Propulsion/control modular booster

#1. Field of the Invention

#This invention relates to a device that adds extra capabilities to guided missiles. More particularly, the device minimizes trajectory apogees of a guided missile, by providing a booster which utilizes three-axis thrust vector control (TVC).

#2. Description of the Prior Art

#FIG. 1 is a perspective view of a guided missile and the invention;

#FIG. 2 is a side view of the invention with a partial cut-away of the booster shroud;

#FIG. 3 is a forward end view of the booster shown in FIG. 2;

#FIG. 1 is a perspective view of a guided missile 10 and apogee control booster 15. FIG. 2 shows a side view of booster 15, which is composed of three major components: a rocket motor/solid propellant module 20, a boost guidance unit (BGU) 30, and a thrust vector control (TVC) unit 50. Guided missile 10 may either be submarine launched or surface vessel launched, and may be the type to normally carry its onw missile guidance unit (MGU) that receives initial commands from the launch vessel's fire control system.

#FIG. 2 shows a side view of booster 15 and details of rocket motor/solid propellant module 20. Module 20 is of the type normally found in the rocket industry. A rocket shroud 21 encircles the internal components and provides the structural backbone of module 20. The lower half of shroud 21 is cut away in FIG. 2 to show the internal parts of module 20.

#Module 20 is of the standard, tubular shape and has a propellant grain 22 cast inside it and case bonded to its inside walls. A pyrotechnic igniter 23 extends into the central bore of propellant grain 22, and is electrically connected to an arm/firing device 24 which is electrically connected through wiring harness 27 to a power source on the launch vehicle. Arm/firing device 24 acts to block the electric charge from reaching igniter 23 thereby preventing igniter 23 from discharging until the proper time.