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To suppress the large overload caused by control surface deflection when the flight mode transitions,reducing the requirements of servos and available overload,the flight control law was designed combining the robust servo LQR and the classical control. Take the pitch angle control mode for example,the characteristics of robust LQR control method were analyzed,pitch rate control law was designed using robust servo LQR optimal control method,pitch angle control law was designed using classical control method,the control effects were verified according to nonlinear digital simulation. The results showed that:the overshoot of pitch angle response decreasing by 50% using robust LQR control method, LQR robust servo control than conventional PID control overshoot is reduced by 50%,The phenomenon of a larger angle rate because of servo command mutation is suppressed in initial response, the requirements of available overload is greatly reduced. The form of the control law was simple,and easy to implement in engineering.