Aerocapture for manned Mars missions - Status and challenges

Details Aerocapture for manned Mars missions - Status and challenges Aerocapture for manned Mars missions - Status and challenges

Aug 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991afm..conf.....w&link_type=abstract

AIAA, Atmospheric Flight Mechanics Conference, New Orleans, LA, Aug. 12-14, 1991. 25 p.

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Computation

Aerocapture, Aerothermodynamics, Manned Mars Missions, Pioneer Venus Spacecraft, Spacecraft Control, Computational Fluid Dynamics, Lift Drag Ratio, Reynolds Number, Stagnation Point

Scientific paper

The current status for manned Mars missions and the associated challenges are summarized. Mission benefits are considered to increase with increasing Mars entry velocity. However, significant benefits accrue at moderate entry velocities between 7 and 8 km/sec, which is the realistically achievable range in view of g-limits and heating constraints. Blunt, low mass/drag coefficient (reference area) vehicles with L/Ds from 0.3 to 0.5 are found to be the preferred configurations, taking into account their adequate control authority and good payload packaging characteristics. The overall design characteristics of Mars aerocapture vehicles can be established with good confidence, using flight and ground test data and the state-of-the-art flow field analysis techniques. The principal challenges are identified as follows: to refine the knowledge of the Martian atmosphere in order to reduce design conservatism, to extend present stagnation region heating analyses to the entire vehicle forebody, and to develop reflective low-wall-catalycity TPS systems for enabling reusable vehicles.

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