摘要
以往研究已经证明机翼后掠角和后缘弯度的单独改变均可增强飞行器的机动性,探究将后掠角作为冗余控制器后飞机滚转运动收敛特性问题。首先利用计算流体力学方法,探讨了后掠角非对称变化对气动特性的影响规律,建立了不同工况下研究对象飞机后掠角、柔性后缘两种广义操纵面的操纵效能函数。其次综合Kane方法建立的稳定滚转子系统动力学模型,在考虑飞机阻尼力矩影响下,确定了监督控制器-主控制器控制架构下系统主、从控制器控制律。最后将后掠角非对称偏转作为系统冗余控制输入,以操纵面偏转速率为特征量,分析了不同工况下后掠角非对称变化对飞行器稳定滚转运动收敛特性的影响。通过分析可知,采用冗余操纵面设计,可有效增大滚转控制力矩,避免操纵面进入饱和状态,提升飞机整体控制效能。通过两种工况下的仿真结果可知,后掠角操纵面可增强系统容错能力、提升高升力下飞机操纵性能,但会增大系统达到稳定所需的时间。
Previous studies have shown that the maneuverability of aircraft can be enhanced by changing the sweepback and wing camber separately. The convergence characteristics of aircraft roll control with sweep angle as a new redundant controller are investigated. Firstly, the method of computational fluid dynamics is used to establish roll efficiency functions for both general control surfaces under different working conditions, and Kane’s method is used for the dynamics equations of stable roll subsystem. Then, on the basis of dynamic model of the stable roll subsystem established by Kane’s method, the control laws of the main and supervisory controller are determined under supervisory-main control architecture by considering the influence of the damping moment. Finally, with asymmetric change of sweep as the redundant input of the system, the convergence characteristics of the stable roll motion of the aircraft under different working conditions are analyzed by introducing the deflection rate of generalized control surfaces as characteristics quantity. Analysis results show that using redundant control surfaces can effectively increase rolling moment and prevent controllers from turning into saturation state, which will improve the control efficiency inside the whole flight envelope. Simulation results under two working conditions show that using sweepback generalized control surface can enhance system’s fault tolerance capability and improve the performance of aircraft under high lift, but will increase the time required to stabilize the system.
作者
马航
宋笔锋
裴扬
白春玉
MA Hang;SONG Bifeng;PEI Yang;BAI Chunyu(School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China;Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics, Aircraft Strength Research Institute of China, Xi’an 710065, China)
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2019年第5期1094-1102,共9页
Systems Engineering and Electronics
基金
航空科学基金(20174123008)资助课题
关键词
非对称后掠角
柔性后缘
滚转效能
控制分配
asymmetric sweep angle
flexible trailing edge
roll efficiency
control allocation
