Hypersonic flight is currently an extremely important research area that represents a disruptive technology with the potential to revolutionize modern aviation, military defense, and space exploration. Advancements in high-speed vehicle development are possible if insights can be gained, analyzed, and used to create new technologies. New insights will require advancements of current measurement techniques as well as novel forms and integration techniques to fill existing technological gaps. The purpose of this project is to develop high temperature sensors on Ceramic Matrix Composite (CMC) components that can survive and operate in the extreme environmental conditions of hypersonic flight including high temperature, vibration and acoustic environments to address these gaps. Acrees proposed thin film sensors are fabricated either directly on CMC components (direct write) or on thin ceramic substrates that can be affixed to CMC components and thermal protection system (TPS) of hypersonic vehicles, allowing versatility in their use. The development of these advanced sensors will allow for vehicle Structural Health Monitoring (SHM) and advances in hypersonic aircraft research and design. The long-term goal for this technology is an operational, reusable hypersonic aircraft. Anticipated Benefits The advanced sensors developed in this project will be used for the development, design and deployment of hypersonic aircraft. They will be used for vehicle Structural Health Monitoring (SHM) in extreme hypersonic environments. The advanced high temperature sensor technology developed in this project can be used in virtually any aircraft or land-based combustion turbines for structural health monitoring.
