Dual Use Catalytically Initiated Combustor (CIC) for Rocket Engine Ignition and Thruster Applications

This proposal responds to subtopic O2.02 "Propulsion Technologies" and the stated need to develop component technologies that will lead to future propulsion systems that are reliable and have adequate performance without requiring excessive specialized handling equipment and procedures or needing to push materials and designs to the limits of their capabilities. We propose the development of a low part count and low energy Catalytically Initiated Combustor (CIC) that can serve as a rocket engine igniter as well as the basis for a family of low cost and highly reliable launch vehicle and satellite thrusters. We propose a 6-month Phase I program to 1) demonstrate reliable ignition and operation of our baseline CIC with hydrogen, methane, and propane fuels, 2) demonstrate reliable ignition and operation of our baseline CIC under cold gas inlet conditions, 3) demonstrate extended duration hot fire testing and durability of our CIC design over multiple ignition cycles, and 4) demonstrate rapid pulsed operation necessary for a launch vehicle or space craft thruster application. Under our proposed Phase I effort, we will also conduct a market survey of potential customers and define a flight weight CIC with maximum commercial utility as either an igniter or small thruster.