Innovative Flight Instrumentation for Hypersonics

In this proposal we exploit the remote sensing attributes of ultrasound to non-intrusively measure temperature, transient temperature and heat flux in both insulating and metallic aeroshells. In previous work, we have demonstrated the capability to non-intrusively measure the local temperature at the inner surface of large caliber Navy guns using sensors attached to the external gun barrel surface (2.5” from the measurement point). In the proposed effort, we modify the measurement methods to apply to relevant aeroshell materials and configurations found in hypersonic flight. Analytical methods to accurately treat thermal transients and extract heat flux from the ultrasonic data are also developed. The ultrasonic methods are non-intrusive and do not require breeching the aeroshell. The ability to locate sensors on the interior surfaces removes the sensor from the chemically reactive environment of hypersonic airbreathing propulsion systems which allows operation of the test facilities at extreme temperatures. Acquisition of localized and instantaneous temperature data from previously inaccessible regions will improve the Air Force’s ability to control, understand, and optimize hypersonic vehicle performance. The ability to perform such measurements without breeching the interior or exterior surfaces of hypersonic vehicles is critical for flight vehicles.