초록 ▼

An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve c

An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve communicating the fuel and the oxidizer and a second conduit, spatially removed from the first conduit, has a second valve communicating the fuel and the oxidizer. An inlet system for delivering atmospheric oxygen for combustion with the fuel rich gases generated within the missile and a nozzle exhausts combustion products that result from combustion of the fuel, the liquid and solid oxidizers, and air.

대표청구항 ▼

What is claimed is: 1. 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 missi

What is claimed is: 1. 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 180°;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; andan obstructed air inlet having a nose end and a body end with said body end terminating at said combustor.