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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 253 records · Page 14
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NASA NTRS1989

GOES-I/M ascent maneuvers from transfer orbit to station

The Geostationary Operational Environmental Satellite (GOES)-I/M station acquisition sequence consists nominally of three in-plane/out-of-plane maneuvers at apogee on the line of relative nodes and a small in-plane maneuver at perigee. Existing software to determine maneuver attitude, ignition time, and burn duration required modification to optimize the out-of-plane parts and admit the noninertial, three-axis stabilized attitude. The Modified Multiple Impulse Station Acquisition Maneuver Planning Program (SENARIO2) was developed from its predecessor, SCENARIO, to optimize the out-of-plane components of the impulsive delta-V vectors. Additional new features include commputation of short term J sub 2 perturbations and output of all premaneuver and postmaneuver orbit elements, coarse maneuver attitudes, propellant usage, spacecraft antenna aspect angles, and ground station coverage. The output data are intended to be used in the launch window computation and by the maneuver targeting computation (General Maneuver (GMAN) Program) software. The maneuver targeting computation in GMAN was modified to admit the GOES-I/M maneuver attitude. Appropriate combinations of ignition time, burn duration, and attitude enable any reasonable target orbit to be achieved.

Abeyagunawardene, S.↗
NASA NTRS1989

The controllability of the aeroassist flight experiment atmospheric skip trajectory

The Aeroassist Flight Experiment (AFE) will be the first vehicle to simulate a return from geosynchronous orbit, deplete energy during an aerobraking maneuver, and navigate back out of the atmosphere to a low earth orbit It will gather scientific data necessary for future Aeroasisted Orbitl Transfer Vehicles (AOTV's). Critical to mission success is the ability of the atmospheric guidance to accurately attain a targeted post-aeropass orbital apogee while nulling inclination errors and compensating for dispersions in state, aerodynamic, and atmospheric parameters. In typing to satisfy mission constraints, atmospheric entry-interface (EI) conditions, guidance gains, and trajectory. The results of the investigation are presented; emphasizing the adverse effects of dispersed atmospheres on trajectory controllability.

Wood, R.↗
NASA NTRS1989

Optimal trajectories for the aeroassisted flight experiment. Part 3: Formulation, results, and analysis

The determination of optimal trajectories for the aero-assisted flight experiment (AFE) is investigated. The intent of this experiment is to simulate a GEO-to-LEO transfer, where GEO denotes a geosynchronous Earth orbit and LEO denotes a low Earth orbit. The trajectories of an AFE spacecraft are analyzed in a 3D-space, employing the full system of 6 ODEs describing the atmospheric pass. The atmospheric entry conditions are given, and the atmospheric exit conditions are adjusted in such a way that the following conditions are satisfied: (1) the atmospheric velocity depletion is such that, after exiting, the AFE spacecraft first ascends to a specified apogee and then descends to a specified perigee; and (2) the exit orbital plane is identical with the entry orbital plane. The final maneuver, not analyzed here, includes the rendezvous with and the capture by the space shuttle.

Miele, A.↗
NASA NTRS1989

Advanced onboard propulsion benefits and status

Future commercial space systems may include geosynchronous-orbit communication satellites; Earth-observing satellites in polar, sun-synchronous orbits; and tended low-earth-orbit platforms. All such space systems require onboard propulsion for a variety of functions, including stationkeeping and drag makeup, apogee motors, and delivery and return. In many cases, the onboard propulsion exerts a major influence on the overall mission performance, lifetime, and integration. NASA has established a Low Thrust Propulsion Program, which is developing chemical and electric propulsion concepts that offer potential for significant benefits for onboard propulsion for the various classes of commercial spacecraft. The onboard propulsion requirements of future commercial space systems are briefly discussed, followed by a summary of the characteristics and status of relevant elements of the NASA Low Thrust program.

Byers, David C.↗
NASA NTRS1990

A statistical study of magnetic field magnitude changes during substorms in the near earth tail

Using AMPTE/CCE data taken in 1985 and 1986 when the CCE apogee (8.8 earth radii) was within 4.5 hours of midnight, 167 injection events in the near-earth magnetotail have been cataloged. These events are exactly or nearly dispersionless on a 72-sec time scale from 25 keV to 285 keV. The changes in the field magnitude are found to be consistent with the expected effects of the diversion/disruption of the cross-tail current during a substorm, and the latitudinal position of the current sheet is highly variable within the orbit of CCE. The local time variation of the magnetic-field changes implies that the substorm current wedge is composed of longitudinally broad Birkeland currents.

Lopez, R. E.↗
NASA NTRS1990

Remote sensing of the thermosphere, plasmasphere, and exosphere

An instrument package for remotely measuring thermospheric, exospheric, and plasmaspheric structure and composition is described. This instrument will be flown aboard the second test flight of the Black Brant XII rocket, with an expected apogee of about 1300 km. The experiment package consists 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 He II 304 A photometer consists of a layered synthetic microstructure mirror tuned at 304 A to focus incidence radiation onto a detector. The high altitude to be attained by the rocket is ideally suited to probe the coupling of the various atmospheric regions through the simultaneous measurement of the altitude distributions of several major thermospheric, ionospheric, and exospheric constituents.

Chakrabarti, S.↗
NASA NTRS1989

Double-lunar swingby trajectories for the spacecraft of the International Solar Terrestrial Physics program

The ISEE-3 satellite carried out the first extensive exploration of the distant geomagnetic tail during 1983. ISEE-3's orbit was altered with four lunar gravity assists that alternately decreased and increased its orbital energy while keeping the apogees aligned in the antisolar direction. Two spacecraft of the International Solar Terrestrial Physics program will use similar double-lunar swingby orbits to study the solar wind and the geomagnetic environment. Geotail will be built in Japan for the Institute of Space and Astronautical Sciences; its main purpose will be to explore the earth's geomagnetic tail. Wind is a NASA spacecraft that will monitor the solar wind upstream from the earth and will also study the bowshock region of the magnetosphere. Current plans call for launches of both by NASA with expendable launch vehicles during the second half of 1992.

Dunham, David W.↗
NASA NTRS1990

Mass estimation in the breakups of Soviet satellites

An attempt is made to estimate the mass of the parent satellite from the mass of the debris remaining from its breakup using a technique based on the decay rate and radar cross-section time history. The decay of perigee and apogee with time of an object in orbit provides the area-to-mass ratio and the radar cross-section provides a measure of the effective area of the object, while combining the two gives the mass of the object. The technique has been successfully applied to 12 U.S. breakups and one Arianespace breakup. Calculations exhibiting good agreement with reference mass are also discussed for Soviet intact C-class boosters, intact ASAT target satellites, and intact navigational satellites. It is found that the calculated mass of the ASAT interceptor spacecraft is about one-half of the expected mass, but it is pointed out that this may be due to fuel carried on board. For ASAT target breakups the calculated mass is 20-30 times too low; no clear explanation can yet be found for this phenomenon.

Badhwar, Gautam D.↗
NASA NTRS1990

Satellite situation report, volume 30, no. 1

Space objects are listed as well as those which decayed during this reporting period. Data provided include international designation and catalog number, nation of source, launch data, inclination, apogee, and perigee. Transmitting frequencies for satellites being monitored by NASA's space flight tracking and data network are given.

Source record↗
NASA NTRS1990

Satellite situation report, volume 30, no. 4

Space objects are listed as well as those which decayed during this reporting period. Data provided include international designation and catalog number, nation of source, launch date, inclination, apogee, and perigee. Transmitting frequencies for satellites being monitored by NASA's space flight tracking and data network are given.

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NASA NTRS1990

High-Latitude Communications Satellite (HILACS)

The Naval Postgraduate School in the AE 4871 Advanced Spacecraft Design course designed a communications satellite (HILACS) that will provide a continuous UHF communications link between stations located north of the region covered by geosynchronous communications satellites. The communications payload will operate only for that portion of the orbit necessary to provide specific coverage. The satellite orbit is elliptic with perigee at 1204 km in the Southern Hemisphere and an apogee at 14,930 km with 63.4 degrees inclination. Analysis and design of each of the subsystems was done to the extent possible within the constraints of an eleven week quarter and the design and analysis tools available. Work was completed in orbital analysis, the reaction control system, attitude control subsystem, electric power subsystem, telemetry, tracking, and control, thermal control subsystem, and the structures subsystem. The design team consisted of 12 students. Additional support was provided by the Jet Propulsion Laboratory and the Naval Research Laboratory.

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NASA NTRS1991

Analysis of error in TOMS total ozone as a function of orbit and attitude parameters

Computer simulations of orbital scenarios were performed to examine the effects of orbital altitude, equator crossing time, attitude uncertainty, and orbital eccentricity on ozone observations by future satellites. These effects were assessed by determining changes in solar and viewing geometry and earth daytime coverage loss. The importance of these changes on ozone retrieval was determined by simulating uncertainties in the TOMS ozone retrieval algorithm. The major findings are as follows: (1) Drift of equator crossing time from local noon would have the largest effect on the quality of ozone derived from TOMS. The most significant effect of this drift is the loss of earth daytime coverage in the winter hemisphere. The loss in coverage increases from 1 degree latitude for + or - 1 hour from noon, 6 degrees for + or - 3 hours from noon, to 53 degrees for + or - 6 hours from noon. An additional effect is the increase in ozone retrieval errors due to high solar zenith angles. (2) To maintain contiguous earth coverage, the maximum scan angle of the sensor must be increased with decreasing orbital altitude. The maximum scan angle required for full coverage at the equator varies from 60 degrees at 600 km altitude to 45 degrees at 1200 km. This produces an increase in spacecraft zenith angle, theta, which decreases the ozone retrieval accuracy. The range in theta was approximately 72 degrees for 600 km to approximately 57 degrees at 1200 km. (3) The effect of elliptical orbits is to create gaps in coverage along the subsatellite track. An elliptical orbit with a 200 km perigee and 1200 km apogee produced a maximum earth coverage gap of about 45 km at the perigee at nadir. (4) An attitude uncertainty of 0.1 degree in each axis (pitch, roll, yaw) produced a maximum scan angle to view the pole, and maximum solar zenith angle).

Gregg, W. W.↗
NASA NTRS1991

Mass comparisons of electric propulsion systems for NSSK of geosynchronous spacecraft

A model was developed and exercised to allow wet mass comparisons of three axis stabilized communication satellites delivered to geosynchronous transfer orbit. The mass benefits of using advanced chemical propulsion for apogee injection and north-south stationkeeping (NSSK) functions or electric propulsion (hydrazine arcjets and xenon ion thrusters) for NSSK functions are documented. A large derated ion thrusters is proposed which minimizes thruster lifetime concerns and qualification test times when compared to those of smaller ion thrusters planned for NSSK applications. The mass benefits, which depend on the spacecraft mass and mission duration, increase dramatically with arcjet specific impulse in the 500 to 600 s range, but are nearly constant for the derated ion thruster operated in the 2300 to 3000 s range. For a given mission, the mass benefits with an ion system are typically double those of the arcjet system; however, the total thrusting time with arcjets is less than 1/3 that with ion thrusters for the same thruster power. The mass benefits may permit increases in revenue producing payload or reduce launch costs by allowing a move to a smaller launch vehicle.

Rawlin, Vincent K.↗
NASA NTRS1990

Ion composition in and near the frontside boundary layer

A unique set of magnetopause crossings by the AMPTE/CCE spacecraft from near its 8.8 R(E) apogee is used to identify 13 crossings within the first two years after launch time that contain significant data intervals in the magnetosheath, boundary layer, and nearby outer magnetosphere. It is concluded that shocked solar wind or magnetosheath ions as well as ions from the outer magnetosphere overlap the boundary layer. Low-energy He(2+) as well as high charge state CNO, Si, and Fe group ions clearly overlap the boundary layer from their solar wind source. Similarly, O(+), N(+), O2(+) and NO(+) + O2(+) overlap the boundary layer from their magnetospheric source region. It is found that ion densities in the boundary layer are roughly one half those observed in the respective source regions, and that ion transport across the boundary layer is a one-way process with dawn-dusk asymmetry.

Eastman, T. E.↗
NASA NTRS1991

Ion burst event in the earth's dayside magnetosheath

The Medium Energy Particle Analizer instrument on the AMPTE/CCE Spacecraft provided ion angular distributions as rapidly as every 6 sec for H, He, and O at energies of 10 keV to 2 MeV in the dayside magnetosheath whenever the solar wind pressure compressed the magnetopause within 8.75 R(E), the CCE apogee. This paper discusses a burst of energetic particles in the subsolar magnetosheath and its association with rapid changes in the local magnetic field direction in such a way the magnetic field connected the spacecraft to the magnetopause during the enhancement. It is found that magnetosheath angular distributions outside the burst peaked at 90 deg pitch angles, whereas during the burst they exhibited field-aligned streaming either parallel or antiparallel to the magnetic-field combined with a clear earthward gradient. The clear earthward gradients at E not smaller than 10 KeV, the streaming, and the slope change in the burst-time magnetosheath spectrum at about 10 KeV suggest magnetospheric source for the burst-time not smaller than 10 KeV ions and heated solar wind for E less than 10 KeV.

Paschalidis, N. P.↗
NASA NTRS1990

Near equatorial signatures of dynamic auroral processes

Low energy electrons detected in the midmagnetosphere near the geomagnetic equator are hypothesized to originate from the auroral region near the ionospheric ends of the flux tubes. Electrons between 0.1 and 25 eV having pitch angle distributions peaked within 5 deg of B are routinely observed with electron spectrometers on the AMPTE/CCE satellite at radial distances of 7 R(e) to apogee at 9 R(e). If of auroral origin, as suggested, the detection of such fluxes provides important information about the auroral acceleration process, its dynamics, and about the effects of pitch angle scattering mechanisms in the magnetosphere.

Klumpar, D. M.↗
NASA NTRS1990

Wave-particle interactions on the FAST satellite

NASA's Fast Auroral Snapshot, or 'FAST' satellite, scheduled for launch in 1993, will investigate the plasma physics of the low altitude auroral zone from a 3500-km apogee polar orbit. FAST will give attention to wave, double-layer, and soliton production processes due to electrons and ions, as well as to wave-wave interactions, and the acceleration of electrons and ions by waves and electric fields. FAST will employ an intelligent data-handling system capacle of data acquisition at rates of up to 1 Mb/sec, in addition to a 1-Gbit solid-state memory. The data need be gathered for only a few minutes during passes through the auroral zone, since the most interesting auroral phenomena occur in such narrow regions as auroral arcs, electrostatic shocks, and superthermal electron bursts.

Temerin, M. A.↗
NASA NTRS1991

Mass comparisons of electric propulsion systems for NSSK of geosynchronous spacecraft

A model was developed and exercised to allow wet mass comparisons of three-axis stabilized communications satellites delivered to geosynchronous transfer orbit. The mass benefits of using advanced chemical propulsion for apogee injection and north-south stationkeeping (NSSK) functions or electric propulsion (hydrazine arcjets and xenon ion thrusters) for NSSK functions are documented. A large derated ion thruster is proposed which minimizes thruster lifetime concerns and qualification test times when compared to those of smaller ion thrusters planned for NSSK applications. The mass benefits, which depend on the spacecraft mass and mission duration, increase dramatically with arcjet specific impulse in the 500-600 s range, but are nearly constant for the derated ion thruster operated in the 2300-3000 s range. For a given mission, the mass benefits with an ion system are typically double those of the arcjet system; however, the total thrusting time with arcjets is less than one-third that with ion thrusters for the same thruster power.

Rawlin, V. K.↗