Missile fin locking mechanism

DETAILED DESCRIPTION OF THE INVENTION Shown generally at (10) in FIG.
1 is a missile (12) which may be carried by appropriate fittings (not shown) underneath the wing of an aircraft for ultimate launching at a target.
Attached to an outer surface (14) of the missile is a plurality of fins (16-22) which as illustrated are disposed 90.
degree.
apart around the circumference of the missile.
Although four such control fins are shown in this particular drawing it should be understood that a lesser or greater number may be utilized depending upon the particular missile and its intended missions.
All or some of the fins (16-22) may be moveable for purposes of controlling the direction of flight both in yaw and pitch in accordance with a guidance mechanism included within the missile.
For example, one such guidance mechanism may utilize Global Positioning System (GPS) signals as is well known to direct the missile to a desired target which has been preprogramed into the guidance system of the missile.
Thus, after launch the GPS signals are utilized to provide motion to an appropriate drive mechanism which is connected by a drive train to a shaft upon which the fins (16-22) are mounted to effect movement of one or more of the fins to thus control the flight path of the missile.
As above referred to, while the missile (12) is affixed to the exterior to the aircraft and before launch, the fins (16-20) are subjected to aerodynamic loads as the aircraft carrying the missile moves through the atmosphere.
These aerodynamic loads can cause movement to the fins thus causing them to improperly direct the flight path of the missile (12) after launch or alternatively may apply such loads to the drive train deleteriously affecting it and cause failure of the missile as a result of fatigue, strain or failure of the drive train as a result of the application of the aerodynamic loads.
As is shown particularly in FIG.
2, a plurality of locking pins such as shown at 24, one for each of the fins (16-22) are adapted to extend outwardly away from the outer surface (14) of the missile (12) and into engagement with an opening (26) which is provided internally of the control fin (16)