A Reconstruction of Aerothermal Environment Thermal Protection System Response of the Mars Science Laboratory Entry Vehicle

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AAS-2013-311.pdf (2.34 MB)
Author(s)
Bose, Deepak
White, Todd R.
Mahzari, Milad
Edquist, Karl
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Daniel Guggenheim School of Aerospace Engineering
The Daniel Guggenheim School of Aeronautics was established in 1931, with a name change in 1962 to the School of Aerospace Engineering
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https://hdl.handle.net/1853/74870
Abstract
An initial assessment and reconstruction of Mars Science Laboratory (MSL) entry aerothermal environment and thermal protection system (TPS) response is performed using the on-board instrumentation suite called MSL Entry, Descent, and Landing Instrumentation (MEDLI). The analysis is performed using the current best estimated trajectory. The MEDLI suite in part provides in-depth temperature measurements at seven locations on the heat shield. The temperature data show the occurrence of boundary layer transition to turbulence on the leeside forebody of the entry vehicle. The data also suggest that the TPS recession is lower than nominal model predictions using diffusion limited surface oxidation. The model predictions of temperatures show an underprediction in the stagnation and apex regions, and an overprediction in the leeside region. An estimate of time-varying aeroheating using an inverse reconstruction technique is also presented. The reconstructed aeroheating is sensitive to the choice of a recession model.
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2013-02
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