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Aerothermodynamic Design of the Mars Science Laboratory Backshell and Parachute ConeAerothermodynamic design environments are presented for the Mars Science Laboratory entry capsule backshell and parachute cone. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux) design entry trajectories from a 2009 launch. Transient interference effects from reaction control system thruster plumes were included in the design environments when necessary. The limiting backshell design heating conditions of 6.3 W/sq cm for heat flux and 377 J/sq cm for total heat load are not influenced by thruster firings. Similarly, the thrusters do not affect the parachute cover lid design environments (13 W/sq cm and 499 J/sq cm). If thruster jet firings occur near peak dynamic pressure, they will augment the design environments at the interface between the backshell and parachute cone (7 W/sq cm and 174 J/sq cm). Localized heat fluxes are higher near the thruster fairing during jet firings, but these areas did not require additional thermal protection material. Finally, heating bump factors were developed for antenna radomes on the parachute cone
Document ID
Document Type
Conference Paper
Edquist, Karl T.
(NASA Langley Research Center Hampton, VA, United States)
Dyakonov, Artem A.
(NASA Langley Research Center Hampton, VA, United States)
Wright, Michael J.
(NASA Ames Research Center Moffett Field, CA, United States)
Tang, Chun Y.
(Eloret Corp. Moffett Field, CA, United States)
Date Acquired
August 24, 2013
Publication Date
June 22, 2009
Subject Category
Report/Patent Number
AIAA Paper 2009-4078
Meeting Information
41st AIAA Thermophysics Conference(Texas)
Funding Number(s)
WBS: WBS: 857464.02.07.08
Distribution Limits
Public Use Permitted.
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