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

This NASA Phase II 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 250 deg;C upper temperature limit to 1000 deg;C and above. Such modifications involve 1) improved packaging processes to reach approximately 500 deg;C continuously, 2) the use of very high temperature polymer-derived ceramic thermal barrier materials to reach 1000 deg;C intermittently, and 3) the optimization of wide bandwidth frequency response of DC to above 5MHz with thermal barrier materials. 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.