Patent ID: 8921749
Filing Date: 2014-12-30
Classification: F42B

Abstract:
1. A drive mechanism for a control actuation system of a guided missile, comprising: a reversible electric motor for rotating a power shaft, said motor mounted inside and being constrained from free movement by a control actuation system housing having a central longitudinal axis, said power shaft having a distal end extending from said motor, a spur gear pinion coupled to the distal end of said power shaft; a lead screw having a proximal and a distal end, said proximal end coupled to a spur gear, wherein said spur gear meshingly engages with said spur gear pinion, said spur gear configured to rotate in the opposite direction of said spur gear pinion; a lead nut threadingly engaged and configured to move linearly along the central axis of said lead screw, wherein said lead nut has at least one integrally-formed pin; a crank arm having at least one slot, wherein said crank arm is coupled to said lead nut by pin-and-slot engagement wherein said at least one slot of said crank arm engages with said at least one integrally-formed pin of said lead nut; wherein said crank arm is fixedly attached to the canard shaft of a canard assembly; and wherein said lead screw is oriented parallel to said motor and perpendicular to said central longitudinal axis.