改进动态面控制方法及其在过失速机动中的应用  

An improved dynamic surface control law and its application in post-stall maneuvers

作　　者：章胜 汪清[1] 何开锋[1] 邵元培[1] 

机构地区：[1]中国空气动力研究与发展中心计算空气动力学研究所,四川绵阳621000

出　　处：《空气动力学学报》2017年第5期718-726,共9页Acta Aerodynamica Sinica

摘　　要：为提高模型飞行试验中飞机过失速机动控制品质,发展了一种考虑非定常气动力效应与舵回路作动器模型的改进动态面飞行控制律。针对一般仿射模型情形的控制律设计了流程:首先针对子系统推导动态面控制律,然后综合全系统并考虑控制约束导出滑模控制律,在一定的假设条件下,证明了闭环控制系统为输入-状态稳定。在应用提出的控制方法进行过失速机动控制律设计中,为准确预测飞机非定常气动力效应,利用过载测量量反解飞机气动力、采用微分方程模型计算飞机非定常力矩。由于综合了作动器动力学模型,控制律的控制效果受作动器带宽影响较小,可以有效消除由作动器动态响应引起的控制效果变差问题,同时控制律中对非定常气动力效应的有效预测也有利于过失速机动品质的改善。To enhance the f ly in g quality of aircratt pos--stall maneuver in a model f l ig h t te s t, an improved dynamic surface f l ig ht control law was proposed in consideration of the unsteady aerodynamics effect and the actuator model. The controller designing procedure was established for general affine models. In the procedure, the dynamic surface controller fo r the sub-systemwas first developed. Then the slide mode control technique was employed to synthesize the whole system with the control l imitat ion . The closed system was proved to be input-to-state stable under certain conditions. To accurately predict the unsteady aerodynamics in the post-stall maneuver controller designing, the overload measurement was used to solve the aircraft aerodynamic force, and the dif ferential equation model was developed to compute the unsteady aerodynamic moment. The control effect of the proposed controller is nearly independent of the actuator bandwidth due to the inclusion of actuator model, and the lag effect from the dynamic response of the actuator is effectively attenuated. The valid prediction of the unsteady aerodynamics is also helpful to improve the quality of the post-stall maneuver.

关 键 词：模型飞行试验 过失速机动 非定常气动力 动态面控制 骨模控制 

分 类 号：V249[航空宇航科学与技术—飞行器设计]