Hypervelocity impact facility for simulating materials exposure to impact by space debris

Details Hypervelocity impact facility for simulating materials exposure to impact by space debris Hypervelocity impact facility for simulating materials exposure to impact by space debris

Apr 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993ldef.symp..479r&link_type=abstract

In NASA. Langley Research Center, LDEF: 69 Months in Space. Second Post-Retrieval Symposium, Part 2 p 479-492 (SEE N93-29354 11-

Mathematics

Probability

Earth Orbital Environments, Ejecta, Hypervelocity Impact, Long Duration Exposure Facility, Space Debris, Velocity Distribution, Armor, Bumpers, Controlled Atmospheres, Meteorite Craters, Probability Theory, Residues, Solar Arrays, Space Stations

Scientific paper

As a result of man's venturing into space, the local debris contributed by his presence exceeds, at some orbital altitudes, that of the natural component. Man's contribution ranges from fuel residue to large derelect satellites that weigh many kilograms. Current debris models are able to predict the growth of the problem and suggest that spacecraft must employ armor or bumper shields for some orbital altitudes now, and that, the problem will become worse as a function of time. The practical upper limit to the velocity distribution is on the order of 40 km/s and is associated with the natural environment. The maximum velocity of the man-made component is in the 14-16 km/s range. The Long Duration Exposure Facility (LDEF) has verified that the 'high probability of impact' particles are in the microgram to milligram range. These particles can have significant effects on coatings, insulators, and thin metallic layers. The surface of thick materials becomes pitted and the local debris component is enhanced by ejecta from the debris spectrum in a controlled environment. The facility capability is discussed in terms of drive geometry, energetics, velocity distribution, diagnostics, and projectile/debris loading. The facility is currently being used to study impact phenomena on Space Station Freedom's solar array structure, other solar array materials, potential structural materials for use in the station, electrical breakdown in the space environment, and as a means of clarifying or duplicating the impact phenomena on the LDEF surfaces. The results of these experiments are described in terms of the mass/velocity distribution incident on selected samples, crater dynamics, and sample geometry.

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