Abstract:

The missiles formation flight control system including of missile inner-loop controller; outer-loop and formation controller is described. The missile formation flight controller and missile outer-loop controller are emphatically analyzed. Facing the augmentative flight control system possessing overload autopilot as a missile inner-loop, a decoupled controller based on the total energy control theory is designed. A combination of proportion and differential control of the position error is used in the design of the missile formation flight controller to generate the control command for the single missile. Simulation result demonstrates that each loop and the missiles formation controller are capable of controlling, and the reconfigure action could be achieved rapidly and stably, and then the engagement mission presented by the mission planning system could be implemented.