Patent ID: 8056319

Claim:
An insensitive combined cycle missile propulsion system, comprising: a first section of said missile having an upstream end and an opposing downstream end with a solid fuel contained therein, said sold fuel having an opening extending therethrough; a second section of said missile containing a liquid oxidizer adjacent said upstream end with a first liquid oxidizer injector disposed therebetween; a first conduit adjacent said downstream end having a shaped bend effective to change a direction of flow of combustion products of said solid fuel and said liquid oxidizer by about 180Â°; a second conduit having a second liquid oxidizer injector extending from said second section to a point downstream of said shaped bend; a rocket nozzle downstream of said second liquid oxidizer injector effective to exhaust combustion products resulting from combustion of said solid fuel and said liquid oxidizer into a combustor; an oxidizer rich boost propellant coating interior walls of said combustor; and an obstructed air inlet having a nose end and a body end with said body end terminating at said combustor.