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Arc Jet Testing of the TIRS Cover Thermal Protection System for Mars Exploration RoverThis paper summarizes the arc jet test results of the Mars Exploration Rover (MER) Silicone Impregnated Reusable Ceramic Ablator (SIRCA) Transverse Impulse Rocket System (TIRS) Cover test series in the Panel Test Facility (PTF) at NASA Ames Research Center (ARC). NASA ARC performed aerothermal environment analyses, TPS sizing and thermal response analyses, and arc jet testing to evaluate the MER SIRCA TIRS Cover design and interface to the aeroshell structure. The primary objective of this arc jet test series was to evaluate specific design details of the SIRCA TIRS Cover interface to the MER aeroshell under simulated atmospheric entry heating conditions. Four test articles were tested in an arc jet environment with various sea] configurations. The test condition was designed to match the predicted peak flight heat load at the gap region between the SIRCA and the backshell TPS material, SLA-561S, and resulted in an over-test (with respect to heat flux and heat load) for the apex region of the SIRCA TIRS Cover. The resulting pressure differential was as much as twenty times that predicted for the flight case, depending on the location, and there was no post-test visual evidence of over-heating or damage to the seal, bracket, or backshell structure. The exposed titanium bolts were in good condition at post-test and showed only a small amount of oxidation at the leading edge locations. Repeatable thermocouple data were obtained and SIRCA thermal response analyses were compared to applicable thermocouple data. For the apex region of the SIRCA TIRS Cover, a one-dimensional thermal response prediction proved overly conservative, as there were strong multi-dimensional conduction effects evident from the thermocouple data. The one-dimensional thermal response prediction compared well with the thermocouple data for the leading edge "lip" region at the bolt location. In general, the test results yield confidence in the baseline seal design to prevent hot gas ingestion at the bracket and composite aeroshell structure interface.
Document ID
20020094258
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Szalai, Christine E.
(NASA Ames Research Center Moffett Field, CA United States)
Chen, Y.-K.
(NASA Ames Research Center Moffett Field, CA United States)
Loomis, Mark
(NASA Ames Research Center Moffett Field, CA United States)
Hui, Frank
(NASA Ames Research Center Moffett Field, CA United States)
Scrivens, Larry
(Eloret Corp. United States)
Date Acquired
August 20, 2013
Publication Date
October 2, 2002
Subject Category
Cybernetics, Artificial Intelligence And Robotics
Meeting Information
Meeting: 36th AIAA Thermophysics Conference
Location: Orlando, FL
Country: United States
Start Date: June 23, 2003
End Date: June 26, 2003
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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