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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 271 records · Page 15
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NASA NTRS1991

Periodic oscillations of the quasi-parallel bow shock as observed with the AMPTE/CCE spacecraft

The AMPTE/CCE spacecraft has, on occasion, encountered the earth's bow shock near apogee (about 9 earth radii). During one encounter, on November 1, 1984, the bow shock was observed to pass back and forth over the spacecraft several times in a periodic fashion. The period of the oscillation was about 20 seconds, and an upstream wave with a similar period was observed in the solar wind just prior to the multiple shock crossings. Minimum variance analysis of the shock crossings shows that the magnetic field carried out a single rotation through 360 deg for each pair of shock crossings. This implies that the shock was responding to the rotation of the field in the upstream wave, and it is shown how the plasma displacement associated with the upstream wave can produce the observed oscillations. These data may provide support for the wavelike structure of quasi-parallel shocks predicted in simulations.

Strangeway, R. J.↗
NASA NTRS1991

German telecommunications satellite (Deutscher fernmelde satellit) (DFS-1 and -2)

The German Telecommunications Satellite (DFS) Program is to provide telecommunications service for high data rate transmission of text and video data to the Federal Republic of Germany within the 11-14 GHz and 20-30 GHz bands. The space segment of this program is composed of three satellites, DFS-1, DFS-2, and DFS-3, which will be located at 23.5 degrees E longitude of the geostationary orbit. The DFS will be launched from the Center Spatial Guyanis in French Giana on an Ariane launch vehicle. The mission follows the typical injection sequence: parking orbit, transfer orbit, and earth orbit. Attitude maneuvers will be performed to orient the spacecraft prior to Apogee Kick Motor (AKM) firing. After AKM firing, drift phase orbital and attitude maneuvers will be performed to place the spacecraft in its final geostationary position. The Deep Space Network (DSN) will support the transfer and drift orbit mission phases. Information is presented in tabular form for the following areas: DSN support, compatibility testing, frequency assignments, telemetry, command, and tracking support responsibilities.

Hiendlmeier, G.↗
NASA NTRS1991

Hipparcos

The primary objective of Hipparcos is to provide very accurate star map data and star position accuracies on the order of 2 arc seconds. Hipparcos was planned to be in a geostationary orbit, but due to failure of the apogee motor, it is currently in a high elliptical orbit and has a 10.8 hour period. Goldstone 26 m will provide 6-8 hours per day support for real-time telemetry and command. Mission-dependent equipment is required at Goldstone, and telemetry and command data will be transmitted from Goldstone to European Space Operations Control Center (ESOC) via satellite links. Operations support is scheduled to begin 12 Mar. 1990.

Source record↗
NASA NTRS1991

International Solar Terrestrial Physics (ISTP) WIND Mission

The launch of the WIND spacecraft will place the satellite into a sunside apogee double-lunar swing-by orbit for a period of one year, after which WIND may be transferred to a Sun-Earth L1 Halo orbit. Information is presented in tabular form on the following topics: Deep Space Network support; frequency assignments, telemetry, command, and ranging.

Sanford, R.↗
NASA NTRS1991

International Solar Terrestrial Physics (ISTP) program polar mission

The polar spacecraft will be launched from Western Test Ranges (WTR) into a 2 earth radii by 9 earth radii polar orbit, with apogee near the North Pole. Information is presented on the following topics: Deep Space Network support, frequency assignments, telemetry, command, and ranging.

Sanford, R.↗
NASA NTRS1991

Minimum fuel coplanar aeroassisted orbital transfer using collocation and nonlinear programming

The fuel optimal control problem arising in coplanar orbital transfer employing aeroassisted technology is addressed. The mission involves the transfer from high energy orbit (HEO) to low energy orbit (LEO) without plane change. The basic approach here is to employ a combination of propulsive maneuvers in space and aerodynamic maneuvers in the atmosphere. The basic sequence of events for the coplanar aeroassisted HEO to LEO orbit transfer consists of three phases. In the first phase, the transfer begins with a deorbit impulse at HEO which injects the vehicle into a elliptic transfer orbit with perigee inside the atmosphere. In the second phase, the vehicle is optimally controlled by lift and drag modulation to satisfy heating constraints and to exit the atmosphere with the desired flight path angle and velocity so that the apogee of the exit orbit is the altitude of the desired LEO. Finally, the second impulse is required to circularize the orbit at LEO. The performance index is maximum final mass. Simulation results show that the coplanar aerocapture is quite different from the case where orbital plane changes are made inside the atmosphere. In the latter case, the vehicle has to penetrate deeper into the atmosphere to perform the desired orbital plane change. For the coplanar case, the vehicle needs only to penetrate the atmosphere deep enough to reduce the exit velocity so the vehicle can be captured at the desired LEO. The peak heating rates are lower and the entry corridor is wider. From the thermal protection point of view, the coplanar transfer may be desirable. Parametric studies also show the maximum peak heating rates and the entry corridor width are functions of maximum lift coefficient. The problem is solved using a direct optimization technique which uses piecewise polynomial representation for the states and controls and collocation to represent the differential equations. This converts the optimal control problem into a nonlinear programming problem which is solved numerically by using a modified version of NPSOL. Solutions were obtained for the described problem for cases with and without heating constraints. The method appears to be more robust than other optimization methods. In addition, the method can handle complex dynamical constraints.

Shi, Yun Yuan↗
NASA NTRS1991

Bristol Today

The topics are presented in viewgraph form and include the following: corporate organization; product groups; the CRV7 rocket weapon system; Black Brant Sounding Rockets; apogee performance; space payload experience; the Orbital Express; and program and procurement requirements.

Source record↗
NASA NTRS1992

Space Storable Rocket Technology (SSRT) basic program

The Space Storable Rocket Technology Program (SSRT) was conducted to establish a technology for a new class of high performance and long life bipropellant engines using space storable propellants. The results are described. Task 1 evaluated several characteristics for a number of fuels to determine the best space storable fuel for use with LO2. The results indicated that LO2-N2H4 is the best propellant combination and provides the maximum mission/system capability maximum payload into GEO of satellites. Task 2 developed two models, performance and thermal. The performance model indicated the performance goal of specific impulse greater than or = 340 seconds (sigma = 204) could be achieved. The thermal model was developed and anchored to hot fire test data. Task 3 consisted of design, fabrication, and testing of a 200 lbf thrust test engine operating at a chamber pressure of 200 psia using LO2-N2H4. A total of 76 hot fire tests were conducted demonstrating performance greater than 340 (sigma = 204) which is a 25 second specific impulse improvement over the existing highest performance flight apogee type engines.

Chazen, M. L.↗
NASA NTRS1992

Observations of transverse ion acceleration in the topside auroral ionosphere

The paper reports data obtained from a sounding rocket flight which reached an apogee of 927 km and passed through several auroral arcs. Therma/superthermal ions were sampled by charged particle analyzers which allowed for a rapid (about 1 s) sampling of their distribution function. During portions of the flight when the rocket was not in an energetic auroral structure, the ion data are fit to a Maxwellian function which yields the plasma parameters. Throughout the middle portion of the flight, above 700-km altitude, ion distributions having a superthermal tail were measured. When the rocket was immersed in energetic auroral electron precipitation, two other ion distributions were observed. Transversely accelerated ions which represented bulk heating of the ambient population were observed continuously in these arcs. The characteristic perpendicular energy of the transversely bulk heated ions reached as high as 3 eV compared to typically less than 0.4 eV during nonauroral times. The observations are discussed in terms of some current theories of transverse ion energization.

Garbe, G. P.↗
NASA NTRS1992

Nonadiabatic heating of the central plasma sheet at substorm onset

Heating events in the plasma sheet boundary layer and central plasma sheet are found to occur at the onset of expansive phase activity. The main effect is a dramatic increase in plasma temperature, coincident with a partial dipolarization of the magnetic field. Fluxes of energetic particles increase without dispersion during these events which occur at all radial distances up to 23 RE, the apogee of the ISEE spacecraft. A major difference between these heating events and those observed at geosynchronous distances lies in the heating mechanism which is nonadiabatic beyond 10 RE but may be adiabatic closer to earth. The energy required to account for the increase in plasma thermal energy is comparable with that required for Joule heating of the ionosphere. The plasma sheet must be considered as a major sink in the energy balance of a substorm. Lobe magnetic pressures during these events are estimated. Change in lobe pressure are generally not correlated with onsets or intensifications of expansive phase activity.

Huang, C. Y.↗
NASA NTRS1992

Test experience, 490 N high performance (321 sec Isp) engine

Engines with area ratios of 44:1 and 286:1 are tested by means of hot fire tests using the NTO/MMH bipropellant to maximize the performance of the combined technologies. The low-thrust engine systems are designed with oxidation resistant materials that can operate at temperatures of more than 2204 C for tens of hours. The chamber is attached to the injector in a configuration that prevents overheating of the injector, valve, and the spacecraft interface. Three injectors with 44:1 area ratios are capable of nominal specific impulse values of 309 sec, and a performance of 321 lbf-sec/lbm is noted for an all-welded engine assembly with area ratio of 286:1. The all-welded engine is shown to have an acceptable design margin for thermal characteristics. High-performance liquid apogee engines are shown to perform optimally when based on iridium/rhenium chamber technology, use of a special platelet injector, and the minimization of losses due to fuel-film cooling.

Schoenman, L.↗
NASA NTRS1992

A methodology for selective removal of orbital debris

Earth-orbiting objects, large enough to be tracked, were surveyed for possible systematic debris removal. Based upon the statistical collision studies of others, it was determined that objects in orbits approximately 1000 km above the Earth's surface are at greatest collisional risk. Russian C-1B boosters were identified as the most important target of opportunity for debris removal. Currently, more than 100 in tact boosters are orbiting the Earth with apogees between 950 km and 1050 km. Using data provided by Energia USA, specific information on the C-1B booster, in terms of rendezvous and capture strategies, was discussed.

Ash, R. L.↗
NASA NTRS1991

High speed civil transport

This report discusses the design and marketability of a next generation supersonic transport. Apogee Aeronautics Corporation has designated its High Speed Civil Transport (HSCT): Supercruiser HS-8. Since the beginning of the Concorde era, the general consensus has been that the proper time for the introduction of a next generation Supersonic Transport (SST) would depend upon the technical advances made in the areas of propulsion (reduction in emissions) and material composites (stronger, lighter materials). It is believed by many in the aerospace industry that these beforementioned technical advances lie on the horizon. With this being the case, this is the proper time to begin the design phase for the next generation HSCT. The design objective for a HSCT was to develop an aircraft that would be capable of transporting at least 250 passengers with baggage at a distance of 5500 nmi. The supersonic Mach number is currently unspecified. In addition, the design had to be marketable, cost effective, and certifiable. To achieve this goal, technical advances in the current SST's must be made, especially in the areas of aerodynamics and propulsion. As a result of these required aerodynamic advances, several different supersonic design concepts were reviewed.

Source record↗
NASA NTRS1992

Satellite situation report, volume 32, no. 4

This report consists of data computed at the U.S. Space Command, GSFC, or provided by satellite owners. A space objects box score table is presented with data under the following headings: source/organization, objects in orbit, and decayed objects. The objects in orbit and decayed objects headings have payload, debris, and total as subheadings. The bulk of the document is objects-in-orbit tables with data under the following headings: international designation, name, catalog number, source, launch date, period minutes, inclination, apogee (km), perigee (km), and notes.

Source record↗
NASA NTRS1992

Anomalous aspects of magnetosheath flow and of the shape and oscillations of the magnetopause during an interval of strongly northward interplanetary magnetic field

On 15 Feb. 1978, the orientation of the interplanetary magnetic field (IMF) remained steadily northward for more than 12 hours. The ISEE 1 and 2 spacecraft were located near apogee on the dawn side flank of the magnetotail. IMP 8 was almost symmetrically located in the magnetosheath on the dusk flank and IMP 7 was upstream in the solar wind. Using plasma and magnetic field data, we show the following: (1) the magnetosheath flow speed on the flanks of the magnetotail steadily exceeded the solar wind speed by 20 percent; (2) surface waves with approximately a 5-min period and very non-sinusoidal waveform were persistently present on the dawn magnetopause and waves of similar period were present in the dusk magnetosheath; and (3) the magnetotail ceased to flare at an antisunward distance of 15 R(sub E). We propose that the acceleration of the magnetosheath flow is achieved by magnetic tension in the draped field configuration for northward IMF and that the reduction of tail flaring is consistent with a decreased amount of open magnetic flux and a larger standoff distance of the subsolar magnetopause. Results of a three-dimensional magnetohydrodynamic simulation support this phenomenological model.

Chen, Sheng-Hsien↗
NASA NTRS1992

Strv1-b Flight Experiment

The Space Technology Research Vehicle (STRV-1b) is discussed. The STRV-1b is a small (100 watt) satellite flown by the British Defense Research Agency (DRA). The mission goal is to fly new and emerging space technologies at a more reasonable cost in a short-term timeframe. The STRV-1b's orbit can be described as a geosynchronous transfer orbit (GTO) with a perigee of 200 km, an apogee of 36,000 km (geosynchronous earth orbit (GEO)), and a period of 10.5 hours. The Phillips Laboratory plans to use the STRV-1b to test up to 20 advanced experimental photovoltaic cells. The discussion is presented in vugraph form.

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NASA NTRS1992

Auroral X-ray imaging from high- and low-earth orbit

Observations of bremsstrahlung X-rays emitted by energetic electrons impacting the earth's atmosphere can be used for remotely sensing the morphology, intensity, and energy spectra of electron precipitation from the magnetosphere. Two auroral X-ray imagers, developed for future spaceflight, will be discussed. Polar Ionospheric X-ray Imaging Experiment is scheduled for launch on the NASA International Solar-Terrestrial Physics/Global Geospace Science program POLAR satellite in May, 1994. The POLAR orbit, with an apogee and perigee of 9 and 1.8 R(E) (earth radii), respectively, affords the opportunity to image the aurora from high altitude above the north pole continuously for several hours. The Magnetospheric Atmospheric X-ray Imaging Experiment is scheduled for launch aboard the NOAA-I satellite in late 1992. The 800-km polar orbit passes over both the northern and southern auroral zones every 101 minutes. The presentation emphasizes the experimental approaches used to exploit these very different orbits for remote sensing of the earth's auroral zones.

Mckenzie, D. L.↗
NASA NTRS1992

The Coronal Ultraviolet Berkeley Spectrometer (CUBS)

We describe an instrument package to remotely measure thermospheric, exospheric, and plasmaspheric structure and composition. This instrument was flown aboard the second test flight of the Black Brant XII sounding rocket on December 5, 1989, which attained an apogee of 1460 km. The experiment package consisted of a spectrophotometer to measure He I 584 A, O II 834 A, O I 989 A, hydrogen Lyman beta (1025 A), hydrogen Lyman alpha (1216 A), and O I 1304 A transitions, and a photometer to measure the He II 304 A emission. The optical design of the spectrophotometer was identical to that of the Berkeley Extreme Ultraviolet (EUV) Airglow Rocket Spectrometer payload, flown on September 30, 1988 aboard the maiden flight of the Black Brant XII rocket. We present the initial data analysis and describe directions we will go toward the completion of our study.

Bush, Brett C.↗