Electrolytic Igniter for Ionic Liquid Monopropellants Navy SBIR FY2016.1 Sol No.: Navy SBIR FY2016.1 Topic No.: N161-067 Topic Title: Electrolytic Igniter for Ionic Liquid Monopropellants Proposal No.: N161-067-0958 Firm: Ultramet 12173 Montague Street Pacoima, California 91331 Contact: Matthew Wright Phone: (818) 899-0236 Web Site: http://www.ultramet.com Abstract: Some advanced liquid monopropellants provide the unique property of ionic conductivity, which opens the possibility of using electrolysis for ignition. In recent work for the Navy, Ultramet demonstrated electrolytic decomposition of two different ionic liquid monopropellant formulations. The results of those tests were reduced to key design principles that will be used in this project to develop hardware. The design to be pursued is based on a simple, robust fabrication process used in industry for the manufacture of similar devices. Ultramet will produce the hardware and Pennsylvania State University will evaluate the electrolysis units using established techniques. The most important metric for a successful system is achieving the reaction time necessary for divert and attitude control system (DACS) thrusters on missile defense kill vehicles, meaning that propellant ignition must be very fast. To this end, the Penn State tests will focus on designs that enable propellant reactivity at very short time scales. Benefits: The proposed electrolysis-based ignition system will eliminate the catalyst degradation and washout issues plaguing ionic liquid monopropellant catalysts. Potential applications will be numerous as it will enable use of advanced monopropellants that offer performance beyond that of monopropellant hydrazine and bipropellant NTO/MMH. The use of toxic propellants such as hydrazine can be eliminated in gas generators on military aircraft and fuel pressurization systems for tactical missiles. Because such a fast ramp rate and high ultimate temperature can be achieved, it is applicable to use in divert and attitude control systems for kinetic kill vehicles and other missile defense systems. The ignition system can be used for orbit transfer, maneuvering, station keeping, and attitude control on military, civil, and commercial satellites and spacecraft. Return