Patent ID: 7966809

Claim:
A hybrid rocket system, comprising: a motor case having a proximal end and a distal end, the motor case defining an interior volume, the interior volume including: (a) a combustion chamber near a proximal end of the interior volume; (b) a first nozzle at a distal end of the interior volume; (c) a combustion port between the combustion chamber and the nozzle, wherein the combustion port is smaller in diameter than a diameter of the combustion chamber; (d) a spherical oxidizer tank at the proximal end of the interior volume, the oxidizer tank defining an internal cavity configured to hold a principal fluid oxidizer, the internal cavity larger in diameter than the diameter of the combustion port; (e) a valve port having a valve between the oxidizer tank and the combustion chamber, the valve port providing communication between the internal cavity of the oxidizer tank and the combustion chamber, wherein a hole extends through the motor case into the valve port, the hole sized to receive the valve therethrough for insertion into the valve port; wherein the motor case, the oxidizer tank, and the valve port are all formed of the same material and wherein the material is a solid rocket fuel, the solid rocket fuel burns with the principal fluid oxidizer from the valve port for propulsion.