesize that intensification of the summer heat low over the Australian continent through enhanced greenhouse forcing accentuated the southward pull of the Intertropical Convergence Zone (ITCZ). Additional forcing mechanisms including the variability of the Walker circulation and Indian Ocean Dipole, the heat and moisture transfer from the tropical Indian Ocean and deglacial sea-level changes remain highly debated. High-resolution Miocene records from the South China Sea (ODP Site 1146) indicate that the latitudinal displacement of the ITCZ also impacted the long-term development of the SE Asian summer monsoon. Antarctic ice growth episodes at 14.6, 14.2, 13.9, and 13.1 Ma coincided with surface warming and freshening, implying high sensitivity of tropical rain belts to the inter-hemispheric temperature gradient. However, comparable records of the long-term evolution of the Indian and Indonesian-Australian monsoonal subsystems that would allow testing of this hypothesis are still

  4. Carbonate and lignite cycles in the Ptolemais Basin: Orbital control and suborbital variability (Late Neogene, northern Greece)

    NASA Astrophysics Data System (ADS)

    Weber, M. E.; Tougiannidis, N.; Ricken, W.; Rolf, C.; Kleineder, M.; Bertram, N.; Antoniadis, P.

    2009-04-01

    ), assuming that the lignite phase is associated with maximum temperature and humidity. The reason to apply the tuning was primarily to obtain a better temporal control on the cyclicity documented in the suborbital frequency band. These higher-frequency variations provide a significant contribution and visually resemble those that have been documented for the Greenland Ice Sheet during the last glacial cycle. Future goals of our work include the establishment of possible teleconnections to other parts of the global climate system. We would like to evaluate (i) how the aridification of the Messinian salinity crisis affected the Upper Miocene limnic record, (ii) why the lignite production was enhanced during the warm Lower Pliocene and how the link to the warm global climate might have been created, and (iii) whether the massive northern hemisphere glaciation during the Upper Pliocene might have contributed to the termination of lignite formation in the Ptolemais Basin.

  5. PhoneSat In-flight Experience Results

    NASA Technical Reports Server (NTRS)

    Salas, Alberto Guillen; Attai, Watson; Oyadomari, Ken Y.; Priscal, Cedric; Schimmin, Rogan S.; Gazulla, Oriol Tintore; Wolfe, Jasper L.

    2014-01-01

    Over the last decade, consumer technology has vastly improved its performances, become more affordable and reduced its size. Modern day smartphones offer capabilities that enable us to figure out where we are, which way we are pointing, observe the world around us, and store and transmit this information to wherever we want. These capabilities are remarkably similar to those required for multi-million dollar satellites. The PhoneSat project at NASA Ames Research Center is building a series of CubeSat-size spacecrafts using an off-the-shelf smartphone as its on-board computer with the goal of showing just how simple and cheap space can be. Since the PhoneSat project started, different suborbital and orbital flight activities have proven the viability of this revolutionary approach. In early 2013, the PhoneSat project launched the first triage of PhoneSats into LEO. In the five day orbital life time, the nano-satellites flew the first functioning smartphone-based satellites (using the Nexus One and Nexus S phones), the cheapest satellite (a total parts cost below $3,500) and one of the fastest on-board processors (CPU speed of 1GHz). In this paper, an overview of the PhoneSat project as well as a summary of the in-flight experimental results is presented.

  6. Green Flight Challenge

    NASA Video Gallery

    The CAFE Green Flight Challenge sponsored by Google will be held at the CAFE Foundation Flight Test Center at Charles M. Schulz Sonoma County Airport in Santa Rosa, Calif. The Green Flight Challeng...

  7. Pre-Flight Testing of Spaceborne GPS Receivers using a GPS Constellation Simulator

    NASA Technical Reports Server (NTRS)

    Kizhner, Semion; Davis, Edward; Alonso, R.

    1999-01-01

    The NASA Goddard Space Flight Center (GSFC) Global Positioning System (GPS) applications test facility has been established within the GSFC Guidance Navigation and Control Center. The GPS test facility is currently housing the Global Simulation Systems Inc. (GSSI) STR2760 GPS satellite 40-channel attitude simulator and a STR4760 12-channel navigation simulator. The facility also contains a few other resources such as an atomic time standard test bed, a rooftop antenna platform and a radome. It provides a new capability for high dynamics GPS simulations of space flight that is unique within the aerospace community. The GPS facility provides a critical element for the development and testing of GPS based technologies i.e. position, attitude and precise time determination used on-board a spacecraft, suborbital rocket balloon. The GPS simulation system is configured in a transportable rack and is available for GPS component development as well as for component, spacecraft subsystem and system level testing at spacecraft integration and tests sites. The GPS facility has been operational since early 1996 and has utilized by space flight projects carrying GPS experiments, such as the OrbView-2 and the Argentine SAC-A spacecrafts. The SAC-A pre-flight test data obtained by using the STR2760 simulator and the comparison with preliminary analysis of the GPS data from SAC-A telemetry are summarized. This paper describes pre-flight tests and simulations used to support a unique spaceborne GPS experiment. The GPS experiment mission objectives and the test program are described, as well as the GPS test facility configuration needed to verify experiment feasibility. Some operational and critical issues inherent in GPS receiver pre-flight tests and simulations using this GPS simulation, and test methodology are described. Simulation and flight data are presented. A complete program of pre-flight testing of spaceborne GPS receivers using a GPS constellation simulator is detailed.

  8. Pre-Flight Testing of Spaceborne GPS Receivers Using a GPS Constellation Simulator

    NASA Technical Reports Server (NTRS)

    Kizhner, Semion; Davis, Edward; Alonso, Roberto

    1999-01-01

    The NASA Goddard Space Flight Center (GSFC) Global Positioning System (GPS) applications test facility has been established within the GSFC Guidance Navigation and Control Center. The GPS test facility is currently housing the Global Simulation Systems Inc. (GSSI) STR2760 GPS satellite 40-channel attitude simulator and a STR4760 12-channel navigation simulator. The facility also contains a few other resources such as an atomic time standard test bed, a rooftop antenna platform and a radome. It provides a new capability for high dynamics GPS simulations of space flight that is unique within the aerospace community. The GPS facility provides a critical element for the development and testing of GPS based technologies i.e. position, attitude and precise time determination used on-board a spacecraft, suborbital rocket or balloon. The GPS simulator system is configured in a transportable rack and is available for GPS component development as well as for component, spacecraft subsystem and system level testing at spacecraft integration and test sites. The GPS facility has been operational since early 1996 and has been utilized by space flight projects carrying GPS experiments, such as the OrbView-2 and the Argentine SAC-A spacecrafts. The SAC-A pre-flight test data obtained by using the STR2760 simulator and the comparison with preliminary analysis of the GPS data from SAC-A telemetry are summarized. This paper describes pre-flight tests and simulations used to support a unique spaceborne GPS experiment. The GPS experiment mission objectives and the test program are described, as well as the GPS test facility configuration needed to verify experiment feasibility. Some operational and critical issues inherent in GPS receiver pre-flight tests and simulations using this GPS simulator, and test methodology are described. Simulation and flight data are presented. A complete program of pre-flight testing of spaceborne GPS receivers using a GPS constellation simulator is

  9. Flight Test Series 3: Flight Test Report

    NASA Technical Reports Server (NTRS)

    Marston, Mike; Sternberg, Daniel; Valkov, Steffi

    2015-01-01

    This document is a flight test report from the Operational perspective for Flight Test Series 3, a subpart of the Unmanned Aircraft System (UAS) Integration in the National Airspace System (NAS) project. Flight Test Series 3 testing began on June 15, 2015, and concluded on August 12, 2015. Participants included NASA Ames Research Center, NASA Armstrong Flight Research Center, NASA Glenn Research Center, NASA Langley Research center, General Atomics Aeronautical Systems, Inc., and Honeywell. Key stakeholders analyzed their System Under Test (SUT) in two distinct configurations. Configuration 1, known as Pairwise Encounters, was subdivided into two parts: 1a, involving a low-speed UAS ownship and intruder(s), and 1b, involving a high-speed surrogate ownship and intruder. Configuration 2, known as Full Mission, involved a surrogate ownship, live intruder(s), and integrated virtual traffic. Table 1 is a summary of flights for each configuration, with data collection flights highlighted in green. Section 2 and 3 of this report give an in-depth description of the flight test period, aircraft involved, flight crew, and mission team. Overall, Flight Test 3 gathered excellent data for each SUT. We attribute this successful outcome in large part from the experience that was acquired from the ACAS Xu SS flight test flown in December 2014. Configuration 1 was a tremendous success, thanks to the training, member participation, integration/testing, and in-depth analysis of the flight points. Although Configuration 2 flights were cancelled after 3 data collection flights due to various problems, the lessons learned from this will help the UAS in the NAS project move forward successfully in future flight phases.

  10. Flight projects overview

    NASA Technical Reports Server (NTRS)

    Levine, Jack

    1988-01-01

    Information is given in viewgraph form on the activities of the Flight Projects Division of NASA's Office of Aeronautics and Space Technology. Information is given on space research and technology strategy, current space flight experiments, the Long Duration Exposure Facility, the Orbiter Experiment Program, the Lidar In-Space Technology Experiment, the Ion Auxiliary Propulsion System, the Arcjet Flight Experiment, the Telerobotic Intelligent Interface Flight Experiment, the Cryogenic Fluid Management Flight Experiment, the Industry/University In-Space Flight Experiments, and the Aeroassist Flight Experiment.

  11. Point-to-point people with purpose—Exploring the possibility of a commercial traveler market for point-to-point suborbital space transportation

    NASA Astrophysics Data System (ADS)

    Webber, Derek

    2013-12-01

    An argument was made at the First Arcachon Conference on Private Human Access to Space in 2008 [1] that some systematic market research should be conducted into potential market segments for point-to-point suborbital space transportation (PtP), in order to understand whether a commercial market exists which might augment possible government use for such a vehicle. The cargo market potential was subsequently addressed via desk research, and the results, which resulted in a pessimistic business case outlook, were presented in [2]. The same desk research approach is now used in this paper to address the potential business and wealthy individual passenger traveler market segment ("point-to-point people with purpose"). The results, with the assumed ticket pricing, are not encouraging.

  12. Corrigendum to "Monte Carlo simulations of the secondary neutron ambient and effective dose equivalent rates from surface to suborbital altitudes and low Earth orbit"

    NASA Astrophysics Data System (ADS)

    El-Jaby, Samy

    2016-06-01

    A recent paper published in Life Sciences in Space Research (El-Jaby and Richardson, 2015) presented estimates of the secondary neutron ambient and effective dose equivalent rates, in air, from surface altitudes up to suborbital altitudes and low Earth orbit. These estimates were based on MCNPX (LANL, 2011) (Monte Carlo N-Particle eXtended) radiation transport simulations of galactic cosmic radiation passing through Earth's atmosphere. During a recent review of the input decks used for these simulations, a systematic error was discovered that is addressed here. After reassessment, the neutron ambient and effective dose equivalent rates estimated are found to be 10 to 15% different, though, the essence of the conclusions drawn remains unchanged.

  13. More Than the Sum of the Parts: Satellite Aerosol Remote Sensing, and Its Relationship to Sub-Orbital Measurements and Models

    NASA Technical Reports Server (NTRS)

    Kahn, Ralph

    2016-01-01

    Space-borne instruments are providing increasing amounts of data relating to global aerosol spectral optical depth, horizontal and vertical distribution, and very loose, but spatially and temporally extensive, constraints on particle micro-physical properties. The data sets, and many of the underlying techniques, are evolving rapidly. They represent a vast amount of information, potentially useful to the AAAR community. However, there are also issues, some quite subtle, that scientific users must take into consideration. This tutorial will provide one view of the answers to the following four questions: 1) What satellite-derived aerosol products are available? 2) What are their strengths and limitations? 3) How are they being used now? 4) How might they be used in conjunction with each other, with sub-orbital measurements, and with models to address cutting-edge aerosol questions?

  14. 14 CFR 437.57 - Operating area containment.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... containment. (a) During each permitted flight, a permittee must contain its reusable suborbital rocket's..., railway traffic, or waterborne vessel traffic. (c) The FAA may prohibit a reusable suborbital...

  15. 14 CFR 437.57 - Operating area containment.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... containment. (a) During each permitted flight, a permittee must contain its reusable suborbital rocket's..., railway traffic, or waterborne vessel traffic. (c) The FAA may prohibit a reusable suborbital...

  16. 14 CFR 437.57 - Operating area containment.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... containment. (a) During each permitted flight, a permittee must contain its reusable suborbital rocket's..., railway traffic, or waterborne vessel traffic. (c) The FAA may prohibit a reusable suborbital...

  17. 14 CFR 437.57 - Operating area containment.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... containment. (a) During each permitted flight, a permittee must contain its reusable suborbital rocket's..., railway traffic, or waterborne vessel traffic. (c) The FAA may prohibit a reusable suborbital...

  18. 14 CFR 437.57 - Operating area containment.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... containment. (a) During each permitted flight, a permittee must contain its reusable suborbital rocket's..., railway traffic, or waterborne vessel traffic. (c) The FAA may prohibit a reusable suborbital...

  19. Phonesat In-flight Experience Results

    NASA Technical Reports Server (NTRS)

    Attai, Watson; Guillen, Salas Alberto; Oyadomari, Ken Yuji; Priscal, Cedric; Shimmin, Rogan Stuart; Gazulla, Oriol Tintore; Wolfe, Jasper Lewis

    2014-01-01

    Consumer technology, over the last decade, has begun to encompass devices that enable us to figure out where we are, which way we are pointing, observe the world around us, and store and transmit this information to wherever we want. Once separate consumer products such as GPS units, digital cameras and mobile phones are now combined into the modern day Smartphone. Since these capabilities are remarkably similar to those required for the multi-million dollar satellites - so why not use a multihundred dollar Smartphone instead? The PhoneSat project of NASA Ames Research Center is developing technology demonstrations utilizing these extraordinary advances to show just how simple and cheap Space can be. The style of development revolves around the "release early, release often" Silicon Valley mentality. PhoneSat is a series of 1U CubeSat size spacecrafts that use an off-the-shelf Smartphone as their onboard computer. By doing so, PhoneSat takes advantage of the high computational capability, large memory as well as ultra-tiny sensors like high-resolution cameras and navigation devices that Smartphones offer. Along with a Smartphone, PhoneSat is equipped with other commercially available technology products, such as medical brushless motors that are used as reaction wheels. Over the four years that NASA Ames Research Center has been developing the PhoneSat project, different suborbital and orbital flight activities have proven the validity of this revolutionary approach. In early 2013, the PhoneSat project launched the first triage of PhoneSats into LEO. In the five day orbital life time, the nano-satellites flew the first functioning Smartphone based satellites (using the Nexus One and Nexus S phones), the cheapest satellite (a total parts cost below $3,500) and one of the fastest on-board processors (CPU speed of 1GHz). In late 2013, the PhoneSat project launched an improved version of its bus to a higher altitude orbit which provided data about the overall system

  20. Flight Test Engineering

    NASA Technical Reports Server (NTRS)

    Pavlock, Kate Maureen

    2013-01-01

    Although the scope of flight test engineering efforts may vary among organizations, all point to a common theme: flight test engineering is an interdisciplinary effort to test an asset in its operational flight environment. Upfront planning where design, implementation, and test efforts are clearly aligned with the flight test objective are keys to success. This chapter provides a top level perspective of flight test engineering for the non-expert. Additional research and reading on the topic is encouraged to develop a deeper understanding of specific considerations involved in each phase of flight test engineering.

  1. 'Mighty Eagle' Takes Flight

    NASA Video Gallery

    The "Mighty Eagle," a NASA robotic prototype lander, had a successful first untethered flight Aug. 8 at the Marshall Center. During the 34-second flight, the Mighty Eagle soared and hovered at 30 f...

  2. Autonomous Soaring Flight Results

    NASA Technical Reports Server (NTRS)

    Allen, Michael J.

    2006-01-01

    A viewgraph presentation on autonomous soaring flight results for Unmanned Aerial Vehicles (UAV)'s is shown. The topics include: 1) Background; 2) Thermal Soaring Flight Results; 3) Autonomous Dolphin Soaring; and 4) Future Plans.

  3. 2015 Annual Report for the Flight Opportunities Program

    NASA Technical Reports Server (NTRS)

    Van Dijk, Alexander

    2015-01-01

    Welcome to this third edition of the Flight Opportunities program annual report. In this edition, we continue our story of pathfinding NASA's role in the partnership with the U.S. commercial space and space technology R&D communities to advance national space interests and develop technologies critical to NASA's future missions. 2015 was the year in which a planned change to our payload solicitation strategy saw its first tangible result. As you might remember from our 2014 annual report, in 2015 we set out to facilitate a more direct interaction between flight providers and technology developers by providing fixed funding awards to researchers to directly purchase the flight service(s) that best meet their needs. The selection and award of the first six REDDI-F1 flight grants to non-U.S. government researchers was an important milestone in this regard. From now on, using the REDDI-F1 solicitation appendix, the program will enable non-U.S. government researchers to directly purchase flight services on the emerging suborbital market. The same (or similar) commercial flight services will be available to NASA and other U.S. government agencies (OGA) through commercial contracts that NASA has established through our program. For the latter, our program is available to provide campaign management services, similar to the role we play(ed) for technology payloads remaining in our pool from earlier selections. The full impact of this broader strategic change will likely become more visible in the years ahead as our legacy pool gets depleted and we have implemented a new NASA- and OGA-specific call for proposals. One observation that can already be made after two rounds of REDDI-F1 solicitations is that through this change, the list of commercial flight service providers of interest to non-U.S. government researchers has grown from five in 2014 to nine in 2015. On the industry development front, our Announcement of Collaborative Opportunities (ACO) solicitation was promoted

  4. In Flight, Online

    ERIC Educational Resources Information Center

    Lucking, Robert A.; Wighting, Mervyn J.; Christmann, Edwin P.

    2005-01-01

    The concept of flight for human beings has always been closely tied to imagination. To fly like a bird requires a mind that also soars. Therefore, good teachers who want to teach the scientific principles of flight recognize that it is helpful to share stories of their search for the keys to flight. The authors share some of these with the reader,…

  5. Open-Loop Flight Testing of COBALT GN&C Technologies for Precise Soft Landing

    NASA Technical Reports Server (NTRS)

    Carson, John M., III; Amzajerdian, Farzin; Seubert, Carl R.; Restrepo, Carolina I.

    2017-01-01

    A terrestrial, open-loop (OL) flight test campaign of the NASA COBALT (CoOperative Blending of Autonomous Landing Technologies) platform was conducted onboard the Masten Xodiac suborbital rocket testbed, with support through the NASA Advanced Exploration Systems (AES), Game Changing Development (GCD), and Flight Opportunities (FO) Programs. The COBALT platform integrates NASA Guidance, Navigation and Control (GN&C) sensing technologies for autonomous, precise soft landing, including the Navigation Doppler Lidar (NDL) velocity and range sensor and the Lander Vision System (LVS) Terrain Relative Navigation (TRN) system. A specialized navigation filter running onboard COBALT fuzes the NDL and LVS data in real time to produce a precise navigation solution that is independent of the Global Positioning System (GPS) and suitable for future, autonomous planetary landing systems. The OL campaign tested COBALT as a passive payload, with COBALT data collection and filter execution, but with the Xodiac vehicle Guidance and Control (G&C) loops closed on a Masten GPS-based navigation solution. The OL test was performed as a risk reduction activity in preparation for an upcoming 2017 closed-loop (CL) flight campaign in which Xodiac G&C will act on the COBALT navigation solution and the GPS-based navigation will serve only as a backup monitor.

  6. Submillimetre-sized dust aggregate collision and growth properties. Experimental study of a multi-particle system on a suborbital rocket

    NASA Astrophysics Data System (ADS)

    Brisset, J.; Heißelmann, D.; Kothe, S.; Weidling, R.; Blum, J.

    2016-08-01

    Context. In the very first steps of the formation of a new planetary system, dust agglomerates grow inside the protoplanetary disk that rotates around the newly formed star. In this disk, collisions between the dust particles, induced by interactions with the surrounding gas, lead to sticking. Aggregates start growing until their sizes and relative velocities are high enough for collisions to result in bouncing or fragmentation. With the aim of investigating the transitions between sticking and bouncing regimes for colliding dust aggregates and the formation of clusters from multiple aggregates, the Suborbital Particle and Aggregation Experiment (SPACE) was flown on the REXUS 12 suborbital rocket. Aims: The collisional and sticking properties of sub-mm-sized aggregates composed of protoplanetary dust analogue material are measured, including the statistical threshold velocity between sticking and bouncing, their surface energy and tensile strength within aggregate clusters. Methods: We performed an experiment on the REXUS 12 suborbital rocket. The protoplanetary dust analogue materials were micrometre-sized monodisperse and polydisperse SiO2 particles prepared into aggregates with sizes around 120 μm and 330 μm, respectively and volume filling factors around 0.37. During the experimental run of 150 s under reduced gravity conditions, the sticking of aggregates and the formation and fragmentation of clusters of up to a few millimetres in size was observed. Results: The sticking probability of the sub-mm-sized dust aggregates could be derived for velocities decreasing from ~22 to 3 cm s-1. The transition from bouncing to sticking collisions happened at 12.7+2.1-1.4 cm s-1 for the smaller aggregates composed of monodisperse particles and at 11.5+1.9-1.3 and 11.7+1.9-1.3 cm s-1 for the larger aggregates composed of mono- and polydisperse dust particles, respectively. Using the pull-off force of sub-mm-sized dust aggregates from the clusters, the surface energy of the

  7. Advanced flight software reconfiguraton

    NASA Technical Reports Server (NTRS)

    Porcher, Bryan

    1991-01-01

    Information is given in viewgraph form on advanced flight software reconfiguration. Reconfiguration is defined as identifying mission and configuration specific requirements, controlling mission and configuration specific data, binding this information to the flight software code to perform specific missions, and the release and distribution of the flight software. The objectives are to develop, demonstrate, and validate advanced software reconfiguration tools and techniques; to demonstrate reconfiguration approaches on Space Station Freedom (SSF) onboard systems displays; and to interactively test onboard systems displays, flight software, and flight data.

  8. Climate-dependent fluvial architecture and processes on a suborbital timescale in areas of rapid tectonic uplift: An example from the NE Tibetan Plateau

    NASA Astrophysics Data System (ADS)

    Wang, Xianyan; Vandenberghe, Jef; Yi, Shuangwen; Van Balen, Ronald; Lu, Huayu

    2015-10-01

    The substantial tectonic uplift (1000-2500 m in a few million years) of the Northeastern Tibetan Plateau (NETP), together with the major climatic changes during the Quaternary, provides an opportunity to study the impact of tectonic and climatic changes on the morphological development and sedimentary architecture of fluvial deposits. The effects of these processes are revealed by a terrace staircase, together with the stratigraphy of each individual terrace, in the confluence zone of the Huang Shui and Yellow Rivers in the NETP, during the late Quaternary. On the basis of morphological mapping and OSL-dating, at least seven strath terraces were identified that formed during the last glacial cycle, which are preserved at locations where tectonic uplift was sufficient to separate them altitudinally from one another. The terraces are composed of stacked fluvial gravels, sands and alluvial loams. The principal result is that we demonstrate that the terraces were formed in response to climatic cycles on a suborbital timescale. For each terrace, the lower coarse-grained sediments (gravel and sand) were deposited during cold periods (such as the LGM, MIS3b, MIS4 and MIS5d) associated with a strong Asian winter monsoon. The aggradation during cold periods was associated with floodplain widening. The river incised slightly during the transitions from cold to warm phases, resulting in the transformation of the previous river plain into a terrace. The coarse grained cold phase deposits are covered by inter-bedded, horizontally-laminated silt and sand (representing flood sediments that often contain reworked soil material), during the (cold to warm) transitional phases. The floodplain accumulation on the terrace continued during the subsequent warm period. The warm periods (such as MIS3a, MIS3c, and MIS5a) of the climatic cycles are associated with a strong Asian summer monsoon. Pronounced incision took place at the subsequent warm-cold transitions. After this warm

  9. Suborbital Measurements of Spectral Aerosol Optical Depth and Its Variability at Subsatellite Grid Scales in Support of CLAMS 2001.

    NASA Astrophysics Data System (ADS)

    Redemann, J.; Schmid, B.; Eilers, J. A.; Kahn, R.; Levy, R. C.; Russell, P. B.; Livingston, J. M.; Hobbs, P. V.; Smith, W. L.; Holben, B. N.

    2005-04-01

    As part of the Chesapeake Lighthouse and Aircraft Measurements for Satellites (CLAMS) experiment, 10 July-2 August 2001, off the central East Coast of the United States, the 14-channel NASA Ames Airborne Tracking Sunphotometer (AATS-14) was operated aboard the University of Washington's Convair 580 (CV-580) research aircraft during 10 flights (45 flight hours). One of the main research goals in CLAMS was the validation of satellite-based retrievals of aerosol properties. The goal of this study in particular was to perform true over-ocean validations (rather than over-ocean validation with ground-based, coastal sites) at finer spatial scales and extending to longer wavelengths than those considered in previous studies. Comparisons of aerosol optical depth (AOD) between the Aerosol Robotic Network (AERONET) Cimel instrument at the Chesapeake Lighthouse and airborne measurements by AATS-14 in its vicinity showed good agreement with the largest r-square correlation coefficients at wavelengths of 0.38 and 0.5 μm (>0.99). Coordinated low-level flight tracks of the CV-580 during Terra overpass times permitted validation of over-ocean Moderate Resolution Imaging Spectroradiometer (MODIS) level 2 (MOD04_L2) multiwavelength AOD data (10 km × 10 km, nadir) in 16 cases on three separate days. While the correlation between AATS-14- and MODIS-derived AOD was weak with an r square of 0.55, almost 75% of all MODIS AOD measurements fell within the prelaunch estimated uncertainty range Δτ = ±0.03 ± 0.05τ. This weak correlation may be due to the small AODs (generally less than 0.1 at 0.5 μm) encountered in these comparison cases. An analogous coordination exercise resulted in seven coincident over-ocean matchups between AATS-14 and Multiangle Imaging Spectroradiometer (MISR) measurements. The comparison between AATS-14 and the MISR standard algorithm regional mean AODs showed a stronger correlation with an r square of 0.94. However, MISR AODs were systematically larger than

  10. 14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Flag Operations § 121.493 Flight time limitations: Flight engineers and flight navigators. (a)...

  11. 14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Flag Operations § 121.493 Flight time limitations: Flight engineers and flight navigators. (a)...

  12. 14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Flag Operations § 121.493 Flight time limitations: Flight engineers and flight navigators. (a)...

  13. 14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Flag Operations § 121.493 Flight time limitations: Flight engineers and flight navigators. (a)...

  14. 14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Flag Operations § 121.493 Flight time limitations: Flight engineers and flight navigators. (a)...

  15. Flight code validation simulator

    SciTech Connect

    Sims, B.A.

    1995-08-01

    An End-To-End Simulation capability for software development and validation of missile flight software on the actual embedded computer has been developed utilizing a 486 PC, i860 DSP coprocessor, embedded flight computer and custom dual port memory interface hardware. This system allows real-time interrupt driven embedded flight software development and checkout. The flight software runs in a Sandia Digital Airborne Computer (SANDAC) and reads and writes actual hardware sensor locations in which IMU (Inertial Measurements Unit) data resides. The simulator provides six degree of freedom real-time dynamic simulation, accurate real-time discrete sensor data and acts on commands and discretes from the flight computer. This system was utilized in the development and validation of the successful premier flight of the Digital Miniature Attitude Reference System (DMARS) in January 1995 at the White Sands Missile Range on a two stage attitude controlled sounding rocket.

  16. Flight control actuation system

    NASA Technical Reports Server (NTRS)

    Wingett, Paul T. (Inventor); Gaines, Louie T. (Inventor); Evans, Paul S. (Inventor); Kern, James I. (Inventor)

    2006-01-01

    A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.

  17. Flight control actuation system

    NASA Technical Reports Server (NTRS)

    Wingett, Paul T. (Inventor); Gaines, Louie T. (Inventor); Evans, Paul S. (Inventor); Kern, James I. (Inventor)

    2004-01-01

    A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.

  18. Flight telerobotic servicer

    NASA Technical Reports Server (NTRS)

    Haley, Dennis

    1990-01-01

    Viewgraphs on the Space Station Flight Telerobotic Servicer (SSFTS) are presented. Topics covered include: SSFTS design; SSFTS elements; FTS mission requirements; FTS general requirements; flight telerobotic servicer - telerobot; FTS manipulator; force-torque transducer; end effector changeout mechanism; flight telerobotic servicer - end-of-arm tooling; user interfaces; FTS data management and processing; control subsystem; FTS vision subsystem and camera positioning assembly; FTS workstation display assembly panel; mini-master hand controller; and FTS NASREM system architecture.

  19. Digital flight control research

    NASA Technical Reports Server (NTRS)

    Potter, J. E.; Stern, R. G.; Smith, T. B.; Sinha, P.

    1974-01-01

    The results of studies which were undertaken to contribute to the design of digital flight control systems, particularly for transport aircraft are presented. In addition to the overall design considerations for a digital flight control system, the following topics are discussed in detail: (1) aircraft attitude reference system design, (2) the digital computer configuration, (3) the design of a typical digital autopilot for transport aircraft, and (4) a hybrid flight simulator.

  20. Autonomous Flight Safety System

    NASA Technical Reports Server (NTRS)

    Simpson, James

    2010-01-01

    The Autonomous Flight Safety System (AFSS) is an independent self-contained subsystem mounted onboard a launch vehicle. AFSS has been developed by and is owned by the US Government. Autonomously makes flight termination/destruct decisions using configurable software-based rules implemented on redundant flight processors using data from redundant GPS/IMU navigation sensors. AFSS implements rules determined by the appropriate Range Safety officials.

  1. Unified powered flight guidance

    NASA Technical Reports Server (NTRS)

    Brand, T. J.; Brown, D. W.; Higgins, J. P.

    1973-01-01

    A complete revision of the orbiter powered flight guidance scheme is presented. A unified approach to powered flight guidance was taken to accommodate all phases of exo-atmospheric orbiter powered flight, from ascent through deorbit. The guidance scheme was changed from the previous modified version of the Lambert Aim Point Maneuver Mode used in Apollo to one that employs linear tangent guidance concepts. This document replaces the previous ascent phase equation document.

  2. YF-17 in Flight

    NASA Technical Reports Server (NTRS)

    1976-01-01

    The Northrop Aviation YF-17 technology demonstrator aircraft in flight during a 1976 flight research program at NASA's Dryden Flight Research Center, Edwards, California. From May 27 to July 14, 1976, the Dryden Flight Research Center, Edwards, California, flew the Northrop Aviation YF-17 technology demonstrator to test the high-performance U.S. Air Force fighter at transonic speeds. The objectives of the seven-week flight test program included the study of maneuverability of this aircraft at transonic speeds and the collection of in-flight pressure data from around the afterbody of the aircraft to improve wind-tunnel predictions for future fighter aircraft. Also studied were stability and control and buffeting at high angles of attack as well as handling qualities at high load factors. Another objective of this program was to familiarize center pilots with the operation of advanced high-performance fighter aircraft. During the seven-week program, all seven of the center's test pilots were able to fly the aircraft with Gary Krier serving as project pilot. In general the pilots reported no trouble adapting to the aircraft and reported that it was easy to fly. There were no familiarization flights. All 25 research flights were full-data flights. They obtained data on afterbody pressures, vertical-fin dynamic loads, agility, pilot physiology, and infrared signatures. Average flight time was 45 minutes, although two flights involving in-flight refueling lasted approximately one hour longer than usual. Dryden Project Manager Roy Bryant considered the program a success. Center pilots felt that the aircraft was generations ahead of then current active military aircraft. Originally built for the Air Force's lightweight fighter program, the YF-17 Cobra left Dryden to support the Northrop/Navy F-18 Program. The F-18 Hornet evolved from the YF-17.

  3. Bat flight: aerodynamics, kinematics and flight morphology.

    PubMed

    Hedenström, Anders; Johansson, L Christoffer

    2015-03-01

    Bats evolved the ability of powered flight more than 50 million years ago. The modern bat is an efficient flyer and recent research on bat flight has revealed many intriguing facts. By using particle image velocimetry to visualize wake vortices, both the magnitude and time-history of aerodynamic forces can be estimated. At most speeds the downstroke generates both lift and thrust, whereas the function of the upstroke changes with forward flight speed. At hovering and slow speed bats use a leading edge vortex to enhance the lift beyond that allowed by steady aerodynamics and an inverted wing during the upstroke to further aid weight support. The bat wing and its skeleton exhibit many features and control mechanisms that are presumed to improve flight performance. Whereas bats appear aerodynamically less efficient than birds when it comes to cruising flight, they have the edge over birds when it comes to manoeuvring. There is a direct relationship between kinematics and the aerodynamic performance, but there is still a lack of knowledge about how (and if) the bat controls the movements and shape (planform and camber) of the wing. Considering the relatively few bat species whose aerodynamic tracks have been characterized, there is scope for new discoveries and a need to study species representing more extreme positions in the bat morphospace.

  4. Flight research and testing

    NASA Technical Reports Server (NTRS)

    Putnam, Terrill W.; Ayers, Theodore G.

    1988-01-01

    Flight research and testing form a critical link in the aeronautic R and D chain. Brilliant concepts, elegant theories, and even sophisticated ground tests of flight vehicles are not sufficient to prove beyond doubt that an unproven aeronautical concept will actually perform as predicted. Flight research and testing provide the ultimate proof that an idea or concept performs as expected. Ever since the Wright brothers, flight research and testing have been the crucible in which aeronautical concepts have advanced and been proven to the point that engineers and companies have been willing to stake their future to produce and design new aircraft. This is still true today, as shown by the development of the experimental X-30 aerospace plane. The Dryden Flight Research Center (Ames-Dryden) continues to be involved in a number of flight research programs that require understanding and characterization of the total airplane in all the aeronautical disciplines, for example the X-29. Other programs such as the F-14 variable-sweep transition flight experiment have focused on a single concept or discipline. Ames-Dryden also continues to conduct flight and ground based experiments to improve and expand the ability to test and evaluate advanced aeronautical concepts. A review of significant aeronautical flight research programs and experiments is presented to illustrate both the progress made and the challenges to come.

  5. Flight research and testing

    NASA Technical Reports Server (NTRS)

    Putnam, Terrill W.; Ayers, Theodore G.

    1989-01-01

    Flight research and testing form a critical link in the aeronautic research and development chain. Brilliant concepts, elegant theories, and even sophisticated ground tests of flight vehicles are not sufficient to prove beyond a doubt that an unproven aeronautical concept will actually perform as predicted. Flight research and testing provide the ultimate proof that an idea or concept performs as expected. Ever since the Wright brothers, flight research and testing were the crucible in which aeronautical concepts were advanced and proven to the point that engineers and companies are willing to stake their future to produce and design aircraft. This is still true today, as shown by the development of the experimental X-30 aerospace plane. The Dryden Flight Research Center (Ames-Dryden) continues to be involved in a number of flight research programs that require understanding and characterization of the total airplane in all the aeronautical disciplines, for example the X-29. Other programs such as the F-14 variable-sweep transition flight experiment have focused on a single concept or discipline. Ames-Dryden also continues to conduct flight and ground based experiments to improve and expand the ability to test and evaluate advanced aeronautical concepts. A review of significant aeronautical flight research programs and experiments is presented to illustrate both the progress being made and the challenges to come.

  6. Technology review of flight crucial flight controls

    NASA Technical Reports Server (NTRS)

    Rediess, H. A.; Buckley, E. C.

    1984-01-01

    The results of a technology survey in flight crucial flight controls conducted as a data base for planning future research and technology programs are provided. Free world countries were surveyed with primary emphasis on the United States and Western Europe because that is where the most advanced technology resides. The survey includes major contemporary systems on operational aircraft, R&D flight programs, advanced aircraft developments, and major research and technology programs. The survey was not intended to be an in-depth treatment of the technology elements, but rather a study of major trends in systems level technology. The information was collected from open literature, personal communications and a tour of several companies, government organizations and research laboratories in the United States, United Kingdom, France, and the Federal Republic of Germany.

  7. The Calibration of a Large Number of Scientific Instruments for the Auroral Spatial Structures Probe Sub-Orbital Mission.

    NASA Astrophysics Data System (ADS)

    Swenson, A.; Miller, J.; Neilsen, T. L.; Fish, C. S.; Swenson, C.

    2014-12-01

    The Auroral Spatial Structures Probe (ASSP) is a NASA sounding rocket mission to be launched in the early January 2015 time frame from the Poker Flat Research Range. The primary scientific objective of this mission is to determine the contribution of small spatial and temporal scale fluctuations of the electric fields to the larger-scale processes during active aurora. This will be accomplished through the use of a constellation of six small payloads ejected at high velocity from a sounding rocket. The multiple baseline observations of the electric and magnetic fields will be used to observe variability of both the E-field and the Poynting flux. These observations will be placed in the context of available data, including winds, large scale E-fields, and proxy conductivity (airglow images) observations.Each sub-payload will carry a crossed pair of electric field double-probe sensors, a three-axis magnetometer, and a Langmuir probe. In total there are eight of each instrument type requireing calibration. Since the instruments need to be calibrated over temperature a full calibration of a single instrument is very time-consuming. The decision was made to automate the calibration process. Measurements were taken using a relay switch-box connecting the instruments to test sources. Calibration data were saved into a database. Using post-processing scripts on these databases a calibration for each instrument at each temperature point was made. This approach is a prototype process that might be used for calibrating a large constellation of CubeSats with similar instruments. In this poster we review the ASSP science and mission, and the results of the pre-flight calibration of the science instruments.

  8. X-43A Flight Controls

    NASA Technical Reports Server (NTRS)

    Baumann, Ethan

    2006-01-01

    A viewgraph presentation detailing X-43A Flight controls at NASA Dryden Flight Research Center is shown. The topics include: 1) NASA Dryden, Overview and current and recent flight test programs; 2) Unmanned Aerial Vehicle Synthetic Aperture Radar (UAVSAR) Program, Program Overview and Platform Precision Autopilot; and 3) Hyper-X Program, Program Overview, X-43A Flight Controls and Flight Results.

  9. Space Flight. Teacher Resources.

    ERIC Educational Resources Information Center

    2001

    This teacher's guide contains information, lesson plans, and diverse student learning activities focusing on space flight. The guide is divided into seven sections: (1) "Drawing Activities" (Future Flight; Space Fun; Mission: Draw); (2) "Geography" (Space Places); (3) "History" (Space and Time); (4)…

  10. Flight Test Techniques

    DTIC Science & Technology

    2009-07-01

    Fort Rucker, AL 36362-5276 8. PERFORMING ORGANIZATION REPORT NUMBER TOP 7-4-020 9. SPONSORING/ MONITORING AGENCY NAME(S) AND ADDRESS(ES...2 3. REQUIRED TEST CONDITIONS ............................................. 3 3.1...3. REQUIRED TEST CONDITIONS . 3.1 Air Vehicle Flight Test Techniques. Many different flight test techniques are in existence. As technology

  11. Electromechanical flight control actuator

    NASA Technical Reports Server (NTRS)

    1979-01-01

    The feasibility of using an electromechanical actuator (EMA) as the primary flight control equipment in aerospace flight is examined. The EMA motor design is presented utilizing improved permanent magnet materials. The necessary equipment to complete a single channel EMA using the single channel power electronics breadboard is reported. The design and development of an improved rotor position sensor/tachometer is investigated.

  12. Exploring flight crew behaviour

    NASA Technical Reports Server (NTRS)

    Helmreich, R. L.

    1987-01-01

    A programme of research into the determinants of flight crew performance in commercial and military aviation is described, along with limitations and advantages associated with the conduct of research in such settings. Preliminary results indicate significant relationships among personality factors, attitudes regarding flight operations, and crew performance. The potential theoretical and applied utility of the research and directions for further research are discussed.

  13. Autonomous Flight Safety System

    NASA Technical Reports Server (NTRS)

    Ferrell, Bob; Santuro, Steve; Simpson, James; Zoerner, Roger; Bull, Barton; Lanzi, Jim

    2004-01-01

    Autonomous Flight Safety System (AFSS) is an independent flight safety system designed for small to medium sized expendable launch vehicles launching from or needing range safety protection while overlying relatively remote locations. AFSS replaces the need for a man-in-the-loop to make decisions for flight termination. AFSS could also serve as the prototype for an autonomous manned flight crew escape advisory system. AFSS utilizes onboard sensors and processors to emulate the human decision-making process using rule-based software logic and can dramatically reduce safety response time during critical launch phases. The Range Safety flight path nominal trajectory, its deviation allowances, limit zones and other flight safety rules are stored in the onboard computers. Position, velocity and attitude data obtained from onboard global positioning system (GPS) and inertial navigation system (INS) sensors are compared with these rules to determine the appropriate action to ensure that people and property are not jeopardized. The final system will be fully redundant and independent with multiple processors, sensors, and dead man switches to prevent inadvertent flight termination. AFSS is currently in Phase III which includes updated algorithms, integrated GPS/INS sensors, large scale simulation testing and initial aircraft flight testing.

  14. Java for flight software

    NASA Technical Reports Server (NTRS)

    Benowitz, E.; Niessner, A.

    2003-01-01

    This work involves developing representative mission-critical spacecraft software using the Real-Time Specification for Java (RTSJ). This work currently leverages actual flight software used in the design of actual flight software in the NASA's Deep Space 1 (DSI), which flew in 1998.

  15. A Preliminary Investigation of Supercharging an Air-Cooled Engine in Flight

    NASA Technical Reports Server (NTRS)

    Ware, Marsden; Schey, Oscar W

    1929-01-01

    This report presents the results of preliminary tests made on the effects of supercharging an air-cooled engine under airplane flight conditions. Service training airplanes were used in the investigation equipped with production types of Wright J engines. A N.A.C.A. Roots type supercharger was driven from the rear of the engine. In addition to measuring those quantities that would enable the determination of the climb performance, measurements were made of the cylinder-head temperatures and the carburetor pressures and temperatures. The supercharging equipment was not removed from the airplane when making flights without supercharging, but a by-pass valve, which controlled the amount of supercharging by returning to the atmosphere the surplus air delivered by the supercharger, was left full open. With the supercharger so geared that ground-level pressure could be maintained to 18,500 feet, it was found that the absolute ceiling was increased from 19,400 to 32,600 feet, that the time to climb to 16,00 feet was decreased from 32 to 16 minutes, and that this amount of supercharging apparently did not injure the engine. (author)

  16. The flight of Archaeopteryx.

    PubMed

    Chatterjee, Sankar; Templin, R Jack

    2003-01-01

    The origin of avian flight is often equated with the phylogeny, ecology, and flying ability of the primitive Jurassic bird, Archaeopteryx. Debate persists about whether it was a terrestrial cursor or a tree dweller. Despite broad acceptance of its arboreal life style from anatomical, phylogenetic, and ecological evidence, a new version of the cursorial model was proposed recently asserting that a running Archaeopteryx could take off from the ground using thrust and sustain flight in the air. However, Archaeopteryx lacked both the powerful flight muscles and complex wing movements necessary for ground takeoff. Here we describe a flight simulation model, which suggests that for Archaeopteryx, takeoff from a perch would have been more efficient and cost-effective than from the ground. Archaeopteryx may have made short flights between trees, utilizing a novel method of phugoid gliding.

  17. Miscarriage Among Flight Attendants

    PubMed Central

    Grajewski, Barbara; Whelan, Elizabeth A.; Lawson, Christina C.; Hein, Misty J.; Waters, Martha A.; Anderson, Jeri L.; MacDonald, Leslie A.; Mertens, Christopher J.; Tseng, Chih-Yu; Cassinelli, Rick T.; Luo, Lian

    2015-01-01

    Background Cosmic radiation and circadian disruption are potential reproductive hazards for flight attendants. Methods Flight attendants from 3 US airlines in 3 cities were interviewed for pregnancy histories and lifestyle, medical, and occupational covariates. We assessed cosmic radiation and circadian disruption from company records of 2 million individual flights. Using Cox regression models, we compared respondents (1) by levels of flight exposures and (2) to teachers from the same cities, to evaluate whether these exposures were associated with miscarriage. Results Of 2654 women interviewed (2273 flight attendants and 381 teachers), 958 pregnancies among 764 women met study criteria. A hypothetical pregnant flight attendant with median firsttrimester exposures flew 130 hours in 53 flight segments, crossed 34 time zones, and flew 15 hours during her home-base sleep hours (10 pm–8 am), incurring 0.13 mGy absorbed dose (0.36 mSv effective dose) of cosmic radiation. About 2% of flight attendant pregnancies were likely exposed to a solar particle event, but doses varied widely. Analyses suggested that cosmic radiation exposure of 0.1 mGy or more may be associated with increased risk of miscarriage in weeks 9–13 (odds ratio = 1.7 [95% confidence interval = 0.95–3.2]). Risk of a first-trimester miscarriage with 15 hours or more of flying during home-base sleep hours was increased (1.5 [1.1–2.2]), as was risk with high physical job demands (2.5 [1.5–4.2]). Miscarriage risk was not increased among flight attendants compared with teachers. Conclusions Miscarriage was associated with flight attendant work during sleep hours and high physical job demands and may be associated with cosmic radiation exposure. PMID:25563432

  18. Aerosol-Radiation-Cloud Interactions in the South-East Atlantic: Future Suborbital Activities to Address Knowledge Gaps in Satellite and Model Assessments

    NASA Technical Reports Server (NTRS)

    Redemann, Jens; Wood, R.; Zuidema, P.; Haywood, J.; Piketh, S.; Formenti, P.; L'Ecuyer, T.; Kacenelenbogen, M.; Segal-Rosenheimer, M.; Shinozuka, Y.; LeBlanc, S.; Vaughan, M.; Schmidt, S.; Flynn, C.; Schmid, B.; Luna, B.; Abel, S.

    2016-01-01

    Southern Africa produces almost a third of the Earth's biomass burning (BB) aerosol particles. Particles lofted into the mid-troposphere are transported westward over the South-East (SE) Atlantic, home to one of the three permanent subtropical stratocumulus (Sc) cloud decks in the world. The SE Atlantic stratocumulus deck interacts with the dense layers of BB aerosols that initially overlay the cloud deck, but later subside and may mix into the clouds. These interactions include adjustments to aerosol-induced solar heating and microphysical effects, and their global representation in climate models remains one of the largest uncertainties in estimates of future climate. Hence, new observations over the SE Atlantic have significant implications for global climate change scenarios. Our understanding of aerosol-cloud interactions in the SE Atlantic is hindered both by the lack of knowledge on aerosol and cloud properties, as well as the lack of knowledge about detailed physical processes involved. Most notably, we are missing knowledge on the absorptive and cloud nucleating properties of aerosols, including their vertical distribution relative to clouds, on the locations and degree of aerosol mixing into clouds, on the processes that govern cloud property adjustments, and on the importance of aerosol effects on clouds relative to co-varying synoptic scale meteorology. We discuss the current knowledge of aerosol and cloud property distributions based on satellite observations and sparse suborbital sampling. Recent efforts to make full use of A-Train aerosol sensor synergies will be highlighted. We describe planned field campaigns in the region to address the existing knowledge gaps. Specifically, we describe the scientific objectives and implementation of the five synergistic, international research activities aimed at providing some of the key aerosol and cloud properties and a process-level understanding of aerosol-cloud interactions over the SE Atlantic: NASA

  19. Earth Science Microwave Remote Sensing at NASA's Goddard Space Flight Center

    NASA Technical Reports Server (NTRS)

    Kim, Edward; Busalacchi, Antonio J. (Technical Monitor)

    2000-01-01

    The Goddard Space Flight Center (GSFC) was established as NASA's first space flight center in 1959. Its 12,000 personnel are active in the Earth and space sciences, astronomy, space physics, tracking and communications. GSFC's mission is to expand our knowledge of the Earth and its environment, the solar system, and the universe through observations from space. The main Goddard campus is located in Greenbelt, Maryland, USA, just north of Washington, D.C. The Wallops Flight Facility (operational since 1945), located on the Atlantic coast of Virginia was consolidated with the Goddard Space Flight Center in 1982. Wallops is now NASA's principal facility for management and implementation of suborbital research programs, and supports a wide variety of airborne science missions as well. As the lead Center for NASA's Earth Science Enterprise (ESE)--a long-term, coordinated research effort to study the Earth as a global environmental system--GSFC scientists and engineers are involved in a wide range of Earth Science remote sensing activities. Their activities range from basic geoscience research to the development of instruments and technology for space missions, as well as the associated Calibration/Validation (Cal/Val) work. The shear breadth of work in these areas precludes an exhaustive description here. Rather, this article presents selected brief overviews of microwave-related Earth Science applications and the ground-based, airborne, and space instruments that are in service, under development, or otherwise significantly involving GSFC. Likewise, contributing authors are acknowledged for each section, but the results and projects they describe represent the cumulative efforts of many persons at GSFC as well as at collaborating institutions. For further information, readers are encouraged to consult the listed websites and references.

  20. Future Flight Decks

    NASA Technical Reports Server (NTRS)

    Arbuckle, P. Douglas; Abbott, Kathy H.; Abbott, Terence S.; Schutte, Paul C.

    1998-01-01

    The evolution of commercial transport flight deck configurations over the past 20-30 years and expected future developments are described. Key factors in the aviation environment are identified that the authors expect will significantly affect flight deck designers. One of these is the requirement for commercial aviation accident rate reduction, which is probably required if global commercial aviation is to grow as projected. Other factors include the growing incrementalism in flight deck implementation, definition of future airspace operations, and expectations of a future pilot corps that will have grown up with computers. Future flight deck developments are extrapolated from observable factors in the aviation environment, recent research results in the area of pilot-centered flight deck systems, and by considering expected advances in technology that are being driven by other than aviation requirements. The authors hypothesize that revolutionary flight deck configuration changes will be possible with development of human-centered flight deck design methodologies that take full advantage of commercial and/or entertainment-driven technologies.

  1. Future X Pathfinder: Quick, Low Cost Flight Testing for Tomorrow's Launch Vehicles

    NASA Technical Reports Server (NTRS)

    London, John, III; Sumrall, Phil

    1999-01-01

    The DC-X and DC-XA Single Stage Technology flight program demonstrated the value of low cost rapid prototyping and flight testing of launch vehicle technology testbeds. NASA is continuing this important legacy through a program referred to as Future-X Pathfinder. This program is designed to field flight vehicle projects that cost around $100M each, with a new vehicle flying about every two years. Each vehicle project will develop and extensively flight test a launch vehicle technology testbed that will advance the state of the art in technologies directly relevant to future space transportation systems. There are currently two experimental, or "X" vehicle projects in the Pathfinder program, with additional projects expected to follow in the near future. The first Pathfinder project is X-34. X-34 is a suborbital rocket plane capable of flights to Mach 8 and 75 kilometers altitude. There are a number of reusable launch vehicle technologies embedded in the X-34 vehicle design, such as composite structures and propellant tanks, and advanced reusable thermal protection systems. In addition, X-34 is designed to carry experiments applicable to both the launch vehicle and hypersonic aeronautics community. X-34 is scheduled to fly later this year. The second Pathfinder project is the X-37. X-37 is an orbital space plane that is carried into orbit either by the Space Shuttle or by an expendable launch vehicle. X-37 provides NASA access to the orbital and orbital reentry flight regimes with an experimental testbed vehicle. The vehicle will expose embedded and carry-on advanced space transportation technologies to the extreme environments of orbit and reentry. Early atmospheric approach and landing tests of an unpowered version of the X-37 will begin next year, with orbital flights beginning in late 2001. Future-X Pathfinder is charting a course for the future with its growing fleet of low-cost X- vehicles. X-34 and X-37 are leading the assault on high launch costs and

  2. Initial Flight Test of the Production Support Flight Control Computers at NASA Dryden Flight Research Center

    NASA Technical Reports Server (NTRS)

    Carter, John; Stephenson, Mark

    1999-01-01

    The NASA Dryden Flight Research Center has completed the initial flight test of a modified set of F/A-18 flight control computers that gives the aircraft a research control law capability. The production support flight control computers (PSFCC) provide an increased capability for flight research in the control law, handling qualities, and flight systems areas. The PSFCC feature a research flight control processor that is "piggybacked" onto the baseline F/A-18 flight control system. This research processor allows for pilot selection of research control law operation in flight. To validate flight operation, a replication of a standard F/A-18 control law was programmed into the research processor and flight-tested over a limited envelope. This paper provides a brief description of the system, summarizes the initial flight test of the PSFCC, and describes future experiments for the PSFCC.

  3. Columbia's first shakedown flight

    NASA Astrophysics Data System (ADS)

    Bell, Peter M.

    The space shuttle orbiter Columbia, first of the planned fleet of spacecraft in the nation's space transportation system, will liftoff on its first orbital shakedown flight on or about the 10th of April 1981. Launch will be from the NASA Kennedy Space Center Launch Complex 39A, no earlier than 45 minutes after sunrise. Crew for the first orbital flight will be John W. Young, commander, veteran of two Gemini and two Apollo space flights, and U.S. Navy Capt. Robert L. Crippen, pilot. Crippen has not flown in space.

  4. Intelligent flight control systems

    NASA Technical Reports Server (NTRS)

    Stengel, Robert F.

    1993-01-01

    The capabilities of flight control systems can be enhanced by designing them to emulate functions of natural intelligence. Intelligent control functions fall in three categories. Declarative actions involve decision-making, providing models for system monitoring, goal planning, and system/scenario identification. Procedural actions concern skilled behavior and have parallels in guidance, navigation, and adaptation. Reflexive actions are spontaneous, inner-loop responses for control and estimation. Intelligent flight control systems learn knowledge of the aircraft and its mission and adapt to changes in the flight environment. Cognitive models form an efficient basis for integrating 'outer-loop/inner-loop' control functions and for developing robust parallel-processing algorithms.

  5. Flight Dynamics Analysis Branch

    NASA Technical Reports Server (NTRS)

    Stengle, Tom; Flores-Amaya, Felipe

    2000-01-01

    This report summarizes the major activities and accomplishments carried out by the Flight Dynamics Analysis Branch (FDAB), Code 572, in support of flight projects and technology development initiatives in fiscal year 2000. The report is intended to serve as a summary of the type of support carried out by the FDAB, as well as a concise reference of key accomplishments and mission experience derived from the various mission support roles. The primary focus of the FDAB is to provide expertise in the disciplines of flight dynamics, spacecraft trajectory, attitude analysis, and attitude determination and control. The FDAB currently provides support for missions and technology development projects involving NASA, government, university, and private industry.

  6. Identification of atypical flight patterns

    NASA Technical Reports Server (NTRS)

    Statler, Irving C. (Inventor); Ferryman, Thomas A. (Inventor); Amidan, Brett G. (Inventor); Whitney, Paul D. (Inventor); White, Amanda M. (Inventor); Willse, Alan R. (Inventor); Cooley, Scott K. (Inventor); Jay, Joseph Griffith (Inventor); Lawrence, Robert E. (Inventor); Mosbrucker, Chris (Inventor)

    2005-01-01

    Method and system for analyzing aircraft data, including multiple selected flight parameters for a selected phase of a selected flight, and for determining when the selected phase of the selected flight is atypical, when compared with corresponding data for the same phase for other similar flights. A flight signature is computed using continuous-valued and discrete-valued flight parameters for the selected flight parameters and is optionally compared with a statistical distribution of other observed flight signatures, yielding atypicality scores for the same phase for other similar flights. A cluster analysis is optionally applied to the flight signatures to define an optimal collection of clusters. A level of atypicality for a selected flight is estimated, based upon an index associated with the cluster analysis.

  7. Controlled Hypersonic Flight Air Data System and Flight Instrumentation

    DTIC Science & Technology

    2007-06-01

    strongly on the flight envelope, re-entry trajectory and vehicle structure. Flight envelope and re-entry trajectory influence primarily the sensor...6 3.3 Flight Wind angles and basic considerations...determination the Mach number independence principle can however be used to derive simple analytic expressions. 3.3 Flight Wind angles and basic

  8. SR-71 Flight

    NASA Video Gallery

    Two SR-71A aircraft were loaned from the U.S. Air Force for use for high-speed, high-altitude research at the NASA Dryden Flight Research Center, Edwards, California. One of them was later returned...

  9. Human Space Flight

    NASA Technical Reports Server (NTRS)

    Woolford, Barbara; Mount, Frances

    2004-01-01

    The first human space flight, in the early 1960s, was aimed primarily at determining whether humans could indeed survive and function in micro-gravity. Would eating and sleeping be possible? What mental and physical tasks could be performed? Subsequent programs increased the complexity of the tasks the crew performed. Table 1 summarizes the history of U.S. space flight, showing the projects, their dates, crew sizes, and mission durations. With over forty years of experience with human space flight, the emphasis now is on how to design space vehicles, habitats, and missions to produce the greatest returns to human knowledge. What are the roles of the humans in space flight in low earth orbit, on the moon, and in exploring Mars?

  10. Beta experiment flight report

    NASA Technical Reports Server (NTRS)

    1982-01-01

    A focused laser Doppler velocimeter system was developed for the measurement of atmospheric backscatter (beta) from aerosols at infrared wavelengths. The system was flight tested at several different locations and the results of these tests are summarized.

  11. Orion Abort Flight Test

    NASA Technical Reports Server (NTRS)

    Hayes, Peggy Sue

    2010-01-01

    The purpose of NASA's Constellation project is to create the new generation of spacecraft for human flight to the International Space Station in low-earth orbit, the lunar surface, as well as for use in future deep-space exploration. One portion of the Constellation program was the development of the Orion crew exploration vehicle (CEV) to be used in spaceflight. The Orion spacecraft consists of a crew module, service module, space adapter and launch abort system. The crew module was designed to hold as many as six crew members. The Orion crew exploration vehicle is similar in design to the Apollo space capsules, although larger and more massive. The Flight Test Office is the responsible flight test organization for the launch abort system on the Orion crew exploration vehicle. The Flight Test Office originally proposed six tests that would demonstrate the use of the launch abort system. These flight tests were to be performed at the White Sands Missile Range in New Mexico and were similar in nature to the Apollo Little Joe II tests performed in the 1960s. The first flight test of the launch abort system was a pad abort (PA-1), that took place on 6 May 2010 at the White Sands Missile Range in New Mexico. Primary flight test objectives were to demonstrate the capability of the launch abort system to propel the crew module a safe distance away from a launch vehicle during a pad abort, to demonstrate the stability and control characteristics of the vehicle, and to determine the performance of the motors contained within the launch abort system. The focus of the PA-1 flight test was engineering development and data acquisition, not certification. In this presentation, a high level overview of the PA-1 vehicle is given, along with an overview of the Mobile Operations Facility and information on the White Sands tracking sites for radar & optics. Several lessons learned are presented, including detailed information on the lessons learned in the development of wind

  12. 1999 Flight Mechanics Symposium

    NASA Technical Reports Server (NTRS)

    Lynch, John P. (Editor)

    1999-01-01

    This conference publication includes papers and abstracts presented at the Flight Mechanics Symposium held on May 18-20, 1999. Sponsored by the Guidance, Navigation and Control Center of Goddard Space Flight Center, this symposium featured technical papers on a wide range of issues related to orbit-attitude prediction, determination, and control; attitude sensor calibration; attitude determination error analysis; attitude dynamics; and orbit decay and maneuver strategy. Government, industry, and the academic community participated in the preparation and presentation of these papers.

  13. International Flight Planning Handbook.

    DTIC Science & Technology

    1985-04-01

    SAC pilots and navigators for international operations and provide increased confidence to deal effectively with contingencies that might occur. -, The...control and altitude separation. Therefore, aircrft separation is greater than operations within a radar enviro :..en:. The service is provided by the ICAO...within the CONUS ARTCC system are connected. Therefore, a handoff of a flight will be effected prior to entry into an adjoining FIR or UIR. Once a flight

  14. The flight robotics laboratory

    NASA Technical Reports Server (NTRS)

    Tobbe, Patrick A.; Williamson, Marlin J.; Glaese, John R.

    1988-01-01

    The Flight Robotics Laboratory of the Marshall Space Flight Center is described in detail. This facility, containing an eight degree of freedom manipulator, precision air bearing floor, teleoperated motion base, reconfigurable operator's console, and VAX 11/750 computer system, provides simulation capability to study human/system interactions of remote systems. The facility hardware, software and subsequent integration of these components into a real time man-in-the-loop simulation for the evaluation of spacecraft contact proximity and dynamics are described.

  15. X-29 in flight

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Two X-29 aircraft, featuring one of the most unusual designs in aviation history, were flown at the NASA Ames-Dryden Flight Research Facility (later redesignated the Dryden Flight Research Center), Edwards, Calif., as technology demonstrators to investigate a host of advanced concepts and technologies. This 23 second clip begins with a camera pan from the aircraft's right rear quarter forward as the X-29 flies along in a near- stall maneuver.

  16. Magnesium and Space Flight

    PubMed Central

    Smith, Scott M.; Zwart, Sara R.

    2015-01-01

    Magnesium is an essential nutrient for muscle, cardiovascular, and bone health on Earth, and during space flight. We sought to evaluate magnesium status in 43 astronauts (34 male, 9 female; 47 ± 5 years old, mean ± SD) before, during, and after 4–6-month space missions. We also studied individuals participating in a ground analog of space flight (head-down-tilt bed rest; n = 27 (17 male, 10 female), 35 ± 7 years old). We evaluated serum concentration and 24-h urinary excretion of magnesium, along with estimates of tissue magnesium status from sublingual cells. Serum magnesium increased late in flight, while urinary magnesium excretion was higher over the course of 180-day space missions. Urinary magnesium increased during flight but decreased significantly at landing. Neither serum nor urinary magnesium changed during bed rest. For flight and bed rest, significant correlations existed between the area under the curve of serum and urinary magnesium and the change in total body bone mineral content. Tissue magnesium concentration was unchanged after flight and bed rest. Increased excretion of magnesium is likely partially from bone and partially from diet, but importantly, it does not come at the expense of muscle tissue stores. While further study is needed to better understand the implications of these findings for longer space exploration missions, magnesium homeostasis and tissue status seem well maintained during 4–6-month space missions. PMID:26670248

  17. Magnesium and Space Flight.

    PubMed

    Smith, Scott M; Zwart, Sara R

    2015-12-08

    Magnesium is an essential nutrient for muscle, cardiovascular, and bone health on Earth, and during space flight. We sought to evaluate magnesium status in 43 astronauts (34 male, 9 female; 47 ± 5 years old, mean ± SD) before, during, and after 4-6-month space missions. We also studied individuals participating in a ground analog of space flight (head-down-tilt bed rest; n = 27 (17 male, 10 female), 35 ± 7 years old). We evaluated serum concentration and 24-h urinary excretion of magnesium, along with estimates of tissue magnesium status from sublingual cells. Serum magnesium increased late in flight, while urinary magnesium excretion was higher over the course of 180-day space missions. Urinary magnesium increased during flight but decreased significantly at landing. Neither serum nor urinary magnesium changed during bed rest. For flight and bed rest, significant correlations existed between the area under the curve of serum and urinary magnesium and the change in total body bone mineral content. Tissue magnesium concentration was unchanged after flight and bed rest. Increased excretion of magnesium is likely partially from bone and partially from diet, but importantly, it does not come at the expense of muscle tissue stores. While further study is needed to better understand the implications of these findings for longer space exploration missions, magnesium homeostasis and tissue status seem well maintained during 4-6-month space missions.

  18. Designing Flight Deck Procedures

    NASA Technical Reports Server (NTRS)

    Degani, Asaf; Wiener, Earl

    2005-01-01

    Three reports address the design of flight-deck procedures and various aspects of human interaction with cockpit systems that have direct impact on flight safety. One report, On the Typography of Flight- Deck Documentation, discusses basic research about typography and the kind of information needed by designers of flight deck documentation. Flight crews reading poorly designed documentation may easily overlook a crucial item on the checklist. The report surveys and summarizes the available literature regarding the design and typographical aspects of printed material. It focuses on typographical factors such as proper typefaces, character height, use of lower- and upper-case characters, line length, and spacing. Graphical aspects such as layout, color coding, fonts, and character contrast are discussed; and several cockpit conditions such as lighting levels and glare are addressed, as well as usage factors such as angular alignment, paper quality, and colors. Most of the insights and recommendations discussed in this report are transferable to paperless cockpit systems of the future and computer-based procedure displays (e.g., "electronic flight bag") in aerospace systems and similar systems that are used in other industries such as medical, nuclear systems, maritime operations, and military systems.

  19. 14 CFR 121.414 - Initial and transition training and checking requirements: flight instructors (airplane), flight...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ....414 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED... flight training for flight instructors (airplane), flight engineer instructors (airplane), and flight... to develop during instruction. (4) For flight engineer instructors (airplane) and flight...

  20. 14 CFR 121.414 - Initial and transition training and checking requirements: flight instructors (airplane), flight...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ....414 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED... flight training for flight instructors (airplane), flight engineer instructors (airplane), and flight... to develop during instruction. (4) For flight engineer instructors (airplane) and flight...

  1. 14 CFR 121.414 - Initial and transition training and checking requirements: flight instructors (airplane), flight...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ....414 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED... flight training for flight instructors (airplane), flight engineer instructors (airplane), and flight... to develop during instruction. (4) For flight engineer instructors (airplane) and flight...

  2. Flight Planning in the Cloud

    NASA Technical Reports Server (NTRS)

    Flores, Sarah L.; Chapman, Bruce D.; Tung, Waye W.; Zheng, Yang

    2011-01-01

    This new interface will enable Principal Investigators (PIs), as well as UAVSAR (Uninhabited Aerial Vehicle Synthetic Aperture Radar) members to do their own flight planning and time estimation without having to request flight lines through the science coordinator. It uses an all-in-one Google Maps interface, a JPL hosted database, and PI flight requirements to design an airborne flight plan. The application will enable users to see their own flight plan being constructed interactively through a map interface, and then the flight planning software will generate all the files necessary for the flight. Afterward, the UAVSAR team can then complete the flight request, including calendaring and supplying requisite flight request files in the expected format for processing by NASA s airborne science program. Some of the main features of the interface include drawing flight lines on the map, nudging them, adding them to the current flight plan, and reordering them. The user can also search and select takeoff, landing, and intermediate airports. As the flight plan is constructed, all of its components are constantly being saved to the database, and the estimated flight times are updated. Another feature is the ability to import flight lines from previously saved flight plans. One of the main motivations was to make this Web application as simple and intuitive as possible, while also being dynamic and robust. This Web application can easily be extended to support other airborne instruments.

  3. Long duration flights management

    NASA Astrophysics Data System (ADS)

    Sosa-Sesma, Sergio; Letrenne, Gérard; Spel, Martin; Charbonnier, Jean-Marc

    Long duration flights (LDF) require a special management to take the best decisions in terms of ballast consumption and instant of separation. As a contrast to short duration flights, where meteorological conditions are relatively well known, for LDF we need to include the meteorological model accuracy in trajectory simulations. Dispersions on the fields of model (wind, temperature and IR fluxes) could make the mission incompatible with safety rules, authorized zones and others flight requirements. Last CNES developments for LDF act on three main axes: 1. Although ECMWF-NCEP forecast allows generating simulations from a 4D point (altitude, latitude, longitude and UT time), result is not statistical, it is determinist. To take into account model dispersion a meteorological NCEP data base was analyzed. A comparison between Analysis (AN) and Forecast (FC) for the same time frame had been done. Result obtained from this work allows implementing wind and temperature dispersions on balloon flight simulator. 2. For IR fluxes, NCEP does not provide ascending IR fluxes in AN mode but only in FC mode. To obtain the IR fluxes for each time frame, satellite images are used. A comparison between FC and satellites measurements had been done. Results obtained from this work allow implementing flux dispersions on balloon flight simulator. 3. An improved cartography containing a vast data base had been included in balloon flight simulator. Mixing these three points with balloon flight dynamics we have obtained two new tools for observing balloon evolution and risk, one of them is called ASTERISK (Statistic Tool for Evaluation of Risk) for calculations and the other one is called OBERISK (Observing Balloon Evolution and Risk) for visualization. Depending on the balloon type (super pressure, zero pressure or MIR) relevant information for the flight manager is different. The goal is to take the best decision according to the global situation to obtain the largest flight duration with

  4. XV-15 in flight

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The XV-15 Tilt-Rotor aircraft was designed by Bell Aircraft, Niagara Falls, New York, in the mid-1970's under a contract with NASA and the U.S. Army. It was capable of taking off and landing vertically like a helicopter and of flying horizontally when its 'prop rotors' were rotated forward and downward. NASA Ames Research Center, Mountain View, California, and the Army Air Mobility Laboratory cooperated in a program to obtain two of the aircraft for flight research. The first aircraft arrived at Ames on March 23, 1978. After wind-tunnel testing in the Ames 40-by-80-foot wind tunnel, the aircraft began its contractor flight tests at Ames on April 23, 1979. Bell, Army, and U.S. Marine pilots flew it on 140 separate missions over the next year before turning the aircraft over to Ames. That center, in turn, chose to perform the initial flight research at the Dryden Flight Research Center, Edwards, California, where aircraft Number 2 began flight research with Dryden pilots on October 3, 1980, followed by aircraft Number 1 (previously the wind-tunnel model) the following year. Service pilots continued to fly the aircraft, including missions at Fort Huachuca, Arizona, and aboard the Navy USS Tripoli. Ames pilots also flew the XV-15 extensively during its lengthy period of flight research. The Ames flight research team finally returned aircraft Number 2 to Bell Helicopter in April 1994. The successful flight research with the XV-15, spearheaded by the team at Ames, led to the military V-22 Osprey and to the possibility of using tilt-rotor aircraft as a solution to the problem of crowded airports and highways. The XV-15 weighed 9,076 pounds empty and measured slightly more than 46 feet in length. The distance from the ground to the top of the tail was nearly 13 feet, and the span of its forward-swept wings was about 32 feet. It featured two three-bladed rotors, each measuring 25 feet in diameter. This movie clip runs about 49 seconds showing the XV-15 aircraft turning and

  5. Eclipse takeoff and flight

    NASA Technical Reports Server (NTRS)

    1998-01-01

    This 25-second clip shows the QF-106 'Delta Dart' tethered to the USAF C-141A during takeoff and in flight. NASA Dryden Flight Research Center, Edwards, California, supported a Kelly Space and Technology, Inc. (KST)/U.S. Air Force project known as Eclipse, which demonstrated a reusable tow launch vehicle concept. The purpose of the project was to demonstrate a reusable tow launch vehicle concept that had been conceived and patented by KST. Kelly Space obtained a contract with the USAF Research Laboratory for the tow launch demonstration project under the Small Business Innovation Research (SBIR) program. The USAF SBIR contract included the modifications to turn the QF-106 into the Experimental Demonstrator #1 (EXD-01), and the C141A aircraft to incorporate the tow provisions to link the two aircraft, as well as conducting flight tests. The demonstration consisted of ground and flight tests. These tests included a Combined Systems Test of both airplanes joined by a tow rope, a towed taxi test, and six towed flights. The primary goal of the project was demonstrating the tow phase of the Eclipse concept using a scaled-down tow aircraft (C-141A) and a representative aerodynamically-shaped aircraft (QF-106A) as a launch vehicle. This was successfully accomplished. On December 20, 1997, NASA research pilot Mark Stucky flew a QF-106 on the first towed flight behind an Air Force C-141 in the joint Eclipse project with KST to demonstrate the reusable tow launch vehicle concept developed by KST. Kelly hoped to use the data from the tow tests to validate a tow-to-launch procedure for reusable space launch vehicles. Stucky flew six successful tow tests between December 1997 and February 6, 1998. On February 6, 1998, the sixth and final towed flight brought the project to a successful completion. Preliminary flight results determined that the handling qualities of the QF-106 on tow were very stable; actual flight measured values of tow rope tension were well within predictions

  6. Perseus Post-flight

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Crew members check out the Perseus proof-of-concept vehicle on Rogers Dry Lake, adjacent to the Dryden Flight Research Center, Edwards, California, after a test flight in 1991. Perseus B is a remotely piloted aircraft developed as a design-performance testbed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project. Perseus is one of several flight vehicles involved in the ERAST project. A piston engine, propeller-powered aircraft, Perseus was designed and built by Aurora Flight Sciences Corporation, Manassas, Virginia. The objectives of Perseus B's ERAST flight tests have been to reach and maintain horizontal flight above altitudes of 60,000 feet and demonstrate the capability to fly missions lasting from 8 to 24 hours, depending on payload and altitude requirements. The Perseus B aircraft established an unofficial altitude record for a single-engine, propeller-driven, remotely piloted aircraft on June 27, 1998. It reached an altitude of 60,280 feet. In 1999, several modifications were made to the Perseus aircraft including engine, avionics, and flight-control-system improvements. These improvements were evaluated in a series of operational readiness and test missions at the Dryden Flight Research Center, Edwards, California. Perseus is a high-wing monoplane with a conventional tail design. Its narrow, straight, high-aspect-ratio wing is mounted atop the fuselage. The aircraft is pusher-designed with the propeller mounted in the rear. This design allows for interchangeable scientific-instrument payloads to be placed in the forward fuselage. The design also allows for unobstructed airflow to the sensors and other devices mounted in the payload compartment. The Perseus B that underwent test and development in 1999 was the third generation of the Perseus design, which began with the Perseus Proof-Of-Concept aircraft. Perseus was initially developed as part of NASA's Small High-Altitude Science Aircraft (SHASA) program, which later evolved

  7. Perseus in Flight

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The Perseus proof-of-concept vehicle in flight at the Dryden Flight Research Center, Edwards, California in 1991. Perseus is one of several remotely-piloted aircraft designed for high-altitude, long-endurance scientific sampling missions being evaluated under the ERAST program. Perseus B is a remotely piloted aircraft developed as a design-performance testbed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project. Perseus is one of several flight vehicles involved in the ERAST project. A piston engine, propeller-powered aircraft, Perseus was designed and built by Aurora Flight Sciences Corporation, Manassas, Virginia. The objectives of Perseus B's ERAST flight tests have been to reach and maintain horizontal flight above altitudes of 60,000 feet and demonstrate the capability to fly missions lasting from 8 to 24 hours, depending on payload and altitude requirements. The Perseus B aircraft established an unofficial altitude record for a single-engine, propeller-driven, remotely piloted aircraft on June 27, 1998. It reached an altitude of 60,280 feet. In 1999, several modifications were made to the Perseus aircraft including engine, avionics, and flight-control-system improvements. These improvements were evaluated in a series of operational readiness and test missions at the Dryden Flight Research Center, Edwards, California. Perseus is a high-wing monoplane with a conventional tail design. Its narrow, straight, high-aspect-ratio wing is mounted atop the fuselage. The aircraft is pusher-designed with the propeller mounted in the rear. This design allows for interchangeable scientific-instrument payloads to be placed in the forward fuselage. The design also allows for unobstructed airflow to the sensors and other devices mounted in the payload compartment. The Perseus B that underwent test and development in 1999 was the third generation of the Perseus design, which began with the Perseus Proof-Of-Concept aircraft. Perseus was initially

  8. Aerodynamics of bird flight

    NASA Astrophysics Data System (ADS)

    Dvořák, Rudolf

    2016-03-01

    Unlike airplanes birds must have either flapping or oscillating wings (the hummingbird). Only such wings can produce both lift and thrust - two sine qua non attributes of flying.The bird wings have several possibilities how to obtain the same functions as airplane wings. All are realized by the system of flight feathers. Birds have also the capabilities of adjusting the shape of the wing according to what the immediate flight situation demands, as well as of responding almost immediately to conditions the flow environment dictates, such as wind gusts, object avoidance, target tracking, etc. In bird aerodynamics also the tail plays an important role. To fly, wings impart downward momentum to the surrounding air and obtain lift by reaction. How this is achieved under various flight situations (cruise flight, hovering, landing, etc.), and what the role is of the wing-generated vortices in producing lift and thrust is discussed.The issue of studying bird flight experimentally from in vivo or in vitro experiments is also briefly discussed.

  9. VUV Testing of Science Cameras at MSFC: QE Measurement of the CLASP Flight Cameras

    NASA Technical Reports Server (NTRS)

    Champey, Patrick; Kobayashi, Ken; Winebarger, Amy; Cirtain, Jonathan; Hyde, David; Robertson, Bryan; Beabout, Brent; Beabout, Dyana; Stewart, Mike

    2015-01-01

    The NASA Marshall Space Flight Center (MSFC) has developed a science camera suitable for sub-orbital missions for observations in the UV, EUV and soft X-ray. Six cameras were built and tested for the Chromospheric Lyman-Alpha Spectro-Polarimeter (CLASP), a joint National Astronomical Observatory of Japan (NAOJ) and MSFC sounding rocket mission. The CLASP camera design includes a frame-transfer e2v CCD57-10 512x512 detector, dual channel analog readout electronics and an internally mounted cold block. At the flight operating temperature of -20 C, the CLASP cameras achieved the low-noise performance requirements (less than or equal to 25 e- read noise and greater than or equal to 10 e-/sec/pix dark current), in addition to maintaining a stable gain of approximately equal to 2.0 e-/DN. The e2v CCD57-10 detectors were coated with Lumogen-E to improve quantum efficiency (QE) at the Lyman- wavelength. A vacuum ultra-violet (VUV) monochromator and a NIST calibrated photodiode were employed to measure the QE of each camera. Four flight-like cameras were tested in a high-vacuum chamber, which was configured to operate several tests intended to verify the QE, gain, read noise, dark current and residual non-linearity of the CCD. We present and discuss the QE measurements performed on the CLASP cameras. We also discuss the high-vacuum system outfitted for testing of UV and EUV science cameras at MSFC.

  10. VUV testing of science cameras at MSFC: QE measurement of the CLASP flight cameras

    NASA Astrophysics Data System (ADS)

    Champey, P.; Kobayashi, K.; Winebarger, A.; Cirtain, J.; Hyde, D.; Robertson, B.; Beabout, B.; Beabout, D.; Stewart, M.

    2015-08-01

    The NASA Marshall Space Flight Center (MSFC) has developed a science camera suitable for sub-orbital missions for observations in the UV, EUV and soft X-ray. Six cameras were built and tested for the Chromospheric Lyman-Alpha Spectro-Polarimeter (CLASP), a joint MSFC, National Astronomical Observatory of Japan (NAOJ), Instituto de Astrofisica de Canarias (IAC) and Institut D'Astrophysique Spatiale (IAS) sounding rocket mission. The CLASP camera design includes a frame-transfer e2v CCD57-10 512 × 512 detector, dual channel analog readout and an internally mounted cold block. At the flight CCD temperature of -20C, the CLASP cameras exceeded the low-noise performance requirements (<= 25 e- read noise and <= 10 e- /sec/pixel dark current), in addition to maintaining a stable gain of ≍ 2.0 e-/DN. The e2v CCD57-10 detectors were coated with Lumogen-E to improve quantum efficiency (QE) at the Lyman- wavelength. A vacuum ultra-violet (VUV) monochromator and a NIST calibrated photodiode were employed to measure the QE of each camera. Three flight cameras and one engineering camera were tested in a high-vacuum chamber, which was configured to operate several tests intended to verify the QE, gain, read noise and dark current of the CCD. We present and discuss the QE measurements performed on the CLASP cameras. We also discuss the high-vacuum system outfitted for testing of UV, EUV and X-ray science cameras at MSFC.

  11. Perseus in Flight

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The Perseus proof-of-concept vehicle flies over Rogers Dry Lake at the Dryden Flight Research Center, Edwards, California, to test basic design concepts for the remotely-piloted, high-altitude vehicle. Perseus B is a remotely piloted aircraft developed as a design-performance testbed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project. Perseus is one of several flight vehicles involved in the ERAST project. A piston engine, propeller-powered aircraft, Perseus was designed and built by Aurora Flight Sciences Corporation, Manassas, Virginia. The objectives of Perseus B's ERAST flight tests have been to reach and maintain horizontal flight above altitudes of 60,000 feet and demonstrate the capability to fly missions lasting from 8 to 24 hours, depending on payload and altitude requirements. The Perseus B aircraft established an unofficial altitude record for a single-engine, propeller-driven, remotely piloted aircraft on June 27, 1998. It reached an altitude of 60,280 feet. In 1999, several modifications were made to the Perseus aircraft including engine, avionics, and flight-control-system improvements. These improvements were evaluated in a series of operational readiness and test missions at the Dryden Flight Research Center, Edwards, California. Perseus is a high-wing monoplane with a conventional tail design. Its narrow, straight, high-aspect-ratio wing is mounted atop the fuselage. The aircraft is pusher-designed with the propeller mounted in the rear. This design allows for interchangeable scientific-instrument payloads to be placed in the forward fuselage. The design also allows for unobstructed airflow to the sensors and other devices mounted in the payload compartment. The Perseus B that underwent test and development in 1999 was the third generation of the Perseus design, which began with the Perseus Proof-Of-Concept aircraft. Perseus was initially developed as part of NASA's Small High-Altitude Science Aircraft (SHASA

  12. 2001 Flight Mechanics Symposium

    NASA Technical Reports Server (NTRS)

    Lynch, John P. (Editor)

    2001-01-01

    This conference publication includes papers and abstracts presented at the Flight Mechanics Symposium held on June 19-21, 2001. Sponsored by the Guidance, Navigation and Control Center of Goddard Space Flight Center, this symposium featured technical papers on a wide range of issues related to attitude/orbit determination, prediction and control; attitude simulation; attitude sensor calibration; theoretical foundation of attitude computation; dynamics model improvements; autonomous navigation; constellation design and formation flying; estimation theory and computational techniques; Earth environment mission analysis and design; and, spacecraft re-entry mission design and operations.

  13. Soaring flight in Guinea

    NASA Technical Reports Server (NTRS)

    Idrac, P

    1920-01-01

    The term soaring is applied here to the flight of certain large birds which maneuver in the air without moving their wings. The author explains the methods of his research and here gives approximate figures for the soaring flight of the Egyptian Vulture and the African White backed Vulture. Figures are given in tabular form for relative air speed per foot per second, air velocity per foot per second, lift/drag ratio, and selected coefficients. The author argues that although the figures given were taken from a very limited series of observations, they have nevertheless thrown some light on the use by birds of the internal energy of the air.

  14. LSRA in flight

    NASA Technical Reports Server (NTRS)

    1993-01-01

    A NASA CV-990, modified as a Landing Systems Research Aircraft (LSRA), in flight over NASA's Dryden Flight Research Center, Edwards, California, for a test of the space shuttle landing gear system. The space shuttle landing gear test unit, operated by a high-pressure hydraulic system, allowed engineers to assess and document the performance of space shuttle main and nose landing gear systems, tires and wheel assemblies, plus braking and nose wheel steering performance. The series of 155 test missions for the space shuttle program provided extensive data about the life and endurance of the shuttle tire systems and helped raise the shuttle crosswind landing limits at Kennedy.

  15. ASTRID rocket flight test

    SciTech Connect

    Whitehead, J.C.; Pittenger, L.C.; Colella, N.J.

    1994-07-01

    On February 4, 1994, we successfully flight tested the ASTRID rocket from Vandenberg Air Force Base. The technology for this rocket originated in the Brilliant Pebbles program and represents a five-year development effort. This rocket demonstrated how our new pumped-propulsion technology-which reduced the total effective engine mass by more than one half and cut the tank mass to one fifth previous requirements-would perform in atmospheric flight. This demonstration paves the way for potential cost-effective uses of the new propulsion system in commercial aerospace vehicles, exploration of the planets, and defense applications.

  16. Space Shuttle flight control system

    NASA Technical Reports Server (NTRS)

    Klinar, W. J.; Kubiak, E. T.; Peters, W. H.; Saldana, R. L.; Smith, E. E., Jr.; Stegall, H. W.

    1975-01-01

    The Space Shuttle is a control stabilized vehicle with control provided by an all digital, fly-by-wire flight control system. This paper gives a description of the several modes of flight control which correspond to the Shuttle mission phases. These modes are ascent flight control (including open loop first stage steering, the use of four computers operating in parallel and inertial guidance sensors), on-orbit flight control (with a discussion of reaction control, phase plane switching logic, jet selection logic, state estimator logic and OMS thrust vector control), entry flight control and TAEM (terminal area energy management to landing). Also discussed are redundancy management and backup flight control.

  17. Flight mechanics applications for tethers in space: Cooperative Italian-US programs

    NASA Technical Reports Server (NTRS)

    Bevilacqua, Franco; Merlina, Pietro; Anderson, John L.

    1990-01-01

    Since the 1974 proposal by Giuseppe Colombo to fly a tethered subsatellite from the Shuttle Orbiter, the creative thinking of many scientists and engineers from Italy and U.S. has generated a broad range of potential tether applications in space. Many of these applications have promise for enabling innovative research and operational activities relating to flight mechanics in earth orbit and at suborbital altitudes. From a flight mechanics standpoint the most interesting of the currently proposed flight demonstrations are: the second Tethered Satellite System experiment which offers both the potential for aerothermodynamics and hypersonics research and for atmospheric science research; the Tethered Initiated Space Recovery System which would enable orbital deboost and recovery of a re-entry vehicle and waste removal from a space station; and the Tether Elevator/Crawler System which would provide a variable microgravity environment and space station center of mass management. The outer atmospheric and orbital flight mechanics characteristics of these proposed tether flight demonstrations are described. The second Tethered Satellite System mission will deploy the tethered satellite earthward and will bring it as low as 130 km from ground and thus into the transition region between the atmosphere (non-ionized) and the partially ionized ionosphere. The atmospheric flight mechanics of the tethered satellite is discussed and simulation results are presented. The Tether Initiated Space Recovery System experiment will demonstrate the ability of a simple tether system to deboost and recover a reentry vehicle. The main feature of this demonstration is the utilization of a Small Expendable Deployment System (SEDS) and the low-tension deployment assumed to separate the reentry vehicle from the Shuttle. This low-tension deployment maneuver is discussed and its criticalities are outlined. The Tether Elevator/Crawler System is a new space element able to move in a controlled way

  18. 76 FR 20070 - Commercial Space Transportation Safety Approval Performance Criteria

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-11

    ....19 (a)(4). NASTAR's ] STS-400 suborbital space flight simulator (a multi-axis centrifuge) is capable of replicating the G forces associated with suborbital space flight within the following parameters... Federal Aviation Administration Commercial Space Transportation Safety Approval Performance...

  19. Insect Flight and MAVs

    DTIC Science & Technology

    2007-11-02

    flight u After 350 million years of evolution , they have probably found good solutions for – Kinematics – Wing design – Control Systems High-Lift...Plane Episyrphus balteatus Hoverflies, dragonflies , small birds and bats rely on dynamic stall on the downstroke (red) for weight support Fling

  20. Weather and Flight Testing

    NASA Technical Reports Server (NTRS)

    Wiley, Scott

    2007-01-01

    This viewgraph document reviews some of the weather hazards involved with flight testing. Some of the hazards reviewed are: turbulence, icing, thunderstorms and winds and windshear. Maps, pictures, satellite pictures of the meteorological phenomena and graphs are included. Also included are pictures of damaged aircraft.

  1. Flight Termination Criteria

    NASA Astrophysics Data System (ADS)

    Haber, Jerold M.; Larson, Erik

    2013-09-01

    The first line of defense in protecting the public against the threat of injury from a failing space booster is the flight termination system. Consequently, these systems must be highly reliable and the criteria for flight termination must be carefully formulated. Criteria must be developed based on observable data that allows adequate time for the data to be assessed and a flight termination action to be triggered. Criteria should be set so that 1) the chance a good vehicle will be terminated is small, 2) the chance of failing to terminate an errant vehicle before it can hazard population centers or valuable assets is minimal, and 3) there is assurance that the combination of the planned trajectory and mission rules do not induce excessive risks to land based populations, air lanes, and shipping lanes should the vehicle need to be terminated [1].This paper provides an overview of the approaches to developing and implement flight termination criteria and a tool for understanding risk implications of proposed criteria.

  2. White Flight: Some Hypotheses.

    ERIC Educational Resources Information Center

    Wegmann, Robert G.

    The available literature on white flight, or, more properly, school resegregation -- the phenomenon of white withdrawal (total or partial) from desegregated schools -- is reviewed in this paper which also reports some new research in this area. The distinction is made between those schools located on the fringes of the inner city, which first…

  3. Autonomous Formation Flight

    NASA Technical Reports Server (NTRS)

    Schkolnik, Gerard S.; Cobleigh, Brent

    2004-01-01

    NASA's Strategic Plan for the Aerospace Technology Enterprise includes ambitious objectives focused on affordable air travel, reduced emissions, and expanded aviation-system capacity. NASA Dryden Flight Research Center, in cooperation with NASA Ames Research Center, the Boeing Company, and the University of California, Los Angeles, has embarked on an autonomous-formation-flight project that promises to make significant strides towards these goals. For millions of years, birds have taken advantage of the aerodynamic benefit of flying in formation. The traditional "V" formation flown by many species of birds (including gulls, pelicans, and geese) enables each of the trailing birds to fly in the upwash flow field that exists just outboard of the bird immediately ahead in the formation. The result for each trailing bird is a decrease in induced drag and thus a reduction in the energy needed to maintain a given speed. Hence, for migratory birds, formation flight extends the range of the system of birds over the range of birds flying solo. The Autonomous Formation Flight (AFF) Project is seeking to extend this symbiotic relationship to aircraft.

  4. Flight Model Discharge System

    DTIC Science & Technology

    1989-09-01

    Itterconnection wiring diagram for the ESA ............................... 34 3-13 Typical gain versus total count curve for CEM...42 3-16 Calibration curve for energy bin 12 of the ion ESA ....................... 43 3-17 Flight ESA S/N001...Calibration curves for SPM S/N001 ......................................... 67 4-11 Calibration curves for SPM S/N002

  5. F-104 in flight

    NASA Technical Reports Server (NTRS)

    1993-01-01

    F-104G N826NA during a 1993 flight over the Mojave desert, outfitted with an experiment pylon under the center fuselage and wing racks. The F-104 was originally designed by Kelly Johnson of the Lockheed Skunk Works as a day fighter. The aircraft soon proved ideal for both research and training. For instance, a modified F-104 tested the reaction control jets for the X-15. The F-104's short wings and low lift to drag ratio made it ideal to simulate the X-15 landing profile, which the F-104s often undertook before X-15 flights in order to acquaint pilots with the rocket plane's landing characteristics. This training role continued with the lifting bodies. NASA F-104s were also used for high-speed research after the X-1E was retired. Finally, the F-104s were also used as chase planes for research missions. The F-104G was a late model designed as a fighter bomber for low-level strike missions. It was built for use by the West German Air Force and other foreign governments. N826NA accomplished a wide-range of research activities, including tests of the Space Shuttle's Thermal Protection System (TPS) tiles. The aircraft made 1,415 flights before being retired. It is now on display at the Dryden Flight Research Center.

  6. Flight Mechanics Symposium 1997

    NASA Technical Reports Server (NTRS)

    Walls, Donna M. (Editor)

    1997-01-01

    This conference publication includes papers and abstracts presented at the Flight Mechanics Symposium. This symposium featured technical papers on a wide range of issues related to orbit-attitude prediction, determination, and control; attitude sensor calibration; attitude determination error analysis; attitude dynamics; and orbit decay and maneuver strategy. Government, industry, and the academic community participated in the preparation and presentation of these papers.

  7. Flight telerobotic servicer legacy

    NASA Astrophysics Data System (ADS)

    Shattuck, Paul L.; Lowrie, James W.

    1992-11-01

    The Flight Telerobotic Servicer (FTS) was developed to enhance and provide a safe alternative to human presence in space. The first step for this system was a precursor development test flight (DTF-1) on the Space Shuttle. DTF-1 was to be a pathfinder for manned flight safety of robotic systems. The broad objectives of this mission were three-fold: flight validation of telerobotic manipulator (design, control algorithms, man/machine interfaces, safety); demonstration of dexterous manipulator capabilities on specific building block tasks; and correlation of manipulator performance in space with ground predictions. The DTF-1 system is comprised of a payload bay element (7-DOF manipulator with controllers, end-of-arm gripper and camera, telerobot body with head cameras and electronics module, task panel, and MPESS truss) and an aft flight deck element (force-reflecting hand controller, crew restraint, command and display panel and monitors). The approach used to develop the DTF-1 hardware, software and operations involved flight qualification of components from commercial, military, space, and R controller, end-of-arm tooling, force/torque transducer) and the development of the telerobotic system for space applications. The system is capable of teleoperation and autonomous control (advances state of the art); reliable (two-fault tolerance); and safe (man-rated). Benefits from the development flight included space validation of critical telerobotic technologies and resolution of significant safety issues relating to telerobotic operations in the Shuttle bay or in the vicinity of other space assets. This paper discusses the lessons learned and technology evolution that stemmed from developing and integrating a dexterous robot into a manned system, the Space Shuttle. Particular emphasis is placed on the safety and reliability requirements for a man-rated system as these are the critical factors which drive the overall system architecture. Other topics focused on include

  8. Spacewedge #1 in Flight

    NASA Technical Reports Server (NTRS)

    1992-01-01

    A Spacewedge subscale model, built to help develop potential autonomous recovery systems for spacecraft as well as methods for delivering large Army cargo loads to precision landings, maneuvers through the air under its steerable parafoil during 1992 flight testing. From October 1991 to December 1996, NASA Ames-Dryden Flight Research Facility (after 1994, the Dryden Flight Research Center, Edwards, California) conducted a research program know as the Spacecraft Autoland Project. This Project was designed to determine the feasibility of the autonomous recovery of a spacecraft using a ram-air parafoil system for the final stages of flight, including a precision landing. The Johnson Space Center and the U.S. Army participated in various phases of the program. The Charles Stark Draper Laboratory developed the software for Wedge 3 under contract to the Army. Four generic spacecraft (each called a Spacewedge or simply a Wedge) were built; the last one was built to test the feasibility of a parafoil for delivering Army cargoes. Technology developed during this program has applications for future spacecraft recovery systems, such as the X-38 Crew Return Vehicle demonstrator. The Spacewedge program demonstrated precision flare and landing into the wind at a predetermined location. The program showed that a flexible, deployable system using autonomous navigation and landing was a viable and practical way to recover spacecraft. NASA researchers conducted flight tests of the Spacewedge at three sites near Dryden, a hillside near Tehachapi, the Rogers Dry Lakebed at Edwards Air Force Base, and the California City Airport Drop Zone. During the first phase of testing 36 flights were made. Phase II consisted of 45 flights using a smaller parafoil. A third Phase of 34 flights was conducted primarily by the Army and resulted in the development of an Army guidance system for precision offset cargo delivery. The wedge used during the Army phase was not called a Spacewedge but simply a

  9. Pathfinder aircraft flight

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The Pathfinder research aircraft's wing structure is clearly defined as it soars under a clear blue sky during a test flight from Dryden Flight Research Center, Edwards, California, in November of 1996. Pathfinder was a lightweight, solar-powered, remotely piloted flying wing aircraft used to demonstrate the use of solar power for long-duration, high-altitude flight. Its name denotes its mission as the 'Pathfinder' or first in a series of solar-powered aircraft that will be able to remain airborne for weeks or months on scientific sampling and imaging missions. Solar arrays covered most of the upper wing surface of the Pathfinder aircraft. These arrays provided up to 8,000 watts of power at high noon on a clear summer day. That power fed the aircraft's six electric motors as well as its avionics, communications, and other electrical systems. Pathfinder also had a backup battery system that could provide power for two to five hours, allowing for limited-duration flight after dark. Pathfinder flew at airspeeds of only 15 to 20 mph. Pitch control was maintained by using tiny elevators on the trailing edge of the wing while turns and yaw control were accomplished by slowing down or speeding up the motors on the outboard sections of the wing. On September 11, 1995, Pathfinder set a new altitude record for solar-powered aircraft of 50,567 feet above Edwards Air Force Base, California, on a 12-hour flight. On July 7, 1997, it set another, unofficial record of 71,500 feet at the Pacific Missile Range Facility, Kauai, Hawaii. In 1998, Pathfinder was modified into the longer-winged Pathfinder Plus configuration. (See the Pathfinder Plus photos and project description.)

  10. The NASA Flight Demonstration Program

    NASA Technical Reports Server (NTRS)

    Levin, G. M.; Routh, D.

    1985-01-01

    The Flight Demonstration Program was initiated by the Office of Space Flight in October 1983. The purposes of this program are to conduct an ongoing series of flight demonstrations which demonstrate critical enabling technology to potential Shuttle users and at the same time provide hands on experience to NASA engineers. Flight demonstrations are selected through a peer review process in response to an annual solicitation issued by the Flight Demonstration Office at NASA Headquarters. As of July 1985 one major flight demonstration has been successfully conducted, two flight demonstrations are scheduled to fly in November on STS 61-B, and five flight demonstrations are in various stages of development and planned to be flown during the next three years.

  11. Boeing flight deck design philosophy

    NASA Technical Reports Server (NTRS)

    Stoll, Harty

    1990-01-01

    Information relative to Boeing flight deck design philosophy is given in viewgraph form. Flight deck design rules, design considerations, functions allocated to the crew, redundancy and automation concerns, and examples of accident data that were reviewed are listed.

  12. Cardiovascular physiology in space flight

    NASA Technical Reports Server (NTRS)

    Charles, John B.; Bungo, Michael W.

    1991-01-01

    The effects of space flight on the cardiovascular system have been studied since the first manned flights. In several instances, the results from these investigations have directly contradicted the predictions based on established models. Results suggest associations between space flight's effects on other organ systems and those on the cardiovascular system. Such findings provide new insights into normal human physiology. They must also be considered when planning for the safety and efficiency of space flight crewmembers.

  13. YF-12 in flight

    NASA Technical Reports Server (NTRS)

    1972-01-01

    The Flight Research Center's involvement with the YF-12A, an interceptor version of the Lockheed A-12, began in 1967. Ames Research Center was interested in using wind tunnel data that had been generated at Ames under extreme secrecy. Also, the Office of Advanced Research and Technology (OART) saw the YF-12A as a means to advance high-speed technology, which would help in designing the Supersonic Transport (SST). The Air Force needed technical assistance to get the latest reconnaissance version of the A-12 family, the SR-71A, fully operational. Eventually, the Air Force offered NASA the use of two YF-12A aircraft, 60-6935 and 60-6936. A joint NASA-USAF program was mapped out in June 1969. NASA and Air Force technicians spent three months readying 935 for flight. On 11 December 1969, the flight program got underway with a successful maiden flight piloted by Col. Joe Rogers and Maj. Gary Heidelbaugh of the SR-71/F-12 Test Force. During the program, the Air Force concentrated on military applications, and NASA pursued a loads research program. NASA studies included inflight heating, skin-friction cooling, 'coldwall' research (a heat transfer experiment), flowfield studies, shaker vane research, and tests in support of the Space Shuttle landing program. Ultimately, 935 became the workhorse of the program, with 146 flights between 11 December 1969 and 7 November 1979. The second YF-12A, 936, made 62 flights. It was lost in a non-fatal crash on 24 June 1971. It was replaced by the so-called YF-12C (SR-71A 61-7951, modified with YF-12A inlets and engines and a bogus tail number 06937). The Lockheed A-12 family, known as the Blackbirds, were designed by Clarence 'Kelly' Johnson. They were constructed mostly of titanium to withstand aerodynamic heating. Fueled by JP-7, the Blackbirds were capable of cruising at Mach 3.2 and attaining altitudes in excess of 80,000 feet. The first version, a CIA reconnaissance aircraft that first flew in April 1962 was called the A-12. An

  14. NASA Dryden Flight Research Center

    NASA Technical Reports Server (NTRS)

    Navarro, Robert

    2009-01-01

    This DVD has several short videos showing some of the work that Dryden is involved in with experimental aircraft. These are: shots showing the Active AeroElastic Wing (AAW) loads calibration tests, AAW roll maneuvers, AAW flight control surface inputs, Helios flight, and takeoff, and Pathfinder takeoff, flight and landing.

  15. Flight crew health stabilization program

    NASA Technical Reports Server (NTRS)

    Wooley, B. C.; Mccollum, G. W.

    1975-01-01

    The flight crew health stabilization program was developed to minimize or eliminate the possibility of adverse alterations in the health of flight crews during immediate preflight, flight, and postflight periods. The elements of the program, which include clinical medicine, immunology, exposure prevention, and epidemiological surveillance, are discussed briefly. No crewmember illness was reported for the missions for which the program was in effect.

  16. Bisphosphonate ISS Flight Experiment

    NASA Technical Reports Server (NTRS)

    LeBlanc, Adrian; Matsumoto, Toshio; Jones, Jeffrey; Shapiro, Jay; Lang, Thomas; Shackleford, Linda; Smith, Scott M.; Evans, Harlan; Spector, Elizabeth; Ploutz-Snyder, Robert; Sibonga, Jean; Keyak, Joyce; Nakamura, Toshitaka; Kohri, Kenjiro; Ohshima, Hiroshi; Moralez, Gilbert

    2014-01-01

    The bisphosphonate study is a collaborative effort between the NASA and JAXA space agencies to investigate the potential for antiresorptive drugs to mitigate bone changes associated with long-duration spaceflight. Elevated bone resorption is a hallmark of human spaceflight and bed rest (common zero-G analog). We tested whether an antiresorptive drug in combination with in-flight exercise would ameliorate bone loss and hypercalcuria during longduration spaceflight. Measurements include DXA, QCT, pQCT, and urine and blood biomarkers. We have completed analysis of 7 crewmembers treated with alendronate during flight and the immediate postflight (R+<2 week) data collection in 5 of 10 controls without treatment. Both groups used the advanced resistive exercise device (ARED) during their missions. We previously reported the pre/postflight results of crew taking alendronate during flight (Osteoporosis Int. 24:2105-2114, 2013). The purpose of this report is to present the 12-month follow-up data in the treated astronauts and to compare these results with preliminary data from untreated crewmembers exercising with ARED (ARED control) or without ARED (Pre-ARED control). Results: the table presents DXA and QCT BMD expressed as percentage change from preflight in the control astronauts (18 Pre-ARED and the current 5 ARED-1-year data not yet available) and the 7 treated subjects. As shown previously the combination of exercise plus antiresorptive is effective in preventing bone loss during flight. Bone measures for treated subjects, 1 year after return from space remain at or near baseline values. Except in one region, the treated group maintained or gained bone 1 year after flight. Biomarker data are not currently available for either control group and therefore not presented. However, data from other studies with or without ARED show elevated bone resorption and urinary Ca excretion while bisphosphonate treated subjects show decreases during flight. Comparing the two control

  17. 14 CFR 121.414 - Initial and transition training and checking requirements: flight instructors (airplane), flight...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ....414 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED... training for flight instructors (airplane), flight engineer instructors (airplane), and flight navigator... instruction. (4) For flight engineer instructors (airplane) and flight navigator instructors (airplane),...

  18. 14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... certain flight tests. (a) No person may operate a civil aircraft (except a manned free balloon) that is... used for a flight test for an airline transport pilot certificate or a class or type rating on...

  19. Becoming a flight surgeon.

    PubMed

    Gallé-Tessonneau, J R

    1988-12-01

    This text is the inaugural lesson given by the Professor of Aeronautic Psychiatry and starts the training period for new flight surgeons in the French Air Force. Introducing the French Air Force Medicine Training Session, the author speaks about the psychological aspects in aviation medicine. Three points of pilots' psychology are developed: 1) the pilot's body as the source of intense sensations and as an object of important value; 2) the libidinal, narcissistic, and defensive aspects of the pilot's spirit; and 3) the pilot's environment with its characteristic relationships. These facts influence the medical approach and modify the physician-pilot relationship. The flight surgeon must pay attention and get ready for this specific practice.

  20. Optimal symmetric flight studies

    NASA Technical Reports Server (NTRS)

    Weston, A. R.; Menon, P. K. A.; Bilimoria, K. D.; Cliff, E. M.; Kelley, H. J.

    1985-01-01

    Several topics in optimal symmetric flight of airbreathing vehicles are examined. In one study, an approximation scheme designed for onboard real-time energy management of climb-dash is developed and calculations for a high-performance aircraft presented. In another, a vehicle model intermediate in complexity between energy and point-mass models is explored and some quirks in optimal flight characteristics peculiar to the model uncovered. In yet another study, energy-modelling procedures are re-examined with a view to stretching the range of validity of zeroth-order approximation by special choice of state variables. In a final study, time-fuel tradeoffs in cruise-dash are examined for the consequences of nonconvexities appearing in the classical steady cruise-dash model. Two appendices provide retrospective looks at two early publications on energy modelling and related optimal control theory.

  1. Flight Day 2 Highlights

    NASA Technical Reports Server (NTRS)

    2003-01-01

    The STS-107 second flight day begins with a shot of the Spacehab Research Double Module. Live presentations of experiments underway inside of the Spacehab Module are presented. Six experiments are shown. As part of the Space Technology and Research Student Payload, students from Australia, China, Israel, Japan, New York, and Liechtenstein are studying the effect that microgravity has on ants, spiders, silkworms, fish, bees, granular materials, and crystals. Mission Specialist Kalpana Chawla is seen working with the zeolite crystal growth experiment.

  2. MARS Flight Engineering Status

    SciTech Connect

    Fast, James E.; Dorow, Kevin E.; Morris, Scott J.; Thompson, Robert C.; Willett, Jesse A.

    2010-04-06

    The Multi-sensor Airborne Radiation Survey Flight Engineering project (MARS FE) has designed a high purity germanium (HPGe) crystal array for conducting a wide range of field measurements. In addition to the HPGe detector system, a platform-specific shock and vibration isolation system and environmental housing have been designed to support demonstration activities in a maritime environment on an Unmanned Surface Vehicle (USV). This report describes the status of the equipment as of the end of FY09.

  3. Infrared Thermography Flight Experimentation

    NASA Technical Reports Server (NTRS)

    Blanchard, Robert C.; Carter, Matthew L.; Kirsch, Michael

    2003-01-01

    Analysis was done on IR data collected by DFRC on May 8, 2002. This includes the generation of a movie to initially examine the IR flight data. The production of the movie was challenged by the volume of data that needed to be processed, namely 40,500 images with each image (256 x 252) containing over 264 million points (pixel depth 4096). It was also observed during the initial analysis that the RTD surface coating has a different emissivity than the surroundings. This fact added unexpected complexity in obtaining a correlation between RTD data and IR data. A scheme was devised to generate IR data near the RTD location which is not affected by the surface coating This scheme is valid as long as the surface temperature as measured does not change too much over a few pixel distances from the RTD location. After obtaining IR data near the RTD location, it is possible to make a direct comparison with the temperature as measured during the flight after adjusting for the camera s auto scaling. The IR data seems to correlate well to the flight temperature data at three of the four RID locations. The maximum count intensity occurs closely to the maximum temperature as measured during flight. At one location (RTD #3), there is poor correlation and this must be investigated before any further progress is possible. However, with successful comparisons at three locations, it seems there is great potential to be able to find a calibration curve for the data. Moreover, as such it will be possible to measure temperature directly from the IR data in the near future.

  4. Neural Flight Control System

    NASA Technical Reports Server (NTRS)

    Gundy-Burlet, Karen

    2003-01-01

    The Neural Flight Control System (NFCS) was developed to address the need for control systems that can be produced and tested at lower cost, easily adapted to prototype vehicles and for flight systems that can accommodate damaged control surfaces or changes to aircraft stability and control characteristics resulting from failures or accidents. NFCS utilizes on a neural network-based flight control algorithm which automatically compensates for a broad spectrum of unanticipated damage or failures of an aircraft in flight. Pilot stick and rudder pedal inputs are fed into a reference model which produces pitch, roll and yaw rate commands. The reference model frequencies and gains can be set to provide handling quality characteristics suitable for the aircraft of interest. The rate commands are used in conjunction with estimates of the aircraft s stability and control (S&C) derivatives by a simplified Dynamic Inverse controller to produce virtual elevator, aileron and rudder commands. These virtual surface deflection commands are optimally distributed across the aircraft s available control surfaces using linear programming theory. Sensor data is compared with the reference model rate commands to produce an error signal. A Proportional/Integral (PI) error controller "winds up" on the error signal and adds an augmented command to the reference model output with the effect of zeroing the error signal. In order to provide more consistent handling qualities for the pilot, neural networks learn the behavior of the error controller and add in the augmented command before the integrator winds up. In the case of damage sufficient to affect the handling qualities of the aircraft, an Adaptive Critic is utilized to reduce the reference model frequencies and gains to stay within a flyable envelope of the aircraft.

  5. Flight Crew Health Maintenance

    NASA Technical Reports Server (NTRS)

    Gullett, C. C.

    1970-01-01

    The health maintenance program for commercial flight crew personnel includes diet, weight control, and exercise to prevent heart disease development and disability grounding. The very high correlation between hypertension and overweight in cardiovascular diseases significantly influences the prognosis for a coronary prone individual and results in a high rejection rate of active military pilots applying for civilian jobs. In addition to physical fitness the major items stressed in pilot selection are: emotional maturity, glucose tolerance, and family health history.

  6. Dryden Flight Research Center

    NASA Technical Reports Server (NTRS)

    Kostyk, Christopher Barry

    2007-01-01

    As part of a session at the 2007 Thermal & Fluids Analysis Workshop (TFAWS), an overview of the operations at NASA Dryden Flight Research Center was given. Mission support at this site includes the Aeronautics Research Mission Directorate (ARMD); Exploration Systems Mission Directorate (ESMD), Science - ER-2; Science - G3 UAVSAR; Science - Ikhana and Space Operations. In addition, the presentation describes TFAWS related work at Dryden.

  7. Flight Software Math Library

    NASA Technical Reports Server (NTRS)

    McComas, David

    2013-01-01

    The flight software (FSW) math library is a collection of reusable math components that provides typical math utilities required by spacecraft flight software. These utilities are intended to increase flight software quality reusability and maintainability by providing a set of consistent, well-documented, and tested math utilities. This library only has dependencies on ANSI C, so it is easily ported. Prior to this library, each mission typically created its own math utilities using ideas/code from previous missions. Part of the reason for this is that math libraries can be written with different strategies in areas like error handling, parameters orders, naming conventions, etc. Changing the utilities for each mission introduces risks and costs. The obvious risks and costs are that the utilities must be coded and revalidated. The hidden risks and costs arise in miscommunication between engineers. These utilities must be understood by both the flight software engineers and other subsystem engineers (primarily guidance navigation and control). The FSW math library is part of a larger goal to produce a library of reusable Guidance Navigation and Control (GN&C) FSW components. A GN&C FSW library cannot be created unless a standardized math basis is created. This library solves the standardization problem by defining a common feature set and establishing policies for the library s design. This allows the libraries to be maintained with the same strategy used in its initial development, which supports a library of reusable GN&C FSW components. The FSW math library is written for an embedded software environment in C. This places restrictions on the language features that can be used by the library. Another advantage of the FSW math library is that it can be used in the FSW as well as other environments like the GN&C analyst s simulators. This helps communication between the teams because they can use the same utilities with the same feature set and syntax.

  8. X-29 flight maneuvers

    NASA Technical Reports Server (NTRS)

    1989-01-01

    Two X-29 aircraft, featuring one of the most unusual designs in aviation history, were flown at the NASA Dryden Flight Research Center, Edwards, Calif., as technology demonstrators to investigate a host of advanced concepts and technologies. This 30-second clip of air-to-air footage shows the X-29 as it makes hard left and right aileron turns followed up with a few barrel rolls.

  9. Advanced flight control system study

    NASA Technical Reports Server (NTRS)

    Hartmann, G. L.; Wall, J. E., Jr.; Rang, E. R.; Lee, H. P.; Schulte, R. W.; Ng, W. K.

    1982-01-01

    A fly by wire flight control system architecture designed for high reliability includes spare sensor and computer elements to permit safe dispatch with failed elements, thereby reducing unscheduled maintenance. A methodology capable of demonstrating that the architecture does achieve the predicted performance characteristics consists of a hierarchy of activities ranging from analytical calculations of system reliability and formal methods of software verification to iron bird testing followed by flight evaluation. Interfacing this architecture to the Lockheed S-3A aircraft for flight test is discussed. This testbed vehicle can be expanded to support flight experiments in advanced aerodynamics, electromechanical actuators, secondary power systems, flight management, new displays, and air traffic control concepts.

  10. Solar array flight experiment

    NASA Technical Reports Server (NTRS)

    1986-01-01

    Emerging satellite designs require increasing amounts of electrical power to operate spacecraft instruments and to provide environments suitable for human habitation. In the past, electrical power was generated by covering rigid honeycomb panels with solar cells. This technology results in unacceptable weight and volume penalties when large amounts of power are required. To fill the need for large-area, lightweight solar arrays, a fabrication technique in which solar cells are attached to a copper printed circuit laminated to a plastic sheet was developed. The result is a flexible solar array with one-tenth the stowed volume and one-third the weight of comparably sized rigid arrays. An automated welding process developed to attack the cells to the printed circuit guarantees repeatable welds that are more tolerant of severe environments than conventional soldered connections. To demonstrate the flight readiness of this technology, the Solar Array Flight Experiment (SAFE) was developed and flown on the space shuttle Discovery in September 1984. The tests showed the modes and frequencies of the array to be very close to preflight predictions. Structural damping, however, was higher than anticipated. Electrical performance of the active solar panel was also tested. The flight performance and postflight data evaluation are described.

  11. X-4 in flight

    NASA Technical Reports Server (NTRS)

    1951-01-01

    In the early days of transonic flight research, many aerodynamicists believed that eliminating conventional tail surfaces could reduce the problems created by shock wave interaction with the tail's lifting surfaces. To address this issue, the Army Air Forces's Air Technical Service awarded a contract to Northrop Aircraft Corporation on 5 April 1946 to build a piloted 'flying laboratory.' Northrop already had experience with tailless flying wing designs such as the N-1M, N-9M, XB-35, and YB-49. Subsequently, the manufacturer built two semi-tailless X-4 research aircraft, the first of which flew half a century ago. The X-4 was designed to investigate transonic compressibility effects at speeds near Mach 0.85 to 0.88, slightly below the speed of sound. Northrop project engineer Arthur Lusk designed the aircraft with swept wings and a conventional fuselage that housed two turbojet engines. It had a vertical stabilizer, but no horizontal tail surfaces. It was one of the smallest X-planes ever built, and every bit of internal space was used for systems and instrumentation. The first X-4 arrived at Muroc Air Force Base by truck on 15 November 1948. Over the course of several weeks, engineers conducted static tests, and Northrop test pilot Charles Tucker made initial taxi runs. Although small of stature, he barely fit into the diminutive craft. Tucker, a veteran Northrop test pilot, had previously flown the XB-35 and YB-49 flying wing bomber prototypes. Prior to flying for Northrop, he had logged 400 hours in jet airplanes as a test pilot for Lockheed and the Air Force. He would now be responsible for completing the contractor phase of the X-4 flight test program. Finally, all was ready. Tucker climbed into the cockpit, and made the first flight on 15 December 1948. It only lasted 18 minutes, allowing just enough time for the pilot to become familiar with the basic handling qualities of the craft. The X-4 handled well, but Tucker noted some longitudinal instability at all

  12. Conceptual design of a crewed reusable space transportation system aimed at parabolic flights: stakeholder analysis, mission concept selection, and spacecraft architecture definition

    NASA Astrophysics Data System (ADS)

    Fusaro, Roberta; Viola, Nicole; Fenoglio, Franco; Santoro, Francesco

    2016-06-01

    This paper proposes a methodology to derive architectures and operational concepts for future earth-to-orbit and sub-orbital transportation systems. In particular, at first, it describes the activity flow, methods, and tools leading to the generation of a wide range of alternative solutions to meet the established goal. Subsequently, the methodology allows selecting a small number of feasible options among which the optimal solution can be found. For the sake of clarity, the first part of the paper describes the methodology from a theoretical point of view, while the second part proposes the selection of mission concepts and of a proper transportation system aimed at sub-orbital parabolic flights. Starting from a detailed analysis of the stakeholders and their needs, the major objectives of the mission have been derived. Then, following a system engineering approach, functional analysis tools as well as concept of operations techniques allowed generating a very high number of possible ways to accomplish the envisaged goals. After a preliminary pruning activity, aimed at defining the feasibility of these concepts, more detailed analyses have been carried out. Going on through the procedure, the designer should move from qualitative to quantitative evaluations, and for this reason, to support the trade-off analysis, an ad-hoc built-in mission simulation software has been exploited. This support tool aims at estimating major mission drivers (mass, heat loads, manoeuverability, earth visibility, and volumetric efficiency) as well as proving the feasibility of the concepts. Other crucial and multi-domain mission drivers, such as complexity, innovation level, and safety have been evaluated through the other appropriate analyses. Eventually, one single mission concept has been selected and detailed in terms of layout, systems, and sub-systems, highlighting also logistic, safety, and maintainability aspects.

  13. Conceptual design of a crewed reusable space transportation system aimed at parabolic flights: stakeholder analysis, mission concept selection, and spacecraft architecture definition

    NASA Astrophysics Data System (ADS)

    Fusaro, Roberta; Viola, Nicole; Fenoglio, Franco; Santoro, Francesco

    2017-03-01

    This paper proposes a methodology to derive architectures and operational concepts for future earth-to-orbit and sub-orbital transportation systems. In particular, at first, it describes the activity flow, methods, and tools leading to the generation of a wide range of alternative solutions to meet the established goal. Subsequently, the methodology allows selecting a small number of feasible options among which the optimal solution can be found. For the sake of clarity, the first part of the paper describes the methodology from a theoretical point of view, while the second part proposes the selection of mission concepts and of a proper transportation system aimed at sub-orbital parabolic flights. Starting from a detailed analysis of the stakeholders and their needs, the major objectives of the mission have been derived. Then, following a system engineering approach, functional analysis tools as well as concept of operations techniques allowed generating a very high number of possible ways to accomplish the envisaged goals. After a preliminary pruning activity, aimed at defining the feasibility of these concepts, more detailed analyses have been carried out. Going on through the procedure, the designer should move from qualitative to quantitative evaluations, and for this reason, to support the trade-off analysis, an ad-hoc built-in mission simulation software has been exploited. This support tool aims at estimating major mission drivers (mass, heat loads, manoeuverability, earth visibility, and volumetric efficiency) as well as proving the feasibility of the concepts. Other crucial and multi-domain mission drivers, such as complexity, innovation level, and safety have been evaluated through the other appropriate analyses. Eventually, one single mission concept has been selected and detailed in terms of layout, systems, and sub-systems, highlighting also logistic, safety, and maintainability aspects.

  14. The 737 graphite composite flight spoiler flight service evaluation

    NASA Technical Reports Server (NTRS)

    Coggeshall, R. L.

    1985-01-01

    The flight service experience of 111 graphite-epoxy spoilers on 737 transport aircraft and related ground based environmental exposure of graphite-epoxy material specimens is covered. Spoilers have been installed on 28 aircraft representing seven major airlines operating throughout the world. An extended flight service evaluation program of 15 years is presently underway. As of December 1984, a total of 2,092, 155 spoiler flight hours and 2,954,814 spoiler landings had been accumulated by this fleet.

  15. Orion Pad Abort 1 Flight Test - Ground and Flight Operations

    NASA Technical Reports Server (NTRS)

    Hackenbergy, Davis L.; Hicks, Wayne

    2011-01-01

    This paper discusses the ground and flight operations aspects to the Pad Abort 1 launch. The paper details the processes used to plan all operations. The paper then discussions the difficulties of integration and testing, while detailing some of the lessons learned throughout the entire launch campaign. Flight operational aspects of the launc are covered in order to provide the listener with the full suite of operational issues encountered in preparation for the first flight test of the Orion Launch Abort System.

  16. The 737 graphite composite flight spoiler flight service evaluation

    NASA Technical Reports Server (NTRS)

    Coggeshall, Randy L.

    1987-01-01

    The ninth flight service report was prepared in compliance with the requirements of Contract NAS1-11668. It covers the flight service experience of 111 graphite-epoxy spoilers on 737 transport aircraft and related ground-based environmental exposure of graphite epoxy material specimens for the period 1 Jan. 1985 through 31 Dec. 1986. Spoilers have been installed on 28 aircraft representing seven major airlines operating throughout the world. An extended flight service evaluation program of 15 years is presently underway. As of 31 Dec. 1986, a total of 3,339,608 spoiler flight-hours and 3,320,952 spoiler landings had been accumulated by this fleet.

  17. Enhanced Flight Termination System Flight Demonstration and Results

    NASA Technical Reports Server (NTRS)

    Tow, David; Arce, Dennis

    2007-01-01

    This paper discusses the methodology, requirements, tests, and implementation plan for the live demonstration of the Enhanced Flight Termination System (EFTS) using a missile program at two locations in Florida: Eglin Air Force Base (AFB) and Tyndall AFB. The demonstration included the integration of EFTS Flight Termination Receivers (FTRs) onto the missile and the integration of EFTS-program-developed transmitter assets with the mission control system at Eglin and Tyndall AFBs. The initial test stages included ground testing and captive-carry flights, followed by a launch in which EFTS was designated as the primary flight termination system for the launch.

  18. Flight Mechanics Project

    NASA Technical Reports Server (NTRS)

    Steck, Daniel

    2009-01-01

    This report documents the generation of an outbound Earth to Moon transfer preliminary database consisting of four cases calculated twice a day for a 19 year period. The database was desired as the first step in order for NASA to rapidly generate Earth to Moon trajectories for the Constellation Program using the Mission Assessment Post Processor. The completed database was created running a flight trajectory and optimization program, called Copernicus, in batch mode with the use of newly created Matlab functions. The database is accurate and has high data resolution. The techniques and scripts developed to generate the trajectory information will also be directly used in generating a comprehensive database.

  19. The Third Flight Magnet

    NASA Technical Reports Server (NTRS)

    McGhee, R. Wayne

    1998-01-01

    A self-shielded superconducting magnet was designed for the NASA Goddard Space Flight Center Adiabatic Demagnetization Refrigerator Program. This is the third magnet built from this design. The magnets utilize Cryomagnetics' patented ultra-low current technology. The magnetic system is capable of reaching a central field of two tesla at slightly under two amperes and has a total inductance of 1068 henries. This final report details the requirements of the magnet, the specifications of the resulting magnet, the test procedures and test result data for the third magnet (Serial # C-654-M), and recommended precautions for use of the magnet.

  20. In-Flight System Identification

    NASA Technical Reports Server (NTRS)

    Morelli, Eugene A.

    1998-01-01

    A method is proposed and studied whereby the system identification cycle consisting of experiment design and data analysis can be repeatedly implemented aboard a test aircraft in real time. This adaptive in-flight system identification scheme has many advantages, including increased flight test efficiency, adaptability to dynamic characteristics that are imperfectly known a priori, in-flight improvement of data quality through iterative input design, and immediate feedback of the quality of flight test results. The technique uses equation error in the frequency domain with a recursive Fourier transform for the real time data analysis, and simple design methods employing square wave input forms to design the test inputs in flight. Simulation examples are used to demonstrate that the technique produces increasingly accurate model parameter estimates resulting from sequentially designed and implemented flight test maneuvers. The method has reasonable computational requirements, and could be implemented aboard an aircraft in real time.

  1. KC-135 winglet flight results

    NASA Technical Reports Server (NTRS)

    Montoya, L. C.

    1981-01-01

    Three KC-135 winglet configurations were flight tested for cant/incidence angles of 15 deg/-4 deg, 15 deg/-2 deg, and 0 deg/-4 deg, as well as the basic wing. The flight results for the 15 deg/-4 deg and basic wing configurations confirm the wind tunnel predicted 7% incremental decrease in total drag at cruise conditions. The 15 deg/-4 configuration flight measured wing and winglet pressure distributions, loads, stability and control, flutter, and buffet also correlate well with predicted values. The only unexpected flight results as compared with analytical predictions is a flutter speed decrease for the 0 deg/-4 deg configuration. The 15 deg/-2 deg configuration results show essentially the same incremental drag reduction as the 15 deg/-4 deg configuration; however, the flight loads are approximately 30% higher for the 15 deg/-2 deg configuration. The drag data for the 0 deg/-4 deg configuration show only a flight drag reduction.

  2. An Autonomous Flight Safety System

    NASA Technical Reports Server (NTRS)

    Bull, James B.; Lanzi, Raymond J.

    2007-01-01

    The Autonomous Flight Safety System (AFSS) being developed by NASA s Goddard Space Flight Center s Wallops Flight Facility and Kennedy Space Center has completed two successful developmental flights and is preparing for a third. AFSS has been demonstrated to be a viable architecture for implementation of a completely vehicle based system capable of protecting life and property in event of an errant vehicle by terminating the flight or initiating other actions. It is capable of replacing current human-in-the-loop systems or acting in parallel with them. AFSS is configured prior to flight in accordance with a specific rule set agreed upon by the range safety authority and the user to protect the public and assure mission success. This paper discusses the motivation for the project, describes the method of development, and presents an overview of the evolving architecture and the current status.

  3. Advanced flight control system study

    NASA Technical Reports Server (NTRS)

    Mcgough, J.; Moses, K.; Klafin, J. F.

    1982-01-01

    The architecture, requirements, and system elements of an ultrareliable, advanced flight control system are described. The basic criteria are functional reliability of 10 to the minus 10 power/hour of flight and only 6 month scheduled maintenance. A distributed system architecture is described, including a multiplexed communication system, reliable bus controller, the use of skewed sensor arrays, and actuator interfaces. Test bed and flight evaluation program are proposed.

  4. XB-70A in flight

    NASA Technical Reports Server (NTRS)

    1968-01-01

    The XB-70 was the world's largest experimental aircraft. Capable of flight at speeds of three times the speed of sound (2,000 miles per hour) at altitudes of 70,000 feet, the XB-70 was used to collect in-flight information for use in the design of future supersonic aircraft, military and civilian. This 23-second video clip shows the XB-70A taxiing, taking off, and in flight.

  5. Suborbital measurements of spectral aerosol optical depth and its variability at sub-satellite-grid scales in support of CLAMS, 2001

    NASA Astrophysics Data System (ADS)

    Redemann, J.; Schmid, B.; Eilers, J. A.; Kahn, R.; Levy, R. C.; Russell, P. B.; Livingston, J. M.; Hobbs, P. V.; Smith, W. L.; Holben, B. N.

    2003-12-01

    As part of the Chesapeake Lighthouse and Aircraft Measurements for Satellites (CLAMS) experiment, July 10 - August 2, 2001, the 14-channel NASA Ames Airborne Tracking Sunphotometer (AATS-14) was operated aboard the University of Washington CV-580 during 10 research flights (\\~45 flight hours). Among others, CLAMS research goals included validation of satellite-based retrievals of aerosol properties. AATS-14 measures the direct solar beam transmission at 14 discrete wavelengths (354-1558 nm), yielding aerosol optical depth spectra and columnar water vapor for such validation purposes. Comparisons of AOD between the AERONET Cimel instrument at COVE and airborne measurements by AATS-14 in its vicinity showed good agreement with largest r-square correlation coefficients at wavelengths of 380 and 500nm (>0.99). Coordinated low-level flight tracks of the CV-580 during Terra overpass times permitted validation of over-ocean MODIS level 2 (MOD04_L2) multi-wavelength AOD data (10x10km, nadir) in 16 cases on 3 separate days. While the correlation between AATS-14 and MODIS-derived AOD was poor with an r-square of 0.55, almost 75% of all MODIS AOD measurements were still in the desired uncertainty range (+/-0.03+/-0.05*AOD). This may be due to the small AODs (generally less than 0.1 at 500nm) encountered in these comparison cases. An analogous coordination exercise resulted in 7 exact over-ocean match-ups between AATS-14 and MISR measurements. The comparison between AATS-14 and the MISR standard algorithm regional mean AODs showed a much stronger correlation with an r-square of 0.94. However, MISR AODs were systematically higher than the corresponding AATS values, with an rms difference of 0.06. AATS data collected during nine extended low-level CV-580 flight tracks were used to assess spatial variability in AOD at horizontal scales up to 100 km. At UV and mid-visible wavelengths, the largest absolute gradients in AOD were 0.1-0.2 per 50 km horizontal distance. In the near IR

  6. Information Display System for Atypical Flight Phase

    NASA Technical Reports Server (NTRS)

    Statler, Irving C. (Inventor); Ferryman, Thomas A. (Inventor); Amidan, Brett G. (Inventor); Whitney, Paul D. (Inventor); White, Amanda M. (Inventor); Willse, Alan R. (Inventor); Cooley, Scott K. (Inventor); Jay, Joseph Griffith (Inventor); Lawrence, Robert E. (Inventor); Mosbrucker, Chris J. (Inventor); Rosenthal, Loren J. (Inventor); Lynch, Robert E. (Inventor); Chidester, Thomas R. (Inventor); Prothero, Gary L. (Inventor); Andrei, Adi (Inventor); Romanowski, Timothy P. (Inventor); Robin, Daniel E. (Inventor); Prothero, Jason W. (Inventor)

    2007-01-01

    Method and system for displaying information on one or more aircraft flights, where at least one flight is determined to have at least one atypical flight phase according to specified criteria. A flight parameter trace for an atypical phase is displayed and compared graphically with a group of traces, for the corresponding flight phase and corresponding flight parameter, for flights that do not manifest atypicality in that phase.

  7. Human Space Flight

    NASA Technical Reports Server (NTRS)

    Woolford, Barbara

    2006-01-01

    The performance of complex tasks on the International Space Station (ISS) requires significant preflight crew training commitments and frequent skill and knowledge refreshment. This report documents a recently developed just-in-time training methodology, which integrates preflight hardware familiarization and procedure training with an on-orbit CD-ROM-based skill enhancement. This just-in-time concept was used to support real-time remote expert guidance to complete medical examinations using the ISS Human Research Facility (HRF). An American md Russian ISS crewmember received 2-hours of hands on ultrasound training 8 months prior to the on-orbit ultrasound exam. A CD-ROM-based Onboard Proficiency Enhancement (OPE) interactive multimedia program consisting of memory enhancing tutorials, and skill testing exercises, was completed by the crewmember six days prior to the on-orbit ultrasound exam. The crewmember was then remotely guided through a thoracic, vascular, and echocardiographic examination by ultrasound imaging experts. Results of the CD ROM based OPE session were used to modify the instructions during a complete 35 minute real-time thoracic, cardiac, and carotid/jugular ultrasound study. Following commands from the ground-based expert, the crewmember acquired all target views and images without difficulty. The anatomical content and fidelity of ultrasound video were excellent and adequate for clinical decision-making. Complex ultrasound experiments with expert guidance were performed with high accuracy following limited pre-flight training and CD-ROM-based in-flight review, despite a 2-second communication latency.

  8. NASA - Human Space Flight

    NASA Technical Reports Server (NTRS)

    Davis, Jeffrey R.

    2006-01-01

    The presentation covers five main topical areas. The first is a description of how things work in the microgravity environment such as convection and sedimentation. The second part describes the effects of microgravity on human physiology. This is followed by a description of the hazards of space flight including the environment, the space craft, and the mission. An overview of biomedical research in space, both on shuttle and ISS is the fourth section of the presentation. The presentation concludes with a history of space flight from Ham to ISS. At CART students (11th and 12th graders from Fresno Unified and Clovis Unified) are actively involved in their education. They work in teams to research real world problems and discover original solutions. Students work on projects guided by academic instructors and business partners. They will have access to the latest technology and will be expected to expand their learning environment to include the community. They will focus their studies around a career area (Professional Sciences, Advanced Communications, Engineering and Product Development, or Global Issues).

  9. [In-flight emergencies].

    PubMed

    Jessen, Knud

    2005-10-17

    It is estimated that at least one billion passengers travel by air every year. It is predicted that this number will double in the future, including an increasing number of aged passengers. It is further estimated that for every ten million passengers, 225 acute in-flight incidents and one death will occur. Modern commercial aircraft impose certain physical and physiological stresses on passengers, due mainly to the lowered barometric pressure in the cabin during cruising. The top five in-flight incidents are vasovagal, cardiac, pulmonary, and gastrointestinal attacks and minor traumas and burns. Travel by air is, however, safe and can be tolerated by most people. Each aircraft is equipped with emergency oxygen and medical kits, the crew is trained in advanced first aid, and a link to a ground-based medical centre often exists. Ill and elderly people can have their journey specifically prepared for by communication between their physician and the medical service of the particular company, providing the best opportunity for a smooth journey.

  10. BEAM Technology Flight Demonstration

    NASA Technical Reports Server (NTRS)

    Wang, David

    2005-01-01

    As technologies advance, their growing complexity makes them harder to maintain. Detection methods for isolating and identifying impending problems are needed to balance this complexity. Through comparison of signal pairs from onboard sensors, the Beacon-based Exception Analysis For Multimissions (BEAM) algorithm can identify and help classify deviations in system operation from a data-trained statistical model. The goal of this task is to mature BEAM and validate its performance on a flying test bed. A series of F-18 flight demonstrations with BEAM monitoring engine parameters in real time was used to demonstrate in-the-field readiness. Captured F-18 and simulated F-18 engine data were used in model creation and training. The algorithm was then ported to the embedded system with a data buffering, file writing, and data-time-stamp monitoring shell to reduce the impact of embedded system faults on BEAM'S ability to correctly identify engine faults. Embedded system testing identified hardware related restrictions and contributed to iterative improvements in the code's runtime performance. The system was flown with forced engine flameouts and other pilot induced faults to simulate operation out of the norm. Successful detection of these faults, confirmed through post-flight data analysis, helped BEAM achieve TRL6.

  11. Shuttle Risk Progression by Flight

    NASA Technical Reports Server (NTRS)

    Hamlin, Teri; Kahn, Joe; Thigpen, Eric; Zhu, Tony; Lo, Yohon

    2011-01-01

    Understanding the early mission risk and progression of risk as a vehicle gains insights through flight is important: . a) To the Shuttle Program to understand the impact of re-designs and operational changes on risk. . b) To new programs to understand reliability growth and first flight risk. . Estimation of Shuttle Risk Progression by flight: . a) Uses Shuttle Probabilistic Risk Assessment (SPRA) and current knowledge to calculate early vehicle risk. . b) Shows impact of major Shuttle upgrades. . c) Can be used to understand first flight risk for new programs.

  12. Tactical Night Terrain Flight Navigation

    DTIC Science & Technology

    1979-09-01

    an reverse aide It necesarmy and identify by block unmber) Terrain flight Night flight Surface nav’igation 20,. AW4~ACT ( C ~venoUa sov ero " eom a maa...were used on each test flight. The helicopter used for the low-level flights were equipped initially with a commercial radar altimeter with a single...indicator, which was later changed to a military AN/APN-209 radar altimeter with dual indicators. The second helicopter was used for command and

  13. Development and Flight-testing of Astronomical Instrumentation for Future NASA Astrophysics Missions

    NASA Astrophysics Data System (ADS)

    France, Kevin

    We propose a four year suborbital research program to continue the University of Colorado's efforts in the development and flight testing of instrument designs and critical path technologies for ultraviolet spectroscopy in support of future NASA Explorer, Probe-, and Flagship-class missions. This proposal builds on our existing program of high-resolution spectroscopy for the 100 - 160 nm bandpass with the development of a new high-efficiency imaging spectrograph operating in the same band. The ultimate goal of the University of Colorado ultraviolet rocket program is to develop the technical capabilities to enable a future, highly multiplexed ultraviolet spectrograph (with both high-resolution and imaging spectroscopy modes), e.g., an analog to the successful HST-STIS instrument, with an order-of-magnitude higher efficiency. We do this in the framework of a university led program where undergraduate, graduate, and postdoctoral training is paramount and cutting edge science investigations support our baseline technology development program. In the proposed effort, we will optimize our high-resolution (R > 100,000) echelle spectrograph payload (CHESS) with the first science flight of a new, large-format CCD array provided by our collaborators at JPL and Arizona State University. We will launch CHESS to study our local interstellar environment with spectral resolving power and bandpass that cannot be achieved with any suite of current or planned space missions. In parallel with the proposed science flights of CHESS, we will design, calibrate, and launch a new high-throughput imaging spectrograph (SISTINE); the first sub-arcsecond imaging, medium spectral resolution (R = 10,000), spectrograph ever flown with spectral coverage over the entire 100 - 160 nm bandpass. SISTINE incorporates several novel optical technologies that were highlighted as major hardware drivers for NASA's next large ultraviolet/optical/near-IR observatory by the 2014 Cosmic Origins Technology

  14. SHEFEX II Flight Instrumentation And Preparation Of Post Flight Analysis

    NASA Astrophysics Data System (ADS)

    Thiele, Thomas; Siebe, Frank; Gulhan, Ali

    2011-05-01

    A main disadvantage of modern TPS systems for re- entry vehicles is the expensive manufacturing and maintenance process due to the complex geometry of these blunt nose configurations. To reduce the costs and to improve the aerodynamic performance the German Aerospace Center (DLR) is following a different approach using TPS structures consisting of flat ceramic tiles. To test these new sharp edged TPS structures the SHEFEX I flight experiment was designed and successfully performed by DLR in 2005. To further improve the reliability of the sharp edged TPS design at even higher Mach numbers, a second flight experiment SHEFEX II will be performed in September 2011. In comparison to SHEFEX I the second flight experiment has a fully symmetrical shape and will reach a maximum Mach number of about 11. Furthermore the vehicle has an active steering system using four canards to control the flight attitude during re-entry, e.g. roll angle, angle of attack and sideslip. After a successful flight the evaluation of the flight data will be performed using a combination of numerical and experimental tools. The data will be used for the improvement of the present numerical analysis tools and to get a better understanding of the aerothermal behaviour of sharp TPS structures. This paper presents the flight instrumentation of the SHEFEX II TPS. In addition the concept of the post flight analysis is presented.

  15. Stirling to Flight Initiative

    NASA Technical Reports Server (NTRS)

    Hibbard, Kenneth E.; Mason, Lee S.; Ndu, Obi; Smith, Clayton; Withrow, James P.

    2016-01-01

    Flight (S2F) initiative with the objective of developing a 100-500 We Stirling generator system. Additionally, a different approach is being devised for this initiative to avoid pitfalls of the past, and apply lessons learned from the recent ASRG experience. Two key aspects of this initiative are a Stirling System Technology Maturation Effort, and a Surrogate Mission Team (SMT) intended to provide clear mission pull and requirements context. The S2F project seeks to lead directly into a DOE flight system development of a new SRG. This paper will detail the proposed S2F initiative, and provide specifics on the key efforts designed to pave a forward path for bringing Stirling technology to flight.

  16. Do birds sleep in flight?

    NASA Astrophysics Data System (ADS)

    Rattenborg, Niels C.

    2006-09-01

    The following review examines the evidence for sleep in flying birds. The daily need to sleep in most animals has led to the common belief that birds, such as the common swift ( Apus apus), which spend the night on the wing, sleep in flight. The electroencephalogram (EEG) recordings required to detect sleep in flight have not been performed, however, rendering the evidence for sleep in flight circumstantial. The neurophysiology of sleep and flight suggests that some types of sleep might be compatible with flight. As in mammals, birds exhibit two types of sleep, slow-wave sleep (SWS) and rapid eye-movement (REM) sleep. Whereas, SWS can occur in one or both brain hemispheres at a time, REM sleep only occurs bihemispherically. During unihemispheric SWS, the eye connected to the awake hemisphere remains open, a state that may allow birds to visually navigate during sleep in flight. Bihemispheric SWS may also be possible during flight when constant visual monitoring of the environment is unnecessary. Nevertheless, the reduction in muscle tone that usually accompanies REM sleep makes it unlikely that birds enter this state in flight. Upon landing, birds may need to recover the components of sleep that are incompatible with flight. Periods of undisturbed postflight recovery sleep may be essential for maintaining adaptive brain function during wakefulness. The recent miniaturization of EEG recording devices now makes it possible to measure brain activity in flight. Determining if and how birds sleep in flight will contribute to our understanding of a largely unexplored aspect of avian behavior and may also provide insight into the function of sleep.

  17. 49 CFR 1552.3 - Flight training.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 49 Transportation 9 2010-10-01 2010-10-01 false Flight training. 1552.3 Section 1552.3..., DEPARTMENT OF HOMELAND SECURITY CIVIL AVIATION SECURITY FLIGHT SCHOOLS Flight Training for Aliens and Other Designated Individuals § 1552.3 Flight training. This section describes the procedures a flight school...

  18. Digital flight control systems

    NASA Technical Reports Server (NTRS)

    Caglayan, A. K.; Vanlandingham, H. F.

    1977-01-01

    The design of stable feedback control laws for sampled-data systems with variable rate sampling was investigated. These types of sampled-data systems arise naturally in digital flight control systems which use digital actuators where it is desirable to decrease the number of control computer output commands in order to save wear and tear of the associated equipment. The design of aircraft control systems which are optimally tolerant of sensor and actuator failures was also studied. Detection of the failed sensor or actuator must be resolved and if the estimate of the state is used in the control law, then it is also desirable to have an estimator which will give the optimal state estimate even under the failed conditions.

  19. Flight deck engine advisor

    NASA Technical Reports Server (NTRS)

    Shontz, W. D.; Records, R. M.; Antonelli, D. R.

    1992-01-01

    The focus of this project is on alerting pilots to impending events in such a way as to provide the additional time required for the crew to make critical decisions concerning non-normal operations. The project addresses pilots' need for support in diagnosis and trend monitoring of faults as they affect decisions that must be made within the context of the current flight. Monitoring and diagnostic modules developed under the NASA Faultfinder program were restructured and enhanced using input data from an engine model and real engine fault data. Fault scenarios were prepared to support knowledge base development activities on the MONITAUR and DRAPhyS modules of Faultfinder. An analysis of the information requirements for fault management was included in each scenario. A conceptual framework was developed for systematic evaluation of the impact of context variables on pilot action alternatives as a function of event/fault combinations.

  20. The Cibola flight experiment

    SciTech Connect

    Caffrey, Michael Paul; Nelson, Anthony; Salazar, Anthony; Roussel - Dupre, Diane; Katko, Kim; Palmer, Joseph; Robinson, Scott; Wirthlin, Michael; Howes, William; Richins, Daniel

    2009-01-01

    The Cibola Flight Experiment (CFE) is an experimental small satellite carrying a reconfigurable processing instrument developed at the Los Alamos National Laboratory that demonstrates the feasibility of using FPGA-based high-performance computing for sensor processing in the space environment. The CFE satellite was launched on March 8, 2007 in low-earth orbit and has operated extremely well since its deployment. The nine Xilinx Virtex FPGAs used in the payload have been used for several high-throughput sensor processing applications and for single-event upset (SEU) monitoring and mitigation. This paper will describe the CFE system and summarize its operational results. In addition, this paper will describe the results from several SEU detection circuits that were performed on the spacecraft.

  1. Flight Operations Analysis Tool

    NASA Technical Reports Server (NTRS)

    Easter, Robert; Herrell, Linda; Pomphrey, Richard; Chase, James; Wertz Chen, Julie; Smith, Jeffrey; Carter, Rebecca

    2006-01-01

    Flight Operations Analysis Tool (FLOAT) is a computer program that partly automates the process of assessing the benefits of planning spacecraft missions to incorporate various combinations of launch vehicles and payloads. Designed primarily for use by an experienced systems engineer, FLOAT makes it possible to perform a preliminary analysis of trade-offs and costs of a proposed mission in days, whereas previously, such an analysis typically lasted months. FLOAT surveys a variety of prior missions by querying data from authoritative NASA sources pertaining to 20 to 30 mission and interface parameters that define space missions. FLOAT provides automated, flexible means for comparing the parameters to determine compatibility or the lack thereof among payloads, spacecraft, and launch vehicles, and for displaying the results of such comparisons. Sparseness, typical of the data available for analysis, does not confound this software. FLOAT effects an iterative process that identifies modifications of parameters that could render compatible an otherwise incompatible mission set.

  2. X-38 - First Flight

    NASA Technical Reports Server (NTRS)

    1997-01-01

    Reminiscent of the lifting body research flights conducted more than 30 years earlier, NASA's B-52 mothership lifts off carrying a new generation of lifting body research vehicle--the X-38. The X-38 was designed to help develop an emergency crew return vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also

  3. X-38 - First Flight

    NASA Technical Reports Server (NTRS)

    1997-01-01

    In a scene reminiscent of the lifting body research flights conducted more than 30 years earlier, this photo shows a close-up view of NASA's B-52 mothership as it lifts off carrying a new generation of lifting body research vehicle--the X-38. The X-38 was designed to help develop an emergency crew return vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the

  4. Cibola flight experiment

    SciTech Connect

    Roussel-Dupre, D.; Caffrey, M. P.

    2004-01-01

    Los Alamos National Laboratory is building the Cibola Flight Experiment (CFE), a reconfigurable processor payload intended for a Low Earth Orbit system. It will survey portions of the VHF and UHF radio spectra. The experiment uses networks of reprogrammable, Field Programmable Gate Arrays (FPGAs) to process the received signals for ionospheric and lightning studies. The objective is to validate the on-orbit use of commercial, reconfigurable FPGA technology utilizing several different single-event upset mitigation schemes. It will also detect and measure impulsive events that occur in a complex background. Surrey Satellite Technology, Ltd (SSTL) is building the small host satellite, CFESat, based upon SSTL's disaster monitoring constellation (DMC) and Topsat mission satellite designs. The CFESat satellite will be launched by the Space Test Program in September 2006 on the US Air Force Evolved Expendable Launch Vehicle (EELV) using the EELV's Secondary Payload Adapter (ESPA) that allows up to six small satellites to be launched as 'piggyback' passengers with larger spacecraft.

  5. Future Flight Central

    NASA Technical Reports Server (NTRS)

    1999-01-01

    NASA 'Future Flight Central,' the world's first full-scale virtual airport control tower, opened December 13, 1999 at NASA Ames Research Center, Moffett Field, California. Constructed at a cost of $10 million, the two story facility was jointly funded by NASA and the Federal Aviation Administration (FAA). The facility is designed to test ways to solve potential air and ground traffic problems at commercial airports under realistic airport conditions and configurations. The facility provides an opportunity for airlines and airports to mitigate passenger delays by fine tuning airport hub operations, gate management, ramp movement procedures, and various other airport improvements. Twelve rear projection screens provide a seamless 360 degree high- resolution view of the airport or other screens being depicted. The imaging system, powered by supercomputers, provides a realistic view of weather conditions, enviromental and seasonal effects and the movement of up to 200 active aircraft and ground vehicles.

  6. Space flight rehabilitation.

    PubMed

    Payne, Michael W C; Williams, David R; Trudel, Guy

    2007-07-01

    The weightless environment of space imposes specific physiologic adaptations on healthy astronauts. On return to Earth, these adaptations manifest as physical impairments that necessitate a period of rehabilitation. Physiologic changes result from unloading in microgravity and highly correlate with those seen in relatively immobile terrestrial patient populations such as spinal cord, geriatric, or deconditioned bed-rest patients. Major postflight impairments requiring rehabilitation intervention include orthostatic intolerance, bone demineralization, muscular atrophy, and neurovestibular symptoms. Space agencies are preparing for extended-duration missions, including colonization of the moon and interplanetary exploration of Mars. These longer-duration flights will result in more severe and more prolonged disability, potentially beyond the point of safe return to Earth. This paper will review and discuss existing space rehabilitation plans for major postflight impairments. Evidence-based rehabilitation interventions are imperative not only to facilitate return to Earth but also to extend the safe duration of exposure to a physiologically hostile microgravity environment.

  7. Adaptive nonlinear flight control

    NASA Astrophysics Data System (ADS)

    Rysdyk, Rolf Theoduor

    1998-08-01

    Research under supervision of Dr. Calise and Dr. Prasad at the Georgia Institute of Technology, School of Aerospace Engineering. has demonstrated the applicability of an adaptive controller architecture. The architecture successfully combines model inversion control with adaptive neural network (NN) compensation to cancel the inversion error. The tiltrotor aircraft provides a specifically interesting control design challenge. The tiltrotor aircraft is capable of converting from stable responsive fixed wing flight to unstable sluggish hover in helicopter configuration. It is desirable to provide the pilot with consistency in handling qualities through a conversion from fixed wing flight to hover. The linear model inversion architecture was adapted by providing frequency separation in the command filter and the error-dynamics, while not exiting the actuator modes. This design of the architecture provides for a model following setup with guaranteed performance. This in turn allowed for convenient implementation of guaranteed handling qualities. A rigorous proof of boundedness is presented making use of compact sets and the LaSalle-Yoshizawa theorem. The analysis allows for the addition of the e-modification which guarantees boundedness of the NN weights in the absence of persistent excitation. The controller is demonstrated on the Generic Tiltrotor Simulator of Bell-Textron and NASA Ames R.C. The model inversion implementation is robustified with respect to unmodeled input dynamics, by adding dynamic nonlinear damping. A proof of boundedness of signals in the system is included. The effectiveness of the robustification is also demonstrated on the XV-15 tiltrotor. The SHL Perceptron NN provides a more powerful application, based on the universal approximation property of this type of NN. The SHL NN based architecture is also robustified with the dynamic nonlinear damping. A proof of boundedness extends the SHL NN augmentation with robustness to unmodeled actuator

  8. X-1 in flight

    NASA Technical Reports Server (NTRS)

    1947-01-01

    The Bell Aircraft Corporation X-1-1 (#46-062) in flight. The shock wave pattern in the exhaust plume is visible. The X-1 series aircraft were air-launched from a modified Boeing B-29 or a B-50 Superfortress bombers. The X-1-1 was painted a bright orange by Bell Aircraft. It was thought that the aircraft would be more visable to those doing the tracking during a flight. When NACA received the airplanes they were painted white, which was an easier color to find in the skies over Muroc Air Field in California. This particular craft was nicknamed 'Glamorous Glennis' by Chuck Yeager in honor of his wife, and is now on permanent display in the Smithsonian Institution's National Air and Space Museum in Washington, DC. There were five versions of the Bell X-1 rocket-powered research aircraft that flew at the NACA High-Speed Flight Research Station, Edwards, California. The bullet-shaped X-1 aircraft were built by Bell Aircraft Corporation, Buffalo, N.Y. for the U.S. Army Air Forces (after 1947, U.S. Air Force) and the National Advisory Committee for Aeronautics (NACA). The X-1 Program was originally designated the XS-1 for EXperimental Sonic. The X-1's mission was to investigate the transonic speed range (speeds from just below to just above the speed of sound) and, if possible, to break the 'sound barrier.' Three different X-1s were built and designated: X-1-1, X-1-2 (later modified to become the X-1E), and X-1-3. The basic X-1 aircraft were flown by a large number of different pilots from 1946 to 1951. The X-1 Program not only proved that humans could go beyond the speed of sound, it reinforced the understanding that technological barriers could be overcome. The X-1s pioneered many structural and aerodynamic advances including extremely thin, yet extremely strong wing sections; supersonic fuselage configurations; control system requirements; powerplant compatibility; and cockpit environments. The X-1 aircraft were the first transonic-capable aircraft to use an all

  9. ER-2 in flight

    NASA Technical Reports Server (NTRS)

    1996-01-01

    In this film clip, we see an ER-2 on its take off roll and climb as it departs from runway 22 at Edwards AFB, California. In 1981, NASA acquired its first ER-2 aircraft. The agency obtained a second ER-2 in 1989. These airplanes replaced two Lockheed U-2 aircraft, which NASA had used to collect scientific data since 1971. The U-2, and later the ER-2, were based at the Ames Research Center, Moffett Field, California, until 1997. In 1997, the ER-2 aircraft and their operations moved to NASA Dryden Flight Research Center, Edwards, California. Since the inaugural flight for this program, August 31, 1971, NASA U-2 and ER-2 aircraft have flown more than 4,000 data missions and test flights in support of scientific research conducted by scientists from NASA, other federal agencies, states, universities, and the private sector. NASA is currently using two ER-2 Airborne Science aircraft as flying laboratories. The aircraft, based at NASA Dryden, collect information about our surroundings, including Earth resources, celestial observations, atmospheric chemistry and dynamics, and oceanic processes. The aircraft also are used for electronic sensor research and development, satellite calibration, and satellite data validation. The ER-2 is a versatile aircraft well-suited to perform multiple mission tasks. It is 30 percent larger than the U-2 with a 20 feet longer wingspan and a considerably increased payload over the older airframe. The aircraft has four large pressurized experiment compartments and a high-capacity AC/DC electrical system, permitting it to carry a variety of payloads on a single mission. The modular design of the aircraft permits rapid installation or removal of payloads to meet changing mission requirements. The ER-2 has a range beyond 3,000 miles (4800 kilometers); is capable of long flight duration and can operate at altitudes up to 70,000 feet (21.3 kilometers) if required. Operating at an altitude of 65,000 feet (19.8 kilometers) the ER-2 acquires data

  10. History of Manned Space Flight

    NASA Technical Reports Server (NTRS)

    1975-01-01

    U.S. manned space projects from Mercury Redstone 3 through Skylab 4 are briefly described including dates, flight duration, crew, and number of earth/moon orbits. The flight costs of each project are itemized. Highlights in the history of the manned space program from 1957 to February, 1974 are included.

  11. Strategy in space flight experiments

    NASA Technical Reports Server (NTRS)

    Marvin, Dean; Severns, James

    1991-01-01

    The main topics of the workshop were the evaluation of both the need for flight testing of solar array hardware and the opportunities for such testing. Spacecraft charging effects, array dynamics, cost-effectiveness, and methods of flight planning were also discussed.

  12. In-flight Medical Emergencies

    PubMed Central

    Chandra, Amit; Conry, Shauna

    2013-01-01

    Introduction: Research and data regarding in-flight medical emergencies during commercial air travel are lacking. Although volunteer medical professionals are often called upon to assist, there are no guidelines or best practices to guide their actions. This paper reviews the literature quantifying and categorizing in-flight medical incidents, discusses the unique challenges posed by the in-flight environment, evaluates the legal aspects of volunteering to provide care, and suggests an approach to managing specific conditions at 30,000 feet. Methods: We conducted a MEDLINE search using search terms relevant to aviation medical emergencies and flight physiology. The reference lists of selected articles were reviewed to identify additional studies. Results: While incidence studies were limited by data availability, syncope, gastrointestinal upset, and respiratory complaints were among the most common medical events reported. Chest pain and cardiovascular events were commonly associated with flight diversion. Conclusion: When in-flight medical emergencies occur, volunteer physicians should have knowledge about the most common in-flight medical incidents, know what is available in on-board emergency medical kits, coordinate their therapy with the flight crew and remote resources, and provide care within their scope of practice. PMID:24106549

  13. STS-80 Post Flight Presentation

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The flight crew of STS-80, Cmdr. Kenneth D. Cockrell, Pilot Kent V. Rominger, Mission Specialists, Tamara E. Jernigan, Thomas D. Jones, and F. Story Musgrave give a post flight presentation of their mission. This presentation is divided into two parts first a slide presentation of still shots, and the second is a video presentation.

  14. Laminar-flow flight experiments

    NASA Technical Reports Server (NTRS)

    Wagner, Richard D.; Maddalon, Dal V.; Bartlett, D. W.; Collier, F. S., Jr.; Braslow, A. L.

    1989-01-01

    The flight testing conducted over the past 10 years in the NASA laminar-flow control (LFC) will be reviewed. The LFC program was directed towards the most challenging technology application, the high supersonic speed transport. To place these recent experiences in perspective, earlier important flight tests will first be reviewed to recall the lessons learned at that time.

  15. Aircraft flight test trajectory control

    NASA Technical Reports Server (NTRS)

    Menon, P. K. A.; Walker, R. A.

    1988-01-01

    Two design techniques for linear flight test trajectory controllers (FTTCs) are described: Eigenstructure assignment and the minimum error excitation technique. The two techniques are used to design FTTCs for an F-15 aircraft model for eight different maneuvers at thirty different flight conditions. An evaluation of the FTTCs is presented.

  16. Energy requirements for space flight

    NASA Technical Reports Server (NTRS)

    Lane, Helen W.

    1992-01-01

    Both the United States and the Soviet Union perform human space research. This paper reviews data available on energy metabolism in the microgravity of space flight. The level of energy utilization in space seems to be similar to that on earth, as does energy availability. However, despite adequate intake of energy and protein and in-flight exercise, lean body mass was catabolized, as indicated by negative nitrogen balance. Metabolic studies during simulated microgravity (bed rest) and true microgravity in flight have shown changes in blood glucose, fatty acids and insulin concentrations, suggesting that energy metabolism may be altered during space flight. Future research should focus on the interactions of lean body mass, diet and exercise in space, and their roles in energy metabolism during space flight.

  17. Applications of Payload Directed Flight

    NASA Technical Reports Server (NTRS)

    Ippolito, Corey; Fladeland, Matthew M.; Yeh, Yoo Hsiu

    2009-01-01

    Next generation aviation flight control concepts require autonomous and intelligent control system architectures that close control loops directly around payload sensors in manner more integrated and cohesive that in traditional autopilot designs. Research into payload directed flight control at NASA Ames Research Center is investigating new and novel architectures that can satisfy the requirements for next generation control and automation concepts for aviation. Tighter integration between sensor and machine requires definition of specific sensor-directed control modes to tie the sensor data directly into a vehicle control structures throughout the entire control architecture, from low-level stability- and control loops, to higher level mission planning and scheduling reasoning systems. Payload directed flight systems can thus provide guidance, navigation, and control for vehicle platforms hosting a suite of onboard payload sensors. This paper outlines related research into the field of payload directed flight; and outlines requirements and operating concepts for payload directed flight systems based on identified needs from the scientific literature.'

  18. Orion Exploration Flight Test Post-Flight Inspection and Analysis

    NASA Technical Reports Server (NTRS)

    Miller, J. E.; Berger, E. L.; Bohl, W. E.; Christiansen, E. L.; Davis, B. A.; Deighton, K. D.; Enriquez, P. A.; Garcia, M. A.; Hyde, J. L.; Oliveras, O. M.

    2017-01-01

    The multipurpose crew vehicle, Orion, is being designed and built for NASA to handle the rigors of crew launch, sustainment and return from scientific missions beyond Earth orbit. In this role, the Orion vehicle is meant to operate in the space environments like the naturally occurring meteoroid and the artificial orbital debris environments (MMOD) with successful atmospheric reentry at the conclusion of the flight. As a result, Orion's reentry module uses durable porous, ceramic tiles on almost thirty square meters of exposed surfaces to accomplish both of these functions. These durable, non-ablative surfaces maintain their surface profile through atmospheric reentry; thus, they preserve any surface imperfections that occur prior to atmospheric reentry. Furthermore, Orion's launch abort system includes a shroud that protects the thermal protection system while awaiting launch and during ascent. The combination of these design features and a careful pre-flight inspection to identify any manufacturing imperfections results in a high confidence that damage to the thermal protection system identified post-flight is due to the in-flight solid particle environments. These favorable design features of Orion along with the unique flight profile of the first exploration flight test of Orion (EFT-1) have yielded solid particle environment measurements that have never been obtained before this flight.

  19. Integrated Approach to Flight Crew Training

    NASA Technical Reports Server (NTRS)

    Carroll, J. E.

    1984-01-01

    The computer based approach used by United Airlines for flight training is discussed. The human factors involved in specific aircraft accidents are addressed. Flight crew interaction and communication as they relate to training and flight safety are considered.

  20. NASA test flights with increased flight stress indices

    NASA Technical Reports Server (NTRS)

    Smith, I. S., Jr.

    1991-01-01

    This paper presents the objectives, results, and conclusions stemming from a series of six test flights conducted for the National Aeronautics and Space Administration (NASA) by the National Scientific Balloon Facility (NSBF). Results from the test flights indicate that: (1) the current two U.S. balloon films are capable of being flown at significantly increased flight stress index values; (2) payload weights less than the design minimum payload can be reliably flown without fear of structural failure due to increased circumferential stress; and (3) large and rapid decreases in payload weight can be tolerated by current balloons without structural failure.

  1. Flight testing of the Capillary Pumped Loop Flight Experiment

    NASA Technical Reports Server (NTRS)

    Butler, Dan; Ottenstein, Laura; Ku, Jentung

    1995-01-01

    The Capillary Pumped Loop Flight Experiment (CAPL) employs a passive two-phase thermal control system that uses the latent heat of vaporization of ammonia to transfer heat over long distances. CAPL was designed as a prototype of the Earth Observing System (EOS) instrument thermal control systems. The purpose of the mission was to provide validation of the system performance in micro-gravity, prior to implementation on EOS. CAPL was flown on STS-60 in February, 1994, with some unexpected results related to gravitational effects on two-phase systems. Flight test results and post flight investigations will be addressed, along with a brief description of the experiment design.

  2. Foreign technology summary of flight crucial flight control systems

    NASA Technical Reports Server (NTRS)

    Rediess, H. A.

    1984-01-01

    A survey of foreign technology in flight crucial flight controls is being conducted to provide a data base for planning future research and technology programs. Only Free World countries were surveyed, and the primary emphasis was on Western Europe because that is where the most advanced technology resides. The survey includes major contemporary systems on operational aircraft, R&D flight programs, advanced aircraft developments, and major research and technology programs. The information was collected from open literature, personal communications, and a tour of several companies, government organizations, and research laboratories in the United Kingdom, France, and the Federal Republic of Germany. A summary of the survey results to date is presented.

  3. Current Simulator Substitution Practices in Flight Training

    DTIC Science & Technology

    1977-02-01

    environments. The percentage reduction of the original in-flight syllabus (effectiveness) and the ratio of simulator hours required per in-flight...in the report are percent flight TAEG Report No. 43 syllabus reduction and flight substitution ratio. Explanatory information is provided to...formula (Percent Flight Syllabus Reduction) expresses the overall ability of the simulator to reduce the amount of in-flight training in the syllabus

  4. 14 CFR 437.3 - Definitions.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... suborbital rocket to the effects of altitude, velocity, acceleration, or burn duration that exceed a level or... area, that a reusable suborbital rocket's instantaneous impact point may not traverse. Key flight... permitted flights may take place. Permitted vehicle means a reusable suborbital rocket operated by a...

  5. 14 CFR 437.3 - Definitions.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... suborbital rocket to the effects of altitude, velocity, acceleration, or burn duration that exceed a level or... area, that a reusable suborbital rocket's instantaneous impact point may not traverse. Key flight... permitted flights may take place. Permitted vehicle means a reusable suborbital rocket operated by a...

  6. 14 CFR 437.3 - Definitions.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... suborbital rocket to the effects of altitude, velocity, acceleration, or burn duration that exceed a level or... area, that a reusable suborbital rocket's instantaneous impact point may not traverse. Key flight... permitted flights may take place. Permitted vehicle means a reusable suborbital rocket operated by a...

  7. 14 CFR 437.3 - Definitions.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... suborbital rocket to the effects of altitude, velocity, acceleration, or burn duration that exceed a level or... area, that a reusable suborbital rocket's instantaneous impact point may not traverse. Key flight... permitted flights may take place. Permitted vehicle means a reusable suborbital rocket operated by a...

  8. 14 CFR 437.3 - Definitions.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... suborbital rocket to the effects of altitude, velocity, acceleration, or burn duration that exceed a level or... area, that a reusable suborbital rocket's instantaneous impact point may not traverse. Key flight... permitted flights may take place. Permitted vehicle means a reusable suborbital rocket operated by a...

  9. IVGEN Post Flight Analysis

    NASA Technical Reports Server (NTRS)

    Mcquillen, John; Brown, Dan; Hussey, Sam; Zoldak, John

    2014-01-01

    The Intravenous Fluid Generation (IVGEN) Experiment was a technology demonstration experiment that purified ISS potable water, mixed it with salt, and transferred it through a sterilizing filter. On-orbit performance was verified as appropriate and two 1.5 l bags of normal saline solution were returned to earth for post-flight testing by a FDA certified laboratory for compliance with United States Pharmacopiea (USP) standards. Salt concentration deviated from required values and an analysis identified probable causes. Current efforts are focused on Total Organic Content (TOC) testing, and shelf life.The Intravenous Fluid Generation (IVGEN) Experiment demonstrated the purification of ISS potable water, the mixing of the purified water with sodium chloride, and sterilization of the solution via membrane filtration. On-orbit performance was monitored where feasible and two 1.5-liter bags of normal saline solution were returned to earth for post-flight testing by a FDA-registered laboratory for compliance with United States Pharmacopeia (USP)standards [1]. Current efforts have been focused on challenge testing with identified [2] impurities (total organic-carbon), and shelf life testing. The challenge testing flowed known concentrations of contaminants through the IVGEN deionizing cartridge and membrane filters to test their effectiveness. One finding was that the filters and DI-resin themselves contribute to the contaminant load during initial startup, suggesting that the first 100 ml of fluid be discarded. Shelf life testing is ongoing and involves periodic testing of stored DI cartridges and membrane filters that are capped and sealed in hermetic packages. The testing is conducted at six month intervals measuring conductivity and endotoxins in the effluent. Currently, the packaging technique has been successfully demonstrated for one year of storage testing. The USP standards specifies that the TOC be conducted at point of generation as opposed to point of

  10. Flight Tests Validate Collision-Avoidance System

    NASA Video Gallery

    Flights tests of a smartphone-assisted automatic ground collision avoidance system at NASA's Dryden Flight Research Center consistently commanded evasive maneuvers when it sensed that the unmanned ...

  11. Uncertainty of in-flight thrust determination

    NASA Technical Reports Server (NTRS)

    Abernethy, Robert B.; Adams, Gary R.; Steurer, John W.; Ascough, John C.; Baer-Riedhart, Jennifer L.; Balkcom, George H.; Biesiadny, Thomas

    1986-01-01

    Methods for estimating the measurement error or uncertainty of in-flight thrust determination in aircraft employing conventional turbofan/turbojet engines are reviewed. While the term 'in-flight thrust determination' is used synonymously with 'in-flight thrust measurement', in-flight thrust is not directly measured but is determined or calculated using mathematical modeling relationships between in-flight thrust and various direct measurements of physical quantities. The in-flight thrust determination process incorporates both ground testing and flight testing. The present text is divided into the following categories: measurement uncertainty methodoogy and in-flight thrust measurent processes.

  12. Nutritional Biochemistry of Space Flight

    NASA Technical Reports Server (NTRS)

    Smith, Scott M.

    2000-01-01

    Adequate nutrition is critical for maintenance of crew health during and after extended-duration space flight. The impact of weightlessness on human physiology is profound, with effects on many systems related to nutrition, including bone, muscle, hematology, fluid and electrolyte regulation. Additionally, we have much to learn regarding the impact of weightlessness on absorption, mtabolism , and excretion of nutrients, and this will ultimately determine the nutrient requirements for extended-duration space flight. Existing nutritional requirements for extended-duration space flight have been formulated based on limited flight research, and extrapolation from ground-based research. NASA's Nutritional Biochemistry Laboratory is charged with defining the nutritional requirements for space flight. This is accomplished through both operational and research projects. A nutritional status assessment program is included operationally for all International Space Station astronauts. This medical requirement includes biochemical and dietary assessments, and is completed before, during, and after the missions. This program will provide information about crew health and nutritional status, and will also provide assessments of countermeasure efficacy. Ongoing research projects include studies of calcium and bone metabolism, and iron absorption and metabolism. The calcium studies include measurements of endocrine regulation of calcium homeostasis, biochemical marker of bone metabolism, and tracer kinetic studies of calcium movement in the body. These calcium kinetic studies allow for estimation of intestinal absorption, urinary excretion, and perhaps most importantly - deposition and resorption of calcium from bone. The Calcium Kinetics experiment is currently being prepared for flight on the Space Shuttle in 2001, and potentially for subsequent Shuttle and International Space Station missions. The iron study is intended to assess whether iron absorption is down-regulated dUl1ng

  13. Space Flight Immunodeficiency

    NASA Technical Reports Server (NTRS)

    Shearer, William T.

    1999-01-01

    The National Aeronautics and Space Administration (NASA) has had sufficient concern for the well-being of astronauts traveling in space to create the National Space Biomedical Research Institute (NSBRI), which is investigating several areas of biomedical research including those of immunology. As part of the Immunology, Infection, and Hematology Team, the co-investigators of the Space Flight Immunodeficiency Project began their research projects on April 1, 1998 and are now just into the second year of work. Two areas of research have been targeted: 1) specific immune (especially antibody) responses and 2) non-specific inflammation and adhesion. More precise knowledge of these two areas of research will help elucidate the potential harmful effects of space travel on the immune system, possibly sufficient to create a secondary state of immunodeficiency in astronauts. The results of these experiments are likely to lead to the delineation of functional alterations in antigen presentation, specific immune memory, cytokine regulation of immune responses, cell to cell interactions, and cell to endothelium interactions.

  14. SR-71 flight

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The movie clip shown here runs about 13 seconds and shows an air-to-air shot of the front of the SR-71 aircraft and a head-on view of it coming in for a landing. Two SR-71A aircraft on loan from the U.S. Air Force have been used for high-speed, high-altitude research at the NASA Dryden Flight Research Center, Edwards, California, since 1991. One of them was later returned to the Air Force. A third SR-71 on loan from the Air Force is an SR-71B used for training but not for flight research. Developed for the U.S. Air Force as reconnaissance aircraft more than 30 years ago, SR-71 aircraft are still the world's fastest and highest-flying production aircraft. These aircraft can fly more than 2200 miles per hour (Mach 3+ or more than three times the speed of sound) and at altitudes of over 85,000 feet. This operating environment makes the aircraft excellent platforms to carry out research and experiments in a variety of areas--aerodynamics, propulsion, structures, thermal protection materials, high-speed and high-temperature instrumentation, atmospheric studies, and sonic-boom characterization. Data from the SR-71 high-speed research program may be used to aid designers of future supersonic or hypersonic aircraft and propulsion systems, including a possible high-speed civil transport. The SR-71 program at Dryden has been part of the NASA overall high-speed aeronautical research program, and projects have involved other NASA research centers, other government agencies, universities, and commercial firms. One of the first major experiments to be flown in the NASA SR-71 program was a laser air-data collection system. This system used laser light instead of air pressure to produce airspeed and attitude reference data such as angle of attack and angle of sideslip. These data are normally obtained with small tubes and vanes extending into the air stream, or from tubes with flush openings on the aircraft outer skin. The flights provided information on the presence of

  15. NASA Sounding Rockets and Hi-C

    NASA Video Gallery

    The Sounding Rockets Program Office (SRPO), located at NASA Goddard Space Flight Center's Wallops Flight Facility, provides suborbital launch vehicles, payload development, and field operations sup...

  16. Dynamic Flight Envelope Assessment with Flight Safety Applications

    NASA Astrophysics Data System (ADS)

    Pandita, Rohit

    Aircraft have a manufacturer prescribed operating flight envelope for safe operation, exceeding these limits can result in unrecoverable departures or even structural failure. Numerous commercial aircraft accidents in the past have been attributed to loss-of-control (LOC) resulting from exceeding the safe operating flight envelope. Hence, real-time knowledge of the safe operating flight envelope is essential for safe flight operation, a problem known as dynamic flight envelope assessment. This dissertation explores dynamic flight envelope assessment from a control theoretic perspective. Two notions of the flight envelope, namely, the reachable sets and the region-of-attraction analysis are investigated. The NASA generic transport model (GTM) aircraft dynamics is used as an application problem. Linear and nonlinear techniques for flight envelope assessment are formulated in the linear matrix inequality (LMI) and sum-of-squares (SOS) framework, respectively. LMI and SOS problems are computationally tractable convex optimization problems for which many semi-definite programming solvers are available. This thesis also investigated fault detection and isolation strategies. Commercial jet transport aircrafts make extensive use of active controls. Faults or failures in the flight control system (FCS) elements like sensors or control effectors can lead to catastrophic failure. Model-based fault detection and isolation (FDI) filters can provide analytical redundancy by reliably detecting such faults in the system. Practical application of model-based FDI filters is limited so far due to poor performance, false alarms and missed detection arising out of uncertain dynamics of the aircraft, effect of nonlinearities in the system and the influence of closed-loop controllers. An application of closed-loop metrics to assess worst case FDI filter performance in the presence of a controller and uncertain dynamics is presented. Longitudinal GTM dynamics are considered. An Hinfinity

  17. Bumblebee Flight in Heavy Turbulence

    NASA Astrophysics Data System (ADS)

    Engels, T.; Kolomenskiy, D.; Schneider, K.; Lehmann, F.-O.; Sesterhenn, J.

    2016-01-01

    High-resolution numerical simulations of a tethered model bumblebee in forward flight are performed superimposing homogeneous isotropic turbulent fluctuations to the uniform inflow. Despite tremendous variation in turbulence intensity, between 17% and 99% with respect to the mean flow, we do not find significant changes in cycle-averaged aerodynamic forces, moments, or flight power when averaged over realizations, compared to laminar inflow conditions. The variance of aerodynamic measures, however, significantly increases with increasing turbulence intensity, which may explain flight instabilities observed in freely flying bees.

  18. SPIRIT 1 Final Flight Report

    DTIC Science & Technology

    1991-05-15

    If _ PL-TR-91-2226 Environmental Research Papers, No.1094 AD-A257 088" S PI R IT I llll l ii l li l IilI FINAL FLIGHT REPORT Donald R. Smith Michael...24213• :_• ./1111111111 II/ ll/ I111ll /i l ! 1111 I~lll’ "This technical report has been reviewed and is approved for publication" ,’TP" D. PRICE...the 500- to 2000-cm-1 (5- to 20-jim) region. This report provides a detailed overview of the SPIRIT 1 flight and mission and the analysis of the flight

  19. Calcium Kinetics During Space Flight

    NASA Technical Reports Server (NTRS)

    Smith, Scott M.; OBrien, K. O.; Abrams, S. A.; Wastney, M. E.

    2005-01-01

    Bone loss during space flight is one of the most critical challenges to astronaut health on space exploration missions. Defining the time course and mechanism of these changes will aid in developing means to counteract bone loss during space flight, and will have relevance for other clinical situations that impair weight-bearing activity. Bone health is a product of the balance between bone formation and bone resorption. Early space research could not clearly identify which of these was the main process altered in bone loss, but identification of the collagen crosslinks in the 1990s made possible a clear understanding that the impact of space flight was greater on bone resorption, with bone formation being unchanged or only slightly decreased. Calcium kinetics data showed that bone resorption was greater during flight than before flight (668 plus or minus 130 vs. 427 plus or minus 153 mg/d, p less than 0.001), and clearly documented that true intestinal calcium absorption was lower during flight than before flight (233 plus or minus 87 vs. 460 plus or minus 47 mg/d, p less than 0.01). Weightlessness had a detrimental effect on the balance in bone turnover: the difference between daily calcium balance during flight (-234 plus or minus 102 mg/d) and calcium balance before flight (63 plus or minus 75 mg/d) approached 300 mg/d (p less than 0.01). These data demonstrate that the bone loss that occurs during space flight is a consequence of increased bone resorption and decreased intestinal calcium absorption. Examining the changes in bone and calcium homeostasis in the initial days and weeks of space flight, as well as at later times on missions longer than 6 months, is critical to understanding the nature of bone adaptation to weightlessness. To increase knowledge of these changes, we studied bone adaptation to space flight on the 16-day Space Shuttle Columbia (STS-107) mission. When the brave and talented crew of Columbia were lost during reentry on the tragic morning

  20. Flight Rules Critical Readiness Review

    NASA Technical Reports Server (NTRS)

    Kim, E.; Knudsen, F.; Rice, S.

    2010-01-01

    The increment 23/24 Critical Readiness Review (CRR) flight rules are presented. The topics include: 1) B13-152 Acoustic Constraints; 2) B13-113 IFM/Corrective Action Prioritization Due to Loss of Exercise Capability; 3) B13-116 Constraints on Treadmill VIS Failure; 4) B13-201 Medical Management of ISS Fire/Smoke Response; 5) ARED and T2 Exercise constraints Flight rules (flight and stage specific); 6) FYI: B14 FR to be updated with requirement to sample crew sleep locations prior to receiving a "recommendation" from SRAG on where to sleep.

  1. Vapor Compression Distillation Flight Experiment

    NASA Technical Reports Server (NTRS)

    Hutchens, Cindy F.

    2002-01-01

    One of the major requirements associated with operating the International Space Station is the transportation -- space shuttle and Russian Progress spacecraft launches - necessary to re-supply station crews with food and water. The Vapor Compression Distillation (VCD) Flight Experiment, managed by NASA's Marshall Space Flight Center in Huntsville, Ala., is a full-scale demonstration of technology being developed to recycle crewmember urine and wastewater aboard the International Space Station and thereby reduce the amount of water that must be re-supplied. Based on results of the VCD Flight Experiment, an operational urine processor will be installed in Node 3 of the space station in 2005.

  2. Cardiovascular function in space flight

    NASA Technical Reports Server (NTRS)

    Nicogossian, A. E.; Charles, J. B.; Bungo, M. W.; Leach-Huntoon, C. S.

    1990-01-01

    Postflight orthostatic intolerance and cardiac hemodynamics associated with manned space flight have been investigated on seven STS missions. Orthostatic heart rates appear to be influenced by the mission duration. The rates increase during the first 7-10 days of flight and recover partially after that. Fluid loading is used as a countermeasure to the postflight orthostatic intolerance. The carotid baroreceptor function shows only slight responsiveness to orthostatic stimulation. Plots of the baroreceptor function are presented. It is concluded that an early adaptation to the space flight conditions involves a fluid shift and that the subsequent alterations in the neutral controlling mechanisms contribute to the orthoststic intolerance.

  3. Immune responses in space flight

    NASA Technical Reports Server (NTRS)

    Sonnenfeld, G.

    1998-01-01

    Space flight has been shown to have profound effects on immunological parameters of humans, monkeys and rodents. These studies have been carried out by a number of different laboratories. Among the parameters affected are leukocyte blastogenesis, natural killer cell activity, leukocyte subset distribution, cytokine production - including interferons and interleukins, and macrophage maturation and activity. These changes start to occur only after a few days space flight, and some changes continue throughout long-term space flight. Antibody responses have received only very limited study, and total antibody levels have been shown to be increased after long-term space flight. Several factors could be involved in inducing these changes. These factors could include microgravity, lack of load-bearing, stress, acceleration forces, and radiation. The mechanism(s) for space flight-induced changes in immune responses remain(s) to be established. Certainly, there can be direct effects of microgravity, or other factors, on cells that play a fundamental role in immune responses. However, it is now clear that there are interactions between the immune system and other physiological systems that could play a major role. For example, changes occurring in calcium use in the musculoskeletal system induced by microgravity or lack of use could have great impact on the immune system. Most of the changes in immune responses have been observed using samples taken immediately after return from space flight. However, there have been two recent studies that have used in-flight testing. Delayed-type hypersensitivity responses to common recall antigens of astronauts and cosmonauts have been shown to be decreased when tested during space flights. Additionally, natural killer cell and blastogenic activities are inhibited in samples taken from rats during space flight. Therefore, it is now clear that events occurring during space flight itself can affect immune responses. The biological

  4. Iced Aircraft Flight Data for Flight Simulator Validation

    NASA Technical Reports Server (NTRS)

    Ratvasky, Thomas P.; Blankenship, Kurt; Rieke, William; Brinker, David J.

    2003-01-01

    NASA is developing and validating technology to incorporate aircraft icing effects into a flight training device concept demonstrator. Flight simulation models of a DHC-6 Twin Otter were developed from wind tunnel data using a subscale, complete aircraft model with and without simulated ice, and from previously acquired flight data. The validation of the simulation models required additional aircraft response time histories of the airplane configured with simulated ice similar to the subscale model testing. Therefore, a flight test was conducted using the NASA Twin Otter Icing Research Aircraft. Over 500 maneuvers of various types were conducted in this flight test. The validation data consisted of aircraft state parameters, pilot inputs, propulsion, weight, center of gravity, and moments of inertia with the airplane configured with different amounts of simulated ice. Emphasis was made to acquire data at wing stall and tailplane stall since these events are of primary interest to model accurately in the flight training device. Analyses of several datasets are described regarding wing and tailplane stall. Key findings from these analyses are that the simulated wing ice shapes significantly reduced the C , max, while the simulated tail ice caused elevator control force anomalies and tailplane stall when flaps were deflected 30 deg or greater. This effectively reduced the safe operating margins between iced wing and iced tail stall as flap deflection and thrust were increased. This flight test demonstrated that the critical aspects to be modeled in the icing effects flight training device include: iced wing and tail stall speeds, flap and thrust effects, control forces, and control effectiveness.

  5. Flight Testing a Digital Flight Control System. Issues and Results

    DTIC Science & Technology

    1984-07-01

    Program is primarily oriented to the development, integration, and I - evaluation of new flight control technologies . The testbed used in this program is...will be tested for safe operations to give confidence in case of non-rUettable automatic IBU engagement. ISSUE: CONTROL LAW AND REDUNDANCY MAGEMENT CO...were available. Being an advanced development program evaluating new aspects of integrated flight control technology , the latter approach was chosen

  6. Infrared Sensing Aeroheating Flight Experiment: STS-96 Flight Results

    NASA Technical Reports Server (NTRS)

    Blanchard, Robert C.; Wilmoth, Richard G.; Glass, Christopher E.; Merski, N. Ronald, Jr.; Berry, Scott A.; Bozung, Timothy J.; Tietjen, Alan; Wendt, Jodean; Dawson, Don

    2001-01-01

    Major elements of an experiment called the Infrared Sensing Aeroheating Flight Experiment are discussed. The primary experiment goal is to provide reentry global temperature images from infrared measurements to define the characteristics of hypersonic boundary-layer transition during flight. Specifically, the experiment is to identify, monitor, and quantity hypersonic boundary layer windward surface transition of the X-33 vehicle during flight. In addition, the flight data will serve as a calibration and validation of current boundary layer transition prediction techniques, provide benchmark laminar, transitional, and fully turbulent global aeroheating data in order to validate existing wind tunnel and computational results, and to advance aeroheating technology. Shuttle Orbiter data from STS-96 used to validate the data acquisition and data reduction to global temperatures, in order to mitigate the experiment risks prior to the maiden flight of the X-33, is discussed. STS-96 reentry midwave (3-5 micron) infrared data were collected at the Ballistic Missile Defense Organization/Innovative Sciences and Technology Experimentation Facility site at NASA-Kennedy Space Center and subsequently mapped into global temperature contours using ground calibrations only. A series of image mapping techniques have been developed in order to compare each frame of infrared data with thermocouple data collected during the flight. Comparisons of the ground calibrated global temperature images with the corresponding thermocouple data are discussed. The differences are shown to be generally less than about 5%, which is comparable to the expected accuracy of both types of aeroheating measurements.

  7. Ares I-X Launch Abort System, Crew Module, and Upper Stage Simulator Vibroacoustic Flight Data Evaluation, Comparison to Predictions, and Recommendations for Adjustments to Prediction Methodology and Assumptions

    NASA Technical Reports Server (NTRS)

    Smith, Andrew; Harrison, Phil

    2010-01-01

    The National Aeronautics and Space Administration (NASA) Constellation Program (CxP) has identified a series of tests to provide insight into the design and development of the Crew Launch Vehicle (CLV) and Crew Exploration Vehicle (CEV). Ares I-X was selected as the first suborbital development flight test to help meet CxP objectives. The Ares I-X flight test vehicle (FTV) is an early operational model of CLV, with specific emphasis on CLV and ground operation characteristics necessary to meet Ares I-X flight test objectives. The in-flight part of the test includes a trajectory to simulate maximum dynamic pressure during flight and perform a stage separation of the Upper Stage Simulator (USS) from the First Stage (FS). The in-flight test also includes recovery of the FS. The random vibration response from the ARES 1-X flight will be reconstructed for a few specific locations that were instrumented with accelerometers. This recorded data will be helpful in validating and refining vibration prediction tools and methodology. Measured vibroacoustic environments associated with lift off and ascent phases of the Ares I-X mission will be compared with pre-flight vibration predictions. The measured flight data was given as time histories which will be converted into power spectral density plots for comparison with the maximum predicted environments. The maximum predicted environments are documented in the Vibroacoustics and Shock Environment Data Book, AI1-SYS-ACOv4.10 Vibration predictions made using statistical energy analysis (SEA) VAOne computer program will also be incorporated in the comparisons. Ascent and lift off measured acoustics will also be compared to predictions to assess whether any discrepancies between the predicted vibration levels and measured vibration levels are attributable to inaccurate acoustic predictions. These comparisons will also be helpful in assessing whether adjustments to prediction methodologies are needed to improve agreement between the

  8. Identification of a typical flight patterns

    NASA Technical Reports Server (NTRS)

    Statler, Irving C. (Inventor); Ferryman, Thomas A (Inventor); Amidan, Brett G. (Inventor); Whitney, Paul D. (Inventor); White, M. (Inventor); Willse, Alan R. (Inventor); Cooley, Scott K. (Inventor); Jay, Joseph Griffith (Inventor); Lawrence, Robert E. (Inventor); Mosbrucker, Chris (Inventor)

    2005-01-01

    Method and system for analyzing aircraft data, including multiple selected flight parameters for a selected phase of a selected flight, and for determining when the selected phase of the selected flight is atypical, when compared with corresponding data for the same phase for other similar flights. A flight signature is computed using continuous- valued and discrete-valued flight parameters for the selected flight parameters and is optionally compared with a statistical distribution of other observed flight signatures, yielding a typicality scores for the same phase for other similar flights. A cluster analysis is optionally applied to the flight signatures to define an optimal collection of clusters. A level of atypicality for a selected flight is estimated, based upon an index associated with the cluster analysis.

  9. The Simple Science of Flight

    NASA Astrophysics Data System (ADS)

    Tennekes, Henk

    1997-05-01

    From the smallest gnat to the largest aircraft, all things that fly obey the same aerodynamic principles. The Simple Science of Flight offers a leisurely introduction to the mechanics of flight and, beyond that, to the scientific attitude that finds wonder in simple calculations, forging connections between, say, the energy efficiency of a peanut butter sandwich and that of the kerosene that fuels a jumbo jet. It is the product of a lifetime of watching and investigating the way flight happens. The hero of the book is the Boeing 747, which Tennekes sees as the current pinnacle of human ingenuity in mastering the science of flight. Also covered are paper airplanes, kites, gliders, and human-powered flying machines as well as birds and insects. Tennekes explains concepts like lift, drag, wing loading, and cruising speed through many fascinating comparisons, anecdotes, and examples.

  10. "Space flight is utter bilge"

    NASA Astrophysics Data System (ADS)

    Yeomans, Donald

    2004-01-01

    Despite skepticism and ridicule from scientists and the public alike, a small handful of dreamers kept faith in their vision of space flight and planned for the day when humanity would break loose from Earth.

  11. Counterconditioning for a Flight Phobia

    ERIC Educational Resources Information Center

    Sank, Lawrence I.

    1976-01-01

    This article describes a concentrated program of desensitization used to treat flight phobia. A case history illustrates the use of expanded emotive imagery, stimulus breakdown and techniques of covert positive reinforcement. (SJL)

  12. Flight selection at United Airlines

    NASA Technical Reports Server (NTRS)

    Traub, W.

    1980-01-01

    Airline pilot selection proceedures are discussed including psychogical and personality tests, psychomotor performance requirements, and flight skills evaluation. Necessary attitude and personality traits are described and an outline of computer selection, testing, and training techniques is given.

  13. Analytic Verification of Flight Software

    NASA Technical Reports Server (NTRS)

    Dvorak, D.

    1998-01-01

    In the realm of space exploration, the biggest obstacle to widespread application of autonomy in flight software is not technical feasibility; it is doubt about its trustworthiness as a replacement for human-in-the-loop decision-making.

  14. Flight Analogs (Bed Rest Research)

    NASA Video Gallery

    Flight Analogs / Bed Rest Research Projects provide NASA with a ground based research platform to complement space research. By mimicking the conditions of weightlessness in the human body here on ...

  15. Reduced Gravity Education Flight Program

    NASA Video Gallery

    NASA'€™s Reduced Gravity Education Flight Program gives students and educators the opportunity to design, build and fly an experiment in microgravity and get a look at what it takes to be a NASA en...

  16. NASA's Robotic Lander Takes Flight

    NASA Video Gallery

    On Wednesday, June 8, the lander prototype managed by the Robotic Lunar Lander Development Project at NASA's Marshall Space Flight Center in Huntsville, Ala., hovered autonomously for 15 seconds at...

  17. Metabolic energy required for flight

    NASA Astrophysics Data System (ADS)

    Lane, H. W.; Gretebeck, R. J.

    1994-11-01

    This paper reviews data available from U.S. and U.S.S.R. studies on energy metabolism in the microgravity of space flight. Energy utilization and energy availability in space seem to be similar to those on Earth. However, negative nitrogen balances in space in the presence of adequate energy and protein intakes and in-flight exercise, suggest that lean body mass decreases in space. Metabolic studies during simulated (bed rest) and actual microgravity have shown changes in blood glucose, fatty acids, and insulin levels, suggesting that energy metabolism may be altered during flight. Future research should focus on the interactions of lean body mass, diet, and exercise in space and their roles in energy metabolism during space flight.

  18. Metabolic energy required for flight

    NASA Technical Reports Server (NTRS)

    Lane, H. W.; Gretebeck, R. J.

    1994-01-01

    This paper reviews data available from U.S. and U.S.S.R. studies on energy metabolism in the microgravity of space flight. Energy utilization and energy availability in space seem to be similar to those on Earth. However, negative nitrogen balances in space in the presence of adequate energy and protein intakes and in-flight exercise, suggest that lean body mass decreases in space. Metabolic studies during simulated (bed rest) and actual microgravity have shown changes in blood glucose, fatty acids, and insulin levels, suggesting that energy metabolism may be altered during flight. Future research should focus on the interactions of lean body mass, diet, and exercise in spaced and their roles in energy metabolism during space flight.

  19. Technical Seminar: "Flight Deck Technologies"""

    NASA Video Gallery

    Reduced visibility affects the safety and efficiency of nearly all flight operations. As a result, researchers are improving ways to give pilots a vision capability that is independent of actual vi...

  20. Bird flight and airplane flight. [instruments to measure air currents and flight characteristics

    NASA Technical Reports Server (NTRS)

    Magnan, A.

    1980-01-01

    Research was based on a series of mechanical, electrical, and cinematographic instruments developed to measure various features of air current behavior as well as bird and airplane flight. Investigation of rising obstruction and thermal currents led to a theory of bird flight, especially of the gliding and soaring types. It was shown how a knowledge of bird flight can be applied to glider and ultimately motorized aircraft construction. The instruments and methods used in studying stress in airplanes and in comparing the lift to drag ratios of airplanes and birds are described.

  1. Engineering Applications of Bird Flight

    DTIC Science & Technology

    2009-04-27

    are available in the Zoology Department and Southwell Laboratories of Oxford University. These will be used to test models of the automatic flow...Fellow in the Department of Zoology , Oxford University, with expertise in animal flight dynamics and control. Dr Adrian Thomas (MA, PhD) is a University...Lecturer in the Department of Zoology , Oxford University, with expertise in the aerodynamics of animal flight. Dr Marko Bacic (MEng, D.Phil.) is a

  2. Space Flight Safety - Discussing perspectives

    NASA Astrophysics Data System (ADS)

    Smirnov, N. N.

    2016-09-01

    The present section accumulates selected papers from the Second IAA Space Flight Safety Symposium - the international action consolidating the international efforts on safety of space flights at new scientific and technological level. It was held in St. Petersburg in the period since June 29 till July 3, 2015. Venue - the congress-hall and Proving ground of «Special Materials Corp»- Scientific and production association of special materials (St. Petersburg, Sampsonievsky pr. 28a) (Figs. 1 and 2).

  3. Sensory Coordination of Insect Flight

    DTIC Science & Technology

    2009-12-29

    flies ( Hermetia Illucens ) to elicit controlled take-off and landing in free flight (Pilot experiments completed. Follow- up experiments in progress...neerii. 2) Location of odor sources in the fruit fly, Drosophila melanogaster. 3) Wing-haltere coordination in the soldier fly, Hermetia illucens ...coordination in the soldier fly, Hermetia illucens (Tanvi Deora): One of the key sensory inputs for flight stability in Diptera comes from the haltere

  4. Aircraft flight test trajectory control

    NASA Technical Reports Server (NTRS)

    Menon, P. K. A.; Walker, R. A.

    1988-01-01

    Two control law design techniques are compared and the performance of the resulting controllers evaluated. The design requirement is for a flight test trajectory controller (FTTC) capable of closed-loop, outer-loop control of an F-15 aircraft performing high-quality research flight test maneuvers. The maneuver modeling, linearization, and design methodologies utilized in this research, are detailed. The results of applying these FTTCs to a nonlinear F-15 simulation are presented.

  5. In-flight thrust determination

    NASA Technical Reports Server (NTRS)

    Abernethy, Robert B.; Adams, Gary R.; Ascough, John C.; Baer-Riedhart, Jennifer L.; Balkcom, George H.; Biesiadny, Thomas

    1986-01-01

    The major aspects of processes that may be used for the determination of in-flight thrust are reviewed. Basic definitions are presented as well as analytical and ground-test methods for gathering data and calculating the thrust of the propulsion system during the flight development program of the aircraft. Test analysis examples include a single-exhaust turbofan, an intermediate-cowl turbofan, and a mixed-flow afterburning turbofan.

  6. Fuel Subsystems Flight Test Handbook

    DTIC Science & Technology

    1981-12-01

    aircraft fuel subsystems and the requirements to which they are designed . Details are provided of individual testes, test support requirements and eval...Flight Test Engineering, AFFTC. It is designed to introduce a newly assigned flight test engineer to the subject and provide a working reference for...Refueling Subsystem 17 Fuel Dump Subsystem 18 Heat Exchangers 18 REVIEW OF DESIGN AND TEST REQUIREMENTS 19 Classification of Requirements Other Than 20

  7. Long-Duration Space Flight

    NASA Technical Reports Server (NTRS)

    1997-01-01

    Session WA1 includes short reports concerning: (1) Medical and Physiological Studies During 438-Day Space Flights: (2) Human Performance During a 14 Month Space Mission: (3) Homeostasis in Long-Term Microgravity Conditions; (4) Strategy of Preservation of Health of Cosmonauts in Prolonged and Superprolonged Space Flights; (5) Rehabilitation of Cosmonauts Health Following Long-Term Space Missions; and (6) Perfect Cosmonauts: Some Features of Bio-Portrait.

  8. Solar array flight dynamic experiment

    NASA Technical Reports Server (NTRS)

    Schock, R. W.

    1986-01-01

    The purpose of the Solar Array Flight Dynamic Experiment (SAFDE) is to demonstrate the feasibility of on-orbit measurement and ground processing of large space structures dynamic characteristics. Test definition or verification provides the dynamic characteristic accuracy required for control systems use. An illumination/measurement system was developed to fly on space shuttle flight STS-31D. The system was designed to dynamically evaluate a large solar array called the Solar Array Flight Experiment (SAFE) that had been scheduled for this flight. The SAFDE system consisted of a set of laser diode illuminators, retroreflective targets, an intelligent star tracker receiver and the associated equipment to power, condition, and record the results. In six tests on STS-41D, data was successfully acquired from 18 retroreflector targets and ground processed, post flight, to define the solar array's dynamic characteristic. The flight experiment proved the viability of on-orbit test definition of large space structures dynamic characteristics. Future large space structures controllability should be greatly enhanced by this capability.

  9. Solar array flight dynamic experiment

    NASA Technical Reports Server (NTRS)

    Schock, Richard W.

    1987-01-01

    The purpose of the Solar Array Flight Dynamic Experiment (SAFDE) is to demonstrate the feasibility of on-orbit measurement and ground processing of large space structures' dynamic characteristics. Test definition or verification provides the dynamic characteristic accuracy required for control systems use. An illumination/measurement system was developed to fly on space shuttle flight STS-41D. The system was designed to dynamically evaluate a large solar array called the Solar Array Flight Experiment (SAFE) that had been scheduled for this flight. The SAFDE system consisted of a set of laser diode illuminators, retroreflective targets, an intelligent star tracker receiver and the associated equipment to power, condition, and record the results. In six tests on STS-41D, data was successfully acquired from 18 retroreflector targets and ground processed, post flight, to define the solar array's dynamic characteristic. The flight experiment proved the viability of on-orbit test definition of large space structures dynamic characteristics. Future large space structures controllability should be greatly enhanced by this capability.

  10. Solar array flight dynamic experiment

    NASA Technical Reports Server (NTRS)

    Schock, Richard W.

    1986-01-01

    The purpose of the Solar Array Flight Dynamic Experiment (SAFDE) is to demonstrate the feasibility of on-orbit measurement and ground processing of large space structures dynamic characteristics. Test definition or verification provides the dynamic characteristic accuracy required for control systems use. An illumination/measurement system was developed to fly on Space Shuttle flight STS-31D. The system was designed to dynamically evaluate a large solar array called the Solar Array Flight Experiment (SAFE) that had been scheduled for this flight. The SAFDE system consisted of a set of laser diode illuminators, retroreflective targets, an intelligent star tracker receiver and the associated equipment to power, condition, and record the results. In six tests on STS-41D, data was successfully acquired from 18 retroreflector targets and ground processed, post flight, to define the solar array's dynamic characteristic. The flight experiment proved the viability of on-orbit test definition of large space structures dynamic characteristics. Future large space structures controllability should be greatly enhanced by this capability.

  11. Advanced concepts flight simulation facility.

    PubMed

    Chappell, S L; Sexton, G A

    1986-12-01

    The cockpit environment is changing rapidly. New technology allows airborne computerised information, flight automation and data transfer with the ground. By 1995, not only will the pilot's task have changed, but also the tools for doing that task. To provide knowledge and direction for these changes, the National Aeronautics and Space Administration (NASA) and the Lockheed-Georgia Company have completed three identical Advanced Concepts Flight Simulation Facilities. Many advanced features have been incorporated into the simulators - e g, cathode ray tube (CRT) displays of flight and systems information operated via touch-screen or voice, print-outs of clearances, cockpit traffic displays, current databases containing navigational charts, weather and flight plan information, and fuel-efficient autopilot control from take-off to touchdown. More importantly, this cockpit is a versatile test bed for studying displays, controls, procedures and crew management in a full-mission context. The facility also has an air traffic control simulation, with radio and data communications, and an outside visual scene with variable weather conditions. These provide a veridical flight environment to evaluate accurately advanced concepts in flight stations.

  12. 14 CFR 27.151 - Flight controls.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Flight controls. 27.151 Section 27.151... STANDARDS: NORMAL CATEGORY ROTORCRAFT Flight Flight Characteristics § 27.151 Flight controls. (a... response to control system input....

  13. 14 CFR 29.151 - Flight controls.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Flight controls. 29.151 Section 29.151... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Flight Flight Characteristics § 29.151 Flight controls. (a... response to control system input....

  14. 14 CFR 29.151 - Flight controls.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Flight controls. 29.151 Section 29.151... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Flight Flight Characteristics § 29.151 Flight controls. (a... response to control system input....

  15. 14 CFR 29.151 - Flight controls.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Flight controls. 29.151 Section 29.151... STANDARDS: TRANSPORT CATEGORY ROTORCRAFT Flight Flight Characteristics § 29.151 Flight controls. (a) Longitudinal, lateral, directional, and collective controls may not exhibit excessive breakout force,...

  16. 14 CFR 27.151 - Flight controls.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Flight controls. 27.151 Section 27.151... STANDARDS: NORMAL CATEGORY ROTORCRAFT Flight Flight Characteristics § 27.151 Flight controls. (a) Longitudinal, lateral, directional, and collective controls may not exhibit excessive breakout force,...

  17. 14 CFR 27.151 - Flight controls.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Flight controls. 27.151 Section 27.151... STANDARDS: NORMAL CATEGORY ROTORCRAFT Flight Flight Characteristics § 27.151 Flight controls. (a) Longitudinal, lateral, directional, and collective controls may not exhibit excessive breakout force,...

  18. Kinetographic determination of airplane flight characteristics

    NASA Technical Reports Server (NTRS)

    Raethjen, P; Knott, H

    1927-01-01

    The author's first experiments with a glider on flight characteristics demonstrated that an accurate flight-path measurement would enable determination of the polar diagram from a gliding flight. Since then he has endeavored to obtain accurate flight measurements by means of kinetograph (motion-picture camera). Different methods of accomplishing this are presented.

  19. 14 CFR 93.323 - Flight plans.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight plans. 93.323 Section 93.323... Canyon National Park, AZ § 93.323 Flight plans. Each certificate holder conducting a commercial SFRA operation must file a visual flight rules (VFR) flight plan in accordance with § 91.153. This section...

  20. 14 CFR 93.323 - Flight plans.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight plans. 93.323 Section 93.323... Canyon National Park, AZ § 93.323 Flight plans. Each certificate holder conducting a commercial SFRA operation must file a visual flight rules (VFR) flight plan in accordance with § 91.153. This section...

  1. 14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... certain flight tests. (a) No person may operate a civil aircraft (except a manned free balloon) that is... transport pilot certificate or a class or type rating on that certificate, or for a part 121...

  2. 14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... certain flight tests. (a) No person may operate a civil aircraft (except a manned free balloon) that is... transport pilot certificate or a class or type rating on that certificate, or for a part 121...

  3. 14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... certain flight tests. (a) No person may operate a civil aircraft (except a manned free balloon) that is... transport pilot certificate or a class or type rating on that certificate, or for a part 121...

  4. Propulsion Flight-Test Fixture

    NASA Technical Reports Server (NTRS)

    Palumbo, Nate; Vachon, M. Jake; Richwine, Dave; Moes, Tim; Creech, Gray

    2003-01-01

    NASA Dryden Flight Research Center s new Propulsion Flight Test Fixture (PFTF), designed in house, is an airborne engine-testing facility that enables engineers to gather flight data on small experimental engines. Without the PFTF, it would be necessary to obtain such data from traditional wind tunnels, ground test stands, or laboratory test rigs. Traditionally, flight testing is reserved for the last phase of engine development. Generally, engines that embody new propulsion concepts are not put into flight environments until their designs are mature: in such cases, either vehicles are designed around the engines or else the engines are mounted in or on missiles. However, a captive carry capability of the PFTF makes it possible to test engines that feature air-breathing designs (for example, designs based on the rocket-based combined cycle) economically in subscale experiments. The discovery of unknowns made evident through flight tests provides valuable information to engine designers early in development, before key design decisions are made, thereby potentially affording large benefits in the long term. This is especially true in the transonic region of flight (from mach 0.9 to around 1.2), where it can be difficult to obtain data from wind tunnels and computational fluid dynamics. In January 2002, flight-envelope expansion to verify the design and capabilities of the PFTF was completed. The PFTF was flown on a specially equipped supersonic F-15B research testbed airplane, mounted on the airplane at a center-line attachment fixture, as shown in Figure 1. NASA s F-15B testbed has been used for several years as a flight-research platform. Equipped with extensive research air-data, video, and other instrumentation systems, the airplane carries externally mounted test articles. Traditionally, the majority of test articles flown have been mounted at the centerline tank-attachment fixture, which is a hard-point (essentially, a standardized weapon-mounting fixture

  5. Aircraft flight path angle display system

    NASA Technical Reports Server (NTRS)

    Lambregts, Antonius A. (Inventor)

    1991-01-01

    A display system for use in an aircraft control wheel steering system provides the pilot with a single, quickened flight path angle display to overcome poor handling qualities due to intrinsic flight path angle response lags, while avoiding multiple information display symbology. The control law for the flight path angle control system is designed such that the aircraft's actual flight path angle response lags the pilot's commanded flight path angle by a constant time lag .tau., independent of flight conditions. The synthesized display signal is produced as a predetermined function of the aircraft's actual flight path angle, the time lag .tau. and command inputs from the pilot's column.

  6. Extending a Flight Management Computer for Simulation and Flight Experiments

    NASA Technical Reports Server (NTRS)

    Madden, Michael M.; Sugden, Paul C.

    2005-01-01

    In modern transport aircraft, the flight management computer (FMC) has evolved from a flight planning aid to an important hub for pilot information and origin-to-destination optimization of flight performance. Current trends indicate increasing roles of the FMC in aviation safety, aviation security, increasing airport capacity, and improving environmental impact from aircraft. Related research conducted at the Langley Research Center (LaRC) often requires functional extension of a modern, full-featured FMC. Ideally, transport simulations would include an FMC simulation that could be tailored and extended for experiments. However, due to the complexity of a modern FMC, a large investment (millions of dollars over several years) and scarce domain knowledge are needed to create such a simulation for transport aircraft. As an intermediate alternative, the Flight Research Services Directorate (FRSD) at LaRC created a set of reusable software products to extend flight management functionality upstream of a Boeing-757 FMC, transparently simulating or sharing its operator interfaces. The paper details the design of these products and highlights their use on NASA projects.

  7. Laser Powered Aircraft Takes Flight

    NASA Technical Reports Server (NTRS)

    2003-01-01

    A team of NASA researchers from Marshall Space Flight Center (MSFC) and Dryden Flight Research center have proven that beamed light can be used to power an aircraft, a first-in-the-world accomplishment to the best of their knowledge. Using an experimental custom built radio-controlled model aircraft, the team has demonstrated a system that beams enough light energy from the ground to power the propeller of an aircraft and sustain it in flight. Special photovoltaic arrays on the plane, similar to solar cells, receive the light energy and convert it to electric current to drive the propeller motor. In a series of indoor flights this week at MSFC, a lightweight custom built laser beam was aimed at the airplane `s solar panels. The laser tracks the plane, maintaining power on its cells until the end of the flight when the laser is turned off and the airplane glides to a landing. The laser source demonstration represents the capability to beam more power to a plane so that it can reach higher altitudes and have a greater flight range without having to carry fuel or batteries, enabling an indefinite flight time. The demonstration was a collaborative effort between the Dryden Center at Edward's, California, where the aircraft was designed and built, and MSFC, where integration and testing of the laser and photovoltaic cells was done. Laser power beaming is a promising technology for consideration in new aircraft design and operation, and supports NASA's goals in the development of revolutionary aerospace technologies. Photographed with their invention are (from left to right): David Bushman and Tony Frackowiak, both of Dryden; and MSFC's Robert Burdine.

  8. Mars Balloon Flight Test Results

    NASA Technical Reports Server (NTRS)

    Hall, Jeffery L.; Pauken, Michael T.; Kerzhanovich, Viktor V.; Walsh, Gerald J.; Kulczycki, Eric A.; Fairbrother, Debora; Shreves, Chris; Lachenmeier, Tim

    2009-01-01

    This paper describes a set of four Earth atmosphere flight test experiments on prototype helium superpressure balloons designed for Mars. Three of the experiments explored the problem of aerial deployment and inflation, using the cold, low density environment of the Earth's stratosphere at an altitude of 30-32 km as a proxy for the Martian atmosphere. Auxiliary carrier balloons were used in three of these test flights to lift the Mars balloon prototype and its supporting system from the ground to the stratosphere where the experiment was conducted. In each case, deployment and helium inflation was initiated after starting a parachute descent of the payload at 5 Pa dynamic pressure, thereby mimicking the conditions expected at Mars after atmospheric entry and high speed parachute deceleration. Upward and downward looking video cameras provided real time images from the flights, with additional data provided by onboard temperature, pressure and GPS sensors. One test of a 660 cc pumpkin balloon was highly successful, achieving deployment, inflation and separation of the balloon from the flight train at the end of inflation; however, some damage was incurred on the balloon during this process. Two flight tests of 12 m diameter spherical Mylar balloons were not successful, although some lessons were learned based on the failure analyses. The final flight experiment consisted of a ground-launched 12 m diameter spherical Mylar balloon that ascended to the designed 30.3 km altitude and successfully floated for 9.5 hours through full noontime daylight and into darkness, after which the telemetry system ran out of electrical power and tracking was lost. The altitude excursions for this last flight were +/-75 m peak to peak, indicating that the balloon was essentially leak free and functioning correctly. This provides substantial confidence that this balloon design will fly for days or weeks at Mars if it can be deployed and inflated without damage.

  9. Automated ISS Flight Utilities

    NASA Technical Reports Server (NTRS)

    Offermann, Jan Tuzlic

    2016-01-01

    EVADES output. As mentioned above, GEnEVADOSE makes extensive use of ROOT version 6, the data analysis framework developed at the European Organization for Nuclear Research (CERN), and the code is written to the C++11 standard (as are the other projects). My second project is the Automated Mission Reference Exposure Utility (AMREU).Unlike GEnEVADOSE, AMREU is a combination of three frameworks written in both Python and C++, also making use of ROOT (and PyROOT). Run as a combination of daily and weekly cron jobs, these macros query the SRAG database system to determine the active ISS missions, and query minute-by-minute radiation dose information from ISS-TEPC (Tissue Equivalent Proportional Counter), one of the radiation detectors onboard the ISS. Using this information, AMREU creates a corrected data set of daily radiation doses, addressing situations where TEPC may be offline or locked up by correcting doses for days with less than 95% live time (the total amount time the instrument acquires data) by averaging the past 7 days. As not all errors may be automatically detectable, AMREU also allows for manual corrections, checking an updated plaintext file each time it runs. With the corrected data, AMREU generates cumulative dose plots for each mission, and uses a Python script to generate a flight note file (.docx format) containing these plots, as well as information sections to be filled in and modified by the space weather environment officers with information specific to the week. AMREU is set up to run without requiring any user input, and it automatically archives old flight notes and information files for missions that are no longer active. My other projects involve cleaning up a large data set from the Charged Particle Directional Spectrometer (CPDS), joining together many different data sets in order to clean up information in SRAG SQL databases, and developing other automated utilities for displaying information on active solar regions, that may be used by the

  10. 14 CFR 125.297 - Approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Approval of flight simulators and flight... MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Crewmember Requirements § 125.297 Approval of flight simulators and flight training devices....

  11. 14 CFR 125.297 - Approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Approval of flight simulators and flight... MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Crewmember Requirements § 125.297 Approval of flight simulators and flight training devices....

  12. 14 CFR 125.297 - Approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Approval of flight simulators and flight... MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Crewmember Requirements § 125.297 Approval of flight simulators and flight training devices....

  13. 14 CFR 125.297 - Approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Approval of flight simulators and flight... MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Crewmember Requirements § 125.297 Approval of flight simulators and flight training devices....

  14. 14 CFR 125.297 - Approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Approval of flight simulators and flight... MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Crewmember Requirements § 125.297 Approval of flight simulators and flight training devices....

  15. 14 CFR 91.143 - Flight limitation in the proximity of space flight operations.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight limitation in the proximity of space flight operations. 91.143 Section 91.143 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Flight Rules General § 91.143 Flight limitation in the proximity of space flight operations....

  16. 14 CFR 91.143 - Flight limitation in the proximity of space flight operations.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Flight limitation in the proximity of space flight operations. 91.143 Section 91.143 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Flight Rules General § 91.143 Flight limitation in the proximity of space flight operations....

  17. 14 CFR 91.143 - Flight limitation in the proximity of space flight operations.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight limitation in the proximity of space flight operations. 91.143 Section 91.143 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Flight Rules General § 91.143 Flight limitation in the proximity of space flight operations....

  18. 14 CFR 91.143 - Flight limitation in the proximity of space flight operations.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight limitation in the proximity of space flight operations. 91.143 Section 91.143 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Flight Rules General § 91.143 Flight limitation in the proximity of space flight operations....

  19. 14 CFR 91.143 - Flight limitation in the proximity of space flight operations.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight limitation in the proximity of space flight operations. 91.143 Section 91.143 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Flight Rules General § 91.143 Flight limitation in the proximity of space flight operations....

  20. 14 CFR 93.305 - Flight-free zones and flight corridors.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Flight Rules Area within the following flight-free zones: (a) Desert View Flight-free Zone. That airspace... west between the Desert View and Bright Angel Flight-free Zones, is designated the “Zuni Point Corridor... zone and the Desert View Flight-free Zone, is designated the “Zuni Point Corridor.” The corridor to...

  1. 14 CFR 93.305 - Flight-free zones and flight corridors.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Flight Rules Area within the following flight-free zones: (a) Desert View Flight-free Zone. That airspace... west between the Desert View and Bright Angel Flight-free Zones, is designated the “Zuni Point Corridor... zone and the Desert View Flight-free Zone, is designated the “Zuni Point Corridor.” The corridor to...

  2. 14 CFR 93.305 - Flight-free zones and flight corridors.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... Flight Rules Area within the following flight-free zones: (a) Desert View Flight-free Zone. That airspace... west between the Desert View and Bright Angel Flight-free Zones, is designated the “Zuni Point Corridor... zone and the Desert View Flight-free Zone, is designated the “Zuni Point Corridor.” The corridor to...

  3. 14 CFR 93.305 - Flight-free zones and flight corridors.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Flight Rules Area within the following flight-free zones: (a) Desert View Flight-free Zone. That airspace... west between the Desert View and Bright Angel Flight-free Zones, is designated the “Zuni Point Corridor... zone and the Desert View Flight-free Zone, is designated the “Zuni Point Corridor.” The corridor to...

  4. 14 CFR 93.305 - Flight-free zones and flight corridors.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Flight Rules Area within the following flight-free zones: (a) Desert View Flight-free Zone. That airspace... west between the Desert View and Bright Angel Flight-free Zones, is designated the “Zuni Point Corridor... zone and the Desert View Flight-free Zone, is designated the “Zuni Point Corridor.” The corridor to...

  5. 14 CFR 121.414 - Initial and transition training and checking requirements: flight instructors (airplane), flight...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... checking requirements: flight instructors (airplane), flight instructors (simulator). 121.414 Section 121... training and checking requirements: flight instructors (airplane), flight instructors (simulator). (a) No.... The observation check may be accomplished in part or in full in an airplane, in a flight simulator,...

  6. 14 CFR 135.340 - Initial and transition training and checking: Flight instructors (aircraft), flight instructors...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... checking: Flight instructors (aircraft), flight instructors (simulator). 135.340 Section 135.340... and transition training and checking: Flight instructors (aircraft), flight instructors (simulator... simulator, or in a flight training device. This paragraph applies after March 19, 1997. (b) The...

  7. Aurora Flight Sciences' Perseus B Remotely Piloted Aircraft in Flight

    NASA Technical Reports Server (NTRS)

    1998-01-01

    A long, slender wing and a pusher propeller at the rear characterize the Perseus B remotely piloted research aircraft, seen here during a test flight in June 1998. Perseus B is a remotely piloted aircraft developed as a design-performance testbed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project. Perseus is one of several flight vehicles involved in the ERAST project. A piston engine, propeller-powered aircraft, Perseus was designed and built by Aurora Flight Sciences Corporation, Manassas, Virginia. The objectives of Perseus B's ERAST flight tests have been to reach and maintain horizontal flight above altitudes of 60,000 feet and demonstrate the capability to fly missions lasting from 8 to 24 hours, depending on payload and altitude requirements. The Perseus B aircraft established an unofficial altitude record for a single-engine, propeller-driven, remotely piloted aircraft on June 27, 1998. It reached an altitude of 60,280 feet. In 1999, several modifications were made to the Perseus aircraft including engine, avionics, and flight-control-system improvements. These improvements were evaluated in a series of operational readiness and test missions at the Dryden Flight Research Center, Edwards, California. Perseus is a high-wing monoplane with a conventional tail design. Its narrow, straight, high-aspect-ratio wing is mounted atop the fuselage. The aircraft is pusher-designed with the propeller mounted in the rear. This design allows for interchangeable scientific-instrument payloads to be placed in the forward fuselage. The design also allows for unobstructed airflow to the sensors and other devices mounted in the payload compartment. The Perseus B that underwent test and development in 1999 was the third generation of the Perseus design, which began with the Perseus Proof-Of-Concept aircraft. Perseus was initially developed as part of NASA's Small High-Altitude Science Aircraft (SHASA) program, which later evolved into the ERAST

  8. Supersonic Retropropulsion Flight Test Concepts

    NASA Technical Reports Server (NTRS)

    Post, Ethan A.; Dupzyk, Ian C.; Korzun, Ashley M.; Dyakonov, Artem A.; Tanimoto, Rebekah L.; Edquist, Karl T.

    2011-01-01

    NASA's Exploration Technology Development and Demonstration Program has proposed plans for a series of three sub-scale flight tests at Earth for supersonic retropropulsion, a candidate decelerator technology for future, high-mass Mars missions. The first flight test in this series is intended to be a proof-of-concept test, demonstrating successful initiation and operation of supersonic retropropulsion at conditions that replicate the relevant physics of the aerodynamic-propulsive interactions expected in flight. Five sub-scale flight test article concepts, each designed for launch on sounding rockets, have been developed in consideration of this proof-of-concept flight test. Commercial, off-the-shelf components are utilized as much as possible in each concept. The design merits of the concepts are compared along with their predicted performance for a baseline trajectory. The results of a packaging study and performance-based trade studies indicate that a sounding rocket is a viable launch platform for this proof-of-concept test of supersonic retropropulsion.

  9. Immune function during space flight

    NASA Technical Reports Server (NTRS)

    Sonnenfeld, Gerald; Shearer, William T.

    2002-01-01

    It is very likely that the human immune system will be altered in astronauts exposed to the conditions of long-term space flight: isolation, containment, microgravity, radiation, microbial contamination, sleep disruption, and insufficient nutrition. In human and animal subjects flown in space, there is evidence of immune compromise, reactivation of latent virus infection, and possible development of a premalignant or malignant condition. Moreover, in ground-based space flight model investigations, there is evidence of immune compromise and reactivation of latent virus infection. All of these observations in space flight itself or in ground-based models of space flight have a strong resonance in a wealth of human pathologic conditions involving the immune system where reactivated virus infections and cancer appear as natural consequences. The clinical conditions of Epstein-Barr-driven lymphomas in transplant patients and Kaposi's sarcoma in patients with autoimmune deficiency virus come easily to mind in trying to identify these conditions. With these thoughts in mind, it is highly appropriate, indeed imperative, that careful investigations of human immunity, infection, and cancer be made by space flight researchers.

  10. Flight Crew Health Stabilization Program

    NASA Technical Reports Server (NTRS)

    Johnston, Smith L.

    2010-01-01

    This document establishes the policy and procedures for the HSP and is authorized through the Director, Johnson Space Center (JSC). This document delineates the medical operations requirements for the HSP. The HSP goals are accomplished through an awareness campaign and procedures such as limiting access to flight crewmembers, medical screening, and controlling flight crewmember activities. NASA's Human Space Flight Program uses strategic risk mitigation to achieve mission success while protecting crew health and safety. Infectious diseases can compromise crew health and mission success, especially in the immediate preflight period. The primary purpose of the Flight Crew Health Stabilization Program (HSP) is to mitigate the risk of occurrence of infectious disease among astronaut flight crews in the immediate preflight period. Infectious diseases are contracted through direct person-to-person contact, and through contact with infectious material in the environment. The HSP establishes several controls to minimize crew exposure to infectious agents. The HSP provides a quarantine environment for the crew that minimizes contact with potentially infectious material. The HSP also limits the number of individuals who come in close contact with the crew. The infection-carrying potential of these primary contacts (PCs) is minimized by educating them in ways to avoid infections and avoiding contact with the crew if they are or may be sick. The transmission of some infectious diseases can be greatly curtailed by vaccinations. PCs are strongly encouraged to maintain updated vaccinations.

  11. The 737 graphite composite flight spoiler flight service evaluation

    NASA Technical Reports Server (NTRS)

    Stoecklin, R. L.

    1975-01-01

    The flight service experience of 108 graphite-epoxy spoilers on 737 transport aircraft, and related ground-based environmental exposure of graphite-epoxy material specimens were evaluated. Four spoilers were installed on each of 27 aircraft for a 5-year study. As of February 28, 1975, a total of 294,280 spoiler flight-hours and 460,686 spoiler landings were accumulated. Based on visual, ultrasonic, and destructive testing, no moisture migration into the honeycomb core and no core corrosion has occurred. Tests of removed spoilers and of ground-based exposure specimens after the first year of service indicate no significant changes in composite strength.

  12. JetStar in flight

    NASA Technical Reports Server (NTRS)

    1981-01-01

    This 18-second movie clip shows the NASA Dryden Lockheed C-140 JetStar in flight with its pylon-mounted air-turbine-drive system used to gather information on the acoustic characteristics of subscale advanced design propellers. Data was gathered through 28 flush-mounted microphones on the skin of the aircraft. From 1976 to 1987 the NASA Lewis Research Center, Cleveland, Ohio -- today known as the Glenn Research Center -- engaged in research and development of an advanced turboprop concept in partnership with Hamilton Standard, Windsor Locks, Connecticut, the largest manufacturer of propellers in the United States. The Advanced Turboprop Project took its impetus from the energy crisis of the early 1970's and sought to produce swept propeller blades that would increase efficiency and reduce noise. As the project progressed, Pratt & Whitney, Allison Gas Turbine Division of General Motors, General Electric, Gulfstream, Rohr Industries, Boeing, Lockheed, and McDonnell Douglas, among others, also took part. NASA Lewis did the much of the ground research and marshaled the resources of these and other members of the aeronautical community. The team came to include the NASA Ames Research Center, Langley Research Center, and the Ames-Dryden Flight Research Facility (before and after that time, the Dryden Flight Research Center). Together, they brought the propeller to the flight research stage, and the team that worked on the project won the coveted Collier Trophy for its efforts in 1987. To test the acoustics of the propeller the team developed, it mounted propeller models on a C-140 JetStar aircraft fuselage at NASA Dryden. The JetStar was modified with the installation of an air-turbine-drive system. The drive motor, with a test propeller, was mounted on a pylon atop the JetStar. The JetStar was equipped with an array of 28 microphones flush-mounted in the fuselage of the aircraft beneath the propeller. Microphones mounted on the wings and on an accompanying Learjet chase

  13. F-18 SRA in flight

    NASA Technical Reports Server (NTRS)

    1995-01-01

    NASA's Dryden Flight Research Center, Edwards, California, is using this early-model F-18 Hornet as a flying research platform to evaluate a number of emerging technologies in aircraft control and information systems. The Systems Research Aircraft, a pre-production two-seat version of the twin-engine tactical fighter aircraft, has been extensively modified for its research role. Among projects flown on the plane are experiments to evaluate fiber optics for flight-critical control systems, advanced air data acquisition systems, and electrically-powered flight control actuators which do not require connection to the aircraft central hydraulic system. The new technologies could lead to lighter and more efficient aircraft designs with higher performance and greater safety.

  14. Vision Aspects of Space Flight

    NASA Technical Reports Server (NTRS)

    Manuel, Keith; Billica, Roger (Technical Monitor)

    2000-01-01

    Vision, being one of our most important senses, is critically important in the unique working environment of space flight. Critical evaluation of the astronauts visual system begins with pre-selection examinations resulting in an average of 65% of all medical disqualification's caused by ocular findings. With an average age of 42, approximately 60% of the astronaut corps requires vision correction. Further demands of the unique training and working environment of microgravity, variable lighting from very poor to extreme brightness of sunlight and exposure to extremes of electromagnetic energy results in unique eyewear and contact lens applications. This presentation will describe some of those unique eyewear and contact lens applications used in space flight and training environments. Additionally, ocular findings from 26 shuttle and 5 MIR mission post-flight examinations will be presented.

  15. Readiness for First Crewed Flight

    NASA Technical Reports Server (NTRS)

    Schaible, Dawn M.

    2011-01-01

    The NASA Engineering and Safety Center (NESC) was requested to develop a generic framework for evaluating whether any given program has sufficiently complete and balanced plans in place to allow crewmembers to fly safely on a human spaceflight system for the first time (i.e., first crewed flight). The NESC assembled a small team which included experts with experience developing robotic and human spaceflight and aviation systems through first crewed test flight and into operational capability. The NESC team conducted a historical review of the steps leading up to the first crewed flights of Mercury through the Space Shuttle. Benchmarking was also conducted with the United States (U.S.) Air Force and U.S. Navy. This report contains documentation of that review.

  16. Flight directors for STOl aircraft

    NASA Technical Reports Server (NTRS)

    Rabin, U. H.

    1983-01-01

    Flight director logic for flight path and airspeed control of a powered-lift STOL aircraft in the approach, transition, and landing configurations are developed. The methods for flight director design are investigated. The first method is based on the Optimal Control Model (OCM) of the pilot. The second method, proposed here, uses a fixed dynamic model of the pilot in a state space formulation similar to that of the OCM, and includes a pilot work-load metric. Several design examples are presented with various aircraft, sensor, and control configurations. These examples show the strong impact of throttle effectiveness on the performance and pilot work-load associated with manual control of powered-lift aircraft during approach. Improved performed and reduced pilot work-load can be achieved by using direct-lift-control to increase throttle effectiveness.

  17. Cardiovascular function in space flight

    NASA Technical Reports Server (NTRS)

    Nicogossian, A. E.; Charles, J. B.; Bungo, M. W.; Leach-Huntoon, C. S.; Nicgossian, A. E.

    1991-01-01

    Changes in orthostatic heart rate have been noted universally in Soviet and U.S. crewmembers post space flight. The magnitude of these changes appears to be influenced by mission duration, with increasing orthostatic intolerance for the first 7-10 days of flight and then a partial recovery in the orthostatic heart rate response. Fluid loading has been used as a countermeasure to this postflight orthostatic intolerance. Previous reports have documented the effectiveness of this technique, but it has also been noted that the effectiveness of volume expansion diminishes as flight duration exceeds one week. The response of carotid baroreceptor function was investigated utilizing a commercially available neck collar which could apply positive and negative pressure to effect receptor stimulation. Bedrest studies had validated the usefulness and validity of the device. In these studies it was shown that carotid baroreceptor function curves demonstrated less responsiveness to orthostatic stimulation than control individuals. Twelve Space Shuttle crewmembers were examined pre- and postflight from flights lasting from 4-5 days. Plots of baroreceptor function were constructed and plotted as change in R-R interval vs. carotid distending pressure (an orthostatic stimulus). Typical sigmoidal curves were obtained. Postflight the resting heart rate was higher (smaller R-R interval) and the range of R-R value and the slope of the carotid sigmoidal response were both depressed. These changes were not significant immediately postflight (L + O), but did become significant by the second day postflight (L + 2), and remained suppressed for several days thereafter. It is hypothesized that the early adaptation to space flight involves a central fluid shift during the initial days of flight, but subsequent alterations in neural controlling mechanisms (such as carotid baroreceptor function) contribute to orthostatic intolerance.

  18. Calbindins decreased after space flight

    NASA Technical Reports Server (NTRS)

    Sergeev, I. N.; Rhoten, W. B.; Carney, M. D.

    1996-01-01

    Exposure of the body to microgravity during space flight causes a series of well-documented changes in Ca2+ metabolism, yet the cellular and molecular mechanisms leading to these changes are poorly understood. Calbindins, vitamin D-dependent Ca2+ binding proteins, are believed to have a significant role in maintaining cellular Ca2+ homeostasis. In this study, we used biochemical and immunocytochemical approaches to analyze the expression of calbindin-D28k and calbindin-D9k in kidneys, small intestine, and pancreas of rats flown for 9 d aboard the space shuttle. The effects of microgravity on calbindins in rats from space were compared with synchronous Animal Enclosure Module controls, modeled weightlessness animals (tail suspension), and their controls. Exposure to microgravity resulted in a significant and sustained decrease in calbindin-D28k content in the kidney and calbindin-D9k in the small intestine of flight animals, as measured by enzyme-linked immunosorbent assay (ELISA). Modeled weightlessness animals exhibited a similar decrease in calbindins by ELISA. Immunocytochemistry (ICC) in combination with quantitative computer image analysis was used to measure in situ the expression of calbindins in the kidney and the small intestine, and the expression of insulin in pancreas. There was a large decrease of immunoreactivity in renal distal tubular cell-associated calbindin-D28k and in intestinal absorptive cell-associated calbindin-D9k of space flight and modeled weightlessness animals compared with matched controls. No consistent difference in pancreatic insulin immunoreactivity between space flight, modeled weightlessness, and controls was observed. Regression analysis of results obtained by quantitative ICC and ELISA for space flight, modeled weightlessness animals, and their controls demonstrated a significant correlation. These findings after a short-term exposure to microgravity or modeled weightlessness suggest that a decreased expression of calbindins

  19. The aerodynamics of insect flight.

    PubMed

    Sane, Sanjay P

    2003-12-01

    The flight of insects has fascinated physicists and biologists for more than a century. Yet, until recently, researchers were unable to rigorously quantify the complex wing motions of flapping insects or measure the forces and flows around their wings. However, recent developments in high-speed videography and tools for computational and mechanical modeling have allowed researchers to make rapid progress in advancing our understanding of insect flight. These mechanical and computational fluid dynamic models, combined with modern flow visualization techniques, have revealed that the fluid dynamic phenomena underlying flapping flight are different from those of non-flapping, 2-D wings on which most previous models were based. In particular, even at high angles of attack, a prominent leading edge vortex remains stably attached on the insect wing and does not shed into an unsteady wake, as would be expected from non-flapping 2-D wings. Its presence greatly enhances the forces generated by the wing, thus enabling insects to hover or maneuver. In addition, flight forces are further enhanced by other mechanisms acting during changes in angle of attack, especially at stroke reversal, the mutual interaction of the two wings at dorsal stroke reversal or wing-wake interactions following stroke reversal. This progress has enabled the development of simple analytical and empirical models that allow us to calculate the instantaneous forces on flapping insect wings more accurately than was previously possible. It also promises to foster new and exciting multi-disciplinary collaborations between physicists who seek to explain the phenomenology, biologists who seek to understand its relevance to insect physiology and evolution, and engineers who are inspired to build micro-robotic insects using these principles. This review covers the basic physical principles underlying flapping flight in insects, results of recent experiments concerning the aerodynamics of insect flight, as well

  20. Improved Flight Test Procedures for Flutter Clearance

    NASA Technical Reports Server (NTRS)

    Lind, Rick C.; Brenner, Martin J.; Freudinger, Lawrence C.

    1997-01-01

    Flight flutter testing is an integral part of flight envelope clearance. This paper discusses advancements in several areas that are being investigated to improve efficiency and safety of flight test programs. Results are presented from recent flight testing of the F/A-18 Systems Research Aircraft. A wingtip excitation system was used to generate aeroelastic response data. This system worked well for many flight conditions but still displayed some anomalies. Wavelet processing is used to analyze the flight data. Filtered transfer functions are generated that greatly improve system identification. A flutter margin is formulated that accounts for errors between a model and flight data. Worst-case flutter margins are computed to demonstrate the flutter boundary may lie closer to the flight envelope than previously estimated. This paper concludes with developments for a distributed flight analysis environment and on-line health monitoring.

  1. STS-112 Post Flight Presentation

    NASA Technical Reports Server (NTRS)

    2002-01-01

    The STS-112 post flight presentation begins with a shot of the moonrise over the Earth's Limb. A photograph of the STS-112 crew is shown. The crew consists of Mission Specialists Sandy Magnus, David Wolf, Piers Sellers and Fodor Yurchikhin, Pilot Pam Melroy and Commander Jeff Ashby. The crew departs from the Operations and Control Building to the launch pad at Kennedy Space Center in Florida. Sandy Magnus is shown preparing to board the Space Shuttle Atlantis. The actual STS-112 launch with flight deck activity during rendezvous with the International Space Station is also presented.

  2. Advanced flight computer. Special study

    NASA Technical Reports Server (NTRS)

    Coo, Dennis

    1995-01-01

    This report documents a special study to define a 32-bit radiation hardened, SEU tolerant flight computer architecture, and to investigate current or near-term technologies and development efforts that contribute to the Advanced Flight Computer (AFC) design and development. An AFC processing node architecture is defined. Each node may consist of a multi-chip processor as needed. The modular, building block approach uses VLSI technology and packaging methods that demonstrate a feasible AFC module in 1998 that meets that AFC goals. The defined architecture and approach demonstrate a clear low-risk, low-cost path to the 1998 production goal, with intermediate prototypes in 1996.

  3. Enabling Electric Propulsion for Flight

    NASA Technical Reports Server (NTRS)

    Ginn, Starr Renee

    2015-01-01

    Team Seedling project AFRC and LaRC 31ft distributed electric propulsion wing on truck bed up 75 miles per hour for coefficient of lift validation. Convergent Aeronautic Solutions project, sub-project Convergent Electric Propulsion Technologies AFRC, LaRC and GRC, re-winging a 4 passenger Tecnam aircraft with a 31ft distributed electric propulsion wing. Advanced Air Transport Technologies (Fixed Wing), Hybrid Electric Research Theme, developing a series hybrid ironbird and flight sim to study integration and performance challenges in preparation for a 1-2 MW flight project.

  4. Thermal energy storage flight experiments

    NASA Technical Reports Server (NTRS)

    Namkoong, D.

    1989-01-01

    Consideration is given to the development of an experimental program to study heat transfer, energy storage, fluid movement, and void location under microgravity. Plans for experimental flight packages containing Thermal Energy Storage (TES) material applicable for advanced solar heat receivers are discussed. Candidate materials for TES include fluoride salts, salt eutectics, silicides, and metals. The development of a three-dimensional computer program to describe TES material behavior undergoing melting and freezing under microgravity is also discussed. The TES experiment concept and plans for ground and flight tests are outlined.

  5. The NASA Sharp Flight Experiment

    NASA Technical Reports Server (NTRS)

    Rasky, Daniel J.; Salute, Joan; Kolodziej, Paul; Bull, Jeffrey

    1998-01-01

    The Slender Hypersonic Aerothermodynamic Research Program (SHARP) was initiated by NASA Ames, and executed in partnership with Sandia National Laboratory and the US Air Force, to demonstrate sharp, passive leading edge designs for hypersonic vehicles, incorporating new ultra-high temperature ceramics (UHTC's). These new ceramic composites have been undergoing development, characterization and ground testing at NASA Ames for the last nine years. This paper will describe the background, flight objectives, design and pertinent flight results of SHARP, and some of the potential implications for future hypersonic vehicle designs.

  6. Enabling Electric Propulsion for Flight

    NASA Technical Reports Server (NTRS)

    Ginn, Starr

    2014-01-01

    Description of current ARMD projects; Team Seedling project AFRC and LaRC 31ft distributed electric propulsion wing on truck bed up 75 miles per hour for coefficient of lift validation. Convergent Aeronautic Solutions project (new ARMD reorg), sub-project Convergent Electric Propulsion Technologies AFRC, LaRC and GRC, re-winging a 4 passenger Tecnam aircraft with a 31ft distributed electric propulsion wing. Advanced Air Transport Technologies (Fixed Wing), Hybrid Electric Research Theme, developing a series hybrid ironbird and flight sim to study integration and performance challenges in preparation for a 1-2 MW flight project.

  7. ADEPT SR-1 Flight Experiment

    NASA Technical Reports Server (NTRS)

    Wercinski, Paul F.

    2017-01-01

    The ADEPT architecture represents a completely new approach for entry vehicle design using a high-performance carbon fabric to serve as the primary drag surface of the mechanically deployed decelerator and to protect the payload from hypersonic aerothermal heating during entry. The initial system-level development of the nano-ADEPT architecture will culminate in the launch of a 0.7-m deployed diameter ADEPT sounding rocket flight experiment. The SR-1 sounding rocket flight experiment is a critical milestone in the technology maturation plan for ADEPT and will generate performance data on in-space deployment and aerodynamic stability.

  8. Flight simulator with spaced visuals

    NASA Technical Reports Server (NTRS)

    Gilson, Richard D. (Inventor); Thurston, Marlin O. (Inventor); Olson, Karl W. (Inventor); Ventola, Ronald W. (Inventor)

    1980-01-01

    A flight simulator arrangement wherein a conventional, movable base flight trainer is combined with a visual cue display surface spaced a predetermined distance from an eye position within the trainer. Thus, three degrees of motive freedom (roll, pitch and crab) are provided for a visual proprioceptive, and vestibular cue system by the trainer while the remaining geometric visual cue image alterations are developed by a video system. A geometric approach to computing runway image eliminates a need to electronically compute trigonometric functions, while utilization of a line generator and designated vanishing point at the video system raster permits facile development of the images of the longitudinal edges of the runway.

  9. Flight crew sleep during multiple layover polar flights

    NASA Technical Reports Server (NTRS)

    Sasaki, Mitsuo; Kurosaki, Yuko S.; Spinweber, Cheryl L.; Graeber, R. C.; Takahashi, Toshiharu

    1993-01-01

    This study investigated changes in sleep after multiple transmeridian flights. The subjects were 12 B747 airline pilots operating on the following polar flight: Tokyo (TYO)-Anchorage (ANC)-London (LON)-Anchorage-Tokyo. Sleep polysmonograms were recorded on two baseline nights (B1, B2), during layovers, and, after returning to Tokyo, two recovery nights were recorded (R1, R2). In ANC (outbound), total sleep time was reduced and, sleep efficiency was low (72.0 percent). In London, time in bed increased slightly, but sleep efficiency was still reduced. On return to ANC (inbound), there was considerable slow wave sleep rebound and multiple awakenings reduced sleep efficiency to 76.8 percent. Sleep efficiency on R2 was significantly lower than on B1 but not different from R1. To sum up, sleep of aircrews flying multiple transmeridian flights is disrupted during layovers and this effect persists during the two recovery nights. As a result, there is a marked cumulative sleep loss during multilegs polar route trip in comparison to single leg flights. These findings suggest that following such extensive transmeridian trips, crews should have at least three nights of recovery sleep in their home time zone before returning to duty.

  10. Flight evaluation: Ohio University omega receiver base

    NASA Technical Reports Server (NTRS)

    Chamberlin, K. A.; Lilley, R. W.; Salter, R. J.

    1974-01-01

    A flight evaluation is presented of the Ohio University Omega Receiver Base, developed under the NASA Tri-University Program in Air Transportation, to provide a vehicle for the transfer of flight-test data to NASA and to other participants in the Tri-University program. Chart recordings of flight data are given, along with chronological listings of significant events which occurred during the flight. Digital data was prepared in data-processing card form for distribution. Data include phase measurements from all eight Omega time-slots for the duration of the flight, plus event marks which serve to correlate the phase data with flight-path documentation.

  11. Aurora Flight Sciences' Perseus B Remotely Piloted Aircraft in Flight

    NASA Technical Reports Server (NTRS)

    1998-01-01

    A long, slender wing and a pusher propeller at the rear characterize the Perseus B remotely piloted research aircraft, seen here during a test flight in June 1998. Perseus B is a remotely piloted aircraft developed as a design-performance testbed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project. Perseus is one of several flight vehicles involved in the ERAST project. A piston engine, propeller-powered aircraft, Perseus was designed and built by Aurora Flight Sciences Corporation, Manassas, Virginia. The objectives of Perseus B's ERAST flight tests have been to reach and maintain horizontal flight above altitudes of 60,000 feet and demonstrate the capability to fly missions lasting from 8 to 24 hours, depending on payload and altitude requirements. The Perseus B aircraft established an unofficial altitude record for a single-engine, propeller-driven, remotely piloted aircraft on June 27, 1998. It reached an altitude of 60,280 feet. In 1999, several modifications were made to the Perseus aircraft including engine, avionics, and flight-control-system improvements. These improvements were evaluated in a series of operational readiness and test missions at the Dryden Flight Research Center, Edwards, California. Perseus is a high-wing monoplane with a conventional tail design. Its narrow, straight, high-aspect-ratio wing is mounted atop the fuselage. The aircraft is pusher-designed with the propeller mounted in the rear. This design allows for interchangeable scientific-instrument payloads to be placed in the forward fuselage. The design also allows for unobstructed airflow to the sensors and other devices mounted in the payload compartment. The Perseus B that underwent test and development in 1999 was the third generation of the Perseus design, which began with the Perseus Proof-Of-Concept aircraft. Perseus was initially developed as part of NASA's Small High-Altitude Science Aircraft (SHASA) program, which later evolved into the ERAST

  12. X-43A Final Flight Observations

    NASA Technical Reports Server (NTRS)

    Grindle, Laurie

    2011-01-01

    The presentation will provide an overview of the final flight of the NASA X-43A project. The project consisted of three flights, two planned for Mach 7 and one for Mach 10. The first flight, conducted on June 2, 2001, was unsuccessful and resulted in a nine-month mishap investigation. A two-year return to flight effort ensued and concluded when the second Mach 7 flight was successfully conducted on March 27, 2004. The third and final flight, which occurred on November 16, 2004, was the first Mach 10 flight demonstration of an airframe-integrated, scramjet-powered, hypersonic vehicle. As such, the final flight presented first time technical challenges in addition to final flight project closeout concerns. The goals and objectives for the third flight as well as those for the project will be presented. The configuration of the Hyper-X stack including the X-43A, Hyper-X launch vehicle, and Hyper-X research vehicle adapter wil also be presented. Mission differences, vehicle modifications and lessons learned from the first and second flights as they applied to the third flight will also be discussed. Although X-43A flight 3 was always planned to be the final flight of the X-43A project, the X-43 program had two other vehicles and corresponding flight phases in X-43C and X-43B. Those other projects never manifested under the X-43 banner and X-43A flight 3 also became the final flight of X-43 program.

  13. In-Flight Laboratory Analysis

    NASA Technical Reports Server (NTRS)

    Baumann, David; Perusek, Gail; Nelson, Emily; Krihak, Michael; Brown, Dan

    2012-01-01

    One-year study objectives align with HRP requirements. HRP requirements include measurement panels for research and medical operations - These measurement panels are distinctly different. Instrument requirements are defined - Power, volume and mass not quite a critical limitation as for medical operations (deep space exploration missions). One-year evaluation goals will lead HHC towards in-flight laboratory analysis capability.

  14. STS-111 Post Flight Presentation

    NASA Technical Reports Server (NTRS)

    2002-01-01

    The crews of STS-111 (Endeavour's crew: Ken Cockrell, Commander; Paul Lockhart, Pilot; Franklin Chang-Diaz, Mission Specialist (MS); Philippe Perrin, MS; International Space Station's (ISS) Expedition 4 crew: Yury Onufrienko, Commander; Daniel Bursch, Flight Engineer; Carl Walz, Flight Engineer; ISS Expedition 5 crew: Valery Korzun, Commander; Peggy Whitson, Flight Engineer; Sergei Treschev, Flight Engineer) narrate this video of highlights from the mission. It includes footage from each major portion of the mission: launch preparation, launch, entering orbit, opening payload bay doors, rendezvous of Endeavour with ISS, docking of the crafts and the meeting between Endeavour and Expedition 5 crews and the Expedition 4 crew, which Expedition 5 relieved. Docked operations include: crew transfer procedures, transfer of goods, EVA (extravehicular activity) prep, EVA performed by Chang-Diaz and Perrin which included installing a grapple fixture, mounting the Mobile Base System (MBS) to the Mobile Transporter (MT), and changing a joint on the station's Canadarm 2 robotic arm. The video ends with re-entry and landing of the shuttle.

  15. Low Gravity Flight Complement Data

    NASA Technical Reports Server (NTRS)

    Crews, H. C., Jr.

    1979-01-01

    The structural and mechanical design and performance requirements for a space transportation system carrier which will accommodate essentially self-supporting low-g MEA and MAUS facilities are described. Also included are the mission requirements for the materials processing facility and MEA/MAUS experiment flight implementation reguirements.

  16. Physical examination during space flight

    NASA Technical Reports Server (NTRS)

    Harris, B. A. Jr; Billica, R. D.; Bishop, S. L.; Blackwell, T.; Layne, C. S.; Harm, D. L.; Sandoz, G. R.; Rosenow, E. C. 3rd

    1997-01-01

    OBJECTIVE: To develop techniques for conducting a physical examination in microgravity and to describe and document the physiologic changes noted with use of a modified basic physical examination. DESIGN: On the basis of data gathered from physical examinations on KC-135 flights, three physical variables were assessed serially in astronauts during two shuttle missions (of 8- and 10-day duration, respectively). Preflight, in-flight, and postflight examinations were conducted by trained physician-astronauts or flight surgeons, who used this modified examination. MATERIAL AND METHODS: Five male and two female crewmembers participated in the "hands-on" physical examination of all physiologic systems except the genitourinary system. Level of edema, intensity of bowel sounds, and peripheral reflexes were assessed and graded. RESULTS: This investigation identified unique elements of a physical examination performed during space flight that will assist in the development of standard methods for conducting examinations of astronauts in weightlessness. In addition, demonstrable changes induced by microgravity were noted in most physiologic systems examined. CONCLUSION: The data support the hypothesis that the microgravity examination differs from that conducted on earth or in a 1g environment. In addition, alterations in the physiologic response can be detected with use of hands-on technique. These data are invaluable in the development of optimal medical care for humans in space.

  17. Time of flight mass spectrometer

    DOEpatents

    Ulbricht, Jr., William H.

    1984-01-01

    A time-of-flight mass spectrometer is described in which ions are desorbed from a sample by nuclear fission fragments, such that desorption occurs at the surface of the sample impinged upon by the fission fragments. This configuration allows for the sample to be of any thickness, and eliminates the need for complicated sample preparation.

  18. LANDSAT-1 flight evaluation report

    NASA Technical Reports Server (NTRS)

    1975-01-01

    Flight performance analysis for the tenth quarter of operation orbit 11467 to 12745 of LANDSAT 1 are presented. Payload subsystems discussed include: power subsystem; attitude control subsystem; telemetry subsystem; electrical interface subsystem; narrowband tape recorders; wideband telemetry subsystem; return beam vidicon subsystem; multispectral scanner subsystem; and data collection system.

  19. Aerodynamic Simulation of Indoor Flight

    ERIC Educational Resources Information Center

    De Leon, Nelson; De Leon, Matthew N.

    2007-01-01

    We develop a two-dimensional flight simulator for lightweight (less than 10 g) indoor planes. The simulator consists of four coupled time differential equations describing the plane CG, plane pitch and motor. The equations are integrated numerically with appropriate parameters and initial conditions for two planes: (1) Science Olympiad and (2)…

  20. F-18 SRA during flight

    NASA Technical Reports Server (NTRS)

    1996-01-01

    This bright blue-and-white twin-jet aircraft may look like an ordinary F/A-18 Hornet fighter, but inside its a different bird. Currently being flown by NASA's Dryden Flight Research Center, Edwards, California, in a multi-year, joint NASA/DOD/industry program, the former Navy fighter has been modified into a unique Systems Research Aircraft (SRA) to investigate a host of new technologies in the areas of flight controls, airdata sensing and advanced computing. One of the more than 20 experiments being tested aboard the SRA F-18 is an advanced air data sensing system which uses a group of pressure taps flush-mounted on the forward fuselage to measure both altitude and wind speed and direction--critical data for flight control and research investigations. The Real-Time Flush Air Data Sensing system concept is being evaluated for possible use on the X-33 resuable space-launch vehicle. The primary goal of the SRA program is to validate through flight research cutting-edge technologies which could benefit future aircraft and spacecraft by improving efficiency and performance, reducing weight and complexity, with a resultant reduction on development and operational costs.