Missile Autopilot Design Based on Non-zero Set Point LQR Method

It's an efficient way to introduce static unstablity in the design of air-to-air missile.A two-loop longitudinal autopilot is designed to solve the problem of control on the statically unstable missile based on the theory of Non-zero set point regulator.Firstly,a missile's longitudinal model in the style of state space notation is introduced,which is established on the hesperian body axis system,at the same time,the distance between accelerometer and centroid is drawn into the model.And then,the optimal control is derivated from the theory of LQR and Non-zero set point regulator,with which a common result is obtained,and then,the autopilot is designed.At last,the weights are researched with the classical control theory,and the autopilot's performance is analyzed from its robustness、anti-jamming ability and the affection of the distance between accelerometer and centroid.Results show that the autopilot has a stronger robustness,which can control the statically unstable missile efficiently.