Patent ID: 6543716
Filing Date: 2003-04-08
Classification: B63G,F41F,F41G,F42B,G01S

Abstract:
In a guided missile having a rocket motor disposed within the body of such missile to provide forward thrust and a control surface assembly, consisting of a set of movable vanes in the jet stream of the rocket motor and a like set of movable aerodynamic control surfaces outside the body of such missile, each one of both such sets being affixed to a different shaft rotatably mounted in the body of such missile, actuators for the control surface assembly, each one of such actuators comprising:(a) an electric motor disposed within the body of the guided missile about the shaft affixed to the movable aerodynamic control surface; (b) a reduction gear also disposed within the body of the guided missile about the shaft affixed to the movable aerodynamic control surface, such gear being connected between the electric motor and such shaft; (c) pulley means disposed within the body of the guided missile to connect such shaft and the shaft supporting a corresponding one of the set of movable vanes; and (d) means for actuating the electric motor.