Advanced Instrumentation for Carbon-Carbon Structures in Hypersonic Environments

An integrated measurement sensor for carbon-carbon (C-C) structures is needed for testing in arc-jet facilities to meet testing needs for future hypersonic flight systems. This work continues development on a measurement suite capable of surviving the long duration glide phase characteristic of hypersonic vehicles. A fast-response pressure sensor, an instrumented temperature measurement plug, and a novel temperature, heat flux, and recession sensor, based on a proprietary thin-film thermocouple technology being developed by Exo-Atmospheric Technologies, LLC, were designed for direct integration with designed during Phase I for use in Phase II testing. The sensors and prototype hardware were fabricated and simple bench-top tests were performed to verify sealing and structural integrity of the integrated sensors. A demonstration of field serviceability and sensor replacement was also conducted completing all objectives outlined in the initial topic call. Phase II will pursue advanced development of the integrated sensing suite with bench-top testing and high-enthalpy testing to optimize the design and its integration / installation methodology based on Phase I results. Phase II testing will be conducted at three high-enthalpy test facilities (AFRL RC-18, LHMEL, NASA Ames AHF). Tests in these facilities will demonstrate sensor robustness at extreme conditions, characteristic of hypersonic flight.