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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 289 records · Page 16
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NASA NTRS1976

Ballistic trajectories for Mercury Orbiter missions using optimal Venus flybys, a systematic search

The considered approach, which has been previously studied by Hollenbeck et al. (1973) makes use of a Venus gravity assist. The search for ideal trajectories for Mercury Orbiter missions involves a determination of trajectories with the lowest possible Mercury approach speed. Ideal Venus-to-Mercury transfers and opportunities are discussed. The second part of the reported investigation is concerned with the determination of suitable trajectories for the trip from earth to Venus. On the basis of the obtained data it appears that the best ten trajectories can deliver spacecraft from a low of 720 kg to a high of 1230 kg to orbits with 500 km periapse and 24 hr periods. The corresponding flight times are 790 days and 1243 days.

Bender, D. F.↗
NASA NTRS1977

The mass of Phobos from Viking flybys

The mass of the Martian satellite Phobos has been determined by processing radiometric tracking data obtained from the Viking-1 spacecraft during a series of 14 near encounters which occurred in February 1977. Distances of closest approach ranged from 89 to 213 km from the center of mass of the satellite. Our best estimate for the gravitational constant of Phobos is (6.6 plus or minus 0.8) x 10 to the -4th cu km/sq sec. The corresponding density of Phobos based on a volume estimate of 4800 plus or minus 960 cu km from Mariner 9 imaging is 2.0 plus or minus 0.5 gm/cu cm.

Christensen, E. J.↗
NASA NTRS1981

Operational compensation for effect of close Titan flyby on remainder of Voyager 1 Saturn near encounter

The satellite instrument pointing update process (SPUP) developed for the Voyager 1 Saturn encounter is assessed. At certain times, navigation errors translated into target pointing errors, impede camera operation. Two sigma pointing accuracy of 1.5 to 2.0 mrads per axis was required. The SPUP combines correction slews implemented by immediate action commands with preevent modifications. The process worked perfectly, producing good quality images of target areas.

Laeser, R. P.↗
NASA NTRS1986

Groundbased infrared imaging of Comet Giacobini-Zinner - The distribution of dust during the ICE flyby

A thermal-infrared image of Comet Giacobini-Zinner has been used to determine the spatial distribution of dust grains in the Comet's coma. In the present paper the results of this imaging which bear on the expected impact rate of dust grains on the International Cometary Explorer (ICE) are emphasized. The expected impact rate is calculated for a range of grain radii. For particle sizes comparable to those inferred for most comets, the impact rate is on the order of several hundred per second. This rate is in agreement with the predictions by Divine (1985), but it is more than two orders of magnitude larger than the rate observed by ICE if the observed impacts were on the spacecraft body. However, the observed impact rate is roughly comparable to that inferred from the infrared imaging if, as suggested by Gurnett et al. (1986), the impacts were on the ICE antennae, which had a much smaller cross-sectional area than the spacecraft body.

Campins, H.↗
NASA NTRS1986

Numerical simulation of spacecraft charging by impact-induced plasmas during a cometary flyby

A numerical model is developed for the interaction of a cometary probe, such as Giotto, with its environment, i.e., dust particles and gas. The spacecraft was set on a course to pass the comet at a velocity of 69 km/sec, so a chance existed that a potential field would form around the spacecraft and block lower energy particles from reaching the spacecraft instruments. The motion of electrons and ions is traced as a function of time to examine the evolution of the electric field, electric potential and the total space charge distributions on the surface of the spacecraft and its environment. Account is taken of the density of the particles and gas molecules at various distances from the comet, the collision energies involved, and the Giotto geometry. A solution is defined for the Poisson equation to describe the evolution of the plasma around Giotto, including the effects of ion collisions with the Al bumper protecting the spacecraft. The simulation predicts formation of an ion wake behind Giotto and the evolution of a positive potential on the order of 10 V around the spacecraft, i.e., sufficient for a positive potential barrier near the surface of the spacecraft.

Thiemann, H.↗
NASA NTRS1986

Concept for a manned Mars flyby

A concept is presented for a three man crew to fly by the planet Mars. The ground rule for the study is to execute the mission as quickly as possible which dictates using late 1990's technologies and space infrastructure. The proposed mission described herein uses a preliminary concept for the agency's Manned Orbit Transfer Vehicle (MOTV) and proposed space station elements. The space vehicle will depart from the LEO space station and is delivered to Low Earth Orbit (LEO) by a future launch vehicle of a Shuttle Derived Launch Vehicle (SDV) class. The trajectory parameters are chosen such that the mission duration is on the order of one year, with a two and one-half hour period within ten planetary radii of Mars. If the issues of acceptable crew g loads and entry vehicle heat load can be resolved, then the returning vehicle can aerobrake at Earth into a space station compatible orbit. Otherwise, a propulsive maneuver will be required to reduce vehicle velocity prior to Earth entry interface. It is possible to execute a mission of reasonable capability at an initial LEO departure weight of 716,208 pounds for the aerobraked case of 1,350,000 pounds for the propulsive case.

Barney B Roberts↗
NASA NTRS1986

A proposed comet nucleus penetrator for the Comet Rendezvous Asteroid Flyby mission

The importance of the study of comets has led NASA to plan a mission to rendezvous with comet Tempel 2 in 1997. Critical to the understanding of comets will be measurements of the nucleus material to determine its elemental and isotopic composition, its mechanical properties, and its thermal state and properties. this paper describes a proposal for a Comet Nucleus Penetrator to accomplish these measurement goals. The Comet Nucleus Penetrator will implant instruments into the comet's nucleus beneath a probable volatile-depleted surface mantle into material more representative of the bulk composition of the nucleus.

Swenson, B. L.↗
NASA NTRS1987

Some diatomic molecules from comet P/Halley's UV spectra near spacecraft flybys

The abundances of diatomic molecules seen in the UV both give clues to the parent compounds and help unravel the gas and ion mass spectrometry. From IUE spectra of comet Halley, upper limits on SH and CS(+) column densities and estimates of probable NO, S2, and SO are found. In particular, judged from the 226-nm gamma band, NO was relatively abundant at 2-8 x 10 to the 13th/sq cm on March 9-14. The production rate of S2 was around 1 x 10 to the 27th molecules/s at that time, but both showed day-to-day variability by 2-3 times.

Wallis, Max K.↗
NASA NTRS1991

On the lack of a magnetic signature of Triton's magnetospheric interaction on the Voyager 2 flyby trajectory

There is strong, albeit indirect, evidence for a sub-Alfvenic and transonic interaction between Triton and the Neptunian magnetosphere. A new inspection of magnetic field data around Triton encounter shows no evidence for the interaction. It is shown that this is due to the geometry of Triton's Alfvenic wings, which were probably too far from the spacecraft during the encounter. The situation is complicated by finite ion gyroradius effects, which tend to smear out the simple Alfven wings such as encountered at Io.

Neubauer, F. M.↗
NASA NTRS1991

Galileo orbit determination from launch through the first earth flyby

The data types used in the Galileo orbit determination process and the primary effects on the spacecraft for the first two trajectory legs of the mission are discussed. These types are: two-way coherent Doppler, two-way range, and delta differential one-way range. Attention is given to four primary nongravitational accelerations that affect the Galileo spacecraft: Delta(V) from TCMs, the Delta(V) from attitude updates, the Delta(V) from thruster maintenance events, and solar radiation pressure.

Pollmeier, V. M.↗
NASA NTRS1992

Magnetic field observations during the Ulysses flyby of Jupiter

The Ulysses magnetic field measurements confirmed the general structure of the dayside magnetosphere and showed that the importance of the current sheet dynamics extends well into the middle and outer magnetosphere. On the dusk side, the magnetic field was found to be swept back significantly toward the magnetotail. It is pointed out that the external current densities need to be modified with respect to previous observations on the inbound pass which shows that Jovian magnetic and magnetospheric models are highly sensitive to both the intensity and the structure assumed for the current sheet. Data obtained revealed that all boundaries and boundary layers in the magnetosphere have a very complex microstructure.

Balogh, A.↗
NASA NTRS1985

Comet Halley Returns. Voyager/Uranus Flyby

This videotape shows the five exploratory spacecraft, representing several countries, that will study Comet Halley: Giotto, Vega 1 and 2, Planet A, and Sakigaki.

Source record↗
NASA NTRS1993

Lunar impact basins: New data for the nearside northern high latitudes and eastern limb from the second Galileo flyby

During the December 1992 Galileo Earth/Moon encounter the northern half of the nearside, the eastern limb, and parts of the western farside of the Moon were illuminated and in view, a geometry that was complementary to the first lunar encounter in December, 1990, which obtained images of the western limb and eastern farside. The Galileo Solid State Imaging System (SSI) obtained multispectral images for these regions during the second encounter and color ratio composite images were compiled using combinations of band ratios chosen on the basis of telescopic spectra and laboratory spectra of lunar samples. Ratios of images taken at 0.41 and 0.76 micron are sensitive to changes in the slope in the visible portion of the spectrum, and ratios of 0.99 and 0.76 micron relate to the strength of near-infrared absorptions due to iron-rich mafic minerals (0.76/0.99 ratio) such as olivine and pyroxene. Results of the analyses of the compositional diversity of the crust, maria, and Copernican craters are presented elsewhere. Primary objectives for lunar basin analysis for the second encounter include analysis of: the north polar region and the Humboldtianum basin; the characteristics of the Imbrium basin along its northern border and the symmetry of associated deposits; the origin of light plains north of Mare Frigoris and associated with several other basins; the nature and significance of pre-basin substrate; the utilization of the stereo capability to assess subtle basis structure; the identification of previously unrecognized ancient basins; basin deposits and structure for limb and farside basins; and assessment of evidence for proposed ancient basins. These data and results will be applied to addressing general problems of evaluation of the nature and origin of basin deposits, investigation of mode of ejecta emplacement and ejecta mixing, analysis of the origin of light plains deposits, analysis of basin deposit symmetry/asymmetry, investigation of basin depth of excavation and crustal stratigraphy, and assessment of models for basin formation and evolution. Here we discuss some preliminary results concerning lunar impact basins, their deposits, and prebasin substrates, using the same approaches that we employed for the Orientale and South Pole-Aitken basins using the data from the first encounter.

Head, J. W.↗
NASA NTRS1995

Galileo flybys of Earth: The nature of the distant shock

We report on observations of the Earth's bow shock at unprecedentedly large downtail distances, some as remote as 360 R(sub E). Suprisingly, we find that even at these large distances, the bow shock signature remains clear. The cases we report are among the weakest shocks ever clearly identified. These shocks reveal patterns of field changes remarkably similar to those observed for stronger shocks. Indeed, several of the shocks could serve as textbook examples because they occur in unusually quiet and steady solar wind conditions. The quasi- perpendicular shocks are, in some cases preceded by whistler wave trains. Several of the shocks which have normal vectors in the transitional region between quasiperpendicular and quasiparallel are associated with large amplitude wave disturbances in the downstream plasma. Although low Mach number, these shocks are the source of large amplitude turbulence. We show a range of fits to the locations of the shock crossings, and argue that, for steady solar wind conditions, there is no sign of tail flapping. The displacement of the shock from the tail axis appears to be governed by the interplanetary magnetic field orientation as previously reported for Venus.

Kivelson, M. G.↗
NASA NTRS1970

HELIOS Configuration for Close Sun Flyby

This report is the documented result of an Internal study effort to examine possible spacecraft configurations for flight to within 0.20 AU of the sun. The objective of this study was to optimize the HELIOS spacecraft design for flights closer than 0.3 AU without jeopardizing the HELIOS Project costs or schedule. The results of the study meet this objective. In addition to this written report, an oral presentation has been prepared for the Second HELIOS Joint Working Group Meeting at GSFC on 27 April 1970. In the performance of this study, Messerschmitt-Bolkow-Blohm GMBH was assisted by the General Electric Company, Missile and Space Division, Valley Forge, Pennsylvania.

Lex, J.↗
NASA NTRS2000

The Cassini/Huygens Flyby of Jupiter

At the and of the year 2000 the Cassini/Huygens spacecraft will fly by the planet Jupiter at a range of 137 jovian radii. A preliminary assessment has indicated that the instruments aboard Cassini/Huygens can make measurements that will make unique contributions to audio of the jovian system. In this presentation we will discuss the status of the plans for observations of the jovian system by Cassini/Huygens. We shall also consider the possibilities for observations carried out in cooperation with the Galileo spacecraft presently in orbit about Jupiter, with other spacecraft, and with various observatories on the ground.

Matson, Dennis L.↗
NASA NTRS2001

Flyby Delivers Multiple Deep Jupiter Probes

In situ probes are the most reliable means for sampling composition and conditions deep in giant planet atmospheres. While exceeding its baseline mission, the Galileo probe entered a distinctly non-representative region of Jupiter (a 'hot spot') and apparently did not measure the full deep abundances of such important species as H2O and H2S, whose measured abundances were still increasing at the deepest datum. Multiple deep (approx. 100 bar) in situ probes minimize the hot spot risk, and address spatial variations and deep constituent abundances. Additional information is contained in the original extended abstract.

Spilker, T. R.↗
NASA NTRS2001

Galilean Satellite Surface Non-Ice Constituents: New Results from the Cassini/Huygens VIMS Jupiter Flyby in the Context of the Galileo NIMS Results

The Cassini mission Visible and Infrared Mapping Spectrometer (VIMS) is currently returning data for the Galilean satellites. Examples of the new satellite data and the initial interpretations will be presented in the context of the Galileo NIMS data and results. Additional information is contained in the original extended abstract.

McCord, T. B.↗