Procedure for steering a low-speed missile, weapon system...

Details Procedure for steering a low-speed missile, weapon system... Procedure for steering a low-speed missile, weapon system...

G - Physics

05

D

89/3

G05D 1/10 (2006.01) F42B 15/033 (1985.01)

Patent

CA 1265947

ABSTRACT OF THE DISCLOSURE A missile for launching from a launching tube, including a combat payload and a propulsion system of the propulsive fuel-load type. The propulsion system comprises two boosters arranged in the rear of the missile, the combustion of the boosters being terminated before the missile exits from the launching tube. The boosters impart a low initial speed to the missile when the missile exits from the launching tube. A flight propulsion unit includin- g lateral nozzles enables steering of the missile by force and arranged for simultaneously imparting to the missile during flight of the missile axial propulsive thrust and maneuver forces for steering by force. The combat payload, the two boosters and the flight propulsion unit are arranged in the missile, so that when the missile exits from the launching tube after combustion of the two boosters, the center of gravity of the missile is positioned in a plane trans- verse to the longitudinal axis of the missile and including the maneuver forces, and during the flight of the missile and progressive combustion of the flight propulsion unit, the position of the center of gravity of the missile moves rear- wardly along the longitudinal axis of the missile, thereby enabling the generation of the aerodynamic torques for produc- ing maneuver forces which are added to the maneuver forces pro- vided for the steering by force.

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