Flying wing aircraft reconfiguration flight control law design method based on the LI adaptive control and sliding mode observer is proposed in this paper. In the condition of no failure information, the LI adaptation law and control law are used to reconfiguration actuator failures. For high gain question, low-pass filter is used to restrain the high frequency oscillation and eliminate the high frequency control signal. For LI adaptive reconfiguration control system, the asymptotical control stability is proved. In order to decrease the control error caused by reconfiguration error and airplane model uncertainty, the sliding mode observer is designed and used to generate the compensating signal. The simulation results show that the flying wing aircraft has good control performance in the condition of actuator surface failure.