Patent ID: 6481198
Filing Date: 2002-11-19
Classification: F02K

Abstract:
A multi-stage rocket motor assembly comprising:at least one main motor subassembly comprising at least one flight igniter, a main motor case structure containing at least one main combustion chamber loaded with at least one main propellant which is ignitable by said flight igniter, and a nozzle subassembly defining a combustion product passage in communication with said combustion chamber, said combustion product passage including a throat portion and an aft exhaust portion; and at least one launch motor subassembly comprising at least one launch igniter and a launch motor case structure, said launch motor case structure housing at least one launch combustion chamber loaded with at least one launch propellant which is ignitable by said launch igniter, said launch motor subassembly and said nozzle subassembly being detachably connected to permit both detachment of said launch motor subassembly from at least said nozzle subassembly while said rocket motor assembly is in flight and jettisoning of said launch motor subassembly after initiation of said main propellant, wherein said flight igniter is integrated with said launch motor subassembly to permit said flight igniter to be jettisoned essentially in unison with said launch motor subassembly, and wherein said launch motor subassembly does not extend substantially beyond said aft end portion of said nozzle subassembly.