Patent ID: 6834828
Filing Date: 2004-12-28
Classification: F42B

Abstract:
A system for the deployment of guidance devices from the body of guided ordnance comprising:A) a missile body having a longitudinal dimension; B) a plurality of actuators in % aid body; C) a plurality of fins about the periphery of said body each comprising: I) a main body; II) a first end proximate connected to one of said actuators via a shaft; and III) a distal end remote from said first end; each of said fins being capable of longitudinal rotation by the action one of said actuators on one of said shafts; D) a plurality of slots equal in number to said fins, and parallel to said longitudinal dimension, each having an inner surface; each of said fins being located in one of said slots and further including a hinge and a spring intermediate said distal end and said actuator, each of said springs serving to force rotation of one of said fins about said hinge and toward said inner surface, such that upon longitudinal rotation of said fins by said actuators to a point where said fin clears said slot, said spring forces said fin to deploy via rotation about said hinge.