Solid rocket motor with dual interrupted thrust

摘要

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.