Quantitative Dual-Band IR Thermography for Global Temperature Measurements

The proposed effort would develop a dual-band infrared thermography technique to deliver quantitative surface temperature measurements in harsh hypersonic ground test environments. A proof-of-concept instrument would be designed using commercial off-the-shelf components and existing IR detectors; with a near-term goal of a benchtop demonstration in a simulated test environment. The target application would be NASA LaRC hypersonic facilities; namely the 20-inch Mach 6 Tunnel; 31-inch Mach 10 Tunnel; and Arc-Heated Scramjet Test Facility.

NASA has a growing interest in reusable; air-breathing hypersonic vehicles for low-cost access to space as well as other civil and commercial missions. These systems must be designed to withstand the intense thermal loads inherent to sustained hypersonic flight in the atmosphere. NASA also has a sustained interest in developing advanced thermal protection systems for atmospheric reentry. Whether it be high-speed civil aviation transport or advanced reentry systems; there are clear strategic needs to develop high-temperature materials and structures to enable hypersonic flight. In this pursuit; NASA internal and partnered programs will require quantitative surface temperature measurements in harsh aerothermodynamic ground test environments. Dual-band IR is poised to deliver that capability.

This is early/mid-stage (TRL 2) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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