This NASA Phase I STTR program would develop wireless networked, high temperature, wide bandwidth pressure sensors for use in propulsion systems during ground test and launch operations. Both applications require broadband and in particular high frequency response for adequate diagnostics, and operation at very high temperatures in rocket engine environments. The team proposes major changes in pressure sensor fabrication and implementation to allow order of magnitude increases in their temperature range, from their current 125 °C upper temperature limit to 500 °C and above. The proposed approach involves the avoidance of conventional soldering processes to reach approximately 300 °C and the use of very high temperature polymer-derived ceramic potting and thermal barrier insulation materials to reach 500 °C and above. The team will transition the wireless networked, high temperature, high frequency pressure sensors from their current concept to prototype stage products of use for rocket engine applications.
The proposed wireless networked, high temperature, wide bandwidth pressure sensors can be used in the propulsion systems during ground test and launch operations. Currently, there are no commercial pressure sensors that can cover the wide frequency bandwidth from DC to 5MHz, even without high temperature capacities. The advantage of the proposed sensors over these existing low temperature products is their DC to 5MHz frequency response.
Primary customers would be university, government laboratory and industry researchers. Customers for wireless networked, high temperature, high frequency pressure transducers will be the manufacturers of engines and of high speed vehicles and flight control systems. Broader commercial sensor opportunities include oil and gas down-hole measurements.