Inverse Estimation of the Mars Science Laboratory Entry Aerothermal Environment and Thermal Protection System Response

Files
AIAA-2013-2780.pdf (827.62 KB)
Author(s)
Mahzari, Milad
Braun, Robert D.
White, Todd R.
Bose, Deepak
Advisor(s)
Editor(s)
Associated Organization(s)
Organizational Unit
Organizational Unit
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
Series
Collections
Research Publications
Supplementary to:
Permanent Link
https://hdl.handle.net/1853/74068
Abstract
The Mars Science Laboratory entry vehicle successfully landed the Curiosity rover on the Martian surface on August 5, 2012. A phenolic impregnated carbon ablator heatshield was used to protect the spacecraft against the severe aeroheating environments of atmospheric entry. This heatshield was instrumented with a comprehensive set of pressure and temperature sensors. The objective of this paper is to perform an inverse estimation of the entry vehicle's surface heating and heatshield material properties. The surface heating is estimated using the flight temperature data from the shallowest thermocouple. The sensitivity of the estimated surface heating profile to estimation tuning parameters, measurement errors, recession uncertainty and material property uncertainty is investigated. A Monte Carlo analysis is conducted to quantify the uncertainty bounds associated with the nominal estimated surface heating. Additionally, a thermocouple driver approach is employed to estimate heatshield material properties using the flight data from the deeper thermocouples while applying the shallowest thermocouple temperature as the surface boundary condition.
Sponsor
Date
2013-06
Extent
Resource Type
Text
Resource Subtype
Paper
Rights Statement
Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved
Rights URI
https://rightsstatements.org/page/InC/1.0/?language=en