Wireless Networked, High Temperature, Wide Bandwidth Pressure Sensors for Propulsion System Monitoring

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 deg;C upper temperature limit to 500 deg;C and above. The proposed approach involves the avoidance of conventional soldering processes to reach approximately 300 deg;C and the use of very high temperature polymer-derived ceramic potting and thermal barrier insulation materials to reach 500 deg;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.