Abstract:

Since a system has a characteristic of control delay during the design of the aircraft optimal feedback controller, the delay control system is transformed to a nondelay control system by utilizing the continuous states transform method.Then using the solution of the non-delay control system,which makes the performance index smallest,the state function of the original system can be calculated. With the help of relationship between the delay feedback control and the statetransformed optimal control, it can help find the gain of the optimal time delay feedback control. Simulation is made to verify the hovering data of unmanned helicopter experiments and the results validate the proposed control method.