Patent ID: 7254936

Claim:
A multi-engine solid propellant rocket stage, comprising a plurality of solid propellant rocket engines, each solid propellant rocket engine comprising: a propellant formed into a predetermined shape and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand said hot, high-pressure gas into the atmosphere, wherein said predetermined shape comprises a combustion cavity, wherein said propellant forms said nozzle as a part of said predetermined shape, wherein said plurality of rocket engines are connected in parallel so that more than one of said rocket engines may burn and provide thrust simultaneously, wherein nozzles of substantially all of said plurality of rocket engines are configured and positioned to expand gas into the atmosphere in a substantially same direction, wherein said multi-engine solid propellant rocket stage is shaped as an integrally formed stackable plate, and wherein corresponding points in said predetermined shapes of said plurality of rocket engines are substantially coplanar.