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At least 343 records · Page 19

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NASA NTRS1986

Comment

Frank et al.'s (1986) suggestion that the earth is impacted by small (100-Mg) comets at the rate of 20/min is reconsidered in the light of recent comet models. The possibility of such a swarm of comets is found to be problematical because of the large number of comets required and because thermal stability arguments, while not excluding such a possibility, imply that it is implausible. In a reply, Frank et al. reaffirm their findings that such small comets, following direct elliptical orbits about the sun, are distributed in a disk centered on the sun and lying near the ecliptic plane at heliocentric radial distances 1-10,000 AU. The presence of these comets in the inner solar system is attributed to the gravitational action of the outer planets, passing stars, or interstellar clouds on comets is more distant orbits.

Mckay, C. P.↗

NASA NTRS1986

Efficient inverse solution of Kepler's equation

A bicubic polynomial approximation to Kepler's equation for elliptic orbits is shown to provide accurate starting values for efficient numerical solution of this equation for eccentric anomaly. In the approximate equation, a cubic in mean anomaly is set equal to a cubic in eccentric anomaly. The coefficients in the two cubics are obtained as functions of eccentricity by specifying values of function and slope at the midpoint and the endpoint of the complete interval (0 to pi). The initial estimate of eccentric anomaly to use in an iteration formula is obtained by evaluating the cubic in mean anomaly and finding the single real root of the cubic in eccentric anomaly. Numerical results are presented which indicate that the estimate accuracy of this method is roughly an order of magnitude better than that of other recently-reported formulas.

Boltz, Frederick W.↗

NASA NTRS1987

Geomagnetic field-line resonant harmonics measured by the Viking and AMPTE/CCE magnetic field experiments

The first simultaneous observations of multiple harmonic, azimuthally polarized, ULF pulsations at two points along a geomagnetic flux tube in space are reported. In March 1986, the elliptically orbiting equatorial AMPTE/CCE satellite was oriented with the apogee near 0830 h MLT, and the orbital plane of the polar-orbiting Viking satellite was at 1000 MLT. The satellites were situated within approximately the same flux tube but with an effective separation of approximately 10 R(e) near L = 8 on the inbound pass of the AMPTE/CCE orbit. Structured harmonic pulsations were observed by the magnetic field experiments on both spacecraft, and they appeared to turn off and on simultaneously at both locations. Both the observations and the relative amplitudes along the magnetic field lines support recent ideas of multiple field-line resonances of Alfven waves.

Zanetti, L. J.↗

NASA NTRS1988

Satellite Interference Analysis and Simulation Using Personal Computers

This report presents the complete analysis and formulas necessary to quantify the interference experienced by a generic satellite communications receiving station due to an interfering satellite. Both satellites, the desired as well as the interfering satellite, are considered to be in elliptical orbits. Formulas are developed for the satellite look angles and the satellite transmit angles generally related to the land mask of the receiving station site for both satellites. Formulas for considering Doppler effect due to the satellite motion as well as the Earth's rotation are developed. The effect of the interfering-satellite signal modulation and the Doppler effect on the power received are considered. The statistical formulation of the interference effect is presented in the form of a histogram of the interference to the desired signal power ratio. Finally, a computer program suitable for microcomputers such as IBM AT is provided with the flowchart, a sample run, results of the run, and the program code.

Kantak, Anil↗

NASA NTRS1987

The rings of Uranus

The rings of Uranus are not all circular; nor do they all lie in the plane of Uranus' equator. The epsilon ring of Uranus, which is the largest and outermost one, ranges in width from 20 to 96 km in proportion to the distance of the ring material from Uranus. Typical rings can be modeled by assuming that its edges are defined by a combination of smooth elliptical orbits and random 'wiggles'. A transition from a few large moons in outer regions to many small moons just outside ring-filled inner regions is a feature noted to be held in common by the ring and moon systems of Saturn, Uranus, and Neptune.

Cuzzi, Jeffrey N.↗

NASA NTRS1989

Magnetic fields near Mars - First results

The magnetic fields of Mars have been measured from Phobos 2 with high temporal resolution in the tail and down to an 850-km altitude. During four successive highly elliptical orbits, the position of the bow shock as well as that of a transition layer, the 'planetopause', were identified. Subsequent circular orbits at 6000-km altitude provided the first high-resolution data in the planetary tail and indicate that the interplanetary magnetic field mainly controls the magnetic tail. Magnetic turbulence was also detected when the spacecraft crossed the orbit of Phobos, indicating the possible existence of a torus near the orbit of this moon.

Riedler, W.↗

NASA NTRS1990

Martian bow shock - Phobos observations

Data obtained with the Magma magnetometer on the subsolar passes of the Phobos spacecraft during its 3 elliptic orbits reveals a turbulent bow shock with a strong foot consistent with the reflection of solar wind protons. The bow shock lies at a subsolar distance of 1.47 + or - .03 R(M). The circular orbit phase of the mission reveals a bow shock with a highly varying location. The median terminator crossing lies at 2.72 Mars radii. The location of the bow shock in the terminator plane is sensitive to neither the EUV flux nor to planetary longitude.

Schwingenschuh, K.↗

NASA NTRS1990

Magellan mission to Venus

The Magellan spacecraft arrived at Venus on August 10, 1990 to begin global high-resolution radar image and altimeter mapping and gravity field determination of the planet. Mapping of this cloud covered planet is done from an elliptical orbit with a 3.15 hour period and a 275 km periapsis. After the initial checkout of the spacecraft, the primary missions lasts for 243 days (one Venus day); the time it takes for Venus to make one revolution beneath the spacecraft. The data collected by Magellan is expected to provide an understanding of the geological and geophysical nature of the planet Venus, and the general processes that control planetary evolution.

Boyce, Joseph M.↗

NASA NTRS1991

Magellan imaging radar mission to Venus

The Magellan imaging-radar mapping mission has collected and processed data from the spacecraft in an elliptical orbit around Venus. A brief description is given of the mission and the spacecraft, followed by a more detailed description of the radar system design, which used earth-orbiting SAR experience and several innovations in its design to operate from an orbit around another planet. The radar sensor, ground processing, and data products are described. This multimode radar is the only science instrument on the mission and has the objective of mapping at least 70 percent of the planet surface. It has three modes: SAR, altimetry, and passive radiometry. The radar system has produced maps of almost all of the Venusian surface with a resolution better than 600-m equivalent optical line pair, and the best resolution obtained is equivalent to less than 300 m. Some of the early radar images are shown.

Johnson, William T. K.↗

NASA NTRS1991

CRAF/Cassini (C/C)

The Comet Rendezvous Asteroid Flyby (CRAF) is a mission to rendezvous with the comet Tempel 2 and to station-keep at the comet for a period of 2.6 years, including the comet perihelion. There is a flyby of the asteroid Mandeville prior to the arrival at Tempel 2. The Cassini is a mission to place a spacecraft in a highly elliptical orbit around the planet Saturn and deliver a probe to the surface of its satellite Titan. There is a flyby of the asteroid 1989 UR1 prior to arrival at Saturn. Coverage goals for the two missions are explained. Information is given in tabular form for frequency assignments, telemetry, command, navigation, and tracking support responsibility.

Draper, R.↗

NASA NTRS1991

Magellan

The Magellan Mission consists of a single spacecraft to be placed in an elliptical orbit around Venus. The main objective of the mission is to perform radar imaging, altimetry, and reflectivity of 90 percent of the planet for one Venusian year (243 days). A flight profile is given, and information is presented in tabular form on the following topics: Deep Space Network support, frequency assignments, telemetry, command, and tracking support responsibilities.

Scott, J.↗

NASA NTRS1991

Pioneer 12 (PN-12)

The DSN (Deep Space Network) mission support requirements for Pioneer 12 are summarized. The Pioneer 12 spacecraft is in a 24-hour elliptical orbit around Venus. Atmospheric and altimetry data are obtained mainly around periapsis, and planetary imaging is normally performed around apoapsis. The Pioneer 12 mission objectives are outlined and the DSN support requirements are defined through the presentation of tables and narratives describing the spacecraft flight profile; DSN support coverage; frequency assignments; support parameters for telemetry, command and support systems; and tracking support responsibility.

Lozier, D.↗

NASA NTRS1992

Electromagnetic ion cyclotron waves observed near the oxygen cyclotron frequency by ISEE 1 and 2

The first results of observations of ion cyclotron waves by the elliptically orbiting ISEE 1 and 2 pair of spacecraft are reported. The most intense waves (8 nT) were observed in the outer plasmasphere where convection drift velocities were largest and the Alfven velocity was a minimum. Wave polarization is predominantly left-handed with propagation almost parallel to the ambient magnetic field, and the spectral slot and polarization reversal predicted by cold plasma propagation theory are identified in the wave data. Computations of the experimental wave spectra during the passage through the plasmapause show that the spectral slots relate to the local plasma parameters, possibly suggesting an ion cyclotron wave growth source near the spacecraft. A regular wave packet structure seen over the first 30 min of the event is attributed to the modulation of this energy source by the Pc 5 waves seen at the same time.

Fraser, B. J.↗

NASA NTRS1992

Analysis of Phobos mission gamma ray spectra from Mars

The determination of the elemental composition of the surface of a planetary body can be achieved, in many cases, by remote-sensing gamma ray spectroscopy. A gamma ray spectrometer was carried on the Soviet spacecraft Phobos-2, and obtained data while in an elliptical orbit around Mars. Results of two independent approaches to data analysis, one by the Soviet group and one by an American group are reported. The results for five elements are given for two different orbits of Mars. Major geologic units that contribute to the signal for each orbit have been identified. The results from the two techniques are in general agreement and there appear to be no geologically significant differences between the results for each orbit.

Trombka, J. I.↗

NASA NTRS1992

Aerobraking Magellan

While the Magellan spacecraft is currently in an elliptical orbit around Venus, its orbit may be circularized by means of an aerobraking maneuver during which a minor amount of aerodynamic drag is applied to 1000-2000 orbits. An evaluation is presently undertaken of the thermal-control and operational problems arising from such a maneuver, in virtue of its not having been considered among the design requirements of the spacecraft. Attention is given to atmospheric erosion and contamination problems to which the spacecraft surfaces could be exposed.

Lyons, Daniel T.↗

NASA NTRS1992

Robust rendezvous maneuver point conditions

This study develops rendezvous maneuver point conditions that are robust to one dimensional errors in state estimation and burn execution. Allowing small deviations in the time of intercept provides a degree of freedom that can be used to compensate for these errors. The direction of allowable burn deviation is developed for errors in state estimation and burn execution. The maneuver points for which the error is aligned with the insensitive direction provide excellent rendezvous initiation points. The method is applied to sample rendezvous for vehicles in circular and elliptic orbits. Robust maneuver points are selected and the vehicles' relative motion plotted, demonstrating the validity of the maneuver points. Finally, a graphical illustration of the error focusing effect is demonstrated by means of a Monte Carlo simulation.

Fogle, Debra Ann↗

NASA NTRS1993

Three-dimensional simulations of the solar wind interaction with Mars

Three-dimensional hybrid particle simulations of the dayside portion of the Mars/solar wind interaction have been performed. These simulations are compared with the in situ measurements taken during the elliptical orbits of Phobos 2. The comparisons show considerable agreement between the magnetic field data and the simulations results. The results of the simulations bring into question the type of structures created in the subsolar region of Mars. It appears that the large larmor radius of the solar wind ions prevents the formation of a traditional collisionless shock in the subsolar region of the interaction.

Brecht, Stephen H.↗

NASA NTRS1993

The Magellan aerobraking experiment - Attitude control simulation and preliminary flight results

On May 25, 1993 the Magellan spacecraft began an experiment on 'aerobraking', or use of aerodynamic drag from the Venusian atmosphere to provide deceleration. The Magellan spacecraft will strive to transition from a highly elliptical orbit into a near-circular orbit in approximately 70 days by successively dipping into the atmosphere to gain the necessary reduction in orbital velocity. Magellan will be the first three-axis stabilized spacecraft to perform this type of multipass aerobraking, and will also be attempting to achieve the largest velocity reduction to date, all with a spacecraft that was not designed for this application. This paper addresses redesign of the attitude control system onboard Magellan for use during aerobraking. The dynamics and control of the spacecraft were simulated, and these results are presented and summarized. Modifications necessary to the existing flight control system and, specifically, to the mass expulsion control scheme are discussed. Changes were minimized though, due to the low-cost, high-risk approach to Magellan's aerobraking experiment. Some initial flight results from the first week of aerobraking operations will be highlighted.

Carpenter, Anita S.↗