A Method of Autopilot Design for a Missile with Lateral Thrust

In this a synchronous blended method for missiles with aero-fin and lateral thrust control is presented.The mathematical model of the missile with this blended control and the details of autopilot design are given.The autopilot has the traditional structure.The iner part is rate loop which adopt continuous control policy,the outer part is accelerometer feedback loop which adopt variable structure control law to decrease the effect of parameter variation.The simulation results show that this blended method could increase the maxmal output acceleration and the fast reponse ability simultaneously,and the autopilot has good performance.