Patent ID: 8291691

Claim:
A multi-purpose rocket motor comprising: (a) a chamber having a longitudinal axis terminating at a fore end and an aft end, and comprising a nozzle at said aft end, (b) a thermally insulating barrier dividing said chamber into fore and aft segments arranged along said longitudinal axis, with a fore propellant grain in said fore segment and an aft propellant grain in said aft segment, (c) an attitude maneuvering port in said fore segment oriented to produce attitude maneuvering of said rocket motor; and (d) a guidance and control system selecting between a first mode of operation wherein said barrier is in a closed condition, causing combustion gas from combustion of said fore propellant grain to be released from said chamber through said attitude maneuvering port, and a second mode of operation wherein said barrier is in an open condition permitting flow of combustion gas generated in said fore segment through said aft segment to achieve combined axial thrust from said fore and aft propellant grains when combusted, said guidance and control system being independent of ignition of either said fore propellant grain or said aft propellant grain, and wherein said barrier is sufficiently frangible to rupture to said open condition upon ignition of said fore propellant grain when said attitude maneuvering port is closed.