PHYSICAL SCIENCES INC. — Department of Defense SBIR Phase I: N211-092

Description

The Navy is in need of an in-flight diagnostic tool capable of measuring surface temperatures and recession rates of various materials and geometries of the Thermal Protection System (TPS) of hypersonic missile surfaces during flight tests. Atmospheric friction heating dictates varying requirements for aircraft surfaces, including high temperature survival and/or sacrificial material ablation over the flight profile. The overall goal of this project is to develop a non-intrusive recession rate and surface temperature monitoring system that will be operational in flight test environments. In Phase I, the project will demonstrate the feasibility of a novel ultrasound-based approach for measuring the temperature at the distal (heated) side of the TPS. Leveraging recent success in recession analysis in challenging hypersonic materials (thick carbon – carbon composites), including under heating, we will measure temperature and recession in C-C and refractory materials. In Phase II, we will develop a sensor package that is fully integrated for ground test demonstration, ideally with ablative material furnished by the Navy, and design critical system components to meet the flight (aircraft internal) environmental and communication interface requirements. In Phase III, we will develop and produce flight test units that will be ready for onboard experimental hypersonic vehicle flight tests.