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A preliminary TPS design for MRSR - Aerobraking at Mars and at earthAn investigation was made to determine the feasibility of using an aerobrake system for an unmanned mission to Mars and for a return vehicle to earth. A preliminary thermal protection system (TPS) is examined for two small nose radius, straight biconic vehicles aerocapturing at Mars. The TPS for these vehicles, entering at 6 km/s and 8 km/s, are shown to have an advantage over a propulsive burn velocity reduction for orbit insertion. The TPS for each vehicle consisted of an ablator in the region of high heating, and reusable insulation over the rest of the structure. It was determined that a reusable TPS could be used over 98 percent of the aeroshell structure. Also presented is the preliminary TPS design for an Apollo-shaped vehicle aerocapturing at earth. As with the biconics, this vehicle had an ablator in the region of high heating, and reusable insulation on the aft conic section. In contrast to the vehicles aerocapturing at Mars, the ablator is used on 63 percent of the vehicle's aeroshell structure.
Document ID
19900032596
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Williams, S. D.
(Lockheed Engineering and Sciences Co. Houston, TX, United States)
Pavlosky, J. E.
(Lockheed Engineering and Sciences Co. Houston, TX, United States)
Curry, D. M.
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 90-0052
Accession Number
90A19651
Distribution Limits
Public
Copyright
Other

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