Micropropulsion Thruster for Low Power Satellites

An enhanced electrically controlled extinguishable solid propellant (ECESP) developed under this SBIR program will be tested in a core burning motor configuration, thus making possible higher thrust levels than achievable in previously tested end burningmotor designs. Specifically the enhancement entails the use of additives that confer increased electrical conductivity to the propellant surface following combustion and extinguishments of the propellant. A conductive coating is applied only to the boresurface of the propellant to enable initial ignition at this surface. This property allows for the design of a motor grain with fixed copper electrodes and no moving parts. This will make it possible to carry out both station keeping and orbitalplacement of a satellite utilizing a single thruster system. Thus, a satellite employing this technology could change orbital configuration and placement multiple times during its operational lifetime. The proposed motor design and propellant system isexpected to provide greater flexibiity and reduced cost over current satellite propulsion systems. A single thruster can be used for both manuevering and station keeping of satellites. This is expected to be used in both military and commercialsatellites,that can be used in missions for surveilance, communication and to inspect and repair satellites already in orbit.