HIGH PERFORMANCE ELECTRICALLY CONTROLLED SOLID SOLUTION PROPELLANT

"This research is directed towards the development of a high energy electrically controlled solid propellant for maneuvering thrusters in micro satellites. Combustion of this propellant will depend on the continuous but low level input of electricalenergy. Extinguishment will take place rapidly upon removal of this electrical energy. The propellant will have a principal oxidizer and a base binder. The oxidizer will be formulated to retain its liquid state down to - 20 degrees centigrade. Theresultant propellant will be aged at 35 and 50 degrees centigrade for a period of 6 months. The aged propellant will be tested for DSC, TGA, density, ignition, combustion, extinquishment and electrical resistivity. These results will be compared to theresults from the same tests for these propellants prior to aging. A final formulation will be selected. Repeated batches will be made of this formulation to establish reproducibility and samples will be furnished to the Electric Propulsion Lab at AFRLfor combustion testing in small motor configurations. Industry requirements and specifications will be researched to enable proper tailoring of propellant properties and performance"