Abstract:

Combined with the characteristics of wingdamaged aircraft, a method of neuroadaptive compensation based robust nonlinear modelinversion control is proposed for oneside of wing damage suddenly in flight. The method employs one singlehiddenlayer neural network (SHL NN) adaptive element and one robust element in pseudocontrol of the undamaged aircraft model with emodification adaptive laws to compensate model errors, external disturbances and NN approximation errors simultaneously. In addition, a dynamic nonlinear damping technique is employed to expand the pseudocontrol law above for robustifying the unmodelled actuator dynamics of the damaged plant. Finally, the strict stability proof is given and the realization of the inversion process is derived. The simulation results validate the strong stability and robustness of the control algorithm under wing damage accompanied with output noise and unmodelled actuator dynamics.