PROCEDURE FOR STEERING A LOW-SPEED MISSILE, WEAPON SYSTEM AND MISSILE FOR IMPLEMENTATION OF THE PROCEDURE

摘要

ABSTRACT OF THE DISCLOSUREA missile for launching from a launching tube,including a combat payload and a propulsion system of thepropulsive fuel-load type. The propulsion system comprisestwo boosters arranged in the rear of the missile, thecombustion of the boosters being terminated before themissile exits from the launching tube. The boosters imparta low initial speed to the missile when the missile exitsfrom the launching tube. A flight propulsion unit includin-g lateral nozzles enables steering of the missile by forceand arranged for simultaneously imparting to the missileduring flight of the missile axial propulsive thrust andmaneuver forces for steering by force. The combat payload,the two boosters and the flight propulsion unit are arrangedin the missile, so that when the missile exits from thelaunching tube after combustion of the two boosters, the centerof gravity of the missile is positioned in a plane trans-verse to the longitudinal axis of the missile and includingthe maneuver forces, and during the flight of the missileand progressive combustion of the flight propulsion unit, theposition of the center of gravity of the missile moves rear-wardly along the longitudinal axis of the missile, therebyenabling 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.