Patent ID: 8299411
Filing Date: 2012-10-30
Classification: B64C,F42B

Abstract:
1. A system for controlling a control surface on a missile, the system comprising: a control surface; an elongated member coupled to said control surface of said missile, said elongated member having a first member end and a second member end; a T-shaped bar coupled to said elongated member, said bar having a first bar end and a second bar end; a pivotable link coupled to said elongated member; first actuator means coupled to said T-shaped bar at said first bar end; second actuator means coupled to said T-shaped bar at said second bar end; wherein said control surface is coupled to said elongated member at said first member end of said elongated member; said T-shaped bar is coupled to said elongated member at said second member end of said elongated member, said second member end being coupled to said T-shaped bar at a point between said first bar end and said second bar end; when either said first or second actuator means is actuated, said elongated member pivots about said pivotable link to deploy or retract said control surface.