Thermal performance of FRSI/graphite epoxy materials for the Orbiter TPS applicationRadiant tests have been conducted to evaluate the performance of the Flexible Reusable Surface Insulation (FRSI) when bonded to Graphite/Epoxy (G/E) honeycomb sandwich structures. The results from this study indicate reasonable agreement with the baseline FRSI properties that existed prior to this test program. An updated Thermal Math Model (TMM) prediction technique was developed, with the use of the well-defined boundary conditions, which appears to be valid in analyzing the complex heat transfer associated with the honeycomb structure. The updated TM analysis of flight data resulted in good agreement of predicted temperatures with flight data for bondline responses of Orbiter FRSI/GE TPS applications.
Document ID
19840054708
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Norman, I. (Rockwell International Corp. Houston, TX, United States)
Ritrivi, C. A. (Rockwell International Corp. Houston, TX, United States)
Tillian, D. J. (Rockwell International Corp. Houston, TX, United States)
Maraia, R. J. (NASA Johnson Space Center Houston, TX, United States)