Central data system concepts for spacecraft data management.
Spacecraft central data system for deep space solar probe data management
Bello, L. M.↗
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A common solar electric upper stage for multi-mission applications.
The concept of using a solar-electric upper stage for multi-mission application is practical, economical, and versatile approach to space expMission capabilities include a Mercury orbiter, asteroid and comet rendezvous, a solar probe, and extra-ecliptic probe, and outer planet flybys and orbiters. The 17.5-kw vehicle has an injected mass of 1500 to 2500 kg and carries up to 500 kg of attached or separable payload packages. Mission characteristics, performance tradeoffs and a concepegn configuration are presented, and program plans, cost estimates and advanced technology requirements are identified.
Meissinger, H. F.↗
Titan/Centaur: NASA's newest launch vehicle
Titan/Centaur is NASA's last new expendable launch vehicle prior to the advent of the space shuttle. Titan/Centaur is an adaptation of the Air Force Titan 3 booster with an improved version of the Centaur stage and a new 4.2 meters payload fairing. Titan/Centaur is initially being used for high performance escape missions (Helios Solar Probe - 340 kilograms' Viking Mars Orbiter and Lander - 3,629 kilograms, and Mariner Jupiter/Saturn Fly-Bys at 771 kilograms, but is also particularly suited for larger spacecraft in synchronous orbits (transfer - 7,031 kilograms and equatorial, with three Centaur burns - 3,175 kilograms). The program which began in 1965 with internal NASA feasibility studies will culminate in a proof flight launch in early 1974. With the new payload fairing, which also encloses Centaur, payloads of nearly 8.5 meters long and 3.8 meters in diameter can be accommodated.
Stofan, A. J.↗
Titan/Centaur - NASA's newest launch vehicle.
Titan/Centaur is NASA's last 'new-expendable' launch vehicle prior to the advent of the Space Shuttle. Titan/Centaur is an adaptation of the Air Force Titan III booster with an improved version of the Centaur stage and a new 4.2-meter payload fairing. Titan/Centaur is initially being used for high performance escape missions (Helios Solar Probe - 340 kilograms, Viking Mars Orbiter and Lander - 3,629 kilograms, and Mariner Jupiter/Saturn Fly-Bys at 771 kilograms), but is also particularly suited for larger spacecraft in synchronous orbits (transfer - 7,031 kilograms and equatorial, with three Centaur burns - 3,175 kilograms). The program which began in 1965 with internal NASA feasibility studies will culminate in a 'proof flight' launch in early 1974. With the new payload fairing, which also encloses Centaur, payloads nearly 8.5 meters long and 3.8 meters in diameter can be accommodated.
Stofan, A. J.↗
Project Helios-A
The Helios-A solar probe which will fly within 28 million miles of the sun is described as a joint American and German project. The spacecraft and instrument designs, planned experiments, and mission are briefly discussed.
Source record↗
Spin test on HELIOS louver
The effect of the spin motion of the solar probe on the characteristic of the louver was investigated. The qualification test set-up and procedure is described along with tests results.
Joo, F.↗
The large-scale magnetic field in the solar wind
A literature review is presented of theoretical models of the interaction of the solar wind and interplanetary magnetic fields. Observations of interplanetary magnetic fields by the IMP and OSO spacecraft are discussed. The causes for cosmic ray variations (Forbush decreases) by the solar wind are examined. The model of Parker is emphasized. This model shows the three dimensional magnetic field lines of the solar wind to have the form of spirals wrapped on cones. It is concluded that an out-of-the-ecliptic solar probe mission would allow the testing and verification of the various theoretical models examined. Diagrams of the various models are shown.
Burlaga, L. F.↗
Titan/Centaur D-1TTC-5 Helios B flight data report
The fourth operational flight of the newest NASA unmanned launch vehicle is reported. The spacecraft was the Helios B, the second of two solar probes designed and built by the Federal Republic of Germany. The primary mission objective, to place the Helios spacecraft on a heliocentric orbit in the ecliptic plane with a perihelion distance of 0.29 AU, was successfully accomplished. After successful injection of the Helios spacecraft, a series of experiments were performed with the Centaur stage to demonstrate its operational capabilities. All objectives of the extended mission phase were successfully met. This report presents the analysis of the launch vehicle flight data for the primary mission phase of the TC-5 flight.
Adams, K. A.↗
The Helios mechanical despin drive assembly for the high-gain antenna reflector
Helios is the German-American solar probe which comes within 0.31 Astronomical Units of the sun. A special thermal design and a dry lubrication system have resulted in successful operation up to now, with Helios having finished its first orbit around the sun.
Mueller, E. J. W.↗
Solar flare effects on the zodiacal light
Results are reported for an observational and theoretical study of possible solar-flare effects on the zodiacal light. A seven-year search for flare-induced brightness variations in the light is described which discovered no significant changes in either the level of brightness from night to night or the shape of the main zodiacal-light cone at elongations greater than 25 deg from the sun. Several possible dynamical effects of solar flares on the zodiacal dust cloud are investigated theoretically, including increased ion drag from a passing shock wave, possible rotational bursting of dust particles as a result of ion impacts, and fluorescence of the dust particles. It is found that the kinetic energy carried by shock-front ions is not sufficient to cause the dust to fluoresce, that increased ion drag may be significant only at heliocentric distances less than 0.1 AU, and that particles larger than 10 microns cannot attain bursting speeds at the appropriate distances. The question is considered of whether changes in the brightness of the polarized component as a result of variations in electron number density can be observed from earth or the Helios solar probe.
Misconi, N. Y.↗
The Helios program and the sun
Helios A and B are the first two missions inside the orbit of the Mercury towards the sun. They were launched from Cape Kennedy December 10, 1974 and January 15, 1976 respectively. The interplanetary cruise in the ecliptic plane carried the Helios Solar Probes in an ecliptical orbit around the sun to perihelions as close as 0.31 (Helios A) and 0.29 (Helios B) Astronomical Units to the sun. In this technical paper the scientific mission and German and American plans and design versus accomplished mission are presented by the German and United States Project Managers and the Mission Operations Manager. A brief outline of the scope of the project, spacecraft and experiments development, integration and test programs is given. Engineering and system performance results from the Helios A and B flights, which succeeded in passing closer to the sun than any previous spacecraft, are presented. Some of the preliminary scientific findings of the ten active and two passive experiments of this ambitious German/United States cooperative project are outlined.
Ousley, G. W.↗
Solar neutron spectroscopy near the sun
A brief note is summarized to show the importance of solar neutron observations for the advancement of phenomena crucial for solar physics, and to suggest the constraints which must be placed on the Solar Probe Mission for carrying out studies of this kind.
Simpson, J. A.↗
What is the fate of interplanetary dust
The following general picture of the interplanetary dust is presented: (1) size distribution; (2) spatial distribution; (3) composition; (4) dynamics; and (5) origin. The solar probe mission provides a unique opportunity to study the evolution of the interplanetary dust and its eventual destruction near the sun. Two destructive processes (fragmentation and vaporization) of interplanetary dust are discussed.
Hanner, M. S.↗
Drag-free estimation feasibility study
A drag compensation system for solar probes and other spacecraft that require a drag-free capability is presented. Estimation techniques, derived from modern control theory, are proposed.
Schaechter, D. B.↗
Astrodynamics 1979; Proceedings of the Conference, Provincetown, Mass., June 25-27, 1979. Parts 1 & 2
Topics are presented on navigation systems, inner planets, comets and asteroids, outer planets, earth orbital applications, and computational methods. Individual subjects include an overview of the Navstar Global Positioning System and the Navy Navigation Satellite System, the solar probe mission, Uranus mission options, as well as a study of lifetimes of geosynchronous transfer orbits, and the price of oil in the year 2000.
Penzo, P.↗
Gravitational radiation detection with spacecraft Doppler tracking - Limiting sensitivities and prospective missions
The prospects of using spacecraft Doppler tracking, in NASA missions, for the detection of gravitational waves are examined. The sensitivity limits of such detection are characterized in terms of plasma scintillation, troposphere scintillation, receiver noise, MDA and ODA quantization error, and clock jitter. Current and possible future NASA missions that will involve gravitational wave experiments are briefly reviewed, including the Galileo, solar polar, Halley/Tempel-2, and solar probe missions.
Estabrook, F. B.↗
Hectometer and kilometer solar observations
Three dimensional 'snapshots' of the large scale solar magnetic field topology as well as the solar wind electron density distribution from about 0.1 to 1 AU are obtained by tracking traveling solar radio bursts at the hectometer and kilometer wavelengths with instruments aboard the ISEE-3 satellite and the HELIOS-2 solar probe. Both instruments observe in the frequency range from 30 kHz to a 1 MHz and both are equipped with dipole antennas located in the vehicle spin plane. ISEE-3 also has a dipole along the spin axis and the signals from the two ISEE-3 antennas are combined to give the aximuth and elevation angles of the radio source. Triangulation between HELIOS-2 and ISEE-3 provides the additional observation necessary to determine uniquely the position of the radio source in space at each observing frequency.
Stone, R. G.↗
Radial evolution of ion distribution functions
A survey of solar wind ion velocity distributions and derived parameters (temperature, ion differential speed, heat flux, adiabatic invariants) is presented with emphasis on the heliocentric distance range between 0.3 and 1 AU traversed by the Helios solar probe. The radial evolution of nonthermal features are discussed which are observed to be most pronounced at perihelion. Within the framework of quasilinear plasma theory, wave particle interactions that may shape the ion distributions are considered. Some results of a self consistent model calculation are presented accounting for ion acceleration and heating by resonant momentum and energy exchange with ion cyclotron and magnetosonic waves propagating away from the Sun along the interplanetary magnetic field. Another tentative explanation for the occurrence of large perpendicular proton temperatures is offered in terms of heating by Landau damping of lower hybrid waves.
Marsch, E.↗