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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 109 records · Page 6
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NASA NTRS1987

Timescales for planetary accretion and the structure of the protoplanetary disk

Models of planetary accretion which assume the mass of condensable matter in the protoplanetary disk was equal to that present in the planets today predict accretion timescales for the outer planets approximately or less than 10 to the 8th years. Such timescales are inconsistent with observations of star forming regions, which suggest that most of the gas in disks around one solar mass is removed in a few x 10 to the 6th years. A unified scenario was outlined for solar system formation consistent with astrophysical constraints. Jupiter's core could have grown by runaway accretion of planetesimals to a mass sufficient to initiate rapid accretion of gas in times of order of 500,000 to 5,000,000 years, provided the surface density of solids in its accretion zone was at least 5 to 10 times greater than that required by minimum mass models of the protoplanetary disk. The inner planets and the asteroids can be accounted for in this picture if the surface density of the solar nebula was relatively uniform out to Jupiter's orbit. The formation of such a protoplanetary disk requires significant transport of mass and angular momentum, and is consistent with viscous accretion disk models of the solar nebula.

Lissauer, Jack J.↗
NASA NTRS1979

Aerocapture vehicle mission design concepts for the inner and outer planets

The paper presents mission design concepts using an aerocapture vehicle for future missions to the inner and outer planets which require substantial payloads in orbit that can not be readily realized using the present Space Transportation System (STS). Aerocapture is a mission design technique that utilizes aerodynamically controlled atmospheric entry to capture payloads into orbit as opposed to a completely propulsive orbit insertion. Results are presented which demonstrate great performance gains and acceptable accuracy using aerocapture. Attention is also given to the potential for aerocapture vehicle system design commonality for different missions, in order to demonstrate the ability of aerocapture as an interplanetary delivery technique to substantially augment the STS performance capabilities.

Cruz, M. I.↗
NASA NTRS1972

Comparison of the solar sail with electric propulsion systems

The propulsive efficiencies of the solar sail and of electric propulsion systems are compared on the basis of specific impulse. It is shown that the solar sail is more efficient at one a.u. for mission durations greater than about two months, that the advantage is increased for missions toward the inner planets, and that the same conclusions are reached when the comparison is based on maximizing the momentum transferred to the payload. Other factors that will influence the choice of a propulsion system for a specific mission are mentioned.

Macneal, R. H.↗
NASA NTRS1972

Physico-chemical processes in the solar nebula, as inferred from meteorites.

Many properties of meteorites suggest that they formed in a cooling solar nebula. Chemical differences among chondrites, encompassing nearly all known elements, can be accounted for by as few as 4 processes: loss of an early condensate (above 1300 K), loss of nickel-iron (1050 to 700 K), partial remelting of the condensate (600 to 450 K), and accretion (500 to 360 K). The same processes seem to have affected the inner planets. Reasonably concordant accretion temperatures are obtained by various cosmothermometers. These accretion temperatures are 3 times higher than present black-body temperatures in the asteroid belt, suggesting that accretion took place only during a high-temperature stage of necessarily short duration.

Anders, E.↗
NASA NTRS1973

Skylab experiments. Volume 5: Astronomy and space physics

The astronomy and space physics investigations conducted in the Skylab program include over 20 experiments in four categories to explore space phenomena that cannot be observed from earth. The categories of space research are as follows: (1) phenomena within the solar system, such as the effect of solar energy on Earth's atmosphere, the composition of interplanetary space, the possibility of an inner planet, and the X-ray radiation from Jupiter, (2) analysis of energetic particles such as cosmic rays and neutrons in the near-earth space, (3) stellar and galactic astronomy, and (4) self-induced environment surrounding the Skylab spacecraft.

Source record↗
NASA NTRS1974

Mariner Venus/Mercury 1973 solar radiation force and torques

The need for an improvement of the mathematical model of the solar radiation force and torques for the Mariner Venus/Mercury spacecraft arises from the fact that this spacecraft will be steering toward the inner planets (Venus and Mercury), where, due to the proximity of the Sun, the effect of the solar radiation pressure is much larger than it was on the antecedent Mariner spacecraft, steering in the opposite direction. Therefore, although the model yielded excellent results in the case of the Mariner 9 Mars Orbiter, additional effects of negligible magnitudes for the previous missions of the Mariner spacecraft should now be included in the model. This study examines all such effects and incorporates them into the already existing model, as well as using the improved model for calculation of the solar radiation force and torques acting on the Mariner Venus/Mercury spacecraft.

Georgevic, R. M.↗
NASA NTRS1975

Preliminary geologic terrain map of Mercury

A geologic terrain map of Mercury has been constructed by use of the photogeologic methods employed for the moon and Mars. The oldest and most widespread unit, intercrater plains, forms nearly level to rolling surfaces on which are superposed numerous secondary impact craters. This unit may represent a very old surface that predates the last heavy bombardment of the inner planets. The effects of this bombardment are recorded in a second widespread unit, heavily cratered terrain, consisting of closely spaced craters and basins from 30 km to several hundred kilometers in diameter. Units formed by excavation of the 1300-km-diameter Caloris basin are widespread on one hemisphere of the planet. The development of the Caloris basin was followed relatively quickly by emplacement of widespread plains materials, most of which are probably volcanic.

Trask, N. J.↗
NASA NTRS1976

Optimal three-dimensional reusable tug trajectories for planetary missions including correction for nodal precession

Equations are derived by using the maximum principle to maximize the payload of a reusable tug for planetary missions. The analysis includes a correction for precession of the space shuttle orbit. The tug returns to this precessed orbit (within a specified time) and makes the required nodal correction. A sample case is analyzed that represents an inner planet mission as specified by a fixed declination and right ascension of the outgoing asymptote and the mission energy. The reusable stage performance corresponds to that of a typical cryogenic tug. Effects of space shuttle orbital inclination, several trajectory parameters, and tug thrust on payload are also investigated.

Borsody, J.↗
NASA NTRS1976

Performance of a recoverable tug for planetary missions including use of perigee propulsion and corrections for nodal regression

Mathematical equations are derived by using the Maximum Principle to obtain the maximum payload capability of a reusable tug for planetary missions. The mathematical formulation includes correction for nodal precession of the space shuttle orbit. The tug performs this nodal correction in returning to this precessed orbit. The sample case analyzed represents an inner planet mission as defined by the declination (fixed) and right ascension of the outgoing asymptote and the mission energy. Payload capability is derived for a typical cryogenic tug and the sample case with and without perigee propulsion. Optimal trajectory profiles and some important orbital elements are also discussed.

Borsody, J.↗
NASA NTRS1976

Planetary missions in the Shuttle era

A conservative fifteen-year plan for planetary exploration is presented in which the Space Shuttle is considered as just a basic transportation system that should be quite economical and have excellent reliability. It is noted that these planned missions are limited by the out-of-orbit escape capability of the Shuttle's Interim Upper Stage (IUS), rather than by the orbital payload capability of the Shuttle itself. A mission model is provided in which a rather even balance is maintained among missions to the inner planets, the outer planets, the comets and asteroids, and interplanetary missions out of the ecliptic plane; the cost estimate for this model is plotted. Launch requirements for the various missions are compared with the performance available from various IUS candidates under evaluation, and it is shown that even the lower-performance candidates can be brought up to the capability of the current Titan IIIE/Centaur/TE-364 expendable launch vehicle, which is adequate for most of the missions in the program. Missions which require higher-performance IUS options are noted, including the Mariner Jupiter and Saturn Orbiters.

Kraemer, R. S.↗
NASA NTRS1976

Performance of a recoverable Tug for planetary missions including use of perigee propulsion and corrections for nodal regression

Mathematical equations are derived by using the Maximum Principle to obtain the maximum payload capability of a reusable Tug for planetary missions. The mathematical formulation includes correction for nodal precession of the Space Shuttle orbit. The Tug performs this nodal correction in returning to this precessed orbit. The sample case analyzed represents an inner planet mission as defined by the declination (fixed) and right ascension of the outgoing asymptote and the mission energy. Payload capability is derived for a typical cryogenic Tug and the sample case with and without perigee propulsion. Optimal trajectory profiles and some important orbital elements are also discussed.

Borsody, J.↗
NASA NTRS1976

Solar sail mission applications

The paper discusses the concept and the current baseline configuration of a reusable solar sail vehicle using light pressure for propulsion. The range of characteristic accelerations which solar sail vehicles might achieve during early years of operation is estimated to be from 0.2 to 1.3 mm/sq sec, with overall sail efficiency about 80 to 90%. Operating without the expenditure of propellant, the vehicle has the potential of delivering large payloads throughout the solar system. Detailed attention is given to various possible missions of the solar sail vehicle operating as an Interplanetary Shuttle. The vehicle may deliver payloads to the inner planets, asteroids, short period comets, or sun polar orbits and then return to earth, possibly with samples. It may also be used for outer planet missions or solar system escape. An 800-m sail may return samples totaling 200 kg from Mars and deliver them to an earth orbital laboratory. The first mission for the solar sail may be rendezvous with Halley's comet in 1982.

Wright, J. L.↗
NASA NTRS1974

Geologic guide to the island of Hawaii: A field guide for comparative planetary geology

With geological data available for all inner planets except Venus, we are entering an era of true comparative planetary geology, when knowledge of the differences and similarities for classes of structures (e.g., shield volcanoes) will lead to a better understanding of general geological processes, regardless of planet. Thus, it is imperative that planetologists, particularly those involved in geological mapping and surface feature analysis for terrestrial planets, be familiar with volcanic terrain in terms of its origin, structure, and morphology. One means of gaining this experience is through field trips in volcanic terrains - hence, the Planetology Conference in Hawaii. In addition, discussions with volcanologists at the conference provide an important basis for establishing communications between the two fields that will facilitate comparative studies as more data become available.

Greeley, R.↗
NASA NTRS1977

SUNSPOT: A computer program for producing optimal solar sail planetocentric trajectories

The input, output and subroutines, including listings, for the SUNSPOT code are described. SUNSPOT can calculate time optimal planetocentric trajectories including orbit-to-orbit transfer and orbit to a subescape point. Trajectories about the the four inner planets can be calculated, and shadowing, oblateness, and solar motion may be included. A penalty function may be included to prevent trajectories which intersect the planet's surface.

Sackett, L. L.↗
NASA NTRS1977

Optimal solar sail planetocentric trajectories

The analysis of solar sail planetocentric optimal trajectory problem is described. A computer program was produced to calculate optimal trajectories for a limited performance analysis. A square sail model is included and some consideration is given to a heliogyro sail model. Orbit to a subescape point and orbit to orbit transfer are considered. Trajectories about the four inner planets can be calculated and shadowing, oblateness, and solar motion may be included. Equinoctial orbital elements are used to avoid the classical singularities, and the method of averaging is applied to increase computational speed. Solution of the two-point boundary value problem which arises from the application of optimization theory is accomplished with a Newton procedure. Time optimal trajectories are emphasized, but a penalty function has been considered to prevent trajectories which intersect a planet's surface.

Sackett, L. L.↗
NASA NTRS1978

Icy craters on the Galilean satellites

The high degree of echo depolarization observed for linearly polarized incident waves in the case of radar observations of Europa, Ganymede, and Callisto is consistent with a rough, icy surface. Measurements with circularly polarized waves, however, conducted in 1976 suggest that the types of surface irregularities found on the Galilean satellites must be very different from those on the moon and the inner planets. A description is presented of an investigation in which geometrical optics and the Stokes-vector formalism are employed to examine several possible configurations which could cause the circular polarization transmitted to exceed unity. On the basis of the obtained results it appears that a model which postulates that significant parts of the surfaces of the three satellites are covered with an icy layer at least several kilometers thick and saturated with hemispherical craters can explain nearly all the observed radar behavior.

Ostro, S. J.↗
NASA NTRS1978

Planetary benchmarks

Design criteria and technology requirements for a system of radar reference devices to be fixed to the surfaces of the inner planets are discussed. Offshoot applications include the use of radar corner reflectors as landing beacons on the planetary surfaces and some deep space applications that may yield a greatly enhanced knowledge of the gravitational and electromagnetic structure of the solar system. Passive retroreflectors with dimensions of about 4 meters and weighing about 10 kg are feasible for use with orbiting radar at Venus and Mars. Earth-based observation of passive reflectors, however, would require very large and complex structures to be delivered to the surfaces. For Earth-based measurements, surface transponders offer a distinct advantage in accuracy over passive reflectors. A conceptual design for a high temperature transponder is presented. The design appears feasible for the Venus surface using existing electronics and power components.

Uphoff, C.↗