Patent ID: 7921638

Claim:
A miniature rocket propulsion system comprising: a plurality of primary propellant storage chambers separated by a motor body structure, at least a portion of which contains a non-flowable, aft end-burning primary propellant; a plurality of secondary propellant storage chambers, at least a portion of which contains a flowable secondary propellant, wherein the secondary propellant is complementary to the primary propellant, the secondary propellant being self-pressurizing, having a vapor pressure at ambient conditions of greater than the combustion pressure of the primary propellant in the primary propellant storage chambers; and at least one secondary propellant delivery channel associated with each secondary propellant storage chamber, the channel connecting the secondary propellant storage chamber to the primary propellant storage chamber, the channel passing through the motor body structure and along at least a portion of the length of the primary propellant storage chamber, the channel configured to introduce the secondary propellant to an afterburner region of the primary propellant storage chamber or a nozzle proximate thereto, wherein the secondary propellant is delivered directly to the afterburner region of the primary propellant storage chamber following depletion of the primary propellant past an interface of the secondary propellant delivery channel and the primary propellant storage chamber, wherein the rocket propulsion system has a mass of about 1.5 kg or less.