Experimental and numerical investigation of the effect of the structural of a fin actuation system on system behavior

The fin actuation system moves the fins that provide the missile guidance. It is very important to reduce the uncertainties about the behavior of these systems to a minimum level so that the missile can make a successful flight. In this study, the system of the structural of electromechanical fin actuation system which is based on an inverted slider crank mechanism effects on the system. Experimental and numerical investigated, for an air to ground missile. Clearance on revolute joint and structure deformation affecting the actuation of the fin under aerodynamic loads have been examined in detail. Mechanism analyzes were carried out by multibody dynamic simulations. The main load acting on the system is due to the aerodynamic hinge forces. The elastic deformations caused by the aerodynamic forces were analyzed using the finite element method for different fin angles. Also, involuntary change of the fin angle has been investigated under the forces which are exerted by using a real-time fin loading system. The variation of the angle of the fin resulting from the elastic deformation and the clearance of revolute joint was obtained in real time at different fin angles. The mechanism analysis of the fin actuation system was verified by analytical methods; on the other hand, the result obtained from the experimental measurements and analyzes performed using the finite element method. Results were compared and a high consistency was obtained between them.