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Grard, R.

Publications and source records attributed to Grard, R..

9 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1993

Dielectric properties of Mars' surface: Proposed measurement on a Mars lander

Recent studies of missions to Mars (MESUR by NASA and Marsnet by ESA) have suggested the development of semihard landers. One type was to be extremely basic, consisting mainly of a meteorological package, but with the possibility of other small, low-mass, low-power instruments. In particular, this type of lander was also considered for the exploration of the polar regions. Two methods to investigate the surface material at the landing site are discussed. Both measure the dielectric constant epsilon of the ground material. This information can then be used to elucidate the surface composition and structure. The determination of the permittivity would be of high scientific value, especially in the case of a landing on the polar ice.

Ulamec, S.↗
NASA NTRS1989

First measurements of plasma waves near Mars

Preliminary results from electric field measurements in the environment of Mars using the plasma-wave system on board Phobos 2 are reported. Electron-plasma oscillations observed upstream of the bow shock correspond to a solar-wind density of 2/cu cm. The shock-foot boundary was crossed up to three times on each orbit. The shock ramp was detected at altitudes between 0.45 and 0.75 Mars radii R(M) above the planetary surface. The density increased by about a factor of two at the ramp. The shock position, although variable, seems to be consistent with previous measurements. The downstream magnetosheath contained broadband electric-field noise below the plasma frequency. The boundary of th obstacle, or plasmapause, was crossed at altitudes of the order of 0.28 R(M); the cold plasma density was highly variable within the planetopause and reached the unexpected value of 700/cu cm on the third orbit, at 0.25 R(M) altitude. Bursts of waves with frequencies below the electron cyclotron frequency occur within the planetopause.

Grard, R.↗
NASA NTRS1988

An instrument for measuring the complex permittivity of the Martian top soil

This permittivity measuring instrument measures the resistivity rho and the relative dielectric constant epsilon sub r of the Martian top soil along the path of a rover. This aim is achieved by measuring the real and imaginary parts of the complex permittivity epsilon = epsilon sub r - j epsilon sub i where epsilon sub i = omega epsilon sub o rho/1; epsilon sub 1 is the permittivity of vacuum and omega is a variable angular working frequency. The experimental technique consists in evaluating the mutual, or transfer, impedance of a quadrupolar probe, i.e., in quantifying the influence of the Martian ground on the electrical coupling of two Hertz dipoles. The horizontal and vertical spatial resolutions are of the order of the length and separation of the dipoles, typically 1 to 2 metres. The four-electrode method for measuring the ground resistivity on earth was first applied by Wenner and Schlumberger, but the proposed investigation bears closer resemblance to a similar instrument developed for ground surveying at shallow depth, in connection with archaelogical and pedological research. A quadrupolar probe will provide essential information about the electric properties of the Martian ground and will contribute usefully to the identification of the soil structure and composition in association with other experimental equipment (camera, infra-red detector, gamma and X-ray spectrometers, chemical analyzers, ground temperature probes).

Grard, R.↗
NASA NTRS1987

Giotto-spacecraft charging due to impact generated plasma in the presence of dielectric materials

The charging effects of a conducting/dielectric model spacecraft in the impact induced plasma environment are contrasted. The results of dynamic model calculations indicate larger charging times and higher positive spacecraft potentials for a conducting/dielectric spacecraft. The potential and particle distributions around the spacecraft differ quantitatively and qualitatively in both cases.

Thiemann, 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 NTRS1985

Charging effects in the cometary environment of Halley

Electrostatic charging of the Giotto spacecraft in different impact induced charged particle environments was studied with 3D numerical particle-in-cell models. The simulation results are assessed according to first experimental results of Giotto and Vega instruments. Decreasing and even negative spacecraft potentials measured on Vega near closest approach to the comet suggest the influence of the cometary plasma, which is also confirmed by corresponding numerical simulations.

Thiemann, H.↗
NASA NTRS1984

Magnetospheric pulsations observed by ISEE 1 and 2 satellites

The ISEE 1 and 2 spacecraft studied whether observed amplitude variations in hydromagnetic waves were due to the motion of the spacecraft through a time stationary structure or were due to temporal changes. The data provide evidence for spatially limited standing hydromagnetic wave resonant regions. The standing wave harmonic and Poynting vector were deduced from the simultaneous observations of the wave magnetic and electric field.

Singer, H. J.↗