Sample records for orbit insertion moi
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Creating the Mars Orbit Insertion (MOI) visualizations for Mars Odyssey
NASA Technical Reports Server (NTRS)
Gorjian, Z.
2002-01-01
In close coordination with key personnel from the Mars Odyssey team a series of 18 animations were produced in time for the MOI event and press conference. This presentation will have 5 parts which will detail how the animations were produced and how Odyssey team members contributed to the work to make it as accurate and informative as possible.
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Report on the loss of the Mars Climate Orbiter Mission : JPL special review board
NASA Technical Reports Server (NTRS)
Brace, Richard; Casani, John; Farquhar, Robert; Haynes, Norm; Jordan, Frank; Kohlhase, Charles; Mitchell, Robert; Polutchko, Robert J.; Schallenmuller, Al; Slonski, John P.;
1999-01-01
The Mars Climate Orbiter (MCO) was launched on December 11, 1998. The MCO was to arrive at Mars and begin orbit insertion on September 23, 1999. The Mars Orbit Insertion (MOI) burn, a 16-minute maneuver to slow the spacecraft and enable capture into an orbit around Mars, began on schedule. Five minutes into the maneuver, and approximately 49 seconds before the anticipated time for loss of communication, the MCO was occulted by Mars. Thereafter, no contact with the spacecraft could be established. On September 24, 1999, an internal JPL team (the MCO Peer Review Team) was appointed to help investigate the reason for the loss of spacecraft signal. The Peer Review Team's findings are presented in this report.
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NASA Technical Reports Server (NTRS)
Helfrich, Cliff; Berry, David S.; Bhat, Ramachandra; Border, James; Graat, Eric; Halsell, Allen; Kruizinga, Gerhard; Lau, Eunice; Mottinger, Neil; Rush, Brian;
2015-01-01
In late 2013, the Indian Space Research Organization (ISRO) launched its "Mars Orbiter Mission" (MOM). ISRO engaged NASA's Jet Propulsion Laboratory (JPL) for navigation services to support ISRO's objectives of MOM achieving and maintaining Mars orbit. The navigation support included planning, documentation, testing, orbit determination, maneuver design /analysis, and tracking data analysis. Several of MOM's attributes had an impact on navigation processes, e.g., S -band telecommunications, Earth Orbit Phase maneuvers, and frequent angular momentum desaturation s (AMDs). The primary source of tracking data was NASA/ JPL's Deep Space Network (DSN); JPL also conducted a performance assessment of Indian Deep Space Network (IDSN) tracking data. Planning for the Mars Orbit Insertion (MOI) was complicated by a pressure regulator failure that created uncertainty regarding MOM's main engine and raised potential planetary protection issues. A successful main engine test late on approach resolved these issues; it was quickly followed by a successful MOI on 24-September - 2014 at 02:00 UTC. Less than a month later, Comet Siding Spring's Mars flyby necessitated plans to minimize potential spacecraft damage. At the time of this writing, MOM's orbital operations continue, and plans to extend JPL 's support are in progress. This paper covers the JPL 's support of MOM through the Comet Siding Spring event.
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Mesarich, Carl H.; Rees-George, Jonathan; Gardner, Paul P.; Ghomi, Fatemeh Ashari; Gerth, Monica L.; Andersen, Mark T.; Rikkerink, Erik H. A.; Fineran, Peter C.
2017-01-01
Pseudomonas syringae pv. actinidiae (Psa), the causal agent of kiwifruit canker, is one of the most devastating plant diseases of recent times. We have generated two mini-Tn5-based random insertion libraries of Psa ICMP 18884. The first, a ‘phenotype of interest’ (POI) library, consists of 10,368 independent mutants gridded into 96-well plates. By replica plating onto selective media, the POI library was successfully screened for auxotrophic and motility mutants. Lipopolysaccharide (LPS) biosynthesis mutants with ‘Fuzzy-Spreader’-like morphologies were also identified through a visual screen. The second, a ‘mutant of interest’ (MOI) library, comprises around 96,000 independent mutants, also stored in 96-well plates, with approximately 200 individuals per well. The MOI library was sequenced on the Illumina MiSeq platform using Transposon-Directed Insertion site Sequencing (TraDIS) to map insertion sites onto the Psa genome. A grid-based PCR method was developed to recover individual mutants, and using this strategy, the MOI library was successfully screened for a putative LPS mutant not identified in the visual screen. The Psa chromosome and plasmid had 24,031 and 1,236 independent insertion events respectively, giving insertion frequencies of 3.65 and 16.6 per kb respectively. These data suggest that the MOI library is near saturation, with the theoretical probability of finding an insert in any one chromosomal gene estimated to be 97.5%. However, only 47% of chromosomal genes had insertions. This surprisingly low rate cannot be solely explained by the lack of insertions in essential genes, which would be expected to be around 5%. Strikingly, many accessory genes, including most of those encoding type III effectors, lacked insertions. In contrast, 94% of genes on the Psa plasmid had insertions, including for example, the type III effector HopAU1. These results suggest that some chromosomal sites are rendered inaccessible to transposon insertion, either by DNA-binding proteins or by the architecture of the nucleoid. PMID:28249011
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Emirates Mars Mission Planetary Protection Plan
NASA Astrophysics Data System (ADS)
Awadhi, Mohsen Al
2016-07-01
The United Arab Emirates is planning to launch a spacecraft to Mars in 2020 as part of the Emirates Mars Mission (EMM). The EMM spacecraft, Amal, will arrive in early 2021 and enter orbit about Mars. Through a sequence of subsequent maneuvers, the spacecraft will enter a large science orbit and remain there throughout the primary mission. This paper describes the planetary protection plan for the EMM mission. The EMM science orbit, where Amal will conduct the majority of its operations, is very large compared to other Mars orbiters. The nominal orbit has a periapse altitude of 20,000 km, an apoapse altitude of 43,000 km, and an inclination of 25 degrees. From this vantage point, Amal will conduct a series of atmospheric investigations. Since Amal's orbit is very large, the planetary protection plan is to demonstrate a very low probability that the spacecraft will ever encounter Mars' surface or lower atmosphere during the mission. The EMM team has prepared methods to demonstrate that (1) the launch vehicle targets support a 0.01% probability of impacting Mars, or less, within 50 years; (2) the spacecraft has a 1% probability or less of impacting Mars during 20 years; and (3) the spacecraft has a 5% probability or less of impacting Mars during 50 years. The EMM mission design resembles the mission design of many previous missions, differing only in the specific parameters and final destination. The following sequence describes the mission: 1.The mission will launch in July, 2020. The launch includes a brief parking orbit and a direct injection to the interplanetary cruise. The launch targets are specified by the hyperbolic departure's energy C3, and the hyperbolic departure's direction in space, captured by the right ascension and declination of the launch asymptote, RLA and DLA, respectively. The targets of the launch vehicle are biased away from Mars such that there is a 0.01% probability or less that the launch vehicle arrives onto a trajectory that impacts Mars. 2.The spacecraft is deployed from the launch vehicle and powers on. 3.Within the first month, the spacecraft executes a trajectory correction maneuver to remove the launch bias. The target of this maneuver may still have a small bias to further reduce the probability of inadvertently impacting Mars. 4.Four additional trajectory correction maneuvers are scheduled and planned in the interplanetary cruise in order to target the precise arrival conditions at Mars. The targeted arrival conditions are specified by an altitude above the surface of Mars and an inclination relative to Mars' equator. The closest approach to Mars during the Mars Orbit Insertion (MOI) is over 600 km and the periapsis altitude of the first orbit about Mars is nominally 500 km. The inclination of the first orbit about Mars is nominally around 18 degrees. 5.The Mars Orbit Insertion is performed as a pitch-over burn, approaching no closer than approximately 600 km, and targeting a capture orbit period of 35-40 hours. 6.The spacecraft Capture Orbit has a nominal periapse altitude of 500 km, a nominal apoapse altitude of approximately 45,000 km, and a nominal period of approximately 35 hours. The mission expects that this orbit will be somewhat different after executing the real MOI due to maneuver execution errors. The full range of expected Capture Orbit sizes is acceptable from a planetary protection perspective. 7.The spacecraft remains in the Capture Orbit for two months. 8.The spacecraft then executes three maneuvers in the Transition to Science phase, raising the orbital periapse, raising the orbit inclination, adjusting the apoapse, and placing the argument of periapse near a value of 177 deg. The three maneuvers are nominally one week apart. The first maneuver is large and will raise the periapse significantly, thereafter significantly reducing the probability of Amal impacting Mars in the future.
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Towards a multiconfigurational method of increments
NASA Astrophysics Data System (ADS)
Fertitta, E.; Koch, D.; Paulus, B.; Barcza, G.; Legeza, Ö.
2018-06-01
The method of increments (MoI) allows one to successfully calculate cohesive energies of bulk materials with high accuracy, but it encounters difficulties when calculating dissociation curves. The reason is that its standard formalism is based on a single Hartree-Fock (HF) configuration whose orbitals are localised and used for the many-body expansion. In situations where HF does not allow a size-consistent description of the dissociation, the MoI cannot be guaranteed to yield proper results either. Herein, we address the problem by employing a size-consistent multiconfigurational reference for the MoI formalism. This leads to a matrix equation where a coupling derived by the reference itself is employed. In principle, such an approach allows one to evaluate approximate values for the ground as well as excited states energies. While the latter are accurate close to the avoided crossing only, the ground state results are very promising for the whole dissociation curve, as shown by the comparison with density matrix renormalisation group benchmarks. We tested this two-state constant-coupling MoI on beryllium rings of different sizes and studied the error introduced by the constant coupling.
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2007-11-25
detected by the peak criteria. (*): standard deviation]. Cntrl MOI 1 H1N1 MOI 10 H1N1 MOI 10 H6N2 MOI 10 H9N2 Pea k No. R.T. A. S.P . R.T. A. S.P...by the peak criteria. (*): standard deviation]. Cntrl MOI 1 H1N1 MOI 10 H1N1 MOI 10 H6N2 MOI 10 H9N2 Pea k No. R.T. A. S.P . R.T. A. S.P . R.T...factor) 12 Cntrl MOI 1 H1N1 MOI 10 H1N1 MOI 10 H6N2 MOI 10 H9N2 Peak No. Chem ID 24 hr 48 hr 24 hr 48 hr 24 hr 48 hr 24 hr 48 hr 24 hr 48 hr
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The Mars Reconnaissance Orbiter Mission: From Launch to the Primary Science Orbit
NASA Technical Reports Server (NTRS)
Johnston, Martin D.; Graf, James E.; Zurek, Richard W.; Eisen, Howard J.; Jai, Benhan; Erickson, James K.
2007-01-01
The Mars Reconnaissance Orbiter (MRO) was launched from Cape Canaveral Air Force Station, Florida, USA, aboard an Atlas V-401 launch vehicle on August 12, 2005. The MRO spacecraft carries a very sophisticated scientific payload. Its primary science mission is to to provide global, regional survey, and targeted observations from a low altitude orbit for one Martian year (687 Earth days). After a seven month interplanetary transit, the spacecraft fired its six main engines and established a highly elliptical capture orbit at Mars. During the post-MOI early check-out period, four instruments acquired engineering-quality data. This was followed by five months of aerobraking operations. After aerobraking was terminated, a series of propulsive maneuvers were used to establish the desired low altitude science orbit. As the spacecraft is readied for its primary science mission, spacecraft and instrument checkout and deployment activities have continued.
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MOI to TEI : a Mars Sample Return strategy
NASA Technical Reports Server (NTRS)
Smith, Chad W.; Maddock, Robert W.
2006-01-01
This paper describes the issues and challenges related to the design of the rendezvous between the Earth Return Vehicle (ERV) and the Orbiting Sample (OS) for the Mars Sample Return (MSR) mission. In particular, attention will be focused on the strategy for 'optimizing' the intermediate segment of the rendezvous process, during which there are a great number of variables that must be considered and well understood.
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Contingency study for the third international Sun-Earth Explorer (ISEE-3) satellite
NASA Technical Reports Server (NTRS)
Dunham, D. W.
1979-01-01
The third satellite of the international Sun-Earth Explorer program was inserted into a periodic halo orbit about L sub 1, the collinear libration point between the Sun and the Earth-Moon barycenter. A plan is presented that was developed to enable insertion into the halo orbit in case there was a large underperformance of the Delta second or third stage during the maneuver to insert the spacecraft into the transfer trajectory. After one orbit of the Earth, a maneuver would be performed near perigee to increase the energy of the orbit. A relatively small second maneuver would put the spacecraft in a transfer trajectory to the halo orbit, into which it could be inserted for a total cost within the fuel budget. Overburns (hot transfer trajectory insertions) were also studied.
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Lunar prospector mission design and trajectory support
NASA Technical Reports Server (NTRS)
Lozier, David; Galal, Ken; Folta, David; Beckman, Mark
1998-01-01
The Lunar Prospector mission is the first dedicated NASA lunar mapping mission since the Apollo Orbiter program which was flown over 25 years ago. Competitively selected under the NASA Discovery Program, Lunar Prospector was launched on January 7, 1998 on the new Lockheed Martin Athena 2 launch vehicle. The mission design of Lunar Prospector is characterized by a direct minimum energy transfer trajectory to the moon with three scheduled orbit correction maneuvers to remove launch and cislunar injection errors prior to lunar insertion. At lunar encounter, a series of three lunar orbit insertion maneuvers and a small circularization burn were executed to achieve a 100 km altitude polar mapping orbit. This paper will present the design of the Lunar Prospector transfer, lunar insertion and mapping orbits, including maneuver and orbit determination strategies in the context of mission goals and constraints. Contingency plans for handling transfer orbit injection and lunar orbit insertion anomalies are also summarized. Actual flight operations results are discussed and compared to pre-launch support analysis.
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NASA Technical Reports Server (NTRS)
Roberts, Craig; Case, Sara; Reagoso, John; Webster, Cassandra
2015-01-01
The Deep Space Climate Observatory mission launched on February 11, 2015, and inserted onto a transfer trajectory toward a Lissajous orbit around the Sun-Earth L1 libration point. This paper presents an overview of the baseline transfer orbit and early mission maneuver operations leading up to the start of nominal science orbit operations. In particular, the analysis and performance of the spacecraft insertion, mid-course correction maneuvers, and the deep-space Lissajous orbit insertion maneuvers are discussed, com-paring the baseline orbit with actual mission results and highlighting mission and operations constraints..
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Mars Observer Lecture: Mars Orbit Insertion
NASA Technical Reports Server (NTRS)
Dodd, Suzanne R. (Personal Name)
1993-01-01
The Mars Observer mission spacecraft was primarily designed for exploring Mars and the Martian environment. The Mars Observer was launched on September 25, 1992. The spacecraft was lost in the vicinity of Mars on August 21, 1993 when the spacecraft began its maneuvering sequence for Martian orbital insertion. This videotape shows a lecture by Suzanne R. Dodd, the Mission Planning Team Chief for the Mars Observer Project. Ms Dodd begins with a brief overview of the mission and the timeline from the launch to orbital insertion. Ms Dodd then reviews slides showing the trajectory of the spacecraft on its trip to Mars. Slides of the spacecraft being constructed are also shown. She then discusses the Mars orbit insertion and the events that will occur to move the spacecraft from the capture orbit into a mapping orbit. During the trip to Mars, scientists at JPL had devised a new strategy, called Power In that would allow for an earlier insertion into the mapping orbit. The talk summarizes this strategy, showing on a slide the planned transition orbits. There are shots of the Martian moon, Phobos, taken from the Viking spacecraft, as Ms Dodd explains that the trajectory will allow the orbiter to make new observations of that moon. She also explains the required steps to prepare for mapping after the spacecraft has achieved the mapping orbit around Mars. The lecture ends with a picture of Mars from the Observer on its approach to the planet.
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2003-09-04
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, Richard Parker, with NASA, watches a monitor showing images from a camera inserted beneath tiles of the orbiter Endeavour to inspect for corrosion.
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Electric Propulsion for Low Earth Orbit Constellations
NASA Technical Reports Server (NTRS)
Oleson, Steven R.; Sankovic, John M.
1998-01-01
Hall Effect electric propulsion was evaluated for orbit insertion, satellite repositioning, orbit maintenance and de-orbit applications for a sample low earth orbit satellite constellation. Since the low masses of these satellites enable multiple spacecraft per launch, the ability to add spacecraft to a given launch was used as a figure of merit. When compared to chemical propulsion, the Hall thruster system can add additional spacecraft per launch using planned payload power levels. One satellite can be added to the assumed four satellite baseline chemical launch without additional mission times. Two or three satellites may be added by providing part of the orbit insertion with the Hall system. In these cases orbit insertion times were found to be 35 and 62 days. Depending on the electric propulsion scenario, the resulting launch vehicle savings is nearly two, three or four Delta 7920 launch vehicles out of the chemical baseline scenarios eight Delta 7920 launch vehicles.
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Electric Propulsion for Low Earth Orbit Constellations
NASA Technical Reports Server (NTRS)
Oleson, Steven R.; Sankovic, John M.
1998-01-01
Hall effect electric propulsion was evaluated for orbit insertion, satellite repositioning, orbit maintenance and de-orbit applications for a sample low earth orbit satellite constellation. Since the low masses of these satellites enable multiple spacecraft per launch, the ability to add spacecraft to a given launch was used as a figure of merit. When compared to chemical propulsion, the Hall thruster system can add additional spacecraft per launch using planned payload power levels. One satellite can be added to the assumed four satellite baseline chemical launch without additional mission times. Two or three satellites may be added by providing part of the orbit insertion with the Hall system. In these cases orbit insertion times were found to be 35 and 62 days. Depending, on the electric propulsion scenario, the resulting launch vehicle savings is nearly two, three or four Delta 7920 launch vehicles out of the chemical baseline scenario's eight Delta 7920 launch vehicles.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Meng, Xiangyu; Shi, Xianbo; Wang, Yong
The mutual optical intensity (MOI) model is extended to include the propagation of partially coherent radiation through non-ideal mirrors. The propagation of the MOI from the incident to the exit plane of the mirror is realised by local ray tracing. The effects of figure errors can be expressed as phase shifts obtained by either the phase projection approach or the direct path length method. Using the MOI model, the effects of figure errors are studied for diffraction-limited cases using elliptical cylinder mirrors. Figure errors with low spatial frequencies can vary the intensity distribution, redistribute the local coherence function and distortmore » the wavefront, but have no effect on the global degree of coherence. The MOI model is benchmarked againstHYBRIDand the multi-electronSynchrotron Radiation Workshop(SRW) code. The results show that the MOI model gives accurate results under different coherence conditions of the beam. Other than intensity profiles, the MOI model can also provide the wavefront and the local coherence function at any location along the beamline. The capability of tuning the trade-off between accuracy and efficiency makes the MOI model an ideal tool for beamline design and optimization.« less
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A Survey of Ballistic Transfers to Low Lunar Orbit
NASA Technical Reports Server (NTRS)
Parker, Jeffrey S.; Anderson, Rodney L.; Peterson, Andrew
2011-01-01
A simple strategy is identified to generate ballistic transfers between the Earth and Moon, i.e., transfers that perform two maneuvers: a trans-lunar injection maneuver to depart the Earth and a Lunar Orbit Insertion maneuver to insert into orbit at the Moon. This strategy is used to survey the performance of numerous transfers between varying Earth parking orbits and varying low lunar target orbits. The transfers surveyed include short 3-6 day direct transfers, longer 3-4 month low energy transfers, and variants that include Earth phasing orbits and/or lunar flybys.
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Mutual optical intensity propagation through non-ideal mirrors
Meng, Xiangyu; Shi, Xianbo; Wang, Yong; ...
2017-08-18
The mutual optical intensity (MOI) model is extended to include the propagation of partially coherent radiation through non-ideal mirrors. The propagation of the MOI from the incident to the exit plane of the mirror is realised by local ray tracing. The effects of figure errors can be expressed as phase shifts obtained by either the phase projection approach or the direct path length method. Using the MOI model, the effects of figure errors are studied for diffraction-limited cases using elliptical cylinder mirrors. Figure errors with low spatial frequencies can vary the intensity distribution, redistribute the local coherence function and distortmore » the wavefront, but have no effect on the global degree of coherence. The MOI model is benchmarked againstHYBRIDand the multi-electronSynchrotron Radiation Workshop(SRW) code. The results show that the MOI model gives accurate results under different coherence conditions of the beam. Other than intensity profiles, the MOI model can also provide the wavefront and the local coherence function at any location along the beamline. The capability of tuning the trade-off between accuracy and efficiency makes the MOI model an ideal tool for beamline design and optimization.« less
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2003-11-11
KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility insert the liquid oxygen feedline for the 17-inch disconnect in the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.
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Mars Observer trajectory and orbit design
NASA Technical Reports Server (NTRS)
Beerer, Joseph G.; Roncoli, Ralph B.
1991-01-01
The Mars Observer launch, interplanetary, Mars orbit insertion, and mapping orbit designs are described. The design objective is to enable a near-maximum spacecraft mass to be placed in orbit about Mars. This is accomplished by keeping spacecraft propellant requirements to a minimum, selecting a minimum acceptable launch period, equalizing the spacecraft velocity change requirement at the beginning and end of the launch period, and constraining the orbit insertion maneuvers to be coplanar. The mapping orbit design objective is to provide the opportunity for global observation of the planet by the science instruments while facilitating the spacecraft design. This is realized with a sun-synchronous near-polar orbit whose ground-track pattern covers the planet at progressively finer resolution.
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Finite element model for MOI applications using A-V formulation
NASA Astrophysics Data System (ADS)
Xuan, L.; Shanker, B.; Udpa, L.; Shih, W.; Fitzpatrick, G.
2001-04-01
Magneto-optic imaging (MOI) is a relatively new sensor application of an extension of bubble memory technology to NDT and produce easy-to-interpret, real time analog images. MOI systems use a magneto-optic (MO) sensor to produce analog images of magnetic flux leakage from surface and subsurface defects. The instrument's capability in detecting the relatively weak magnetic fields associated with subsurface defects depends on the sensitivity of the magneto-optic sensor. The availability of a theoretical model that can simulate the MOI system performance is extremely important for optimization of the MOI sensor and hardware system. A nodal finite element model based on magnetic vector potential formulation has been developed for simulating MOI phenomenon. This model has been used for predicting the magnetic fields in simple test geometry with corrosion dome defects. In the case of test samples with multiple discontinuities, a more robust model using the magnetic vector potential Ā and electrical scalar potential V is required. In this paper, a finite element model based on A-V formulation is developed to model complex circumferential crack under aluminum rivets in dimpled countersink.
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Specific feature of magnetooptical images of stray fields of magnets of various geometrical shapes
NASA Astrophysics Data System (ADS)
Ivanov, V. E.; Koveshnikov, A. V.; Andreev, S. V.
2017-08-01
Specific features of magnetooptical images (MOIs) of stray fields near the faces of prismatic hard magnetic elements have been studied. Attention has primarily been focused on MOIs of fields near faces oriented perpendicular to the magnetic moment of hard magnetic elements. With regard to the polar sensitivity, MOIs have practically uniform brightness and geometrically they coincide with the figures of the bases of the elements. With regard to longitudinal sensitivity, MOIs consist of several sectors, the number of which is determined by the number of angles of the image. Each angle is divided by the bisectrix into two sectors of different brightnesses; therefore, the MOI of a triangular magnet consists of three sectors. A rectangle consists of four sectors separated by the bisectrices of the interior angles. In all types of figures, these lines converge at the center of the figure and form a singular point of the source or sink type.
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Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion
NASA Technical Reports Server (NTRS)
Cork, M. J.; French, R. L.; Leising, C. J.; Schmit, D. D.
1972-01-01
On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
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Wang, Junming; Zhang, Hong; Chen, Wei; Li, Guigang
2012-01-01
Anophthalmia is associated with a range of psychosocial difficulties and hydroxyapatite orbital implant insertion and prosthesis wearing is the predominant rehabilitation therapy for anophthalmia. However, few articles have compared preoperative and postoperative psychosocial outcomes using standardized questionnaires. This study aimed to investigate the psychosocial benefits of hydroxyapatite orbital implant insertion and prosthesis wearing in this patient population. In all, 36 participants were tested preoperatively and 6-months postoperatively using standardized measures of anxiety and depression (Hospital Anxiety and Depression Scale), social anxiety and social avoidance (Derriford Appearance Scale-Short Form), and quality of life (World Health Organization Quality of Life Scale-Short Form). Before treatment, levels of depression were comparable with population norms; however, levels of general anxiety were slightly raised, levels of social anxiety, social avoidance, and quality of life were significantly poorer than population norms. Treatment resulted in significant improvement in psychosocial adjustment with improvements in all study variables for the participant group as a whole. Hydroxyapatite orbital implant insertion and prosthesis wearing offers significant improvements in psychological and physical functioning for patients with anophthalmia.
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NASA Technical Reports Server (NTRS)
Textor, G. P.; Kelly, L. B.; Kelly, M.
1972-01-01
The Deep Space Tracking and Data System activities in support of the Mariner Mars 1971 project from the first trajectory correction maneuver on 4 June 1971 through cruise and orbit insertion on 14 November 1971 are presented. Changes and updates to the TDS requirements and to the plan and configuration plus detailed information on the TDS flight support performance evaluation and the preorbital testing and training are included. With the loss of Mariner 8 at launch, a few changes to the Mariner Mars 1971 requirements, plan, and configuration were necessitated. Mariner 9 is now assuming the former mission plan of Mariner 8, including the TV mapping cycles and a 12-hr orbital period. A second trajectory correction maneuver was not required because of the accuracy of the first maneuver. All testing and training for orbital operations were completed satisfactorily and on schedule. The orbit insertion was accomplished with excellent results.
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NASA Astrophysics Data System (ADS)
Akim, E. L.; Zaslavsky, G. S.; Morskoy, I. M.; Ruzsky, E. G.; Stepaniants, V. A.; Tuchin, A. G.
2010-02-01
This paper is concerned with the problems of ballistics, navigation, and flight control of the space craft (SC) in the Phobos-Grunt mission. We consider an insertion into the Earth-Mars transfer trajectory, the Earth-Mars transfer, the strategy of corrections, and the accuracy of the insertion of the SC into Martian orbit. During the orbital maneuvering stage in the sphere of influence of Mars, we set up a scheme that allows for the insertion of the SC, with the prescribed accuracy, into a point 80-km above the Phobos surface over the theoretical landing area. We specify the sequence for a controlled landing and provide methods for solving the problems of navigation and control during a self-c ontained landing. We also consider the liftoff from Phobos, insertion into the parking orbit, and the Mars-Earth transfer.
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First Materials Science Research Rack Capabilities and Design Features
NASA Technical Reports Server (NTRS)
Schaefer, D.; King, R.; Cobb, S.; Whitaker, Ann F. (Technical Monitor)
2001-01-01
The first Materials Science Research Rack (MSRR-1) will accommodate dual Experiment Modules (EM's) and provide simultaneous on-orbit processing operations capability. The first international Materials Science Experiment Module for the MSRR-1 is an international cooperative research activity between NASA's Marshall Space Flight Center (MSFC) and the European Space Agency's (ESA) European Space Research and Technology Center. (ESTEC). This International Standard Payload Rack (ISPR) will contain the Materials Science Laboratory (MSL) developed by ESA as an Experiment Module. The MSL Experiment Module will accommodate several on-orbit exchangeable experiment-specific Module Inserts. Module Inserts currently planned are a Quench Module Insert, Low Gradient Furnace, Solidification with Quench Furnace, and Diffusion Module Insert. The second Experiment Module for the MSRR-1 configuration is a commercial device supplied by MSFC's Space Products Department (SPD). It includes capabilities for vapor transport processes and liquid metal sintering. This Experiment Module will be replaced on-orbit with other NASA Materials Science EMs.
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Tascon, Marcos; Alam, Md Nazmul; Gómez-Ríos, Germán Augusto; Pawliszyn, Janusz
2018-02-20
Technologies that efficiently integrate the sampling and sample preparation steps with direct introduction to mass spectrometry (MS), providing simple and sensitive analytical workflows as well as capabilities for automation, can generate a great impact in a vast variety of fields, such as in clinical, environmental, and food-science applications. In this study, a novel approach that facilitates direct coupling of Bio-SPME devices to MS using a microfluidic design is presented. This technology, named microfluidic open interface (MOI), which operates under the concept of flow-isolated desorption volume, consists of an open-to-ambient desorption chamber (V ≤ 7 μL) connected to an ionization source. Subsequently, compounds of interest are transported to the ionization source by means of the self-aspiration process intrinsic of these interfaces. Thus, any ionization technology that provides a reliable and constant suction, such as electrospray ionization (ESI), atmospheric-pressure chemical ionization (APCI), or inductively coupled plasma ionization (ICP), can be hyphenated to MOI. Using this setup, the desorption chamber is used to release target compounds from the coating, while the isolation of the flow enables the ionization source to be continuously fed with solvent, all without the necessity of employment of additional valves. As a proof of concept, the design was applied to an ESI-MS/MS system for experimental validation. Furthermore, numerical simulations were undertaken to provide a detailed understanding of the fluid flow pattern inside the interface, then used to optimize the system for better efficiency. The analytical workflow of the developed Bio-SPME-MOI-MS setup consists of the direct immersion of SPME fibers into the matrix to extract/enrich analytes of interest within a short period of time, followed by a rinsing step with water to remove potentially adhering proteins, salts, and/or other interfering compounds. Next, the fiber is inserted into the MOI for desorption of compounds of interest. Finally, the volume contained in the chamber is drained and moved toward the electrospray needle for ionization and direct introduction to MS. Aiming to validate the technology, the fast determination of selected immunosuppressive drugs (e.g., tacrolimus, cyclosporine, sirolimus, and everolimus) from 100 μL of whole blood was assessed. Limits of quantitation in the subppb range were obtained for all studied compounds. Good linearity (r 2 ≥ 0.99) and excellent precision, with (8%) and without (14%) internal standard correction, were attained.
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Transfer Trajectory Design for the Mars Atmosphere and Volatile Evolution (MAVEN) Mission
NASA Technical Reports Server (NTRS)
Folta, David; Demcak, Stuart; Young, Brian; Berry, Kevin
2013-01-01
The Mars Atmosphere and Volatile Evolution (MAVEN) mission will determine the history of the loss of volatiles from the Martian atmosphere from a highly inclined elliptical orbit. MAVEN will launch from Cape Canaveral Air Force Station on an Atlas-V 401 during an extended 36-day launch period opening November 18, 2013. The MAVEN Navigation and Mission Design team performed a Monte Carlo analysis of the Type-II transfer to characterize; dispersions of the arrival B-Plane, trajectory correction maneuvers (TCMs), and the probability of Mars impact. This paper presents detailed analysis of critical MOI event coverage, maneuver constraints, deltaV-99 budgets, and Planetary Protection requirements.
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Electric Propulsion for Low Earth Orbit Communication Satellites
NASA Technical Reports Server (NTRS)
Oleson, Steven R.
1997-01-01
Electric propulsion was evaluated for orbit insertion, satellite positioning and de-orbit applications on big (hundreds of kilograms) and little (tens of kilograms) low earth orbit communication satellite constellations. A simple, constant circumferential thrusting method was used. This technique eliminates the complex guidance and control required when shading of the solar arrays must be considered. Power for propulsion was assumed to come from the existing payload power. Since the low masses of these satellites enable multiple spacecraft per launch, the ability to add spacecraft to a given launch was used as a figure of merit. When compared to chemical propulsion ammonia resistojets, ion, Hall, and pulsed plasma thrusters allowed an additional spacecraft per launch Typical orbit insertion and de-orbit times were found to range from a few days to a few months.
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Air ambulance tasking: mechanism of injury, telephone interrogation or ambulance crew assessment?
Wilmer, Ian; Chalk, Graham; Davies, Gareth Edward; Weaver, Anne Elizabeth; Lockey, David John
2015-10-01
The identification of serious injury is critical to the tasking of air ambulances. London's Air Ambulance (LAA) is dispatched by a flight paramedic based on mechanism of injury (MOI), paramedical interrogation of caller (INT) or land ambulance crew request (REQ).This study aimed to demonstrate which of the dispatch methods was most effective (in accuracy and time) in identifying patients with serious injury. A retrospective review of 3 years of data (to December 2010) was undertaken. Appropriate dispatch was defined as the requirement for LAA to escort the patient to hospital or for resuscitation on-scene. Inaccurate dispatch was where LAA was cancelled or left the patient in the care of the land ambulance crew. The χ(2) test was used to calculate p values; with significance adjusted to account for multiple testing. There were 2203 helicopter activations analysed: MOI 18.9% (n=417), INT 62.4% (n=1375) and REQ 18.7% (n=411). Appropriate dispatch rates were MOI 58.7% (245/417), INT 69.7% (959/1375) and REQ 72.2% (297/411). INT and REQ were both significantly more accurate than MOI (p<0.0001). There was no significant difference in accuracy between INT and REQ (p=0.36). Combining MOI and INT remotely identified 80.2% of patients, with an overtriage rate of 32.8%. Mean time to dispatch (in minutes) was MOI 4, INT 8 and REQ 21. Telephone interrogation of the caller by a flight paramedic is as accurate as ground ambulance crew requests, and both are significantly better than MOI in identifying serious injury. Overtriage remains an issue with all methods. Published by the BMJ Publishing Group Limited. For permission to use (where not already granted under a licence) please go to http://group.bmj.com/group/rights-licensing/permissions.
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[Construction of rAAV2-GPIIb/IIIa vector and test of its expression and function in vitro].
Wang, Kai; Peng, Jian-Qiang; Chen, Fang-Ping; Wu, Xiao-Bin
2006-04-01
This study was aimed to explore the possibility of rAAV2 vector-mediating gene therapy for Glanzmann' s thrombasthenia. The rAAV2-GPIIb/IIIa vector was constructed. The GPIIb/IIIa gene expression in mammal cell were examined by different methods, such as: detection of mRNA expression in BHK-21 cells after 24 hours of infection (MOI = 1 x 10(5) v.g/cell) was performed by RT-PCR; the relation between MOI and quantity of GPII6/IIIa gene expression was detected by FACS after 48 hours of infection; GPIIb/IIIa protein expression in BHK-21 cells after 48 hours of infection (MOI = 10(5) v x g/cell) was assayed by Western blot, GPIIb/IIIa protein expression on cell surface was detected by immunofluorescence, and the biological function of expressing product was determined by PAC-1 conjunct experiments. The results showed that GPIIb/IIIa gene expression in mRNA level could be detected in BHK-21 cells after 24 hours of infection at MOI = 1 x 10(5) v x g/cell and the GPIIb/IIIa gene expression in protein level could be detected in BHK-21 cells after 48 hours of infection at MOI = 1 x 10(5) v x g/cell. In certain range, quantity of GPIIb/IIIa gene expression increased with MOI, but overdose of MOI decreased quantity of GPIIb/IIIa gene expression. Activated product of GPIIb/IIIa gene expression could combined with PAC-I, and possesed normal biological function. In conclusion, rAAV2 vactor can effectively mediate GPIIb and GPIIIa gene expressing in mammal cells, and the products of these genes exhibit biological function. This result may provide a basis for application of rAAV2 vector in Glanzmann's thrombasthenia gene therapy in furture.
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Demographics of high-energy mechanisms of injury in the Kids Inpatient Database.
Leung, Brian; Koval, Kenneth J; Carney, Brian; Spratt, Kevin F
2006-01-01
The purpose of this study was to review the relationship of patient demographics to mechanism of injury (MOI). The 2000 Kids Inpatient Database (KID) was used. Logistic regression was used to evaluate the relationship between each MOI relative to other MOIs for each of five identified predictors (age, gender, race, socioeconomic status, geographic region). The KID had 87,795 children with a MOI coded and complete data for all predictors. For motor vehicle accidents, 16- to 20-year-olds were up to 3.72 times more likely to be involved than any other age group, and males were 40% less likely compared with females. For firearm hospitalizations, 16- to 20-year-old black males have significantly higher risk compared with all other identified groups.
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14 CFR 417.3 - Definitions and acronyms.
Code of Federal Regulations, 2010 CFR
2010-01-01
... vehicle during— (i) The ascent to initial orbital insertion and through at least one complete orbit; and (ii) Each subsequent orbital maneuver or burn from initial park orbit, or direct ascent to a higher or... launch vehicle achieves orbit or can no longer reach a populated or other protected area. Command...
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14 CFR 417.3 - Definitions and acronyms.
Code of Federal Regulations, 2011 CFR
2011-01-01
... vehicle during— (i) The ascent to initial orbital insertion and through at least one complete orbit; and (ii) Each subsequent orbital maneuver or burn from initial park orbit, or direct ascent to a higher or... launch vehicle achieves orbit or can no longer reach a populated or other protected area. Command...
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14 CFR 417.3 - Definitions and acronyms.
Code of Federal Regulations, 2014 CFR
2014-01-01
... vehicle during— (i) The ascent to initial orbital insertion and through at least one complete orbit; and (ii) Each subsequent orbital maneuver or burn from initial park orbit, or direct ascent to a higher or... launch vehicle achieves orbit or can no longer reach a populated or other protected area. Command...
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14 CFR 417.3 - Definitions and acronyms.
Code of Federal Regulations, 2012 CFR
2012-01-01
... vehicle during— (i) The ascent to initial orbital insertion and through at least one complete orbit; and (ii) Each subsequent orbital maneuver or burn from initial park orbit, or direct ascent to a higher or... launch vehicle achieves orbit or can no longer reach a populated or other protected area. Command...
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14 CFR 417.3 - Definitions and acronyms.
Code of Federal Regulations, 2013 CFR
2013-01-01
... vehicle during— (i) The ascent to initial orbital insertion and through at least one complete orbit; and (ii) Each subsequent orbital maneuver or burn from initial park orbit, or direct ascent to a higher or... launch vehicle achieves orbit or can no longer reach a populated or other protected area. Command...
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Computer Assisted Exercise Environment for Terrorist Attack Consequence Management
2006-09-01
security and crisis management. Fig. 3. Third Generation SSR for Integrated Security Sector MoD MoI MoEM MoFA Special Services Integrated Security...Ministries: MoEM , MoI, MoD, MH, MoEW, MoE, MoAF National Media, NGOs, other agencies District EOC / LEMA MHS/IDS/WIS Field EOC MHS/IDS/WIS MHS IDS...SRA EDA DG Environment ... EU SR Fund MoD MoI MoE&S MoEM ... National USA Great Britain Netherlands Germany ... Bilateral BSEC Stab. Pact ... Regional
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Energetic particle diffusion and the A ring: Revisiting noise from Cassini's orbital insertion
NASA Astrophysics Data System (ADS)
Crary, Frank; Kollmann, Peter
2016-04-01
Immediately following Cassini's orbital insertion on July 1, 2004 the Cassini spacecraft passed over the Saturn's main rings. In anticipation of the final phase of the Cassini mission, with orbits inside and over the main rings, we have re-examined data from the CAPS instrument taken during the orbital insertion period. One previously-neglected feature is the detector noise in the ELS sensor. This has proven to be a sensitive, relative measure of omni-directional energetic (>5 MeV) electron flux. The data are obtained at 31.25 ms time resolution, corresponding to 0.46 km spatial resolution. Over the A ring, the energetic electron flux was essentially zero (~3 counts per sample.) At the edge of the A ring, this dramatically increased to approximately 2500 counts per sample in the space of 17.5 km. We use these results to derive the energetic particle diffusion rate and the absorption (optical depth) of the ring.
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Treatment of congenital anophthalmos with self-inflating polymer expanders: a new method.
Wiese, K G; Vogel, M; Guthoff, R; Gundlach, K K
1999-04-01
Congenital anophthalmos is a rare malformation in which the optic vesicle fails to develop. This leads to a small bony orbit, a constricted mucosal socket, short eyelids, reduced palpebral fissure and malar hypoplasia. The treatment includes both aesthetic and functional aspects. Therefore, a two-step procedure is described using a new self-inflating hydrogel expander. A lens-shaped expander with a diameter of 8 mm expands the lids and the mucosal socket to allow insertion of an eye prosthesis. As a second step, orbital expansion is performed with a spherical device. The expanders absorb lacrimal fluid from the mucosal socket or tissue fluid and start swelling when implanted in the orbital tissue. The insertion of an expander into the orbit as well as into the conjunctival pocket including its fixation by a single suture took only a few minutes and was an easy procedure. The expansion of the small conjunctival sockets was successfully completed in all cases within a period of 2-4 weeks. The weight (= volume in ml) of devices increased from 0.15-1.5 g (lens-shaped expander; weight in grams = volume in ml) respectively, 0.3-3.5 g (spherical device). The expanders inserted in orbital tissue increased from 0.4-4.4 g. This is equivalent to a 10 to 11 fold increase in their water-free volumes. Orbital expansion with spherical devices in combination with the inserted eye prosthesis enlarges the lid and palpebral fissures also. In contrast to conventional silicon balloon expanders, the procedure using self-inflating hydrogel expanders is simple and highly efficient.
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Compartmental Innervation of the Superior Oblique Muscle in Mammals.
Le, Alan; Poukens, Vadims; Ying, Howard; Rootman, Daniel; Goldberg, Robert A; Demer, Joseph L
2015-10-01
Intramuscular innervation of mammalian horizontal rectus extraocular muscles (EOMs) is compartmental. We sought evidence of similar compartmental innervation of the superior oblique (SO) muscle. Three fresh bovine orbits and one human orbit were dissected to trace continuity of SO muscle and tendon fibers to the scleral insertions. Whole orbits were also obtained from four humans (two adults, a 17-month-old child, and a 33-week stillborn fetus), two rhesus monkeys, one rabbit, and one cow. Orbits were formalin fixed, embedded whole in paraffin, serially sectioned in the coronal plane at 10-μm thickness, and stained with Masson trichrome. Extraocular muscle fibers and branches of the trochlear nerve (CN4) were traced in serial sections and reconstructed in three dimensions. In the human, the lateral SO belly is in continuity with tendon fibers inserting more posteriorly on the sclera for infraducting mechanical advantage, while the medial belly is continuous with anteriorly inserting fibers having mechanical advantage for incycloduction. Fibers in the monkey superior SO insert more posteriorly on the sclera to favor infraduction, while the inferior portion inserts more anteriorly to favor incycloduction. In all species, CN4 bifurcates prior to penetrating the SO belly. Each branch innervates a nonoverlapping compartment of EOM fibers, consisting of medial and lateral compartments in humans and monkeys, and superior and inferior compartments in cows and rabbits. The SO muscle of humans and other mammals is compartmentally innervated in a manner that could permit separate CN4 branches to selectively influence vertical versus torsional action.
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Lin, Chen-Si; Wang, Chinling; Tsai, Hsiang-Jung; Chou, Chung-Hsi
2010-11-15
It remains unclear whether the growth of Listeria monocytogenes on a ready-to-eat (RTE) meat matrix has an impact on the bacterium's pathogenic abilities. In this study, we investigated the impact of environments on virulence by growing L. monocytogenes (F2365 strain) on brain heart infusion agar (BHI), tryptic soy agar (TSA), and RTE turkey meat matrices. Bacteria cultured from these media were harvested and used to infect mouse macrophage cell line J774A.1 with different MOIs to examine their invasion ability. At MOI=10 and 50, the numbers of bacteria recovered from cells infected with turkey-meat-grown Listeria were significantly higher than those from the two nutrient-rich growth media. Additionally, MOI played a role in determining L. monocytogenes recovery rates, since significant differences were found amongst all three groups at low MOI, while no significant differences were found between BHI and TSA groups at high MOI. These results indicate that environmental changes affect the ability of L. monocytogenes to invade and survive intracellularly while grown on RTE-meat matrix. Copyright © 2010 Elsevier B.V. All rights reserved.
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A strategy for developing a launch vehicle system for orbit insertion: Methodological aspects
NASA Astrophysics Data System (ADS)
Klyushnikov, V. Yu.; Kuznetsov, I. I.; Osadchenko, A. S.
2014-12-01
The article addresses methodological aspects of a development strategy to design a launch vehicle system for orbit insertion. The development and implementation of the strategy are broadly outlined. An analysis is provided of the criterial base and input data needed to define the main requirements for the launch vehicle system. Approaches are suggested for solving individual problems in working out the launch vehicle system development strategy.
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Richard, F; Ouédraogo, C; Compaoré, J; Dubourg, D; De Brouwere, V
2007-08-01
To describe the implementation of a cost-sharing system for emergency obstetric care in an urban health district of Ouagadougou, Burkina Faso and analyse its results after 1 year of activity. Service availability and use, service quality, knowledge of the cost-sharing system in the community and financial viability of the system were measured before and after the system was implemented. Different sources of data were used: community survey, anthropological study, routine data from hospital files and registers and specific data collected on major obstetric interventions (MOI) in all the hospitals utilized by the district population. Direct costs of MOI were collected for each patient through an individual form and monitored during the year 2005. Rates of MOI for absolute maternal indications (AMI) were calculated for the period 2003-2005. The direct cost of a MOI was on average 136US$, including referral cost. Through the cost-sharing system this amount was shared between families (46US$), health centres (15US$), Ministry of Health (38US$) and local authority (37US$). The scheme was started in January 2005. The rate of cost recovery was 91.3% and the balance at the end of 2005 was slightly positive (4.7% of the total contribution). The number of emergency referrals by health centres increased from 84 in 2004 to 683 in 2005. MOI per 100 expected births increased from 1.95% in 2003 to 3.56% in 2005 and MOI for AMI increased from 0.75% to 1.42%. The dramatic increase in MOI suggests that the cost-sharing scheme decreased financial and geographical barriers to emergency obstetric care. Other positive effects on quality of care were documented but the sustainability of such a system remains uncertain in the dynamic context of Burkina Faso (decentralization).
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Abort Options for Human Missions to Earth-Moon Halo Orbits
NASA Technical Reports Server (NTRS)
Jesick, Mark C.
2013-01-01
Abort trajectories are optimized for human halo orbit missions about the translunar libration point (L2), with an emphasis on the use of free return trajectories. Optimal transfers from outbound free returns to L2 halo orbits are numerically optimized in the four-body ephemeris model. Circumlunar free returns are used for direct transfers, and cislunar free returns are used in combination with lunar gravity assists to reduce propulsive requirements. Trends in orbit insertion cost and flight time are documented across the southern L2 halo family as a function of halo orbit position and free return flight time. It is determined that the maximum amplitude southern halo incurs the lowest orbit insertion cost for direct transfers but the maximum cost for lunar gravity assist transfers. The minimum amplitude halo is the most expensive destination for direct transfers but the least expensive for lunar gravity assist transfers. The on-orbit abort costs for three halos are computed as a function of abort time and return time. Finally, an architecture analysis is performed to determine launch and on-orbit vehicle requirements for halo orbit missions.
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Stability of the wobbling motion in the triaxially deformed odd-A nucleus
NASA Astrophysics Data System (ADS)
Tanabe, Kosai; Sugawara-Tanabe, Kazuko
2017-12-01
In order to analyze the content of the exact solutions for particle-rotor models with both the rigid and the hydrodynamical moments of inertia (MoI), as a theoretical probe we apply the Holstein-Primakoff (HP) boson expansion method to the total angular momentum I and the single-particle angular momentum j. We study the competition between Coriolis force and the single-particle potential by employing the different choices of the diagonal HP boson representations for the components of I and j along a common coordinate axis, and along perpendicular axes. We do not find any wobbling level sequence associated with the rotation around the principal axis with the medium MoI. The staggering in the alignments of I about the axis with the medium MoI is found in the limited range of I, while the vector R(=I-j) is confined about the axis with the largest MoI.
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Earth recovery mode analysis for a Martian sample return mission
NASA Technical Reports Server (NTRS)
Green, J. P.
1978-01-01
The analysis has concerned itself with evaluating alternative methods of recovering a sample module from a trans-earth trajectory originating in the vicinity of Mars. The major modes evaluated are: (1) direct atmospheric entry from trans-earth trajectory; (2) earth orbit insertion by retropropulsion; and (3) atmospheric braking to a capture orbit. In addition, the question of guided vs. unguided entry vehicles was considered, as well as alternative methods of recovery after orbit insertion for modes (2) and (3). A summary of results and conclusions is presented. Analytical results for aerodynamic and propulsive maneuvering vehicles are discussed. System performance requirements and alternatives for inertial systems implementation are also discussed. Orbital recovery operations and further studies required to resolve the recovery mode issue are described.
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JunoCam: Approach and Orbit 1 Imaging
NASA Astrophysics Data System (ADS)
Ravine, M. A.; Caplinger, M. A.; Hansen, C. J.; Ingersoll, A. P.; Bolton, S. J.
2016-10-01
Juno went into orbit around Jupiter on 4 July 2016. Junocam took images of Jupiter and its satellites in the weeks before Jupiter Orbit Insertion (JOI) and the weeks after. Much higher resolution data will be acquired in late August 2016.
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NASA Technical Reports Server (NTRS)
Maddock, Robert W.; Bowes, Angela; Powell, Richard W.; Prince, Jill L. H.; Cianciolo, Alicia Dwyer
2012-01-01
When entering orbit about a planet or moon with an appreciable atmosphere, instead of using only the propulsion system to insert the spacecraft into its desired orbit, aerodynamic drag can be used after the initial orbit insertion to further decelerate the spacecraft. Several past NASA missions have used this aerobraking technique to reduce the fuel required to deliver a spacecraft into a desired orbit. Aerobraking was first demonstrated at Venus with Magellan in 1993 and then was used to achieve the science orbit of three Mars orbiters: Mars Global Surveyor in 1997, Mars Odyssey in 2001, and Mars Reconnaissance Orbiter in 2006. Although aerobraking itself reduces the propellant required to reach a final low period orbit, it does so at the expense of additional mission time to accommodate the aerobraking operations phase (typically 3-6 months), a large mission operations staff, and significant Deep Space Network (DSN) coverage. By automating ground based tasks and analyses associated with aerobraking and moving these onboard the spacecraft, a flight project could save millions of dollars in operations staffing and DSN costs (Ref. 1).
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NASA Technical Reports Server (NTRS)
Genova, Anthony L.; Loucks, Michael; Carrico, John
2014-01-01
The purpose of this extended abstract is to present results from a failed lunar-orbit insertion (LOI) maneuver contingency analysis for the Lunar Atmosphere Dust Environment Explorer (LADEE) mission, managed and operated by NASA Ames Research Center in Moffett Field, CA. The LADEE spacecrafts nominal trajectory implemented multiple sub-lunar phasing orbits centered at Earth before eventually reaching the Moon (Fig. 1) where a critical LOI maneuver was to be performed [1,2,3]. If this LOI was missed, the LADEE spacecraft would be on an Earth-escape trajectory, bound for heliocentric space. Although a partial mission recovery is possible from a heliocentric orbit (to be discussed in the full paper), it was found that an escape-prevention maneuver could be performed several days after a hypothetical LOI-miss, allowing a return to the desired science orbit around the Moon without leaving the Earths sphere-of-influence (SOI).
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Federal Register 2010, 2011, 2012, 2013, 2014
2012-07-02
... the MOI in parallel with the U.S.-Singapore Free Trade Agreement. In Section 3 of the MOI, the... for comments and suggestions, and is not a request for applications. No granting of money is directly...
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The power to detect linkage in complex disease by means of simple LOD-score analyses.
Greenberg, D A; Abreu, P; Hodge, S E
1998-01-01
Maximum-likelihood analysis (via LOD score) provides the most powerful method for finding linkage when the mode of inheritance (MOI) is known. However, because one must assume an MOI, the application of LOD-score analysis to complex disease has been questioned. Although it is known that one can legitimately maximize the maximum LOD score with respect to genetic parameters, this approach raises three concerns: (1) multiple testing, (2) effect on power to detect linkage, and (3) adequacy of the approximate MOI for the true MOI. We evaluated the power of LOD scores to detect linkage when the true MOI was complex but a LOD score analysis assumed simple models. We simulated data from 14 different genetic models, including dominant and recessive at high (80%) and low (20%) penetrances, intermediate models, and several additive two-locus models. We calculated LOD scores by assuming two simple models, dominant and recessive, each with 50% penetrance, then took the higher of the two LOD scores as the raw test statistic and corrected for multiple tests. We call this test statistic "MMLS-C." We found that the ELODs for MMLS-C are >=80% of the ELOD under the true model when the ELOD for the true model is >=3. Similarly, the power to reach a given LOD score was usually >=80% that of the true model, when the power under the true model was >=60%. These results underscore that a critical factor in LOD-score analysis is the MOI at the linked locus, not that of the disease or trait per se. Thus, a limited set of simple genetic models in LOD-score analysis can work well in testing for linkage. PMID:9718328
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The power to detect linkage in complex disease by means of simple LOD-score analyses.
Greenberg, D A; Abreu, P; Hodge, S E
1998-09-01
Maximum-likelihood analysis (via LOD score) provides the most powerful method for finding linkage when the mode of inheritance (MOI) is known. However, because one must assume an MOI, the application of LOD-score analysis to complex disease has been questioned. Although it is known that one can legitimately maximize the maximum LOD score with respect to genetic parameters, this approach raises three concerns: (1) multiple testing, (2) effect on power to detect linkage, and (3) adequacy of the approximate MOI for the true MOI. We evaluated the power of LOD scores to detect linkage when the true MOI was complex but a LOD score analysis assumed simple models. We simulated data from 14 different genetic models, including dominant and recessive at high (80%) and low (20%) penetrances, intermediate models, and several additive two-locus models. We calculated LOD scores by assuming two simple models, dominant and recessive, each with 50% penetrance, then took the higher of the two LOD scores as the raw test statistic and corrected for multiple tests. We call this test statistic "MMLS-C." We found that the ELODs for MMLS-C are >=80% of the ELOD under the true model when the ELOD for the true model is >=3. Similarly, the power to reach a given LOD score was usually >=80% that of the true model, when the power under the true model was >=60%. These results underscore that a critical factor in LOD-score analysis is the MOI at the linked locus, not that of the disease or trait per se. Thus, a limited set of simple genetic models in LOD-score analysis can work well in testing for linkage.
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Tuersunjiang, Nuermaimaiti; Odhiambo, John F.; Long, Nathan M.; Shasa, Desiree R.; Nathanielsz, Peter W.
2013-01-01
Obesity at conception and excess gestational weight gain pose significant risks for adverse health consequences in human offspring. This study evaluated the effects of reducing dietary intake of obese/overfed ewes beginning in early gestation on fetal development. Sixty days prior to conception, ewes were assigned to a control diet [CON: 100% of National Research Council (NRC) recommendations], a diet inducing maternal obesity (MO: 150% of NRC recommendations), or a maternal obesity intervention diet (MOI: 150% of NRC recommendations to day 28 of gestation, then 100% NRC) until necropsy at midgestation (day 75) or late (day 135) gestation. Fetal size and weight, as well as fetal organ weights, were greater (P < 0.05) at midgestation in MO ewes than those of CON and MOI ewes. By late gestation, whereas fetal size and weight did not differ among dietary groups, cardiac ventricular weights and wall thicknesses as well as liver and perirenal fat weights remained elevated in fetuses from MO ewes compared with those from CON and MOI ewes. MO ewes and fetuses exhibited elevated (P < 0.05) plasma concentrations of triglycerides, cholesterol, insulin, glucose, and cortisol at midgestation compared with CON and MOI ewes and fetuses. In late gestation, whereas plasma triglycerides and cholesterol, insulin, and cortisol remained elevated in MO vs. CON and MOI ewes and fetuses, glucose concentrations were elevated in both MO and MOI fetuses compared with CON fetuses, which was associated with elevated placental GLUT3 expression in both groups. These data are consistent with the concept that reducing maternal diet of obese/overfed ewes to requirements from early gestation can prevent subsequent alterations in fetal growth, adiposity, and glucose/insulin dynamics. PMID:23921140
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Tuersunjiang, Nuermaimaiti; Odhiambo, John F; Long, Nathan M; Shasa, Desiree R; Nathanielsz, Peter W; Ford, Stephen P
2013-10-01
Obesity at conception and excess gestational weight gain pose significant risks for adverse health consequences in human offspring. This study evaluated the effects of reducing dietary intake of obese/overfed ewes beginning in early gestation on fetal development. Sixty days prior to conception, ewes were assigned to a control diet [CON: 100% of National Research Council (NRC) recommendations], a diet inducing maternal obesity (MO: 150% of NRC recommendations), or a maternal obesity intervention diet (MOI: 150% of NRC recommendations to day 28 of gestation, then 100% NRC) until necropsy at midgestation (day 75) or late (day 135) gestation. Fetal size and weight, as well as fetal organ weights, were greater (P < 0.05) at midgestation in MO ewes than those of CON and MOI ewes. By late gestation, whereas fetal size and weight did not differ among dietary groups, cardiac ventricular weights and wall thicknesses as well as liver and perirenal fat weights remained elevated in fetuses from MO ewes compared with those from CON and MOI ewes. MO ewes and fetuses exhibited elevated (P < 0.05) plasma concentrations of triglycerides, cholesterol, insulin, glucose, and cortisol at midgestation compared with CON and MOI ewes and fetuses. In late gestation, whereas plasma triglycerides and cholesterol, insulin, and cortisol remained elevated in MO vs. CON and MOI ewes and fetuses, glucose concentrations were elevated in both MO and MOI fetuses compared with CON fetuses, which was associated with elevated placental GLUT3 expression in both groups. These data are consistent with the concept that reducing maternal diet of obese/overfed ewes to requirements from early gestation can prevent subsequent alterations in fetal growth, adiposity, and glucose/insulin dynamics.
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NASA Technical Reports Server (NTRS)
1976-01-01
Various phases of planetary operations related to the Viking mission to Mars are described. Topics discussed include: approach phase, Mars orbit insertion, prelanding orbital activities, separation, descent and landing, surface operations, surface sampling and operations starting, orbiter science and radio science, Viking 2, Deep Space Network and data handling.
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Design of the Recovery Trajectory for JAXA Venus Orbiter Akatsuki
NASA Astrophysics Data System (ADS)
Campagnola, Stefano; Kawakatsu, Yasuhiro
2015-12-01
Akatsuki ("dawn" in Japanese) is the JAXA Venus orbiter that was scheduled to enter orbit around Venus on Dec. 7 th , 2010. Following the failure of the main engine during the orbit insertion maneuver, the spacecraft escaped Venus on a 200-day orbit around the Sun, only to return in early 2017. This paper presents the design and implementation of the recovery trajectory, which involves perihelion maneuvers to re-encounter Venus in late 2015. Relying only on the onboard propellant, the trajectory rescued the mission by (1) anticipating the beginning of the science phase within the nominal lifetime of the spacecraft, and (2) halving the Δ v requirements for the orbit insertion maneuver. Several trajectories are designed with an innovative use of a technique called non-tangent V-Infinity Leveraging Transfers (VILTs). Candidate solutions are then recomputed in higher fidelity models, and one solution is finally selected for its low Δv requirements and for programmatic reasons. The results of the perihelion maneuver campaign are also presented.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, the left-hand Orbital Maneuvering System (OMS) pod is lowered toward the orbiter Discovery for installation. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, the left-hand Orbital Maneuvering System (OMS) pod is maneuvered toward the engine interfaces on the orbiter Discovery for installation. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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Burn Delay Analysis of the Lunar Orbit Insertion for Korea Pathfinder Lunar Orbiter
NASA Astrophysics Data System (ADS)
Bae, Jonghee; Song, Young-Joo; Kim, Young-Rok; Kim, Bangyeop
2017-12-01
The first Korea lunar orbiter, Korea Pathfinder Lunar Orbiter (KPLO), has been in development since 2016. After launch, the KPLO will execute several maneuvers to enter into the lunar mission orbit, and will then perform lunar science missions for one year. Among these maneuvers, the lunar orbit insertion (LOI) is the most critical maneuver because the KPLO will experience an extreme velocity change in the presence of the Moon’s gravitational pull. However, the lunar orbiter may have a delayed LOI burn during operation due to hardware limitations and telemetry delays. This delayed burn could occur in different captured lunar orbits; in the worst case, the KPLO could fly away from the Moon. Therefore, in this study, the burn delay for the first LOI maneuver is analyzed to successfully enter the desired lunar orbit. Numerical simulations are performed to evaluate the difference between the desired and delayed lunar orbits due to a burn delay in the LOI maneuver. Based on this analysis, critical factors in the LOI maneuver, the periselene altitude and orbit period, are significantly changed and an additional delta-V in the second LOI maneuver is required as the delay burn interval increases to 10 min from the planned maneuver epoch.
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NASA Technical Reports Server (NTRS)
1973-01-01
Parametric studies and subsystem comparisons for the orbital radar mapping mission to planet Venus are presented. Launch vehicle requirements and primary orbiter propulsion system requirements are evaluated. The systems parametric analysis indicated that orbit size and orientation interrelated with almost all of the principal spacecraft systems and influenced significantly the definition of orbit insertion propulsion requirements, weight in orbit capability, radar system design, and mapping strategy.
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Shuttle on-orbit rendezvous targeting: Circular orbits
NASA Technical Reports Server (NTRS)
Bentley, E. L.
1972-01-01
The strategy and logic used in a space shuttle on-orbit rendezvous targeting program are described. The program generates ascent targeting conditions for boost to insertion into an intermediate parking orbit, and generates on-orbit targeting and timeline bases for each maneuver to effect rendezvous with a space station. Time of launch is determined so as to eliminate any plane change, and all work was performed for a near-circular space station orbit.
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Federal Register 2010, 2011, 2012, 2013, 2014
2013-09-17
... NanoRacks, LLC, and NanoRacks locker insert and student experiments created under NASA's Student..., and mathematics education initiative.\\2\\ According to its Space Act Agreement with NASA,\\3\\ NanoRacks... opportunities to NanoRacks for the launch of its insert and the experiments the insert carries. Orbital provided...
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"Doi Moi" (Renovation) and Higher Education Reform in Vietnam
ERIC Educational Resources Information Center
Thanh, Pham Thi Hong
2011-01-01
Vietnam has experienced significant social, economic, political, and educational changes during the last two decades since the "Doi Moi" policy was implemented. To respond to new requirements required by the global economy, Vietnamese education has undergone remarkable reforms. This article critically examines these reforms in three…
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Kinetics of Cell Fusion Induced by a Syncytia-Producing Mutant of Herpes Simplex Virus Type I
Person, Stanley; Knowles, Robert W.; Read, G. Sullivan; Warner, Susan C.; Bond, Vincent C.
1976-01-01
We have isolated a number of plaque-morphology mutants from a strain of herpes simplex virus type I which, unlike the wild type, cause extensive cell fusion during a productive viral infection. After the onset of fusion, there is an exponential decrease in the number of single cells as a function of time after infection. At a multiplicity of infection (MOI) of 3.8 plaque-forming units per cell, fusion begins 5.3 h after infection with the number of single cells decreasing to 10% of the original number 10.2 h after infection. As the MOI is gradually increased from 0.4 to 8, the onset of fusion occurs earlier during infection. However, when the MOI is increased from 8 to 86, the onset of fusion does not occur any earlier. The rate of fusion is independent of the MOI for an MOI greater than 1. The rate of fusion varies linearly with initial cell density up to 3.5 × 104 cells/cm2 and is independent of initial cell density at higher cell concentrations. To assay cell fusion we have developed a simple quantitative assay using a Coulter counter to measure the number of single cells as a function of time after infection. Data obtained using a Coulter counter are similar to those obtained with a microscope assay. PMID:173881
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agr-Dependent Interactions of Staphylococcus aureus USA300 with Human Polymorphonuclear Neutrophils
Pang, Yun Yun; Schwartz, Jamie; Thoendel, Matthew; Ackermann, Laynez W.; Horswill, Alexander R.; Nauseef, William M.
2010-01-01
The emergence of serious infections due to community-associated methicillin-resistant Staphylococcus aureus (CA-MRSA) has fueled interest in the contributions of specific staphylococcal virulence factors to clinical disease. To assess the contributions of agr-dependent factors to the fate of organisms in polymorphonuclear neutrophils (PMN), we examined the consequences for organism and host cells of feeding PMN with wild-type CA-MRSA (LAC) or CA-MRSA (LAC agr KO) at different multiplicities of infection (MOIs). Phagocytosed organisms rapidly increased the transcription of RNAIII in a time- and MOI-dependent fashion; extracellular USA300 (LAC) did not increase RNAIII expression despite having the capacity to respond to autoinducing peptide-enriched culture medium. HOCl-mediated damage and intracellular survival were the same in the wild-type and USA300 (LAC agr KO). PMN lysis by ingested USA300 (LAC) was time- and MOI-dependent and, at MOIs >1, required α-hemolysin (hla) as USA300 (LAC agr KO) and USA300 (LAC hla KO) promoted PMN lysis only at high MOIs. Taken together, these data demonstrate activation of the agr operon in human PMN with the subsequent production of α-hemolysin and PMN lysis. The extent to which these events in the phagosomes of human PMN contribute to the increased morbidity and mortality of infections with USA300 (LAC) merits further study. PMID:20829608
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NASA Technical Reports Server (NTRS)
Rosenstein, B. J.
1973-01-01
The Pioneer Venus orbiter and multiprobe missions require spacecraft maneuvers for successful accomplishment. This report presents the results of studies performed to define the propulsion subsystems required to perform those maneuvers. Primary goals were to define low mass subsystems capable of performing the required missions with a high degree of reliability for low cost. A review was performed of all applicable propellants and thruster types, as well as propellant management techniques. Based on this review, a liquid monopropellant hydrazine propulsion subsystem was selected for all multiprobe mission maneuvers, and for all orbiter mission maneuvers except orbit insertion. A pressure blowdown operating mode was selected using helium as the pressurizing gas. The forces associated with spacecraft rotations were used to control the liquid-gas interface and resulting propellant orientation within the tank.
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NASA Astrophysics Data System (ADS)
Song, Young-Joo; Bae, Jonghee; Kim, Young-Rok; Kim, Bang-Yeop
2016-12-01
In this study, the uncertainty requirements for orbit, attitude, and burn performance were estimated and analyzed for the execution of the 1st lunar orbit insertion (LOI) maneuver of the Korea Pathfinder Lunar Orbiter (KPLO) mission. During the early design phase of the system, associate analysis is an essential design factor as the 1st LOI maneuver is the largest burn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance achieved. For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival trajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such as varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the 1st LOI maneuver. The current analysis assumed an impulsive LOI maneuver, and two-body equations of motion were adapted to simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis to analyze diverse uncertainties that might arise at the moment when the maneuver is executed. As a result, three major requirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for the burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn performances were simultaneously estimated and analyzed to maintain the 1st elliptical orbit achieved around the moon within the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the target insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction (MCC) maneuver during the transfer. More detailed system requirements for the KPLO mission, particularly for the spacecraft bus itself and for the flight dynamics subsystem at the ground control center, are expected to be prepared and established based on the current results, including a contingency trajectory design plan.
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Crandell, Douglas W; Mazumder, Shivnath; Evans, P Andrew; Baik, Mu-Hyun
2015-12-01
Density functional theory calculations demonstrate that the reversal of regiochemical outcome of the addition for substituted methyl propiolates in the rhodium-catalyzed [(2 + 2) + 2] carbocyclization with PPh 3 and ( S )-xyl-binap as ligands is both electronically and sterically controlled. For example, the ester functionality polarizes the alkyne π* orbital to favor overlap of the methyl-substituted terminus of the alkyne with the p π -orbital of the alkenyl fragment of the rhodacycle during alkyne insertion with PPh 3 as the ligand. In contrast, the sterically demanding xyl-binap ligand cannot accommodate the analogous alkyne orientation, thereby forcing insertion to occur at the sterically preferred ester terminus, overriding the electronically preferred orientation for alkyne insertion.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, the left-hand Orbital Maneuvering System (OMS) pod (seen from the back) is lifted off its transporter. The OMS pod will be installed on the orbiter Discovery. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers stand by as the left-hand Orbital Maneuvering System (OMS) pod is maneuvered toward the engine interfaces on the orbiter Discovery for installation. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, the left-hand Orbital Maneuvering System (OMS) pod is lifted at an angle from the transporter below. The OMS pod will be installed on the orbiter Discovery. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, the left-hand Orbital Maneuvering System (OMS) pod (top of photo) is poised behind the engine interfaces on the orbiter Discovery for installation. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers on an upper level watch as the left-hand Orbital Maneuvering System (OMS) pod is lifted high to maneuver it toward the orbiter Discovery for installation. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers check the lifting of the left-hand Orbital Maneuvering System (OMS) pod. The OMS pod will be installed on the orbiter Discovery. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, the left-hand Orbital Maneuvering System (OMS) pod (seen from the front) is lifted off its transporter. The OMS pod will be installed on the orbiter Discovery. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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2004-04-21
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, a worker on an upper level watches as the left-hand Orbital Maneuvering System (OMS) pod is lifted high to maneuver it toward the orbiter Discovery for installation. The Orbital Maneuvering System provides the thrust for orbit insertion, orbit circularization, orbit transfer, rendezvous, deorbit, abort to orbit and abort once around. It can provide up to 1,000 pounds of propellant to the aft reaction control system. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers.
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FIRST BEAM TESTS OF THE APS MBA UPGRADE ORBIT FEEDBACK CONTROLLER
DOE Office of Scientific and Technical Information (OSTI.GOV)
Sereno, N. S.; Arnold, N.; Brill, A.
The new orbit feedback system required for the APS multi-bend acromat (MBA) ring must meet challenging beam stability requirements. The AC stability requirement is to correct rms beam motion to 10 % the rms beam size at the insertion device source points from 0.01 to 1000 Hz. The vertical plane represents the biggest challenge for AC stability which is required to be 400 nm rms for a 4 micron vertical beam size. In addition long term drift over a period of 7 days is required to be 1 micron or less at insertion de- vice BPMs and 2 microns formore » arc bpms. We present test re- sults of theMBA prototype orbit feedback controller (FBC) in the APS storage ring. In this test, four insertion device BPMs were configured to send data to the FBC for process- ing into four fast corrector setpoints. The configuration of four bpms and four fast correctors creates a 4-bump and the configuration of fast correctors is similar to what will be implemented in the MBA ring. We report on performance benefits of increasing the sampling rate by a factor of 15 to 22.6 kHz over the existing APS orbit feedback system, lim- itations due to existing storage ring hardware and extrapo- lation to theMBA orbit feedback design. FBC architecture, signal flow and processing design will also be discussed.« less
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Mars Geoscience Climatology Orbiter (MGCO) extended study: Technical volume
NASA Technical Reports Server (NTRS)
1983-01-01
The FLTSATCOM Earth orbiting communications satellite is a prominent candidate to serve as the Mars Geoscience Climatology Orbiter (MGCO) spacecraft. Major aspects directly applicable are: (1) the incorporation of solid orbit insertion motor; (2) the ability to cruise to Mars in the spin-stabilized mode; (3) ample capability for payload mass and power; (4) attitude control tried to nadir and orbit plane coordinates; (5) exemplary Earth orbital performance record and projected lifetime; and (6) existence of an on-going procurement into the MGCO time period.
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Maximizing Science Return: A Representative Trajectory for Dynamo
NASA Technical Reports Server (NTRS)
Lyons, Daniel T.
1999-01-01
This presentation discusses a possible Dynamo Orbit for a future Mars global surveyor. The goal of the proposed orbit is to allow for the greatest amount of mapping of the Martian surface during the mission. The presentation discusses the dynamic pressure, periapsis altitude, the Apoapsis Altitude, the aerodynamic heating rate,and the change in velocity during the aerobraking phase of the orbit and the orbital insertion.
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"Laisse-moi rire! Fais-moi parler!" ("Let Me Laugh! Make Me Speak!").
ERIC Educational Resources Information Center
Borgomano, Laure
1983-01-01
A discussion of the use of cartoons and humorous vignettes in French instruction is presented. It is suggested that there exists a wealth of such material but little guidance in using it. Problems of cultural context, understanding the use of pictures, and potential for classroom discussion are considered. (MSE)
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Articulation of Medium of Instruction Politics in the Malaysian Chinese Press
ERIC Educational Resources Information Center
Samuel, Moses; Khan, Mahmud Hasan; Ng, Lee Luan; Cheang, Kin Wai
2014-01-01
In postcolonial multilingual societies, matters of education are deeply rooted in the discourse of ethnicity. In Malaysia, the interface between ethnicity and education is reflected in recent debates on the choice of medium of instruction (MOI). In 2002, the Malaysian government introduced English as MOI by replacing Malay, the national language,…
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WETS - Azura Half Scale Testing MOIS Documentation
Nelson, Eric
2015-05-30
This submission includes documentation on the Modular Ocean Instrumentation System (MOIS) installation on the Azura 1/2 scale wave energy converter at the Marine Station Kaneohe Bay (MCBH). Data from the deployment will be uploaded over the course of the test. The instrumentation and data come from the NREL team participating in this testing.
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The Transformation of Higher Education in Vietnam after DoiMoi: A Story of "Dualism"
ERIC Educational Resources Information Center
Tran, Hien
2009-01-01
This research was undertaken to investigate the transformation of higher education reform in Vietnam since "DoiMoi," which involves examining its rationale and practical implementation. The reform reveals an interesting picture of Vietnam's higher education system, in which two development visions--a "market-led" vision and a…
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ERIC Educational Resources Information Center
Tollefson, James W.
2015-01-01
In some settings, medium of instruction (MOI) policies in multilingual education break out into public debates in mass media involving politicians, business leaders, government officials, parents, and school children. These public discussions of MOI often index struggles over the distribution of political power and economic resources, and issues…
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Seo, Jina; Seo, Dong Joo; Oh, Hyejin; Jeon, Su Been; Oh, Mi-Hwa; Choi, Changsun
2016-01-01
This study aimed to inhibit Escherichia coli (E. coli) O157:H7 artificially contaminated in fresh meat using bacteriophage. Among 14 bacteriophages, the highly lytic bacteriophage BPECO19 strain was selected to inhibit E. coli O157:H7 in artificially contaminated meat samples. Bacteriophage BPECO19 significantly reduced E. coli O157:H7 bacterial load in vitro in a multiplicity of infection (MOI)-dependent manner. E. coli O157:H7 was completely inhibited only in 10 min in vitro by the treatment of 10,000 MOI BPECO19. The treatment of BPECO19 at 100,000 MOI completely reduced 5 Log CFU/cm2 E. coli O157:H7 bacterial load in beef and pork at 4 and 8h, respectively. In chicken meat, a 4.65 log reduction of E. coli O157:H7 was observed at 4 h by 100,000 MOI. The treatment of single bacteriophage BPECO19 was an effective method to control E. coli O157:H7 in meat samples. PMID:27194926
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Were, Martin C; Siika, Abraham; Ayuo, Paul O; Atwoli, Lukoye; Esamai, Fabian
2015-01-01
Current approaches for capacity building in Health Informatics (HI) in developing countries mostly focus on training, and often rely on support from foreign entities. In this paper, we describe a comprehensive and multidimensional capacity-building framework by Lansang & Dennis, and its application for HI capacity building as implemented in a higher-education institution in Kenya. This framework incorporates training, learning-by-doing, partnerships, and centers of excellence. At Moi University (Kenya), the training dimensions include an accredited Masters in HI Program, PhD in HI, and HI short courses. Learning-by-doing occurs through work within MOH facilities at the AMPATH care and treatment program serving 3 million people. Moi University has formed strategic HI partnerships with Regenstrief Institute, Inc. (USA), University of Bergen (Norway), and Makerere University (Uganda), among others. The University has also created an Institute of Biomedical Informatics to serve as an HI Center of Excellence in the region. This Institute has divisions in Training, Research, Service and Administration. The HI capacity-building approach by Moi provides a model for adoption by other institutions in resource-limited settings.
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GRAIL TCM-5 Go/No-Go: Developing Lunar Orbit Insertion (LOI) Criteria
NASA Technical Reports Server (NTRS)
Chung, Min-Kun J.
2013-01-01
The Gravity Recovery and Interior Laboratory (GRAIL) mission successfully completed mapping the Moon's gravity field to an unprecedented level for a better understanding of the internal structure and thermal evolution of the Moon. The mission success was critically dependent on the success of the Lunar Orbit Insertion (LOI). In this paper we establish a set of LOI criteria to meet all the requirements and we use these criteria to establish Go/No-Go boundaries of the last, statistical Trajectory Correction Maneuvers (TCM-5s) for operations.
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Keller, M J; Wheeler, D G; Cooper, E; Meier, J L
2003-06-01
Prior studies have suggested a role of the five copies of the 19-bp-repeat cyclic AMP (cAMP)-response element (CRE) in major immediate-early (MIE) promoter activation, the rate-limiting step in human cytomegalovirus (HCMV) replication. We used two different HCMV genome modification strategies to test this hypothesis in acutely infected cells. We report the following: (i) the CREs do not govern basal levels of MIE promoter activity at a high or low multiplicity of infection (MOI) in human foreskin fibroblast (HFF)- or NTera2-derived neuronal cells; (ii) serum and virion components markedly increase MIE promoter-dependent transcription at a low multiplicity of infection (MOI), but this increase is not mediated by the CREs; (iii) forskolin stimulation of the cAMP signaling pathway induces a two- to threefold increase in MIE RNA levels in a CRE-specific manner at a low MOI in both HFF- and NTera2-derived neuronal cells; and (iv) the CREs do not regulate basal levels of HCMV DNA replication at a high or low MOI in HFF. Their presence does impart a forskolin-induced increase in viral DNA replication at a low MOI but only when basal levels of MIE promoter activity are experimentally diminished. In conclusion, the 19-bp-repeat CREs add to the robust MIE promoter activity that occurs in the acutely infected stimulated cells, although the CREs' greater role may be in other settings.
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Optimization of Insertion Cost for Transfer Trajectories to Libration Point Orbits
NASA Technical Reports Server (NTRS)
Howell, K. C.; Wilson, R. S.; Lo, M. W.
1999-01-01
The objective of this work is the development of efficient techniques to optimize the cost associated with transfer trajectories to libration point orbits in the Sun-Earth-Moon four body problem, that may include lunar gravity assists. Initially, dynamical systems theory is used to determine invariant manifolds associated with the desired libration point orbit. These manifolds are employed to produce an initial approximation to the transfer trajectory. Specific trajectory requirements such as, transfer injection constraints, inclusion of phasing loops, and targeting of a specified state on the manifold are then incorporated into the design of the transfer trajectory. A two level differential corrections process is used to produce a fully continuous trajectory that satisfies the design constraints, and includes appropriate lunar and solar gravitational models. Based on this methodology, and using the manifold structure from dynamical systems theory, a technique is presented to optimize the cost associated with insertion onto a specified libration point orbit.
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Optimum instantaneous impulsive orbital injection to attain a specified asymptotic velocity vector.
NASA Technical Reports Server (NTRS)
Bean, W. C.
1971-01-01
A nalysis of the necessary conditions of Battin for instantaneous orbital injection, with consideration of the uniqueness of his solution, and of the further problem which arises in the degenerate case when radius vector and asymptotic vector are separated by 180 deg. It is shown that when the angular separation between radius vector and asymptotic velocity vector satisfies theta not equal to 180 deg, there are precisely two insertion-velocity vectors which permit attainment of the target asymptotic velocity vector, one yielding posigrade, the other retrograde motion. When theta equals to 180 deg, there is a family of insertion-velocity vectors which permit attainment of a specified asymptotic velocity vector with a unique insertion-velocity vector for every arbitrary orientation of a target unit angular momentum vector.
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NASA Technical Reports Server (NTRS)
Turner, A. E.
1987-01-01
The potential for satellites in two orbits, the sun-synchronous 12-hour equatorial orbit (STET) and the apogee at constant time-of-day equatorial orbit (ACE), to off-load peaks in the CONUS geostationary communications traffic is discussed. These orbits are found to require maneuvers of smaller magnitudes for insertion than geostationary orbits. Advantages of the ACE orbit over the STET orbit are discussed, including larger satellite mass capability for a given launch vehicle, lower slant ranges, and larger angular separation from the geostationary arc for a nonequatorial ground observer.
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Ideology, Linguistic Capital and the Medium of Instruction in Hong Kong.
ERIC Educational Resources Information Center
Morrison, Keith; Lui, Icy
2000-01-01
Examines the links between linguistic capital, cultural capital, linguistic imperialism, and the use of English as the medium of instruction (MOI) in Hong Kong. Suggests that the notion of linguistic imperialism in Hong Kong is superceded by the notion of linguistic capital, although neither presents a complete analysis of the MOI issue in Hong…
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Processing Instruction and Meaning-Based Output Instruction: A Response to Keating and Farley (2008)
ERIC Educational Resources Information Center
VanPatten, Bill; Farmer, Jeffrey L.; Clardy, Caleb L.
2009-01-01
Research on Processing Instruction (PI) has yielded consistently positive results across a variety of measures. In addition, in comparison to other instructional interventions, PI tends to yield superior results. The one difference is comparative research with Meaning-based Output Instruction (MOI) in which in a number of studies, MOI is seen to…
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Medium of Instruction in Asia: Context, Processes and Outcomes
ERIC Educational Resources Information Center
Hamid, M. Obaidul; Nguyen, Hoa Thi Mai; Baldauf, Richard B., Jr.
2013-01-01
One major impact of globalisation on education is denoted by the growing trend to use English, the global language, as a medium of instruction (MOI) in emerging polities that are trying to enhance their English-speaking capacities. This article emphasises developing an understanding of MOI from a language policy and planning as well as an…
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The electronic and optical properties of CH3NH3MoI3 perovskite
NASA Astrophysics Data System (ADS)
Kansara, Shivam; Sonvane, Yogesh; Gupta, Sanjeev K.
2018-05-01
In this work, a first-principles theoretical study of hybrid perovskite CH3NH3MoI3 is performed using PBE exchange-correlation approximations in density functional theory. The results of electronic band structure are 0.90 eV (M-point: Direct) and 0.60 eV (R-X point: Indirect), respectively. We have also calculated the dielectric properties such as real, imaginary, extension coefficient (K) and reflectivity (R) properties of hybrid perovskite CH3NH3MoI3. The low-bandgap molecules are used to absorb near-IR range and typically having a bandgap smaller than 1.6 eV. This is particularly attractive in organic photovoltaics (OPV), photodetectors (PDs), and ambipolar field-effect transistors (FETs).
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NASA Technical Reports Server (NTRS)
Garn, Michelle; Qu, Min; Chrone, Jonathan; Su, Philip; Karlgaard, Chris
2008-01-01
Lunar orbit insertion LOI is a critical maneuver for any mission going to the Moon. Optimizing the geometry of this maneuver is crucial to the success of the architecture designed to return humans to the Moon. LOI burns necessary to meet current NASA Exploration Constellation architecture requirements for the lunar sortie missions are driven mainly by the requirement for global access and "anytime" return from the lunar surface. This paper begins by describing the Earth-Moon geometry which creates the worst case (delta)V for both the LOI and the translunar injection (TLI) maneuvers over the full metonic cycle. The trajectory which optimizes the overall (delta)V performance of the mission is identified, trade studies results covering the entire lunar globe are mapped onto the contour plots, and the effects of loitering in low lunar orbit as a means of reducing the insertion (delta)V are described. Finally, the lighting conditions on the lunar surface are combined with the LOI and TLI analyses to identify geometries with ideal lighting conditions at sites of interest which minimize the mission (delta)V.
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Lin, Qiang; Fu, Xiaozhe; Li, Ningqiu; Wan, Quanyuan; Chen, Wenjie; Huang, Yunmao; Huang, Zhibin; Li, Jun; Zhao, Lijuan; Lin, Li
2017-10-01
In spite of the quite common co-infections of viruses in the cultured fish, most of the previous studies have just simply focused on the infection of a single pathogen. In this report, we observed that about 13% of cultured Chinese perch have been co-infected by infectious spleen and kidney necrosis virus (ISKNV) and Siniperca chuatsi rhabdovirus (SCRV). Furthermore, Chinese perch could co-infected by ISKNV and SCRV by intraperitoneally injection with the two viruses. Interestingly, we revealed that the two viruses could even co-infect a single cell of Chinese perch in vivo and a single Chinese perch brain cells (CPB) cell in vitro. The dynamic co-infected viruses loads in the different tissues of Chinese perch showed dependent. When CPB cells were infected with the same 10 MOI of SCRV and ISKNV, the replication of SCRV overwhelmed the replication of ISKNV. When the MOI of ISKNV (10 MOI) was 10,000 times of MOI of SCRV (0.001 MOI), the dynamic virus loads of the two viruses in CPB cells indicated that co-infections could synergistically stimulate both viruses replication at the late time points but not at early time points. The co-infections of ISKNV and SCRV in the cultured Chinese perch will shed a new light on the prevention of the viral diseases of Chinese perch. The development of multivalent vaccine which could be effective for preventing against the co-infections of the viruses is highly needed. Copyright © 2017 Elsevier Ltd. All rights reserved.
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Toward an Online Master of Public Health Degree in Kenya: Moi University's Path
ERIC Educational Resources Information Center
Koskei, Peter; Ruto-Korir, Rose; Carrier, Carol; Sales, Gregory
2018-01-01
As higher education institutions around the world strive to ensure they remain relevant by meeting the needs of today's digitally-focused students, the number of online courses and degree programs is increasing dramatically. Not surprisingly, given this trend, in recent years the School of Public Health at Moi University, in Eldoret, Kenya, has…
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ERIC Educational Resources Information Center
Kemboi, Rebecca J. Kimongo; Kindiki, Nyaga; Misigo, Benard
2016-01-01
This study investigated the relationship between personality types and career choices of undergraduate students of Moi University. In Kenya, students are allowed to revise their career choices at various levels of education before they settle on one course of study in the University. The process of choosing careers begins in form three where…
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Phage therapy dosing: The problem(s) with multiplicity of infection (MOI).
Abedon, Stephen T
2016-01-01
The concept of bacteriophage multiplicity of infection (MOI) - ratios of phages to bacteria - historically has been less easily applied than many phage workers would prefer or, perhaps, may be aware. Here, toward clarification of the concept, I discuss multiplicity of infection in terms of semantics, history, mathematics, pharmacology, and actual practice. For phage therapy and other biocontrol purposes it is desirable, especially, not to solely employ MOI to describe what phage quantities have been applied during dosing. Why? Bacterial densities can change between bacterial challenge and phage application, may not be easily determined immediately prior to phage dosing, and/or target bacterial populations may not be homogeneous with regard to phage access and thereby inconsistent in terms of what MOI individual bacteria experience. Toward experiment reproducibility and as practiced generally for antibacterial application, phage dosing instead should be described in terms of concentrations of formulations (phage titers) as well as volumes applied and, in many cases, absolute numbers of phages delivered. Such an approach typically will be far more desirable from a pharmacological perspective than solely indicating ratios of agents to bacteria. This essay was adapted, with permission, from an appendix of the 2011 monograph, Bacteriophages and Biofilms , Nova Science Publishers.
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Limiting opportunities for cheating stabilizes virulence in insect parasitic nematodes.
Shapiro-Ilan, David; Raymond, Ben
2016-03-01
Cooperative secretion of virulence factors by pathogens can lead to social conflict when cheating mutants exploit collective secretion, but do not contribute to it. If cheats outcompete cooperators within hosts, this can cause loss of virulence. Insect parasitic nematodes are important biocontrol tools that secrete a range of significant virulence factors. Critically, effective nematodes are hard to maintain without live passage, which can lead to virulence attenuation. Using experimental evolution, we tested whether social cheating might explain unstable virulence in the nematode Heterorhabditis floridensis by manipulating relatedness via multiplicity of infection (MOI), and the scale of competition. Passage at high MOI, which should reduce relatedness, led to loss of fitness: virulence and reproductive rate declined together and all eight independent lines suffered premature extinction. As theory predicts, relatedness treatments had more impact under stronger global competition. In contrast, low MOI passage led to more stable virulence and increased reproduction. Moreover, low MOI lineages showed a trade-off between virulence and reproduction, particularly for lines under stronger between-host competition. Overall, this study indicates that evolution of virulence theory is valuable for the culture of biocontrol agents: effective nematodes can be improved and maintained if passage methods mitigate possible social conflicts.
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[Virtual Planning of Prosthetic Treatment of the Orbit].
Veit, Johannes A; Thierauf, Julia; Egner, Kornelius; Wiggenhauser, Paul Severin; Friedrich, Daniel; Greve, Jens; Schuler, Patrick J; Hoffmann, Thomas K; Schramm, Alexander
2017-06-01
Optimal positioning of bone-anchored implants in the treatment of patients with orbital prosthesis is challenging. The definition of implant axis as well as the positioning of the implants is important to prevent failures in prosthetic rehabilitation in these patients. We performed virtual planning of enossal implants at a base of a standard fan beam CT scan using the software CoDiagnostiX™ (DentalWings, Montréal, Canada). By 3D-printing a surgical guide for drilling and implant insertion was manufactured (Med-610™, Stratasys, Rehovot, Israel). An orbital exenteration was performed in a patient after shrinkage of the eyelids 20 years after enucleation and radiation of the orbit due to rhabdomyosarcoma. 4 Vistafix-3 implants (Cochlear™, Cochlea, Centennial, USA) were primarily inserted after resection with the help of the 3D-surgical guide. Prosthetic rehabilitation could be achieved as preplanned to a predictable result. The individual prosthesis of the orbit showed good functional and esthetic outcome. The virtual 3D-planning of endosseous implants for prosthetic orbital and periorbital reconstruction is easy to use and facilitates optimal placement of implants especially in posttherapeutically altered anatomic situations. © Georg Thieme Verlag KG Stuttgart · New York.
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Cardiomyopathie du péripartum: à propos d’une observation et revue de la littérature
Bouzerda, Abdelmajid
2016-01-01
La cardiomyopathie du péripartum ou cardiomyopathie gravidique primitive, est une entité rare et méconnue définie comme une insuffisance cardiaque systolique survenant le dernier mois de la grossesse ou les cinq premiers mois du postpartum en l'absence d'étiologie connue ou de cardiopathie préexistante. Nous rapportons l'observation d'une jeune patiente de 31 ans sans antécédents pathologiques particuliers admise pour une poussée d'insuffisance cardiaque gauche 1mois après son accouchement. Le contexte de péripartum nous a fait penser au diagnostic et a motivé la réalisation d'une Echocardiographie qui a confirmé cette entité. PMID:28154713
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NASA Technical Reports Server (NTRS)
Byrnes, D. V.; Carney, P. C.; Underwood, J. W.; Vogt, E. D.
1974-01-01
Development, test, conversion, and documentation of computer software for the mission analysis of missions to halo orbits about libration points in the earth-sun system is reported. The software consisting of two programs called NOMNAL and ERRAN is part of the Space Trajectories Error Analysis Programs (STEAP). The program NOMNAL targets a transfer trajectory from Earth on a given launch date to a specified halo orbit on a required arrival date. Either impulsive or finite thrust insertion maneuvers into halo orbit are permitted by the program. The transfer trajectory is consistent with a realistic launch profile input by the user. The second program ERRAN conducts error analyses of the targeted transfer trajectory. Measurements including range, doppler, star-planet angles, and apparent planet diameter are processed in a Kalman-Schmidt filter to determine the trajectory knowledge uncertainty. Execution errors at injection, midcourse correction and orbit insertion maneuvers are analyzed along with the navigation uncertainty to determine trajectory control uncertainties and fuel-sizing requirements. The program is also capable of generalized covariance analyses.
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Galileo Jupiter approach orbit determination
NASA Technical Reports Server (NTRS)
Miller, J. K.; Nicholson, F. T.
1984-01-01
Orbit determination characteristics of the Jupiter approach phase of the Galileo mission are described. Predicted orbit determination performance is given for the various mission events that occur during Jupiter approach. These mission events include delivery of an atmospheric entry probe, acquisition of probe science data by the Galileo orbiter for relay to earth, delivery of an orbiter to a close encounter of the Galilean satellite Io, and insertion of the orbiter into orbit about Jupiter. The orbit determination strategy and resulting accuracies are discussed for the data types which include Doppler, range, optical imaging of Io, and a new Very Long Baseline Interferometry (VLBI) data type called Differential One-Way Range (DOR).
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Goh, B T; Teoh, K H
2015-05-01
Surgical implant placement in the orbital region for the support of a prosthesis is challenging due to the thin orbital rim and proximity to vital structures. This article reports the use of a computer-aided design and manufacturing (CAD/CAM) stereolithographic surgical template protocol for orbital implant placement in four patients, who were followed-up for about 7 years. A total of 11 orbital implants were inserted, eight of these in irradiated bone. No intraoperative complications were noted in any of the patients and the implants were all inserted in the planned positions. The survival rate of implants placed in irradiated bone that received hyperbaric oxygen therapy was 62.5% (5/8). One implant failed in a burns injury patient at 74 months after functional loading. The overall survival of implants in the orbital region and the cumulative survival at 7 years was 63.6%. With regard to skin reactions around the abutments, 85% were grade 0, 13% were grade 1, and 2% were grade 2 according to the Holgers classification. The mean survival time of the first prosthesis was 49 months. High patient satisfaction was achieved with the implant-retained orbital prostheses. Copyright © 2014 International Association of Oral and Maxillofacial Surgeons. Published by Elsevier Ltd. All rights reserved.
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ERIC Educational Resources Information Center
Taylor-Leech, Kerry
2013-01-01
Timor-Leste offers a rich case study of the array of discursive influences on medium-of-instruction (MOI) policy in multilingual, post-colonial developing contexts. MOI policy in this young nation is a site of tension between struggles to define national identity in the shadow of colonial language ideologies and the globalised discourses of…
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NREL MOIS Data for NWEI Azura September 2016
Eric Nelson
2016-10-07
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navys Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura June 2016
Eric Nelson
2016-06-30
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navys Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura July 2016
Eric Nelson
2016-09-25
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navys Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura August 2016
Eric Nelson
2016-10-03
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navys Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura November 2015
Eric Nelson
2016-05-25
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura August 2015
Eric Nelson
2016-05-23
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura July 2015
Eric Nelson
2016-05-23
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura April 2016
Eric Nelson
2016-05-31
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura June 2015
Eric Nelson
2016-05-18
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura March 2016
Eric Nelson
2016-05-31
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura December 2015
Eric Nelson
2016-05-27
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura January 2016
Eric Nelson
2016-05-27
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura February 2016
Eric Nelson
2016-05-31
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura September 2015
Eric Nelson
2016-05-24
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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NREL MOIS Data for NWEI Azura October 2015
Eric Nelson
2016-05-24
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below).
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ERIC Educational Resources Information Center
Jones, Jennifer M.
2014-01-01
This paper investigates the perceptions of teachers from one Sabaot dominated primary school in western Kenya regarding the medium of instruction (MoI) policy in different class levels. While their "ideal" MoI policy bears some resemblance to the official policy which advocates mother tongue (MT) as medium in lower primary and English in…
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Singh, Balraj; Kinne, Hannah E.; Milligan, Ryan D.; Washburn, Laura J.; Olsen, Mark; Lucci, Anthony
2016-01-01
We have previously shown that only 0.01% cells survive a metabolic challenge involving lack of glutamine in culture medium of SUM149 triple-negative Inflammatory Breast Cancer cell line. These cells, designated as SUM149-MA for metabolic adaptability, are resistant to chemotherapeutic drugs, and they efficiently metastasize to multiple organs in nude mice. We hypothesized that obesity-related molecular networks, which normally help in cellular and organismal survival under metabolic challenges, may help in the survival of MA cells. The fat mass and obesity-associated protein FTO is overexpressed in MA cells. Obesity-associated cis-acting elements in non-coding region of FTO regulate the expression of IRX3 gene, thus activating obesity networks. Here we found that IRX3 protein is significantly overexpressed in MA cells (5 to 6-fold) as compared to the parental SUM149 cell line, supporting our hypothesis. We also obtained evidence that additional key regulators of energy balance such as ARID5B, IRX5, and CUX1 P200 repressor could potentially help progenitor-like TNBC cells survive in glutamine-free medium. MO-I-500, a pharmacological inhibitor of FTO, significantly (>90%) inhibited survival and/or colony formation of SUM149-MA cells as compared to untreated cells or those treated with a control compound MO-I-100. Curiously, MO-I-500 treatment also led to decreased levels of FTO and IRX3 proteins in the SUM149 cells initially surviving in glutamine-free medium as compared to MO-I-100 treatment. Interestingly, MO-I-500 treatment had a relatively little effect on cell growth of either the SUM149 or SUM149-MA cell line when added to a complete medium containing glutamine that does not pose a metabolic challenge. Importantly, once selected and cultured in glutamine-free medium, SUM149-MA cells were no longer affected by MO-I-500 even in Gln-free medium. We conclude that panresistant MA cells contain interconnected molecular networks that govern developmental status and energy balance, and genetic and epigenetic alterations that are selected during cancer evolution. PMID:27390851
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Contingency Trajectory Design for a Lunar Orbit Insertion Maneuver Failure by the LADEE Spacecraft
NASA Technical Reports Server (NTRS)
Genova, A. L.
2014-01-01
This paper presents results from a contingency trajectory analysis performed for the Lunar Atmosphere & Dust Environment Explorer (LADEE) mission in the event of a missed lunar-orbit insertion (LOI) maneuver by the LADEE spacecraft. The effects of varying solar perturbations in the vicinity of the weak stability boundary (WSB) in the Sun-Earth system on the trajectory design are analyzed and discussed. It is shown that geocentric recovery trajectory options existed for the LADEE spacecraft, depending on the spacecraft's recovery time to perform an Earth escape-prevention maneuver after the hypothetical LOI maneuver failure and subsequent path traveled through the Sun-Earth WSB. If Earth-escape occurred, a heliocentric recovery option existed, but with reduced science capacapability for the spacecraft in an eccentric, not circular near-equatorial retrograde lunar orbit.
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Mission Advantages of Constant Power, Variable Isp Electrostatic Thrusters
NASA Technical Reports Server (NTRS)
Oleson, Steven R.
2000-01-01
Electric propulsion has moved from station-keeping capability for spacecraft to primary propulsion with the advent of both the Deep Space One asteroid flyby and geosynchronous spacecraft orbit insertion. In both cases notably more payload was delivered than would have been possible with chemical propulsion. To provide even greater improvements electrostatic thruster performance could be varied in specific impulse, but kept at constant power to provide better payload or trip time performance for different mission phases. Such variable specific impulse mission applications include geosynchronous and low earth orbit spacecraft stationkeeping and orbit insertion, geosynchronous reusable tug missions, and interplanetary probes. The application of variable specific impulse devices is shown to add from 5 to 15% payload for these missions. The challenges to building such devices include variable voltage power supplies and extending fuel throughput capabilities across the specific impulse range.
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On-orbit flight control algorithm description
NASA Technical Reports Server (NTRS)
1975-01-01
Algorithms are presented for rotational and translational control of the space shuttle orbiter in the orbital mission phases, which are external tank separation, orbit insertion, on-orbit and de-orbit. The program provides a versatile control system structure while maintaining uniform communications with other programs, sensors, and control effectors by using an executive routine/functional subroutine format. Software functional requirements are described using block diagrams where feasible, and input--output tables, and the software implementation of each function is presented in equations and structured flow charts. Included are a glossary of all symbols used to define the requirements, and an appendix of supportive material.
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An interplanetary targeting and orbit insertion maneuver design technique
NASA Technical Reports Server (NTRS)
Hintz, G. R.
1980-01-01
The paper describes a tradeoff in selecting a planetary encounter aimpoint and a spacecraft propulsive maneuver strategy in the Pioneer Venus Orbiter Mission. The method uses parametric data spanning a region of acceptable targeting aimpoints in the delivery space and the geometric considerations. Real-time maneuver adjustments accounted for known attitude control errors, orbit determination updates, and late changes in a targeting specification.
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Bruce, Jared M; Echemendia, Ruben J; Meeuwisse, Willem; Hutchison, Michael G; Aubry, Mark; Comper, Paul
2017-04-04
Little research examines how to best identify concussed athletes. The purpose of the present study was to develop a preliminary risk decision model that uses visible signs (VS) and mechanisms of injury (MOI) to predict the likelihood of subsequent concussion diagnosis. Coders viewed and documented VS and associated MOI for all NHL games over the course of the 2013-2014 and 2014-2015 regular seasons. After coding was completed, player concussions were identified from the NHL injury surveillance system and it was determined whether players exhibiting VS were subsequently diagnosed with concussions by club medical staff as a result of the coded event. Among athletes exhibiting VS, suspected loss of consciousness, motor incoordination or balance problems, being in a fight, having an initial hit from another player's shoulder and having a secondary hit on the ice were all associated with increased risk of subsequent concussion diagnosis. In contrast, having an initial hit with a stick was associated with decreased risk of subsequent concussion diagnosis. A risk prediction model using a combination of the above VS and MOI was superior to approaches that relied on individual VS and associated MOI (sensitivity=81%, specificity=72%, positive predictive value=26%). Combined use of VS and MOI significantly improves a clinician's ability to identify players who need to be evaluated for possible concussion. A preliminary concussion prediction log has been developed from these data. Pending prospective validation, the use of these methods may improve early concussion detection and evaluation. © Article author(s) (or their employer(s) unless otherwise stated in the text of the article) 2017. All rights reserved. No commercial use is permitted unless otherwise expressly granted.
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Mars Reconnaissance Orbiter Aerobraking Daily Operations and Collision Avoidance
NASA Technical Reports Server (NTRS)
Long, Stacia M.; You, Tung-Han; Halsell, C. Allen; Bhat, Ramachand S.; Demcak, Stuart W.; Graat, Eric J.; Higa, Earl S.; Highsmith, Dolan E.; Mottinger, Neil A.; Jah, Moriba K.
2007-01-01
The Mars Reconnaissance Orbiter reached Mars on March 10, 2006 and performed a Mars orbit insertion maneuver of 1 km/s to enter into a large elliptical orbit. Three weeks later, aerobraking operations began and lasted about five months. Aerobraking utilized the atmospheric drag to reduce the large elliptical orbit into a smaller, near circular orbit. At the time of MRO aerobraking, there were three other operational spacecraft orbiting Mars and the navigation team had to minimize the possibility of a collision. This paper describes the daily operations of the MRO navigation team during this time as well as the collision avoidance strategy development and implementation.
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NASA Astrophysics Data System (ADS)
Zamani, Mehdi; Hocini, Abdesselam
2017-05-01
We have investigated the potential of the SiO2/ZrO2 matrix doped with CoFe2O4 magnetic nanoparticles in order to overcome the problem of integration of the magneto-optical isolators (MOIs). In this way, we have performed a theoretical study for the case of designing perfect and adjustable MOIs based on magnetophotonic crystals (MPCs) containing SiO2/ZrO2 matrix doped with CoFe2O4 magnetic nanoparticles as a magnetic medium. Despite the existence the attenuation coefficient for SiO2/ZrO2 matrix at wavelength 1550 nm that leads to a non-perfect transmittance, we could introduce an MPC structure having no reflectance; therefore, an ideal MOI for eliminating unwanted back-reflection could be achieved.
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First Materials Science Research Facility Rack Capabilities and Design Features
NASA Technical Reports Server (NTRS)
Cobb, S.; Higgins, D.; Kitchens, L.; Curreri, Peter (Technical Monitor)
2002-01-01
The first Materials Science Research Rack (MSRR-1) is the primary facility for U.S. sponsored materials science research on the International Space Station. MSRR-1 is contained in an International Standard Payload Rack (ISPR) equipped with the Active Rack Isolation System (ARIS) for the best possible microgravity environment. MSRR-1 will accommodate dual Experiment Modules and provide simultaneous on-orbit processing operations capability. The first Experiment Module for the MSRR-1, the Materials Science Laboratory (MSL), is an international cooperative activity between NASA's Marshall Space Flight Center (MSFC) and the European Space Agency's (ESA) European Space Research and Technology Center (ESTEC). The MSL Experiment Module will accommodate several on-orbit exchangeable experiment-specific Module Inserts which provide distinct thermal processing capabilities. Module Inserts currently planned for the MSL are a Quench Module Insert, Low Gradient Furnace, and a Solidification with Quench Furnace. The second Experiment Module for the MSRR-1 configuration is a commercial device supplied by MSFC's Space Products Development (SPD) Group. Transparent furnace assemblies include capabilities for vapor transport processes and annealing of glass fiber preforms. This Experiment Module is replaceable on-orbit. This paper will describe facility capabilities, schedule to flight and research opportunities.
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ERIC Educational Resources Information Center
Hashimoto, Kayoko
2013-01-01
While the medium-of-instruction (MOI) has been seen as one of the most crucial decision-making areas in language policies, it is curious that the equivalent Japanese expression to MOI is absent from educational policy documents. In a nation where the Japanese language is called the national language and enjoys the status of an official language,…
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ERIC Educational Resources Information Center
Hamid, M. Obaidul; Jahan, Iffat; Islam, M. Monjurul
2013-01-01
The use of English as a medium of instruction (MOI) in polities across the world has drawn attention of language policy and planning scholars and researchers. Increasingly, research on MOI policy and practice focuses on how macro-level policies are translated into action by "actors" including teachers and students in the micro-context.…
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Lunar Orbit Insertion Targeting and Associated Outbound Mission Design for Lunar Sortie Missions
NASA Technical Reports Server (NTRS)
Condon, Gerald L.
2007-01-01
This report details the Lunar Orbit Insertion (LOI) arrival targeting and associated mission design philosophy for Lunar sortie missions with up to a 7-day surface stay and with global Lunar landing site access. It also documents the assumptions, methodology, and requirements validated by TDS-04-013, Integrated Transit Nominal and Abort Characterization and Sensitivity Study. This report examines the generation of the Lunar arrival parking orbit inclination and Longitude of the Ascending Node (LAN) targets supporting surface missions with global Lunar landing site access. These targets support the Constellation Program requirement for anytime abort (early return) by providing for a minimized worst-case wedge angle [and an associated minimum plane change delta-velocity (V) cost] between the Crew Exploration Vehicle (CEV) and the Lunar Surface Access Module (LSAM) for an LSAM launch anytime during the Lunar surface stay.
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Measuring Stability and Security in Iraq
2009-06-01
preventing judges from receiving registered firearms. The U.S. Marshal Service continues to provide handguns to judges and their security details and...in the South, a trend expected to continue throughout 2010. Overall, crude oil production peaked at 2.54 million barrels per day (mbpd) in...the best way to utilize MoI human and material resources. The result of this commission was the MoI 2009 training plan, which addresses the issue of
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Mars Redox Chemistry: Atacama Desert Soils as a Terrestrial Analog
NASA Technical Reports Server (NTRS)
Quinn, R. C.; Grunthaner, F. J.; Taylor, C. L.; Zent, A. P.
2003-01-01
The motivation for this work is to perform quantitative site characterizations of soil chemical processes to allow further development and field validation of the Mars Oxidant Instrument (MOI). The MOI is an in situ survey instrument designed to establish the presence of reactive chemical species in the martian soil, dust, or atmosphere, and to provide detailed reaction model system measurements to enable comprehensive Earthbased study. Functioning as a survey instrument, MOI tests the broad range of hypotheses explaining the reactivity of the martian surface material that have been put forth since the Viking experiments. This work is currently being carried out under the NASA ASTEP funded AstroBioLab (Jeffery Bada, PI). A second objective is to use Atacama field and Viking data to perform comparative studies, with the goal of furthering the understanding of the formation mechanisms and properties of martian oxidants.
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Magneto-optical imaging technique for hostile environments: The ghost imaging approach
DOE Office of Scientific and Technical Information (OSTI.GOV)
Meda, A.; Caprile, A.; Avella, A.
2015-06-29
In this paper, we develop an approach to magneto optical imaging (MOI), applying a ghost imaging (GI) protocol to perform Faraday microscopy. MOI is of the utmost importance for the investigation of magnetic properties of material samples, through Weiss domains shape, dimension and dynamics analysis. Nevertheless, in some extreme conditions such as cryogenic temperatures or high magnetic field applications, there exists a lack of domain images due to the difficulty in creating an efficient imaging system in such environments. Here, we present an innovative MOI technique that separates the imaging optical path from the one illuminating the object. The techniquemore » is based on thermal light GI and exploits correlations between light beams to retrieve the image of magnetic domains. As a proof of principle, the proposed technique is applied to the Faraday magneto-optical observation of the remanence domain structure of an yttrium iron garnet sample.« less
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Improving Robotic Operator Performance Using Augmented Reality
NASA Technical Reports Server (NTRS)
Maida, James C.; Bowen, Charles K.; Pace, John W.
2007-01-01
The Special Purpose Dexterous Manipulator (SPDM) is a two-armed robot that functions as an extension to the end effector of the Space Station Robotics Manipulator System (SSRMS), currently in use on the International Space Station (ISS). Crew training for the SPDM is accomplished using a robotic hardware simulator, which performs most of SPDM functions under normal static Earth gravitational forces. Both the simulator and SPDM are controlled from a standard robotic workstation using a laptop for the user interface and three monitors for camera views. Most operations anticipated for the SPDM involve the manipulation, insertion, and removal of any of several types of Orbital Replaceable Unit (ORU), modules which control various ISS functions. Alignment tolerances for insertion of the ORU into its receptacle are 0.25 inch and 0.5 degree from nominal values. The pre-insertion alignment task must be performed within these tolerances by using available video camera views of the intrinsic features of the ORU and receptacle, without special registration markings. Since optimum camera views may not be available, and dynamic orbital lighting conditions may limit periods of viewing, a successful ORU insertion operation may require an extended period of time. This study explored the feasibility of using augmented reality (AR) to assist SPDM operations. Geometric graphical symbols were overlaid on one of the workstation monitors to afford cues to assist the operator in attaining adequate pre-insertion ORU alignment. Twelve skilled subjects performed eight ORU insertion tasks using the simulator with and without the AR symbols in a repeated measures experimental design. Results indicated that using the AR symbols reduced pre-insertion alignment error for all subjects and reduced the time to complete pre-insertion alignment for most subjects.
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Launch vehicle and power level impacts on electric GEO insertion
NASA Technical Reports Server (NTRS)
Oleson, Steven R.; Myers, Roger M.
1996-01-01
Solar Electric Propulsion (SEP) has been shown to increase net geosynchronous spacecraft mass when used for station keeping and final orbit insertion. The impact of launch vehicle selection and power level on the benefits of this approach were examined for 20 and 25 kW systems launched using the Ariane 5, Atlas IIAR, Long March, Proton, and Sea Launch vehicles. Two advanced on-board propulsion technologies, 5 kW ion and Hall thruster systems, were used to establish the relative merits of the technologies and launch vehicles. GaAs solar arrays were assumed. The analysis identifies the optimal starting orbits for the SEP orbit raising/plane changing while considering the impacts of radiation degradation in the Van Allen belts, shading, power degradation, and oblateness. This use of SEP to provide part of the orbit insertion results in net mass increases of 15 - 38% and 18 - 46% for one to two month trip times, respectively, over just using SEP for 15 years of north/south station keeping. SEP technology was shown to have a greater impact on net masses of launch vehicles with higher launch latitudes when avoidance of solar array and payload degradation is desired. This greater impact of SEP could help reduce the plane changing disadvantage of high latitude launch sites. Comparison with results for 10 and 15 kW systems show clear benefits of incremental increases in SEP power level, suggesting that an evolutionary approach to high power SEP for geosynchronous spacecraft is possible.
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Pioneer probe mission with orbiter option
NASA Technical Reports Server (NTRS)
1975-01-01
A spacecraft is described which is based on Pioneer 10 and 11, and existing propulsion technology; it can transport and release a probe for entry into Jupiter's atmosphere, and subsequently maneuver to place the spacecraft in orbit about Jupiter. Orbital operations last 3 years and include maneuvers to provide multiple close satellite encounters which allow the orbit to be significantly changed to explore different parts of the magnetosphere. A mission summary, a guide to related documents, and background information about Jupiter are presented along with mission analysis over the complete mission profile. Other topics discussed include the launch, interplanetary flight, probe release and orbit deflection, probe entry, orbit selection, orbit insertion, periapsis raising, spacecraft description, and the effects of Jupiter's radiation belt on both orbiter and the probe.
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Bicalho, R C; Santos, T M A; Gilbert, R O; Caixeta, L S; Teixeira, L M; Bicalho, M L S; Machado, V S
2010-01-01
The objective of this study was to isolate bacteriophages from environmental samples of 2 large commercial dairy farms using Escherichia coli isolated from the uteri of postpartum Holstein dairy cows as hosts. A total of 11 bacteriophage preparations were isolated from manure systems of commercial dairy farms and characterized for in vitro antimicrobial activity. In addition, a total of 57 E. coli uterine isolates from 5 dairy cows were phylogenetically grouped by triplex PCR. Each E. coli bacterial host from the uterus was inoculated with their respective bacteriophage preparation at several different multiplicities of infections (MOI) to determine minimum inhibitory MOI. The effect of a single dose (MOI=10(2)) of bacteriophage on the growth curve of all 57 E. coli isolates was assessed using a microplate technique. Furthermore, genetic diversity within and between the different bacteriophage preparations was assessed by bacteriophage purification followed by DNA extraction, restriction, and agarose gel electrophoresis. Phylogenetic grouping based on triplex PCR showed that all isolates of E. coli belonged to phylogroup B1. Bacterial growth was completely inhibited at considerably low MOI, and the effect of a single dose (MOI=10(2)) of bacteriophage preparations on the growth curve of all 57 E. coli isolates showed that all bacteriophage preparations significantly decreased the growth rate of the isolates. Bacteriophage preparation 1230-10 had the greatest antimicrobial activity and completely inhibited the growth of 71.7% (n=57) of the isolates. The combined action of bacteriophage preparations 1230-10, 6375-10, 2540-4, and 6547-2, each at MOI=10(2), had the broadest spectrum of action and completely inhibited the growth (final optical density at 600 nm
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Malik, P; McQuiston, S A; Yu, X J; Pepper, K A; Krall, W J; Podsakoff, G M; Kurtzman, G J; Kohn, D B
1997-01-01
We tested the ability of a recombinant adeno-associated virus (rAAV) vector to express and integrate exogenous DNA into human hematopoietic cells in the absence of selection. We developed an rAAV vector, AAV-tNGFR, carrying a truncated rat nerve growth factor receptor (tNGFR) cDNA as a cell surface reporter under the control of the Moloney murine leukemia virus (MoMuLV) long terminal repeat. An analogous MoMuLV-based retroviral vector (L-tNGFR) was used in parallel, and gene transfer and expression in human hematopoietic cells were assessed by flow cytometry and DNA analyses. Following gene transfer into K562 cells with AAV-tNGFR at a multiplicity of infection (MOI) of 13 infectious units (IU), 26 to 38% of cells expressed tNGFR on the surface early after transduction, but the proportion of tNGFR expressing cells steadily declined to 3.0 to 3.5% over 1 month of culture. At an MOI of 130 IU, nearly all cells expressed tNGFR immediately posttransduction, but the proportion of cells expressing tNGFR declined to 62% over 2 months of culture. The decline in the proportion of AAV-tNGFR-expressing cells was associated with ongoing losses of vector genomes. In contrast, K562 cells transduced with the retroviral vector L-tNGFR expressed tNGFR in a constant fraction. Integration analyses on clones showed that integration occurred at different sites. Integration frequencies were estimated at about 49% at an MOI of 130 and 2% at an MOI of 1.3. Transduction of primary human CD34+ progenitor cells by AAV-tNGFR was less efficient than with K562 cells and showed a declining percentage of cells expressing tNGFR over 2 weeks of culture. Thus, purified rAAV caused very high gene transfer and expression in human hematopoietic cells early after transduction, which steadily declined during cell passage in the absence of selection. Although the efficiency of integration was low, overall integration was markedly improved at a high MOI. While prolonged episomal persistence may be adequate for gene therapy of nondividing cells, a very high MOI or improvements in basic aspects of AAV-based vectors may be necessary to improve integration frequency in the rapidly dividing hematopoietic cell population. PMID:9032306
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Malik, P; McQuiston, S A; Yu, X J; Pepper, K A; Krall, W J; Podsakoff, G M; Kurtzman, G J; Kohn, D B
1997-03-01
We tested the ability of a recombinant adeno-associated virus (rAAV) vector to express and integrate exogenous DNA into human hematopoietic cells in the absence of selection. We developed an rAAV vector, AAV-tNGFR, carrying a truncated rat nerve growth factor receptor (tNGFR) cDNA as a cell surface reporter under the control of the Moloney murine leukemia virus (MoMuLV) long terminal repeat. An analogous MoMuLV-based retroviral vector (L-tNGFR) was used in parallel, and gene transfer and expression in human hematopoietic cells were assessed by flow cytometry and DNA analyses. Following gene transfer into K562 cells with AAV-tNGFR at a multiplicity of infection (MOI) of 13 infectious units (IU), 26 to 38% of cells expressed tNGFR on the surface early after transduction, but the proportion of tNGFR expressing cells steadily declined to 3.0 to 3.5% over 1 month of culture. At an MOI of 130 IU, nearly all cells expressed tNGFR immediately posttransduction, but the proportion of cells expressing tNGFR declined to 62% over 2 months of culture. The decline in the proportion of AAV-tNGFR-expressing cells was associated with ongoing losses of vector genomes. In contrast, K562 cells transduced with the retroviral vector L-tNGFR expressed tNGFR in a constant fraction. Integration analyses on clones showed that integration occurred at different sites. Integration frequencies were estimated at about 49% at an MOI of 130 and 2% at an MOI of 1.3. Transduction of primary human CD34+ progenitor cells by AAV-tNGFR was less efficient than with K562 cells and showed a declining percentage of cells expressing tNGFR over 2 weeks of culture. Thus, purified rAAV caused very high gene transfer and expression in human hematopoietic cells early after transduction, which steadily declined during cell passage in the absence of selection. Although the efficiency of integration was low, overall integration was markedly improved at a high MOI. While prolonged episomal persistence may be adequate for gene therapy of nondividing cells, a very high MOI or improvements in basic aspects of AAV-based vectors may be necessary to improve integration frequency in the rapidly dividing hematopoietic cell population.
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14 CFR 417.113 - Launch safety rules.
Code of Federal Regulations, 2010 CFR
2010-01-01
... flight safety analysis of subpart C of this part. These must include criteria for: (i) Surveillance of... criteria for ensuring that: (i) The flight safety system is operating to ensure the launch vehicle will... source at all times from lift-off to orbit insertion for an orbital launch, to the end of powered flight...
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14 CFR 417.113 - Launch safety rules.
Code of Federal Regulations, 2014 CFR
2014-01-01
... flight safety analysis of subpart C of this part. These must include criteria for: (i) Surveillance of... criteria for ensuring that: (i) The flight safety system is operating to ensure the launch vehicle will... source at all times from lift-off to orbit insertion for an orbital launch, to the end of powered flight...
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14 CFR 417.113 - Launch safety rules.
Code of Federal Regulations, 2011 CFR
2011-01-01
... flight safety analysis of subpart C of this part. These must include criteria for: (i) Surveillance of... criteria for ensuring that: (i) The flight safety system is operating to ensure the launch vehicle will... source at all times from lift-off to orbit insertion for an orbital launch, to the end of powered flight...
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14 CFR 417.113 - Launch safety rules.
Code of Federal Regulations, 2013 CFR
2013-01-01
... flight safety analysis of subpart C of this part. These must include criteria for: (i) Surveillance of... criteria for ensuring that: (i) The flight safety system is operating to ensure the launch vehicle will... source at all times from lift-off to orbit insertion for an orbital launch, to the end of powered flight...
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14 CFR 417.113 - Launch safety rules.
Code of Federal Regulations, 2012 CFR
2012-01-01
... flight safety analysis of subpart C of this part. These must include criteria for: (i) Surveillance of... criteria for ensuring that: (i) The flight safety system is operating to ensure the launch vehicle will... source at all times from lift-off to orbit insertion for an orbital launch, to the end of powered flight...
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NASA Technical Reports Server (NTRS)
1969-01-01
Postflight analysis of Apollo 8 mission. Apollo 8 was the second manned flight in the program and the first manned lunar orbit mission. The crew were Frank Borman, Commander; James A. Lovell, Command Module Pilot; and William A. Anders, Lunar Module Pilot. The Apollo 8 space vehicle was launched on time from Kennedy Space Center, Florida, at 7:51:00 AM, EST, on December 21, 1968. Following a nominal boost phase, the spacecraft and S-IVB combination was inserted - into a parking orbit of 98 by 103 nautical miles. After a post-insertion checkout of spacecraft systems, the 319-second translunar injection maneuver was initiated at 2:50:37 by reignition of the S-IVB engine.
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LLOFX earth orbit to lunar orbit delta V estimation program user and technical documentation
NASA Technical Reports Server (NTRS)
1988-01-01
The LLOFX computer program calculates in-plane trajectories from an Earth-orbiting space station to Lunar orbit in such a way that the journey requires only two delta V burns (one to leave Earth circular orbit and one to circularize into Lunar orbit). The program requires the user to supply the Space Station altitude and Lunar orbit altitude (in km above the surface), and the desired time of flight for the transfer (in hours). It then determines and displays the trans-Lunar injection (TLI) delta V required to achieve the transfer, the Lunar orbit insertion (LOI) delta V required to circularize the orbit around the Moon, the actual time of flight, and whether the transfer orbit is elliptical or hyperbolic. Return information is also displayed. Finally, a plot of the transfer orbit is displayed.
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Orbit Determination Error Analysis Results for the Triana Sun-Earth L2 Libration Point Mission
NASA Technical Reports Server (NTRS)
Marr, G.
2003-01-01
Using the NASA Goddard Space Flight Center's Orbit Determination Error Analysis System (ODEAS), orbit determination error analysis results are presented for all phases of the Triana Sun-Earth L1 libration point mission and for the science data collection phase of a future Sun-Earth L2 libration point mission. The Triana spacecraft was nominally to be released by the Space Shuttle in a low Earth orbit, and this analysis focuses on that scenario. From the release orbit a transfer trajectory insertion (TTI) maneuver performed using a solid stage would increase the velocity be approximately 3.1 km/sec sending Triana on a direct trajectory to its mission orbit. The Triana mission orbit is a Sun-Earth L1 Lissajous orbit with a Sun-Earth-vehicle (SEV) angle between 4.0 and 15.0 degrees, which would be achieved after a Lissajous orbit insertion (LOI) maneuver at approximately launch plus 6 months. Because Triana was to be launched by the Space Shuttle, TTI could potentially occur over a 16 orbit range from low Earth orbit. This analysis was performed assuming TTI was performed from a low Earth orbit with an inclination of 28.5 degrees and assuming support from a combination of three Deep Space Network (DSN) stations, Goldstone, Canberra, and Madrid and four commercial Universal Space Network (USN) stations, Alaska, Hawaii, Perth, and Santiago. These ground stations would provide coherent two-way range and range rate tracking data usable for orbit determination. Larger range and range rate errors were assumed for the USN stations. Nominally, DSN support would end at TTI+144 hours assuming there were no USN problems. Post-TTI coverage for a range of TTI longitudes for a given nominal trajectory case were analyzed. The orbit determination error analysis after the first correction maneuver would be generally applicable to any libration point mission utilizing a direct trajectory.
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Proceedings of the FAA Inspection Program Area Review, Held in Ames, Iowa on April 5-7, 1994
1994-07-01
Colin Drury Mr. Locke Easton SUNY Buffalo ANE-1 00, Aircraft Certification Division, Engine and 342 Bell Mall Propeller Directorate Buffalo, NY 14260...and Tech Transfer Walter Validation: 13:10 MOI validation F. Spencer, SNL 13:30 Cost Benefit Analysis Protocol (with MOI example) V. Brechling, NWU 13...on the need for calibration of the instrument were briefly addressed. Cost -Benefit Analysis: ATA members took unexpected interest in the presentation
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Energetic benefits and adaptations in mammalian limbs: Scale effects and selective pressures.
Kilbourne, Brandon M; Hoffman, Louwrens C
2015-06-01
Differences in limb size and shape are fundamental to mammalian morphological diversity; however, their relevance to locomotor costs has long been subject to debate. In particular, it remains unknown if scale effects in whole limb morphology could partially underlie decreasing mass-specific locomotor costs with increasing limb length. Whole fore- and hindlimb inertial properties reflecting limb size and shape-moment of inertia (MOI), mass, mass distribution, and natural frequency-were regressed against limb length for 44 species of quadrupedal mammals. Limb mass, MOI, and center of mass position are negatively allometric, having a strong potential for lowering mass-specific locomotor costs in large terrestrial mammals. Negative allometry of limb MOI results in a 40% reduction in MOI relative to isometry's prediction for our largest sampled taxa. However, fitting regression residuals to adaptive diversification models reveals that codiversification of limb mass, limb length, and body mass likely results from selection for differing locomotor modes of running, climbing, digging, and swimming. The observed allometric scaling does not result from selection for energetically beneficial whole limb morphology with increasing size. Instead, our data suggest that it is a consequence of differing morphological adaptations and body size distributions among quadrupedal mammals, highlighting the role of differing limb functions in mammalian evolution. © 2015 The Author(s). Evolution © 2015 The Society for the Study of Evolution.
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Machado, Soraya A; Kuzmin, Yuriy; Tkach, Vasyl V; Dos Santos, Jeannie Nascimento; Gonçalves, Evonnildo Costa; de Vasconcelos Melo, Francisco Tiago
2018-05-09
A new species of the genus Serpentirhabdias Tkach, Kuzmin et Snyder, 2014, S. moi n. sp., is described from a colubroid snake Chironius exoletus from Caxiuanã National Forest, State of Pará, Brazil. The species is characterised by having a triangular oral opening, absence of the buccal capsule, presence of six minute onchia in the oesophastome, and excretory glands of approximately the same length as the oesophagus. These qualitative morphological characters, as well as some measurements, differentiate the new species from other Neotropical and Nearctic Serpentirhabdias spp. The morphological description of parasitic adults of S. moi n. sp. is complemented by the description of free-living stages including males, females, and infective larvae. Comparative analysis of partial sequences of cox1 and 12S mitochondrial genes strongly supported the status of S. moi n. sp. as a new species. Molecular phylogeny based on sequences of the nuclear DNA region spanning the 3' end of the 18S nuclear rRNA gene, ITS region (ITS1 + 5.8S + ITS2) and 5' end of the 28S gene supported monophyly of all rhabdiasid genera included in the analysis and placed the new species into the Serpentirhabdias clade as sister taxon to S. fuscovenosa. Copyright © 2018 Elsevier B.V. All rights reserved.
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Giorno, Thais Biondino Sardella; Silva, Bárbara Vasconcellos da; Pinto, Angelo da Cunha; Fernandes, Patricia Dias
2016-04-15
There has been growing interest in the synthesis of new derivatives from isatin, found in Isatis genus. Our objectives were to characterize the antinociceptive mechanism of action of isatin, N-methyl-isatin (MI) and N-methyl-3-(2-oxopropyl)-3-hydroxy-2-oxindole (MOI). Substances (0.1-10mg/kg, p.o.) were studied in chemical (paw licking induced by formalin, capsaicin or glutamate) or thermal (hot plate) models of nociception. The involvement of several systems was evaluated using different receptor antagonists. All three substances inhibit both phases of formalin-induced licking, increase the area under the curve and MI and MOI have a higher effect than that of morphine (in hot plate). Capsaicin and glutamate-induced licking were also reduced by all three substances. In the hot plate model, the antinociceptive effect of isatin was reduced by naloxone and atropine; naloxone, atropine and L-NAME reduced MI effect while naloxone, atropine, L-NAME, mecamylamine and ondansetron reduced MOI effect. Our results suggest that isatin, MI and MOI: 1) present activity in models of nociception; 2) capsaicin and glutamate receptors seems to participate in the mechanism of action; 3) opioid, cholinergic, serotoninergic, nitrergic and adrenergic systems may be involved, at least in part, in the mechanism of action of some of these substances. Copyright © 2016 Elsevier Inc. All rights reserved.
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Ndoua, Claude Cyrille Noa; Tebeu, Pierre Marie; Kemfang, Jean Dupont; Kasia, Jean Marie
2015-01-01
Nous rapportons les résultats d'une série de 21 cas de prise en charge par cryothérapie de lésions intra-épithéliales cervicales au Centre Hospitalier et Universitaire (CHU) de Yaoundé. Notre objectif principal était d’évaluer les résultats préliminaires de la prise en charge des lésions précancéreuses éligibles pour la cryothérapie. Il s'agissait d'une étude transversale descriptive qui s'est étalée sur 24 mois. Etaient inclus dans l’étude toutes les femmes traitées par cryothérapie. Nous avons exclu les patientes traitées par une autre méthode, les patientes perdues de vue et les dossiers incomplets. Le statut cervical a été déterminé à 6 semaines, 6 mois et 12 mois. Les complications précoces et tardives ont également été répertoriées. Au total 95.2% des lésions étaient cicatrisées à 6 semaines. A 6 mois, toutes les lésions avaient disparu et au 12ème mois, la guérison était effective chez 95.2% des patientes. Les saignements et l'hydrorrhée étaient les principales complications tardives avec des fréquences respectives de 66.7% et 95.2%. Aucun cas de sténose cervicale n'a été répertorié. La cryothérapie peut être utilisée comme méthode de traitement pour des lésions précancéreuses du col. PMID:26140068
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Kurath, Gael; Purcell, Maureen K.; Wargo, Andrew; Park, Jeong Woo; Moon, Chang Hoon
2010-01-01
Infectious haematopoietic necrosis virus (IHNV) is one of the most important viral pathogens of salmonids. In rainbow trout, IHNV isolates in the M genogroup are highly pathogenic, while U genogroup isolates are significantly less pathogenic. We show here that, at a multiplicity of infection (MOI) of 1, a representative U type strain yielded 42-fold less infectious virus than an M type strain in the rainbow trout–derived RTG-2 cell line at 24 h post-infection (p.i.). However, at an MOI of 10, there was only fivefold difference in the yield of infectious virus between the U and M strains. Quantification of extracellular viral genomic RNA suggested that the number of virus particles released from cells infected with the U strain at a MOI of 1 was 47-fold lower than from M-infected cells, but U and M virions were equally infectious by particle to infectivity ratios. At an MOI of 1, U strain intracellular viral genome accumulation and transcription were 37- and 12-fold lower, respectively, than those of the M strain at 24 h p.i. Viral nucleocapsid (N) protein accumulation in U strain infections was fivefold lower than in M strain infections. These results suggest that the block in U type strain growth in RTG-2 cells was because of the effects of reduced genome replication and transcription. The reduced growth of the U strain does not seem to be caused by defective genes, because the U and M strains grew equally well in the permissive epithelioma papulosum cyprini cell line at an MOI of 1. This suggests that host-specific factors in RTG-2 cells control the growth of the IHNV U and M strains differently, leading to growth restriction of the U type virus during the RNA synthesis step.
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Mars Observer Press Conference JPL
NASA Astrophysics Data System (ADS)
1993-08-01
The Mars Observer mission spacecraft was primarily designed for exploring Mars and the Martian environment. The Mars Observer was launched on September 25, 1992. The spacecraft was lost in the vicinity of Mars on August 21, 1993 when the spacecraft began its maneuvering sequence for Martian orbital insertion. This videotape shows a press briefing, held after the spacecraft had not responded to attempts to communicate with it, to explain to the press the problems and the steps that were being taken to re-establish communication with the spacecraft. The communications had been shutdown prior to the orbital insertion burn to protect the instruments. At the time of the press conference, the communications system was still not operational, and attempts were being made to re-establish communication. Bob McMillan of the Public Affairs Office at JPL gives the initial announcement of the continuing communication problem with the spacecraft. Mr. McMillan introduces William Piotrowski, acting director of solar system exploration, who reiterates that there is indeed no communication with the Observer spacecraft. He is followed by Glenn Cunningham, the Project Manager of the Mars Observer who speaks about the attempts to re-establish contact. Mr. Cunningham is followed by Satenios Dallas, the Mission Manager for the Mars Observer Project, who speaks about the sequence of events leading up to the communication failure, and shows an animated video presenting the orbital insertion maneuvers. The briefing was then opened up for questions from the assembled press, both at JPL and at the other NASA Centers. The questions are about the possible reasons for the communication failure, and the attempts to restore communications with the spacecraft. Dr. Arden L. Albee, chief scientist for the Mars Observer Mission, joins the other panel members to answer questions. At the end of the press briefing the animation of the Mars orbital insertion is shown again.
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Crandell, Douglas W.; Mazumder, Shivnath
2015-01-01
Density functional theory calculations demonstrate that the reversal of regiochemical outcome of the addition for substituted methyl propiolates in the rhodium-catalyzed [(2 + 2) + 2] carbocyclization with PPh3 and (S)-xyl-binap as ligands is both electronically and sterically controlled. For example, the ester functionality polarizes the alkyne π* orbital to favor overlap of the methyl-substituted terminus of the alkyne with the pπ-orbital of the alkenyl fragment of the rhodacycle during alkyne insertion with PPh3 as the ligand. In contrast, the sterically demanding xyl-binap ligand cannot accommodate the analogous alkyne orientation, thereby forcing insertion to occur at the sterically preferred ester terminus, overriding the electronically preferred orientation for alkyne insertion. PMID:28757978
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Conestoga 2: A low cost commercial space transport system
NASA Technical Reports Server (NTRS)
Rasmussen, R. O.
1984-01-01
Conestoga 2 is currently under development. It is capable of inserting 500 Kg satellites into 800 Km circular polar orbits. Conestoga 2 makes maximum use of existing (developed) technology and hardware. Its commercial objective is to fill a need for low cost low Earth orbital transport not efficiently served by Shuttle or larger space transport systems. Low Earth orbit markets, foreign participation, and launch site considerations are discussed along with technical and economic trade-offs.
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Strengthening the Security of ESA Ground Data Systems
NASA Astrophysics Data System (ADS)
Flentge, Felix; Eggleston, James; Garcia Mateos, Marc
2013-08-01
A common approach to address information security has been implemented in ESA's Mission Operations (MOI) Infrastructure during the last years. This paper reports on the specific challenges to the Data Systems domain within the MOI and how security can be properly managed with an Information Security Management System (ISMS) according to ISO 27001. Results of an initial security risk assessment are reported and the different types of security controls that are being implemented in order to reduce the risks are briefly described.
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2015-02-25
develop, award, execute, or monitor individual contracts funded with U.S. direct assistance. This occurred because the Ministry of Finance ( MoF ...trained staff to collaborate with the Ministry of Finance ( MoF ), MoD, and MoI for budgeting, acquisition planning, procurement, financial management...and contract management and oversight. Finally, CSTC-A must ensure MoF , MoD, and MoI establish standard operating procedures and maintain adequate
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Inferolateral migration of hydrogel orbital implants in microphthalmia.
Tao, Jeremiah P; LeBoyer, Russell M; Hetzler, Kathy; Ng, John D; Nunery, William R
2010-01-01
Hydrogel spheres may be useful in treating orbital hypoplasia associated with congenital microphthalmia. The authors describe migration associated with the use of these devices. The authors retrospectively reviewed 5 cases in which a hydrogel orbital expander (Osmed) was implanted to treat orbital hypoplasia in pediatric patients with congenital microphthalmia (with or without previous surgery). In all 5 cases, a lateral orbitotomy, conjunctiva-sparing approach was used to insert the hydrogel spheres. Two cases involved previously unoperated orbits; 3 patients had prior orbit or socket surgery. Inferolateral movement outside the desired central, deep orbital position occurred in all 5 cases. Four of 5 cases required further procedures to achieve an adequate orbital implant position. Inferolateral migration may occur with hydrogel spheres implanted via a lateral orbitotomy approach in microphthalmia.
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Engineering spin-orbit torque in Co/Pt multilayers with perpendicular magnetic anisotropy
DOE Office of Scientific and Technical Information (OSTI.GOV)
Huang, Kuo-Feng; Wang, Ding-Shuo; Lai, Chih-Huang, E-mail: chlai@mx.nthu.edu.tw
To address thermal stability issues for spintronic devices with a reduced size, we investigate spin-orbit torque in Co/Pt multilayers with strong perpendicular magnetic anisotropy. Note that the spin-orbit torque arises from the global imbalance of the spin currents from the top and bottom interfaces for each Co layer. By inserting Ta or Cu layers to strengthen the top-down asymmetry, the spin-orbit torque efficiency can be greatly modified without compromised perpendicular magnetic anisotropy. Above all, the efficiency builds up as the number of layers increases, realizing robust thermal stability and high spin-orbit-torque efficiency simultaneously in the multilayers structure.
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A study on various methods of supplying propellant to an orbit insertion rocket engine
NASA Technical Reports Server (NTRS)
Boretz, J. E.; Huniu, S.; Thompson, M.; Pagani, M.; Paulsen, B.; Lewis, J.; Paul, D.
1980-01-01
Various types of pumps and pump drives were evaluated to determine the lightest weight system for supplying propellants to a planetary orbit insertion rocket engine. From these analyses four candidate propellant feed systems were identified. Systems Nos. 1 and 2 were both battery powered (lithium-thionyl-chloride or silver-zinc) motor driven pumps. System 3 was a monopropellant gas generator powered turbopump. System 4 was a bipropellant gas generator powered turbopump. Parameters considered were pump break horsepower, weight, reliability, transient response and system stability. Figures of merit were established and the ranking of the candidate systems was determined. Conceptual designs were prepared for typical motor driven pumps and turbopump configurations for a 1000 lbf thrust rocket engine.
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Attenuation of virus production at high multiplicities of infection in Aureococcus anophagefferens
DOE Office of Scientific and Technical Information (OSTI.GOV)
Brown, Christopher M.; Bidle, Kay D., E-mail: bidle@marine.rutgers.edu
2014-10-15
Infection dynamics (saturation kinetics, infection efficiency, adsorption and burst size) for the Aureococcus anophagefferens-Brown Tide virus (AaV) system were investigated using susceptible and resistant strains. Adsorption assays revealed that virus affinity to the cell surface is a key determinant of infectivity. Saturation of infection occurred at a multiplicity of infection (MOI) of 8 viruses per host and resulted in ∼90–95% of infected cells, with burst sizes ranging from 164 to 191. Insight from the AaV genome implicates recycling of host nucleotides rather than de novo synthesis as a constraint on viral replication. Viral yields and mean burst sizes were significantlymore » diminished with increasing MOI. This phenomenon, which was reminiscent of phage-induced ‘lysis from without’, appeared to be caused by viral contact and was unrelated to bacteria, signaling/toxic compounds, or defective interfering viruses. We posit that high-MOI effects attenuate viral proliferation in natural systems providing a negative feedback on virus-induced bloom collapse.« less
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NASA Technical Reports Server (NTRS)
Crouch, Myscha; Carswell, Bill; Farmer, Jeff; Rose, Fred; Tidwell, Paul
2000-01-01
The Material Science Research Rack I (MSRR-1) of the Material Science Research Facility (MSRF) contains an Experiment Module (EM) being developed collaboratively by NASA and the European Space Agency (ESA). This NASA/ESA EM will accommodate several different removable and replaceable Module Inserts (MIs) which are installed on orbit NASA's planned inserts include the Quench Module Insert (QMI) and the Diffusion Module Insert (DMI). The QMI is a high-gradient Bridgman-type vacuum furnace with quench capabilities used for experiments on directional solidification of metal alloys. The DMI is a vacuum Bridgman-Stockbarger-type furnace for experiments on Fickian and Soret diffusion in liquids. This paper discusses specific design features and performance capabilities of each insert. The paper also presents current prototype QMI hardware analysis and testing activities and selected results.
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1988-12-01
Conversion of the Geopotential into the Modified Orbital Elements 83 Appendix C: Useful Derivatives for the Geopotential Calculations 87 Appendix D...replaced by two equinoctial elements , h and k (from a coordinate system with singularities at i = x and for rectilinear orbits ). Also, for long term 3...0. 10 and 0.55 i 15.5) a more well behaved set of variables will be used: two of the equinoctial elements , h and k. These elements eliminate the
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Yan, Ruicheng; Huang, Jiancong; Zhu, Ling; Chang, Lihong; Li, Jingjia; Wu, Xifu; Ye, Jin; Zhang, Gehua
2015-12-01
The optimal multiplicity of infection (MOI) of the recombinant adenovirus Ad-Rad50-GFP carrying a mutant Rad50 gene expression region on the cell growth of nasopharyngeal carcinoma and the viral amplification efficiency of CNE1 cell infected by this adenovirus were studied. The biological titer of Ad-Rad50-GFP was measured by end point dilution method. The impact of recombinant adenoviral vector transfection on the growth of CNE1 cells was observed by cell growth curve. Transfection efficacy of recombinant adenoviral vector was observed and calculated through fluorescence microscope. The expression f mutant Rad50 in the Ad-Rad50-GFP transfected CNE1 cells with optimal MOI was detected by Western Blot after transfection. The biological titer of Ad-Rad50-GFP was 1.26 x 10¹¹ pfu/ml. CNE1 cell growth was not influenced significantly as they were transfected by recombinant adenoviral vector with MOI less than 50. Transfection efficacy of recombinant adenoviral vector was most salient at 24 hours after transfection, with the high expression of mutant Rad50, and the efficiency still remained about 70% after 72 hours. Recombinant adenoviral vector Ad-Rad50-GFP could transfect CNE1 cells as well as result in the expression of mutant Rad50 in CNE1 cells effectively. MOI = 50 was the optimal multiplicity of infection of CNE1 cells transfected by recombinant adenoviral vector Ad-Rad50-GFP.
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NeuroKinect: A Novel Low-Cost 3Dvideo-EEG System for Epileptic Seizure Motion Quantification
Cunha, João Paulo Silva; Choupina, Hugo Miguel Pereira; Rocha, Ana Patrícia; Fernandes, José Maria; Achilles, Felix; Loesch, Anna Mira; Vollmar, Christian; Hartl, Elisabeth; Noachtar, Soheyl
2016-01-01
Epilepsy is a common neurological disorder which affects 0.5–1% of the world population. Its diagnosis relies both on Electroencephalogram (EEG) findings and characteristic seizure−induced body movements − called seizure semiology. Thus, synchronous EEG and (2D)video recording systems (known as Video−EEG) are the most accurate tools for epilepsy diagnosis. Despite the establishment of several quantitative methods for EEG analysis, seizure semiology is still analyzed by visual inspection, based on epileptologists’ subjective interpretation of the movements of interest (MOIs) that occur during recorded seizures. In this contribution, we present NeuroKinect, a low-cost, easy to setup and operate solution for a novel 3Dvideo-EEG system. It is based on a RGB-D sensor (Microsoft Kinect camera) and performs 24/7 monitoring of an Epilepsy Monitoring Unit (EMU) bed. It does not require the attachment of any reflectors or sensors to the patient’s body and has a very low maintenance load. To evaluate its performance and usability, we mounted a state-of-the-art 6-camera motion-capture system and our low-cost solution over the same EMU bed. A comparative study of seizure-simulated MOIs showed an average correlation of the resulting 3D motion trajectories of 84.2%. Then, we used our system on the routine of an EMU and collected 9 different seizures where we could perform 3D kinematic analysis of 42 MOIs arising from the temporal (TLE) (n = 19) and extratemporal (ETE) brain regions (n = 23). The obtained results showed that movement displacement and movement extent discriminated both seizure MOI groups with statistically significant levels (mean = 0.15 m vs. 0.44 m, p<0.001; mean = 0.068 m3 vs. 0.14 m3, p<0.05, respectively). Furthermore, TLE MOIs were significantly shorter than ETE (mean = 23 seconds vs 35 seconds, p<0.01) and presented higher jerking levels (mean = 345 ms−3 vs 172 ms−3, p<0.05). Our newly implemented 3D approach is faster by 87.5% in extracting body motion trajectories when compared to a 2D frame by frame tracking procedure. We conclude that this new approach provides a more comfortable (both for patients and clinical professionals), simpler, faster and lower-cost procedure than previous approaches, therefore providing a reliable tool to quantitatively analyze MOI patterns of epileptic seizures in the routine of EMUs around the world. We hope this study encourages other EMUs to adopt similar approaches so that more quantitative information is used to improve epilepsy diagnosis. PMID:26799795
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The effects of particulates from solid rocket motors fired in space
NASA Technical Reports Server (NTRS)
Mueller, A. C.; Kessler, D. J.
1985-01-01
The orbits attained by kick motor solid propellant particulates are modeled, and an estimate is made of the number of particulates which will remain in orbit. The fuel, Al2O3, is burned while inserting spacecraft into a transfer orbit and again while circularizing the GEO station. It is shown that 23 percent of 1 micron particles deorbit immediately, while most particles enter a retrograde orbit. The resulting flux is an order of magnitude larger than the micrometeoroid flux. The pressures exerted by solar radiation ensure that only 5 percent of the original flux is still in orbit after the first year. The estimates provided are valid for a large number of transfer orbit operations, but will vary widely over the short term.
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Lissajous Orbit Control for the Deep Space Climate Observatory Sun-Earth L1 Libration Point Mission
NASA Technical Reports Server (NTRS)
Roberts, Craig; Case, Sarah; Reagoso, John
2015-01-01
DSCOVR Lissajous Orbit sized such that orbit track never extends beyond 15 degrees from Earth-Sun line (as seen from Earth). Requiring delta-V maneuvers, control orbit to obey a Solar Exclusion Zone (SEZ) cone of half-angle 4 degrees about the Earth-Sun line. Spacecraft should never be less than 4 degrees from solar center as seen from Earth. Following Lissajous Orbit Insertion (LOI), DSCOVR should be in an opening phase that just skirts the 4-degree SEZ. Maximizes time to the point where a closing Lissajous will require avoidance maneuvers to keep it out of the SEZ. Station keeping maneuvers should take no more than 15 minutes.
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Lee, Michael S; Nguyen, Heajung; Shlofmitz, Richard
2017-02-01
We analyzed the incidence of bradycardia and the safety of patients with severely calcified coronary lesions who underwent orbital atherectomy without the insertion of a temporary pacemaker. The presence of severely calcified coronary lesions can increase the complexity of percutaneous coronary intervention due to the difficulty in advancing and optimally expanding the stent. High-pressure inflations to predilate calcified lesions may cause angiographic complications like perforation and dissection. Suboptimal stent expansion is associated with stent thrombosis and restenosis. Orbital atherectomy safely and effectively modifies calcified plaque to facilitate optimal stent expansion. The incidence of bradycardia in orbital atherectomy is unknown. Fifty consecutive patients underwent orbital atherectomy from February 2014 to September 2016 at our institution, none of whom underwent insertion of a temporary pacemaker. The final analysis included 47 patients in this retrospective study as 3 patients were excluded because of permanent pacemaker implantation. The primary endpoint was significant bradycardia, defined as bradycardia requiring emergent pacemaker placement or a heart rate <50 bpm at the end of atherectomy. The primary endpoint occurred in 4% of all patients, all driven by patients who experienced a heart rate decreasing to <50 bpm. The major adverse cardiac and cerebral event rate was 6%, driven by death (2%) and myocardial infarction (4%). No patient experienced target-vessel revascularization, stroke, or stent thrombosis. Angiographic complications included perforation in 2%, slow-flow in 4%, and flow-limiting dissection in 0%. Significant bradycardia was uncommon during orbital atherectomy. Performing orbital atherectomy without a temporary pacemaker appears to be safe.
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Spin-Orbit Torque and Spin Pumping in YIG/Pt with Interfacial Insertion Layers (Postprint)
2018-05-03
Distribution Statement A. Approved for public release: distribution unlimited. © 2018 AMERICAN INSTITUTE OF PHYSICS (STINFO COPY) AIR FORCE RESEARCH ...SPONSORING/MONITORING AGENCY ACRONYM(S) Air Force Research Laboratory Materials and Manufacturing Directorate Wright-Patterson Air Force Base, OH... observe a large enhancement of Gilbert damping with the insertion of Py that cannot be accounted for solely by spin pumping, revealing significant spin
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[Evaluation of the cosmetic effect of orbital endoimplantation after removal the eyeball].
Piskiniene, Raimonda
2006-01-01
The purpose of our study was to evaluate the cosmetic effect of endoimplantation after removal the eyeball. The removal of the globe creates anatomic and physiological alteration of the orbital tissue and orbital bones. A volume deficit occurs when an eye is enucleated. Deep upper lid sulcus, ptosis, lower lid laxity, and enophthalmus of the artificial eye together constitute the postenucleation socket syndrome, which creates an asymmetry of the face. The orbital prosthesis by placing it in the orbital cavity allows correcting volume deficit, so the implant with attached extraocular muscles, together with an artificial eye, creates an illusion of real eye. Forty patients were operated on in Clinic of Eye Diseases of Kaunas University of Medicine Hospital. Twenty patients underwent removal of the eye and procedure of orbital implant insertion (main group). Twenty patients had just an eyeball removal without insertion of an orbital implant (control group). There was a statistically significant difference in exophthalmometry data between main and control groups (14.20+/-2.73 vs. 10.35+/-1.23 mm, respectively; p<0.05). The motility of artificial eye laterally (4.30+/-1.66 mm), medially (3.65+/-1.23 mm), up (3.70+/-1.13 mm), and down (3.40+/-1.19 mm) in the main group was significantly better as compared to the control group (p<0.05), where motility of the artificial eye was 0.60+/-0.68 mm laterally, 0.70+/-0.92 mm medially, 0.30+/-0.66 mm up, and 0.30+/-0.47 mm down. Therefore, a much better symmetry, better movement of the artificial eye, and less severe form of postenucleation syndrome were observed in patients who underwent orbital endoimplantation after eyeball removal.
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Stratospheric Turbulence and Vertical Effective Diffusion Coefficients
1975-09-29
UMBER AFCRL-TR-75.-0519 - 4. TILE (moiS."Eti) S. Tlr OF C RP~hT S PESO0 COVERED STRATOSPHERIC TURBULENCE AND VERTICAL EFFECTIVE DIFFUSION COEFFICIENTS...that CAT plays a prominent role in vertical transport in the stratosphere. I ~1 Unclassified t FUrs,*Tv C , Uq C ~ml .. at ’r *n he.. a* U I Department...phenomenon. Thorpe himself refers (1973) to underwater K-H as "underwater CAT." ____ ____ ____WE006 SflJGLE ( SPAD M LAVER 4" Ri" i0 15 0t (m’iJr
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NREL MOIS Data for NWEI Azura May 2016
Eric Nelson
2016-06-07
NREL MOIS data files for the Azura grid-connected deployment at the 30-meter berth of the US Navy's Wave Energy Test Site (WETS 30m Site) at the Kaneohe Marine Corps Base Hawaii (MCBH) on the windward (northeast) coast of the island of Oahu, HI. See general documentation describing specifics of the data files and formats in a separate NREL submission (linked below). Note: DMS, load cell, and analog data files were not collected during the month of May, 2016 due to a controller software problem that was resolved in early June 2016.
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Spacecraft transfer trajectory design exploiting resonant orbits in multi-body environments
NASA Astrophysics Data System (ADS)
Vaquero Escribano, Tatiana Mar
Historically, resonant orbits have been employed in mission design for multiple planetary flyby trajectories and, more recently, as a source of long-term orbital stability. For instance, in support of a mission concept in NASA's Outer Planets Program, the Jupiter Europa Orbiter spacecraft is designed to encounter two different resonances with Europa during the 'endgame' phase, leading to Europa orbit insertion on the final pass. In 2011, the Interstellar Boundary Explorer spacecraft was inserted into a stable out-of-plane lunar-resonant orbit, the first of this type for a spacecraft in a long-term Earth orbit. However, resonant orbits have not yet been significantly explored as transfer mechanisms between non-resonant orbits in multi-body systems. This research effort focuses on incorporating resonant orbits into the design process to potentially enable the construction of more efficient or even novel transfer scenarios. Thus, the goals in this investigation are twofold: i) to expand the orbit architecture in multi-body environments by cataloging families of resonant orbits, and ii) to assess the role of such families in the design of transfer trajectories with specific patterns and itineraries. The benefits and advantages of employing resonant orbits in the design process are demonstrated through a variety of astrodynamics applications in several multi-body systems. In the Earth-Moon system, locally optimal transfer trajectories from low Earth orbit to selected libration point orbits are designed by leveraging conic arcs and invariant manifolds associated with resonant orbits. Resonant manifolds in the Earth-Moon system offer trajectories that tour the entire space within reasonable time intervals, facilitating the design of libration point orbit tours as well as Earth-Moon cyclers. In the Saturnian system, natural transitions between resonant and libration point orbits are sought and the problem of accessing Hyperion from orbits that are resonant with Titan is also examined. To add versatility to the proposed design method, a system translation technique enables the straightforward transition of solutions from the Earth-Moon system to any Sun-planet or planet-moon three-body system. The circular restricted three-body problem serves as a basis to quickly generate solutions that meet specific requirements, but candidate transfer trajectories are then transitioned to an ephemeris model for validation.
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NASA Astrophysics Data System (ADS)
Song, Young-Joo; Bae, Jonghee; Kim, Young-Rok; Kim, Bang-Yeop
2017-12-01
To ensure the successful launch of the Korea pathfinder lunar orbiter (KPLO) mission, the Korea Aerospace Research Institute (KARI) is now performing extensive trajectory design and analysis studies. From the trajectory design perspective, it is crucial to prepare contingency trajectory options for the failure of the first lunar brake or the failure of the first lunar orbit insertion (LOI) maneuver. As part of the early phase trajectory design and analysis activities, the required time of flight (TOF) and associated delta-V magnitudes for each recovery maneuver (RM) to recover the KPLO mission trajectory are analyzed. There are two typical trajectory recovery options, direct recovery and low energy recovery. The current work is focused on the direct recovery option. Results indicate that a quicker execution of the first RM after the failure of the first LOI plays a significant role in saving the magnitudes of the RMs. Under the conditions of the extremely tight delta-V budget that is currently allocated for the KPLO mission, it is found that the recovery of the KPLO without altering the originally planned mission orbit (a 100 km circular orbit) cannot be achieved via direct recovery options. However, feasible recovery options are suggested within the boundaries of the currently planned delta-V budget. By changing the shape and orientation of the recovered final mission orbit, it is expected that the KPLO mission may partially pursue its scientific mission after successful recovery, though it will be limited.
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Deep Space Network Capabilities for Receiving Weak Probe Signals
NASA Technical Reports Server (NTRS)
Asmar, Sami; Johnston, Doug; Preston, Robert
2005-01-01
Planetary probes can encounter mission scenarios where communication is not favorable during critical maneuvers or emergencies. Launch, initial acquisition, landing, trajectory corrections, safing. Communication challenges due to sub-optimum antenna pointing or transmitted power, amplitude/frequency dynamics, etc. Prevent lock-up on signal and extraction of telemetry. Examples: loss of Mars Observer, nutation of Ulysses, Galileo antenna, Mars Pathfinder and Mars Exploration Rovers Entry, Descent, and Landing, and the Cassini Saturn Orbit Insertion. A Deep Space Network capability to handle such cases has been used successfully to receive signals to characterize the scenario. This paper will describe the capability and highlight the cases of the critical communications for the Mars rovers and Saturn Orbit Insertion and preparation radio tracking of the Huygens probe at (non-DSN) radio telescopes.
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NASA launches dual Dynamics Explorer spacecraft
NASA Technical Reports Server (NTRS)
1981-01-01
A Delta launch vehicle was used to insert Dynamics Explorer A into a highly elliptical polar orbit, ranging from 675 to 24,945 km, and Dynamics Explorer B satellite into a low polar orbit, ranging from 306 to 1,300 km. The two spacecraft are designed to provide specific knowledge about the interaction of energy, electric currents, electric fields, and plasmas between the magnetosphere, the ionosphere, and the atmosphere.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Vallado, David A.; Cefola, Paul J.; Kiziah, Rex R.
Here, observing geosynchronous satellites has numerous applications. Lighting conditions near the equinoxes routinely cause problems for traditional observations of sensors near the equator – the solar exclusion. We investigate using sensors on satellites (in polar and high- altitude orbits) to observe satellites that are in geosynchronous orbit. It is hoped that these satellite configurations will alleviate many of these problems. Assessing the orbit insertion and station-keeping requirements are important to understand. We summarize the literature to understand the relevant perturbing forces and assess the delta-v requirements.
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Vallado, David A.; Cefola, Paul J.; Kiziah, Rex R.; ...
2016-09-09
Here, observing geosynchronous satellites has numerous applications. Lighting conditions near the equinoxes routinely cause problems for traditional observations of sensors near the equator – the solar exclusion. We investigate using sensors on satellites (in polar and high- altitude orbits) to observe satellites that are in geosynchronous orbit. It is hoped that these satellite configurations will alleviate many of these problems. Assessing the orbit insertion and station-keeping requirements are important to understand. We summarize the literature to understand the relevant perturbing forces and assess the delta-v requirements.
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Early Mission Maneuver Operations for the Deep Space Climate Observatory
NASA Technical Reports Server (NTRS)
Roberts, Craig; Case, Sara; Reagoso, John
2015-01-01
DSCOVR Lissajous Orbit sized such that orbit track never extends beyond 15 degrees from Earth-Sun line (as seen from Earth). Requiring delta-V maneuvers, control orbit to obey a Solar Exclusion Zone (SEZ) cone of half-angle 4 degrees about the Earth-Sun line. Spacecraft should never be less than 4 degrees from solar center as seen from Earth. Following Lissajous Orbit Insertion (LOI), DSCOVR should be in an opening phase that just skirts the 4-degree SEZ. Maximizes time to the point where a closing Lissajous will require avoidance maneuvers to keep it out of the SEZ. Station keeping maneuvers should take no more than 15 minutes
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Addition and subtraction operation of optical orbital angular momentum with dielectric metasurfaces
NASA Astrophysics Data System (ADS)
Yi, Xunong; Li, Ying; Ling, Xiaohui; Liu, Yachao; Ke, Yougang; Fan, Dianyuan
2015-12-01
In this work, we propose a simple approach to realize addition and subtraction operation of optical orbital angular momentum (OAM) based on dielectric metasurfaces. The spin-orbit interaction of light in spatially inhomogeneous and anisotropic metasurfaces results in the spin-to-orbital angular momentum conversion. The subtraction system of OAM consists of two cascaded metasurfaces, while the addition system of OAM is constituted by inserting a half waveplate (HWP) between the two metasurfaces. Our experimental results are in good agreement with the theoretical calculation. These results could be useful for OAM-carrying beams applied in optical communication, information processing, etc.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Soukup, J.; Koren, H.S.; Becker, S.
1993-01-01
The study was performed to evaluate the effect of ozone (O3) exposure at 1 ppm for 2 hr on the susceptibility/resistance of adult human alveolar macrophages (AM) to infection with respiratory syncytial virus (RSV) in vitro and on RSV-induced cytokine production by the AM. AM were first exposed to O3 or to filtered air and then infected with RSV at multiplicities of infection (m.o.i.) of 0.1 1.0 and 10. The percentage RSV-infected AM and the amount of infectious virus released by the cells were determined at Days 2 and 4 after infection. Interleukin (IL)-1, IL-6, and tumor necrosis factor (TNF)more » levels in the supernatants were determined on Day 2. No difference in the percentage infected AM or in the amount of infectious RSV produced was found between control and O3-exposed cultures. However, O3-exposed AM infected with RSV at m.o.i. 1 produced less IL-1 in response to RSV infection than control AM:63.6 pg/ml compared with 98.5 pg/ml. No difference in IL-1 was seen with m.o.i. 10. IL-6 levels were also decreased, but only after infection with m.o.i. 0.1. At this level of infection 830 pg/ml was produced by control AM as compared to 468.2 pg/ml by O3-exposed AM. TNF production was unaffected by O3 at all multiplicities of infection. (Copyright (c) 1993 by Academic Press, Inc.)« less
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Zlabek, Vladimir; Burkina, Viktoriia; Borrisser-Pairó, Francesc; Sakalli, Sidika; Zamaratskaia, Galia
2016-05-01
We studied the in vitro metabolism of 3-methylindole (3MI) in hepatic microsomes from fish. Hepatic microsomes from juvenile and adult carp (Cyprinus carpio) and rainbow trout (Oncorhynchus mykiss) were included in the study. Incubation of 3MI with hepatic microsomes revealed the time-dependent formation of two major metabolites, 3-methyloxindole (3MOI) and indole-3-carbinol (I3C). The rate of 3MOI production was similar in both species at both ages. No differences in kinetic parameters were observed (p = 0.799 for Vmax, and p = 0.809 for Km). Production of I3C was detected only in the microsomes from rainbow trout. Km values were similar in juvenile and adult fish (p = 0.957); Vmax was higher in juvenile rainbow trout compared with adults (p = 0.044). In rainbow trout and carp, ellipticine reduced formation of 3MOI up to 53.2% and 81.9% and ketoconazole up to 65.8% and 91.3%, respectively. The formation of I3C was reduced by 53.7% and 51.5% in the presence of the inhibitors ellipticine and ketoconazole, respectively. These findings suggest that the CYP450 isoforms CYP1A and CYP3A are at least partly responsible for 3MI metabolism. In summary, 3MI is metabolised in fish liver to 3MOI and I3C by CYP450, and formation of these metabolites might be species-dependent. Copyright © 2016 Elsevier Ltd. All rights reserved.
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Moments of inclination error distribution computer program
NASA Technical Reports Server (NTRS)
Myler, T. R.
1981-01-01
A FORTRAN coded computer program is described which calculates orbital inclination error statistics using a closed-form solution. This solution uses a data base of trajectory errors from actual flights to predict the orbital inclination error statistics. The Scott flight history data base consists of orbit insertion errors in the trajectory parameters - altitude, velocity, flight path angle, flight azimuth, latitude and longitude. The methods used to generate the error statistics are of general interest since they have other applications. Program theory, user instructions, output definitions, subroutine descriptions and detailed FORTRAN coding information are included.
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NASA Technical Reports Server (NTRS)
Crouch, Myscha; Carswell, Bill; Farmer, Jeff; Rose, Fred; Tidwell, Paul
1999-01-01
The Material Science Research Rack 1 (MSRR-1) of the Material Science Research Facility (MSRF) contains an Experiment Module (EM) being developed collaboratively by NASA and the European Space Agency (ESA). This NASA/ESA EM will accommodate several different removable and replaceable Module Inserts (MIs) which are installed on orbit. Two of the NASA MIs being developed for specific material science investigations are described herein.
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The Kinetics of Swinging a Baseball Bat.
Crisco, Joseph J; Osvalds, Nikolas J; Rainbow, Michael J
2018-04-13
The purpose of this study was to compute the three-dimensional kinetics required to swing three youth baseball bats of varying moments of inertia (MOI). 306 swings by 22 male players (13-18 yrs.) were analyzed. Inverse dynamics with respect to the batter's hands were computed given the known kinematics and physical properties of the bats. We found that peak force increased with larger bat MOI and was strongly correlated with bat tip speed. In contrast, peak moments were weakly correlated with bat MOI and bat tip speed. Throughout the swing, the force applied to the bat was dominated by a component aligned with the long axis of the bat and directed away from the bat knob, while the moment applied to the bat was minimal until just prior to ball impact. These results indicate that players act to mostly "pull" the bat during their swing until just prior to ball impact, at which point they rapidly increase the moment on the bat. This kinetic analysis provides novel insight into the forces and moments used to swing baseball bats.
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Enhanced magneto-optical imaging of internal stresses in the removed surface layer
NASA Astrophysics Data System (ADS)
Agalidi, Yuriy; Kozhukhar, Pavlo; Levyi, Sergii; Turbin, Dmitriy
2015-10-01
The paper describes a software method of reconstructing the state of the removed surface layer by visualising internal stresses in the underlying layers of the sample. Such a problem typically needs to be solved as part of forensic investigation that aims to reveal original marking of a sample with removed surface layer. For example, one may be interested in serial numbers of weapons or vehicles that had the surface layer of metal removed from the number plate. Experimental results of studying gradient internal stress fields in ferromagnetic sample using the NDI method of magneto-optical imaging (MOI) are presented. Numerical modelling results of internal stresses enclosed in the surface marking region are analysed and compared to the experimental results of magneto-optical imaging (MOI). MOI correction algorithm intended for reconstructing internal stress fields in the removed surface layer by extracting stresses retained by the underlying layers is described. Limiting ratios between parameters of a marking font are defined for the considered correction algorithm. Enhanced recognition properties for hidden stresses left by marking symbols are experimentally verified and confirmed.
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Ritter, Birgit; Kilian, Petra; Reboll, Marc Rene; Resch, Klaus; DiStefano, Johanna Kay; Frank, Ronald; Beil, Winfried; Nourbakhsh, Mahtab
2011-02-01
Interleukin-8 (IL-8) plays a central role in the pathogenesis of Helicobacter pylori infection. We used four different H. pylori strains isolated from patients with gastritis or duodenal ulcer disease to examine their differential effects on signaling pathways and IL-8 gene response in gastric epithelial cells. IL-8 mRNA level is elevated in response to high (100) multiplicity of infection (MOI) independent of cagA, vacA, and dupA gene characteristics. By lower MOIs (1 or 10), only cagA ( + ) strains significantly induce IL-8 gene expression. This is based on differential regulation of IL-8 promoter activity. Analysis of intracellular signaling pathways indicates that H. pylori clinical isolates induce IL-8 gene transcription through NF-κB p65, but by a MOI-dependent differential activation of MAPK pathways. Thus, the major virulence factors of H. pylori CagA, VacA, and DupA might play a minor role in the level of IL-8 gene response to a high bacterial load.
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Feasibility analysis of cislunar flight using the Shuttle Orbiter
NASA Technical Reports Server (NTRS)
Haynes, Davy A.
1991-01-01
A first order orbital mechanics analysis was conducted to examine the possibility of utilizing the Space Shuttle Orbiter to perform payload delivery missions to lunar orbit. In the analysis, the earth orbit of departure was constrained to be that of Space Station Freedom. Furthermore, no enhancements of the Orbiter's thermal protection system were assumed. Therefore, earth orbit insertion maneuvers were constrained to be all propulsive. Only minimal constraints were placed on the lunar orbits and no consideration was given to possible landing sites for lunar surface payloads. The various phases and maneuvers of the mission are discussed for both a conventional (Apollo type) and an unconventional mission profile. The velocity impulses needed, and the propellant masses required are presented for all of the mission maneuvers. Maximum payload capabilities were determined for both of the mission profiles examined. In addition, other issues relating to the feasibility of such lunar shuttle missions are discussed. The results of the analysis indicate that the Shuttle Orbiter would be a poor vehicle for payload delivery missions to lunar orbit.
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Preliminary concepts for a solar electric orbit raising experiment
DOE Office of Scientific and Technical Information (OSTI.GOV)
Cohen, R.B.; Penn, J.P.; Janson, S.W.
1989-01-01
Some preliminary concepts for a solar electric orbit raising demonstration that will show technological readiness for the development of operational Electric Orbital Transfer Vehicles (EOTVs) are outlined. These ideas could serve as a template for the proposed Electric Insertion Transfer Experiment (ELITE). At this moment, ELITE is not a funded program. Concepts are presented for a solar electric orbit raising demonstration, for ELITE, and for the path from the proposed ELITE to a future operational EOTV. A brief discussion of the benefits to be derived from the use of EOTVs, the conceptual organization of the ELITE team, the key technologiesmore » for EOTV and ELITE, and some preliminary options for the orbit raising vehicle and representative missions are provided.« less
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Conceptual study and key technology development for Mars Aeroflyby sample collection
NASA Astrophysics Data System (ADS)
Fujita, K.; Ozawa, T.; Okudaira, K.; Mikouchi, T.; Suzuki, T.; Takayanagi, H.; Tsuda, Y.; Ogawa, N.; Tachibana, S.; Satoh, T.
2014-01-01
Conceptual study of Mars Aeroflyby Sample Collection (MASC) is conducted as a part of the next Mars exploration mission currently entertained in Japan Aerospace Exploration Agency. In the mission scenario, an atmospheric entry vehicle is flown into the Martian atmosphere, collects the Martian dust particles as well as atmospheric gases during the guided hypersonic flight, exits the Martian atmosphere, and is inserted into a parking orbit from which a return system departs for the earth to deliver the dust and gas samples. In order to accomplish a controlled flight and a successful orbit insertion, aeroassist orbit transfer technologies are introduced into the guidance and control system. System analysis is conducted to assess the feasibility and to make a conceptual design, finding that the MASC system is feasible at the minimum system mass of 600 kg approximately. The aerogel, which is one of the candidates for the dust sample collector, is assessed by arcjet heating tests to examine its behavior when exposed to high-temperature gases, as well as by particle impingement tests to evaluate its dust capturing capability.
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Optical Navigation Simulation and Performance Analysis for Osiris-Rex Proximity Operations
NASA Technical Reports Server (NTRS)
Jackman, Coralie D.; Nelson, Derek S.; Mccarthy, Leilah K.; Liounis, Andrew J.; Leonard, Jason M.; Antreasian, Peter G.; Getzandanner, Kenneth M.; Moreau, Michael C.
2017-01-01
The OSIRIS-REx mission timeline with OpNav milestones is presented in Figure 1. The first three proximity operations (ProxOps) mission phases focus on Navigation. During these phases, OSIRIS-REx approaches Bennu, conducts equatorial and polar flybys in Preliminary Survey, and inserts into the first mission orbit: Orbit A. During these phases, the OpNav techniques evolve from point-source to resolved-body centroiding to landmark tracking.
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Slow Orbit Feedback at the ALS Using Matlab
DOE Office of Scientific and Technical Information (OSTI.GOV)
Portmann, G.
1999-03-25
The third generation Advanced Light Source (ALS) produces extremely bright and finely focused photon beams using undulatory, wigglers, and bend magnets. In order to position the photon beams accurately, a slow global orbit feedback system has been developed. The dominant causes of orbit motion at the ALS are temperature variation and insertion device motion. This type of motion can be removed using slow global orbit feedback with a data rate of a few Hertz. The remaining orbit motion in the ALS is only 1-3 micron rms. Slow orbit feedback does not require high computational throughput. At the ALS, the globalmore » orbit feedback algorithm, based on the singular valued decomposition method, is coded in MATLAB and runs on a control room workstation. Using the MATLAB environment to develop, test, and run the storage ring control algorithms has proven to be a fast and efficient way to operate the ALS.« less
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The result of Venus Orbit Insertion of Akatsuki on December 7th, 2015
NASA Astrophysics Data System (ADS)
Sugiyama, K. I.; Nakamura, M.; Imamura, T.; Ishii, N.; Abe, T.; Kawakatsu, Y.; Hirose, C.; Satoh, T.; Suzuki, M.; Ueno, M.; Yamazaki, A.; Iwagami, N.; Watanabe, S.; Taguchi, M.; Fukuhara, T.; Takahashi, Y.; Yamada, M.; Imai, M.; Ohtsuki, S.; Uemizu, K.; Hashimoto, G. L.; Takagi, M.; Matsuda, Y.; Ogohara, K.; Sato, N.; Kasaba, Y.; Kouyama, T.; Hirata, N.; Nakamura, R.; Yamamoto, Y.; Horinouchi, T.; Yamamoto, M.; Hayashi, Y. Y.; Nakatsuka, J.; Kashimura, H.; Sakanoi, T.; Ando, H.; Murakami, S. Y.; Sato, T.; Takagi, S.; Nakajima, K.; Peralta, J.; Lee, Y. J.
2015-12-01
Japan launched Venus Climate Orbiter 'Akatsuki' (JAXA's mission code name: PLANET-C) to observe the dynamics of the Venus atmosphere globally and clarify the mechanism of the atmospheric circulation. The launch was on May 21st , 2010 from the Tanegashima Space Center. The cruise to Venus was smooth, however, the first Venus Orbit Insertion (VOI) trial on December 7th, 2010 tuned out to be a failure. Later Akatsuki has been orbiting the sun. Fortunately we keep the spacecraft in a healthy condition and surprisingly we have found another chance to let this spacecraft to meet Venus in 2015. Next VOI trial will be done on December 7th, 2015 and we report the result of this operation at this AGU meeting. This mission is planed to answer the question described below. The radius of the Earth and Venus are almost the same. In addition the radiation from the sun is also almost the same. The climates of these planets, however, are much different. For example, the strong zonal wind is observed on Venus with the period of 4 days, where Venus rotates westward with the period of 243 days. The wind speed is about 100 m s-1. This is called super rotation. We will investigate from data from Akatsuki what attributes to the difference of the climates between Earth and Venus. AKATSUKI was designed for remote sensing from an equatorial, elliptical orbit to tract the atmospheric motion at different altitudes using 5 cameras (3xIR, UV, Visible) and by the radio occultation technique. The first VOI has failed due to a malfunction of the propulsion system. The check valve between the helium tank and the fuel tank was blocked by an unexpected salt formation during the cruising from the Earth to Venus. As a result the main engine (orbital maneuvering engine, OME) became oxidizer-rich and fuel-poor condition, which led to an abnormal combustion in the engine with high temperature, and finally the engine was broken. We decide to use RCS thrusters for Trajectory Control Maneuvers' (TCMs) and finally insert Akatsuki into the orbit. Total thrust force of 4 RCS thrusters is 20 % of that of the main thruster and the orbit after VOI-R becomes a larger ellipse (apoapsis altitude will be finally 3.2x106km ) than the original plan in 2010. We have already done major 6 TCMs before July 31st, 2015 to let the spacecraft to meet Venus in December.
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On Choosing a Rational Flight Trajectory to the Moon
NASA Astrophysics Data System (ADS)
Gordienko, E. S.; Khudorozhkov, P. A.
2017-12-01
The algorithm for choosing a trajectory of spacecraft flight to the Moon is discussed. The characteristic velocity values needed for correcting the flight trajectory and a braking maneuver are estimated using the Monte Carlo method. The profile of insertion and flight to a near-circular polar orbit with an altitude of 100 km of an artificial lunar satellite (ALS) is given. The case of two corrections applied during the flight and braking phases is considered. The flight to an ALS orbit is modeled in the geocentric geoequatorial nonrotating coordinate system with the influence of perturbations from the Earth, the Sun, and the Moon factored in. The characteristic correction costs corresponding to corrections performed at different time points are examined. Insertion phase errors, the errors of performing the needed corrections, and the errors of determining the flight trajectory parameters are taken into account.
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NASA Astrophysics Data System (ADS)
Matlock, Richard S.; Feig, Jason R.; Dickey, Michael R.
A program called the Electric Insertion Transfer Experiment or ELITE for demonstrating the use of solar-electric propulsion is proposed and described. The ELITE concept is based on the use of solar propulsion for the orbit-raising mode of an electric orbital-transfer vehicle (EOTV) and examines issues associated with electric thrusters. Experimental subsystems are compared including arcjet, ion, and magnetoplasmadynamic thrusters, and the design and performance impacts on EOTVs are listed. The ELITE experiment is shown to be capable of studying such issues as the plume-to-plume interaction of multiple thrusters, the contamination of spacecraft components, potential interferences from radio-frequency transmissions, and the charging of spacecraft surfaces. Solar propulsion can be studied within the context of the ELITE program to demonstrate its potential as both enhancing and enabling technology.
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STS-122 Crew Members during Post Insertion / Deorbit Prepreparation in Building 9 NW
2007-03-20
JSC2007-E-14482 (20 March 2007) --- Jerry L. Ross (center), chief, vehicle integration test office, poses for a photo with astronauts Stanley G. Love (left), European Space Agency's (ESA) Hans Schlegel, Leland D. Melvin and Rex J. Walheim, STS-122 mission specialists, as they prepare for a post insertion/de-orbit training session in one of the full-scale trainers (out of frame) in the Space Vehicle Mockup Facility at Johnson Space Center.
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Mission design for a halo orbiter of the earth
NASA Technical Reports Server (NTRS)
Farquhar, R. W.; Muhonen, D. P.; Richardson, D. L.
1976-01-01
The International Sun-Earth Explorer (ISEE) scientific satellite to be stationed in 1978 in the vicinity of the sun-earth interior libration point to continuously monitor the space between the sun and the earth, including the distant geomagnetic tail is described. Orbit selection considerations for the ISEE-C are discussed along with stationkeeping requirements and fuel-optimal trajectories. Due to the alignment of the interior libration point with the sun as viewed from the earth, it will be necessary to place the satellite into a 'halo orbit' around the libration point, in order to eliminate solar interference with down-link telemetry. Parametric data for transfer trajectories between an earth parking orbit (altitude about 185 km) and a libration-point orbit are presented. It is shown that the insertion magnitude required for placing a satellite into an acceptable halo orbit is rather modest.
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Suzuki, K; Barbiellini, B; Orikasa, Y; Go, N; Sakurai, H; Kaprzyk, S; Itou, M; Yamamoto, K; Uchimoto, Y; Wang, Yung Jui; Hafiz, H; Bansil, A; Sakurai, Y
2015-02-27
We present an incisive spectroscopic technique for directly probing redox orbitals based on bulk electron momentum density measurements via high-resolution x-ray Compton scattering. Application of our method to spinel Li_{x}Mn_{2}O_{4}, a lithium ion battery cathode material, is discussed. The orbital involved in the lithium insertion and extraction process is shown to mainly be the oxygen 2p orbital. Moreover, the manganese 3d states are shown to experience spatial delocalization involving 0.16±0.05 electrons per Mn site during the battery operation. Our analysis provides a clear understanding of the fundamental redox process involved in the working of a lithium ion battery.
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Prediction of bone strength at the distal tibia by HR-pQCT and DXA.
Popp, Albrecht W; Windolf, Markus; Senn, Christoph; Tami, Andrea; Richards, R Geoff; Brianza, Stefano; Schiuma, Damiano
2012-01-01
Areal bone mineral density (aBMD) at the distal tibia, measured at the epiphysis (T-EPI) and diaphysis (T-DIA), is predictive for fracture risk. Structural bone parameters evaluated at the distal tibia by high resolution peripheral quantitative computed tomography (HR-pQCT) displayed differences between healthy and fracture patients. With its simple geometry, T-DIA may allow investigating the correlation between bone structural parameter and bone strength. Anatomical tibiae were examined ex vivo by DXA (aBMD) and HR-pQCT (volumetric BMD (vBMD) and bone microstructural parameters). Cortical thickness (CTh) and polar moment of inertia (pMOI) were derived from DXA measurements. Finally, an index combining material (BMD) and mechanical property (polar moment of inertia, pMOI) was defined and analyzed for correlation with torque at failure and stiffness values obtained by biomechanical testing. Areal BMD predicted the vBMD at T-EPI and T-DIA. A high correlation was found between aBMD and microstructural parameters at T-EPIas well as between aBMD and CTh at T-DIA. Finally, at T-DIA both indexes combining BMD and pMOI were strongly and comparably correlated with torque at failure and bone stiffness. Ex vivo, at the distal tibial diaphysis, a novel index combining BMD and pMOI, which can be calculated directly from a single DXA measurement, predicted bone strength and stiffness better than either parameter alone and with an order of magnitude comparable to that of HR-pQCT. Whether this index is suitable for better prediction of fracture risk in vivo deserves further investigation. Copyright © 2011 Elsevier Inc. All rights reserved.
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Fola, Abebe A; Harrison, G L Abby; Hazairin, Mita Hapsari; Barnadas, Céline; Hetzel, Manuel W; Iga, Jonah; Siba, Peter M; Mueller, Ivo; Barry, Alyssa E
2017-03-01
Abstract Plasmodium falciparum and Plasmodium vivax have varying transmission dynamics that are informed by molecular epidemiology. This study aimed to determine the complexity of infection and genetic diversity of P. vivax and P. falciparum throughout Papua New Guinea (PNG) to evaluate transmission dynamics across the country. In 2008-2009, a nationwide malaria indicator survey collected 8,936 samples from all 16 endemic provinces of PNG. Of these, 892 positive P. vivax samples were genotyped at PvMS16 and PvmspF3 , and 758 positive P. falciparum samples were genotyped at Pfmsp2 . The data were analyzed for multiplicity of infection (MOI) and genetic diversity. Overall, P. vivax had higher polyclonality (71%) and mean MOI (2.32) than P. falciparum (20%, 1.39). These measures were significantly associated with prevalence for P. falciparum but not for P. vivax . The genetic diversity of P. vivax ( PvMS16 : expected heterozygosity = 0.95, 0.85-0.98; PvMsp1F3 : 0.78, 0.66-0.89) was higher and less variable than that of P. falciparum ( Pfmsp2 : 0.89, 0.65-0.97). Significant associations of MOI with allelic richness (rho = 0.69, P = 0.009) and expected heterozygosity (rho = 0.87, P < 0.001) were observed for P. falciparum . Conversely, genetic diversity was not correlated with polyclonality nor mean MOI for P. vivax . The results demonstrate higher complexity of infection and genetic diversity of P. vivax across the country. Although P. falciparum shows a strong association of these parameters with prevalence, a lack of association was observed for P. vivax and is consistent with higher potential for outcrossing of this species.
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Ahmed Ismail, Hodan; Ribacke, Ulf; Reiling, Linda; Normark, Johan; Egwang, Tom; Kironde, Fred; Beeson, James G.; Wahlgren, Mats
2013-01-01
Malaria can present itself as an uncomplicated or severe disease. We have here studied the quantity and quality of antibody responses against merozoite antigens, as well as multiplicity of infection (MOI), in children from Uganda. We found higher levels of IgG antibodies toward erythrocyte-binding antigen EBA181, MSP2 of Plasmodium falciparum 3D7 and FC27 (MSP2-3D7/FC27), and apical membrane antigen 1 (AMA1) in patients with uncomplicated malaria by enzyme-linked immunosorbent assay (ELISA) but no differences against EBA140, EBA175, MSP1, and reticulocyte-binding protein homologues Rh2 and Rh4 or for IgM against MSP2-3D7/FC27.Patients with uncomplicated malaria were also shown to have higher antibody affinities for AMA1 by surface plasmon resonance (SPR). Decreased invasion of two clinical P. falciparum isolates in the presence of patient plasma correlated with lower initial parasitemia in the patients, in contrast to comparisons of parasitemia to ELISA values or antibody affinities, which did not show any correlations. Analysis of the heterogeneity of the infections revealed a higher MOI in patients with uncomplicated disease, with the P. falciparum K1 MSP1 (MSP1-K1) and MSP2-3D7 being the most discriminative allelic markers. Higher MOIs also correlated positively with higher antibody levels in several of the ELISAs. In conclusion, certain antibody responses and MOIs were associated with differences between uncomplicated and severe malaria. When different assays were combined, some antibodies, like those against AMA1, seemed particularly discriminative. However, only decreased invasion correlated with initial parasitemia in the patient, signaling the importance of functional assays in understanding development of immunity against malaria and in evaluating vaccine candidates. PMID:23740926
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Mission Design for the Lunar Reconnaissance Orbiter
NASA Technical Reports Server (NTRS)
Beckman, Mark
2007-01-01
The Lunar Reconnaissance Orbiter (LRO) will be the first mission under NASA's Vision for Space Exploration. LRO will fly in a low 50 km mean altitude lunar polar orbit. LRO will utilize a direct minimum energy lunar transfer and have a launch window of three days every two weeks. The launch window is defined by lunar orbit beta angle at times of extreme lighting conditions. This paper will define the LRO launch window and the science and engineering constraints that drive it. After lunar orbit insertion, LRO will be placed into a commissioning orbit for up to 60 days. This commissioning orbit will be a low altitude quasi-frozen orbit that minimizes stationkeeping costs during commissioning phase. LRO will use a repeating stationkeeping cycle with a pair of maneuvers every lunar sidereal period. The stationkeeping algorithm will bound LRO altitude, maintain ground station contact during maneuvers, and equally distribute periselene between northern and southern hemispheres. Orbit determination for LRO will be at the 50 m level with updated lunar gravity models. This paper will address the quasi-frozen orbit design, stationkeeping algorithms and low lunar orbit determination.
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Orbital Maneuvering system design evolution
NASA Technical Reports Server (NTRS)
Gibson, C.; Humphries, C.
1985-01-01
Preliminary design considerations and changes made in the baseline space shuttle orbital maneuvering system (OMS) to reduce cost and weight are detailed. The definition of initial subsystem requirements, trade studies, and design approaches are considered. Design features of the engine, its injector, combustion chamber, nozzle extension and bipropellant valve are illustrated and discussed. The current OMS consists of two identical pods that use nitrogen tetroxide (NTO) and monomethylhydrazine (MMH) propellants to provide 1000 ft/sec of delta velocity for a payload of 65,000 pounds. Major systems are pressurant gas storage and control, propellant storage supply and quantity measurement, and the rocket engine, which includes a bipropellant valve, an injector/thrust chamber, and a nozzle. The subsystem provides orbit insertion, circularization, and on orbit and deorbit capability for the shuttle orbiter.
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Ballistic mode Mercury orbiter missions.
NASA Technical Reports Server (NTRS)
Hollenbeck, G. R.
1973-01-01
The MVM'73 Mercury flyby mission will initiate exploration of this unique planet. No firm plans for follow-on investigations have materialized due to the difficult performance requirements of the next logical step, an orbiter mission. Previous investigations of ballistic mode flight opportunities have indicated requirements for a Saturn V class launch vehicle. Consequently, most recent effort has been oriented to use of solar electric propulsion. More comprehensive study of the ballistic flight mode utilizing Venus gravity-assist has resulted in identification of timely high-performance mission opportunities compatible with programmed launch vehicles and conventional spacecraft propulsion technologies. A likely candidate for an initial orbiter mission is a 1980 opportunity which offers net orbiter spacecraft mass of about 435 kg with the Titan IIIE/Centaur launch vehicle and single stage solid propulsion for orbit insertion.
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Safe operating conditions for NSLS-II Storage Ring Frontends commissioning
DOE Office of Scientific and Technical Information (OSTI.GOV)
Seletskiy, S.; Amundsen, C.; Ha, K.
2015-04-02
The NSLS-II Storage Ring Frontends are designed to safely accept the synchrotron radiation fan produced by respective insertion device when the electron beam orbit through the ID is locked inside the predefined Active Interlock Envelope. The Active Interlock is getting enabled at a particular beam current known as AI safe current limit. Below such current the beam orbit can be anywhere within the limits of the SR beam acceptance. During the FE commissioning the beam orbit is getting intentionally disturbed in the particular ID. In this paper we explore safe operating conditions for the Frontends commissioning.
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Seasat. Volume 3: Ground systems
NASA Technical Reports Server (NTRS)
Pounder, E. (Editor)
1980-01-01
The Seasat Project was a feasibility demonstration of the use of orbital remote sensing for global ocean observation. The satellite was launched in June of 1978 and was operated successfully until October 1978. A massive electrical failure occurred in the power system, terminating the mission prematurely. The ground systems using during the mission life are discussed. Descriptions of the operating organization, the system elements, and the testing program are included. The various phases of the mission: launch and orbit insertion; cruise; and calibration are discussed. A special section is included on the orbit maneuver activites. Operations during the satellite failure are reviewed and summarized.
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Non-Intrusive Magneto-Optic Detecting System for Investigations of Air Switching Arcs
NASA Astrophysics Data System (ADS)
Zhang, Pengfei; Zhang, Guogang; Dong, Jinlong; Liu, Wanying; Geng, Yingsan
2014-07-01
In current investigations of electric arc plasmas, experiments based on modern testing technology play an important role. To enrich the testing methods and contribute to the understanding and grasping of the inherent mechanism of air switching arcs, in this paper, a non-intrusive detecting system is described that combines the magneto-optic imaging (MOI) technique with the solution to inverse electromagnetic problems. The detecting system works in a sequence of main steps as follows: MOI of the variation of the arc flux density over a plane, magnetic field information extracted from the magneto-optic (MO) images, arc current density distribution and spatial pattern reconstruction by inverting the resulting field data. Correspondingly, in the system, an MOI set-up is designed based on the Faraday effect and the polarization properties of light, and an intelligent inversion algorithm is proposed that involves simulated annealing (SA). Experiments were carried out for high current (2 kA RMS) discharge cases in a typical low-voltage switchgear. The results show that the MO detection system possesses the advantages of visualization, high resolution and response, and electrical insulation, which provides a novel diagnostics tool for further studies of the arc.
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Zhong, Daibin; Lo, Eugenia; Wang, Xiaoming; Yewhalaw, Delenasaw; Zhou, Guofa; Atieli, Harrysone E; Githeko, Andrew; Hemming-Schroeder, Elizabeth; Lee, Ming-Chieh; Afrane, Yaw; Yan, Guiyun
2018-05-02
Parasite genetic diversity and multiplicity of infection (MOI) affect clinical outcomes, response to drug treatment and naturally-acquired or vaccine-induced immunity. Traditional methods often underestimate the frequency and diversity of multiclonal infections due to technical sensitivity and specificity. Next-generation sequencing techniques provide a novel opportunity to study complexity of parasite populations and molecular epidemiology. Symptomatic and asymptomatic Plasmodium vivax samples were collected from health centres/hospitals and schools, respectively, from 2011 to 2015 in Ethiopia. Similarly, both symptomatic and asymptomatic Plasmodium falciparum samples were collected, respectively, from hospitals and schools in 2005 and 2015 in Kenya. Finger-pricked blood samples were collected and dried on filter paper. Long amplicon (> 400 bp) deep sequencing of merozoite surface protein 1 (msp1) gene was conducted to determine multiplicity and molecular epidemiology of P. vivax and P. falciparum infections. The results were compared with those based on short amplicon (117 bp) deep sequencing. A total of 139 P. vivax and 222 P. falciparum samples were pyro-sequenced for pvmsp1 and pfmsp1, yielding a total of 21 P. vivax and 99 P. falciparum predominant haplotypes. The average MOI for P. vivax and P. falciparum were 2.16 and 2.68, respectively, which were significantly higher than that of microsatellite markers and short amplicon (117 bp) deep sequencing. Multiclonal infections were detected in 62.2% of the samples for P. vivax and 74.8% of the samples for P. falciparum. Four out of the five subjects with recurrent P. vivax malaria were found to be a relapse 44-65 days after clearance of parasites. No difference was observed in MOI among P. vivax patients of different symptoms, ages and genders. Similar patterns were also observed in P. falciparum except for one study site in Kenyan lowland areas with significantly higher MOI. The study used a novel method to evaluate Plasmodium MOI and molecular epidemiological patterns by long amplicon ultra-deep sequencing. The complexity of infections were similar among age groups, symptoms, genders, transmission settings (spatial heterogeneity), as well as over years (pre- vs. post-scale-up interventions). This study demonstrated that long amplicon deep sequencing is a useful tool to investigate multiplicity and molecular epidemiology of Plasmodium parasite infections.
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Demily, Caroline; Rigard, Caroline; Peyroux, Elodie; Chesnoy-Servanin, Gabrielle; Morel, Aurore; Franck, Nicolas
2016-01-01
Attentional, visuospatial, and social cognition deficits have a negative impact on children’s adaptative and social competences and, as a result, on their ability to achieve a normal functioning and behavior. Until now and despite the frequency of those deficits, there is a lack of children’s specific cognitive remediation tools specifically dedicated to attentional and visuospatial areas. The «Cognitus & Moi» program involves a variety of exercises in a paper and/or pencil (n = 30) or a computerized format (n = 29) and a strategy coaching approach. Each module of «Cognitus & Moi» targets a single impaired cognitive area, within the limits of cognitive domains’ overlapping. The little cartoon character named Cognitus, who illustrates the program, is supposed to be very friendly and kind toward children. Cognitus will accompany them throughout the program for an effective and positive reinforcement. The main goal of «Cognitus & Moi» is to adjust to children’s difficulties in daily life. Moreover, since the cognitive remediation benefit is complex to apply in daily life, the program is based on a metacognitive strategy. After a complete neuropsychological assessment and a psychoeducational session (with the child and the parents), 16 1-h-sessions of cognitive remediation with the therapist are proposed. Each session is composed of three parts: (1) computerized tasks focusing on specific attentional or visuospatial components (20 min). The attentional module targets hearing, visual, and divided attention. A double attention task is also proposed. The visuospatial module targets eye tracking and gaze direction, spatial orientation, visuospatial memory and construction, and mental imagery; (2) pen and paper tasks focusing on the same processes (20 min) and a facial emotion recognition task; (3) a proposal of a home-based task (during 20 min). Weekly, specific attentional and visuospatial home tasks are proposed to the child and analyzed with the parents and the therapist. Indeed, home exercises are useful to promote the transfer of strategies to daily life and their subsequent automation. The heterogeneity of cognitive deficits in intellectual deficiency necessitates an individualized cognitive remediation therapy. In this regard, «Cognitus & Moi» seems to be a promising tool. PMID:26869942
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Results in orbital evolution of objects in the geosynchronous region
NASA Technical Reports Server (NTRS)
Friesen, Larry Jay; Jackson, Albert A., IV; Zook, Herbert A.; Kessler, Donald J.
1990-01-01
The orbital evolution of objects at or near geosynchronous orbit (GEO) has been simulated to investigate possible hazards to working geosynchronous satellites. Orbits of both large satellites and small particles have been simulated, subject to perturbations by nonspherical geopotential terms, lunar and solar gravity, and solar radiation pressure. Large satellites in initially circular orbits show an expected cycle of inclination change driven by lunar and solar gravity, but very little altitude change. They thus have little chance of colliding with objects at other altitudes. However, if such a satellite is disrupted, debris can reach thousands of kilometers above or below the initial satellite altitude. Small particles in GEO experience two cycles driven by solar radiation: an expected eccentricity cycle and an inclination cycle not expected. Particles generated by GEO insertion stage solid rocket motors typically hit the earth or escape promptly; a small fraction appear to remain in persistent orbits.
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Deep Space Network capabilities for receiving weak probe signals
NASA Technical Reports Server (NTRS)
Asmar, Sami; Johnston, Doug; Preston, Robert
2004-01-01
This paper will describe the capability and highlight the cases of the critical communications for the Mars rovers and Saturn Orbit Insertion and preparation radio tracking of the Huygens probe at (non-DSN) radio telescopes.
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Trailing Ballute Aerocapture: Concept and Feasibility Assessment
NASA Technical Reports Server (NTRS)
Miller, Kevin L.; Gulick, Doug; Lewis, Jake; Trochman, Bill; Stein, Jim; Lyons, Daniel T.; Wilmoth, Richard G.
2003-01-01
Trailing Ballute Aerocapture offers the potential to obtain orbit insertion around a planetary body at a fraction of the mass of traditional methods. This allows for lower costs for launch, faster flight times and additional mass available for science payloads. The technique involves an inflated ballute (balloon-parachute) that provides aerodynamic drag area for use in the atmosphere of a planetary body to provide for orbit insertion in a relatively benign heating environment. To account for atmospheric, navigation and other uncertainties, the ballute is oversized and detached once the desired velocity change (Delta V) has been achieved. Analysis and trades have been performed for the purpose of assessing the feasibility of the technique including aerophysics, material assessments, inflation system and deployment sequence and dynamics, configuration trades, ballute separation and trajectory analysis. Outlined is the technology development required for advancing the technique to a level that would allow it to be viable for use in space exploration missions.
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Cardiovascular results from a rhesus monkey flown aboard the Cosmos 1514 spaceflight
NASA Technical Reports Server (NTRS)
Sandler, H.; Hines, J.; Benjamin, B. A.; Halpryn, B. M.; Krotov, V. P.
1987-01-01
The results of the Cosmos 1514 cardiovascular experiment, in which the blood flow to the head and the carotid pressure of a rhesus monkey were measured during the 5-d spaceflight, are reported. A single cylindrical probe containing both pressure and flow transducers was chronically implanted as a cuff around the left common carotid artery; measurements were obtained for 4 min every 2 h and compared to identical recordings obtained during a preflight control period and during 12 h on a launch pad. Immediately on its insertion into orbit, mean arterial pressure increased by 10 percent and has maintained a 16-27 percent increase over the first few hours of flight before returning to baseline level. Blood flow showed reciprocal changes to pressure on orbital insertion. Cardiovascular system changes persisted into the second day of flight, with the signs of adaptation appearing on days 3-5.
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Combined high and low-thrust geostationary orbit insertion with radiation constraint
NASA Astrophysics Data System (ADS)
Macdonald, Malcolm; Owens, Steven Robert
2018-01-01
The sequential use of an electric propulsion system is considered in combination with a high-thrust propulsion system for application to the propellant-optimal Geostationary Orbit insertion problem, whilst considering both temporal and radiation flux constraints. Such usage is found to offer a combined propellant mass saving when compared with an equivalent high-thrust only transfer. This propellant mass saving is seen to increase as the allowable transfer duration is increased, and as the thrust from the low-thrust system is increased, assuming constant specific impulse. It was found that the required plane change maneuver is most propellant-efficiently performed by the high-thrust system. The propellant optimal trajectory incurs a significantly increased electron flux when compared to an equivalent high-thrust only transfer. However, the electron flux can be reduced to a similar order of magnitude by increasing the high-thrust propellant consumption, whilst still delivering an improved mass fraction.
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GRAIL TCM-5 Go/No-Go: Developing Lunar Orbit Insertion Criteria
NASA Technical Reports Server (NTRS)
Chung, Min-Kun J.
2013-01-01
The Gravity Recovery and Interior Laboratory (GRAIL) mission successfully completed mapping the Moon's gravity field to an unprecedented level. The mission success was critically dependent on the success of the Lunar Orbit Insertion (LOI). It was somewhat unfamiliar as it involved an elliptical approach from a low-energy trans-lunar cruise trajectory via Sun-Earth three-body region rather than a more conventional hyperbolic approach from a direct Earth-to-Moon transfer. In addition, how its delivery dispersion affected the science formation of the two spacecraft was not well understood. In this paper we establish a set of LOI criteria to meet all the requirements and we use these criteria to establish Go/No-Go boundaries of the last, statistical Trajectory Correction Maneuvers (TCM-5s) for operations. In the end both spacecraft were found to be within the established boundaries and TCM-5s of both spacecraft were cancelled.
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Enhanced Lighting Techniques and Augmented Reality to Improve Human Task Performance
NASA Technical Reports Server (NTRS)
Maida, James C.; Bowen, Charles K.; Pace, John W.
2005-01-01
One of the most versatile tools designed for use on the International Space Station (ISS) is the Special Purpose Dexterous Manipulator (SPDM) robot. Operators for this system are trained at NASA Johnson Space Center (JSC) using a robotic simulator, the Dexterous Manipulator Trainer (DMT), which performs most SPDM functions under normal static Earth gravitational forces. The SPDM is controlled from a standard Robotic Workstation. A key feature of the SPDM and DMT is the Force/Moment Accommodation (FMA) system, which limits the contact forces and moments acting on the robot components, on its payload, an Orbital Replaceable Unit (ORU), and on the receptacle for the ORU. The FMA system helps to automatically alleviate any binding of the ORU as it is inserted or withdrawn from a receptacle, but it is limited in its correction capability. A successful ORU insertion generally requires that the reference axes of the ORU and receptacle be aligned to within approximately 0.25 inch and 0.5 degree of nominal values. The only guides available for the operator to achieve these alignment tolerances are views from any available video cameras. No special registration markings are provided on the ORU or receptacle, so the operator must use their intrinsic features in the video display to perform the pre-insertion alignment task. Since optimum camera views may not be available, and dynamic orbital lighting conditions may limit viewing periods, long times are anticipated for performing some ORU insertion or extraction operations. This study explored the feasibility of using augmented reality (AR) to assist with SPDM operations. Geometric graphical symbols were overlaid on the end effector (EE) camera view to afford cues to assist the operator in attaining adequate pre-insertion ORU alignment.
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Power subsystem performance prediction /PSPP/ computer program.
NASA Technical Reports Server (NTRS)
Weiner, H.; Weinstein, S.
1972-01-01
A computer program which simulates the operation of the Viking Orbiter Power Subsystem has been developed. The program simulates the characteristics and interactions of a solar array, battery, battery charge controls, zener diodes, power conditioning equipment, and the battery spacecraft and zener diode-spacecraft thermal interfaces. This program has been used to examine the operation of the Orbiter power subsystem during critical phases of the Viking mission - from launch, through midcourse maneuvers, Mars orbital insertion, orbital trims, Lander separation, solar occultations and unattended operation - until the end of the mission. A typical computer run for the first 24 hours after launch is presented which shows the variations in solar array, zener diode, battery charger, batteries and user load characteristics during this period.
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The Pioneer Venus Orbiter: 11 years of data. A laboratory for atmospheres seminar talk
NASA Technical Reports Server (NTRS)
Kasprzak, W. T.
1990-01-01
The Pioneer Venus Orbiter has been in operation since orbit insertion on December 4, 1978. For the past 11 years, it has been acquiring data in the salient features of the planet, its atmosphere, ionosphere, and interaction with the solar wind. A few of the results of this mission are summarized and their contribution to our general understanding of the planet Venus is discussed. Although Earth and Venus are often called twin planets, they are only superficially similar. Possessing no obvious evidence of plate tectonics, lacking water and an intrinsic magnetic field, and having a hot, dense carbon dioxide atmosphere with sulfuric acid clouds makes Venus a unique object of study by the Orbiter's instruments.
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Trajectory Optimization for Crewed Missions to an Earth-Moon L2 Halo Orbit
NASA Astrophysics Data System (ADS)
Dowling, Jennifer
Baseline trajectories to an Earth-Moon L2 halo orbit and round trip trajectories for crewed missions have been created in support of an advanced Orion mission concept. Various transfer durations and orbit insertion locations have been evaluated. The trajectories often include a deterministic mid-course maneuver that decreases the overall change in velocity in the trajectory. This paper presents the application of primer vector theory to study the existence, location, and magnitude of the mid-course maneuver in order to understand how to build an optimal round trip trajectory to an Earth-Moon L2 halo orbit. The lessons learned about when to add mid-course maneuvers can be applied to other mission designs.
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Global Moon Coverage via Hyperbolic Flybys
NASA Technical Reports Server (NTRS)
Buffington, Brent; Strange, Nathan; Campagnola, Stefano
2012-01-01
The scientific desire for global coverage of moons such as Jupiter's Galilean moons or Saturn's Titan has invariably led to the design of orbiter missions. These orbiter missions require a large amount of propellant needed to insert into orbit around such small bodies, and for a given launch vehicle, the additional propellant mass takes away from mass that could otherwise be used for scientific instrumentation on a multiple flyby-only mission. This paper will present methods--expanding upon techniques developed for the design of the Cassini prime and extended missions--to obtain near global moon coverage through multiple flybys. Furthermore we will show with proper instrument suite selection, a flyby-only mission can provide science return similar (and in some cases greater) to that of an orbiter mission.
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The latest views of Venus as observed by the Japanese Orbiter "Akatsuki"
NASA Astrophysics Data System (ADS)
Satoh, Takehiko; Akatsuki Project Team
2016-10-01
Akatsuki, also known as the Venus Climate Orbiter (VCO) of Japan, was launched on 21 May 2010 from Tanegashima Space Center, Kagoshima, Japan. After 6 months of cruising to Venus, an attempt was made to insert Akatsuki in Venus orbit (VOI) on 7 December 2010. However, due to the clogged check valve in a pressurizing system of fuel line, the thrust to decelerate the spacecraft was not enough to allow it captured by the gravitational pull of Venus. After this failure, Akatsuki became an artificial planet around the sun with an orbital period of ~200 days. We waited for 5 earth years (or 9 Akatsuki years), and the second attempt (VOI-R1) was made on the same day, 7 December 2015. It was a great surprise to the world that a "once failed" spacecraft made a successful orbital insertion after many years of time. The orbital period around Venus is slightly shorter than 11 days, with the apoapsis altitude of ~0.37 million km.After Venus Express (VEX), which was in Venus orbit for 8 years, Akatsuki still keeps a unique position and is expected to make a great contribution to the Venus science due primarily to its orbit. In contrast to the polar orbits of Pioneer Venus or VEX, Akatsuki is in a near-equatorial plane and revolves westward, the same direction as the super rotating atmosphere. This orbit allows the spacecraft in a "partial" synchronization with the atmospheric motion when Akatsuki is near the planet. When at greater distances, the atmosphere moves faster than Akatsuki's orbital motion so the spacecraft maps the full longitude range of Venus in several days. This meteorological-satellite-like concept makes Akatsuki the most unique planetary orbiter in the history. To sense the various levels of the atmosphere, to draw 3-dimentional picture of dynamics, Akatsuki is equipped with 5 on-board cameras, UVI (283 and 365 nm wavelength), IR1 (0.90, 0.97, and 1.01 μm), IR2 (1.65, 1.735, 2.02, 2.26, and 2.32 μm), LIR (8-12 μm), and LAC (a special high-speed sensor at visible wavelengths), as well as the ultra-stable oscillator for radio-occultation measurements.At the lecture, the latest views of Venus as acquired with these instruments on Akatsuki will be presented.
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Mars Reconnaissance Orbiter Operational Aerobraking Phase Assessment
NASA Technical Reports Server (NTRS)
Prince, Jill L.; Striepe, Scott A.
2007-01-01
The Mars Reconnaissance Orbiter (MRO) was inserted into orbit around Mars on March 10, 2005. After a brief delay, it began the process of aerobraking - using the atmospheric drag on the vehicle to reduce orbital period. The aerobraking phase lasted approximately 5 months (April 4 to August 30, 2006), during which teams from the Jet Propulsion Laboratory, Lockheed Martin Space Systems Corporation, and NASA Langley Research Center worked together to monitor and maneuver the spacecraft such that thermal margin on the solar arrays was maintained while schedule margin was upheld to provide a final local mean solar time (LMST) at ascending node of 3:00pm on the final aerobraking orbit. This paper will focus on the contribution of the flight mechanics team at NASA Langley Research Center (LaRC) during the aerobraking phase of the MRO mission.
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DOD and Navy applications for laser power beaming
NASA Astrophysics Data System (ADS)
Bennett, Harold E.
1995-04-01
Satellites are of vital importance to the Department of Defense and the Navy as well as to the civilian economy. For example, about 90% of the communications to the fleet are by satellite. Economical means for putting satellites into orbit and maintaining and extending their lifetimes in orbit are just as important for the military as for civilian industries. There is also a significant economic impact to the ability to repair rather than replace satellites that are malfunctioning or have been inserted into the wrong orbits. Laser power beaming can not only accomplish these tasks but also promises to move satellites in orbit quickly and inexpensively, provide boost power for degraded satellites or those which suffer intentional jamming from adversaries, remove space junk even in geosynchronous orbit and provide very high resolution pictures of objects in space by eliminating atmospheric disturbances.
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A High Power Solar Electric Propulsion - Chemical Mission for Human Exploration of Mars
NASA Technical Reports Server (NTRS)
Burke, Laura M.; Martini, Michael C.; Oleson, Steven R.
2014-01-01
Recently Solar Electric Propulsion (SEP) as a main propulsion system has been investigated as an option to support manned space missions to near-Earth destinations for the NASA Gateway spacecraft. High efficiency SEP systems are able to reduce the amount of propellant long duration chemical missions require, ultimately reducing the required mass delivered to Low Earth Orbit (LEO) by a launch vehicle. However, for long duration interplanetary Mars missions, using SEP as the sole propulsion source alone may not be feasible due to the long trip times to reach and insert into the destination orbit. By combining an SEP propulsion system with a chemical propulsion system the mission is able to utilize the high-efficiency SEP for sustained vehicle acceleration and deceleration in heliocentric space and the chemical system for orbit insertion maneuvers and trans-earth injection, eliminating the need for long duration spirals. By capturing chemically instead of with low-thrust SEP, Mars stay time increases by nearly 200 days. Additionally, the size the of chemical propulsion system can be significantly reduced from that of a standard Mars mission because the SEP system greatly decreases the Mars arrival and departure hyperbolic excess velocities (V(sub infinity)).
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Passage through the Ring Plane
2004-06-03
The path that lies ahead for the Cassini-Huygens mission is indicated in this image which illustrates where the spacecraft will be just 27 days from now, when it arrives at Saturn and crosses the ring plane 33 minutes before performing its critical orbital insertion maneuver. The X indicates the point where Cassini will pierce the ring plane on June 30, 2004, going from south to north of the ring plane, 33 minutes before the main engine fires to begin orbital insertion. The indicated point is between the narrow F-ring on the left and Saturn's tenuous G-ring which is too faint to be seen in this exposure. The image was taken on May 11, 2004 when the spacecraft was 26.3 million kilometers (16.3 million miles) from Saturn. Image scale is 158 kilometers (98 miles) per pixel. Moons visible in this image: Janus (181 kilometers or 113 miles across), one of the co-orbital moons; Pandora (84 kilometers or 52 miles across), one of the F ring shepherding moons; and Enceladus (499 kilometers or 310 miles across), a moon which may be heated from within and thus have a liquid sub-surface ocean. http://photojournal.jpl.nasa.gov/catalog/PIA06061
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Givehchi, Sogol; Wong, Yin How; Yeong, Chai Hong; Abdullah, Basri Johan Jeet
2018-04-01
To investigate the effect of radiofrequency ablation (RFA) electrode trajectory on complete tumor ablation using computational simulation. The RFA of a spherical tumor of 2.0 cm diameter along with 0.5 cm clinical safety margin was simulated using Finite Element Analysis software. A total of 86 points inside one-eighth of the tumor volume along the axial, sagittal and coronal planes were selected as the target sites for electrode-tip placement. The angle of the electrode insertion in both craniocaudal and orbital planes ranged from -90° to +90° with 30° increment. The RFA electrode was simulated to pass through the target site at different angles in combination of both craniocaudal and orbital planes before being advanced to the edge of the tumor. Complete tumor ablation was observed whenever the electrode-tip penetrated through the epicenter of the tumor regardless of the angles of electrode insertion in both craniocaudal and orbital planes. Complete tumor ablation can also be achieved by placing the electrode-tip at several optimal sites and angles. Identification of the tumor epicenter on the central slice of the axial images is essential to enhance the success rate of complete tumor ablation during RFA procedures.
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Spin-orbit torque based magnetization switching in Pt/Cu/[Co/Ni]5 multilayer structures
NASA Astrophysics Data System (ADS)
Ostwal, Vaibhav; Penumatcha, Ashish; Hung, Yu-Ming; Kent, Andrew D.; Appenzeller, Joerg
2017-12-01
Spin-Orbit Torque (SOT) in Heavy Metal/Ferromagnet (HM/FM) structures provides an important tool to control the magnetization of FMs and has been an area of interest for memory and logic implementation. Spin transfer torque on the FM in such structures is attributed to two sources: (1) the Spin Hall effect in the HM and (2) the Rashba-effect at the HM/FM interface. In this work, we study the SOT in a Pt/[Co,Ni] structure and compare its strength with the SOT in a Pt/Cu/[Co,Ni] structure where copper, a metal with a low spin-orbit interaction, is inserted between the Pt (HM) layer and the [Co,Ni] (FM) layer. We use an AC harmonic measurement technique to measure the strength of the SOT on the magnetic thin-film layer. Our measurements show that a significant SOT is exerted on the magnetization even after a 6 nm thick copper layer is inserted between the HM and the FM. Also, we find that this torque can be used to switch a patterned magnetic layer in the presence of an external magnetic field.
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Spin-orbit torques from interfacial spin-orbit coupling for various interfaces
NASA Astrophysics Data System (ADS)
Kim, Kyoung-Whan; Lee, Kyung-Jin; Sinova, Jairo; Lee, Hyun-Woo; Stiles, M. D.
2017-09-01
We use a perturbative approach to study the effects of interfacial spin-orbit coupling in magnetic multilayers by treating the two-dimensional Rashba model in a fully three-dimensional description of electron transport near an interface. This formalism provides a compact analytic expression for current-induced spin-orbit torques in terms of unperturbed scattering coefficients, allowing computation of spin-orbit torques for various contexts, by simply substituting scattering coefficients into the formulas. It applies to calculations of spin-orbit torques for magnetic bilayers with bulk magnetism, those with interface magnetism, a normal-metal/ferromagnetic insulator junction, and a topological insulator/ferromagnet junction. It predicts a dampinglike component of spin-orbit torque that is distinct from any intrinsic contribution or those that arise from particular spin relaxation mechanisms. We discuss the effects of proximity-induced magnetism and insertion of an additional layer and provide formulas for in-plane current, which is induced by a perpendicular bias, anisotropic magnetoresistance, and spin memory loss in the same formalism.
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Spin-orbit torques from interfacial spin-orbit coupling for various interfaces.
Kim, Kyoung-Whan; Lee, Kyung-Jin; Sinova, Jairo; Lee, Hyun-Woo; Stiles, M D
2017-09-01
We use a perturbative approach to study the effects of interfacial spin-orbit coupling in magnetic multilayers by treating the two-dimensional Rashba model in a fully three-dimensional description of electron transport near an interface. This formalism provides a compact analytic expression for current-induced spin-orbit torques in terms of unperturbed scattering coefficients, allowing computation of spin-orbit torques for various contexts, by simply substituting scattering coefficients into the formulas. It applies to calculations of spin-orbit torques for magnetic bilayers with bulk magnetism, those with interface magnetism, a normal metal/ferromagnetic insulator junction, and a topological insulator/ferromagnet junction. It predicts a dampinglike component of spin-orbit torque that is distinct from any intrinsic contribution or those that arise from particular spin relaxation mechanisms. We discuss the effects of proximity-induced magnetism and insertion of an additional layer and provide formulas for in-plane current, which is induced by a perpendicular bias, anisotropic magnetoresistance, and spin memory loss in the same formalism.
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Spin-orbit torques from interfacial spin-orbit coupling for various interfaces
Kim, Kyoung-Whan; Lee, Kyung-Jin; Sinova, Jairo; Lee, Hyun-Woo; Stiles, M. D.
2017-01-01
We use a perturbative approach to study the effects of interfacial spin-orbit coupling in magnetic multilayers by treating the two-dimensional Rashba model in a fully three-dimensional description of electron transport near an interface. This formalism provides a compact analytic expression for current-induced spin-orbit torques in terms of unperturbed scattering coefficients, allowing computation of spin-orbit torques for various contexts, by simply substituting scattering coefficients into the formulas. It applies to calculations of spin-orbit torques for magnetic bilayers with bulk magnetism, those with interface magnetism, a normal metal/ferromagnetic insulator junction, and a topological insulator/ferromagnet junction. It predicts a dampinglike component of spin-orbit torque that is distinct from any intrinsic contribution or those that arise from particular spin relaxation mechanisms. We discuss the effects of proximity-induced magnetism and insertion of an additional layer and provide formulas for in-plane current, which is induced by a perpendicular bias, anisotropic magnetoresistance, and spin memory loss in the same formalism. PMID:29333523
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Are you ready for Mars? - Main media events surrounding the arrival of ESA's Mars Express at Mars
NASA Astrophysics Data System (ADS)
2003-11-01
Launched on 2 June 2003 from Baikonur (Kazakhstan) on board a Russian Soyuz launcher operated by Starsem, the European probe -built for ESA by a European team of industrial companies led by Astrium - carries seven scientific instruments that will perform a series of remote-sensing experiments designed to shed new light on the Martian atmosphere, the planet’s structure and its geology. In particular, the British-made Beagle 2 lander, named after the ship on which Charles Darwin explored uncharted areas of the Earth in 1830, will contribute to the search for traces of life on Mars through exobiology experiments and geochemistry research. On Christmas Eve the Mars Express orbiter will be steered on a course taking it into an elliptical orbit, where it will safely circle the planet for a minimum of almost 2 Earth years. The Beagle 2 lander - which will have been released from the mother craft a few days earlier (on 19 December) - instead will stay on a collision course with the planet. It too should also be safe, being designed for atmospheric entry and geared for a final soft landing due to a sophisticated system of parachutes and airbags. On arrival, the Mars Express mission control team will report on the outcome of the spacecraft's delicate orbital insertion manoeuvre. It will take some time for Mars Express to manouvre into position to pick communications from Beagle 2. Hence, initially, other means will be used to check that Beagle 2 has landed: first signals from the Beagle 2 landing are expected to be available throughout Christmas Day, either through pick-up and relay of Beagle 2 radio signals by NASA’s Mars Odyssey, or by direct pick-up by the Jodrell Bank radio telescope in the UK. Mars Express will then pass over Beagle 2 in early January 2004, relaying data and images back to Earth. The first images from the cameras of Beagle 2 and Mars Express are expected to be available between the end of the year and the beginning of January 2004. The key dates relating to the arrival of Mars Express at its destination will be marked by several media events not to be missed. Pencil them into your diaries so as not to miss one of the most exciting events of the year. Tuesday 11 November Mars Express/Beagle 2 Media briefing Royal Society- 6-9 Carlton House Terrace, London 10:00 - 13:00 -Status report on the mission -Technical details on forthcoming Mars Express/Beagle 2 operations -News handling arrangements around Christmas Speakers: Prof. David Southwood, ESA Director of Science; Prof. Colin Pillinger, Beagle 2 Lander Lead Scientist; John Reddy, ESA Mars Express Principal Electrical Systems Engineer. Contact: Peter Barratt, PPARC Tel. + 44 (0) 1793 44 20 25 e-mail: Beagle2@pparc.ac.uk Wednesday 3 December ESA Media briefing ESA/ ESOC, Darmstadt, Germany 10:30 - 12:30 -Scientific outlook and expected results -Status report on the mission -Presentation of upcoming events Speakers: Rudolf Schmidt, ESA Mars Express Project Manager; Augustin Chicarro, ESA Mars Express Project Scientist. In addition, Mars Express scientists and Mission Control Managers will highlight their contribution to the Mars Express mission. In videoconference with ESA/Headquarters, Paris (F); ESA/ESTEC, Noordwijk (NL), ESA/ESRIN, Frascati (I). Contact: Jocelyne Landeau Constantin, ESA/ESOC Tel. + 49 6151 90 26 96 e-mail: Jocelyne.Landeau-Constantin@esa.int Friday 19 December Mars Express Orbiter/ Beagle 2 separation Mission Control Managers announce results of Beagle 2 separation from the mother craft. a.Event at ESA/ESOC, Darmstadt , Germany 08:30 - 14:00 Speakers: Prof. David Southwood, ESA Director of Science; Rudolf Schmidt, ESA Mars Express Project Manager Contact: Jocelyne Landeau Constantin, ESA/ESOC Tel. + 49 6151 90 26 96 e-mail: Jocelyne.Landeau-Constantin@esa.int b.Event in London -location and time t.b.c. Speaker: Prof. Colin Pillinger, Beagle 2 Lander Lead Scientist. Contact: Peter Barratt, PPARC Tel. + 44 (0) 1793 44 20 25 e-mail: Beagle2@pparc.ac.uk Thursday 25 December Christmas on Mars a.Media event at ESA/ ESOC, Darmstadt, Germany 03:00 - 07:00 Mars Express orbit insertion follow-up and Beagle 2 landing- Experience the accomplishment of one of the most exciting phases of the Mars Express mission in real time in the presence of Mission Control Managers and Scientists. 08:30 - 10:00 Christmas media brunch- Announcement of Mars orbit insertion results and Beagle 2 landing, with the participation of Prof. David Sourthwood, ESA Director of Science. Contact: Jocelyne Landeau Constantin, ESA/ESOC Tel. + 49 6151 90 26 96 e-mail: Jocelyne.Landeau-Constantin@esa.int b.Event in central London - location and time t.b.c. Contact: Peter Barratt, PPARC Tel. + 44 (0) 1793 44 20 25 e-mail: Beagle2@pparc.ac.uk Note to Editors: Timeline of expected main mission events 16 December All day Fine targeting of Mars Express to point at landing site - ranging 19 December 06:51 GMT/07:51 CET Decision to release Beagle 2 08:41 GMT/09:41 CET Eject command sent to Mars Express 10:15 GMT/11:15 CET First results of release available 20 December Re-targeting of Mars Express on an orbital insertion course 23 December Update on Mars Express Orbital Insertion Sequence 24 December Night Final decision to steer Mars Express into a Martian orbit 25 December 02:45 GMT/03:45 CET Beagle 2 landing on Mars 03:00 GMT/04:00 CET Mars Express Orbital Insertion 05:15 GMT/06:15 CET Mars Odyssey orbiter flight over Beagle 2 07:00 GMT/08:00 CET First evaluation of Mars Express orbital insertion 22:45 GMT/23:45 CET Possible direct capture of Beagle 2 signals at Jodrell Bank (UK)
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Boeing Low-Thrust Geosynchronous Transfer Mission Experience
NASA Technical Reports Server (NTRS)
Poole, Mark; Ho, Monte
2007-01-01
Since 2000, Boeing 702 satellites have used electric propulsion for transfer to geostationary orbits. The use of the 25cm Xenon Ion Propulsion System (25cm XIPS) results in more than a tenfold increase in specific impulse with the corresponding decrease in propellant mass needed to complete the mission when compared to chemical propulsion[1]. In addition to more favorable mass properties, with the use of XIPS, the 702 has been able to achieve orbit insertions with higher accuracy than it would have been possible with the use of chemical thrusters. This paper describes the experience attained by using the 702 XIPS ascent strategy to transfer satellite to geosynchronous orbits.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Anderson, Mark A.; Bigelow, Matthew; Gilkey, Jeff C.
The Super Strypi Navigation, Guidance & Control Software is a real-time implementation of the navigation, guidance and control algorithms designed to deliver a payload to a desired orbit for the rail launched Super Strypi launch vehicle. The software contains all flight control algorithms required from pre-launch until orbital insertion. The flight sequencer module calls the NG&C functions at the appropriate times of flight. Additional functionality includes all the low level drivers and I/O for communicating to other systems within the launch vehicle and to the ground support equipment. The software is designed such that changes to the launch location andmore » desired orbit can be changed without recompiling the code.« less
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Aerobrake concepts for NTP systems study
NASA Technical Reports Server (NTRS)
Cruz, Manuel I.
1992-01-01
Design concepts are described for landing large spacecraft masses on the Mars surface in support of manned missions with interplanetary transportation using Nuclear Thermal Propulsion (NTP). Included are the mission and systems analyses, trade studies and sensitivity analyses, design analyses, technology assessment, and derived requirements to support this concept. The mission phases include the Mars de-orbit, entry, terminal descent, and terminal touchdown. The study focuses primarily on Mars surface delivery from orbit after Mars orbit insertion using an NTP. The requirements associated with delivery of logistical supplies, habitats, and other equipment on minimum energy Earth to Mars transfers are also addressed in a preliminary fashion.
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Elliptical orbit performance computer program
NASA Technical Reports Server (NTRS)
Myler, T. R.
1981-01-01
A FORTRAN coded computer program which generates and plots elliptical orbit performance capability of space boosters for presentation purposes is described. Orbital performance capability of space boosters is typically presented as payload weight as a function of perigee and apogee altitudes. The parameters are derived from a parametric computer simulation of the booster flight which yields the payload weight as a function of velocity and altitude at insertion. The process of converting from velocity and altitude to apogee and perigee altitude and plotting the results as a function of payload weight is mechanized with the ELOPE program. The program theory, user instruction, input/output definitions, subroutine descriptions and detailed FORTRAN coding information are included.
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Altair Descent and Ascent Reference Trajectory Design and Initial Dispersion Analyses
NASA Technical Reports Server (NTRS)
Kos, Larry D.; Polsgrove, Tara T.; Sostaric, Ronald r.; Braden, Ellen M.; Sullivan, Jacob J.; Lee, Thanh T.
2010-01-01
The Altair Lunar Lander is the linchpin in the Constellation Program (CxP) for human return to the Moon. Altair is delivered to low Earth orbit (LEO) by the Ares V heavy lift launch vehicle, and after subsequent docking with Orion in LEO, the Altair/Orion stack is delivered through translunar injection (TLI). The Altair/Orion stack separating from the Earth departure stage (EDS) shortly after TLI and continues the flight to the Moon as a single stack. Altair performs the lunar orbit insertion (LOI) maneuver, targeting a 100-km circular orbit. This orbit will be a polar orbit for missions landing near the lunar South Pole. After spending nearly 24 hours in low lunar orbit (LLO), the lander undocks from Orion and performs a series of small maneuvers to set up for descending to the lunar surface. This descent begins with a small deorbit insertion (DOI) maneuver, putting the lander on an orbit that has a perilune of 15.24 km (50,000 ft), the altitude where the actual powered descent initiation (PDI) commences. At liftoff from Earth, Altair has a mass of 45 metric tons (mt). However after LOI (without Orion attached), the lander mass is slightly less than 33 mt at PDI. The lander currently has a single descent module main engine, with TBD lb(sub f) thrust (TBD N), providing a thrust-to-weight ratio of approximately TBD Earth g's at PDI. LDAC-3 (Lander design and analysis cycle #3) is the most recently closed design sizing and mass properties iteration. Upgrades for loss of crew (LDAC-2) and loss of mission (LDAC-3) have been incorporated into the lander baseline design (and its Master Equipment List). Also, recently, Altair has been working requirements analyses (LRAC-1). All nominal data here are from the LDAC-3 analysis cycle. All dispersions results here are from LRAC-1 analyses.
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Apollo 11 Mission images - Solar Corona (moon)
1969-07-19
AS11-42-6179 (19 July 1969) --- This photograph of the solar corona was taken from the Apollo 11 spacecraft during trans-lunar coast and prior to lunar orbit insertion. The moon is the dark disc between the spacecraft and the sun.
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NASA Technical Reports Server (NTRS)
Abbas, Mian M.
2014-01-01
Outline: Introduction to the Cassini mission, and Cassini mission Objectives; Cassini spacecraft, instruments, launch, and orbit insertion; Saturn, Rings, and Satellite, Titan; Composite Infrared Spectrometer (CIRS); and Infrared observations of Saturn and titan.
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1973-05-31
S73-27095 (25 May 1973) --- The Skylab 2 crew, consisting of astronauts Charles Conrad Jr., Joseph P. Kerwin and Paul J. Weitz, inside the command module atop a Saturn IB launch vehicle, heads toward the Skylab space station in Earth orbit. The command module was inserted into Earth orbit approximately 10 minutes after liftoff. The three represent the first of three crews who will spend record-setting durations for human beings in space, while performing a variety of experiments. Photo credit: NASA
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1973-05-31
S73-27096 (25 May 1973) --- The Skylab 2 crew, consisting of astronauts Charles Conrad Jr., Joseph P. Kerwin and Paul J. Weitz, inside the command module atop a Saturn IB launch vehicle, heads toward the Skylab space station in Earth orbit. The command module was inserted into Earth orbit approximately 10 minutes after liftoff. The three represent the first of three crews who will spend record-setting durations for human beings in space, while performing a variety of experiments. Photo credit: NASA
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Independent Orbiter Assessment (IOA): Analysis of the orbital maneuvering system
NASA Technical Reports Server (NTRS)
Prust, C. D.; Paul, D. J.; Burkemper, V. J.
1987-01-01
The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. The independent analysis results for the Orbital Maneuvering System (OMS) hardware are documented. The OMS provides the thrust to perform orbit insertion, orbit circularization, orbit transfer, rendezvous, and deorbit. The OMS is housed in two independent pods located one on each side of the tail and consists of the following subsystems: Helium Pressurization; Propellant Storage and Distribution; Orbital Maneuvering Engine; and Electrical Power Distribution and Control. The IOA analysis process utilized available OMS hardware drawings and schematics for defining hardware assemblies, components, and hardware items. Each level of hardware was evaluted and analyzed for possible failure modes and effects. Criticality was asigned based upon the severity of the effect for each failure mode.
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Cicconi, Alessandro; Micheli, Emanuela; Vernì, Fiammetta; Jackson, Alison; Gradilla, Ana Citlali; Cipressa, Francesca; Raimondo, Domenico; Bosso, Giuseppe; Wakefield, James G.; Ciapponi, Laura; Cenci, Giovanni; Gatti, Maurizio
2017-01-01
Abstract Drosophila telomeres are sequence-independent structures maintained by transposition to chromosome ends of three specialized retroelements rather than by telomerase activity. Fly telomeres are protected by the terminin complex that includes the HOAP, HipHop, Moi and Ver proteins. These are fast evolving, non-conserved proteins that localize and function exclusively at telomeres, protecting them from fusion events. We have previously suggested that terminin is the functional analogue of shelterin, the multi-protein complex that protects human telomeres. Here, we use electrophoretic mobility shift assay (EMSA) and atomic force microscopy (AFM) to show that Ver preferentially binds single-stranded DNA (ssDNA) with no sequence specificity. We also show that Moi and Ver form a complex in vivo. Although these two proteins are mutually dependent for their localization at telomeres, Moi neither binds ssDNA nor facilitates Ver binding to ssDNA. Consistent with these results, we found that Ver-depleted telomeres form RPA and γH2AX foci, like the human telomeres lacking the ssDNA-binding POT1 protein. Collectively, our findings suggest that Drosophila telomeres possess a ssDNA overhang like the other eukaryotes, and that the terminin complex is architecturally and functionally similar to shelterin. PMID:27940556
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Applications technology satellites advanced mission study
NASA Technical Reports Server (NTRS)
Gould, L. M.
1972-01-01
Three spacecraft configurations were designed for operation as a high powered synchronous communications satellite. Each spacecraft includes a 1 kw TWT and a 2 kw Klystron power amplifier feeding an antenna with multiple shaped beams. One of the spacecraft is designed to be boosted by a Thor-Delta launch vehicle and raised to synchronous orbit with electric propulsion. The other two are inserted into a elliptical transfer orbit with an Atlas Centaur and injected into final orbit with an apogee kick motor. Advanced technologies employed in the several configurations include tubes with multiple stage collectors radiating directly to space, multiple-contoured beam antennas, high voltage rollout solar cell arrays with integral power conditioning, electric propulsion for orbit raising and on-station attitude control and station-keeping, and liquid metal slip rings.
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Contingency plans for the ISEE-3 libration-point mission
NASA Technical Reports Server (NTRS)
Dunham, D. W.
1979-01-01
During the planning stage of the International Sun-Earth Explorer-3 (ISEE-3) mission, a recovery strategy was developed in case the Delta rocket underperformed during the launch phase. If a large underburn had occurred, the ISEE-3 spacecraft would have been allowed to complete one revolution of its highly elliptical earth orbit. The recovery plan called for a maneuver near perigee to increase the energy of the off-nominal orbit; a relatively small second maneuver would then insert the spacecraft into a new transfer trajectory toward the desired halo orbit target, and a third maneuver would place the spacecraft in the halo orbit. Results of the study showed that a large range of underburns could be corrected for a total nominal velocity deviation cost within the ISEE-3 fuel budget.
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Zhao, Yan-feng; Lu, Ping; Zhou, Xiao-nan; Qu, Chang-feng
2010-03-01
To study the surgical management of enophthalmos after severe malar maxillary complex fracture. The X-ray and CT examination were performed before operation to diagnose the orbital fracture and intraorbital tissue displacement. The fractured orbital rim was repositioned intraoperatively, followed by implantation of shaped titanium mesh to rebuild the orbital floor. The Medpor was inserted above the titanium mesh to correct the enophthalmos. From Sept. 2007 to Jan. 2009, 6 cases of enophthalmos after severe malar-maxillary complex fracture were treated. The enophthalmos was corrected or improved obviously in all the patients. The enophthalmos after severe malar-maxillary complex fracture can be corrected or obviously improved. Shaped titanium mesh can be used to rebuild the orbital floor with the Medpor to reconstruct the intraorbital tissue volume.
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Optimal thrust level for orbit insertion
NASA Astrophysics Data System (ADS)
Cerf, Max
2017-07-01
The minimum-fuel orbital transfer is analyzed in the case of a launcher upper stage using a constantly thrusting engine. The thrust level is assumed to be constant and its value is optimized together with the thrust direction. A closed-loop solution for the thrust direction is derived from the extremal analysis for a planar orbital transfer. The optimal control problem reduces to two unknowns, namely the thrust level and the final time. Guessing and propagating the costates is no longer necessary and the optimal trajectory is easily found from a rough initialization. On the other hand the initial costates are assessed analytically from the initial conditions and they can be used as initial guess for transfers at different thrust levels. The method is exemplified on a launcher upper stage targeting a geostationary transfer orbit.
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Electric propulsion for geostationary orbit insertion
NASA Technical Reports Server (NTRS)
Oleson, Steven R.; Curran, Francis M.; Myers, Roger M.
1995-01-01
Solar electric propulsion (SEP) technology is already being used for geostationary satellite stationkeeping to increase payload mass. By using this same technology to perform part of the orbit transfer additional increases in payload mass can be achieved. Advanced chemical and N2H4 arcjet systems are used to increase the payload mass by performing stationkeeping and part of the orbit transfer. Four mission options are analyzed which show the impact of either sharing the orbit transfer between chemical and SEP systems or having either complete the transfer alone. Results show that for an Atlas 2AS payload increases in net mass (geostationary satellite mass less wet propulsion system mass) of up to 100 kg can be achieved using advanced chemical for the transfer and advanced N2H4 arcjets for stationkeeping. An additional 100 kg can be added using advanced N2H4 arcjets for part of a 40 day orbit transfer.
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Impact of MoO3 interlayer on the energy level alignment of pentacene-C60 heterostructure.
Zou, Ye; Mao, Hongying; Meng, Qing; Zhu, Daoben
2016-02-28
Using in situ ultraviolet photoelectron spectroscopy, the electronic structure evolutions at the interface between pentacene and fullerene (C60), a classical organic donor-acceptor heterostructure in organic electronic devices, on indium-tin oxide (ITO) and MoO3 modified ITO substrates have been investigated. The insertion of a thin layer MoO3 has a significant impact on the interfacial energy level alignment of pentacene-C60 heterostructure. For the deposition of C60 on pentacene, the energy difference between the highest occupied molecular orbital of donor and the lowest unoccupied molecular orbital of acceptor (HOMO(D)-LUMO(A)) offset of C60/pentacene heterostructure increased from 0.86 eV to 1.54 eV after the insertion of a thin layer MoO3 on ITO. In the inverted heterostructrure where pentacene was deposited on C60, the HOMO(D)-LUMO(A) offset of pentacene/C60 heterostructure increased from 1.32 to 2.20 eV after MoO3 modification on ITO. The significant difference of HOMO(D)-LUMO(A) offset shows the feasibility to optimize organic electronic device performance through interfacial engineering approaches, such as the insertion of a thin layer high work function MoO3 films.
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NASA Astrophysics Data System (ADS)
Cusinato, Eleonora; Zanchettin, Davide; Sannino, Gianmaria; Rubino, Angelo
2018-04-01
Large-scale circulation anomalies over the North Atlantic and Euro-Mediterranean regions described by dominant climate modes, such as the North Atlantic Oscillation (NAO), the East Atlantic pattern (EA), the East Atlantic/Western Russian (EAWR) and the Mediterranean Oscillation Index (MOI), significantly affect interannual-to-decadal climatic and hydroclimatic variability in the Euro-Mediterranean region. However, whereas previous studies assessed the impact of such climate modes on air-sea heat and freshwater fluxes in the Mediterranean Sea, the propagation of these atmospheric forcing signals from the surface toward the interior and the abyss of the Mediterranean Sea remains unexplored. Here, we use a high-resolution ocean model simulation covering the 1979-2013 period to investigate spatial patterns and time scales of the Mediterranean thermohaline response to winter forcing from NAO, EA, EAWR and MOI. We find that these modes significantly imprint on the thermohaline properties in key areas of the Mediterranean Sea through a variety of mechanisms. Typically, density anomalies induced by all modes remain confined in the upper 600 m depth and remain significant for up to 18-24 months. One of the clearest propagation signals refers to the EA in the Adriatic and northern Ionian seas: There, negative EA anomalies are associated to an extensive positive density response, with anomalies that sink to the bottom of the South Adriatic Pit within a 2-year time. Other strong responses are the thermally driven responses to the EA in the Gulf of Lions and to the EAWR in the Aegean Sea. MOI and EAWR forcing of thermohaline properties in the Eastern Mediterranean sub-basins seems to be determined by reinforcement processes linked to the persistency of these modes in multiannual anomalous states. Our study also suggests that NAO, EA, EAWR and MOI could critically interfere with internal, deep and abyssal ocean dynamics and variability in the Mediterranean Sea.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Soukup, J.; Koren, H.S.; Becker, S.
1993-02-01
This study was performed to evaluate the effect of ozone (O3) exposure at 1 ppm for 2 hr on the susceptibility/resistance of adult human alveolar macrophages (AM) to infection with respiratory syncytial virus (RSV) in vitro and on RSV-induced cytokine production by the AM. AM were first exposed to O3 or to filtered air and then infected with RSV at multiplicities of infection (m.o.i.) of 0.1, 1.0, and 10. The percentage RSV-infected AM and the amount of infectious virus released by the cells were determined at Days 2 and 4 after infection. Interleukin (IL)-1, IL-6, and tumor necrosis factor (TNF)more » levels in the supernatants were determined on Day 2. No difference in the percentage infected AM or in the amount of infectious RSV produced was found between control and O3-exposed cultures. However, O3-exposed AM infected with RSV at m.o.i. 1 produced less IL-1 in response to RSV infection than control AM: 63.6 pg/ml compared with 98.5 pg/ml. No difference in IL-1 was seen with m.o.i. 10. IL-6 levels were also decreased, but only after infection with m.o.i. 0.1. At this level of infection 830 pg/ml was produced by control AM as compared to 468.2 pg/ml by O3-exposed AM. TNF production was unaffected by O3 at all multiplicities of infection. Statistical analysis of the O3 effect on AM cytokine production induced by the different multiplicities, however, revealed no significant effect of O3. Based on these observations it appears unlikely that O3 alters susceptibility of AM to infection with RSV, nor does O3 dramatically alter cytokine production in response to RSV since effects on IL-1 and IL-6 secretion were only found with the lowest levels of infection which induced cytokine release.« less
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Turunen, Aaro; Hukkanen, Veijo; Nygårdas, Michaela; Kulmala, Jarmo; Syrjänen, Stina
2014-07-08
Oral mucosa is frequently exposed to Herpes simplex virus type 1 (HSV-1) infection and irradiation due to dental radiography. During radiotherapy for oral cancer, the surrounding clinically normal tissues are also irradiated. This prompted us to study the effects of HSV-1 infection and irradiation on viability and apoptosis of oral epithelial cells. Immortal gingival keratinocyte (HMK) cells were infected with HSV-1 at a low multiplicity of infection (MOI) and irradiated with 2 Gy 24 hours post infection. The cells were then harvested at 24, 72 and 144 hours post irradiation for viability assays and qRT-PCR analyses for the apoptosis-related genes caspases 3, 8, and 9, bcl-2, NFκB1, and viral gene VP16. Mann-Whitney U-test was used for statistical calculations. Irradiation improved the cell viability at 144 hours post irradiation (P = 0.05), which was further improved by HSV-1 infection at MOI of 0.00001 (P = 0.05). Simultaneously, the combined effects of infection at MOI of 0.0001 and irradiation resulted in upregulation in NFκB1 (P = 0.05). The combined effects of irradiation and HSV infection also significantly downregulated the expression of caspases 3, 8, and 9 at 144 hours (P = 0.05) whereas caspase 3 and 8 significantly upregulated in non-irradiated, HSV-infected cells as compared to uninfected controls (P = 0.05). Infection with 0.0001 MOI downregulated bcl-2 in non-irradiated cells but was upregulated by 27% after irradiation when compared to non-irradiated infected cells (P = 0.05). Irradiation had no effect on HSV-1 shedding or HSV gene expression at 144 hours. HSV-1 infection may improve the viability of immortal cells after irradiation. The effect might be related to inhibition of apoptosis.
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2014-01-01
Background Oral mucosa is frequently exposed to Herpes simplex virus type 1 (HSV-1) infection and irradiation due to dental radiography. During radiotherapy for oral cancer, the surrounding clinically normal tissues are also irradiated. This prompted us to study the effects of HSV-1 infection and irradiation on viability and apoptosis of oral epithelial cells. Methods Immortal gingival keratinocyte (HMK) cells were infected with HSV-1 at a low multiplicity of infection (MOI) and irradiated with 2 Gy 24 hours post infection. The cells were then harvested at 24, 72 and 144 hours post irradiation for viability assays and qRT-PCR analyses for the apoptosis-related genes caspases 3, 8, and 9, bcl-2, NFκB1, and viral gene VP16. Mann–Whitney U-test was used for statistical calculations. Results Irradiation improved the cell viability at 144 hours post irradiation (P = 0.05), which was further improved by HSV-1 infection at MOI of 0.00001 (P = 0.05). Simultaneously, the combined effects of infection at MOI of 0.0001 and irradiation resulted in upregulation in NFκB1 (P = 0.05). The combined effects of irradiation and HSV infection also significantly downregulated the expression of caspases 3, 8, and 9 at 144 hours (P = 0.05) whereas caspase 3 and 8 significantly upregulated in non-irradiated, HSV-infected cells as compared to uninfected controls (P = 0.05). Infection with 0.0001 MOI downregulated bcl-2 in non-irradiated cells but was upregulated by 27% after irradiation when compared to non-irradiated infected cells (P = 0.05). Irradiation had no effect on HSV-1 shedding or HSV gene expression at 144 hours. Conclusions HSV-1 infection may improve the viability of immortal cells after irradiation. The effect might be related to inhibition of apoptosis. PMID:25005804
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Wijnker, Paul J M; Friedrich, Felix W; Dutsch, Alexander; Reischmann, Silke; Eder, Alexandra; Mannhardt, Ingra; Mearini, Giulia; Eschenhagen, Thomas; van der Velden, Jolanda; Carrier, Lucie
2016-08-01
Hypertrophic cardiomyopathy (HCM) is a cardiac genetic disease characterized by left ventricular hypertrophy, diastolic dysfunction and myocardial disarray. The most frequently mutated gene is MYBPC3, encoding cardiac myosin-binding protein-C (cMyBP-C). We compared the pathomechanisms of a truncating mutation (c.2373_2374insG) and a missense mutation (c.1591G>C) in MYBPC3 in engineered heart tissue (EHT). EHTs enable to study the direct effects of mutants without interference of secondary disease-related changes. EHTs were generated from Mybpc3-targeted knock-out (KO) and wild-type (WT) mouse cardiac cells. MYBPC3 WT and mutants were expressed in KO EHTs via adeno-associated virus. KO EHTs displayed higher maximal force and sensitivity to external [Ca(2+)] than WT EHTs. Expression of WT-Mybpc3 at MOI-100 resulted in ~73% cMyBP-C level but did not prevent the KO phenotype, whereas MOI-300 resulted in ≥95% cMyBP-C level and prevented the KO phenotype. Expression of the truncating or missense mutation (MOI-300) or their combination with WT (MOI-150 each), mimicking the homozygous or heterozygous disease state, respectively, failed to restore force to WT level. Immunofluorescence analysis revealed correct incorporation of WT and missense, but not of truncated cMyBP-C in the sarcomere. In conclusion, this study provides evidence in KO EHTs that i) haploinsufficiency affects EHT contractile function if WT cMyBP-C protein levels are ≤73%, ii) missense or truncating mutations, but not WT do not fully restore the disease phenotype and have different pathogenic mechanisms, e.g. sarcomere poisoning for the missense mutation, iii) the direct impact of (newly identified) MYBPC3 gene variants can be evaluated. Copyright © 2016 Elsevier Ltd. All rights reserved.
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Arecibo/Magellan Composite of Quetzalpetlatl Corona
1997-01-16
This composite image was created by inserting approximately 70 orbits of NASA Magellan data into an image obtained at the Arecibo, Puerto Rico radiotelescope and shows a geologically complex region in the southern hemisphere of Venus. http://photojournal.jpl.nasa.gov/catalog/PIA00217
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2014-09-17
Dwayne Brown, NASA public affairs officer, moderates a media briefing where panelist outlined activities around the Sunday, Sept. 21 orbital insertion at Mars of the agency’s Mars Atmosphere and Volatile EvolutioN (MAVEN) spacecraft, Wednesday, Sept. 17, 2014 at NASA Headquarters in Washington. (Photo credit: NASA/Bill Ingalls)
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Song, Yue; Xia, Zhijun; Shen, Keng; Zhai, Xingyue
2013-05-01
To construct recombinant adenoviruses AdHT-rev-casp3 and Ad-rev-casp3, which express autocatalysis caspase-3 driven by human telomerase reverse transcriptase promoter and cytomegalovirus promoter, respectively; and to investigate their antitumor effects on ovarian cancer in vitro and in vivo. Cell viabilities were determined using the cell counting kit 8 and flow cytometry. Reverse transcriptase polymerase chain reaction and immunoblotting assays were used to detect cellular apoptotic activities after treatments. Tumor growth and survival of mice bearing AO cells were studied. AdHT-rev-casp3 significantly suppressed the survival of AO cells in a dose-dependent modality with a viability rate of 60.45% ± 7.8% at an multiplicity of infection (MOI) of 70 and 42.18 ± 5.3% at an MOI of 100, which was somewhat lower than that of the AO cells treated with Ad-rev-casp3 (32.28% ± 5.3% and 21.84% ± 3.4%, respectively). In contrast, AdHT-rev-casp3 induced little human umbilical vein epithelial cell (HUVEC) death with a viability rate of 98.52% ± 6.9% at an MOI of 70, whereas Ad-rev-casp3 induced significant cell death in HUVEC with a viability rate of 27.14% ± 5.4%. Additionally, AdHT-rev-casp3 (MOI = 70) caused significant apoptosis in AO cells with an apoptotic rate of 25.97%, whereas it caused undetectable apoptosis in HUVECs with the rate of only 1.75%. Ad-rev-casp3 (MOI = 70) caused strong apoptosis in both AO and HUVECs, with the rate of 35.82% and 38.12%, respectively. AdHT-rev-casp3 caused markedly higher levels of active caspase-3, causing no detectable active caspase-3 expression in HUVECs. The tumor growth suppression rate of AdHT-rev-casp3 was 54.94%, significantly higher than that of phosphate-buffered saline at the end point of the study. AdHT-rev-casp3 significantly improved the survival of mice receiving intraperitoneal inoculation of AO cells with little liver damage, with the mean survival of 177 ± 12 days. AdHT-rev-casp3 causes effective apoptosis with significant tumor selectivity, suppresses tumor growth, and improves the mouse survival with little liver toxicity. It can be a potent therapeutic agent for the tumor-targeting treatment of ovarian cancer.
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Zhu, Yuanzheng; Yi, Yangyan; Yang, Shuifa; Zhang, Jing; Wu, Shu; Wang, Zhaohui
2017-09-01
To discuss the possibility of constructing injectable tissue engineered adipose tissue, and to provide a new approach for repairing soft tissue defects. Human adipose-derived stem cells (hADSCs) were extracted from the lipid part of human liposuction aspirate by enzymatic digestion and identified by morphological observation, flow cytometry, and adipogenic induction. The hADSCs underwent transfection by lentivirus vector expressing hepatocyte growth factor and green fluorescent protein (HGF-GFP-LVs) of different multiplicity of infection (MOI, 10, 30, 50, and 100), the transfection efficiency was calculated to determine the optimum MOI. The hADSCs transfected by HGF-GFP-LVs of optimal MOI and being adipogenic inducted were combined with injectable fibrin glue scaffold, and were injected subcutaneously into the right side of the low back of 10 T-cell deficiency BALB/c female nude mice (transfected group); non-HGF-GFP-LVs transfected hADSCs (being adipogenic inducted) combined with injectable fibrin glue scaffold were injected subcutaneously into the left side of the low back (untransfected group); and injectable fibrin glue scaffold were injected subcutaneously into the middle part of the neck (blank control group); 0.4 mL at each point. Twelve weeks later the mice were killed and the implants were taken out. Gross observation, wet weight measurement, HE staining, GFP fluorescence labeling, and immunofluorescence staining were performed to assess the in vivo adipogenic ability of the seed cells and the neovascularization of the grafts. The cultured cells were identified as hADSCs. Poor transfection efficiency was observed in MOI of 10 and 30, the transfection efficiency of MOI of 50 and 100 was more than 80%, so the optimum MOI was 50. Adipose tissue-like new-born tissues were found in the injection sites of the transfected and untransfected groups after 12 weeks of injection, and no new-born tissues was found in the blank control group. The wet-weight of new-born tissue in the transfected group [(32.30±4.06) mg] was significantly heavier than that of the untransfected group [(25.27±3.94) mg] ( t =3.929, P =0.001). The mature adipose cells in the transfected group [(126.93±5.36) cells/field] were significantly more than that in the untransfected group [(71.36±4.52) cells/field] ( t =30.700, P =0.000). Under fluorescence microscopy, some of the single cell adipocytes showed a network of green fluorescence, indicating the presence of GFP labeled exogenous hADSCs in the tissue. The vascular density of new-born tissue of the transfected group [(16.37±2.76)/field] was significantly higher than that of the untransfected group [(9.13±1.68)/field] ( t =8.678, P =0.000). The hADSCs extracted from the lipid part after liposuction can be used as seed cells. After HGF-GFP-LVs transfection and adipose induction, the hADSCs combined with injectable fibrin glue scaffold can construct mature adipose tissue in vivo , which may stimulate angiogenesis, and improve retention rate of new-born tissue.
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Orbital Magnetization of Quantum Spin Hall Insulator Nanoparticles.
Potasz, P; Fernández-Rossier, J
2015-09-09
Both spin and orbital degrees of freedom contribute to the magnetic moment of isolated atoms. However, when inserted in crystals, atomic orbital moments are quenched because of the lack of rotational symmetry that protects them when isolated. Thus, the dominant contribution to the magnetization of magnetic materials comes from electronic spin. Here we show that nanoislands of quantum spin Hall insulators can host robust orbital edge magnetism whenever their highest occupied Kramers doublet is singly occupied, upgrading the spin edge current into a charge current. The resulting orbital magnetization scales linearly with size, outweighing the spin contribution for islands of a few nm in size. This linear scaling is specific of the Dirac edge states and very different from Schrodinger electrons in quantum rings. By modeling Bi(111) flakes, whose edge states have been recently observed, we show that orbital magnetization is robust with respect to disorder, thermal agitation, shape of the island, and crystallographic direction of the edges, reflecting its topological protection.
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Lifetime Estimation of the Upper Stage of GSAT-14 in Geostationary Transfer Orbit.
Jeyakodi David, Jim Fletcher; Sharma, Ram Krishan
2014-01-01
The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days.
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Lifetime Estimation of the Upper Stage of GSAT-14 in Geostationary Transfer Orbit
Jeyakodi David, Jim Fletcher; Sharma, Ram Krishan
2014-01-01
The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days. PMID:27437491
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NASA Astrophysics Data System (ADS)
Avila, Edward R.
The Electric Insertion Transfer Experiment (ELITE) is an Air Force Advanced Technology Transition Demonstration which is being executed as a cooperative Research and Development Agreement between the Phillips Lab and TRW. The objective is to build, test, and fly a solar-electric orbit transfer and orbit maneuvering vehicle, as a precursor to an operational electric orbit transfer vehicle (EOTV). This paper surveys some of the analysis tools used to do parametric studies and discusses the study results. The primary analysis tool was the Electric Vehicle Analyzer (EVA) developed by the Phillips Lab and modified by The Aerospace Corporation. It uses a simple orbit averaging approach to model low-thrust transfer performance, and runs in a PC environment. The assumptions used in deriving the EVA math model are presented. This tool and others surveyed were used to size the solar array power required for the spacecraft, and develop a baseline mission profile that meets the requirements of the ELITE mission.
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Operational Experience with Autonomous Star Trackers on ESA Interplanetary Spacecraft
NASA Technical Reports Server (NTRS)
Lauer, Mathias; Jauregui, Libe; Kielbassa, Sabine
2007-01-01
Mars Express (MEX), Rosetta and Venus Express (VEX) are ESA interplanetary spacecrafts (S/C) launched in June 2003, March 2004 and November 2005, respectively. Mars Express was injected into Mars orbit end of 2003 with routine operations starting in spring 2004. Rosetta is since launch on its way to rendezvous comet Churyumov-Gerasimenko in 2014. It has completed several test and commissioning activities and is performing several planetary swingbys (Earth in spring 2005, Mars in spring 2007, Earth in autumn 2007 and again two years later). Venus Express has also started routine operations since the completion of the Venus orbit insertion maneuver sequence beginning of May 2006. All three S/C are three axes stabilized with a similar attitude and orbit control system (AOCS). The attitude is estimated on board using star and rate sensors and controlled using four reaction wheels. A bipropellant reaction control system with 10N thrusters serves for wheel off loadings and attitude control in safe mode. Mars Express and Venus Express have an additional 400N engine for the planetary orbit insertion. Nominal Earth communication is accomplished through a high gain antenna. All three S/C are equipped with a redundant set of autonomous star trackers (STR) which are based on almost the same hardware. The STR software is especially adapted for the respective mission. This paper addresses several topics related to the experience gained with the STR operations on board the three S/C so far.
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The systems impact of a concentrated solar array on a Jupiter orbiter
NASA Technical Reports Server (NTRS)
Rockey, D. E.; Bamford, R.; Hollars, M. G.; Klemetson, R. W.; Koerner, T. W.; Marsh, E. L.; Price, H.; Uphoff, C.
1981-01-01
Results of a study are presented suggesting that a Galileo Jupiter orbiting mission could be performed with a concentrated solar array power source. A baseline spacecraft design using concentrated arrays is given, and the overall spacecraft implications for attitude control, propulsion, power conditioning and the resultant spacecraft mass are examined. It is noted that while the concentrated array concept still requires extensive development effort, no insurmountable system level barriers preclude the use of a concentrated solar array on this difficult mission, with its stressing radiation environment, its lengthy periods of spacecraft shadowing as it passes behind Jupiter, and, finally, its large delta v burn required for orbital insertion.
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Usage of pre-flight data in short rendezvous mission of Soyuz-TMA spacecrafts
NASA Astrophysics Data System (ADS)
Murtazin, Rafail; Petrov, Nikolay
2014-01-01
The paper describes the reduction of the vehicle autonomous flight duration before docking to the ISS. The Russian Soyuz-TMA spacecraft dock to the ISS two days after launch. Due to the limited volume inside Soyuz-TMA the reduction of time until docking to the ISS is very important, since the long stay of the cosmonauts in the limited volume adds to the strain of the space flight. In the previous papers of the authors it was shown that the existing capabilities of Soyuz-TMA, the ISS and the ground control loop make it possible to transfer to the five-orbit rendezvous profile. However, the analysis of the cosmonauts' schedule on the launch day shows that its duration is at the allowable limit and that is why it is necessary to find a way to further reduce the flight duration of Soyuz-TMA before docking to less than five orbits. In a traditional rendezvous profile, the calculation of rendezvous burns begins only after determination of the actual vehicle insertion orbit. The paper describes an approach in which the first two rendezvous burns are performed as soon as the spacecraft reaches the reference orbit and the values of the burns are calculated prior to the launch based on the pre-flight data for the nominal insertion. This approach decreases the duration of the rendezvous by one orbit. The demonstration flight of a Progress vehicle using the proposed profile was implemented on August 1, 2012 and completely confirmed the correctness of the imbedded principles. The paper considers the possible improvements of the proposed approach and recovery from the contingencies.
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Parallel Fin ORU Thermal Interface for space applications. [Orbital Replaceable Unit
NASA Technical Reports Server (NTRS)
Stobb, C. A.; Limardo, Jose G.
1992-01-01
The Parallel Fin Thermal Interface has been developed as an Orbital Replaceable Unit (ORU) interface. The interface transfers heat from an ORU baseplate to a Heat Acquisition Plate (HAP) through pairs of fins sandwiched between insert plates that press against the fins with uniform pressure. The insert plates are spread apart for ORU baseplate separation and replacement. Two prototype interfaces with different fin dimensions were built (Model 140 and 380). Interfacing surface samples were found to have roughnesses of 56 to 89 nm. Conductance values of 267 to 420 W/sq m C were obtained for the 140 model in vacuum with interface pressures of 131 to 262 kPa (19 to 38 psi). Vacuum conductances ranging from 176 to 267 W/sq m F were obtained for the 380 model at interface pressures of 97 to 152 kPa (14 and 22 psi). Correlations from several sources were found to agree with test data within 20 percent using thermal math models of the interfaces.
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Anatomical study of the opossum (Didelphis albiventris) extraocular muscles.
Matheus, S M; Soares, J C; da Silva, A M; Seullner, G
1995-01-01
The anatomy of the extraocular muscles was studied in 10 adult opossums (Didelphis albiventris) of both sexes. Eight extraocular muscles were identified: 4 rectus muscles, 2 oblique muscles, the levator palpebrae superioris and the retractor ocular bulbi. The rectus muscles originate very close one to another between the orbital surfaces of the presphenoid and palatine bones. These muscles diverge on the way to their insertion which occurs at about 2 mm from the limbus. The levator palpebrae superioris originates with the dorsal rectus and is positioned dorsally in relation to it. The retractor ocular bulbi forms a cone which embraces the optic nerve and is located internally in relation to the rectus muscles. The dorsal oblique originates on the presphenoid bone and after a tendinous trajectory through a trochlea on the medial wall of the orbit, inserts into the ocular bulb. The only muscle arising from the anterior orbital floor is the ventral oblique. The main nerve supply for these muscles is the oculomotor, except for the dorsal oblique which is innervated by the trochlear nerve, and the lateral rectus which is innervated by the abducens nerve. The retractor ocular bulbi receives branches from the inferior division of the oculomotor nerve and some branches from the abducens nerve. Images Fig. 1 Fig. 2 Fig. 3 PMID:7649843
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2006-03-15
KENNEDY SPACE CENTER, FLA. - Inside the orbiter mockup at NASA Kennedy Space Center's Shuttle Landing Facility, volunteer "astronaut" Charlie Plain, with InDyne Inc., gets settled in a seat with the help of United Space Alliance Insertion Tech Mike Thompson before a simulated emergency landing of a shuttle crew. Known as a Mode VI exercise, the operation uses volunteer workers from the Center to pose as astronauts. The purpose of the simulation is to exercise emergency preparedness personnel, equipment and facilities in rescuing astronauts from a downed orbiter and providing immediate medical attention. Photo credit: NASA/George Shelton
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2006-03-15
KENNEDY SPACE CENTER, FLA. - Inside the orbiter mockup at NASA Kennedy Space Center's Shuttle Landing Facility, volunteer "astronaut" Jeremy Garcia, with United Space Alliance (USA), is helped with his launch and entry suit by USA Insertion Tech George Brittingham before a simulated emergency landing of a shuttle crew. Known as a Mode VI exercise, the operation uses volunteer workers from the Center to pose as astronauts. The purpose of the simulation is to exercise emergency preparedness personnel, equipment and facilities in rescuing astronauts from a downed orbiter and providing immediate medical attention. Photo credit: NASA/George Shelton
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Removal of instrument signature from Mariner 9 television images of Mars
NASA Technical Reports Server (NTRS)
Green, W. B.; Jepsen, P. L.; Kreznar, J. E.; Ruiz, R. M.; Schwartz, A. A.; Seidman, J. B.
1975-01-01
The Mariner 9 spacecraft was inserted into orbit around Mars in November 1971. The two vidicon camera systems returned over 7300 digital images during orbital operations. The high volume of returned data and the scientific objectives of the Television Experiment made development of automated digital techniques for the removal of camera system-induced distortions from each returned image necessary. This paper describes the algorithms used to remove geometric and photometric distortions from the returned imagery. Enhancement processing of the final photographic products is also described.
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Closeup View - Astronaut John Glenn - Insertion - Mercury Capsule - Cape
1962-02-20
S62-01004 (1962) --- Astronaut John H. Glenn Jr., pilot of the Mercury Atlas 6 (MA-6) mission, participates in Mercury egress training during MA-6 preflight preparations. Glenn made the free world's first manned Earth-orbital flight on Feb. 20, 1962. Photo credit: NASA
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Rapid evaluation of ion thruster lifetime using optical emission spectroscopy
NASA Technical Reports Server (NTRS)
Rock, B. A.; Mantenieks, M. A.; Parsons, M. L.
1985-01-01
A major life-limiting phenomenon of electric thrusters is the sputter erosion of discharge chamber components. Thrusters for space propulsion are required to operate for extended periods of time, usually in excess of 10,000 hr. Lengthy and very costly life-tests in high-vacuum facilities have been required in the past to determine the erosion rates of thruster components. Alternative methods for determining erosion rates which can be performed in relatively short periods of time at considerably lower costs are studied. An attempt to relate optical emission intensity from an ion bombarded surface (screen grid) to the sputtering rate of that surface is made. The model used a kinetic steady-state (KSS) approach, balancing the rates of population and depopulation of ten low-lying excited states of the sputtered molybdenum atom (MoI) with those of the ground state to relate the spectral intensities of the various transitions of the MoI to the population densities. Once this is accomplished, the population density can be related to the sputtering rate of the target. Radiative and collisional modes of excitation and decay are considered. Since actual data has not been published for MoI excitation rate and decay constants, semiempirical equations are used. The calculated sputtering rate and intensity is compared to the measured intensity and sputtering rates of the 8 and 30 cm ion thrusters.
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Rapid evaluation of ion thruster lifetime using optical emission spectroscopy
NASA Technical Reports Server (NTRS)
Rock, B. A.; Parsons, M. L.; Mantenieks, M. A.
1985-01-01
A major life-limiting phenomenon of electric thrusters is the sputter erosion of discharge chamber components. Thrusters for space propulsion are required to operate for extended periods of time, usually in excess of 10,000 hr. Lengthy and very costly life-tests in high-vacuum facilities have been required in the past to determine the erosion rates of thruster components. Alternative methods for determining erosion rates which can be performed in relatively short periods of time at considerably lower costs are studied. An attempt to relate optical emission intensity from an ion bombarded surface (screen grid) to the sputtering rate of that surface is made. The model used a kinetic steady-state (KSS) approach, balancing the rates of population and depopulation of ten low-lying excited states of the sputtered molybdenum atom (MoI) with those of the ground state to relate the spectral intensities of the various transitions of the MoI to the population densities. Once this is accomplished, the population density can be related to the sputting rate of the target. Radiative and collisional modes of excitation and decay are considered. Since actual data has not been published for MoI excitation rate and decay constants, semiempirical equations are used. The calculated sputtering rate and intensity is compared to the measured intensity and sputtering rates of the 8 and 30 cm ion thrusters.
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Mon Océan & Moi : Network and Teamwork to Better Connect People, Science and Education
NASA Astrophysics Data System (ADS)
Scheurle, C.
2016-02-01
The project « mon océan & moi » can be described as a platform hosting several outreach activities. Some of these address non-scientific audiences in an international/national context and are specifically developed to reach out into school environments. The multidisciplinary team composed of senior and early-career scientists, science communicators and facilitators, school teachers and educators etc. shares common objectives based on (net-)work in a participatory way, so as to propose science-based dissemination with a long-term vision as well as to stimulate critical thinking, ideas and exchanges. Within this context, Internet is certainly an extremely useful tool accompanying the manifold efforts to "best" inform and communicate with the targeted audiences. However, it remains challenging to create opportunities for dialogue at the interface of science and education … and to encourage this dialogue to carry on. « mon océan & moi » covers a few successful outreach activities ("adopt a float" and "MEDITES") that involve scientists and teachers as well as students from universities and schools. Encouraged by the local school authority, these activities aim at different educational levels and suggest a continuous "workflow" combined with specific events (such as training courses, science fairs) during which particular contributions are highlighted. As their approach principally favors teamwork, the most positive outcome observed has been the creation of partnerships truly connecting the people …
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Flight Results of the Chandra X-ray Observatory Inertial Upper Stage Space Mission
NASA Technical Reports Server (NTRS)
Tillotson, R.; Walter, R.
2000-01-01
Under contract to NASA, a specially configured version of the Boeing developed Inertial Upper Stage (IUS) booster was provided by Boeing to deliver NASA's 1.5 billion dollar Chandra X-Ray Observatory satellite into a highly elliptical transfer orbit from a Shuttle provided circular park orbit. Subsequently, the final orbit of the Chandra satellite was to be achieved using the Chandra Integral Propulsion System (IPS) through a series of IPS burns. On 23 July 1999 the Shuttle Columbia (STS-93) was launched with the IUS/Chandra stack in the Shuttle payload bay. Unfortunately, the Shuttle Orbiter was unexpectantly inserted into an off-nominal park orbit due to a Shuttle propulsion anomaly occurring during ascent. Following the IUS/Chandra on-orbit deployment from the Shuttle, at seven hours from liftoff, the flight proven IUS GN&C system successfully injected Chandra into the targeted transfer orbit, in spite of the off-nominal park orbit. This paper describes the IUS GN&C system, discusses the specific IUS GN&C mission data load development, analyses and testing for the Chandra mission, and concludes with a summary of flight results for the IUS part of the Chandra mission.
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Mission Design Overview for Mars 2003/2005 Sample Return Mission
NASA Technical Reports Server (NTRS)
Lee, Wayne J.; DAmario, Louis A.; Roncoli, Ralph B.; Smith, John C.
2000-01-01
In May 2003, a new and exciting chapter in Mars exploration will begin with the launch of the first of three spacecraft that will collectively contribute toward the goal of delivering samples from the Red Planet to Earth. This mission is called Mars Sample Return (MSR) and will utilize both the 2003 and 2005 launch opportunities with an expected sample return in October 2008. NASA and CNES are major partners in this mission. The baseline mission mode selected for MSR is Mars orbit rendezvous (MOR), analogous in concept to the lunar orbit rendezvous (LOR) mode used for Apollo in the 1960s. Specifically, MSR will employ two NASA-provided landers of nearly identical design and one CNES-provided orbiter carrying a NASA payload of rendezvous sensors, orbital capture mechanisms, and an Earth entry vehicle (EEV). The high-level concept is that the landers will launch surface samples into Mars orbit, and the orbiter will retrieve the samples in orbit and then carry them back to Earth. The first element to depart for Mars will be one of the two landers. Currently, it is proposed that an intermediate class launch vehicle, such as the Boeing Delta 3 or Lockheed Martin Atlas 3A, will launch this 1800-kg lander from Cape Canaveral during the May 2003 opportunity. The lander will utilize a Type-1 transfer trajectory with an arrival at Mars in mid-December 2003. Landing will be aided by precision approach navigation and a guided hypersonic entry to achieve a touchdown accuracy of 10 km or better. Although the exact landing site has not yet been determined, it is estimated that lander resource constraints will limit the site to between 15 degrees north and south latitudes. Following touchdown, the lander will deploy a six-wheeled, 60-kg rover carrying an extensive suite of instruments designed to aid in the analysis of the local terrain and collection of core samples from selected rocks. The surface mission is currently designed around a concept called the surface traverse. Each traverse will involve the rover exploring a selected area of terrain up to 100 meters from the lander, the collection of rock core samples, and the delivery of the samples from the traverse back to a sample canister on the lander. Planning estimates indicate that up to three traverses may be possible during the expected 90-sol lifetime of the lander. The canister that will receive the samples from the rover will be attached to the top stage of a small solid-fueled rocket mounted to the deck of the lander. This rocket is called the Mars Ascent Vehicle (MAV) and consists of three stages weighing a total of about 140 kg. After the conclusion of the surface mission, the MAV will lift-off and insert the sample canister into a near-circular orbit with an altitude of about 600 km and inclination of 45 degrees. The sample canister will wait in this orbit until it is retrieved by the orbiter sometime in early 2007. In August 2005, the second lander and a CNES-provided orbiter weighing 2700 kg will depart for Mars. Currently, it is proposed that a single Ariane 5 provided by CNES will launch both of these two elements onto a Type-2 transfer trajectory. Although the orbiter and lander will be launched together, they will separate shortly after injection and will fly to Mars as two independent spacecraft. However, both spacecraft will perform a maneuver between 10 and 15 days after launch so that their arrival times at Mars differ by between 12 and 24 hours. This scheme will reduce the operational complexity at the encounter date. A set of four 60-kg surface probes will ride piggyback on the orbiter to Mars. These CNES-provided probes are called Netlanders and will serve as surface stations for scientific investigations independent of the Mars Sample Return goals. Starting approximately one month prior to arrival at Mars, the orbiter will begin to release the Netlanders one at a time. Each release cycle will take several days, and will include time for precision navigation to execute one or two maneuvers that will target the Netlanders to their proper landing site. All four deployment cycles will be completed prior to 10 days before arrival. Both the orbiter and lander will arrive in late-July 2006. Upon arrival, the lander will perform a precision landing and surface mission similar in concept to the one that was executed during the 2003 opportunity. Although the landing site for the 2005 opportunity has not been selected, it is expected to be different from the 2003 site to enhance the diversity of the collected samples. The orbiter's arrival at Mars will be highlighted by the first use of aerocapture to insert a spacecraft into a capture orbit around another planet. The choice of aerocapture, as opposed to a propulsive orbit insertion, was considered mission enabling due to a reduction of over 2000 m/s in mission AV. Aerocapture will be targeted to produce a 250 km x 1400 km capture orbit with an inclination of 45 degrees. Current analysis indicates that achieving this goal will require approximately six minutes of flight deep in the atmosphere with a targeted periapsis of approach of about 43 km. After factoring into account the penalty for carrying a heat shield to survive aerocapture, the net savings compared to a propulsive orbital insertion amounts to several hundred kilograms.
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14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.
Code of Federal Regulations, 2014 CFR
2014-01-01
... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...
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14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.
Code of Federal Regulations, 2010 CFR
2010-01-01
... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...
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14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.
Code of Federal Regulations, 2012 CFR
2012-01-01
... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...
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14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.
Code of Federal Regulations, 2011 CFR
2011-01-01
... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...
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Astronaut John Glenn, Jr. - Insertion - Mercury Spacecraft - Cape
1962-02-20
S62-00371 (20 Feb. 1962) --- Mercury astronaut John H. Glenn Jr., pilot of the Mercury-Atlas 6 (MA-6) spaceflight, enters the Mercury "Friendship 7" spacecraft during the MA-6 prelaunch preparations at Cape Canaveral, Florida. Glenn became the first American to orbit Earth. Photo credit: NASA
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14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.
Code of Federal Regulations, 2013 CFR
2013-01-01
... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...
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NASA Technical Reports Server (NTRS)
Craig, Larry G.
2010-01-01
This slide presentation reviews three failures of software and how the failures contributed to or caused the failure of a launch or payload insertion into orbit. In order to avoid these systematic failures in the future, failure mitigation strategies are suggested for use.
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Mamlin, Joseph; Kimaiyo, Sylvester; Lewis, Stephen; Tadayo, Hannah; Jerop, Fanice Komen; Gichunge, Catherine; Petersen, Tomeka; Yih, Yuehwern; Braitstein, Paula
2009-01-01
The Academic Model Providing Access to Healthcare (AMPATH) is a partnership between Moi Teaching and Referral Hospital, Moi University School of Medicine, and a consortium of universities led by Indiana University. AMPATH has over 50 000 patients in active care in 17 main clinics around western Kenya. Despite antiretroviral therapy, many patients were not recovering their health because of food insecurity. AMPATH therefore established partnerships with the World Food Program and United States Agency for International Development and began high-production farms to complement food support. Today, nutritionists assess all AMPATH patients and dependents for food security and refer those in need to the food program. We describe the implementation, challenges, and successes of this program. PMID:19059851
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Zhu, Bao-Song; Yu, Li-Yan; Zhao, Kui; Wu, Yong-You; Cheng, Xiao-Li; Wu, Yong; Zhong, Feng-Yun; Gong, Wei; Chen, Qiang; Xing, Chun-Gen
2013-01-01
AIM: To investigate the effects of small interfering RNA (siRNA)-mediated inhibition of Class I phosphoinositide 3-kinase (Class I PI3K) signal transduction on the proliferation, apoptosis, and autophagy of gastric cancer SGC7901 and MGC803 cells. METHODS: We constructed the recombinant replication adenovirus PI3K(I)-RNA interference (RNAi)-green fluorescent protein (GFP) and control adenovirus NC-RNAi-GFP, and infected it into human gastric cancer cells. MTT assay was used to determine the growth rate of the gastric cancer cells. Activation of autophagy was monitored with monodansylcadaverine (MDC) staining after adenovirus PI3K(I)-RNAi-GFP and control adenovirus NC-RNAi-GFP treatment. Immunofluorescence staining was used to detect the expression of microtubule-associated protein 1 light chain 3 (LC3). Mitochondrial membrane potential was measured using the fluorescent probe JC-1. The expression of autophagy was monitored with MDC, LC3 staining, and transmission electron microscopy. Western blotting was used to detect p53, Beclin-1, Bcl-2, and LC3 protein expression in the culture supernatant. RESULTS: The viability of gastric cancer cells was inhibited after siRNA targeting to the Class I PI3K blocked Class I PI3K signal pathway. MTT assays revealed that, after SGC7901 cancer cells were treated with adenovirus PI3K(I)-RNAi-GFP, the rate of inhibition reached 27.48% ± 2.71% at 24 h, 41.92% ± 2.02% at 48 h, and 50.85% ± 0.91% at 72 h. After MGC803 cancer cells were treated with adenovirus PI3K(I)-RNAi-GFP, the rate of inhibition reached 24.39% ± 0.93% at 24 h, 47.00% ± 0.87% at 48 h, and 70.30% ± 0.86% at 72 h (P < 0.05 compared to control group). It was determined that when 50 MOI, the transfection efficiency was 95% ± 2.4%. Adenovirus PI3K(I)-RNAi-GFP (50 MOI) induced mitochondrial dysfunction and activated cell apoptosis in SGC7901 cells, and the results described here prove that RNAi of Class I PI3K induced apoptosis in SGC7901 cells. The results showed that adenovirus PI3K(I)-RNAi-GFP transfection induced punctate distribution of LC3 immunoreactivity, indicating increased formation of autophagosomes. The results showed that the basal level of Beclin-1 and LC3 protein in SGC7901 cells was low. After incubating with adenovirus PI3K(I)-RNAi-GFP (50 MOI), Beclin-1, LC3, and p53 protein expression was significantly increased from 24 to 72 h. We also found that Bcl-2 protein expression down-regulated with the treatment of adenovirus PI3K(I)-RNAi-GFP (50 MOI). A number of isolated membranes, possibly derived from ribosome-free endoplasmic reticulum, were seen. These isolated membranes were elongated and curved to engulf a cytoplasmic fraction and organelles. We used transmission electron microscopy to identify ultrastructural changes in SGC7901 cells after adenovirus PI3K(I)-RNAi-GFP (50 MOI) treatment. Control cells showed a round shape and contained normal-looking organelles, nucleus, and chromatin, while adenovirus PI3K(I)-RNAi-GFP (50 MOI)-treated cells exhibited the typical signs of autophagy. CONCLUSION: After the Class I PI3K signaling pathway has been blocked by siRNA, the proliferation of cells was inhibited and the apoptosis of gastric cancer cells was enhanced. PMID:23555164
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NASA Technical Reports Server (NTRS)
Zuber, Maria T.; Smith, David E.; Asmar, Sami W.; Alomon; Konopliv, Alexander S.; Lemoine, Frank G.; Melosh, H. Jay; Neumann, Gregory A.; Phillips. Roger J.; Solomon, Sean C.;
2012-01-01
The Gravity Recovery And Interior Laboratory (GRAIL) mission, a component of NASA's Discovery Program, launched successfully from Cape Canaveral Air Force Station on September 10, 2011. The dual spacecraft traversed independent, low-energy trajectories to the Moon via the EL-1 Lagrange point and inserted into elliptical, 11.5-hour polar orbits around the Moon on December 31, 2011, and January 1, 2012. The spacecraft are currently executing a series of maneuvers to circularize their orbits at 55-km mean altitude. Once the mapping orbit is achieved, the spacecraft will undergo additional maneuvers to align them into mapping configuration. The mission is on track to initiate the Science Phase on March 8, 2012.
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NASA Technical Reports Server (NTRS)
Hershey, Matthew P.; Newswander, Daniel R.; Evernden, Brent A.
2016-01-01
On January 29, 2016, the Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, deployed Lonestar from the ISS. The deployment of Lonestar, a collaboration between Texas A&M University and the University of Texas at Austin, continued to showcase the simplicity and reliability of the Cyclops deployment system. Cyclops, a NASA-developed, dedicated 10-100 kg class ISS SmallSat deployment system, utilizes the Japanese airlock and robotic systems to seamlessly insert SmallSats into orbit. This paper will illustrate Cyclops' successful deployment of Lonestar from the ISS as well as outline its concept of operations, interfaces, requirements, and processes.
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Space Transportation System (STS) propellant scavenging system study. Volume 1: Technical report
NASA Technical Reports Server (NTRS)
1985-01-01
The objectives are to define the most efficient and cost effective methods for scavenging cryogenic and storable propellants and then define the requirements for these scavenging systems. For cryogenic propellants, scavenging is the transfer of propellants from the Shuttle orbiter external tank (ET) and/or main propulsion subsystems (MPS) propellant lines into storage tanks located in the orbiter payload bay for delivery to the user station by a space based transfer stage or the Space Transportation System (STS) by direct insertion. For storable propellants, scavenging is the direct transfer from the orbital maneuvering subsystem (OMS) and/or tankage in the payload bay to users in LEO as well as users in the vicinity of the Space Station.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, United Space Alliance worker Craig Meyer fits an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttles Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, an External Tank (ET) digital still camera is positioned into the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis to determine if it fits properly. NASA is pursuing use of the camera, beginning with the Shuttles Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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2004-09-17
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an External Tank (ET) digital still camera is positioned into the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis to determine if it fits properly. NASA is pursuing use of the camera, beginning with the Shuttle’s Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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2004-09-17
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, United Space Alliance worker Craig Meyer fits an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttle’s Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
1983-01-01
The approach pictures taken by the Viking 1 and Viking 2 spacecrafts two days before their Mars orbital insertion maneuvers were analyzed in order to search for new satellites within the orbit of Phobos. To accomplish this task, search procedure and analysis strategy were formulated, developed and executed using the substantial image processing capabilities of the Image Processing Laboratory at the Jet Propulsion Laboratory. The development of these new search capabilities should prove to be valuable to NASA in processing of image data obtained from other spacecraft missions. The result of applying the search procedures to the Viking approach pictures was as follows: no new satellites of comparable size (approx. 20 km) and brightness to Phobos or Demios were detected within the orbit of Phobos.
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NASA Technical Reports Server (NTRS)
Hyde, T. W.; Alexander, W. M.
1989-01-01
In 1967, Lunar Explorer 35 was launched from the earth and placed into a stable orbit around the moon. The data from the dust particle experiment on this spacecraft were essentially continuous over a 5-yr period from the time of insertion in lunar orbit. Analysis of this data has been interpreted to show that micron-sized lunar ejecta leave the moon and traverse through selenocentric and cislunar space and obtain either interplanetary/heliocentric orbits or intercept the earth's magnetosphere and move into geocentric orbits. Extensive studies of the orbital trajectories of lunar particles in this size range have now been conducted that include a calculation of the solar radiation force using the full Mie scattering theory. A significant flux of particles with radii less than 0.1 micron are found to intercept the earth's magnetopause surface. This flux is shown to be strongly dependent upon both the particle's density and its index of refraction.
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Saturn's Magnetic Field from the Cassini Grand Finale orbits
NASA Astrophysics Data System (ADS)
Dougherty, M. K.; Cao, H.; Khurana, K. K.; Hunt, G. J.; Provan, G.; Kellock, S.; Burton, M. E.; Burk, T. A.
2017-12-01
The fundamental aims of the Cassini magnetometer investigation during the Cassini Grand Finale orbits were determination of Saturn's internal planetary magnetic field and the rotation rate of the deep interior. The unique geometry of the orbits provided an unprecedented opportunity to measure the intrinsic magnetic field at close distances never before encountered. The surprising close alignment of Saturn's magnetic axis with its spin axis, known about since the days of Pioneer 11, has been a focus of the team's analysis since Cassini Saturn Orbit Insertion. However, the varying northern and southern magnetospheric planetary period oscillations, which fill the magnetosphere, has been a factor in masking the field signals from the interior. Here we describe an overview of the magnetometer results from the Grand Finale orbits, including confirmation of the extreme axisymmetric nature of the planetary magnetic field, implications for knowledge of the rotation rate and the behaviour of external magnetic fields (arising from the ring current, field aligned currents both at high and low latitudes and the modulating effect of the planetary period oscillations).
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Radiation exposure and performance of multiple burn LEO-GEO orbit transfer trajectories
NASA Technical Reports Server (NTRS)
Gorland, S. H.
1985-01-01
Many potential strategies exist for the transfer of spacecraft from low Earth orbit (LEO) to geosynchronous (GEO) orbit. One strategy has generally been utilized, that being a single impulsive burn at perigee and a GEO insertion burn at apogee. Multiple burn strategies were discussed for orbit transfer vehicles (OTVs) but the transfer times and radiation exposure, particularly for potentially manned missions, were used as arguments against those options. Quantitative results concerning the trip time and radiation encountered by multiple burn orbit transfer missions in order to establish the feasibility of manned missions, the vulnerability of electronics, and the shielding requirements are presented. The performance of these multiple burn missions is quantified in terms of the payload and propellant variances from the minimum energy mission transfer. The missions analyzed varied from one to eight perigee burns and ranged from a high thrust, 1 g acceleration, cryogenic hydrogen-oxygen chemical prpulsion system to a continuous burn, 0.001 g acceleration, hydrogen fueled resistojet propulsion system with a trip time of 60 days.
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NASA Technical Reports Server (NTRS)
Quast, Peter; Tung, Frank; West, Mark; Wider, John
2000-01-01
The Chandra X-ray Observatory (CXO, formerly AXAF) is the third of the four NASA great observatories. It was launched from Kennedy Space Flight Center on 23 July 1999 aboard the Space Shuttle Columbia and was successfully inserted in a 330 x 72,000 km orbit by the Inertial Upper Stage (IUS). Through a series of five Integral Propulsion System burns, CXO was placed in a 10,000 x 139,000 km orbit. After initial on-orbit checkout, Chandra's first light images were unveiled to the public on 26 August, 1999. The CXO Pointing Control and Aspect Determination (PCAD) subsystem is designed to perform attitude control and determination functions in support of transfer orbit operations and on-orbit science mission. After a brief description of the PCAD subsystem, the paper highlights the PCAD activities during the transfer orbit and initial on-orbit operations. These activities include: CXO/IUS separation, attitude and gyro bias estimation with earth sensor and sun sensor, attitude control and disturbance torque estimation for delta-v burns, momentum build-up due to gravity gradient and solar pressure, momentum unloading with thrusters, attitude initialization with star measurements, gyro alignment calibration, maneuvering and transition to normal pointing, and PCAD pointing and stability performance.
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Jovian system science issues and implications for a Mariner Jupiter Orbiter mission
NASA Technical Reports Server (NTRS)
Beckman, J. C.; Miner, E. D.
1975-01-01
Science goals for missions to Jupiter in the early 1980's are reviewed and a case is made for the science community to play the key role in assigning relative priorities for these goals. A reference set of measurement requirements and their priorities is established and those high priority goals that are most demanding on spacecraft and mission design are used to develop a reference mission concept. An orbiter mission is required to satisfy a majority of the measurements, and a spacecraft data handling capability as least equivalent to the Mariner Jupiter/Saturn spacecraft is the major system design driver. This reference Mission Concept is called Mariner Jupiter Orbiter. The remaining measurement requirements are reviewed in light of the potential science return of this mission, and certain options are developed to augment this science return. Two attractive options fulfill high priority objectives not achieved by the reference Mariner Jupiter Orbiter mission alone: an atmospheric entry probe, released prior to orbit insertion; and a daughter satellite dedicated to particle and fields measurements, ejected into an independent orbit about Jupiter.
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Independent Orbiter Assessment (IOA): Analysis of the reaction control system, volume 1
NASA Technical Reports Server (NTRS)
Burkemper, V. J.; Haufler, W. A.; Odonnell, R. A.; Paul, D. J.
1987-01-01
The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. This report documents the independent analysis results for the Reaction Control System (RCS). The purpose of the RCS is to provide thrust in and about the X, Y, Z axes for External Tank (ET) separation; orbit insertion maneuvers; orbit translation maneuvers; on-orbit attitude control; rendezvous; proximity operations (payload deploy and capture); deorbit maneuvers; and abort attitude control. The RCS is situated in three independent modules, one forward in the orbiter nose and one in each OMS/RCS pod. Each RCS module consists of the following subsystems: Helium Pressurization Subsystem; Propellant Storage and Distribution Subsystem; Thruster Subsystem; and Electrical Power Distribution and Control Subsystem. Of the failure modes analyzed, 307 could potentially result in a loss of life and/or loss of vehicle.
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NASA Technical Reports Server (NTRS)
Byrnes, D. V.; Carney, P. C.; Underwood, J. W.; Vogt, E. D.
1974-01-01
The six month effort was responsible for the development, test, conversion, and documentation of computer software for the mission analysis of missions to halo orbits about libration points in the earth-sun system. The software consisting of two programs called NOMNAL and ERRAN is part of the Space Trajectories Error Analysis Programs. The program NOMNAL targets a transfer trajectory from earth on a given launch date to a specified halo orbit on a required arrival date. Either impulsive or finite thrust insertion maneuvers into halo orbit are permitted by the program. The transfer trajectory is consistent with a realistic launch profile input by the user. The second program ERRAN conducts error analyses of the targeted transfer trajectory. Measurements including range, doppler, star-planet angles, and apparent planet diameter are processed in a Kalman-Schmidt filter to determine the trajectory knowledge uncertainty.
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Lunar lander conceptual design
NASA Technical Reports Server (NTRS)
Stecklein, J. M.; Petro, A. J.; Stump, W. R.; Adorjan, A. S.; Chambers, T. V.; Donofrio, M.; Hirasaki, J. K.; Morris, O. G.; Nudd, G.; Rawlings, R. P.
1992-01-01
This paper is a first look at the problems of building a lunar lander to support a small lunar surface base. A series of trade studies was performed to define the lander. The initial trades concerned choosing number of stages, payload mass, parking orbit altitude, and propellant type. Other important trades and issues included plane change capability, propellant loading and maintenance location, and reusability considerations. Given a rough baseline, the systems were then reviewed. A conceptual design was then produced. The process was carried through only one iteration. Many more iterations are needed. A transportation system using reusable, aerobraked orbital transfer vehicles (OTV's) is assumed. These OTV's are assumed to be based and maintained at a low Earth orbit (LEO) space station, optimized for transportation functions. Single- and two-stage OTV stacks are considered. The OTV's make the translunar injection (TLI), lunar orbit insertion (LOI), and trans-Earth injection (TEI) burns, as well as midcourse and perigee raise maneuvers.
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Stable low-altitude orbits around Ganymede considering a disturbing body in a circular orbit
NASA Astrophysics Data System (ADS)
Cardoso dos Santos, J.; Carvalho, J. P. S.; Vilhena de Moraes, R.
2014-10-01
Some missions are being planned to visit Ganymede like the Europa Jupiter System Mission that is a cooperation between NASA and ESA to insert the spacecraft JGO (Jupiter Ganymede Orbiter) into Ganymedes orbit. This comprehension of the dynamics of these orbits around this planetary satellite is essential for the success of this type of mission. Thus, this work aims to perform a search for low-altitude orbits around Ganymede. An emphasis is given in polar orbits and it can be useful in the planning of space missions to be conducted around, with respect to the stability of orbits of artificial satellites. The study considers orbits of artificial satellites around Ganymede under the influence of the third-body (Jupiter's gravitational attraction) and the polygenic perturbations like those due to non-uniform distribution of mass (J_2 and J_3) of the main body. A simplified dynamic model for these perturbations is used. The Lagrange planetary equations are used to describe the orbital motion of the artificial satellite. The equations of motion are developed in closed form to avoid expansions in eccentricity and inclination. The results show the argument of pericenter circulating. However, low-altitude (100 and 150 km) polar orbits are stable. Another orbital elements behaved variating with small amplitudes. Thus, such orbits are convenient to be applied to future space missions to Ganymede. Acknowledgments: FAPESP (processes n° 2011/05671-5, 2012/12539-9 and 2012/21023-6).
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Particularité de la cystinose infantile chez l'enfant tunisien
Jellouli, Manel; Turkia, Hadhami Ben; Abidi, Kamel; Hammi, Yosra; Gargah, Tahar
2015-01-01
La cystinose est une maladie rare qui résulte d'un défaut d'expression de la cystinosine transporteur de la cystine du lysosome. La forme infantile est la plus fréquente et la plus sévère. Elle conduit en dehors du traitement à l'insuffisance rénale chronique terminale au cours de la première décade de la vie. Nous rapportons l'expérience tunisienne de la cystinose infantile. Une étude rétrospective sur une période de 25 ans (1990-2014) était menée. Nous avons colligé 8 dossiers de cystinose infantile dans les services de pédiatrie des hôpitaux Charles Nicolle de Tunis et la Rabta de Tunis. Il s'agissait de 5garçons et de 3 filles. L’âge moyen au début des symptômes était de 6,37 mois (2-14 mois). L’âge moyen au moment du diagnostic était de 4 ans (7 mois-6 ans). Les dépôts cornéens de cystine étaient observés chez 7 patients. Sept patients présentaient une hypothyroïdie. La cystéamine était prescrite chez 6 patients. L’âge moyen au moment de la prescription de cystéamine était de 5,12 ans (8 mois- 13 ans). L’âge moyen lors de passage en insuffisance rénale chronique était de 3,4 ans. L’âge moyen lors du passage en insuffisance rénale chronique terminale était de 6,37 ans Actuellement, un patient garde une fonction rénale normale, trois patients sont en insuffisance rénale, deux patients sont décédés et un patient était transplanté. Il faut instaurer dans notre pays les moyens de diagnostic pour traiter tôt la maladie. PMID:26985266
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Wen, Yong; Lan, Jing; Huang, Haiyun; Yu, Meijiao; Cui, Jun; Liang, Jin; Jiang, Baoqi; Xu, Xin
2012-09-01
To establish human periodontal ligament stem cells (hPDLSC) with high and stable expression of enhanced green fluorescent protein (eGFP) and to obtain an ideal vector expression system that suitable for gene therapy in periodontal tissue engineering. hPDLSCs were transfected with eGFP for 48h via different MOI (25, 50, 100, 200 and 400) by lentiviral vector, the transfection efficiency was evaluated by fluorescent microscopy and flow cytometry, and transfected hPDLSCs proliferation was evaluated by MTT. Pluripotent, differentiation capacity and ALP expression status were determined further. Osteoblast-associated genes expressions for osteogenesis were evaluated by quantitative-PCR. In addition, rat molar periodontal fenestration defect model was used for evaluating periodontal tissue engineering. The transfection efficiency after 48h were 44.7%, 60.9%, 71.7%, 85.8%, and 86.9% respectively. There was no significant effect of transfection (at different MOI levels of 25, 50, 100, and 200) on the proliferation of hPDLSCs (designated as eGFP-hPDLSCs) compared with hPDLSCs (P>0.05). However, proliferation of eGFP hPDLSCs at MOI 400 became slower (P<0.05). Both eGFP hPDLSCs and hPDLSCs were able to differentiate into osteocytes and adipocytes under certain conditioned media. At 7 days, expression levels of COL-1, RUNX2 in hPDLSCS were higher than those in eGFP hPDLSCs (P<0.05); expression levels of ALP and OPN in eGFP hPDLSCs were similar to those in hPDLSCs (P>0.05). Newly regenerated bone formation was observed in the defect model used. Among the transfection conditions, 48h transfection at MOI 200 is optimal for labelling hPDLSCs with eGFP in a lentiviral vector. There is no change in capability of the eGFP hPDLSCs osteogenesis. The lentiviral vector with eGFP is an appropriate expression vector system and hPDLSCs are ideal seeding cells for gene therapy in periodontal tissue engineering. Copyright © 2012 Elsevier Ltd. All rights reserved.
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Kateera, Fredrick; Nsobya, Sam L; Tukwasibwe, Stephen; Mens, Petra F; Hakizimana, Emmanuel; Grobusch, Martin P; Mutesa, Leon; Kumar, Nirbhay; van Vugt, Michele
2016-04-26
Malaria remains a public health challenge in sub-Saharan Africa with Plasmodium falciparum being the principal cause of malaria disease morbidity and mortality. Plasmodium falciparum virulence is attributed, in part, to its population-level genetic diversity-a characteristic that has yet to be studied in Rwanda. Characterizing P. falciparum molecular epidemiology in an area is needed for a better understand of malaria transmission and to inform choice of malaria control strategies. In this health-facility based survey, malaria case clinical profiles and parasite densities as well as parasite genetic diversity were compared among P. falciparum-infected patients identified at two sites of different malaria transmission intensities in Rwanda. Data on demographics and clinical features and finger-prick blood samples for microscopy and parasite genotyping were collected(.) Nested PCR was used to genotype msp-2 alleles of FC27 and 3D7. Patients' variables of age group, sex, fever (both by patient report and by measured tympanic temperatures), parasite density, and bed net use were found differentially distributed between the higher endemic (Ruhuha) and lower endemic (Mubuga) sites. Overall multiplicity of P. falciparum infection (MOI) was 1.73 but with mean MOI found to vary significantly between 2.13 at Ruhuha and 1.29 at Mubuga (p < 0.0001). At Ruhuha, expected heterozygosity (EH) for FC27 and 3D7 alleles were 0.62 and 0.49, respectively, whilst at Mubuga, EH for FC27 and 3D7 were 0.26 and 0.28, respectively. In this study, a higher geometrical mean parasite counts, more polyclonal infections, higher MOI, and higher allelic frequency were observed at the higher malaria-endemic (Ruhuha) compared to the lower malaria-endemic (Mubuga) area. These differences in malaria risk and MOI should be considered when choosing setting-specific malaria control strategies, assessing p. falciparum associated parameters such as drug resistance, immunity and impact of used interventions, and in proper interpretation of malaria vaccine studies.
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Autophagy Induced by Intracellular Infection of Propionibacterium acnes
Nakamura, Teruko; Furukawa, Asuka; Uchida, Keisuke; Ogawa, Tomohisa; Tamura, Tomoki; Sakonishi, Daisuke; Wada, Yuriko; Suzuki, Yoshimi; Ishige, Yuki; Minami, Junko; Akashi, Takumi
2016-01-01
Background Sarcoidosis is caused by Th1-type immune responses to unknown agents, and is linked to the infectious agent Propionibacterium acnes. Many strains of P. acnes isolated from sarcoid lesions cause intracellular infection and autophagy may contribute to the pathogenesis of sarcoidosis. We examined whether P. acnes induces autophagy. Methods Three cell lines from macrophages (Raw264.7), mesenchymal cells (MEF), and epithelial cells (HeLa) were infected by viable or heat-killed P. acnes (clinical isolate from sarcoid lymph node) at a multiplicity of infection (MOI) of 100 or 1000 for 1 h. Extracellular bacteria were killed by washing and culturing infected cells with antibiotics. Samples were examined by colony assay, electron-microscopy, and fluorescence-microscopy with anti-LC3 and anti-LAMP1 antibodies. Autophagy-deficient (Atg5-/-) MEF cells were also used. Results Small and large (≥5 μm in diameter) LC3-positive vacuoles containing few or many P. acnes cells (LC3-positive P. acnes) were frequently found in the three cell lines when infected by viable P. acnes at MOI 1000. LC3-positive large vacuoles were mostly LAMP1-positive. A few small LC3-positive/LAMP1-negative vacuoles were consistently observed in some infected cells for 24 h postinfection. The number of LC3-positive P. acnes was decreased at MOI 100 and completely abolished when heat-killed P. acnes was used. LC3-positive P. acnes was not found in autophagy-deficient Atg5-/- cells where the rate of infection was 25.3 and 17.6 times greater than that in wild-type Atg5+/+ cells at 48 h postinfection at MOI 100 and 1000, respectively. Electron-microscopic examination revealed bacterial cells surrounded mostly by a single-membrane including the large vacuoles and sometimes a double or multi-layered membrane, with occasional undigested bacterial cells in ruptured late endosomes or in the cytoplasm. Conclusion Autophagy was induced by intracellular P. acnes infection and contributed to intracellular bacterial killing as an additional host defense mechanism to endocytosis or phagocytosis. PMID:27219015
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Felli, M. C.; Parent, S.; Zelazo, P. D.; Tremblay, R. E.; Séguin, J. R.
2017-01-01
Résumé À la petite enfance, l’adaptation sociale de l’enfant dépend en partie des risques auxquels il est exposé dans son environnement. Toutefois, les mécanismes par lesquels les facteurs de risque opèrent leurs influences sur l’adaptation sociale de l’enfant sont peu documentés. Ainsi, cette étude examine dans un premier temps l’effet principal de l’adversité familiale, un cumul de facteurs de risque, sur les problèmes de comportement intériorisés et extériorisés, ainsi que sur la sécurité d’attachement des enfants d’âge préscolaire. Dans un deuxième temps, elle évalue le rôle médiateur du fonctionnement familial dans le lien entre l’adversité familiale et les problèmes de comportement de même qu’entre l’adversité familiale et la sécurité d’attachement des enfants d’âge préscolaire. Les 572 participants à l’étude (n=572) sont âgés entre cinq et 42 mois lors des mesures de l’adversité familiale et de 42 mois lors de la mesure des problèmes de comportement et du fonctionnement familial. Quatre-vingt d’entre eux (n=80) ont fait l’objet d’une mesure de sécurité d’attachement à 48 mois. Les résultats indiquent, d’abord, un effet principal de l’adversité familiale sur les problèmes de comportement intériorisés et extériorisés. Un effet médiateur significatif du fonctionnement familial est ensuite rapporté dans le lien entre l’adversité familiale et les problèmes de comportement intériorisés et extériorisés. Aucun effet significatif n’est observé pour la sécurité d’attachement des enfants de 48 mois. PMID:28567062
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Stochastic Analysis of Orbital Lifetimes of Spacecraft
NASA Technical Reports Server (NTRS)
Sasamoto, Washito; Goodliff, Kandyce; Cornelius, David
2008-01-01
A document discusses (1) a Monte-Carlo-based methodology for probabilistic prediction and analysis of orbital lifetimes of spacecraft and (2) Orbital Lifetime Monte Carlo (OLMC)--a Fortran computer program, consisting of a previously developed long-term orbit-propagator integrated with a Monte Carlo engine. OLMC enables modeling of variances of key physical parameters that affect orbital lifetimes through the use of probability distributions. These parameters include altitude, speed, and flight-path angle at insertion into orbit; solar flux; and launch delays. The products of OLMC are predicted lifetimes (durations above specified minimum altitudes) for the number of user-specified cases. Histograms generated from such predictions can be used to determine the probabilities that spacecraft will satisfy lifetime requirements. The document discusses uncertainties that affect modeling of orbital lifetimes. Issues of repeatability, smoothness of distributions, and code run time are considered for the purpose of establishing values of code-specific parameters and number of Monte Carlo runs. Results from test cases are interpreted as demonstrating that solar-flux predictions are primary sources of variations in predicted lifetimes. Therefore, it is concluded, multiple sets of predictions should be utilized to fully characterize the lifetime range of a spacecraft.
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Solar system 'fast mission' trajectories using aerogravity assist
NASA Technical Reports Server (NTRS)
Randolph, James E.; Mcronald, Angus D.
1992-01-01
Initial analyses of the aerogravity assist (AGA) delivery technique to solar system targets (and beyond) has been encouraging. Mission opportunities are introduced that do not exist with typical gravity assist trajectories and current launch capabilities. The technique has the most payoff for high-energy missions such as outer planet orbiters and flybys. The goal of this technique is to reduce the flight duration significantly and to eliminate propulsion for orbit insertion. The paper will discuss detailed analyses and parametric studies that consider launch opportunities for missions to the sun, Saturn, Uranus, Neptune, and Pluto using AGA at Venus and Mars.
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Ceres: Its Origin and Predicted Bulk Chemical Composition
NASA Astrophysics Data System (ADS)
Prentice, Andrew
2014-11-01
I explore the formation of Ceres in the framework of the Modern Laplacian theory of Solar System origin (MLT; Prentice 2006 PASA 23 1; 2008 LPSC, abs.1945.pdf). I suggest that all MB asteroids condensed within a gas ring cast off from the equator of the contracting protosolar cloud (PSC) near to the mean present orbit of Ceres. According to the MLT, the shedding of gas rings started at the orbit of Quaoar and comes about through supersonic turbulent stress due to powerful convective motions in the cloud. If the PSC contracts uniformly, the gas ring mean orbital radii Rn (n = 0, 1, 2...) form a geometric sequence and their temperatures Tn scale nearly as Tn ~ A/Rn. The values of the mean ratio Rn/Rn+1 and the constant A depend on the controlling parameters of the PSC. These are chosen so that the mean ratio
matches the observed mean planetary spacing and that the metal mass fraction ~0.71 of the condensate at Mercury’s orbit yields a planet of mean density 5.43 g/cc. For Mercury, Tn = 1638 K and the gas pressure on the gas ring mean orbit is 18 kPa.For Ceres, Tn = 272 K and the gas pressure is 8.9 Pa. The condensate consists mostly of Mg-silicates & SiO2 (mass fraction 0.394), magnetite (0.181), (Fe-Ni-Co)S (0.191), and brucite (0.127). The RTP mean density is 3.391 g/cc. If short-lived radionuclides cause dehydration of the rock and separation of rocks & metals to form a central core, the RTP density of the core is 3.662 g/cc and the mass fractions of separated water and NaCl are 0.04182 and 0.00153. All MB asteroids may initially have been ocean worlds. As Tn exceeds the brine freezing temperature 271 K, the water mantles remain liquid. Collisions between the asteroid embryos dislodge water from the smaller ones, so creating a liquid torus on the gas ring mean orbit. This water is then accreted by the largest embryos. A 4-zone model for Ceres (c) with mean density 2.08 g/cc has a rock (and inner metal) core of mass 0.732Mc, overlain by a 2.5 km thick salt layer and an outer pure ice mantle of mass 0.258 Mc. The MOI factor of this model is 0.295. Perhaps Dawn will find the surface of Ceres to be very flat, though roughened through aeons of impacts, with fresh craters having bright floors and ejecta. -
2014-09-17
Dr. Jim Green, NASA‘s Planetary Science Division Director and Head of Mars Program, gives opening remarks at a media briefing where panelist outlined activities around the Sunday, Sept. 21 orbital insertion at Mars of the agency’s Mars Atmosphere and Volatile EvolutioN (MAVEN) spacecraft, Wednesday, Sept. 17, 2014 at NASA Headquarters in Washington. (Photo credit: NASA/Bill Ingalls)
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Brown, R.H.; Baines, K.H.; Bellucci, G.; Buratti, B.J.; Capaccioni, F.; Cerroni, P.; Clark, R.N.; Coradini, A.; Cruikshank, D.P.; Drossart, P.; Formisano, V.; Jaumann, R.; Langevin, Y.; Matson, D.L.; McCord, T.B.; Mennella, V.; Nelson, R.M.; Nicholson, P.D.; Sicardy, B.; Sotin, Christophe; Baugh, N.; Griffith, C.A.; Hansen, G.B.; Hibbitts, C.A.; Momary, T.W.; Showalter, M.R.
2006-01-01
The Visual and Infrared Mapping Spectrometer observed Phoebe, Iapetus, Titan and Saturn's rings during Cassini's approach and orbital insertion. Phoebe's surface contains water ice, CO2, and ferrous iron. lapetus contains CO2 and organic materials. Titan's atmosphere shows methane fluorescence, and night-side atmospheric emission that may be CO2 and CH3D. As determined from cloud motions, the winds at altitude 25-30 km in the south polar region of Titan appear to be moving in a prograde direction at velocity ???1 m s-1. Circular albedo features on Titan's surface, seen at 2.02 ??m, may be palimpsests remaining from the rheological adjustment of ancient impact craters. As such, their long-term persistence is of special interest in view of the expected precipitation of liquids and solids from the atmosphere. Saturn's rings have changed little in their radial structure since the Voyager flybys in the early 1980s. Spectral absorption bands tentatively attributed to Fe2+ suggest that iron-bearing silicates are a source of contamination of the C ring and the Cassini Division. ?? ESO 2006.
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Mars Pathfinder and Mars Global Surveyor Outreach Compilation
NASA Astrophysics Data System (ADS)
1999-09-01
This videotape is a compilation of the best NASA JPL (Jet Propulsion Laboratory) videos of the Mars Pathfinder and Mars Global Surveyor missions. The mission is described using animation and narration as well as some actual footage of the entire sequence of mission events. Included within these animations are the spacecraft orbit insertion; descent to the Mars surface; deployment of the airbags and instruments; and exploration by Sojourner, the Mars rover. JPL activities at spacecraft control during significant mission events are also included at the end. The spacecraft cameras pan the surrounding Mars terrain and film Sojourner traversing the surface and inspecting rocks. A single, brief, processed image of the Cydonia region (Mars face) at an oblique angle from the Mars Global Surveyor is presented. A description of the Mars Pathfinder mission, instruments, landing and deployment process, Mars approach, spacecraft orbit insertion, rover operation are all described using computer animation. Actual color footage of Sojourner as well as a 360 deg pan of the Mars terrain surrounding the spacecraft is provided. Lower quality black and white photography depicting Sojourner traversing the Mars surface and inspecting Martian rocks also is included.
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Mars Pathfinder and Mars Global Surveyor Outreach Compilation
NASA Technical Reports Server (NTRS)
1999-01-01
This videotape is a compilation of the best NASA JPL (Jet Propulsion Laboratory) videos of the Mars Pathfinder and Mars Global Surveyor missions. The mission is described using animation and narration as well as some actual footage of the entire sequence of mission events. Included within these animations are the spacecraft orbit insertion; descent to the Mars surface; deployment of the airbags and instruments; and exploration by Sojourner, the Mars rover. JPL activities at spacecraft control during significant mission events are also included at the end. The spacecraft cameras pan the surrounding Mars terrain and film Sojourner traversing the surface and inspecting rocks. A single, brief, processed image of the Cydonia region (Mars face) at an oblique angle from the Mars Global Surveyor is presented. A description of the Mars Pathfinder mission, instruments, landing and deployment process, Mars approach, spacecraft orbit insertion, rover operation are all described using computer animation. Actual color footage of Sojourner as well as a 360 deg pan of the Mars terrain surrounding the spacecraft is provided. Lower quality black and white photography depicting Sojourner traversing the Mars surface and inspecting Martian rocks also is included.
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Moisès Broggi i Vallès (1908-2012): Military surgeon and Catalan humanitarian.
Derby, Mark; Jorge, David
2016-02-01
Catalan surgeon Moisès Broggi entered medical practice in 1931 as Spain was modernizing rapidly. Five years later, however, an attempted military coup sparked a nationwide civil war. Broggi offered his services to the embattled Republic and joined the Medical Service of the International Brigades. He served alongside colleagues from many countries, helping to develop advances in military medicine and especially trauma surgery. Broggi chose to remain working in Barcelona as Franco's Nationalist forces entered the city, in spite of the risk of reprisal he faced as a former officer of the International Brigades. Although forced from his leading position in the public health service, he developed a distinguished private practice. In the year of Franco's death he became President of Barcelona's Royal Academy of Medicine and he received many other honours. Just months before his death at the remarkable age of 104, Dr Moisès Broggi continued to discuss and write about the concerns that had directed the course of his life--advances in medical science and the intellectual and political repression that had hindered delivery of those advances. In an article titled Exile and Silence he noted the groundbreaking work carried out under the auspices of the prestigious scientific institutions founded during Spain's Second Republic and the subsequent dark decades of exile suffered by many of their prominent scientists, some of them his close friends. © The Author(s) 2014.
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Hannemann, Holger; Rosenke, Kyle; O'Dowd, John M; Fortunato, Elizabeth A
2009-05-01
Human cytomegalovirus (HCMV) is a common cause of morbidity and mortality in immunocompromised and immunosuppressed individuals. During infection, HCMV is known to employ host transcription factors to facilitate viral gene expression. To further understand the previously observed delay in viral replication and protein expression in p53 knockout cells, we conducted microarray analyses of p53(+/+) and p53(-/-) immortalized fibroblast cell lines. At a multiplicity of infection (MOI) of 1 at 24 h postinfection (p.i.), the expression of 22 viral genes was affected by the absence of p53. Eleven of these 22 genes (group 1) were examined by real-time reverse transcriptase, or quantitative, PCR (q-PCR). Additionally, five genes previously determined to have p53 bound to their nearest p53-responsive elements (group 2) and three control genes without p53 binding sites in their upstream sequences (group 3) were also examined. At an MOI of 1, >3-fold regulation was found for five group 1 genes. The expression of group 2 and 3 genes was not changed. At an MOI of 5, all genes from group 1 and four of five genes from group 2 were found to be regulated. The expression of control genes from group 3 remained unchanged. A q-PCR time course of four genes revealed that p53 influences viral gene expression most at immediate-early and early times p.i., suggesting a mechanism for the reduced and delayed production of virions in p53(-/-) cells.
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NSLS-II storage ring insertion device and front-end commissioning and operation
DOE Office of Scientific and Technical Information (OSTI.GOV)
Wang, G., E-mail: gwang@bnl.gov; Shaftan, T.; Amundsen, C.
The National Synchrotron Light Source II (NSLS-II) is a state of the art 3 GeV third generation light source at Brookhaven National Laboratory. During spring/ summer of 2014, the storage ring was commissioned up to 50 mA without insertion devices. In the fall of 2014, we began commissioning of the project beamlines, which included seven insertion devices on six ID ports. Beamlines IXS, HXN, CSX-1, CSX-2, CHX, SRX, and XPD-1 consist of elliptically polarized undulator (EPU), damping wigglers (DW) and in-vacuum undulators (IVU) covering from VUV to hard x-ray range. In this paper, experience with commissioning and operation is discussed.more » We focus on reaching storage ring performance with IDs, including injection, design emittance, compensation of orbit distortions caused by ID residual field, source point stability, beam alignment and tools for control, monitoring and protection of the ring chambers from ID radiation.« less
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Lunar Reconnaissance Orbiter (LRO) Thruster Control Mode Design and Flight Experience
NASA Technical Reports Server (NTRS)
Hsu, Oscar C.
2010-01-01
National Aeronautics and Space Administration s (NASA) Goddard Space Flight Center (GSFC) in Greenbelt, MD, designed, built, tested, and launched the Lunar Reconnaissance Orbiter (LRO) from Cape Canaveral Air Force Station on June 18, 2009. The LRO spacecraft is the first operational spacecraft designed to support NASA s return to the Moon, as part of the Vision for Space Exploration. LRO was launched aboard an Atlas V 401 launch vehicle into a direct insertion trajectory to the Moon. Twenty-four hours after separation the propulsion system was used to perform a mid-course correction maneuver. Four days after the mid-course correction a series of propulsion maneuvers were executed to insert LRO into its commissioning orbit. The commission period lasted eighty days and this followed by a second set of thruster maneuvers that inserted LRO into its mission orbit. To date, the spacecraft has been gathering invaluable data in support of human s future return to the moon. The LRO Attitude Control Systems (ACS) contains two thruster based control modes: Delta-H and Delta-V. The design of the two controllers are similar in that they are both used for 3-axis control of the spacecraft with the Delta-H controller used for momentum management and the Delta-V controller used for orbit adjust and maintenance maneuvers. In addition to the nominal purpose of the thruster modes, the Delta-H controller also has the added capability of performing a large angle slew maneuver. A suite of ACS components are used by the thruster based control modes, for both initialization and control. For initialization purposes, a star tracker or the Kalman Filter solution is used for providing attitude knowledge and upon entrance into the thruster based control modes attitude knowledge is provided via rate propagation using a inertial reference unit (IRU). Rate information for the controller is also supplied by the IRU. Three-axis control of the spacecraft in the thruster modes is provided by eight 5-lbf class attitude control thrusters configured in two sets of four thrusters for redundancy purposes. Four additional 20-lbf class thrusters configured in two sets of two thrusters are used for Lunar Orbit Insertion maneuvers. The propulsion system is one the few systems on-board the LRO spacecraft that has built in redundancy. The Delta-H controller consists of a Proportional-Derivative (PD) controller with a structural filter on the thrusters and a Proportional controller on the reaction wheels. The PD control that employs the thrusters is used for attitude and rate control. The Proportional controller on the reaction wheels is used for commanding the wheels to a new momentum state. The ground commands used for the Delta-H controller are the system momentum vector, reaction wheel momentum, maximum expected command time, and which set of attitude control thrusters to use. The ability to command both the system momentum vector and reaction wheel momentum in the Delta-H controller provides both a capability and an additional source of operator error. Large angle slews via the Delta-H controller is achievable via this commands because these commands are used for the exit mode criteria. Setting these commands to non-consistent values prevents the mode from exiting nominally.
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Space Shuttle development update
NASA Technical Reports Server (NTRS)
Brand, V.
1984-01-01
The development efforts, since the STS-4 flight, in the Space Shuttle (SS) program are presented. The SS improvements introduced in the last two years include lower-weight loads, communication through the Tracking and Data Relay Satellite, expanded extravehicular activity capability, a maneuvering backpack and the manipulator foot restraint, the improvements in thermal projection system, the 'optional terminal area management targeting' guidance software, a rendezvous system with radar and star tracker sensors, and improved on-orbit living conditions. The flight demonstrations include advanced launch techniques (e.g., night launch and direct insertion to orbit); the on-orbit demonstrations; and added entry and launching capabilities. The entry aerodynamic analysis and entry flight control fine tuning are described. Reusability, improved ascent performance, intact abort and landing flexibility, rollout control, and 'smart speedbrakes' are among the many improvements planned for the future.
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Applied Astronomy: An Optical Survey for Space Debris at GEO
NASA Technical Reports Server (NTRS)
Seitzer, Patrick; Barker, Edwin S.; Abercromby, K.; Rodriquez, H.
2007-01-01
A viewgraph is presented to discuss space debris at Geosynchronous Earth Orbit (GEO). The topics include: 1) Syncom1 launched February 14, 1963 Failed on orbit insertion 1st piece of GEO debris!; 2) Example of recent GEO payload: XM-2 Rock satellite for direct broadcast radio; 3) MODEST Michigan Orbital DEbrisSurvey Telescope the telescope formerly known as the Curtis-Schmidt; 4) GEO Debris Survey; 5) Examples of Detections; 6) Brightness Variations Common; 7) Observed Angular Rates; 8) Two Populations at GEO; 9) High Area-to-Mass Ratio Material (A/M); 10) Examples of MLI; 11) Examples of MLI Release in LEO; 12) Liou & Weaver (2005) models; 13) ESA 1-m Telescope Survey; 14) Two Telescopes March 2007 Survey and Follow-up; 15) Final Eccentricity; and 16) How control Space Debris?
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NASA Astrophysics Data System (ADS)
Bekele, Zelalem Abebe; Meng, Kangkang; Zhao, Bing; Wu, Yong; Miao, Jun; Xu, Xiaoguang; Jiang, Yong
2017-08-01
Symmetry breaking provides new insight into the physics of spin-orbit torque (SOT) and the switching without a magnetic field could lead to significant impact. In this work, we demonstrate the robust zero-field SOT switching of a perpendicular ferromagnet (FM) layer where the symmetry is broken by a bilayer of heavy metals (HMs) with the strong spin-orbit coupling (SOC). We observed the change of coercivity value by 31% after inserting Co2FeAl in the multilayer structure. These two HM layers (Ta and Pt) are used to strengthen the SOC by linear combination. With different angles between the magnetization and the current (i.e. parallel and anti-parallel), the structures show different switching behaviors such as clockwise or counterclockwise.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, from left, United Space Alliance workers Loyd Turner, Craig Meyer and Erik Visser prepare to conduct a fit check of an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttles Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, from left, United Space Alliance workers Loyd Turner, Craig Meyer and Erik Visser conduct a fit check of an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttles Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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2004-09-17
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, from left, United Space Alliance workers Loyd Turner, Craig Meyer and Erik Visser conduct a fit check of an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttle’s Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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2004-09-17
KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, from left, United Space Alliance workers Loyd Turner, Craig Meyer and Erik Visser prepare to conduct a fit check of an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttle’s Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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The Kaguya Mission: Present Status and its Lunar Science.
NASA Astrophysics Data System (ADS)
Kato, M.; Takizawa, Y.; Sasaki, S.; Kaguya Team
2009-04-01
Lunar orbiter Kaguya(SELENE) has been successfully launched on September 14, 2007. After insertion into lunar orbit on October 4 , release of two subsatellites into the elliptical orbits of 100 km perilune, and 2400 km and 800 km apolune, reach the nominal observation orbit with 100 km circular and polar on October 18, and the extension of four sounder antennas with 15 m length and the 12 m mast for magnetometer, and deployment of plasma imager, Kaguya has started nominal observation for ten months on December 21. Most of science instruments show excellent performance for ten months, and continue to acquire their data in extention mission term using saved fuel. New information and insights have been brought to lunar sciences in topography, gravimetry, geology, mineralogy, lithology, plasma physics.
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Ma, C X; Zheng, G Y
2018-02-11
Objective: To construct lentiviral-mediated EphA2 overexpression vectors, transfect them into human lens epithelial cells (HLE-B3) in vitro , and investigate the effect of EphA2 gene overexpression on the proliferation and apoptosis of HLE-B3 exposed to high-concentration dexamethasone. Methods: Experimental Study. The pCDH-CMV- MCS-EF1-RFP plasmid was set up by the digestion of NOTⅠand XbaⅠ double restriction enzyme and ligation of CE ligase, and then the plasmid was transformed into DH10B cells. Seven clons were picked for enzymatic digestion and the clons with correct results were chosen for sequencing. The 293 T/17 cells were co-transfected with the pCDH-CMV-MCS-EF1-RFP-EphA2 and the packaging mixture by Lipofectamine 2000. At different multiplicities of infection (MOI=20, 50, 100, and 200) after 72-hour infection, we observed the expression of RFP and morphological changes of HLE-B3 by an inverted fluorescence microscope, and calculated the transfection efficiency through the flow cytometry. EphA2 protein expression was detected by Western blot. The following experiments were divided into four groups: normal control group (group A), EphA2 overexpression vector transfection group (group B), HLE-B3 cells exposed to dexamethasone group (group C) and EphA2 overexpression vector transfection HLE-B3 cells exposed to dexamethasone group (group D). Statistical analysis method was single factor or two factors variance analysis. Cell survival rate was detected by the Cell Counting Kit-8 assay. Cell apoptosis index was detected by Tunel. Results: Restriction enzyme digestion and sequencing indicated that EphA2 cDNA fragment was successfully inserted in the vector. The infection efficiency was up to 38.6%±3.9%, 49.2%±4.2%, 79.5%±5.5% and 80.2%±6.0% when the MOI was 20, 50, 100 and 200, respectively. There was statistically significant difference ( F= 2 600.8, P= 0.001) among the four groups and between any two groups except between the MOI=100 group and MOI=200 group ( P= 2.507) . The relative quantity of EphA2 protein of the normal control group, empty vector transfection group and EphA2 gene overexpression vector transfection group was (0.561 2±0.031 7) , (0.559 7±0.012 8) and (3.032 0±0.041 9) , respectively. There was statistically significant difference ( F= 2 646.0, P= 0.001) among the three groups and between any two groups except between the normal control group and empty vector transfection group ( P= 0.868) . The survival rate of groups A, B, C and D was 98.18%±1.85%, 122.01%±3.89%, 52.32%±1.99% and 76.18%±3.74%, respectively. There was statistically significant difference among the four groups ( F= 497.6, P= 0.001) . The survival rate of group B was greater than group A ( P= 0.001) . The survival rate of group D was greater than group C ( P= 0.001) . Tunel results showed that the apoptosis index of groups A, B, C and D was 5.4%±1.5%, 5.0%±1.3%, 23.0%±3.9% and 14.4%±2.7%, respectively. There was statistically significant difference among the four groups ( F= 397.6, P= 0.001) . The apoptosis index of group B was lower than group A, but there was no statistically significant difference between them ( P= 0.415) ; the apoptosis index of group D was lower than group C ( P= 0.018). Conclusions: The lentiviral vector carrying human EphA2 gene has been successfully constructed and efficiently expressed in HLE-B3 cells. EphA2 gene overexpression could increase the HLE-B3 cell survival rate and protect HLE-B3 cells from high-concentration dexamethasone-induced reduction of the cell survival rate. EphA2 gene overexpression could protect HLE-B3 cells from high-concentration dexamethasone-induced apoptosis, but it has no remarkable effect on apoptosis of HLE-B3 cells under physiological conditions. (Chin J Ophthalmol, 2018, 54: 125-132) .
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Earth Return Aerocapture for the TransHab/Ellipsled Vehicle
NASA Technical Reports Server (NTRS)
Muth, W. D.; Hoffmann, C.; Lyne, J. E.
2000-01-01
The current architecture being considered by NASA for a human Mars mission involves the use of an aerocapture procedure at Mars arrival and possibly upon Earth return. This technique would be used to decelerate the vehicles and insert them into their desired target orbits, thereby eliminating the need for propulsive orbital insertions. The crew may make the interplanetary journey in a large, inflatable habitat known as the TransHab. It has been proposed that upon Earth return, this habitat be captured into orbit for use on subsequent missions. In this case, the TransHab would be complimented with an aeroshell, which would protect it from heating during the atmospheric entry and provide the vehicle with aerodynamic lift. The aeroshell has been dubbed the "Ellipsled" because of its characteristic shape. This paper reports the results of a preliminary study of the aerocapture of the TransHab/Ellipsled vehicle upon Earth return. Undershoot and overshoot boundaries have been determined for a range of entry velocities, and the effects of variations in the atmospheric density profile, the vehicle deceleration limit, the maximum vehicle roll rate, the target orbit, and the vehicle ballistic coefficient have been examined. A simple, 180 degree roll maneuver was implemented in the undershoot trajectories to target the desired 407 km circular Earth orbit. A three-roll sequence was developed to target not only a specific orbital energy, but also a particular inclination, thereby decreasing propulsive inclination changes and post-aerocapture delta-V requirements. Results show that the TransHab/Ellipsled vehicle has a nominal corridor width of at least 0.7 degrees for entry speeds up to 14.0 km/s. Most trajectories were simulated using continuum flow aerodynamics, but the impact of high-altitude viscous effects was evaluated and found to be minimal. In addition, entry corridor comparisons have been made between the TransHab/Ellipsled and a modified Apollo capsule which is also being considered as the crew return vehicle; because of its slightly higher lift-to-drag ratio, the TransHab has a modest advantage with regard to corridor width. Stagnation-point heating rates and integrated heat loads were determined for a range of vehicle ballistic coefficients and entry velocities.
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NASA Astrophysics Data System (ADS)
2006-03-01
Venus Express mission controllers at the ESA Space Operations Centre (ESOC) in Darmstadt, Germany are making intensive preparations for orbit insertion. This comprises a series of telecommands, engine burns and manoeuvres designed to slow the spacecraft down from a velocity of 29000 km per hour relative to Venus, just before the first burn, to an entry velocity some 15% slower, allowing the probe to be captured into orbit around the planet. The spacecraft will have to ignite its main engine for 50 minutes in order to achieve deceleration and place itself into a highly elliptical orbit around the planet. Most of its 570 kg of onboard propellant will be used for this manoeuvre. The spacecraft’s solar arrays will be positioned so as to reduce the possibility of excessive mechanical load during engine ignition. Over the subsequent days, a series of additional burns will be done to lower the orbit apocentre and to control the pericentre. The aim is to end up in a 24-hour orbit around Venus early in May. The Venus orbit injection operations can be followed live at ESA establishments, with ESOC acting as focal point of interest (see attached programme). In all establishments, ESA specialists will be on hand for interviews. ESA TV will cover this event live from ESOC in Darmstadt. The live transmission will be carried free-to-air. For broadcasters, complete details of the various satellite feeds are listed at http://television.esa.int. The event will be covered on the web at venus.esa.int. The website will feature regular updates, including video coverage of the press conference and podcast from the control room at ESA’s Operations Centre. Media representatives wishing to follow the event at one of the ESA establishments listed below are requested to fill in the attached registration form and fax it back to the place of their choice. For further information, please contact: ESA Media Relations Division Tel : +33(0)1.53.69.7155 Fax: +33(0)1.53.69.7690 Venus Express Orbit Insertion - Tuesday 11 April 2006 ESA/ESOC, Robert Bosch Strasse, 5 - Darmstadt (Germany) PROGRAMME 07:30 - Doors open 08:45 - Start of local event, welcome addresses 09:10 - ESA TV live from Mission Control Room (MCR) starts 09:17 - Engine burn sequence starts 09:45 - Occultation of spacecraft by Venus starts 09:55 - Occultation ends 10:07 - Main engine burn ends 10:20 - Address by Jean-Jacques Dordain, ESA’s Director General, and other officials Break and buffet Interview opportunities 11:30-12:15 - Press Conference Jean-Jacques Dordain, Director General, ESA Prof. David Southwood, Director of Science, ESA Gaele Winters, Director of Operations and Infrastructure, ESA Manfred Warhaut, Flight Operations Director, ESA Håkan Svedhem, Venus Express Project Scientist, ESA Don McCoy, Venus Express Project Manager, ESA 13:15 - End of event at ESOC ACCREDITATION REQUEST FORM Venus Express Orbit Insertion - ESA/ESOC Darmstadt - 11 April 2006 First name:___________________ Surname:_____________________ Media:______________________________________________________ Address: ___________________________________________________ ____________________________________________________________ Tel:_______________________ Fax: ___________________________ Mobile :___________________ E-mail: ________________________ I will be attending the Venus Express Orbit Insertion event at the following site: [ ] Germany Location: ESA/ESOC Address: Robert Bosch Strasse 5, Darmstadt, Germany Opening hours: 07:30 - 13:00 Contact: Jocelyne Landeau-Constantin, Tel: +49.6151.902.696 - Fax: +49.6151.902.961 [ ] France Location: ESA HQ Address: 8/10, rue Mario Nikis - Paris 15, France Opening hours: 08:00 - 13:00 Contact: Anne-Marie Remondin - Tel: +33(0)1.53.69.7155 - fax: +33(0)1.53.69.7690 [ ] The Netherlands Location: Newton Room, ESA/ESTEC Address: Keplerlaan 1, Noordwijk, The Netherlands Opening hours: 08:30 - 12:30 Contact: Michel van Baal, tel. + 31 71 565 3006, fax + 31 71 565 5728 [ ] Italy Location: ESA/ESRIN Address: Via Galileo Galilei, Frascati (Rome), Italy Opening hours: 07:00 - 14:00 Contact: Franca Morgia - Tel: +39.06.9418.0951 - Fax: +39.06.9418.0952 [ ] Spain Location: ESA/ESAC Address: Urbanización Villafranca del Castillo, Villanueva de la Cañada, Madrid, Spain Opening hours: 8:30 - 13:30 Contact: Monica Oerke, Tel + 34 91 813 13 27/59 - Fax: + 34 91 813 12 19
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STS-32 OV-102 air revitalization system (ARS) humidity separator problem
1990-01-20
During STS-32, onboard Columbia, Orbiter Vehicle (OV) 102, a leakage problem at environmental control and life support system (ECLSS) air revitalization system (ARS) humidity separator A below the middeck is solved with a plastic bag and a towel. The towel inserted inside a plastic bag absorbed the water that had collected at the separator inlet.
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STS-32 OV-102 air revitalization system (ARS) humidity separator problem
NASA Technical Reports Server (NTRS)
1990-01-01
During STS-32, onboard Columbia, Orbiter Vehicle (OV) 102, a leakage problem at environmental control and life support system (ECLSS) air revitalization system (ARS) humidity separator A below the middeck is solved with a plastic bag and a towel. The towel inserted inside a plastic bag absorbed the water that had collected at the separator inlet.
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Logarithmic spiral trajectories generated by Solar sails
NASA Astrophysics Data System (ADS)
Bassetto, Marco; Niccolai, Lorenzo; Quarta, Alessandro A.; Mengali, Giovanni
2018-02-01
Analytic solutions to continuous thrust-propelled trajectories are available in a few cases only. An interesting case is offered by the logarithmic spiral, that is, a trajectory characterized by a constant flight path angle and a fixed thrust vector direction in an orbital reference frame. The logarithmic spiral is important from a practical point of view, because it may be passively maintained by a Solar sail-based spacecraft. The aim of this paper is to provide a systematic study concerning the possibility of inserting a Solar sail-based spacecraft into a heliocentric logarithmic spiral trajectory without using any impulsive maneuver. The required conditions to be met by the sail in terms of attitude angle, propulsive performance, parking orbit characteristics, and initial position are thoroughly investigated. The closed-form variations of the osculating orbital parameters are analyzed, and the obtained analytical results are used for investigating the phasing maneuver of a Solar sail along an elliptic heliocentric orbit. In this mission scenario, the phasing orbit is composed of two symmetric logarithmic spiral trajectories connected with a coasting arc.
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NASA Technical Reports Server (NTRS)
Gutkowski, Jeffrey P.; Dawn, Timothy F.; Jedrey, Richard M.
2014-01-01
The first crewed mission, Exploration Mission 2 (EM-2), for the MPCV Orion spacecraft is scheduled for August 2021, and its current mission is to orbit the Moon in a highly elliptical lunar orbit for 3 days. A 21-year scan was performed to identify feasible missions that satisfy the propulsive capabilities of the Interim Cryogenic Propulsion Stage (ICPS) and MPCV Service Module (SM). The mission is divided into 4 phases: (1) a lunar free return trajectory, (2) a hybrid maneuver, during the translunar coast, to lower the approach perilune altitude to 100 km, (3) lunar orbit insertion into a 100 x 10,000 km orbit, and (4) lunar orbit loiter and Earth return to a splashdown off the coast of Southern California. Trajectory data was collected for all feasible missions and converted to information that influence different subsystems including propulsion, power, thermal, communications, and mission operations. The complete 21-year scan data shows seasonal effects that are due to the Earth-Moon geometry and the initial Earth parking orbit. The data and information is also useful to identify mission opportunities around the current planned launch date for EM-2.
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Low cost booster and high performance orbit injection propulsion extended abstract
NASA Technical Reports Server (NTRS)
Sackheim, R. L.
1994-01-01
Space transportation is currently a major element of cost for communications satellite systems. For every dollar spent in manufacturing the satellite, somewhere between 1 and 3 dollars must be spent to launch the satellite into its initial operational orbit. This also makes the weight of the satellite a very critical cost factor because it is important to maximize the useful payload that is placed into orbit to maximize the return on the original investment. It seems apparent then, that tremendous economic advantage for satellite communications systems can be gained from improvements in two key highly leveraged propulsion areas. The first and most important economic improvement can be achieved by significantly lowering the cost of today's launch vehicles. The second gain that would greatly benefit the communications satellite business position is to increase both the useful (payload) weight placed into the orbit and the revenue generating lifetime of the satellite on-orbit. The point of this paper is to first explain that these two goals can best be achieved by cost reduction and performance increasing advancements in rocket propulsion for both the launch vehicle and for the satellite on-board apogee insertion and on-orbit velocity control systems.
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Orbit Determination Support for the Microwave Anisotropy Probe (MAP)
NASA Technical Reports Server (NTRS)
Bauer, Frank (Technical Monitor); Truong, Son H.; Cuevas, Osvaldo O.; Slojkowski, Steven
2003-01-01
NASA's Microwave Anisotropy Probe (MAP) was launched from the Cape Canaveral Air Force Station Complex 17 aboard a Delta II 7425-10 expendable launch vehicle on June 30, 2001. The spacecraft received a nominal direct insertion by the Delta expendable launch vehicle into a 185-km circular orbit with a 28.7deg inclination. MAP was then maneuvered into a sequence of phasing loops designed to set up a lunar swingby (gravity-assisted acceleration) of the spacecraft onto a transfer trajectory to a lissajous orbit about the Earth-Sun L2 Lagrange point, about 1.5 million km from Earth. Because of its complex orbital characteristics, the mission provided a unique challenge for orbit determination (OD) support in many orbital regimes. This paper summarizes the premission trajectory covariance error analysis, as well as actual OD results. The use and impact of the various tracking stations, systems, and measurements will be also discussed. Important lessons learned from the MAP OD support team will be presented. There will be a discussion of the challenges presented to OD support including the effects of delta-Vs at apogee as well as perigee, and the impact of the spacecraft attitude mode on the OD accuracy and covariance analysis.
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Design of multi-mission chemical propulsion modules for planetary orbiters. Volume 1: Summary report
NASA Technical Reports Server (NTRS)
1975-01-01
Results are presented of a conceptual design and feasibility study of chemical propulsion stages that can serve as modular propulsion units, with little or no modification, on a variety of planetary orbit missions, including orbiters of Mercury, Saturn, and Uranus. Planetary spacecraft of existing design or currently under development, viz., spacecraft of the Pioneer and Mariner families, are assumed as payload vehicles. Thus, operating requirements of spin-stabilized and 3-axis stabilized spacecraft have to be met by the respective propulsion module designs. As launch vehicle for these missions the Shuttle orbiter and interplanetary injection stage, or Tug, plus solid-propellant kick motor was assumed. Accommodation constraints and interfaces involving the payloads and the launch vehicle are considered in the propulsion module design. The applicability and performance advantages were evaluated of the space-storable high-energy bipropellants. The incentive for using this advanced propulsion technology on planetary missions is the much greater performance potential when orbit insertion velocities in excess of 4 km/sec are required, as in the Mercury orbiter. Design analyses and performance tradeoffs regarding earth-storable versus space-storable propulsion systems are included. Cost and development schedules of multi-mission versus custom-designed propulsion modules are examined.
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Meslin, Eric M; Were, Edwin; Ayuku, David
2013-09-01
It is a sine qua non that research and health care provided in international settings raise profound ethical questions when different cultural and political values are implicated. Yet ironically, as international health research expands and as research on ethical issues in international health research broadens and deepens, we appear to have moved away from discussing the moral foundations of these activities. For international health research to thrive and lead to the kind of benefits it is capable of, it is helpful to occasionally revisit the foundational premises that justify the enterprise as a whole. We draw on the experience of the Indiana University-Moi University Academic Research Ethics Partnership, an innovative bioethics training program co-located in Indianapolis and Eldoret, Kenya to highlight the changing nature of ethical issues in international health research and the ongoing practical challenges.
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Phinney, Harriet M.
2008-01-01
Research from around the world has suggested that married women’s greatest risk for contracting HIV is from having sexual intercourse with their husbands. On the basis of 6 months of ethnographic research in Hanoi, Vietnam, I argue that the contemporary nature of the HIV epidemic in Hanoi is shaped by 3 interrelated policies implemented in 1986 as part of the government’s new economic policy, Doi Moi (Renovation). Together, these policies structure men’s opportunities for extramarital sexual relations and encourage wives to acquiesce to their husbands’ sexual infidelity, putting both at risk of HIV. I propose 4 structural intervention strategies that address the policies that contribute to men’s opportunities for extramarital liaisons and to marital HIV risk. PMID:18309136
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Tarsitano, Achille; Badiali, Giovanni; Pizzigallo, Angelo; Marchetti, Claudio
2016-10-01
Enophthalmos is a severe complication of primary reconstruction of orbital floor fractures. The goal of secondary reconstruction procedures is to restore symmetrical globe positions to recover function and aesthetics. The authors propose a new method of orbital floor reconstruction using a mirroring technique and a customized titanium mesh, printed using a direct metal laser-sintering method. This reconstructive protocol involves 4 steps: mirroring of the healthy orbit at the affected site, virtual design of a patient-specific orbital floor mesh, CAM procedures for direct laser-sintering of the customized titanium mesh, and surgical insertion of the device. Using a computed tomography data set, the normal, uninjured side of the craniofacial skeleton was reflected onto the contralateral injured side, and a reconstructive orbital floor mesh was designed virtually on the mirrored orbital bone surface. The solid-to-layer files of the mesh were then manufactured using direct metal laser sintering, which resolves the shaping and bending biases inherent in the indirect method. An intraoperative navigation system ensured accuracy of the entire procedure. Clinical outcomes were assessed using 3dMD photogrammetry and computed tomography data in 7 treated patients. The technique described here appears to be a viable method to correct complex orbital floor defects needing delayed reconstruction. This study represents the first step in the development of a wider experimental protocol for orbital floor reconstruction using computer-assisted design-computer-assisted manufacturing technology.
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NASA Technical Reports Server (NTRS)
Peterson, Jeremy D.; Brown, Jonathan M.
2015-01-01
The aim of this investigation is to determine the feasibility of mission disposal by inserting the spacecraft into a heliocentric orbit along the unstable manifold and then manipulating the Jacobi constant to prevent the spacecraft from returning to the Earth-Moon system. This investigation focuses around L1 orbits representative of ACE, WIND, and SOHO. It will model the impulsive delta-V necessary to close the zero velocity curves after escape through the L1 gateway in the circular restricted three body model and also include full ephemeris force models and higher fidelity finite maneuver models for the three spacecraft.
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Credit WCT. Photographic copy of photograph, interior view of Dd ...
Credit WCT. Photographic copy of photograph, interior view of Dd test cell with VO (Viking Orbiter)-75 spacecraft engine mounted for testing. (Viking was a Mars orbiter and lander mission.) The end of the engine nozzle is inserted into a diffuser in order to conduct exhaust gases out of the chamber. All piping and tubing is stainless steel. Note ports in background through which instrumentation wiring passes. Nozzles at top of view are part of an internal fire suppression (or "Firex") system. (JPL negative no. 384-9428, 24 April 1972) - Jet Propulsion Laboratory Edwards Facility, Test Stand D, Edwards Air Force Base, Boron, Kern County, CA
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Small Satellite Propulsion Options
NASA Technical Reports Server (NTRS)
Myers, Roger M.; Oleson, Steven R.; Curran, Francis M.; Schneider, Steven J.
1994-01-01
Advanced chemical and low power electric propulsion offer attractive options for small satellite propulsion. Applications include orbit raising, orbit maintenance, attitude control, repositioning, and deorbit of both Earth-space and planetary spacecraft. Potential propulsion technologies for these functions include high pressure Ir/Re bipropellant engines, very low power arcjets, Hall thrusters, and pulsed plasma thrusters, all of which have been shown to operate in manners consistent with currently planned small satellites. Mission analyses show that insertion of advanced propulsion technologies enables and/or greatly enhances many planned small satellite missions. Examples of commercial, DoD, and NASA missions are provided to illustrate the potential benefits of using advanced propulsion options on small satellites.
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Cassini Imaging Science: First Results at Saturn
NASA Astrophysics Data System (ADS)
Porco, C. C.
The Cassini Imaging Science experiment at Saturn will commence in early February, 2004 -- five months before Cassini's arrival at Saturn. Approach observations consist of repeated multi-spectral `movie' sequences of Saturn and its rings, image sequences designed to search for previously unseen satellites between the outer edge of the ring system and the orbit of Hyperion, images of known satellites for orbit refinement, observations of Phoebe during Cassini's closest approach to the satellite, and repeated multi-spectral `movie' sequences of Titan to detect and track clouds (for wind determination) and to sense the surface. During Saturn Orbit Insertion, the highest resolution images (~ 100 m) obtained during the whole orbital tour will be collected of the dark side of the rings. Finally, imaging sequences are planned for Cassini's first Titan flyby, on July 2, from a distance of ~ 350,000 km, yielding an image scale of ~ 2.1 km on the South polar region. The highlights of these observation sequences will be presented.
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Interplanetary Electric Propulsion Uranus Mission Trades Supporting the Decadal Survey
NASA Technical Reports Server (NTRS)
Dankanich, John W.; McAdams, James
2011-01-01
The Decadal Survey Committee was tasked to develop a comprehensive science and mission strategy for planetary science that updates and extends the National Academies Space Studies Board s current solar system exploration decadal survey. A Uranus orbiter mission has been evaluated as a part of this 2013-2022 Planetary Science Decadal Survey. A comprehensive Uranus orbiter mission design was completed, including a broad search of interplanetary electric propulsion transfer options. The scope of interplanetary trades was limited to electric propulsion concepts, both solar and radioisotope powered. Solar electric propulsion offers significant payloads to Uranus. Inserted mass into the initial science orbit due is highly sensitive to transfer time due to arrival velocities. The recommended baseline trajectory is a 13 year transfer with an Atlas 551, a 1+1 NEXT stage with 15 kW of power using an EEJU trajectory and a 1,000km EGA flyby altitude constraint. This baseline delivers over 2,000kg into the initial science orbit. Interplanetary trajectory trades and sensitivity analyses are presented herein.
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NASA Technical Reports Server (NTRS)
1998-01-01
This NASA JPL (Jet Propulsion Laboratory) video production is a compilation of the best short movies and computer simulation/animations of the Galileo spacecraft's journey to Jupiter. A limited number of actual shots are presented of Jupiter and its natural satellites. Most of the video is comprised of computer animations of the spacecraft's trajectory, encounters with the Galilean satellites Io, Europa and Ganymede, as well as their atmospheric and surface structures. Computer animations of plasma wave observations of Ganymede's magnetosphere, a surface gravity map of Io, the Galileo/Io flyby, the Galileo space probe orbit insertion around Jupiter, and actual shots of Jupiter's Great Red Spot are presented. Panoramic views of our Earth (from orbit) and moon (from orbit) as seen from Galileo as well as actual footage of the Space Shuttle/Galileo liftoff and Galileo's space probe separation are also included.
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Image analysis software as a strategy to improve the radiographic determination of fracture healing.
Duryea, Jeffrey; Evans, Christopher; Glatt, Vaida
2018-05-28
To develop and validate an unbiased, accurate, convenient and inexpensive means of determining when an osseous defect has healed and recovered sufficient strength to allow weight-bearing. A novel image processing software algorithm was created to analyze the radiographic images and produce a metric designed to reflect the bone strength. We used a rat femoral segmental defect model that provides a range of healing responses from complete union to non-union. Femora were examined by X-ray, micro-computed tomography (µCT) and mechanical testing. Accurate simulated radiographic images at different incident X-ray beam angles were produced from the µCT data files. The software-generated metric (SC) showed high levels of correlation with both the mechanical strength (τMech) and the polar moment of inertia (pMOI), with the mechanical testing data having the highest association. The optimization analysis yielded optimal oblique angles θB of 125° for τMech and 50° for pMOI. The Pearson's R values for the optimized model were 0.71 and 0.64 for τMech and pMOI, respectively. Further validation using true radiographs also demonstrated that the metric was accurate, and that the simulations were realistic. The preliminary findings suggest a very promising methodology to assess bone fracture healing using conventional radiography. With radiographs acquired at appropriate incident angles, it proved possible to calculate accurately the degree of healing and the mechanical strength of the bone. Further research is necessary to refine this approach and determine whether it translates to the human clinical setting.
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Meier, Jeffery L; Keller, Michael J; McCoy, James J
2002-01-01
We have shown previously that the human cytomegalovirus (HCMV) major immediate-early (MIE) distal enhancer is needed for MIE promoter-dependent transcription and viral replication at low multiplicities of infection (MOI). To understand how this region works, we constructed and analyzed a series of HCMVs with various distal enhancer mutations. We show that the distal enhancer is composed of at least two parts that function independently to coordinately activate MIE promoter-dependent transcription and viral replication. One such part is contained in a 47-bp segment that has consensus binding sites for CREB/ATF, SP1, and YY1. At low MOI, these working parts likely function in cis to directly activate MIE gene expression, thus allowing viral replication to ensue. Three findings support the view that these working parts are likely cis-acting elements. (i) Deletion of either part of a bisegmented distal enhancer only slightly alters MIE gene transcription and viral replication. (ii) Reversing the distal enhancer's orientation largely preserves MIE gene transcription and viral replication. (iii) Placement of stop codons at -300 or -345 in all reading frames does not impair MIE gene transcription and viral replication. Lastly, we show that these working parts are dispensable at high MOI, partly because of compensatory stimulation of MIE promoter activity and viral replication that is induced by a virion-associated component(s) present at a high viral particle/cell ratio. We conclude that the distal enhancer is a complex multicomponent cis-acting region that is required to augment both MIE promoter-dependent transcription and HCMV replication.
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Magneto-optic imaging inspection of selected corrosion specimens : technical note
DOT National Transportation Integrated Search
1992-06-21
A feasibility demonstration was conducted at the facilities of Physical Research Instrumentation Company, (RI) in Redmond, Washington. The purpose of the demonstration was to compare the effectiveness of the PRI Model 301-1 magneto-optic imaging (MOI...
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Limits on the Core Mass of Jupiter
NASA Astrophysics Data System (ADS)
Stevenson, D. J.
2015-12-01
The core is here defined as the central concentration of elements heavier than hydrogen and helium (it need not be solid and it need not be purely heavy elements and it will not have a sharp boundary). Its determination is a major goal of the Juno mission (2016-17) and it will be difficult to determine because it is expected to be only a few percent of the total mass. It has long been known that there is no prospect of determining the nature of this core (e.g., its density) from gravity measurements, even though the mass can be estimated. By consideration of simple models that are nonetheless faithful to the essential physics, it is further shown that should the core be contaminated with light elements (hydrogen and helium) then the gravity data can tell us the core mass as defined (with some caveats about the fuzziness of its boundary) but not the total mass within some small radius (which could include any light elements mixed in). This is both good and bad news: Good in that the core is thought to be diagnostic of the conditions under which the planet formed but bad in that the admixture also tells us more about both formation process and core erosion. Further, a linear perturbation theory has been developed that provides an easy approximate way of determining how errors in the equation of state (EOS) propagate into errors in the estimated core mass or envelope enrichment in heavies in models that nonetheless satisfy all observables. This theory does not require detailed models of the planet but provides an integral mapping from changes in the EOS into approximate changes in radius at fixed mass, and low degree gravity (or moment of inertia, MOI). This procedure also shows that there exist perturbations that leave the radius, mass and MOI unchanged but cause a change in J2, though in practice the non-uniqueness of structure by this consideration (~0.2% or less in MOI for example) is less than the non-uniqueness arising from likely EOS uncertainties (~1% in total mass, potentially 30% in core mass). Although the likely independent determination of MOI from precession is expected to help in the modeling procedure, the uncertainty in EOS and in the distribution of heavy elements (and resulting non-adiabaticity) will necessarily introduce ambiguity into the determination of core mass.
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3D-Printed Simulation Device for Orbital Surgery.
Lichtenstein, Juergen Thomas; Zeller, Alexander Nicolai; Lemound, Juliana; Lichtenstein, Thorsten Enno; Rana, Majeed; Gellrich, Nils-Claudius; Wagner, Maximilian Eberhard
Orbital surgery is a challenging procedure because of its complex anatomy. Training could especially benefit from dedicated study models. The currently available devices lack sufficient anatomical representation and realistic soft tissue properties. Hence, we developed a 3D-printed simulation device for orbital surgery with tactual (haptic) correct simulation of all relevant anatomical structures. Based on computed tomography scans collected from patients treated in a third referral center, the hard and soft tissue were segmented and virtually processed to generate a 3D-model of the orbit. Hard tissue was then physically realized by 3D-printing. The soft tissue was manufactured by a composite silicone model of the nucleus and the surrounding tissue over a negative mold model also generated by 3D-printing. The final model was evaluated by a group of 5 trainees in oral and maxillofacial surgery (1) and a group of 5 consultants (2). All participants were asked to reconstruct an isolated orbital floor defect with a titanium implant. A stereotactic navigation system was available to all participants. Their experience was evaluated for haptic realism, correct representation of surgical approach, general handling of model, insertion of implant into the orbit, placement and fixation of implant, and usability of navigated control. The items were evaluated via nonparametric statistics (1 [poor]-5 [good]). Group 1 gave an average mark of 4.0 (±0.9) versus 4.6 (±0.6) by group 2. The haptics were rated as 3.6 (±1.1) [1] and 4.2 (±0.8) [2]. The surgical approach was graded 3.7 (±1.2) [1] and 4.0 (±1.0) [2]. Handling of the models was rated 3.5 (±1.1) [1] and 4 (±0.7) [2]. The insertion of the implants was marked as 3.7 (±0.8) [1] and 4.2 (±0.8) [2]. Fixation of the implants was also perceived to be realistic with 3.6 (±0.9) [1] and 4.2 (±0.45) [2]. Lastly, surgical navigation was rated 3.8 (±0.8) [1] and 4.6 (±0.56) [2]. In this project, all relevant hard and soft tissue characteristics of orbital anatomy could be realized. Moreover, it was possible to demonstrate that the entire workflow of an orbital procedure may be simulated. Hence, using this model training expenses may be reduced and patient security could be enhanced. Copyright © 2016 Association of Program Directors in Surgery. Published by Elsevier Inc. All rights reserved.
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Injecting asteroid fragments into resonances
NASA Technical Reports Server (NTRS)
Farinella, Paolo; Gonczi, R.; Froeschle, Christiane; Froeschle, Claude
1992-01-01
We have quantitatively modeled the chance insertion of asteroid collisional fragments into the 3:1 and g = g(sub 6) resonances, through which they can achieve Earth-approaching orbits. Although the results depend on some poorly known parameters, they indicate that most meteorites and near-earth asteroids probably come from a small and non-representative sample of asteroids, located in the neighborhood of the two resonances.
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INSERTION - ASTRONAUT CARPENTER - MERCURY-ATLAS (MA)-7 - CAPE
1962-05-24
S62-02846 (24 May 1962) --- Project Mercury astronaut M. Scott Carpenter, prime pilot for the Mercury-Atlas 7 (MA-7) mission, is assisted into the MA-7 spacecraft by techicians at Launch Pad 14, Cape Canaveral, Florida. MA-7 is the United States? second attempt in orbital flight around Earth. The spacecraft was designated the ?Aurora? 7. Photo credit: NASA
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Neptune aerocapture mission and spacecraft design overview
NASA Technical Reports Server (NTRS)
Bailey, Robert W.; Hall, Jeff L.; Spliker, Tom R.; O'Kongo, Nora
2004-01-01
A detailed Neptune aerocapture systems analysis and spacecraft design study was performed as part of NASA's In-Space Propulsion Program. The primary objectives were to assess the feasibility of a spacecraft point design for a Neptune/Triton science mission. That uses aerocapture as the Neptune orbit insertion mechanism. This paper provides an overview of the science, mission and spacecraft design resulting from that study.
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2001-01-04
The crated 2001 Mars Odyssey spacecraft rests safely inside the Spacecraft Assembly and Encapsulation Facility 2 (SAEF-2) located in the KSC Industrial Area. The spacecraft arrived at KSC’s Shuttle Landing Facility aboard an Air Force C-17 cargo airplane that brought it from Denver, Colo.., location of the Lockheed Martin plant where the spacecraft was built. In the SAEF, Odyssey will undergo final assembly and checkout. This includes installation of two of the three science instruments, integration of the three-panel solar array, and a spacecraft functional test. It will be fueled and then mated to an upper stage booster, the final activities before going to the launch pad. Launch is planned for April 7, 2001 the first day of a 21-day planetary window. Mars Odyssey will be inserted into an interplanetary trajectory by a Boeing Delta II launch vehicle from Pad A at Complex 17 at the Cape Canaveral Air Force Station, Fla. The spacecraft will arrive at Mars on Oct. 20, 2001, for insertion into an initial elliptical capture orbit. Its final operational altitude will be a 250-mile-high, Sun-synchronous polar orbit. Mars Odyssey will spend two years mapping the planet's surface and measuring its environment
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Impact of gradation and moisture content on stiffness parameters of base materials : final report.
DOT National Transportation Integrated Search
2016-01-01
The performance of flexible pavement depends on the mechanical characteristics of its base layer. The mechanical : characteristics such as stiffness and deformation resistance depend on many factors such as the material gradation : fines content, moi...
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Selective Tuning of Gilbert Damping in Spin-Valve Trilayer by Insertion of Rare-Earth Nanolayers.
Zhang, Wen; Zhang, Dong; Wong, Ping Kwan Johnny; Yuan, Honglei; Jiang, Sheng; van der Laan, Gerrit; Zhai, Ya; Lu, Zuhong
2015-08-12
Selective tuning of the Gilbert damping constant, α, in a NiFe/Cu/FeCo spin-valve trilayer has been achieved by inserting different rare-earth nanolayers adjacent to the ferromagnetic layers. Frequency dependent analysis of the ferromagnetic resonances shows that the initially small magnitude of α in the NiFe and FeCo layers is improved by Tb and Gd insertions to various amounts. Using the element-specific technique of X-ray magnetic circular dichroism, we find that the observed increase in α can be attributed primarily to the orbital moment enhancement of Ni and Co, rather than that of Fe. The amplitude of the enhancement depends on the specific rare-earth element, as well as on the lattice and electronic band structure of the transition metals. Our results demonstrate an effective way for individual control of the magnetization dynamics in the different layers of the spin-valve sandwich structures, which will be important for practical applications in high-frequency spintronic devices.
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First Results from NASA's Lunar Atmosphere and Dust Environment Explorer (LADEE)
NASA Technical Reports Server (NTRS)
Elphic, R.; Colaprete, A.; Horanyi, M; Mahaffy, Paul; Boroson, D.; Delory, G.; Noble, s; Hine, B; Salute, J.
2013-01-01
As of early August, 2013, the Lunar Atmosphere and Dust Environment Explorer (LADEE) mission is scheduled for launch on a Minotaur V rocket from Wallops Flight Facility during a five-day launch period that opens on Sept. 6, 2013 (early Sept. 7 UTC). LADEE will address 40 year-old mysteries of the lunar atmosphere and the question of levitated lunar dust. It will also pioneer the next generation of optical space communications. LADEE will assess the composition of the lunar atmosphere and investigate the processes that control its distribution and variability, including sources, sinks, and surface interactions. LADEE will also determine whether dust is present in the lunar exosphere, and reveal its sources and variability. These investigations are relevant to our understanding of surface boundary exospheres and dust processes occurring at many objects throughout the solar system, address questions regarding the origin and evolution of lunar volatiles, and have potential implications for future exploration activities. Following a successful launch, LADEE will enter a series of phasing orbits, which allows the spacecraft to arrive at the Moon at the proper time and phase. This approach accommodates any dispersion in the Minotaur V launch injection. LADEE's arrival at the moon in early October. The spacecraft will approach the moon from its leading edge, travel behind the Moon out of sight of the Earth, and then re-emerge and execute a three-minute Lunar Orbit Insertion maneuver. This will place LADEE in an elliptical retrograde equatorial orbit with an orbital period of approximately 24 hours. A series of maneuvers is then performed to reduce the orbit to become nearly circular with a 156-mile (250- kilometer) altitude. Spacecraft checkout and science instrument commissioning will commence in early-October and will nominally span 30 days but can be extended for an additional 30 days in the event of contingencies. Following commissioning, the 100-day Science Phase is performed at an orbit with periapsis between 20-60 km. This orbit must be constantly managed due to the Moon's highly inhomogeneous gravity field. During the Science Phase, the moon will rotate more than three times underneath the LADEE orbit. LADEE employs a high heritage instrument payload: a Neutral Mass Spectrometer (NMS) from Goddard Space Flight Center, an Ultraviolet/Visible Spectrometer (UVS) from Ames Research Center, and a dust detection experiment (LDEX) from the University of Colorado/LASP. It will also carry the Lunar Laser Communications Demonstration (LLCD) as a technology demonstration. The LLCD is funded by the Human Exploration Operations Mission Directorate (HEOMD), managed by GSFC, and built by the MIT Lincoln Lab. Contingent upon LADEE's successful lunar orbit insertion and checkout, we will report the early results from the science investigations.
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A corrected tether-mission to Jupiter
NASA Astrophysics Data System (ADS)
Sanchez-Arriaga, G.; Charro, M.
2012-09-01
A spacecraft slowly descending in equatorial orbit through the inner magnetosphere of Jupiter over a period of months would provide a wealth of knowledge through space and time resolved observations. An electrodynamic (ED) bare-foil tether has been proposed as allowing a spacecraft to attain a circular orbit below Jovian radiation belts and Halo ring (so as to then carry out scientific observations) using Lorentz drag on the current induced in the tether for orbit insertion, followed by a series of perijove passes to progressively lower the apojove. Accumulated radiation dose was reasonable when using a 50 km long tether. It was recently shown, however, that electron collection by the tether would then be in a relativistic regime. This yields a penetration depth in aluminum exceeding foil thickness. Reducing the length to 10 km is here proposed, followed by a reconsideration of the scientific mission objectives.
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Artist concept illustrating key events on day by day basis during Apollo 9
NASA Technical Reports Server (NTRS)
1969-01-01
Artist concept illustrating key events on day by day basis during Apollo 9 mission. First photograph illustrates activities on the first day of the mission, including flight crew preparation, orbital insertion, 103 north mile orbit, separations, docking and docked Service Propulsion System Burn (19792); Second day events include landmark tracking, pitch maneuver, yaw-roll maneuver, and high apogee orbits (19793); Third day events include crew transfer and Lunar Module system evaluation (19794); Fourth day events include use of camera, day-night extravehicular activity, use of golden slippers, and television over Texas and Louisiana (19795); Fifth day events include vehicles undocked, Lunar Module burns for rendezvous, maximum separation, ascent propulsion system burn, formation flying and docking, and Lunar Module jettison ascent burn (19796); Sixth thru ninth day events include service propulsion system burns and landmark sightings, photograph special tests (19797); Tenth day events i
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Baggie: A unique solution to an orbiter icing problem
NASA Technical Reports Server (NTRS)
Walkover, L. J.
1982-01-01
The orbiter icing problem, located in two lower surface mold line cavities, was solved. These two cavities are open during Shuttle ground operations and ascent, and are then closed after orbit insertion. If not protected, these cavities may be coated with ice, which may be detrimental to the adjacent thermal protection system (TPS) tiles if the ice breaks up during ascent, and may hinder the closing of the cavity doors if the ice does not break up. The problem of ice in these cavities was solved by the use of a passive mechanism called baggie, which is purge curtain used to enclose the cavity and is used in conjunction with gaseous nitrogen as the local purge gas. The baggie, the final solution, is unique in its simplicity, but its design and development were not. The final baggie design and its development testing are discussed. Also discussed are the baggie concepts and other solutions not used.
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Design Tools for Reconfigurable Hardware in Orbit (RHinO)
NASA Technical Reports Server (NTRS)
French, Mathew; Graham, Paul; Wirthlin, Michael; Larchev, Gregory; Bellows, Peter; Schott, Brian
2004-01-01
The Reconfigurable Hardware in Orbit (RHinO) project is focused on creating a set of design tools that facilitate and automate design techniques for reconfigurable computing in space, using SRAM-based field-programmable-gate-array (FPGA) technology. These tools leverage an established FPGA design environment and focus primarily on space effects mitigation and power optimization. The project is creating software to automatically test and evaluate the single-event-upsets (SEUs) sensitivities of an FPGA design and insert mitigation techniques. Extensions into the tool suite will also allow evolvable algorithm techniques to reconfigure around single-event-latchup (SEL) events. In the power domain, tools are being created for dynamic power visualiization and optimization. Thus, this technology seeks to enable the use of Reconfigurable Hardware in Orbit, via an integrated design tool-suite aiming to reduce risk, cost, and design time of multimission reconfigurable space processors using SRAM-based FPGAs.
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NASA Astrophysics Data System (ADS)
Fu, H. R.; Ma, L.; Tian, N.; You, C. Y.; Wang, K.
2018-05-01
A systematic study of anomalous Hall effect (AHE) was performed in perpendicular magnetic anisotropic Pd/Co2MnSi(tCMS)/MgO/Pd films. The AHE was significantly intensified by inserting MgO layer, which can be ascribed to the enhancement of spin-orbit coupling and interfacial scattering contribution. Moreover, it was found that the Co and Mn ions were reduced at the interface of Co2MnSi/MgO with annealing process. The stable amount of Mn-O bonding was observed at the Co2MnSi/MgO interface after annealing, implying that the proper Mn-O bonding could be favorable for achieving large AHE.
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EIVAN - AN INTERACTIVE ORBITAL TRAJECTORY PLANNING TOOL
NASA Technical Reports Server (NTRS)
Brody, A. R.
1994-01-01
The Interactive Orbital Trajectory planning Tool, EIVAN, is a forward looking interactive orbit trajectory plotting tool for use with Proximity Operations (operations occurring within a one kilometer sphere of the space station) and other maneuvers. The result of vehicle burns on-orbit is very difficult to anticipate because of non-linearities in the equations of motion governing orbiting bodies. EIVAN was developed to plot resulting trajectories, to provide a better comprehension of orbital mechanics effects, and to help the user develop heuristics for onorbit mission planning. EIVAN comprises a worksheet and a chart from Microsoft Excel on a Macintosh computer. The orbital path for a user-specified time interval is plotted given operator burn inputs. Fuel use is also calculated. After the thrust parameters (magnitude, direction, and time) are input, EIVAN plots the resulting trajectory. Up to five burns may be inserted at any time in the mission. Twenty data points are plotted for each burn and the time interval can be varied to accommodate any desired time frame or degree of resolution. Since the number of data points for each burn is constant, the mission duration can be increased or decreased by increasing or decreasing the time interval. The EIVAN program runs with Microsoft's Excel for execution on a Macintosh running Macintosh OS. A working knowledge of Excel is helpful, but not imperative, for interacting with EIVAN. The program was developed in 1989.
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Developing School Psychology in Vietnam
ERIC Educational Resources Information Center
Le, Phuong; Hagans, Kristi; Powers, Kristin; Hass, Michael
2011-01-01
Like China, Vietnam is a communist country with increasingly capitalist economic policies. A fundamental change occurred in these policies with the enactment of Vietnam's "doi moi" (renovation) policy in 1986 that called for a "free market with socialist orientations." However, this economic modernization has inadvertently…
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1998-09-04
Workers watch as the Hubble Space Telescope Orbiting Systems Test (HOST)is lowered onto a workstand in the Space Shuttle Processing Facility. To the right can be seen the Rack Insertion Device and Leonardo, a Multi-Purpose Logistics Module. The HOST platform, one of the payloads on the STS-95 mission, is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process
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NASA Technical Reports Server (NTRS)
Williams, F. E.; Price, J. B.; Lemon, R. S.
1972-01-01
The simulation developments for use in dynamics and control analysis during boost from liftoff to orbit insertion are reported. Also included are wind response studies of the NR-GD 161B/B9T delta wing booster/delta wing orbiter configuration, the MSC 036B/280 inch solid rocket motor configuration, the MSC 040A/L0X-propane liquid injection TVC configuration, the MSC 040C/dual solid rocket motor configuration, and the MSC 049/solid rocket motor configuration. All of the latest math models (rigid and flexible body) developed for the MSC/GD Space Shuttle Functional Simulator, are included.
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NASA Technical Reports Server (NTRS)
2005-01-01
KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, a digital still camera has been mounted in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following ET separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
2005-01-01
KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers check the digital still camera they will mount in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following the tank's separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
2005-01-01
KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, a worker mounts a digital still camera in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following the ET separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
2005-01-01
KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers prepare a digital still camera they will mount in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following its separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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NASA Technical Reports Server (NTRS)
2005-01-01
KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers prepare a digital still camera they will mount in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following the ET separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.
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Sustainer electric propulsion system application for spacecraft attitude control
NASA Astrophysics Data System (ADS)
Obukhov, V. A.; Pokryshkin, A. I.; Popov, G. A.; Yashina, N. V.
2010-07-01
Application of electric propulsion system (EPS) requires spacecraft (SC) equipping with large solar panels (SP) for the power supply to electric propulsions. This makes the problem of EPS-equipped SC control at the insertion stage more difficult to solve than in the case of SC equipped with chemical engines, because in addition to the SC attitude control associated with the mission there appears necessity in keeping SP orientation to Sun that is necessary for generation of electric power sufficient for the operation of service systems, purpose-oriented equipment, and EPS. The theoretical study of the control problem is the most interesting for a non-coplanar transfer from high elliptic orbit (HEO) to geostationary orbit (GSO).
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NASA Astrophysics Data System (ADS)
Pelaccio, Dennis G.
1996-03-01
A novel, reusable, Vertical-Takeoff-and-Landing, Single-Stage-to-Orbit (VTOL/SSTO) launch system concept, named HYP-SSTO, is presented in this paper. This launch vehicle system concept uses a highly coupled, main high performance liquid oxygen/liquid hydrogen (LOX/LH2) propulsion system, that is used only for launch, with a hybrid auxiliary propulsion system which is used during final orbit insertion, major orbit maneuvering, and landing propulsive burn phases of flight. By using a hybrid propulsion system for major orbit maneuver burns and landing, this launch system concept has many advantages over conventional VTOL/SSTO concepts that use LOX/LH2 propulsion system(s) burns for all phases of flight. Because hybrid propulsion systems are relatively simple and inert by their nature, this concept has the potential to support short turnaround times between launches, be economical to develop, and be competitive in terms of overall system life-cycle cost. This paper provides a technical description of the novel, reusable HYP-SSTO launch system concept. Launch capability performance, as well as major design and operational system attributes, are identified and discussed.
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Magellan Prelaunch Mission Operations Report
NASA Technical Reports Server (NTRS)
1989-01-01
The Magellan spacecraft will be launched from Kennedy Space Center (KSC) within a 31-day overall launch period extending from April 28 to May 28, 1989. The launch will use the Shuttle Orbiter Atlantis to lift an Inertial Upper Stage (IUS) and the Magellan Spacecraft into low Earth orbit. After the Shuttle achieves its parking orbit, the IUS and attached Magellan spacecraft are deployed from the payload bay. After a short coast time, the two-stage IUS is fired to inject the Magellan spacecraft into an Earth-Venus transfer trajectory. The Magellan spacecraft is powered by single degree of freedom, sun-tracking, solar panels charging a set of nickel-cadmium batteries. The spacecraft is three-axis stabilized by reaction wheels using gyros and a star sensor for attitude reference. The spacecraft carries a solid rocket motor for Venus Orbit Insertion (VOI). A hydrazine propulsion system allows trajectory correction and prevents saturation of the reaction wheels. Communication with Earth through the Deep Space Network (DSN) is provided by S- and X-band telemetry channels, through alternatively a low, medium, or 3.7 m high-gain parabolic antenna rigidly attached to the spacecraft. The high-gain antenna also serves as the radar and radiometer antenna during orbit around Venus.
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Résultats fonctionnels des lésions des tendons fléchisseurs de la main: à propos de 90 cas
Boussakri, Hassan; Azarkane, Mohamad; Elidrissi, Mohamad; Shimi, Mohamad; Elibrahimi, Abdelhalim; Elmrini, Abdelmajid
2013-01-01
Les auteurs rapportent une série de 90 patients, présentant une section tendineuse des fléchisseurs de la main, et suivis avec un recul moyen de 8 mois (min: 2 mois; max: 13 mois). La lésion était localisée dans 12% des cas en zone I, 46% des cas en zone II, 2% en zone III et 25% des cas en zone IV et V. Pour le pouce (13 patients), 10 cas en zone T2 et 3 cas en zone T3. La technique opératoire utilisée était les sutures tendineuses en cadre de Kessler modifié, associée à un surjet épitendineux. Nous avons obtenus 54% de très bons résultats, 34% de résultats moyens et 12% de mauvais résultats. Pour le pouce les résultats semble moins bons avec un taux de résultats médiocre de 48%. Certes les chiffres de cette série sont moins bons que ceux des autres séries publiées dans la littérature. Les facteurs influençant les résultats sont d'abord l'utilisation d'immobilisation postopératoire systématique ainsi que le mécanisme d'agression, et la localisation à la zone II et au pouce. Les complications mécaniques sont représentées par 7% de rupture, toutes au niveau de pouce, et 31% des adhérences tendineuses (soit 30 cas), dont 19 en zone II, l'infections (22%) et 4% des cas d'algodystrophies. PMID:23847698
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NASA Astrophysics Data System (ADS)
Ma, Y.; Weber, R. J.; Maxwell-Meier, K.; Orsini, D. A.; Lee, Y.-N.; Huebert, B. J.; Howell, S. G.; Bertram, T.; Talbot, R. W.; Dibb, J. E.; Scheuer, E.
2004-08-01
As part of the two field studies, Transport and Chemical Evolution over the Pacific (TRACE-P) and the Asian Aerosol Characterization Experiment (ACE-Asia), the inorganic chemical composition of tropospheric aerosols was measured over the western Pacific from three separate aircraft using various methods. Comparisons are made between the rapid online techniques of the particle into liquid sampler (PILS) for measurement of a suite of fine particle a mist chamber/ion chromatograph (MC/IC) measurement of fine sulfate, and the longer time-integrated filter and micro-orifice impactor (MOI) measurements. Comparisons between identical PILS on two separate aircraft flying in formation showed that they were highly correlated (e.g., sulfate r2 of 0.95), but were systematically different by 10 ± 5% (linear regression slope and 95% confidence bounds), and had generally higher concentrations on the aircraft with a low-turbulence inlet and shorter inlet-to-instrument transmission tubing. Comparisons of PILS and mist chamber measurements of fine sulfate on two different aircraft during formation flying had an r2 of 0.78 and a relative difference of 39% ± 5%. MOI ionic data integrated to the PILS upper measurement size of 1.3 μm sampling from separate inlets on the same aircraft showed that for sulfate, PILS and MOI were within 14% ± 6% and correlated with an r2 of 0.87. Most ionic compounds were within ±30%, which is in the range of differences reported between PILS and integrated samplers from ground-based comparisons. In many cases, direct intercomparison between the various instruments is difficult due to differences in upper-size detection limits. However, for this study, the results suggest that the fine particle mass composition measured from aircraft agree to within 30-40%.
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A student's analysis of the Moi University-Linköping University exchange programme.
Mwenda, A S
2012-11-01
Introduction : Moi University College of Health Sciences was established in 1989. It is comprised of the schools of medicine, nursing, public health and dentistry. Since its inception, the college has been in collaboration with Linköping University in Sweden. This collaboration has taken the form of student and staff exchanges, as well as infrastructure and library improvements. This study was carried out to analyse the exchange programme and highlight some of the strengths that the exchange programme brings to the students' academic experience. Methods : A qualitative cross-sectional survey was conducted among the students who participated in the elective/exchange programme in the years 2009, 2010 and 2011. Self-administered questionnaires were completed by the participants. Additional data were obtained from the recommendations and conclusions from the reports that the students wrote after their participation in the exchange programme. Focus group discussions and key informant interviews were also carried out. Results : A total of 46 students participated in the exchange programme: 27 from Moi University and 19 from Linköping University. The disciplines of students reflected the undergraduate courses offered by these universities. The exchange programme's strengths were exposing students to new cultural settings, different healthcare system organisation and influencing future academic and personal lives, as well as making education global. The main challenge facing the exchange programme was language. Discussion : This study shows the exchange programme as a strong pillar of the medical education curriculum, enabling students to get a global perspective on their education, while exposing them to significant cultural and healthcare organisation diversity. There is a need to expand the collaboration so that more students have the opportunity to experience the overseas exchange programme.
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Lakhdar, Nadia; Denguezli, Myriam; Zaouali, Monia; Zbidi, Abdelkrim; Tabka, Zouhair; Bouassida, Anissa
2013-12-01
The purpose of this study was to investigate the effect of 6 months aerobic exercise and diet alone or in combination on markers of inflammation (MOI) in circulation and in adipose abdominal tissue (AT) in obese women. Thirty obese subjects were randomized into a 24-week intervention: (1) exercise (EX), (2) diet (DI), and (3) exercise and diet (EXD). Blood samples were collected at baseline, after 12 and 24 weeks. AT biopsies were obtained only at baseline and after 24 weeks. In the EXD and DI groups, the fat loss was after 12 weeks was -13.74 and -7.8 % (P < 0.01) and after 24 weeks was -21.82 and -17 % (P < 0.01) with no changes in the EX group. After 12 and 24 weeks, maximal oxygen consumption (VO2max) was increased by 21.81-39.54 % (P < 0.05) in the EXD group and 18.09-40.95 % in the EX group with no changes in the DI group. In the EXD and DI groups, circulating levels of tumor necrosis factor α and interleukin 6 were decreased after 24 weeks for both groups (P < 0.01). No changes in the EX group. Homeostatic model assessment for insulin resistance decreased (P < 0.05) only after 24 weeks in the EXD group. In AT biopsies, subjects in the EXD and DI groups exhibited a significant decrease in MO (P < 0.01 for all). No changes in AT biopsies were found in the EX group. In conclusion, chronic aerobic exercise was found to have no effects on circulating and AT MOI despite an increased VO2max. Rather important body composition modifications were found to have beneficial effects on circulating and AT MOI in these obese women.
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NASA Technical Reports Server (NTRS)
Ma, Y.; Weber, R. J.; Maxwell-Meier, K.; Orsini, D. A.; Lee, Y.-N.; Huebert, B. J.; Howell, S. G.; Bertram, T.; Talbot, R. W.
2003-01-01
As part of the two field studies, Transport and Chemical Evolution over the Pacific (TRACE-P), and the Asian Aerosol Characterization Experiment (ACEAsia), the inorganic chemical composition of tropospheric aerosols was measured over the western Pacific from three separate aircraft using various methods. Comparisons are made between the rapid online techniques of the Particle Into Liquid Sampler (PILS) for measurement of a suite of fine particle ionic compounds and a mist chamber (MC/IC) measurement of fine sulfate, and the longer time-integrated filter and multi-orifice impactor (MOI) measurements. Comparisons between identical PILS on two separate aircraft flying in formation showed that they were highly correlated (e.g., sulfate r(sup 2) of 0.95), but were systematically different by 10 +/- 5% (linear regression slope and 95% confidence bounds), and had generally higher concentrations on the aircraft with a low turbulence inlet and shorter inlet-to-instrument transmission tubing. Comparisons of PILS and mist chamber measurements of fine sulfate on two different aircraft during formation flying had an 3 of 0.78 and a relative difference of 39% +/- 5%. MOI ionic data integrated to the PILS upper measurement size of 1.3 pm sampling from separate inlets on the same aircraft showed that for sulfate, PILS and MOI were within 14% +/- 6% and correlated with an r(sup 2) of 0.87. Most ionic compounds were within f 30%, which is in the range of differences reported between PILS and integrated samplers from ground-based comparisons. In many cases, direct intercomparison between the various instruments is difficult due to differences in upper-size detection limits. However, for this study, the results suggest that the fine particle mass composition measured from aircraft agree to within 30-40%.
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Pyélonéphrite xanthogranulomateuse bilatérale focale : à propos d’un cas
El Yacoubi, Souhail; Ziouziou, Imad; Zizi, Mohamed; Jahid, Ahmed; Karmouni, Tariq; El Khader, Khalid; Koutani, Abdellatif; Andaloussi, Ahmed Iben Attya
2014-01-01
Résumé Nous présentons l’observation clinique d’un cas rare de pyélonéphrite xanthogranulomateuse (PXG) bilatérale chez un jeune patient âgé de 17 ans. La découverte progressive de l’infection a débuté par l’apparition de lombalgies bilatérales évoluant depuis un mois, sans autre signe associé. L’urotomodensitométrie penchait en faveur de deux masses rénales bilatérales, soit une masse polaire inférieure droite et une masse polaire supérieure gauche, toutes deux de densité tissulaire. Une biopsie échoguidée a suggéré la présence d’une réaction inflammatoire non spécifique. Une néphrectomie partielle polaire inférieure droite a été effectuée devant la forte présomption de tumeurs rénales malignes. Finalement, l’histologie a orienté le diagnostic vers une PXG. Il s’agit, à notre connaissance, du sixième cas de PXG focale bilatérale rapporté dans la littérature. Notre patient a reçu un traitement antibiotique à base de fluoroquinolone pendant un mois. L’évolution clinique s’est avérée bonne, et les lésions visibles à la tomodensitométrie se sont entièrement résorbées au bout d’un mois. Le patient vit toujours après un an et présente une fonction rénale normale. PMID:25295145
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Meier, Jeffery L.; Keller, Michael J.; McCoy, James J.
2002-01-01
We have shown previously that the human cytomegalovirus (HCMV) major immediate-early (MIE) distal enhancer is needed for MIE promoter-dependent transcription and viral replication at low multiplicities of infection (MOI). To understand how this region works, we constructed and analyzed a series of HCMVs with various distal enhancer mutations. We show that the distal enhancer is composed of at least two parts that function independently to coordinately activate MIE promoter-dependent transcription and viral replication. One such part is contained in a 47-bp segment that has consensus binding sites for CREB/ATF, SP1, and YY1. At low MOI, these working parts likely function in cis to directly activate MIE gene expression, thus allowing viral replication to ensue. Three findings support the view that these working parts are likely cis-acting elements. (i) Deletion of either part of a bisegmented distal enhancer only slightly alters MIE gene transcription and viral replication. (ii) Reversing the distal enhancer’s orientation largely preserves MIE gene transcription and viral replication. (iii) Placement of stop codons at −300 or −345 in all reading frames does not impair MIE gene transcription and viral replication. Lastly, we show that these working parts are dispensable at high MOI, partly because of compensatory stimulation of MIE promoter activity and viral replication that is induced by a virion-associated component(s) present at a high viral particle/cell ratio. We conclude that the distal enhancer is a complex multicomponent cis-acting region that is required to augment both MIE promoter-dependent transcription and HCMV replication. PMID:11739696
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Spacecraft Charging Considerations and Design Efforts for the Orion Crew Module
NASA Technical Reports Server (NTRS)
Scully, Bob
2017-01-01
The Orion Crew Module (CM) is nearing completion for the next flight, designated as Exploration Mission 1 (EM-1). For the uncrewed mission, the flight path will take the CM through a Perigee Raise Maneuver (PRM) out to an altitude of approximately 1800 km, followed by a Trans-Lunar Injection burn, a pass through the Van Allen belts then out to the moon for a lunar flyby, a Distant Retrograde Insertion (DRI) burn, a Distant Retrograde Orbit (DRO), a Distant Retrograde Departure (DRD) burn, a second lunar flyby, an Earth Insertion (EI) burn, and finally entry and landing. All of this, with the exception of the DRO associated maneuvers, is similar to the previous Apollo 8 mission in late 1968. In recent discussions, it is now possible that EM-1 will be a crewed mission, and if this happens, the orbit may be quite different from that just described. In this case, the flight path may take the CM on an out and back pass through the Van Allen belts twice, then out to the moon, again passing through the Van Allen belts twice, then finally back home. Even if the current EM-1 mission doesn't end up as a crewed mission, EM-2 and subsequent missions will undoubtedly follow orbital trajectories that offer comparable exposures to heightened vehicle charging effects. Because of this, and regardless of flight path, the CM vehicle will likely experience a wide range of exposures to energetic ions and electrons, essentially covering the gamut between low earth orbit to geosynchronous orbit and beyond. National Aeronautical and Space Administration (NASA) and Lockheed Martin (LM) engineers and scientists have been working to fully understand and characterize the vehicle's immunity level with regard to surface and deep dielectric charging, and the ramifications of that immunity level pertaining to materials and impacts to operational avionics, communications, and navigational systems. This presentation attempts to chronicle these efforts in a summary fashion, and attempts to capture the results of that work as they pertain to the electrical and avionic systems on-board the Orion CM.
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Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS) - Cyclops
NASA Technical Reports Server (NTRS)
Smith, James P.; Lamb, Craig R.; Ballard, Perry G.
2013-01-01
Access to space for satellites in the 50-100 kg class is a challenge for the small satellite community. Rideshare opportunities are limited and costly, and the small sat must adhere to the primary payloads schedule and launch needs. Launching as an auxiliary payload on an Expendable Launch Vehicle presents many technical, environmental, and logistical challenges to the small satellite community. To assist the community in mitigating these challenges and in order to provide the community with greater access to space for 50-100 kg satellites, the NASA International Space Station (ISS) and Engineering communities in collaboration with the Department of Defense (DOD) Space Test Program (STP) is developing a dedicated 50-100 kg class ISS small satellite deployment system. The system, known as Cyclops, will utilize NASA's ISS resupply vehicles to launch small sats to the ISS in a controlled pressurized environment in soft stow bags. The satellites will then be processed through the ISS pressurized environment by the astronaut crew allowing satellite system diagnostics prior to orbit insertion. Orbit insertion is achieved through use of the Japan Aerospace Exploration Agency's Experiment Module Robotic Airlock (JEM Airlock) and one of the ISS Robotic Arms. Cyclops' initial satellite deployment demonstration of DOD STP's SpinSat and UT/TAMU's Lonestar satellites will be toward the end of 2013 or beginning of 2014. Cyclops will be housed on-board the ISS and used throughout its lifetime. The anatomy of Cyclops, its concept of operations for satellite deployment, and its satellite interfaces and requirements will be addressed further in this paper.
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Demonstration of an Aerocapture GN and C System Through Hardware-in-the-Loop Simulations
NASA Technical Reports Server (NTRS)
Masciarelli, James; Deppen, Jennifer; Bladt, Jeff; Fleck, Jeff; Lawson, Dave
2010-01-01
Aerocapture is an orbit insertion maneuver in which a spacecraft flies through a planetary atmosphere one time using drag force to decelerate and effect a hyperbolic to elliptical orbit change. Aerocapture employs a feedback Guidance, Navigation, and Control (GN&C) system to deliver the spacecraft into a precise postatmospheric orbit despite the uncertainties inherent in planetary atmosphere knowledge, entry targeting and aerodynamic predictions. Only small amounts of propellant are required for attitude control and orbit adjustments, thereby providing mass savings of hundreds to thousands of kilograms over conventional all-propulsive techniques. The Analytic Predictor Corrector (APC) guidance algorithm has been developed to steer the vehicle through the aerocapture maneuver using bank angle control. Through funding provided by NASA's In-Space Propulsion Technology Program, the operation of an aerocapture GN&C system has been demonstrated in high-fidelity simulations that include real-time hardware in the loop, thus increasing the Technology Readiness Level (TRL) of aerocapture GN&C. First, a non-real-time (NRT), 6-DOF trajectory simulation was developed for the aerocapture trajectory. The simulation included vehicle dynamics, gravity model, atmosphere model, aerodynamics model, inertial measurement unit (IMU) model, attitude control thruster torque models, and GN&C algorithms (including the APC aerocapture guidance). The simulation used the vehicle and mission parameters from the ST-9 mission. A 2000 case Monte Carlo simulation was performed and results show an aerocapture success rate of greater than 99.7%, greater than 95% of total delta-V required for orbit insertion is provided by aerodynamic drag, and post-aerocapture orbit plane wedge angle error is less than 0.5 deg (3-sigma). Then a real-time (RT), 6-DOF simulation for the aerocapture trajectory was developed which demonstrated the guidance software executing on a flight-like computer, interfacing with a simulated IMU and simulated thrusters, with vehicle dynamics provided by an external simulator. Five cases from the NRT simulations were run in the RT simulation environment. The results compare well to those of the NRT simulation thus verifying the RT simulation configuration. The results of the above described simulations show the aerocapture maneuver using the APC algorithm can be accomplished reliably and the algorithm is now at TRL-6. Flight validation is the next step for aerocapture technology development.
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THE HYDROLOGIC RESPONSE OF A SMALL CATCHMENT TO CLEAR-CUTTING
We simulated how a landscape disturbance (e.g., fire or clear-cutting) alters hillslope and catchment hydrologic processes. Specifically, we simulated how the pattern and magnitude of tree removal in a catchment increases downslope transport of water and alters catchment soil moi...
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Unexpected Decrease in Moment of Inertia Between N = 98-100 in 162,164Gd
NASA Astrophysics Data System (ADS)
Jones, E. F.; Hamilton, J. H.; Gore, P. M.; Ramayya, A. V.; Hwang, J. K.; Delima, A. P.; Zhu, S. J.; Beyer, C. J.; Luo, Y. X.; Kormicki, J.; Zhang, X. Q.; Ma, W. C.; Rasmussen, J. O.; Lee, I. Y.; Wu, S. C.; Folden, C. M.; Fallon, P.; Zielinski, P.; Gregorich, K. E.; Macchiavelli, A. O.; Ginter, T. N.; Stoyer, M.; Cole, J. D.; Janssens, R. V. F.; Ahmad, I.; Daniel, A. V.; Ter-Akopian, G. M.; Oganessian, Yu. Ts.; Donangelo, R.; Asztalos, S. J.
2003-10-01
From γ-γ-γ coincidence studies of the prompt γ-rays emitted in the spontaneous fission (SF) of 252Cf with Gammasphere, the yrast energy levels in neutron-rich 162,164Gd were identified for the first time from 2+ to 16+ and from 2+ to 14+, respectively. The 2+ level energies are 71.6 and 73.3 keV in 162,164Gd, respectively. The transition energies from every level in 164Gd are higher than those from the same levels in 162Gd. There is a systematic decrease at every level of the moment of inertia (MOI) and similarly β2 deformation in N = 100 164Gd compared to N = 98 162Gd. The minimum in E(2+) and maxima in MOI and β2 occur at N = 98. This behavior is unexpected compared to the E(2+) and β2 trends in Er, Yb, and Hf nuclei where the minima and maxima occur at neutron midshell, N = 104.
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Erwin, Terry L.; Aldebron, Charlotte
2018-01-01
Abstract Thoasia Liebke, 1939 and Straneotia Mateu, 1961 of the Cryptobatida group, subtribe Agrina, Lebiini, living in the Neotropics are diagnosed, described, and illustrated. Occurrences of known species ranges are limited to the northern and western Amazon Basin and Guyana Shield. The following species are described as new: Thoasia surinamensis Erwin & Aldebron, sp. n., Suriname, Thoasia pterosmaragdos Aldebron & Erwin, sp. n., French Guiana, Thoasia manu Erwin & Aldebron, sp. n., Ecuador, Perú; Straneotia cylindroceps Erwin & Aldebron, sp. n., French Guiana, Straneotia confundis Aldebron & Erwin, sp. n., Ecuador, and Straneotia moi Aldebron & Erwin, sp. n., French Guiana. Two of these species, Thoasia manu and Straneotia moi are known from adults collected by insecticidal fogging of lowland rainforest trees, and these trees are listed in their respective descriptions. The following species are redescribed: Thoasia rugifrons Liebke, 1939, French Guiana, Venezuela; Straneotia freyi Mateu, 1961, Brazil; Straneotia amazonica Mateu, 1961, Brazil. PMID:29670431
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Koch, D.; Fertitta, E.; Paulus, B.
Due to the importance of both static and dynamical correlation in the bond formation, low-dimensional beryllium systems constitute interesting case studies to test correlation methods. Aiming to describe the whole dissociation curve of extended Be systems we chose to apply the method of increments (MoI) in its multireference (MR) formalism. To gain insight into the main characteristics of the wave function, we started by focusing on the description of small Be chains using standard quantum chemical methods. In a next step we applied the MoI to larger beryllium systems, starting from the Be{sub 6} ring. The complete active space formalismmore » was employed and the results were used as reference for local MR calculations of the whole dissociation curve. Although this is a well-established approach for systems with limited multireference character, its application regarding the description of whole dissociation curves requires further testing. Subsequent to the discussion of the role of the basis set, the method was finally applied to larger rings and extrapolated to an infinite chain.« less
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System design of the Pioneer Venus spacecraft. Volume 11: Launch vehicle utilization
NASA Technical Reports Server (NTRS)
Varga, R. J.
1973-01-01
A summary of the spacecraft descriptions; the probe bus, large probe, small probe, and orbiter is presented. The highlights on the designs of the Atlas/Centaur spacecraft as compared to the corresponding Thor/Delta spacecraft designs are contained. A comparison is made of the two Atlas/Centaur spacecraft for reference. The major differences are the replacement of the probes of the forward end of the probe bus with the mechanically despun antenna of the orbiter and the replacement of the bicone antenna on the aft end with the orbit insertion motor. The cross sections of the large and small probes are compared. The major features of each probe are described. The Thor/Delta and Atlas/Centaur designs for the probe bus and orbiter are analyzed. The usable spacecraft mass for the Atlas/Centaur is roughly twice that for the Thor/Delta if the Type I trajectory is assumed. It is somewhat less for the Type II trajectory in the designated launch years. This additional mass capability leads to cost savings in many areas which are described.
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Aeroheating Thermal Analysis Methods for Aerobraking Mars Missions
NASA Technical Reports Server (NTRS)
Amundsen, Ruth M.; Dec, John A.; George, Benjamin E.
2002-01-01
Mars missions often employ aerobraking upon arrival at Mars as a low-mass method to gradually reduce the orbit period from a high-altitude, highly elliptical insertion orbit to the final science orbit. Two recent missions that made use of aerobraking were Mars Global Surveyor (MGS) and Mars Odyssey. Both spacecraft had solar arrays as the main aerobraking surface area. Aerobraking produces a high heat load on the solar arrays, which have a large surface area exposed to the airflow and relatively low mass. To accurately model the complex behavior during aerobraking, the thermal analysis must be tightly coupled to the flight mechanics, aerodynamics, and atmospheric modeling efforts being performed during operations. To properly represent the temperatures prior to and during the drag pass, the model must include the orbital solar and planetary heat fluxes. The correlation of the thermal model to flight data allows a validation of the modeling process, as well as information on what processes dominate the thermal behavior. This paper describes the thermal modeling method that was developed for this purpose, as well as correlation for two flight missions, and a discussion of improvements to the methodology.
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Mars Express Interplanetary Navigation from Launch to Mars Orbit Insertion: The JPL Experience
NASA Technical Reports Server (NTRS)
Han, Dongsuk; Highsmith, Dolan; Jah, Moriba; Craig, Diane; Border, James; Kroger, Peter
2004-01-01
The National Aeronautics and Space Administration (NASA) Jet Propulsion Laboratory (JPL) played a significant role in supporting the safe arrival of the European Space Agency (ESA) Mars Express (MEX) orbiter to Mars on 25 December 2003. MEX mission is an international collaboration between member nations of the ESA and NASA, where NASA is supporting partner. JPL's involvement included providing commanding and tracking service with JPL's Deep Space Network (DSN), in addition to navigation assurance. The collaborative navigation effort between European Space Operations Centre (ESOC) and JPL is the first since ESA's last deep space mission, Giotto, and began many years before the MEX launch. This paper discusses the navigational experience during the cruise and final approach phase of the mission from JPL's perspective. Topics include technical challenges such as orbit determination using non-DSN tracking data and media calibrations, and modeling of spacecraft physical properties for accurate representation of non-gravitational dynamics. Also mentioned in this paper is preparation and usage of DSN Delta Differential Oneway Range ((Delta)DOR) measurements, a key element to the accuracy of the orbit determination.
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Mission Design, Guidance, and Navigation of a Callisto-Io-Ganymede Triple Flyby Jovian Capture
NASA Astrophysics Data System (ADS)
Didion, Alan M.
Use of a triple-satellite-aided capture maneuver to enter Jovian orbit reduces insertion DeltaV and provides close flyby science opportunities at three of Jupiter's four large Galilean moons. This capture can be performed while maintaining appropriate Jupiter standoff distance and setting up a suitable apojove for plotting an extended tour. This paper has three main chapters, the first of which discusses the design and optimization of a triple-flyby capture trajectory. A novel triple-satellite-aided capture uses sequential flybys of Callisto, Io, and Ganymede to reduce the DeltaV required to capture into orbit about Jupiter. An optimal broken-plane maneuver is added between Earth and Jupiter to form a complete chemical/impulsive interplanetary trajectory from Earth to Jupiter. Such a trajectory can yield significant fuel savings over single and double-flyby capture schemes while maintaining a brief and simple interplanetary transfer phase. The second chapter focuses on the guidance and navigation of such trajectories in the presence of spacecraft navigation errors, ephemeris errors, and maneuver execution errors. A powered-flyby trajectory correction maneuver (TCM) is added to the nominal trajectory at Callisto and the nominal Jupiter orbit insertion (JOI) maneuver is modified to both complete the capture and target the Ganymede flyby. A third TCM is employed after all the flybys to act as a JOI cleanup maneuver. A Monte Carlo simulation shows that the statistical DeltaV required to correct the trajectory is quite manageable and the flyby characteristics are very consistent. The developed methods maintain flexibility for adaptation to similar launch, cruise, and capture conditions. The third chapter details the methodology and results behind a completely separate project to design and optimize an Earth-orbiting three satellite constellation to perform very long baseline interferometry (VLBI) as part of the 8th annual Global Trajectory Optimisation Competition (GTOC8). A script is designed to simulate the prescribed constellation and record its observations; the observations made are scored according to a provided performance index.
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Microwave sensing of moisture in flowing biomass pellets
USDA-ARS?s Scientific Manuscript database
Production of pelleted biomass is a significant emerging industry in the United States. A primary quality attribute of pelleted biomass is moisture content. This parameter is critical in pricing, binding, combustion, and storage of pelleted biomass. In order to produce pellets of a high quality mois...
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1991-12-01
December, 1991 i--" NASA-Lewis Research Center Cleveland, Ohio 44135 94-08573 Contract No. NAS3-23773 .0l•!ill~• 111 l94 3 16 09V PISULATIXI NOTICI... 3 3.1 Test Hardware and Facility Description...V - Drawings and Layouts of Calorimeter Insert and Related Hardware .... 133 - Ui - FIGURES NUMBER PIALE GE 3 -1 Integrated Component Evaluator (I.C.E
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Fabrication of graphite/epoxy cases for orbit insertion motors
NASA Technical Reports Server (NTRS)
Schmidt, W. W.
1973-01-01
The fabrication procedures are described for filament-wound rocket motor cases, approximately 26.25 inches long by 25.50 inches diameter, utilizing graphite fibers. The process utilized prepreg tape which consists of Fortafil 4-R fibers in the E-759 epoxy resin matrix. This fabrication effect demonstrated an ability to fabricate high quality graphite/epoxy rocket motor cases in the 26.25 inch by 25.50 inch size range.
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JUNO Photovoltaic Power at Jupiter
NASA Technical Reports Server (NTRS)
Dawson, Stephen F.; Stella, Paul; McAlpine, William; Smith, Brian
2012-01-01
This paper summarizes the Juno modeling team work on predicting the Juno solar array performance at critical mission points including Juno Orbit Insertion (JOI) and End of Mission (EOM). This report consists of background on Juno solar array design, a summary of power estimates, an explanation of the modeling approach used by Aerospace, a detailed discussion of loss factors and performance predictions, a thermal analysis, and a review of risks to solar array performance
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Radiation analysis for manned missions to the Jupiter system
NASA Technical Reports Server (NTRS)
De Angelis, G.; Clowdsley, M. S.; Nealy, J. E.; Tripathi, R. K.; Wilson, J. W.
2004-01-01
An analysis for manned missions targeted to the Jovian system has been performed in the framework of the NASA RASC (Revolutionary Aerospace Systems Concepts) program on Human Exploration beyond Mars. The missions were targeted to the Jupiter satellite Callisto. The mission analysis has been divided into three main phases, namely the interplanetary cruise, the Jupiter orbital insertion, and the surface landing and exploration phases. The interplanetary phase is based on departure from the Earth-Moon L1 point. Interplanetary trajectories based on the use of different propulsion systems have been considered, with resulting overall cruise phase duration varying between two and five years. The Jupiter-approach and the orbital insertion trajectories are considered in detail, with the spacecraft crossing the Jupiter radiation belts and staying around the landing target. In the surface exploration phase the stay on the Callisto surface is considered. The satellite surface composition has been modeled based on the most recent results from the GALILEO spacecraft. In the transport computations the surface backscattering has been duly taken into account. Particle transport has been performed with the HZETRN heavy ion code for hadrons and with an in-house developed transport code for electrons and bremsstrahlung photons. The obtained doses have been compared to dose exposure limits. c2004 COSPAR. Published by Elsevier Ltd. All rights reserved.
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Radiation analysis for manned missions to the Jupiter system.
De Angelis, G; Clowdsley, M S; Nealy, J E; Tripathi, R K; Wilson, J W
2004-01-01
An analysis for manned missions targeted to the Jovian system has been performed in the framework of the NASA RASC (Revolutionary Aerospace Systems Concepts) program on Human Exploration beyond Mars. The missions were targeted to the Jupiter satellite Callisto. The mission analysis has been divided into three main phases, namely the interplanetary cruise, the Jupiter orbital insertion, and the surface landing and exploration phases. The interplanetary phase is based on departure from the Earth-Moon L1 point. Interplanetary trajectories based on the use of different propulsion systems have been considered, with resulting overall cruise phase duration varying between two and five years. The Jupiter-approach and the orbital insertion trajectories are considered in detail, with the spacecraft crossing the Jupiter radiation belts and staying around the landing target. In the surface exploration phase the stay on the Callisto surface is considered. The satellite surface composition has been modeled based on the most recent results from the GALILEO spacecraft. In the transport computations the surface backscattering has been duly taken into account. Particle transport has been performed with the HZETRN heavy ion code for hadrons and with an in-house developed transport code for electrons and bremsstrahlung photons. The obtained doses have been compared to dose exposure limits. c2004 COSPAR. Published by Elsevier Ltd. All rights reserved.
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NASA Astrophysics Data System (ADS)
Cardoso dos Santos, Josué; Carvalho, Jean Paulo; Vilhena de Moraes, Rodolpho
Europa and Ganymede are two of the four Jupiter’s moons which compose the Galilean satellite. These ones are planetary satellites of greater interest at the present moment among the scientific community. There are some missions being planned to visit them and and the Jovian system. One of them is the cooperation between NASA and ESA for the Europa Jupiter System Mission (EJSM). In this mission are planned the insertion of the spacecrafts JEO (Jupiter Europa Orbiter) and JGO (Jupiter Ganymede Orbiter) into Europa and Ganymede’s orbit. Thus, there is a great necessity for having a better comprehension of the dynamics of the orbits around this planetary satellite. This comprehension is essential for the success of this type of mission. In this context, this work aims to perform a search for low-altitude orbits around these planetary satellites. An emphasis is given in polar orbits. These orbits can be useful in the planning of aerospace activities to be conducted around this planetary satellite, with respect to the stability of orbits of artificial satellites. The study considers orbits of an artificial satellite around Europa and Ganymede under the influence of the third-body perturbation (the gravitational attraction of Jupiter) and the polygenic perturbations. These last ones occur due to forces such as the non-uniform distribution of mass (J2 and J3) of the main (central) body. A simplified dynamic model for polygenic perturbations is used. A new model for the third-body disturbance is presented considering it in an elliptical orbit. The Lagrange planetary equations, which compose a system of nonlinear differential equations, are used to describe the orbital motion of the artificial satellite around Ganymede. The equations showed here are developed in closed form to avoid expansions in inclination and eccentricity.
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HOST payload for STS-95 being moved into SSPF
NASA Technical Reports Server (NTRS)
1998-01-01
Workers watch as the Hubble Space Telescope Orbiting Systems Test (HOST)is lowered onto a workstand in the Space Shuttle Processing Facility. To the right can be seen the Rack Insertion Device and Leonardo, a Multi-Purpose Logistics Module. The HOST platform, one of the payloads on the STS-95 mission, is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process.
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Navigation of the Twin GRAIL Spacecraft into Science Formation at the Moon
NASA Technical Reports Server (NTRS)
Antreasian, P. G.; Bhat, R. S.; Criddle, K. E.; Goodson, T. D.; Hatch, S. J; Jefferson, D. C.; Lau, E. L.; Mohan, S.; Parker, J. S.; Roncoli, R. B.;
2012-01-01
On February 29, 2012 the twin NASA Gravity Recovery And Interior Laboratory (GRAIL) spacecraft, Ebb and flow, achieved precise synchronized formation for collecting highly sensitive lunar gravity data. This was accomplished after performing a total of 27 propulsive maneuvers between the two spacecraft (13 on Ebb, 14 on Flow) over six months. Each 300 kg GRAIL spacecraft independently flew a 3.8-month, low-energy trajectory to reach the Moon after separation from the launch vehicle on September 10, 2011. The space craft were captured into 11.5 hr co- planar polar orbits after performing Lunar Orbit Insertion (LOI) maneuvers on New Years Eve (Dec 31, 2011) and New Years Day (Jan 1, 2012), respectively for Ebb, and Flow. Once captured, each spacecraft performed clusters of period reduction maneuvers to bring their orbit periods down to just less than 2 hrs. Finally, the orbiters we replaced into science formation by performing five strategic maneuvers (2 on Ebb, 3 on Flow). These maneuvers ensured 3 months of orbit life time with mean altitudes of 55 km and separations of 82-217 km by targeting the orbits' eccentricity vectors to specific locations. This paper will discuss the navigation strategy and performance of the twin GRAIL spacecraft from the September 10, 2011 launch through the end of the Prime Mission Science Phase in June 2012.
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The History and Future of Community Colleges in Vietnam
ERIC Educational Resources Information Center
Le, Anh T.
2013-01-01
Since 1986, with the creation of the Renovation ("Doi moi") policy, Vietnam has demonstrated a strong commitment to the improvement of its higher education system. After 25 years of opening its doors to the global educational environment, Vietnam has achieved some notable accomplishments. The country's higher educational system has…
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USDA-ARS?s Scientific Manuscript database
Release of carbon dioxide through microbial respiration from the world’s crop residues (non-edible plant parts left in the field after harvest) represents an important form of carbon transfer from terrestrial ecosystems to the atmosphere. We hypothesized that alleviation of environmental stress (moi...
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First Results from NASA's Lunar Atmosphere and Dust Environment Explorer (LADEE)
NASA Astrophysics Data System (ADS)
Elphic, R. C.; Colaprete, A.; Horanyi, M.; Mahaffy, P. R.; Delory, G. T.; Noble, S. K.; Boroson, D.; Hine, B.; Salute, J.
2013-12-01
As of early August, 2013, the Lunar Atmosphere and Dust Environment Explorer (LADEE) mission is scheduled for launch on a Minotaur V rocket from Wallops Flight Facility during a five-day launch period that opens on Sept. 6, 2013 (early Sept. 7 UTC). LADEE will address 40 year-old mysteries of the lunar atmosphere and the question of levitated lunar dust. It will also pioneer the next generation of optical space communications. LADEE will assess the composition of the lunar atmosphere and investigate the processes that control its distribution and variability, including sources, sinks, and surface interactions. LADEE will also determine whether dust is present in the lunar exosphere, and reveal its sources and variability. These investigations are relevant to our understanding of surface boundary exospheres and dust processes occurring at many objects throughout the solar system, address questions regarding the origin and evolution of lunar volatiles, and have potential implications for future exploration activities. Following a successful launch, LADEE will enter a series of phasing orbits, which allows the spacecraft to arrive at the Moon at the proper time and phase. This approach accommodates any dispersion in the Minotaur V launch injection. LADEE's arrival at the moon depends on the launch date, but with the Sept. 6 launch date it should arrive at the Moon in early October. The spacecraft will approach the moon from its leading edge, travel behind the Moon out of sight of the Earth, and then re-emerge and execute a three-minute Lunar Orbit Insertion maneuver. This will place LADEE in an elliptical retrograde equatorial orbit with an orbital period of approximately 24 hours. A series of maneuvers is then performed to reduce the orbit to become nearly circular with a 156-mile (250-kilometer) altitude. Spacecraft checkout and science instrument commissioning will commence in early-October and will nominally span 30 days but can be extended for an additional 30 days in the event of contingencies. Following commissioning, the 100-day Science Phase is performed at an orbit with periapsis between 20-60 km. This orbit must be constantly managed due to the Moon's highly inhomogeneous gravity field. During the Science Phase, the moon will rotate more than three times underneath the LADEE orbit. LADEE employs a high heritage instrument payload: a Neutral Mass Spectrometer (NMS) from Goddard Space Flight Center, an Ultraviolet/Visible Spectrometer (UVS) from Ames Research Center, and a dust detection experiment (LDEX) from the University of Colorado/LASP. It will also carry the Lunar Laser Communications Demonstration (LLCD) as a technology demonstration. The LLCD is funded by the Human Exploration Operations Mission Directorate (HEOMD), managed by GSFC, and built by the MIT Lincoln Lab. Contingent upon LADEE's successful lunar orbit insertion and checkout, we will report the early results from the science investigations.
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Development of in-orbit refocusing mechanism for SpaceEye-1 electro-optical payload
NASA Astrophysics Data System (ADS)
Lee, Minwoo; Kim, Jongun; Chang, Jin-Soo; Kang, Myung-Seok
2016-09-01
SpaceEye-1 earth observation satellite, developed by Satrec Initiative Co. Ltd., is a 300 kg scale spacecraft with high resolution electro-optical payload (EOS-D) which performs 1 m GSD, 12 km swath in low earth orbit. Metering structure of EOS-D is manufactured with Carbon Fiber Reinforced Plastic (CFRP). Due to the moisture emission from CFRP metering structure, this spaceborne electro-optical payload undergoes shrinkage after orbit insertion. The shrinkage of metering structure causes change of the distance between primary and secondary mirror. In order to compensate the moisture shrinkage effect, two types of thermal refocusing mechanism were developed, analyzed and applied to EOS-D. Thermal analysis simulating in-orbit thermal condition and thermo-elastic displacement analysis was conducted to calculate the performance of refocusing mechanism. For each EOS-D telescope, analytical refocusing range (displacement change between primary and secondary mirror) was 2.5 um and 3.6 um. Thus, the refocusing mechanism can compensate the dimensional instability of metering structure caused by moisture emission. Furthermore, modal, static and wavefront error analysis was conducted in order to evaluate natural frequency, structural stability and optical performance. As a result, it can be concluded that the refocusing system of EOS-D payload can perform its function in orbit.
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Copernicus: Lunar surface mapper
NASA Technical Reports Server (NTRS)
Redd, Frank J.; Anderson, Shaun D.
1992-01-01
The Utah State University (USU) 1991-92 Space Systems Design Team has designed a Lunar Surface Mapper (LSM) to parallel the development of the NASA Office of Exploration lunar initiatives. USU students named the LSM 'Copernicus' after the 16th century Polish astronomer, for whom the large lunar crater on the face of the moon was also named. The top level requirements for the Copernicus LSM are to produce a digital map of the lunar surface with an overall resolution of 12 meters (39.4 ft). It will also identify specified local surface features/areas to be mapped at higher resolutions by follow-on missions. The mapping operation will be conducted from a 300 km (186 mi) lunar-polar orbit. Although the entire surface should be mapped within six months, the spacecraft design lifetime will exceed one year with sufficient propellant planned for orbit maintenance in the anomalous lunar gravity field. The Copernicus LSM is a small satellite capable of reaching lunar orbit following launch on a Conestoga launch vehicle which is capable of placing 410 kg (900 lb) into translunar orbit. Upon orbital insertion, the spacecraft will weigh approximately 233 kg (513 lb). This rather severe mass constraint has insured attention to component/subsystem size and mass, and prevented 'requirements creep.' Transmission of data will be via line-of-sight to an earth-based receiving system.
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Launch Condition Deviations of Reusable Launch Vehicle Simulations in Exo-Atmospheric Zoom Climbs
NASA Technical Reports Server (NTRS)
Urschel, Peter H.; Cox, Timothy H.
2003-01-01
The Defense Advanced Research Projects Agency has proposed a two-stage system to deliver a small payload to orbit. The proposal calls for an airplane to perform an exo-atmospheric zoom climb maneuver, from which a second-stage rocket is launched carrying the payload into orbit. The NASA Dryden Flight Research Center has conducted an in-house generic simulation study to determine how accurately a human-piloted airplane can deliver a second-stage rocket to a desired exo-atmospheric launch condition. A high-performance, fighter-type, fixed-base, real-time, pilot-in-the-loop airplane simulation has been modified to perform exo-atmospheric zoom climb maneuvers. Four research pilots tracked a reference trajectory in the presence of winds, initial offsets, and degraded engine thrust to a second-stage launch condition. These launch conditions have been compared to the reference launch condition to characterize the expected deviation. At each launch condition, a speed change was applied to the second-stage rocket to insert the payload onto a transfer orbit to the desired operational orbit. The most sensitive of the test cases was the degraded thrust case, yielding second-stage launch energies that were too low to achieve the radius of the desired operational orbit. The handling qualities of the airplane, as a first-stage vehicle, have also been investigated.
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NASA Technical Reports Server (NTRS)
1987-01-01
The detailed design of a small beam-powered trans-atmospheric vehicle, 'The Apollo Lightcraft,' was selected as the project for the design course. The vehicle has a lift-off gross weight of about six (6) metric tons and the capability to transport 500 kg of payload (five people plus spacesuits) to low Earth orbit. Beam power was limited to 10 gigawatts. The principal goal of this project is to reduce the low-Earth-orbit payload delivery cost by at least three orders of magnitude below the space shuttle orbiter--in the post 2020 era. The completely reusable, single-stage-to-orbit, shuttle craft will take off and land vertically, and have a reentry heat shield integrated with its lower surface--much like the Apollo command module. At the appropriate points along the launch trajectory, the combined cycle propulsion system will transition through three or four air breathing modes, and finally a pure rocket mode for orbital insertion. As with any revolutionary flight vehicle, engine development must proceed first. Hence, the objective for the spring semester propulsion course was to design and perform a detailed theoretical analysis on an advanced combined-cycle engine suitable for the Apollo Light craft. The analysis indicated that three air breathing cycles will be adequate for the mission, and that the ram jet cycle is unnecessary.
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Zhang, Wen-Bo; Mao, Chi; Liu, Xiao-Jing; Guo, Chuan-Bin; Yu, Guang-Yan; Peng, Xin
2015-10-01
Orbital floor defects after extensive maxillectomy can cause severe esthetic and functional deformities. Orbital floor reconstruction using the computer-assisted fabricated individual titanium mesh technique is a promising method. This study evaluated the application and clinical outcomes of this technique. This retrospective study included 10 patients with orbital floor defects after maxillectomy performed from 2012 through 2014. A 3-dimensional individual stereo model based on mirror images of the unaffected orbit was obtained to fabricate an anatomically adapted titanium mesh using computer-assisted design and manufacturing. The titanium mesh was inserted into the defect using computer navigation. The postoperative globe projection and orbital volume were measured and the incidence of postoperative complications was evaluated. The average postoperative globe projection was 15.91 ± 1.80 mm on the affected side and 16.24 ± 2.24 mm on the unaffected side (P = .505), and the average postoperative orbital volume was 26.01 ± 1.28 and 25.57 ± 1.89 mL, respectively (P = .312). The mean mesh depth was 25.11 ± 2.13 mm. The mean follow-up period was 23.4 ± 7.7 months (12 to 34 months). Of the 10 patients, 9 did not develop diplopia or a decrease in visual acuity and ocular motility. Titanium mesh exposure was not observed in any patient. All patients were satisfied with their postoperative facial symmetry. Orbital floor reconstruction after extensive maxillectomy with an individual titanium mesh fabricated using computer-assisted techniques can preserve globe projection and orbital volume, resulting in successful clinical outcomes. Copyright © 2015 American Association of Oral and Maxillofacial Surgeons. Published by Elsevier Inc. All rights reserved.
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NASA Astrophysics Data System (ADS)
Kato, Manabu; Sasaki, Susumu; Takizawa, Yoshisada
2010-07-01
The Japanese lunar orbiter Kaguya (SELENE) was successfully launched by an H2A rocket on September 14, 2007. On October 4, 2007, after passing through a phasing orbit 2.5 times around the Earth, Kaguya was inserted into a large elliptical orbit circling the Moon. After the apolune altitude was lowered, Kaguya reached its nominal 100 km circular polar observation orbit on October 19. During the process of realizing the nominal orbit, two subsatellites Okina (Rstar) and Ouna (Vstar) were released into elliptical orbits with 2400 km and 800 km apolune, respectively; both elliptical orbits had 100 km perilunes. After the functionality of bus system was verified, four radar antennas and a magnetometer boom were extended, and a plasma imager was deployed. Acquisition of scientific data was carried out for 10 months of nominal mission that began in mid-December 2007. During the 8-month extended mission, magnetic fields and gamma-rays from lower orbits were measured; in addition to this, low-altitude observations were carried out using a Terrain Camera, a Multiband Imager, and an HDTV camera. New data pertaining to an intense magnetic anomaly and GRS data with higher spatial resolution were acquired to study magnetism and the elemental distribution of the Moon. After some orbital maneuvers were performed by using the saved fuel, the Kaguya spacecraft finally impacted on the southeast part of the Moon. The Kaguya team has archived the initial science data, and since November 2, 2009, the data has been made available to public, and can be accessed at the Kaguya homepage of JAXA. The team continues to also study and publish initial results in international journals. Science purposes of the mission and onboard instruments including initial science results are described in this overview.
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An integral nuclear power and propulsion system concept
NASA Astrophysics Data System (ADS)
Choong, Phillip T.; Teofilo, Vincent L.; Begg, Lester L.; Dunn, Charles; Otting, William
An integral space power concept provides both the electrical power and propulsion from a common heat source and offers superior performance capabilities over conventional orbital insertion using chemical propulsion systems. This paper describes a hybrid (bimodal) system concept based on a proven, inherently safe solid fuel form for the high temperature reactor core operation and rugged planar thermionic energy converter for long-life steady state electric power production combined with NERVA-based rocket technology for propulsion. The integral system is capable of long-life power operation and multiple propulsion operations. At an optimal thrust level, the integral system can maintain the minimal delta-V requirement while minimizing the orbital transfer time. A trade study comparing the overall benefits in placing large payloads to GEO with the nuclear electric propulsion option shows superiority of nuclear thermal propulsion. The resulting savings in orbital transfer time and the substantial reduction of overall lift requirement enables the use of low-cost launchers for several near-term military satellite missions.
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HAN-Based Monopropellant Technology Development
NASA Technical Reports Server (NTRS)
Reed, Brian
2002-01-01
NASA Glenn Research Center is sponsoring efforts to develop technology for high-performance, high-density, low-freezing point, low-hazards monopropellant systems. The program is focused on a family of monopropellant formulations composed of an aqueous solution of hydroxylammonium nitrate (HAN) and a fuel component. HAN-based monopropellants offer significant mass and volume savings to small (less than 100 kg) satellite for orbit raising and on-orbit propulsion applications. The low-hazards characteristics of HAN-based monopropellants make them attractive for applications where ground processing costs are a significant concern. A 1-lbf thruster has been demonstrated to a 20-kg satellite orbit insertion duty cycle, using a formulation compatible with currently available catalysts. To achieve specific impulse levels above those of hydrazine, catalyst materials that can withstand the high-temperature, corrosive combustion environment of HAN-based monopropellants have to be developed. There also needs to be work done to characterize propellant properties, burning behavior, and material compatibility. NASA is coordinating their monopropellant efforts with those of the United States Air Force.
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Yi, Di; Liu, Jian; Hsu, Shang-Lin; ...
2016-05-19
Magnetic anisotropy (MA) is one of the most important material properties for modern spintronic devices. Conventional manipulation of the intrinsic MA, i.e., magnetocrystalline anisotropy (MCA), typically depends upon crystal symmetry. Extrinsic control over the MA is usually achieved by introducing shape anisotropy or exchange bias from another magnetically ordered material. Here we demonstrate a pathway to manipulate MA of 3d transition-metal oxides (TMOs) by digitally inserting nonmagnetic 5d TMOs with pronounced spin-orbit coupling (SOC). High-quality superlattices comprising ferromagnetic La 2/3Sr 1/3MnO 3 (LSMO) and paramagnetic SrIrO 3 (SIO) are synthesized with the precise control of thickness at the atomic scale.more » Magnetic easy-axis reorientation is observed by controlling the dimensionality of SIO, mediated through the emergence of a novel spin-orbit state within the nominally paramagnetic SIO.« less
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Development of the electric vehicle analyzer
NASA Astrophysics Data System (ADS)
Dickey, Michael R.; Klucz, Raymond S.; Ennix, Kimberly A.; Matuszak, Leo M.
1990-06-01
The increasing technological maturity of high power (greater than 20 kW) electric propulsion devices has led to renewed interest in their use as a means of efficiently transferring payloads between earth orbits. Several systems and architecture studies have identified the potential cost benefits of high performance Electric Orbital Transfer Vehicles (EOTVs). These studies led to the initiation of the Electric Insertion Transfer Experiment (ELITE) in 1988. Managed by the Astronautics Laboratory, ELITE is a flight experiment designed to sufficiently demonstrate key technologies and options to pave the way for the full-scale development of an operational EOTV. An important consideration in the development of the ELITE program is the capability of available analytical tools to simulate the orbital mechanics of a low thrust, electric propulsion transfer vehicle. These tools are necessary not only for ELITE mission planning exercises but also for continued, efficient, accurate evaluation of DoD space transportation architectures which include EOTVs. This paper presents such a tool: the Electric Vehicle Analyzer (EVA).
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Exploration Roadmap Working Group (ERWG) Data Collection, NASA's Inputs
NASA Technical Reports Server (NTRS)
Drake, Bret; Landis, Rob; Thomas, Andrew; Mauzy, Susan; Graham, Lee; Culbert, Chris; Troutman, Pat
2010-01-01
This slide presentation reviews four areas for further space exploration: (1) Human Exploration of Mars Design Reference Architecture (DRA) 5.0, (2) Robotic Precursors targeting Near Earth Objects (NEO) for Human Exploration, (3) Notional Human Exploration of Near Earth Objects and (4) Low Earth Orbit (LEO) Refueling to Augment Human Exploration. The first presentation reviews the goals and objectives of the Mars DRA, presents a possible mission profile, innovation requirements for the mission and key risks and challenges for human exploration of Mars. The second presentation reviews the objective and goals of the robotic precursors to the NEO and the mission profile of such robotic exploration. The third presentation reviews the mission scenario of human exploration of NEO, the objectives and goals, the mission operational drivers, the key technology needs and a mission profile. The fourth and last presentation reviews the examples of possible refueling in low earth orbit prior to lunar orbit insertion, to allow for larger delivered payloads for a lunar mission.
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NASA Technical Reports Server (NTRS)
Barnum, P. W.; Renzetti, N. A.; Textor, G. P.; Kelly, L. B.
1973-01-01
The Tracking and Data System (TDS) Support for the Mariner Mars 1971 Mission final report contains the deep space tracking and data acquisition activities in support of orbital operations. During this period a major NASA objective was accomplished: completion of the 180th revolution and 90th day of data gathering with the spacecraft about the planet Mars. Included are presentations of the TDS flight support pass chronology data for each of the Deep Space Stations used, and performance evaluation for the Deep Space Network Telemetry, Tracking, Command, and Monitor Systems. With the loss of Mariner 8 at launch, Mariner 9 assumed the mission plan of Mariner 8, which included the TV mapping cycles and a 12-hr orbital period. The mission plan was modified as a result of a severe dust storm on the surface of Mars, which delayed the start of the TV mapping cycles. Thus, the end of primary mission date was extended to complete the TV mapping cycles.
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A reinterpretation of certain disorders affecting the eye muscles and their tissues
Poonyathalang, Anuchit; Khanna, Sangeeta; Leigh, R John
2007-01-01
Recent discoveries about the orbital tissues prompt a re-evaluation of the way that clinicians think about disorders affecting the extraocular muscles, their nerves and motoneurons in the brainstem. The revolutionary discovery that the orbital layers of the extraocular muscles insert not onto the eyeball, but into fibromuscular pulleys that guide the orbital layers, provides explanations for the kinematic properties of eye rotations and clinical findings in some patients with strabismus. The demonstration that all extraocular fibers types, except pale global fibers, lack synaptic folding provides an explanation for why saccades may remain fast in patients with limited ocular mobility due to myasthenia gravis. More than one mechanism may account for the observation that patients with disorders affecting the eye muscles or their nerves can present with the appearance of central disorders of ocular motility, such as internuclear ophthalmoplegia. New approaches to analyzing saccades in patients with disjunctive eye movements provide the means to identify disorders affecting the peripheral or central components of the ocular motor system, or both. PMID:19668518
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Guidance, navigation, and control study for a solar electric propulsion spacecraft
NASA Technical Reports Server (NTRS)
Kluever, Craig A.
1995-01-01
A preliminary investigation of a lunar-comet rendezvous mission using a solar electric propulsion (SEP) spacecraft was performed in two phases.The first phase involved exploration of the moon and the second involved rendezvous with a comet. The initial phase began with a chemical propulsion translunar injection and chemical insertion into a lunar orbit, followed by a low thrust SEP transfer to a circular, polar, low-lunar orbit. After collecting scientific data at the moon, the SEP spacecraft performed a spiral lunar escape maneuver to begin the interplanetary leg of the mission. After escape from the Earth-moon system, the SEP spacecraft maneuvered in interplanetary space and performed a rendezvous with a comet.The immediate goal of this study was to demonstrate the feasibility of using a low-thrust SEP spacecraft for orbit transfer to both the moon and a comet. Another primary goal was to develop a computer optimization code which would be robust enough to obtain minimum-fuel rendezvous trajectories for a wide range of comets.
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2016-07-04
This is the final view taken by the JunoCam instrument on NASA's Juno spacecraft before Juno's instruments were powered down in preparation for orbit insertion. Juno obtained this color view on June 29, 2016, at a distance of 3.3 million miles (5.3 million kilometers) from Jupiter. The spacecraft is approaching over Jupiter's north pole, providing an unprecedented perspective on the Jupiter system, including its four large moons. http://photojournal.jpl.nasa.gov/catalog/PIA20706
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NASA Astrophysics Data System (ADS)
Houston Jones, J.; Alice Wessen, Manager Of Solar System Eduction; Public Engagement
2010-12-01
NASA's What's Up video podcast supports the Year of the Solar System (YSS) October 2010 - August 2012. During YSS each podcast pairs a popular night sky viewing target (Moon, Comet, Planets, solar system features) with a mission event (launch, flyby, orbit insertion, landing). This product has proven popular with public, formal and informal audiences and will compliment and augment other programming material.
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2018-03-13
Kennedy Space Center scientists worked with OSRAM to insert a smart horticulture lighting system prototype into a food production system. The Phytofy RL prototype LED provides similar wavelength capability to a plant growth system currently on orbit. Photofy RL provides another avenue for future investigators conducting flight experiments to perform ground tests prior to flight under similar lighting conditions. The Phytofy RLs have been used to successfully grow microgreens of Wasabi, Tokyo Bekana, Mizuna, Broccoli, Garnet Giant, and Cauliflower.
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Park, Sung Woo; Choi, Jong Woo; Koh, Kyung S; Oh, Tae Suk
2015-08-01
Reconstruction of traumatic orbital wall defects has evolved to restore the original complex anatomy with the rapidly growing use of computer-aided design and prototyping. This study evaluated a mirror-imaged rapid prototype skull model and a pre-molded synthetic scaffold for traumatic orbital wall reconstruction. A single-center retrospective review was performed of patients who underwent orbital wall reconstruction after trauma from 2012 to 2014. Patients were included by admission through the emergency department after facial trauma or by a tertiary referral for post-traumatic orbital deformity. Three-dimensional (3D) computed tomogram-based mirror-imaged reconstruction images of the orbit and an individually manufactured rapid prototype skull model by a 3D printing technique were obtained for each case. Synthetic scaffolds were anatomically pre-molded using the skull model as guide and inserted at the individual orbital defect. Postoperative complications were assessed and 3D volumetric measurements of the orbital cavity were performed. Paired samples t test was used for statistical analysis. One hundred four patients with immediate orbital defect reconstructions and 23 post-traumatic orbital deformity reconstructions were included in this study. All reconstructions were successful without immediate postoperative complications, although there were 10 cases with mild enophthalmos and 2 cases with persistent diplopia. Reoperations were performed for 2 cases of persistent diplopia and secondary touchup procedures were performed to contour soft tissue in 4 cases. Postoperative volumetric measurement of the orbital cavity showed nonsignificant volume differences between the damaged orbit and the reconstructed orbit (21.35 ± 1.93 vs 20.93 ± 2.07 cm(2); P = .98). This protocol was extended to severe cases in which more than 40% of the orbital frame was lost and combined with extensive soft tissue defects. Traumatic orbital reconstruction can be optimized and successful using an individually manufactured rapid prototype skull model and a pre-molded synthetic scaffold by computer-aid design and manufacturing. Copyright © 2015 American Association of Oral and Maxillofacial Surgeons. Published by Elsevier Inc. All rights reserved.
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A method for the imbibition and germination of wheat seeds in space
NASA Technical Reports Server (NTRS)
Levine, H. G.; Piastuch, W. C.; Sager, J. C. (Principal Investigator)
1999-01-01
A method was developed for the reliable germination in space of wheat seeds on porous tube nutrient delivery systems. Germination paper strips were loosely rolled into cylinders and two seeds inserted close to the outer edges of each cylinder. This configuration: 1) directed the emerging shoots upward and roots downward, 2) was efficient in wicking moisture from the porous tubes, and 3) provided open areas for oxygen diffusion. Cotton tufts were inserted into the bottom crevices of the cylinders to fix the seeds in a mid-level position and cylinders were then storable (indefinitely) prior to the preprogrammed (on-orbit) initiation of imbibition. This method extends both the upper and lower ends of acceptable moisture levels for successful seed germination, increasing the probability of success for spaceflight applications where moisture availability is more variable than on Earth.
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NASA Technical Reports Server (NTRS)
Myrabo, Leik N.; Blandino, John S.; Borkowski, Chris A.; Cross, David P.; Frazier, Scott R.; Hill, Stephen C.; Mitty, Todd J.; Moder, Jeffrey P.; Morales, Ciro; Nyberg, Gregory A.
1987-01-01
The detailed design of a beam-powered transatmospheric vehicle, the Apollo Lightcraft, was selected as the project for the design course. The principal goal is to reduce the LEO payload delivery cost by at least three orders of magnitude below the Space Shuttle Orbiter in the post 2020 era. The completely reusable, single-stage-to-orbit shuttlecraft will take off and land vertically, and have a reentry heat shield integrated with its lower surface. At appropriate points along the launch trajectory, the combined cycle propulsion system will transition through three or four airbreathing modes, and finally use a pure rocket mode for orbital insertion. The objective for the Spring semester propulsion source was to design and perform a detailed theoretical analysis on an advanced combined-cycle engine suitable for the Apollo Lightcraft. The preliminary theoretical analysis of this combined-cycle engine is now completed, and the acceleration performance along representative orbital trajectories was simulated. The total round trip cost is $3430 or $686 per person. This represents a payload delivery cost of $3.11/lb, which is a factor of 1000 below the STS. The Apollo Lightcraft concept is now ready for a more detailed investigation during the Fall semester Transatmosphere Vehicle Design course.
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Capture orbits around asteroids by hitting zero-velocity curves
NASA Astrophysics Data System (ADS)
Wang, Wei; Yang, Hongwei; Zhang, Wei; Ma, Guangfu
2017-12-01
The problem of capturing a spacecraft from a heliocentric orbit into a high parking orbit around binary asteroids is investigated in the current study. To reduce the braking Δ V, a new capture strategy takes advantage of the three-body gravity of the binary asteroid to lower the inertial energy before applying the Δ V. The framework of the circular restricted three-body problem (CR3BP) is employed for the binary asteroid system. The proposed capture strategy is based on the mechanism by which inertial energy can be decreased sharply near zero-velocity curves (ZVCs). The strategy has two steps, namely, hitting the target ZVC and raising the periapsis by a small Δ V at the apoapsis. By hitting the target ZVC, the positive inertial energy decreases and becomes negative. Using a small Δ V, the spacecraft inserts into a bounded orbit around the asteroid. In addition, a rotating mass dipole model is employed for elongated asteroids, which leads to dynamics similar to that of the CR3BP. With this approach, the proposed capture strategy can be applied to elongated asteroids. Numerical simulations validate that the proposed capture strategy is applicable for the binary asteroid 90 Antiope and the elongated asteroid 216 Kleopatra.
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Complementary satellite sound broadcasting systems: A NASA assessment for the Voice of America
NASA Technical Reports Server (NTRS)
Stevens, Grady H.; Spence, Rodney L.
1988-01-01
Satellite concepts are examined which offer potentially significant sound broadcast coverage of audio as a complement to VOA's existing and planned terrestrial sound broadcasting system. HF bands are emphasized but additional discussion is included for systems using higher frequencies. Low altitude satellites, shuttle altitude (275 km) and sun synchronous (about 1600 to 1800 km), would not be practical for international broadcasting since many satellites would be required for reliable and widespread coverage. Two concepts are discussed which would offer significant and practical broadcast coverage at HF. One, an 8-hr posigrade equatorial orbit, would offer about 1 hr of widespread, twice daily, coverage to three areas of the globe. The time of coverage is even greater when confined to densely populated areas only (2 to 3 hrs). Another orbit, the Apogee at Constant Time/Equatorial (ACE), provides the same coverage, but only once daily to each area. The latter orbit is highly elliptical, allowing insertion of a greater payload (more broadcast channels) with the existing launch capability. The ACE and 8-hr orbit concepts led to systems of about equal costs, with the ACE being slightly better.
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USDA-ARS?s Scientific Manuscript database
Mapping of soil moisture is important for many applications such as flood forecasting, soil protection, and crop management. Soil moisture can be estimated at coarse resolutions (>1 km) using satellite remote sensing, but that resolution is poorly suited for many applications. The Equilibrium Mois...
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Communication Channels as Implementation Determinants of Performance Management Framework in Kenya
ERIC Educational Resources Information Center
Sang, Jane
2016-01-01
The purpose of this study to assess communication channels as implementation determinants of performance management framework In Kenya at Moi Teaching and Referral Hospital (MTRH). The communication theory was used to inform the study. This study adopted an explanatory design. The target sampled 510 respondents through simple random and stratified…
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Language, Identity, and Social Divides: Medium of Instruction Debates in Bangladeshi Print Media
ERIC Educational Resources Information Center
Hamid, M. Obaidul; Jahan, Iffat
2015-01-01
This article critically examines the role of language as medium of instruction (MOI) in shaping students' self-perceptions, worldviews, and identities in a globalizing world. We draw on identity and social positioning theories and on Bourdieu's concepts of capital and symbolic struggle to frame our investigation. Using an analytical framework…
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USDA-ARS?s Scientific Manuscript database
For large fields, remote sensing might permit plant low moisture status to be detected early, and this may improve drought detection and monitoring. The objective of this study was to determine whether canopy and soil surface reflectance data derived from a handheld spectroradiometer can detect mois...
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USDA-ARS?s Scientific Manuscript database
The pistachio industry is in need of improved drying technology as the current hot air drying has low energy efficiency and drying rate and high labor cost and also does not produce safe products against microbial contamination. In the current study, dehulled and water- sorted pistachios with a mois...
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Geography Students' Assessment of Internship Experience at a Kenyan University
ERIC Educational Resources Information Center
Simiyu, Robert Romborah; Okaka, Fredrick Okoth; Omondi, Paul
2015-01-01
This paper reports findings of Moi University's geography students' assessment of their internship, which underscore the importance of internship in bridging the gap between theoretical knowledge and its application in the real world of work. Not only were the majority of the students able to apply geographical knowledge and skills in their work…
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None
2017-12-09
Dans une période d'un mois, 2me conférence sur le contrôle d'armes. Le conférencier Drell, américain, parle comme son collègue Worden (AUDIO-1985-005) des problèmes de défense stratégique.
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Koita, Ousmane A; Doumbo, Ogobara K; Ouattara, Amed; Tall, Lalla K; Konaré, Aoua; Diakité, Mahamadou; Diallo, Mouctar; Sagara, Issaka; Masinde, Godfred L; Doumbo, Safiatou N; Dolo, Amagana; Tounkara, Anatole; Traoré, Issa; Krogstad, Donald J
2012-02-01
We identified 480 persons with positive thick smears for asexual Plasmodium falciparum parasites, of whom 454 had positive rapid diagnostic tests (RDTs) for the histidine-rich protein 2 (HRP2) product of the hrp2 gene and 26 had negative tests. Polymerase chain reaction (PCR) amplification for the histidine-rich repeat region of that gene was negative in one-half (10/22) of false-negative specimens available, consistent with spontaneous deletion. False-negative RDTs were found only in persons with asymptomatic infections, and multiplicities of infection (MOIs) were lower in persons with false-negative RDTs (both P < 0.001). These results show that parasites that fail to produce HRP2 can cause patent bloodstream infections and false-negative RDT results. The importance of these observations is likely to increase as malaria control improves, because lower MOIs are associated with false-negative RDTs and false-negative RDTs are more frequent in persons with asymptomatic infections. These findings suggest that the use of HRP2-based RDTs should be reconsidered.
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Grueger, Barbara
2013-01-01
RÉSUMÉ L’allaitement exclusif assure une alimentation optimale aux nourrissons jusqu’à l’âge de six mois. Par la suite, les nourrissons ont besoin d’aliments complémentaires pour répondre à leurs besoins nutritionnels. C’est alors que le sevrage commence. Le sevrage désigne le processus graduel d’introduction d’aliments complémentaires au régime du nourrisson, tout en poursuivant l’allaitement. Il n’y a pas de moment universellement accepté ou scientifiquement démontré pour mettre un terme à l’allaitement. Le moment et le processus de sevrage doivent être adaptés par la mère et l’enfant. Le sevrage peut être soudain ou graduel, prendre plusieurs semaines ou plusieurs mois, être dirigé par l’enfant ou par la mère. Les médecins doivent orienter et soutenir les mères tout au long du processus de sevrage. Le présent document remplace le document de principes sur le sevrage qu’a publié la Société canadienne de pédiatrie en 2004.
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The enhancement of the Transtage for the commercial Titan launch vehicle
NASA Astrophysics Data System (ADS)
Gunter, D.; Gizinski, S.
1987-06-01
The configuration of the Transtage upper stage and its application to the Titan III launch vehicle are examined. The Transtage consists of a control and a propulsion module, and is about 10 feet in diameter and 14.75 feet in length. The elements of the control and propulsion modules and their functions are described. The Transtage/Titan III combination allows for the insertion of a payload into geostationary transfer orbit and eliminates the requirement for a perigee kick motor system. It is observed that the addition of the Transtage upper stage to the Titan III launch vehicle provides a geosynchronous transfer orbit capability of 9500 lbs, flexible mission tailoring, and reliability exceeding 96 percent. Diagrams of the Titan III and the Transtage and its components are provided.
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A Horizontal Take-off and Landing satellite launcher or aerospace plane (HOTOL)
NASA Astrophysics Data System (ADS)
Conchie, P. J.
1985-09-01
An assessment is made of the technology readiness and typical mission profile of a Horizontal Takeoof and Landing (HOTOL) single-stage satellite launch vehicle for 1990s deployment. HOTOL would employ H2-fueled air-breathing propulsion for the first stage of its ascent to low earth orbit through the lower portions of the atmosphere; it would then switch to H2-fueled rocket engines using liquid oxygen from internal tanks for exoatmospheric flight and orbit insertion. Mission cost comparisons are made with alternative launch vehicle design options. HOTOL is approximately the same size as the Concorde SST, and will weigh so much less than the current Space Shuttle as to significantly reduce reentry speeds and temperatures, obviating ceramic insulation systems for the primary structure.
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Apparatus and method of capturing an orbiting spacecraft
NASA Technical Reports Server (NTRS)
Harwell, William D. (Inventor); Gardner, Dale A. (Inventor)
1987-01-01
Apparatus and a method of capturing an orbiting spacecraft by attaching a grapple fixture are discussed. A probe is inserted into an opening, such as a rocket nozzle, in the spacecraft until a stop on the prove mechanism contacts the spacecraft. A lever is actuated releasing a spring loaded rod which moves axially along the probe removing a covering sleeve to expose spring loaded toffle fingers which pivot open engaging the side of the opening. The probe is shortened and tensioned by turning a screw thread, pressing the fingers inside of the opening to compress the spacecraft between the toggle fingers and the stop. A grapple fixture attached to the probe, which is thus secured to the spacecraft, is engaged by appropriate retrieval means such as a remote manipulator arm.
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Studying the energy variation in the powered Swing-By in the Sun-Mercury system
NASA Astrophysics Data System (ADS)
Ferreira, A. F. S.; Prado, A. F. B. A.; Winter, O. C.; Santos, D. P. S.
2017-10-01
A maneuver where a spacecraft passes close to Mercury and uses the gravity of this body combined with an impulse applied at the periapsis, with different magnitudes and directions, is presented. The main objective of this maneuver is the fuel economy in space missions. Using this maneuver, it is possible to insert the spacecraft into an orbit captured around the Sun or Mercury. Trajectories escaping the Solar System are also obtained and mapped. Maps of the spacecraft energy variation relative to the Sun and the types of orbits resulting from the maneuver are presented, based in numerical integrations. The results show that applying the impulse out of the direction of motion can optimize the maneuver due to the effect of the combination of the impulse and the gravity.
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Mechanical features of the shuttle rotating service structure
NASA Technical Reports Server (NTRS)
Crump, J. M.
1985-01-01
With the development of the space shuttle launching facilities, it became mandatory to develop a shuttle rotating service structure to provide for the insertion and/or removal of payloads at the launch pads. The rotating service structure is a welded tubular steel space frame 189 feet high, 65 feet wide, and weighing 2100 tons. At the pivot column the structure is supported on a 30 inch diameter hemispherical bearing. At the opposite terminus the structure is supported on two truck assemblies each having eight 36 inch diameter double flanged wheels. The following features of the rotating service structure are discussed: (1) thermal expansion and contraction; (2) hurricane tie downs; (3) payload changeout room; (4) payload ground handling mechanism; (5) payload and orbiter access platforms; and (6) orbiter cargo bay access.
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Lunar Reconnaissance Orbiter (LRO) Rapid Thermal Design Development
NASA Technical Reports Server (NTRS)
Baker, Charles; Cottingham, Christine; Garrison, Matthew; Melak, Tony; Peabody, Sharon; Powers, Dan
2009-01-01
The Lunar Reconnaissance Orbiter (LRO) project had a rapid development schedule starting with project conception in spring of 2004, instrument and launch vehicle selection late in 2005 and then launch in early 2009. The lunar thermal environment is one of the harshest in our solar system with the heavy infrared loading of the moon due to low albedo, lack of lunar atmosphere, and low effective regolith conduction. This set of constraints required a thermal design which maximized performance (minimized radiator area and cold control heater power) and minimized thermal hardware build at the orbiter level (blanketing, and heater service). The orbiter design located most of the avionics on an isothermalized heat pipe panel called the IsoThermal Panel (ITP). The ITP was coupled by dual bore heat pipes to an Optical Solar Reflector (OSR) covered heat pipe radiator. By coupling all of the avionics to one system, the hardware was simplified. The seven instruments were mainly heritage instruments which resulted in their desired radiators being located by their heritage design. This minimized instrument redesigns and therefore allowed them to be delivered earlier, though it resulted in a more complex orbiter level blanket and heater service design. Three of the instruments were mounted on a tight pointing M55J optical bench that needed to be covered in heaters to maintain pointing. Two were mounted to spacecraft controlled radiators. One was mounted to the ITP Dual Bores. The last was mounted directly to the bus structure on the moon facing panel. The propulsion system utilized four-20 pound insertion thrusters and eight-5 pound attitude control thrusters (ACS) in addition to 1000 kg of fuel in two large tanks. The propulsion system had a heater cylinder and a heated mounting deck for the insertion thrusters which coupled most of the propulsion design together simplifying the heater design. The High Gain Antenna System (HGAS) and Solar Array System (SAS) used dual axis actuator gimbal systems. HGAS required additional boom heaters to cool the approximately 10 W of RF losses thru the rotary joints and wave guides from the 40 W Ka system. By design this module needed a fair amount of heater, blanketing, and radiator complexity. The SAS system required a separate cable wrap radiator to help cool the Solar Array harness which dissipated 30 W thru the actuators and cable wraps. This module also was complex.
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Boundary Layer Transition Protuberance Tests at NASA JSC Arc-Jet Facility
NASA Technical Reports Server (NTRS)
Larin, M. E.; Marichalar, J. J.; Kinder, G. R.; Campbell, C. H.; Riccio, J. R.; Nquyen, T. Q.; DelPapa, S. V.; Pulsonetti, M. V.
2009-01-01
A series of arc-jet tests in support of the Shuttle Orbiter Boundary Layer Transition flight experiment was conducted in the Channel Nozzle of the NASA Johnson Space Center Atmospheric Reentry Materials and Structures Facility. The boundary layer trip was a protrusion of a certain height and geometry fabricated as part of a 6"x6" tile insert, a special test article made of the Boeing Rigid Insulation tile material and coated with the Reaction Cured Glass used for the bottom fuselage tiles of the Space Shuttle Orbiter. A total of five such tile inserts were manufactured: four with the 0.25-in. trip height, and one with the 0.35-in. trip height. The tile inserts were interchangeably installed in the center of the 24"x24" variable configuration tile array mounted in the 24"x24" test section of the channel nozzle. The objectives of the test series were to demonstrate that the boundary layer trip can safely withstand the Space Shuttle Orbiter flight-like re-entry environments and provide temperature data on the protrusion surface, surfaces of the nearby tiles upstream and downstream of the trip, as well as the bond line between the tiles and the structure. The targeted test environments were defined for the tip of the protrusion, away from the nominal surface of the tile array. The arc jet test conditions were approximated in order to produce the levels of the free stream total enthalpy at the protrusion height similar to those expected in flight. The test articles were instrumented with surface, sidewall and bond line thermocouples. Additionally, Tempilaq temperature-indicating paint was applied to the nominal tiles of the tile array in locations not interfering with the protrusion trip. Five different grades of paint were used that disintegrate at different temperatures between 1500 and 2000 deg F. The intent of using the paint was to gauge the RCG-coated tile surface temperature, as well as determine its usefulness for a flight experiment. This paper provides an overview of the channel nozzle arc jet, test articles and test conditions, as well as the results of the arc-jet tests including the measured temperature response of the test articles, their pre- and post-test surface scans, condition of the thermal paint, and continents on the protrusion tip heating achieved in tests compared to the computational fluid dynamics predictions.
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Apollo-Lunar Orbital Rendezvous Technique
NASA Technical Reports Server (NTRS)
1963-01-01
The film shows artists rendition of the spacecrafts, boosters, and flight of the Apollo lunar missions. The Apollo spacecraft will consist of three modules: the manned Command Module; the Service Module, which contains propulsion systems; and the Lunar Excursion Module (LEM) to carry astronauts to the moon and back to the Command and Service Modules. The spacecraft will be launched via a three-stage Saturn booster. The first stage will provide 7.5 million pounds of thrust from five F-1 engines for liftoff and initial powered flight. The second stage will develop 1 million pounds of thrust from five J-2 engines to boost the spacecraft almost into Earth orbit. Immediately after ignition of the second stage, the Launch Escape System will be jettisoned. A single J-2 engine in the S4B stage will provide 200,000 pounds of thrust to place the spacecraft in an earth parking orbit. It also will be used to propel the spacecraft into a translunar trajectory, then it will separate from the Apollo Modules. Onboard propulsion systems will be used to insert the spacecraft into lunar orbit. Two astronauts will enter the LEM, which will separate from the command and service modules. The LEM will go into elliptical orbit and prepare for landing. The LEM will lift off of the Moon's surface to return to the Command and Service Modules, and most likely be left in lunar orbit. After leaving the Moon's orbit, and shortly before entering Earth's orbit, the Service Module will be ejected. The Command Module will be oriented for reentry into the Earth's atmosphere. A drogue parachute will deploy at approximately 50,000 feet, followed by the main parachute system for touchdown.
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Physical properties of the human head: mass, center of gravity and moment of inertia.
Yoganandan, Narayan; Pintar, Frank A; Zhang, Jiangyue; Baisden, Jamie L
2009-06-19
This paper presents a synthesis of biomedical investigations of the human head with specific reference to certain aspects of physical properties and development of anthropometry data, leading to the advancement of dummies used in crashworthiness research. As a significant majority of the studies have been summarized as reports, an effort has been made to chronologically review the literature with the above objectives. The first part is devoted to early studies wherein the mass, center of gravity (CG), and moment of inertia (MOI) properties are obtained from human cadaver experiments. Unembalmed and preserved whole-body and isolated head and head-neck experiments are discussed. Acknowledging that the current version of the Hybrid III dummy is the most widely used anthropomorphic test device in motor vehicle crashworthiness research for frontal impact applications for over 30 years, bases for the mass and MOI-related data used in the dummy are discussed. Since the development and federalization of the dummy in the United States, description of methods used to arrive at these properties form a part of the manuscript. Studies subsequent to the development of this dummy including those from the US Military are also discussed. As the head and neck are coupled in any impact, and increasing improvements in technology such as advanced airbags, and pre-tensioners and load limiters in manual seatbelts affect the kinetics of the head-neck complex, the manuscript underscores the need to pursue studies to precisely determine all the physical properties of the head. Because the most critical parameters (locations of CG and occipital condyles (OC), mass, and MOI) have not been determined on a specimen-by-specimen basis in any single study, it is important to gather these data in future experiments. These critical data will be of value for improving occupant safety, designing advanced restraint systems, developing second generation dummies, and assessing the injury mitigating characteristics of modern vehicle components in all impact modalities.
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Waswa, J
2011-06-01
Issues related to dietary patterns and body image concerns have been among western cultures. It would therefore be inappropriate to use these findings as a basis of intervention in developing countries because this is an emerging issue in developing countries. Although this situation may be in Kenya, there is no data to quantify it and thus the need for research in this area. The main objective of this study was to investigate the perceived body image of Moi University undergraduate female students and its influence on their nutrient intake and nutritional health. Cross sectional Survey was done on 260 female students of Moi University aged 20-25. Stratified followed by systematic sampling was used to get the sample. Questionnaires were used to collect data. Measurements of weight, height and mid-upper arm circumference were taken by the researcher using standardized procedures and equipments. SPSS was used for data analysis. Descriptive statistics were used to summarize data. Chi square tests, t- tests and logistic regression were further done. It was found that most of the respondents with positive (69%) and negative (75%) body image were not comfortable with overweight. The mean BMI was 21.73 +/- 3.03 kg/m2 and MUAC was 26.55 +/- 3.15 cm. Prevalence of underweight and overweight based on BMI was 46% and 9% respectively. Mean intakes of energy, protein, vitamin A and iron were, 1245.92 kcals/day, 36.99g/day, 368.29 RE/day and 12.6g/day respectively. Factors associated with adequacy of nutrient intake were knowledge on food choice and irregular meal patterns. There is need for nutritional counseling and education among university students to address the issue of body image vis a viz food intake since most students skipped meals and this together with knowledge on food choice were found to significantly predict nutrient intake and body image perceptions.
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PARENT, Sophie; MONTÉSINOS-GELET, Isabelle; SÉGUIN, Jean R.; ZELAZO, Philip David; TREMBLAY, Richard E.
2017-01-01
RÉSUMÉ Les études antérieures montrent que les facteurs langagiers et cognitifs chez le jeune enfant ne suffisent pas pour expliquer les différences individuelles dans l’acquisition des compétences relatives à la langue écrite (Sénéchal et LeFevre, 2002). S’inspirant de l’éthologie et de la sociologie, Pellegrini (2001) propose que l’exposition à une plus grande variété d’interlocuteurs et de contextes sociaux pour l’exercice des compétences liées à l’écrit favorise l’acquisition du langage littéraire et des compétences en lecture/écriture. La présente étude a pour but de vérifier cette contribution de la variété des opportunités sociales reliées à l’écrit à l’acquisition des compétences émergentes en littéracie à 5 ans. Cette contribution est examinée de concert avec les ressources financières familiales, l’éducation parentale, la fréquence des activités mère-enfant de lecture/écriture et les compétences verbales et mnémoniques de l’enfant. Les résultats confirment partiellement l’hypothèse de Pellegrini et appuient la pertinence de considérer plusieurs dimensions des expériences sociales préscolaires. La contribution unique de la diversité des activités littéraires de l’enfant à 48 mois s’avère de taille similaire à celle du vocabulaire réceptif évalué à 42 mois et de la mémoire à court terme à 42 mois. La diversité des interlocuteurs n’ajoute toutefois pas au modèle. PMID:28566801
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Multiplicity of Infection and Disease Severity in Plasmodium vivax
Pacheco, M. Andreína; Lopez-Perez, Mary; Vallejo, Andrés F.; Herrera, Sócrates; Arévalo-Herrera, Myriam; Escalante, Ananias A.
2016-01-01
Background Multiplicity of infection (MOI) refers to the average number of distinct parasite genotypes concurrently infecting a patient. Although several studies have reported on MOI and the frequency of multiclonal infections in Plasmodium falciparum, there is limited data on Plasmodium vivax. Here, MOI and the frequency of multiclonal infections were studied in areas from South America where P. vivax and P. falciparum can be compared. Methodology/Principal Findings As part of a passive surveillance study, 1,328 positive malaria patients were recruited between 2011 and 2013 in low transmission areas from Colombia. Of those, there were only 38 P. vivax and 24 P. falciparum clinically complicated cases scattered throughout the time of the study. Samples from uncomplicated cases were matched in time and location with the complicated cases in order to compare the circulating genotypes for these two categories. A total of 92 P. vivax and 57 P. falciparum uncomplicated cases were randomly subsampled. All samples were genotyped by using neutral microsatellites. Plasmodium vivax showed more multiclonal infections (47.7%) than P. falciparum (14.8%). Population genetics and haplotype network analyses did not detect differences in the circulating genotypes between complicated and uncomplicated cases in each parasite. However, a Fisher exact test yielded a significant association between having multiclonal P. vivax infections and complicated malaria. No association was found for P. falciparum infections. Conclusion The association between multiclonal infections and disease severity in P. vivax is consistent with previous observations made in rodent malaria. The contrasting pattern between P. vivax and P. falciparum could be explained, at least in part, by the fact that P. vivax infections have lineages that were more distantly related among them than in the case of the P. falciparum multiclonal infections. Future research should address the possible role that acquired immunity and exposure may have on multiclonal infections and their association with disease severity. PMID:26751811
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Koy, Tshingani; Mukumbi, Henri; Malandala, Ghislain Lubangi Muteba; Donnen, Philippe; Wilmet–Dramaix, Michèle
2014-01-01
Introduction A trithérapie (ARV) introduite en R.D.Congo en 1996, a permis l′amélioration substantielle de la qualité de vie des PVVIH et a réduit la morbimortalité liée au sida en R.D. Congo. L'objectif de cette étude est de présenter le profil épidémiologique comparatif, clinique, ainsi que l’évolution anthropométrique des PVVIH sous ARV à Kinshasa. Méthodes Etude de cohorte sur 438 PVVIH, de 18 ans et plus, suivies entre mai 2010 à 2011 à Amo Congo à Kinshasa. Une comparaison a été faite entre les patients suivis pendant un an et ceux perdus de vue. Le Chi carré de Mc Nemar et l'analyse de variance pour mesures répétées ont été appliqués pour étudier l’évolution. Résultats Près 12 mois de suivi, 11,4% de patients ont été perdus de vue. Parmi eux, on observait des proportions significativement plus élevées de personnes de niveau socioéconomique bas, d'indice de masse corporelle (IMC) bas, présentant de l'anorexie, des affections opportunistes. Les proportions de patients aux stades OMS 3 & 4 et naïfs étaient également significativement plus élevées et la durée sous ARV plus courte. Les gains moyens des paramètres anthropométriques au 12ème mois, étaient importants: de 3,6 [3,2 - 4,0] kg pour le poids, 1,8 (1,4 - 2,3) cm pour le périmètre abdominal, 0,9 (0,8 - 1,2) cm pour le périmètre brachial, 1,4 (1,2 - 1,5) kg/m2 pour l'IMC. La proportion de patients avec un IMC <18,5 kg/m2 a significativement plus baissé entre l'admission et le 12ème mois parmi les patients sans stomatite que parmi ceux avec stomatite. L'IMC moyen évoluait significativement différemment entre l'admission et le 12ème mois selon l’âge et la taille de ménage. Conclusion Les facteurs fragilisant la rétention des patients sous antirétroviraux et une évolution progressive de l’état nutritionnel ont été observés. PMID:25995784
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NASA Astrophysics Data System (ADS)
Uehara, M.; Gattacceca, J.; van der Beek, C. J.; Leroux, H.; Jacob, D.
2010-12-01
We present results of an integrated study of metallic grains in meteorites, combining magneto-optical imaging (MOI), petrography, FE-SEM, TEM, and microprobe analyses. Indeed, metallic Fe-Ni grains in meteorites have inner structures due to Ni diffusion during slow cooling subsequent to metamorphism on their parent body. Previous magnetic studies suggested that tetrataenite (ordered FeNi) is the stable magnetic carriers in these meteorites. On the other hand, mineralogical studies showed that tetrataenite is intimately mixed with other Fe-Ni phases (kamacite and taenite, that contain less than 10 wt.% and around 30 wt.% Ni, respectively), and forms complex microstructures (see below). However, due to the typical spatial resolution of classical bulk magnetic measurements (~1 mm), it has been so far difficult to isolate the contribution of these different Fe-Ni minerals. The MOI technique measures the magnetic flux threading a magneto-optically active film directly placed on the sample. This film rotates the polarization direction of transmitted light (Faraday rotation). Through the analyzer of a reflected light microscope, the vertical component of surface magnetic field of the sample is observed with a spatial resolution of a few µm, which allows direct comparison between mineralogical and magnetic microstructures of metal grains. We studied Agen (H5) and Ausson (L5) ordinary chondrites. Optical and electron microscopies showed two types of micron- to submicron-scaled tetrataenite-bearing microstructures: (1) Zoned taenite particles that consist of a taenite core, surrounded by a "cloudy zone" (20-150 nm large tetrataenite granules embedded in taenite matrix), and a 1-10 µm thick tetrataenite rim. (2) Zoneless plessite particles that consist of < 10 µm large tetrataenite grains embedded in a kamacite matrix. MOI of saturation remanence showed that only the nm-sized tetrataenite granules in cloudy zone carry very strong remanence. Micron-scale mapping of coercivity of remanence (Bcr), by means of DC demagnetization coupled with MOI, combined with FE-SEM and TEM study showed that this cloudy zone has zoning in Ni composition, tetrataenite grain size, and Bcr. The center part has finer tetrataenite (20 nm), lower bulk Ni composition (30 wt.%) and higher Bcr values (up to 1 T) than the outer part (150 nm, 55 wt.%, and 400 mT respectively). Therefore, tetrataenite in the cloudy zone is a potential very stable carrier of extraterrestrial remanence. Moreover, magnetically soft minerals (e.g. kamacite) are occasionally inversely magnetized by stray fields from adjacent cloudy zone. This implies that bulk measurements of FeNi-bearing meteorites may be misleading because of microscopic-scale interactions between magnetically hard tetrataenite and other soft minerals.
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Spacecraft-to-Earth Communications for Juno and Mars Science Laboratory Critical Events
NASA Technical Reports Server (NTRS)
Soriano, Melissa; Finley, Susan; Jongeling, Andre; Fort, David; Goodhart, Charles; Rogstad, David; Navarro, Robert
2012-01-01
Deep Space communications typically utilize closed loop receivers and Binary Phase Shift Keying (BPSK) or Quadrature Phase Shift Keying (QPSK). Critical spacecraft events include orbit insertion and entry, descent, and landing.---Low gain antennas--> low signal -to-noise-ratio.---High dynamics such as parachute deployment or spin --> Doppler shift. During critical events, open loop receivers and Multiple Frequency Shift Keying (MFSK) used. Entry, Descent, Landing (EDL) Data Analysis (EDA) system detects tones in real-time.
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Viking 75 project: Viking lander system primary mission performance report
NASA Technical Reports Server (NTRS)
Cooley, C. G.
1977-01-01
Viking Lander hardware performance during launch, interplanetary cruise, Mars orbit insertion, preseparation, separation through landing, and the primary landed mission, with primary emphasis on Lander engineering and science hardware operations, the as-flown mission are described with respect to Lander system performance and anomalies during the various mission phases. The extended mission and predicted Lander performance is discussed along with a summary of Viking goals, mission plans, and description of the Lander, and its subsystem definitions.
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The United States Air Force Small Business Innovation Research Program
1990-01-01
impossible to draw, and very - satellite’s mass consists of the exists in the metal iridium , which difficult to machine. They also 0 propellant...needed for orbit is ductile and pore free. Iridium tend to be expensive, so that insertion and altitude control, bonds to, but does not react with, cutting...thin layers lifespan is 2400F and 10 hours coatings of iridium , but this track of exotic materials with precisely respectively, record was reversed in
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Huang, Hao; Milione, Giovanni; Lavery, Martin P. J.; Xie, Guodong; Ren, Yongxiong; Cao, Yinwen; Ahmed, Nisar; An Nguyen, Thien; Nolan, Daniel A.; Li, Ming-Jun; Tur, Moshe; Alfano, Robert R.; Willner, Alan E.
2015-01-01
Mode division multiplexing (MDM)– using a multimode optical fiber’s N spatial modes as data channels to transmit N independent data streams – has received interest as it can potentially increase optical fiber data transmission capacity N-times with respect to single mode optical fibers. Two challenges of MDM are (1) designing mode (de)multiplexers with high mode selectivity (2) designing mode (de)multiplexers without cascaded beam splitting’s 1/N insertion loss. One spatial mode basis that has received interest is that of orbital angular momentum (OAM) modes. In this paper, using a device referred to as an OAM mode sorter, we show that OAM modes can be (de)multiplexed over a multimode optical fiber with higher than −15 dB mode selectivity and without cascaded beam splitting’s 1/N insertion loss. As a proof of concept, the OAM modes of the LP11 mode group (OAM−1,0 and OAM+1,0), each carrying 20-Gbit/s polarization division multiplexed and quadrature phase shift keyed data streams, are transmitted 5km over a graded-index, few-mode optical fibre. Channel crosstalk is mitigated using 4 × 4 multiple-input-multiple-output digital-signal-processing with <1.5 dB power penalties at a bit-error-rate of 2 × 10−3. PMID:26450398
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Huang, Hao; Milione, Giovanni; Lavery, Martin P J; Xie, Guodong; Ren, Yongxiong; Cao, Yinwen; Ahmed, Nisar; An Nguyen, Thien; Nolan, Daniel A; Li, Ming-Jun; Tur, Moshe; Alfano, Robert R; Willner, Alan E
2015-10-09
Mode division multiplexing (MDM)- using a multimode optical fiber's N spatial modes as data channels to transmit N independent data streams - has received interest as it can potentially increase optical fiber data transmission capacity N-times with respect to single mode optical fibers. Two challenges of MDM are (1) designing mode (de)multiplexers with high mode selectivity (2) designing mode (de)multiplexers without cascaded beam splitting's 1/N insertion loss. One spatial mode basis that has received interest is that of orbital angular momentum (OAM) modes. In this paper, using a device referred to as an OAM mode sorter, we show that OAM modes can be (de)multiplexed over a multimode optical fiber with higher than -15 dB mode selectivity and without cascaded beam splitting's 1/N insertion loss. As a proof of concept, the OAM modes of the LP11 mode group (OAM-1,0 and OAM+1,0), each carrying 20-Gbit/s polarization division multiplexed and quadrature phase shift keyed data streams, are transmitted 5km over a graded-index, few-mode optical fibre. Channel crosstalk is mitigated using 4 × 4 multiple-input-multiple-output digital-signal-processing with <1.5 dB power penalties at a bit-error-rate of 2 × 10(-3).
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Kim, K S; Hwang, Y W; Won, T Y
2013-12-01
This paper reports the results of a numerical study on carrier injection and exciton transport in an organic light emitting diode (OLED) structure based on tris (8-hydroxyquinolinato) aluminum (Alq3). Because charge accumulation at the interfaces between the emission layer (EML) and transport layer are believed to increase the recombination rate, which also increases the exciton density, a numerical study was performed on the effect of inserting an EML in the bilayer structure. In the first case considered, the lowest unoccupied molecular orbital (LUMO) of the EML was aligned with the LUMO of the hole transport layer (HTL), whereas the highest occupied molecular orbital (HOMO) of the EML was aligned with the HOMO of the electron transport layer (ETL). In the second case, the LUMO of the EML was aligned with the LUMO of the ETL and the HOMO of the EML was aligned with the HOMO of the HTL. In case of a charge-blocking device, most of the recombination appeared to occur at both edges of the EML because the electric field exhibited a peak in these areas. On the other hand, in the case of the charge-confining device, the electric field was confined at the interface between the EML and ETL. This paper also discussed the effect of the insertion of a doping layer as transport layer.
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NASA Astrophysics Data System (ADS)
Huang, Hao; Milione, Giovanni; Lavery, Martin P. J.; Xie, Guodong; Ren, Yongxiong; Cao, Yinwen; Ahmed, Nisar; An Nguyen, Thien; Nolan, Daniel A.; Li, Ming-Jun; Tur, Moshe; Alfano, Robert R.; Willner, Alan E.
2015-10-01
Mode division multiplexing (MDM)- using a multimode optical fiber’s N spatial modes as data channels to transmit N independent data streams - has received interest as it can potentially increase optical fiber data transmission capacity N-times with respect to single mode optical fibers. Two challenges of MDM are (1) designing mode (de)multiplexers with high mode selectivity (2) designing mode (de)multiplexers without cascaded beam splitting’s 1/N insertion loss. One spatial mode basis that has received interest is that of orbital angular momentum (OAM) modes. In this paper, using a device referred to as an OAM mode sorter, we show that OAM modes can be (de)multiplexed over a multimode optical fiber with higher than -15 dB mode selectivity and without cascaded beam splitting’s 1/N insertion loss. As a proof of concept, the OAM modes of the LP11 mode group (OAM-1,0 and OAM+1,0), each carrying 20-Gbit/s polarization division multiplexed and quadrature phase shift keyed data streams, are transmitted 5km over a graded-index, few-mode optical fibre. Channel crosstalk is mitigated using 4 × 4 multiple-input-multiple-output digital-signal-processing with <1.5 dB power penalties at a bit-error-rate of 2 × 10-3.
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Aeroshell Design Techniques for Aerocapture Entry Vehicles
NASA Technical Reports Server (NTRS)
Dyke, R. Eric; Hrinda, Glenn A.
2004-01-01
A major goal of NASA s In-Space Propulsion Program is to shorten trip times for scientific planetary missions. To meet this challenge arrival speeds will increase, requiring significant braking for orbit insertion, and thus increased deceleration propellant mass that may exceed launch lift capabilities. A technology called aerocapture has been developed to expand the mission potential of exploratory probes destined for planets with suitable atmospheres. Aerocapture inserts a probe into planetary orbit via a single pass through the atmosphere using the probe s aeroshell drag to reduce velocity. The benefit of an aerocapture maneuver is a large reduction in propellant mass that may result in smaller, less costly missions and reduced mission cruise times. The methodology used to design rigid aerocapture aeroshells will be presented with an emphasis on a new systems tool under development. Current methods for fast, efficient evaluations of structural systems for exploratory vehicles to planets and moons within our solar system have been under development within NASA having limited success. Many systems tools that have been attempted applied structural mass estimation techniques based on historical data and curve fitting techniques that are difficult and cumbersome to apply to new vehicle concepts and missions. The resulting vehicle aeroshell mass may be incorrectly estimated or have high margins included to account for uncertainty. This new tool will reduce the guesswork previously found in conceptual aeroshell mass estimations.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Wu, Di; Department of Optical Science and Engineering, Key Laboratory of Micro and Nano Photonic Structures; Yu, Guoqiang, E-mail: guoqiangyu@ucla.edu
2016-05-23
We study spin-orbit-torque (SOT)-driven magnetization switching in perpendicularly magnetized Ta/Mo/Co{sub 40}Fe{sub 40}B{sub 20} (CoFeB)/MgO films. The thermal tolerance of the perpendicular magnetic anisotropy (PMA) is enhanced, and the films sustain the PMA at annealing temperatures of up to 430 °C, due to the ultra-thin Mo layer inserted between the Ta and CoFeB layers. More importantly, the Mo insertion layer also allows for the transmission of the spin current generated in the Ta layer due to spin Hall effect, which generates a damping-like SOT and is able to switch the perpendicular magnetization. When the Ta layer is replaced by a Pt layer,more » i.e., in a Pt/Mo/CoFeB/MgO multilayer, the direction of the SOT-induced damping-like effective field becomes opposite because of the opposite sign of spin Hall angle in Pt, which indicates that the SOT-driven switching is dominated by the spin current generated in the Ta or Pt layer rather than the Mo layer. Quantitative characterization through harmonic measurements reveals that the large SOT effective field is preserved for high annealing temperatures. This work provides a route to applying SOT in devices requiring high temperature processing steps during the back-end-of-line processes.« less
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Effect of inserting a hole injection layer in organic light-emitting diodes: A numerical approach
NASA Astrophysics Data System (ADS)
Lee, Hyeongi; Hwang, Youngwook; Won, Taeyoung
2015-01-01
For investigating the effect of inserting a hole injection layer (HIL), we carried out a computational study concerning organic light-emitting diodes (OLEDs) that had a thin CuPc layer as the hole injection layer. We used S-TAD (2, 2', 7, 7'-tetrakis-(N, Ndiphenylamino)-9, 9-spirobifluoren) for the hole transfer layer, S-DPVBi (4, 4'-bis (2, 2'-diphenylvinyl)-1, 1'-spirobiphenyl) for the emission layer and Alq3 (Tris (8-hyroxyquinolinato) aluminium) for the electron transfer layer. This tri-layer device was compared with four-layer devices. To this tri-layer device, we added a thin CuPc layer, which had a 5.3 eV highest occupied molecular orbital (HOMO) level and a 3.8 eV lowest unoccupied molecular orbital (LUMO) level, as a hole injection layer, and we chose this device for Device A. Also, we varied the LUMO level or the HOMO level of the thin CuPc layer. These two devices were identified as Device C and Device D, respectively. In this paper, we simulated the carrier injection, transport and recombination in these four devices. Thereby, we showed the effect of the HIL, and we demonstrated that the characteristics of these devices were improved by adding a thin layer of CuPc between the anode and the HTL.
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The ram accelerator - A chemically driven mass launcher
NASA Technical Reports Server (NTRS)
Kaloupis, P.; Bruckner, A. P.
1988-01-01
The ram accelerator, a chemically propelled mass driver, is presented as a viable new approach for directly launching acceleration-insensitive payloads into low earth orbit. The propulsion principle is similar to that of a conventional air-breathing ramjet. The cargo vehicle resembles the center-body of a ramjet and travels through a tube filled with a pre-mixed fuel and oxidizer mixture. The launch tube acts as the outer cowling of the ramjet and the combustion process travels with the vehicle. Two drive modes of the ram accelerator propulsion system are described, which when used in sequence are capable of accelerating the vehicle to as high as 10 km/sec. The requirements are examined for placing a 2000 kg vehicle into a 500 km orbit with a minimum of on-board rocket propellant for circularization maneuvers. It is shown that aerodynamic heating during atmospheric transit results in very little ablation of the nose. An indirect orbital insertion scenario is selected, utilizing a three step maneuver consisting of two burns and aerobraking. An on-board propulsion system using storable liquid propellants is chosen in order to minimize propellant mass requirements, and the use of a parking orbit below the desired final orbit is suggested as a means to increase the flexibility of the mass launch concept. A vehicle design using composite materials is proposed that will best meet the structural requirements, and a preliminary launch tube design is presented.
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Developing Communication Skills: General Considerations and Specific Techniques.
ERIC Educational Resources Information Center
Joiner, Elizabeth Garner; Westphal, Patricia Barney, Ed.
This practical book is designed for the classroom teacher of a second or foreign language at any level. The articles are grouped into two distinct but interdependent sections on general considerations and specific techniques. The contents of the first section are as follows: "Moi Tarzan, Vous Jane?: A Study of Communicative Competence" by P.B.…
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USDA-ARS?s Scientific Manuscript database
Egg masses of an aquatic snail, Biomphalaria glabrata, matured, and juveniles subsequently eclosed and were mobile in a stable water film of transitory habitats simulated by two different simple test devices described here. The viability of eggs maintained in an unstable film due to low ambient mois...
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Perceptions of Female High School Students on Engineering
ERIC Educational Resources Information Center
Madara, Diana Starovoytova; Namango, Sitati
2016-01-01
There is overwhelming evidence that females are underrepresented in engineering worldwide, and Kenya is not an exception. Recent study at School of Engineering (SOE), Moi University (MU) established that engineering parity ration was found to be 1.68 %, meaning that for every 59 students admitted to MU there was only one student admitted to SOE.…
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USDA-ARS?s Scientific Manuscript database
Dairy slurry is used commonly as an animal-sourced fertilizer in agronomic production. However, residual effects of slurry application on intake and digestibility of alfalfa (Medicago sativa L.) silage from subsequent harvests are not well known. The objective of this study was to determine if mois...
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Policy without a Plan: English as a Medium of Instruction in Rwanda
ERIC Educational Resources Information Center
Pearson, Pamela
2014-01-01
From the time of Belgian colonial rule, French was predominantly the medium of instruction (MOI) in Rwanda. Then, in October 2008, a Rwandan Cabinet resolution called for the immediate implementation of English as the language of instruction in all public schools at all levels--from primary to tertiary. This study reports on ethnographic interview…
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Dissipationless conductance in a topological coaxial cable
NASA Astrophysics Data System (ADS)
Schuster, Thomas; Iadecola, Thomas; Chamon, Claudio; Jackiw, Roman; Pi, So-Young
2016-09-01
We present a dynamical mechanism leading to dissipationless conductance, whose quantized value is controllable in a (3+1)-dimensional electronic system. The mechanism is exemplified by a theory of Weyl fermions coupled to a Higgs field, also known as an axion insulator. We show that the insertion of an axial gauge flux can induce vortex lines in the Higgs field, similar to the development of vortices in a superconductor upon the insertion of magnetic flux. We further show that the necessary axial gauge flux can be generated using Rashba spin-orbit coupling or a magnetic field. Vortex lines in the Higgs field are known to bind chiral fermionic modes, each of which serves as a one-way channel for electric charge with conductance e2/h . Combining these elements, we present a physical picture, the "topological coaxial cable," illustrating how the value of the quantized conductance could be controlled in such an axion insulator.
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ACTS Operational Performance Review: September 1995
NASA Technical Reports Server (NTRS)
Krawczyk, Richard J.
1996-01-01
The Advanced Communications Technology Satellite (ACTS) utilized a proven spacecraft bus with a payload that qualified new technologies to provide a wide range of on-orbit demonstrations. A comprehensive development, qualification and ground test program was implemented to reduce technology risks. Since launch in September, 1993, and insertion into its geostationary slot ACTS has accumulated over 16,000 hours of successful operation. This paper briefly reviews the technology development background then provides a summary of the operational performance observed for the spacecraft bus and communication payload subsystems and units.
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2009-07-23
CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla. , technicians monitor the STSS Demonstrator SV-1 spacecraft as it is lowered to the orbital insertion system. The spacecraft is a midcourse tracking technology demonstrator, part of an evolving ballistic missile defense system. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. It will be launched by NASA for the Missile Defense Agency in late summer. Photo credit: NASA/Tim Jacobs (Approved for Public Release 09-MDA-4800 [30 July 09] )
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2009-07-23
CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla. , the STSS Demonstrator SV-1 spacecraft is lowered toward the orbital insertion system. The spacecraft is a midcourse tracking technology demonstrator, part of an evolving ballistic missile defense system. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. It will be launched by NASA for the Missile Defense Agency in late summer. Photo credit: NASA/Tim Jacobs (Approved for Public Release 09-MDA-4800 [30 July 09] )
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2009-07-23
CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla. , technicians monitor the STSS Demonstrator SV-1 spacecraft as it is lowered to the orbital insertion system. The spacecraft is a midcourse tracking technology demonstrator, part of an evolving ballistic missile defense system. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. It will be launched by NASA for the Missile Defense Agency in late summer. Photo credit: NASA/Tim Jacobs (Approved for Public Release 09-MDA-4800 [30 July 09] )
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2009-07-23
CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla. , the STSS Demonstrator SV-1 spacecraft is lowered to the orbital insertion system. The spacecraft is a midcourse tracking technology demonstrator, part of an evolving ballistic missile defense system. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. It will be launched by NASA for the Missile Defense Agency in late summer. Photo credit: NASA/Tim Jacobs (Approved for Public Release 09-MDA-4800 [30 July 09] )
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2009-07-23
CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla. , the STSS Demonstrator SV-1 spacecraft is moved toward the orbital insertion system. The spacecraft is a midcourse tracking technology demonstrator, part of an evolving ballistic missile defense system. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. It will be launched by NASA for the Missile Defense Agency in late summer. Photo credit: NASA/Tim Jacobs (Approved for Public Release 09-MDA-4800 [30 July 09] )
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Evaluation of 2D ceramic matrix composites in aeroconvective environments
NASA Technical Reports Server (NTRS)
Riccitiello, Salvatore R.; Love, Wendell L.; Balter-Peterson, Aliza
1992-01-01
An evaluation is conducted of a novel ceramic-matrix composite (CMC) material system for use in the aeroconvective-heating environments encountered by the nose caps and wing leading edges of such aerospace vehicles as the Space Shuttle, during orbit-insertion and reentry from LEO. These CMCs are composed of an SiC matrix that is reinforced with Nicalon, Nextel, or carbon refractory fibers in a 2D architecture. The test program conducted for the 2D CMCs gave attention to their subsurface oxidation.
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Skylab 2 Farewell View from the Departing Skylab Command/Service Module
1973-06-22
SL2-07-667 (22 June 1973) --- This overhead view of the Skylab Space Station was taken from the Departing Skylab Command/Service Module during the Skylab 2's final fly-around inspection. The single solar panel is quite evident as well as the parasol solar shield, rigged to replace the missing micrometeoroid shield. Both the second solar panel and the micrometeoroid shield were torn away during a mishap in the original Skylab 1 liftoff and orbital insertion. Photo credit: NASA
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Skylab 2 Farewell View from the Departing Skylab Command/Service Module
1973-06-22
SL2-07-651 (22 June 1973) --- This overhead view of the Skylab Space Station was taken from the Departing Skylab Command/Service Module during the Skylab 2's final fly-around inspection. The single solar panel is quite evident as well as the parasol solar shield, rigged to replace the missing micrometeoroid shield. Both the second solar panel and the micrometeoroid shield were torn away during a mishap in the original Skylab 1 liftoff and orbital insertion. Photo credit: NASA
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Dispersion-based Fresh-slice Scheme for Free-Electron Lasers
DOE Office of Scientific and Technical Information (OSTI.GOV)
Guetg, Marc
The Fresh-slice technique improved the performance of several Self-Amplified Spontaneous Emission Free-Electron laser schemes by granting selective control on the temporal lasing slice without spoiling the other electron bunch slices. So far, the implementation required a special insertion device to create the beam yaw, called dechirper. We demonstrate a novel scheme to enable Freshslice operation based on electron energy chirp and orbit dispersion that can be implemented at any free-electron laser facility without additional hardware.
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An inverse dynamics approach to trajectory optimization for an aerospace plane
NASA Technical Reports Server (NTRS)
Lu, Ping
1992-01-01
An inverse dynamics approach for trajectory optimization is proposed. This technique can be useful in many difficult trajectory optimization and control problems. The application of the approach is exemplified by ascent trajectory optimization for an aerospace plane. Both minimum-fuel and minimax types of performance indices are considered. When rocket augmentation is available for ascent, it is shown that accurate orbital insertion can be achieved through the inverse control of the rocket in the presence of disturbances.
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2014-02-24
VANDENBERG AIR FORCE BASE, Calif. – The second stage for NASA's Orbiting Carbon Observatory-2 mission, or OCO-2, is being towed to the Horizontal Processing Facility at Space Launch Complex 2 from the Building 836 hangar on Vandenberg Air Force Base in California. OCO-2 is scheduled to launch aboard a United Launch Alliance Delta II rocket in July. The rocket's second stage will insert OCO-2 into a polar Earth orbit. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere and provide scientists with a better idea of the chemical compound's impacts on climate change. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. To learn more about OCO-2, visit http://oco.jpl.nasa.gov. Photo credit: NASA/Randy Beaudoin
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OCO-2-Delta II 2nd Stage Arrival
2014-02-21
VANDENBERG AIR FORCE BASE, Calif. – The second stage for NASA's Orbiting Carbon Observatory-2 mission, or OCO-2, arrives at the Building 836 hangar on Vandenberg Air Force Base in California. OCO-2 is scheduled to launch aboard a United Launch Alliance Delta II rocket from Space Launch Complex 2 in July. The rocket's second stage will insert OCO-2 into a polar Earth orbit. OCO-2 will collect precise global measurements of carbon dioxide in the Earth's atmosphere and provide scientists with a better idea of the chemical compound's impacts on climate change. Scientists will analyze this data to improve our understanding of the natural processes and human activities that regulate the abundance and distribution of this important atmospheric gas. To learn more about OCO-2, visit http://oco.jpl.nasa.gov. Photo credit: NASA/Randy Beaudoin
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NASA Astrophysics Data System (ADS)
Kang, Jin Sung; Yoo, Seung Il; Kim, Jin Wook; Yoon, Geum Jae; Yi, Seungjun; Kim, Woo Young
2016-02-01
We used various emissive layer (EML) structures with ultrathin red EMLs to enhance the charge carrier balance and carrier recombination rate in blue PHOLED devices. These EML materials have different energy gaps between highest occupied molecular orbital (HOMO) and lowest unoccupied molecular orbital (LUMO) energy levels. The ultrathin red EMLs, which were inserted in between the blue EMLs, effectively confined the charge carriers in EML, and increased the carrier recombination rate. The thickness of the individual EML was optimized, under 30 nm of the total thickness of EML. The blue PHOLEDs with ultrathin red EMLs achieved a luminous efficiency of 19.24 cd/A, which was 28.7% higher than those without ultrathin red EMLs, and the maximum external quantum efficiency was 11.81% at 500 cd/m2.
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A panoramic view of the Space Station Processing Facility with Unity connecting module
NASA Technical Reports Server (NTRS)
1998-01-01
In this panoramic view of the Space Station Processing Facility (SSPF) can be seen (left to right) Unity connecting module, the Rack Insertion Device and the first Multi-Purpose Launch Module, the Leonardo. Windows at the right above Leonardo allow visitors on tour to watch the activities in the SSPF. The Unity, scheduled to be launched on STS-88 in December 1998, will be mated to the Russian-built Zarya control module which will already be in orbit. STS-88 will be the first Space Shuttle launch for the International Space Station. The Italian-built MPLM, scheduled to be launched on STS-100 on Dec. 2, 1999, will be carried in the payload bay of the Shuttle orbiter, and will provide storage and additional work space for up to two astronauts when docked to the International Space Station.
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Guidance, navigation, and control trades for an Electric Orbit Transfer Vehicle
NASA Astrophysics Data System (ADS)
Zondervan, K. P.; Bauer, T. A.; Jenkin, A. B.; Metzler, R. A.; Shieh, R. A.
The USAF Space Division initiated the Electric Insertion Transfer Experiment (ELITE) in the fall of 1988. The ELITE space mission is planned for the mid 1990s and will demonstrate technological readiness for the development of operational solar-powered electric orbit transfer vehicles (EOTVs). To minimize the cost of ground operations, autonomous flight is desirable. Thus, the guidance, navigation, and control (GNC) functions of an EOTV should reside on board. In order to define GNC requirements for ELITE, parametric trades must be performed for an operational solar-powered EOTV so that a clearer understanding of the performance aspects is obtained. Parametric trades for the GNC subsystems have provided insight into the relationship between pointing accuracy, transfer time, and propellant utilization. Additional trades need to be performed, taking into account weight, cost, and degree of autonomy.
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Fuzzy based attitude controller for flexible spacecraft with on/off thrusters
NASA Astrophysics Data System (ADS)
Knapp, Roger G.; Adams, Neil J.
A fuzzy-based attitude controller is designed for attitude control of a generic spacecraft with on/off thrusters. The controller is comprised of packages of rules dedicated to addressing different objectives (e.g., disturbance rejection, low fuel consumption, avoiding the excitation of flexible appendages, etc.). These rule packages can be inserted or removed depending on the requirements of the particular spacecraft and are parameterized based on vehicle parameters such as inertia or operational parameters such as the maneuvering rate. Individual rule packages can be 'weighted' relative to each other to emphasize the importance of one objective relative to another. Finally, the fuzzy controller and rule packages are demonstrated using the high-fidelity Space Shuttle Interactive On-Orbit Simulator (IOS) while performing typical on-orbit operations and are subsequently compared with the existing shuttle flight control system performance.
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Fuzzy based attitude controller for flexible spacecraft with on/off thrusters
NASA Astrophysics Data System (ADS)
Knapp, Roger Glenn
1993-05-01
A fuzzy-based attitude controller is designed for attitude control of a generic spacecraft with on/off thrusters. The controller is comprised of packages of rules dedicated to addressing different objectives (e.g., disturbance rejection, low fuel consumption, avoiding the excitation of flexible appendages, etc.). These rule packages can be inserted or removed depending on the requirements of the particular spacecraft and are parameterized based on vehicle parameters such as inertia or operational parameters such as the maneuvering rate. Individual rule packages can be 'weighted' relative to each other to emphasize the importance of one objective relative to another. Finally, the fuzzy controller and rule packages are demonstrated using the high-fidelity Space Shuttle Interactive On-Orbit Simulator (IOS) while performing typical on-orbit operations and are subsequently compared with the existing shuttle flight control system performance.
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Small Spacecraft System-Level Design and Optimization for Interplanetary Trajectories
NASA Technical Reports Server (NTRS)
Spangelo, Sara; Dalle, Derek; Longmier, Ben
2014-01-01
The feasibility of an interplanetary mission for a CubeSat, a type of miniaturized spacecraft, that uses an emerging technology, the CubeSat Ambipolar Thruster (CAT) is investigated. CAT is a large delta-V propulsion system that uses a high-density plasma source that has been miniaturized for small spacecraft applications. An initial feasibility assessment that demonstrated escaping Low Earth Orbit (LEO) and achieving Earth-escape trajectories with a 3U CubeSat and this thruster technology was demonstrated in previous work. We examine a mission architecture with a trajectory that begins in Earth orbits such as LEO and Geostationary Earth Orbit (GEO) which escapes Earth orbit and travels to Mars, Jupiter, or Saturn. The goal was to minimize travel time to reach the destinations and considering trade-offs between spacecraft dry mass, fuel mass, and solar power array size. Sensitivities to spacecraft dry mass and available power are considered. CubeSats are extremely size, mass, and power constrained, and their subsystems are tightly coupled, limiting their performance potential. System-level modeling, simulation, and optimization approaches are necessary to find feasible and optimal operational solutions to ensure system-level interactions are modeled. Thus, propulsion, power/energy, attitude, and orbit transfer models are integrated to enable systems-level analysis and trades. The CAT technology broadens the possible missions achievable with small satellites. In particular, this technology enables more sophisticated maneuvers by small spacecraft such as polar orbit insertion from an equatorial orbit, LEO to GEO transfers, Earth-escape trajectories, and transfers to other interplanetary bodies. This work lays the groundwork for upcoming CubeSat launch opportunities and supports future development of interplanetary and constellation CubeSat and small satellite mission concepts.
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Present Status and Near Term Activities for the ExoMars Trace Gas Orbiter.
NASA Astrophysics Data System (ADS)
Svedhem, H.; Vago, J. L.
2017-12-01
The ExoMars 2016 mission was launched on a Proton rocket from Baikonur, Kazakhstan, on 14 March 2016 and arrived at Mars on 19 October 2016. The spacecraft is now performing aerobraking to reduce its orbital period from initial post-insertion orbital period of one Sol to the final science orbit with a 2 hours period. The orbital inclination will be 74 degrees. During the aerobraking a wealth of data has been acquired on the state of the atmosphere along the tracks between 140km and the lowest altitude at about 105 km. These data are now being analysed and compared with existing models. In average TGO measures a lower atmospheric density than predicted, but the numbers lay within the expected variability. ExoMars is a joint programme of the European Space Agency (ESA) and Roscosmos, Russia. It consists of the ExoMars 2016 mission with the Trace Gas Orbiter, TGO, and the Entry Descent and Landing Demonstrator, EDM, named Schiaparelli, and the ExoMars 2020 mission, which carries a lander and a rover. The TGO scientific payload consists of four instruments: ACS and NOMAD, both infrared spectrometers for atmospheric measurements in solar occultation mode and in nadir mode, CASSIS, a multichannel camera with stereo imaging capability, and FREND, an epithermal neutron detector to search for subsurface hydrogen (as proxy for water ice and hydrated minerals). The launch mass of the TGO was 3700 kg, including fuel. In addition to its scientific measurements TGO will act as a relay orbiter for NASA's landers on Mars and as from 2021 for the ESA-Roscosmos Rover and Surface Station.
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Low-Cost Propellant Launch From a Tethered Balloon
NASA Technical Reports Server (NTRS)
Wilcox, Brian
2006-01-01
A document presents a concept for relatively inexpensive delivery of propellant to a large fuel depot in low orbit around the Earth, for use in rockets destined for higher orbits, the Moon, and for remote planets. The propellant is expected to be at least 85 percent of the mass needed in low Earth orbit to support the NASA Exploration Vision. The concept calls for the use of many small ( 10 ton) spin-stabilized, multistage, solid-fuel rockets to each deliver 250 kg of propellant. Each rocket would be winched up to a balloon tethered above most of the atmospheric mass (optimal altitude 26 2 km). There, the rocket would be aimed slightly above the horizon, spun, dropped, and fired at a time chosen so that the rocket would arrive in orbit near the depot. Small thrusters on the payload (powered, for example, by boil-off gases from cryogenic propellants that make up the payload) would precess the spinning rocket, using data from a low-cost inertial sensor to correct for small aerodynamic and solid rocket nozzle misalignment torques on the spinning rocket; would manage the angle of attack and the final orbit insertion burn; and would be fired on command from the depot in response to observations of the trajectory of the payload so as to make small corrections to bring the payload into a rendezvous orbit and despin it for capture by the depot. The system is low-cost because the small rockets can be mass-produced using the same techniques as those to produce automobiles and low-cost munitions, and one or more can be launched from a U.S. territory on the equator (Baker or Jarvis Islands in the mid-Pacific) to the fuel depot on each orbit (every 90 minutes, e.g., any multiple of 6,000 per year).
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Rescue and Calibration of NIMBUS 1-4 IR Film Products, 1964 TO 1972
NASA Astrophysics Data System (ADS)
Morgan, T.; Campbell, G. G.
2017-12-01
Digital data exists from the high resolution infrared instruments on Nimbus 1 to 4 for about 1/4 of the possible orbits for parts of 1964, 1966, 1969 and 1970. We are now digitizing and navigating 35 mm film products from those instruments into digital files. Some of those orbits overlap with the digital data so we can "calibrate" the gray scale pictures into temperatures by comparison. Then that calibration can be extended to orbits with no digital data. This greatly improves the coverage of the night time IR view of the earth. Ultimately these data will be inserted into the NASA archive for general use. We will review our progress on this project and discuss an error estimate for the calibration of the HRIR (High Resolution Infrared Radiometer) data from Nimbus 1, 2 and 3 as well as the THIR (Thermal Infrared Radiometer) data on Nimbus 4. These more complete Infrared views of the Earth provide the opportunity to better understand the weather in this period. Comparisons will be made with pre-satellite era reanalysis products.
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Juno Magnetometer Observations in the Earth's Magnetosphere
NASA Astrophysics Data System (ADS)
Connerney, J. E.; Oliversen, R. J.; Espley, J. R.; MacDowall, R. J.; Schnurr, R.; Sheppard, D.; Odom, J.; Lawton, P.; Murphy, S.; Joergensen, J. L.; Joergensen, P. S.; Merayo, J. M.; Denver, T.; Bloxham, J.; Smith, E. J.; Murphy, N.
2013-12-01
The Juno spacecraft enjoyed a close encounter with Earth on October 9, 2013, en route to Jupiter Orbit Insertion (JOI) on July 5, 2016. The Earth Flyby (EFB) provided a unique opportunity for the Juno particles and fields instruments to sample mission relevant environments and exercise operations anticipated for orbital operations at Jupiter, particularly the period of intense activity around perijove. The magnetic field investigation onboard Juno is equipped with two magnetometer sensor suites, located at 10 and 12 m from the spacecraft body at the end of one of the three solar panel wings. Each contains a vector fluxgate magnetometer (FGM) sensor and a pair of co-located non-magnetic star tracker camera heads which provide accurate attitude determination for the FGM sensors. This very capable magnetic observatory sampled the Earth's magnetic field at 64 vector samples/second throughout passage through the Earth's magnetosphere. We present observations of the Earth's magnetic field and magnetosphere obtained throughout the encounter and compare these observations with those of other Earth-orbiting assets, as available, and with particles and fields observations acquired by other Juno instruments operated during EFB.
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TPS design for aerobraking at Earth and Mars
NASA Astrophysics Data System (ADS)
Williams, S. D.; Gietzel, M. M.; Rochelle, W. C.; Curry, D. M.
1991-08-01
An investigation was made to determine the feasibility of using an aerobrake system for manned and unmanned missions to Mars, and to Earth from Mars and lunar orbits. A preliminary thermal protection system (TPS) was examined for five unmanned small nose radius, straight bi-conic vehicles and a scaled up Aeroassist Flight Experiment (AFE) vehicle aerocapturing at Mars. Analyses were also conducted for the scaled up AFE and an unmanned Sample Return Cannister (SRC) returning from Mars and aerocapturing into Earth orbit. Also analyzed were three different classes of lunar transfer vehicles (LTV's): an expendable scaled up modified Apollo Command Module (CM), a raked cone (modified AFT), and three large nose radius domed cylinders. The LTV's would be used to transport personnel and supplies between Earth and the moon in order to establish a manned base on the lunar surface. The TPS for all vehicles analyzed is shown to have an advantage over an all-propulsive velocity reduction for orbit insertion. Results indicate that TPS weight penalties of less than 28 percent can be achieved using current material technology, and slightly less than the most favorable LTV using advanced material technology.
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NASA Technical Reports Server (NTRS)
Short, R.; Behuncik, J.
1996-01-01
The SOHO spacecraft was successfully launched by an Atlas 2AS from the Eastern Range on December 2, 1995. After a short time in a nearly circular parking orbit, the spacecraft was placed by the Centaur upper stage on a transfer trajectory to the L1 libration point where it was inserted into a class 1 Halo orbit. The nominal mission lifetime is two years which will be spent collecting data from the Sun using a complement of twelve instruments. An overview of the early phases of Flight Dynamics Facility support of the mission is given. Maneuvers required for the mission are discussed, and an evaluation of these maneuvers is given with the attendent effects on the resultant orbit. Thruster performance is presented as well as real time monitoring of thruster activity during maneuvers. Attitude areas presented are the star identification process and role angle determination, momentum management, operating constraints on the star tracker, and guide star switching. A brief description of the two Heads Up displays is given.
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Controlling the motion of a spacecraft when approaching a large object of space debris
NASA Astrophysics Data System (ADS)
Baranov, A. A.; Budyanskiy, A. A.; Razumnyi, Yu. N.
2017-07-01
The problem of calculating the parameters of maneuvering a spacecraft as it approaches a large object of space debris (LOSD) in close near-circular noncoplanar orbits has been considered. In [1-4], the results of analyzing the problem of the flyby of the separated LOSD groups have been presented. It has been assumed that a collector spacecraft approaches the LOSD and captures it or it is inserted into the nozzle of a small spacecraft that has a proper propulsion system (PS). However, in these papers, the flight from one object to another was only analyzed and the problem of approaching to LOSD with a given accuracy was not considered. This paper is a supplement to the cycle of papers [1-4]. It is assumed that, the final stage of approaching the LOSD is implemented by maneuvering in many orbits (up to several dozens) with low-thrust engines, but the PS operating time is fairly small compared with the orbit period in order to make it possible to use impulse approximation in the calculations.