Firing logic optimization design of lateral jets in missile attitude control systems

For a missile with blended lateral jets and aerodynamic fins, a simplified model is derived in short period for the longitudinal plane. Since the fast response requirement on the attitude of the missile, lateral jets are preferable to aerodynamic fins for rapid response, both of which can provide attitude control torque, but with different response speeds. In this situation, the output is predicted via Fliess functional expansion based on the discrete characteristic of lateral jets. A firing logic optimization design of lateral jets in missile attitude control systems is proposed, which is formulated to solve an optimal problem. Considering the uncertainties of disturbance force caused by lateral Jet Interaction Effects, the thrust amplification factor is estimated on line by the same way, which is used to produce the optimal control. Fast response of the angle of attack is achieved by using the proposed attitude control law. Simulation results show the effectiveness of the proposed method.