导弹增量式自适应容错控制系统设计

Aerodynamic parameter uncertainties and actuator failures in missile flight will severely affect the stability and operation of the flight system. Therefore, we investigate an incremental adaptive passive fault tolerant control method to ensure safe control in missile flight as well as effectiveness and reliability of the control algorithm. A control oriented coupled attitude dynamics model was presented. In order to avoid system uncertainties and actuator failures, a passive fault tolerant control law was designed based on incremental nonlinear dynamic inversion. An incremental nonlinear dynamic inversion-based adaptive fault tolerant control law was established by combining the adaptive sliding mode control method and the incremental nonlinear dynamic inversion approach. Meanwhile, the residual of the system was analyzed and compared. A typical full trajectory attitude tracking mission was conducted to verify the control performance under actuator faults. Simulation results show that the proposed system can ensure robustness and fault tolerance without the fault diagnosis knowledge, which could eventually achieve safe and reliable flight control.