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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 199 records · Page 11
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NASA NTRS1983

Press Kit: Project RCA (Satcom 1R)

To replace the RCA SATCOM 1 satellite which provided Earth communications for seven years, NASA is to launch RCA SATCOM 1R using a Delta 3924 launch vehicle. The satellite is to be placed at 139 degrees W longitude, 35,900 kilometers (23,000) miles above the equator. On the seventh apogee, the kick motor will be fired to produce a near synchronous orbit. Satellite life, with continuous full power, is designed to be 10 years. Features of the satellite and launch operations are described.

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NASA NTRS1983

The RCA-F/Delta launch

The Delta 3924 launch vehicle configuration which incorporates the extended long tank Thor booster, nine Castor 4 strap-on motors, the AJ-118 second stage and the TE 364-4 third stage is to place into a synchronous transfer orbit, the second in a series of high-traffic capacity, 24 transponder communications satellites. Three days after launch, the satellite's apogee kick motor circularizes the orbit at geosynchronous altitude of 19,300 NM above the equator at approximately 128 degrees W longitude. The satellite can service commercial and government voice, digital and video communications requirements between Alaska and CONUS. The communications payload, mission requirements and spacecraft systems and subsystems are described.

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NASA NTRS1982

Magsat data availability

It is pointed out that a new era in near-earth magnetic field measurements began with NASA's launch of Magsat in October 1979 into a twilight, sun-synchronous orbit with 96.76 deg inclination, 561-km apogee, and 352-km perigee. A cesium vapor and a fluxgate magnetometer were employed to measure the magnetic field. A measurement of the spacecraft attitude to 20 arcseconds was required to achieve 6 nT (nanotesla) accuracy in the component measurements. This was accomplished with the aid of two star cameras on board the spacecraft and a sun sensor attached to the vector magnetometer. Magsat remained in orbit until June 11, 1980. Magsat has conducted the first truly global geomagnetic survey since the studies performed by the Polar Orbiting Geophysical Observatory (POGO) satellites. A global vector survey was provided of the main geopotential field and lower altitude measurements of crustal anomalies were conducted. Details concerning the availability of these data are discussed.

Langel, R. A.↗
NASA NTRS1983

Geocoronal imaging with Dynamics Explorer - A first look

The ultraviolet photometer of the University of Iowa spin-scan auroral imaging instrumentation on board Dynamics Explorer-1 has returned numerous hydrogen Lyman alpha images of the geocorona from altitudes of 570 km to 23,300 km (1.09 R sub E to 4.66 R sub E geocentric radial distance). The hydrogen density gradient is shown by a plot of the zenith intensities throughout this range, which decrease to near celestial background values as the spacecraft approaches apogee. Characterizing the upper geocorona as optically thin (single-scattering), the zenith intensity is converted directly to vertical column density. This approximation loses its validity deeper in the geocorona, where the hydrogen is demonstrated to be optically thick in that there is no Lyman alpha limb brightening. Further study of the geocoronal hydrogen distribution will require computer modeling of the radiative transfer. Previously announced in STAR as N83-20889

Rairden, R. L.↗
NASA NTRS1983

Observational evidence of Z and L-O mode waves as the origin of auroral kilometric radiation from the Jikiken (EXOS-B) satellite

The present investigation has the objective to present new information on the polarization of the auroral kilometric radiation detected by the Jikiken (EXOS-B) satellite. On September 16, 1978, the satellite had been launched into an orbit with altitudes of the initial apogee and perigee of 30,050 km and 250 km, respectively, and an inclination of -31 deg. This orbit provides the conditions for suitable observations of the spectra of auroral kilometric radiation (AKR) in the proximity of the source regions. A study has been conducted of the discovered Z mode waves. These waves are found to be refracted to a nearly perpendicular direction of propagation with respect to the magnetic field vector within a very short distance of the source position. AKR spectra have been observed at positions where the ambient plasma defines a lower edge of the spectra by the cutoff effects of the waves propagating in the local plasma.

Oya, H.↗
NASA NTRS1983

A portable real-time data processing system for standard meteorological radiosondes

The UMET-1 is a microprocessor-based portable system for automatic real-time processing of flight data transmitted from the standard RAWINSONDE upper atmosphere meteorological balloonsonde. The first 'target system' is described which was designed to receive data from a mobile tracking and telemetry receiving station (TRADAT), as the balloonsonde ascends to apogee. After balloon-burst, the UMET-1 produces user-ready hardcopy.

Staffanson, F. L.↗
NASA NTRS1984

Separation and Staging Mechanisms for the Indian SLV-3 Launch Vehicle

A unique separation and jettison system for the ascent fairing and a staging system for the apogee motor of the first Indian satellite launch vehicle are described. Design features, development problems, and mission constraints are discussed in addition to the solutions adopted. A qualification summary is included for each system, and flight results obtained from SLV-3 launches are described.

Abdulmajeed, M. K.↗
NASA NTRS1984

Application of TOS/AMS to TDRS E and F

The development of the Transfer Orbit Stage (TOS) and the study of an Apogee and Maneuvering Stage (AMS) to be used in conjunction with the TOS are presented. A definition of the TOS/AMS configuration is provided along with a detailed design analysis including layout drawings, component definition, performance, sts and spacecraft interface definition, schedules, cost estimates, and specifications documents.

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NASA NTRS1982

Delta capability for launch of communications satellites

The evolution of capabilities and the current performance levels of the Delta launch vehicle are outlined. The first payload was the Echo I passive communications satellite, weighing 179 lb, and placed in GEO in 1960. Emphasis since then has been to use off-the-shelf hardware where feasible. The latest version in the 3924 first stage, 3920 second stage, and Pam D apogee kick motor third stage. The Delta is presently equipped to place 2800 lb in GEO, as was proven with the 2717 lb Anik-D1 satellite. The GEO payload placement performance matches the Shuttle's, and work is therefore under way to enhance the Delta performance to handle more massive payloads. Installation of the Castor-IV solid motor separation system, thereby saving mass by utilizing compressed nitrogen, rather than mechanical thrusters to remove the strap-on boosters, is indicated, together with use of a higher performance propellant and a wider nose fairing.

Grimes, D. W.↗
NASA NTRS1984

Observation of double-layer-like structures at rocket altitudes

Two hundred and thirty large amplitude electric field pulses in a rocket flight to an apogee of 585 km over an aurora have been observed. While the limitations of the instrumentation only allow limits to be set on the characteristics of these pulses, the limits are nevertheless significant. A typical lower limit on the potential jump of the pulses is about .4 volts. Many of the pulses show structure at a frequency very close (less than 2 percent) to the proton-cyclotron frequency.

Kellogg, P. J.↗
NASA NTRS1984

Correlated dynamical changes in the near-earth and distant magnetotail regions - ISEE 3

It is pointed out that the redeployment of ISEE 3 from its continuous monitoring of the solar wind in a large orbit about the upstream Lagrangian point to an extended magnetotail orbit has afforded an opportunity for deep-tail passage of October 1982, and in the radial range from 200 to 220 R(E) during the near-apogee part of the second tail passage in January-February 1983. Attention is given to instrumentation and data sets, spacecraft positions, and observational data.

Baker, D. N.↗
NASA NTRS1985

Summary Presentation of the Transportation Panel

Space mission scenarios are presented in which tethering is utilized. The technical and cost benefits are considered along with practicality and operational requirements. The mission scenarios considered include: (1) space shuttle delivery of payloads to higher orbits; (2) the downward release of the external tank from a shuttle; (3) space station altitude reboost using shuttle angular momentum; (4) shuttle docking to space station tether; (5) using shuttle based tether to assist launch of upper stage to higher energy orbits; (6) using space station tether to deploy payloads to higher orbits with momentum accumulator; (7) using tethers to discard first stages or apogee motors; and (8) planetary applications of tethers.

Hunter, M. W.↗
NASA NTRS1985

Radiation exposure and performance of multiple burn LEO-GEO orbit transfer trajectories

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.

Gorland, S. H.↗
NASA NTRS1984

Plasmasheet magnetic fields in the distant tail

Data from two deep passes of ISEE-3 through the earth's magnetotail are used to discuss the evolution of the plasmasheet magnetic field as a function of radial distance and geomagnetic activity (Kp). Attention is focused on plasmasheet intervals lasting at least 10 min as recorded during passes lasting 3 and 5 mos with apogees of 221 and 238 earth radii (ER). The dependencies of the By and Bz components on Kp were minimal, although Bz displayed a radial dependence. No relationship was observed between By and Bz. The Bz component changed from a northward orientation at 60-100 ER to a N-S dependence at 200-238 ER. Variations in field measurements indicated turbulence throughout the plasmasheet, also independent of Kp. The data support formation of a plasmoid during periods of high Kp, and can serve as limiting conditions for developing more accurate magnetotail models.

Tsurutani, B. T.↗
NASA NTRS1984

Applications of space tethers

The dynamics of orbiting tethered bodies are reviewed and several practical aplications are examined. Two tethered masses in orbit will seek a local vertical orientation and a stable equilibrium, with energy transferred to the 'upper' object. The tether tensions are provided by accelerations as low a 0.0004 g., permitting long tethers an relatively large masses at the ends. The Shuttle can send a payload into a transfer orbit by placing it at the upper end of the tether, unreeling the tether, then releasing the tether and thereby imparting the excess energy to the satellite while the Orbiter falls to a lower perigee. A 10 ton payload could be unreeled on a 148 km tether, released to a 12 n. mi. apogee, and the Orbiter would be in full deorbit. Similarly, the Orbiter can tether down to deorbit form the Space Station, boosting the Station to a higher orbit. The station can then unreel a large satellite, release it to a higher orbit, thereby returning to the stations original orbit. Unreeling a wire 10 km from the Space station and having the wire cut the earth's magnetic field lines, then closing the contact between the upward and lower ends of the wire, can, with modifications, either provide power or thrust without propellants for the Station.

Bekey, I.↗
NASA NTRS1985

A simplified guidance algorithm for lifting aeroassist orbital transfer vehicles

The derivation, logic, and performance of a simplified atmospheric guidance algorithm for aeroassist orbital-transfer vehicles (AOTVs) are presented. The algorithm was developed to meet the demands for an aerobraking trajectory guidance technique that was uncomplicated, easily integrated into existing trajectory programs, adaptable to a range of vehicle aerodynamic configurations, capable of performance equivalent to currently available guidance programs in compensating for dispersions in entry conditions, atmospheric conditions, and aerodynamic characteristics. The result was a hybrid lifting guidance algorithm combining the method of reference-profile generation with the method of predictor/corrector schemes. The resulting performance is good (less than 3 n.m. error from desired apogee despite uncertainties of + or - 50 percent atmospheric density, + or - 0.2 deg entry flight-path angle, or + or - 50 percent L/D. Combinations of these same dispersions with lesser magnitudes have also been successful, although performance with density 'pockets' within the atmosphere requires more analysis.

Cerimele, C. J.↗
NASA NTRS1985

CCE plasma wave observations during the storm of September 4, 5, 1984

Near 0700 on September 4, 1984 a series of interplanetary discontinuities arrived at earth when the AMPTE Charge Composition Explorer (CCE) was near apogee. During the next few hours the spacecraft passed in and out of the magnetosheath. At the magnetopause boundary, the CCE wave instrument detected strong electron plasma oscillations, weaker electromagnetic waves at the electron plasma frequency, and broadband electrostatic waves. During the subsequent perigee passes on September 4 and 5, the wave observations of upper hybrid resonance emissions, continuum radiation, electrostatic noise bands and unusual low latitude auroral kilometic radiation were used to monitor significant variations in the magnetospheric characteristics as the main storm phases developed.

Scarf, F. L.↗