MESUR probe aerobrake preliminary design study

Details MESUR probe aerobrake preliminary design study MESUR probe aerobrake preliminary design study

Jul 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992thph.confs....t&link_type=abstract

AIAA, Thermophysics Conference, 27th, Nashville, TN, July 6-8, 1992. 13 p.

Physics

Aerobraking, Atmospheric Entry, Mars Probes, Spacecraft Design, Temperature Control, Reentry Shielding, Spacecraft Shielding

Scientific paper

Aerobrake design for the Mars Environmental Survey (MESUR) vehicles is considered which is intended for both a nominal entry velocity of 7 km/sec and a high-speed case of 9 km/sec. Topics discussed include the entry environment, the thermal protection requirements for several types of heat shield materials, the structural design of the aeroshell, and the total aerobrake masses and mass fractions. For the nominal 7 km/sec entry, a silicone elastometric charring ablator, SLA-561, was found to be the lightest heat shield material. For the 7 km/sec entry, the mass fraction of the aerobrake was 13.2 percent. For the 9 km/sec entry, the heat shield consisted of the medium-density ablator AVCOAT-5026; SLA-561 was used on part of the conical skirt. The aerobrake mass fraction in this case was 18 percent. It is recommended that separate aerobrakes be designed for probes entering at 7 and 9 km/sec.

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