Patent ID: 8539753

Claim:
A hybrid rocket motor, comprising: an oxidizer tank containing a supply of oxidizer; a first, annular solid fuel element positioned around the supply of oxidizer; a second solid fuel element positioned concentrically around the first solid fuel element; a combustion port positioned between the first and second solid fuel elements, wherein the oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product; and a nozzle in communication with the combustion port for combustion discharge of the combustion product; wherein a generally enclosed space is positioned below the oxidizer tank and below the first solid fuel element, such that the widest diameter of the generally enclosed space is substantially equal to the outer diameter of the first, annular solid fuel element, wherein the space communicates with a throat of the nozzle via at least one passageway therebetween and wherein the at least one passageway can be used to facilitate liquid injection vector thrust control of the nozzle.