Compound Control Methods For Hypersonic Missiles

For the hypersonic missiles which fly in high density air, the combination of lateral jet thrusters and aerodynamic fins control system is designed in order to make the missile could establish angle of attack and respond to the overload command quickly. The direct force/aerodynamic compound missile usually has two actuators, how to make the aerodynamic fins and the side jet thrusters work coordinated with each other is the key problem for designing compound control system Firstly, we establish the linear pitch channel model of hypersonic missile with lateral jet thrusters. And then, according to the parameters of direct force and direct force moment, we give the analysis and simulation of the requirement of direct force/aerodynamic compound control technique for hypersonic missiles. In the end, based on blended control theory, we use two different methods to design the compound control law respectively:(1) The compound control system design based on LQR .For the aerodynamic fins loop, a missile object with good performance is obtained by LQR method. Furthermore, the lateral jet control law based on DLQR is designed for the discrete system. The simulation results show it can follow the overload command quickly.(2) The compound control system design based on Slide mode variable structure control. The aerodynamic fins loop control law is designed by continual slide mode control and the simulation result show quick response. For the lateral jet loop we use discrete slide mode control method to design the control law. The effectiveness and robustness of the proposed approach is validated by numerical simulation.