The proposed ignition system can be used in attitude control and apogee engines on NASA spacecraft. Potential NASA applications for the foam igniter system include orbit transfer, maneuvering, station keeping, and attitude control for satellites. Any satellite employing hydrazine propulsion will benefit. Promising near-term applications are attitude control systems for planetary spacecraft. The thermal igniter can be used with any monopropellant including hydrazine, thereby removing concerns over catalyst life and inability for cold starts. The technology to be developed can be used in virtually any NASA flight mission because the igniters can be used with hydrazine or higher performance advanced monopropellants (e.g. ADN and AF-315E). Using AF-315E monopropellant can increase specific impulse relative to hydrazine and deliver higher performance, reduce cost, and increase flexibility beyond that of NTO/MMH. The proposed ignition system can be used in attitude control and apogee engines for commercial and government satellites and divert and attitude control system engines for kinetic kill vehicles. The use of toxic propellants such as hydrazine will be eliminated in gas generators on military aircraft and fuel pressurization systems for tactical missiles. Potential military space applications for the foam igniter system are orbit transfer, maneuvering, station keeping, and attitude control for satellites. Any agency with satellites employing hydrazine propulsion will benefit. Promising near-term defense applications are divert and attitude control systems for kinetic energy interceptors, gas generators for auxiliary power units and tank pressurization systems, and liquid gun propellant systems.