飞机结构气动弹性分析与控制研究  

STUDIES ON AEROELASTIC ANALYSIS AND CONTROL OF AIRCRAFT STRUCTURES

作　　者：胡海岩[1] 赵永辉[1] 黄锐[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《力学学报》2016年第1期1-27,共27页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金(11472128;11502106);江苏省自然科学基金(BK20150736)资助项目

摘　　要：随着主动控制技术的发展,飞机结构设计理念已由提高结构刚度的被动设计转变为随控布局的主动设计.主动设计理念不再刻意回避气动弹性问题,而是采用主动控制技术实时调节结构气动弹性,进而减轻结构重量、优化飞机性能.在飞机随控布局主动设计中,必须深入分析结构与气流之间的耦合,才能更好发挥气动弹性主动控制技术的作用.从20世纪80年代起,航空科技界对该问题进行了长期研究,对飞机结构-空气动力-主动控制相互耦合后的关键力学问题有了深入理解.然而,已有研究多基于简化模型,导致研究结果难以直接应用于工程.本文将针对气动弹性动态问题,综述空气动力非线性、控制面间隙非线性、时滞诱发失稳、颤振主动抑制、突风载荷减缓、风洞实验验证等方面的国内外研究进展,重点介绍近年来作者团队所提出的若干方法及相关算例和风洞实验.最后,指出今后一个时期值得研究的若干气动弹性分析与控制问题.The development of active control has witnessed a great change in the design of aircraft structures, from the passive design of increasing structure stiffness to the active design in view of control configured aircraft. The idea of active design does not intentionally avoid the aeroelastic problem, but adjust the structural aeroelasticity via active control so as to reduce the structure weight and optimize the aircraft performance. To achieve this purpose, it is necessary to analyze the coupling between the aircraft structure and surrounding aerodynamic loads. The aeronautical community has made great efforts to study the corresponding aeroelastic problems and gain an insight into the coupling among aircraft structure, aerodynamics and active control since 1980＇s. However, most studies have been based on the simplified models. As such, it is difficult to apply the research achievements to aeronautical industry. This review article surveys the recent advances in the dynamic problems of aircraft aeroelasticity including the aerodynamic nonlinearity, the backlash nonlinearity of control surfaces, instability induced by time delay in control loop, active flutter suppression, gust load alleviation, as well as corresponding wind tunnel tests. The review focuses on the new approaches proposed by the team of authors, and the corresponding numerical simulations and wind tunnel tests over the past decade. Finally, the review addresses a numberof open problems related to the aeroelastic analysis and control.

关 键 词：颤振主动抑制 突风载荷减缓 间隙非线性 反馈时滞 非线性模型降阶 风洞实验 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]