Patent ID: 8099945

Claim:
A propulsion system, comprising: a hybrid rocket motor case having a proximal end and a distal end, the motor case defining an interior volume including a combustion chamber at the proximal end, wherein the motor case is configured to hold solid rocket fuel; a fuel tank coupled to the proximal end of the motor case, the fuel tank defining an internal volume configured to hold a fluid oxidizer; a bulkhead interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead, the access passageway providing exterior access to the interior volume of the motor case or the internal volume of the fuel tank while the hybrid rocket motor is coupled to the fuel tank and wherein at least one valve is positioned in the access passageway; a nozzle coupled to the distal end of the motor case and in communication with the combustion chamber; a conduit that provides a flow path for liquid oxidizer to flow directly from the fuel tank into the nozzle without passing through the combustion chamber such that as the fluid oxidizer flows into the nozzle through the conduit, the fluid oxidizer combusts within hot gases in the nozzle to form a high pressure region within the nozzle where the liquid oxidizer combusts.