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Aerothermodynamic performance and thermal protection design for blunt re-entry bodies at L/D = 0.3Aerodynamic heating and thermal protection design analyses were performed for three blunt re-entry bodies at an L/D = 0.3 returning from low earth orbit. These configurations consisted of a scaled up Apollo command module, a Viking re-entry vehicle, and an Aeroassist Flight Experiment (AFE) aerobrake, each with a maximum diameter of 4.42 m. The aerothermodynamic analysis determined the equilibrium stagnation point heating rate and heat load for nominal and 3-sigma re-entry trajectories and the distribution of heating along the pitch and yaw planes for each of the vehicles at the time of highest heat flux. Using the predicted heating rates and heating distributions, a Thermal Protection System (TPS) design with flight certified materials was tailored for each of the configurations. Results indicated that the heating to the corner of the Viking aeroshell would exceed current limits of reusable tile material. Also, the maximum heating for the AFE would be 15 percent greater than the maximum heating for the Apollo flying the same trajectory. TPS designs showed no significant advantage in TPS weight between the different vehicles; however, heat-shield areal density comparisons showed the Apollo configuration to be the most efficient in terms of TPS weight.
Document ID
19930040973
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Caram, Jose M.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Kowal, T. J.
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 93-0916
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A24970
Distribution Limits
Public
Copyright
Other

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