초록 ▼

The invention disclosed is a solid propellant rocket motor, capable of providing two separate propulsive impulses to a missile. The rocket motor is connected at one end to the missile body, the other end including an exhaust nozzle. The rocket motor comprises two stages connected by an interstage bu

The invention disclosed is a solid propellant rocket motor, capable of providing two separate propulsive impulses to a missile. The rocket motor is connected at one end to the missile body, the other end including an exhaust nozzle. The rocket motor comprises two stages connected by an interstage bulkhead. The bulkhead includes a port opening which is closed by a frangible cover which prevents the second stage from igniting during burning of the first stage, but breaks up into harmless fragments during firing of the second stage.

대표청구항 ▼

A solid propellant rocket motor, capable of providing two separate interrupted propulsive impulses to a missile, comprising: a cylindrical open-end casing, one end of which is to be connected to the missile body, the other end including an exhaust nozzle having a single centrally located opening; a

A solid propellant rocket motor, capable of providing two separate interrupted propulsive impulses to a missile, comprising: a cylindrical open-end casing, one end of which is to be connected to the missile body, the other end including an exhaust nozzle having a single centrally located opening; a first stage combustion chamber adjacent the aft-end of said casing; a first stage igniter and solid propellant composition disposed in said first stage combustion chamber; a second stage combustion chamber adjacent the fore-end of said casing; a second stage igniter and solid propellant composition disposed in said second stage combustion chamber; interstage bulkhead means separating said first and second combustion chambers; central port means provided in said bulkhead to connect said first and second combustion chambers; and port closure means, wherein the area of the port opening is greater than the smallest area of the nozzle opening to ensure sub-sonic flow of combustion gases from said second combustion chamber and wherein said port closure means is dome shaped with a convex surface facing said first stage combustion chamber and a concave surface facing said second stage combustion chamber, said port closure means having a compressive-to-tensile strength ratio of about 3:1 to withstand compressive combustion pressures applied forwardly during the firing of the first stage, and is made of a suitable frangible material which will break up into harmless fragments under tensile combustion pressures exerted rearwardly during the firing of the second stage.