Thermal and heat flow instrumentation for the space shuttle Thermal Protection SystemThe 100 mission lifetime requirement for the space shuttle orbiter vehicle dictates a unique set of requirements for the Thermal Protection System (TPS) thermal and heat flow instrumentation. This paper describes the design and development of such instrumentation with emphasis on assessment of the accuracy of the measurements when the instrumentation is an integral part of the TPS. The temperature and heat flow sensors considered for this application are described and the optimum choices discussed. Installation techniques are explored and the resulting impact on the system error defined.
Document ID
19740056440
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Hartman, G. J.
Neuner, G. J. (Acurex Corp. Mountain View, Calif., United States)
Pavlosky, J. (NASA Johnson Space Center Structures Test Section, Houston, Tex., United States)