Autopilot design for missile with morphing wings

Morphing concepts for missiles have been a topic of current research interest in aerospace engineering. For the morphing wings technology of missile, a kind of autopilot design method is proposed by H∞ control theory. In order to have the better flight performance in the different regimes, the missile can automatically change the wings area symmetrically. The nonlinear dynamic model is established, applying the approach of the multi-rigid body dynamics model, a whole body is viewed as composed of fixed body section and morphing section. By introducing the acceleration and the dynamic characteristic of control surface in the tail of missile, the nonlinear autopilot control system is derived. A linear autopilot controller is designed by solving the Riccati inequation. Finally an illustrative example is given to show that proposed autopilot control law is robust and suitable to the missile with morphing wings in the case of the different aerodynamic parameter, and the acceleration of missile can be tracked the command acceleration.