单侧机翼损伤飞机的神经网络自适应鲁棒非线性控制  

Neural network based robust adaptive nonlinear control for aircraft under one side of wing loss

作　　者：程鹏飞[1] 吴成富[1] 

机构地区：[1]西北工业大学无人机特种技术重点实验室,陕西西安710065

出　　处：《系统工程与电子技术》2016年第3期607-617,共11页Systems Engineering and Electronics

基　　金：解放军总装预研项目(513250202)资助课题

摘　　要：针对飞机飞行中单侧机翼突然损伤问题,结合对损伤飞机的特性分析,提出基于神经网络自适应补偿的鲁棒非线性模型逆控制方法。利用未损伤飞机模型伪控制量中的单隐层神经网络自适应项和鲁棒项,并联合e-modification自适应律对模型误差、外界扰动、神经网络近似误差进行补偿。除此之外,利用动态非线性阻尼技术对上述伪控制律进行扩展,从而适应损伤机体未建模舵动态。最后对上述算法进行严格的稳定性证明,并推导了逆过程的实现方法。仿真结果表明在单侧机翼突然损伤并伴随外部扰动和未建模舵动态下,该控制方法具有较强的稳定性和鲁棒性。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.

关 键 词：单侧机翼损伤 神经网络自适应补偿 非线性模型逆控制 动态非线性阻尼 未建模舵动态 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]