大型民机襟翼间交联系统设计方法研究  

Design method of interconnection struts between flaps of large transport aircraft

作　　者：周晓宸 罗宇波 薛璞[1,2] 陆建国 ZHOU Xiaochen;LUO Yubo;XUE Pu;LU Jianguo(School of Aeronautics,Northwestern Polytechnical University,Xi′an 710072,China;Shaanxi Key Laboratory of Impact Dynamics and Engineering Application,Xi′an 710072,China;Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]陕西省冲击动力学与工程应用重点实验室,陕西西安710072 [3]上海飞机设计研究院,上海201210çö

出　　处：《西北工业大学学报》2022年第4期717-722,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(12072288,11672248)资助。

摘　　要：襟翼间交联系统(ICS)是一种增强襟翼系统可靠性的冗余设计,在襟翼系统故障时对故障引起的破坏起到抑制作用。空客、波音自20世纪80年代以来针对A320、B737等大型民机已经设计了多种ICS并投入使用;而国内在ICS方面的研究较少,目前仍属起步阶段。大型民机是我国航空业下一步发展的重点之一,为了给我国大型民机襟翼系统设计提供技术支持,开展了襟翼间交联系统设计方法研究,提出了一种新的ICS设计,在此基础上研究了交联机构的2个主要设计参数:交联机构的临界位移和吸能元件的平均压溃载荷,并对其力学性能以及在襟翼系统的故障工况中对故障载荷的抑制作用进行了仿真,验证了ICS设计方法的有效性和合理性。In the design of the modern large transport aircraft,flap system has become a standard configuration,which can increase the maximum wing lift and the climb rate of the aircraft.Meanwhile,the reliability of the flap system has always been the focus point of the aviation industry.The interconnection strut between flaps is a kind of redundancy design,which mitigates the failure of flap system enhancing flap system reliability.Since 1980s,aircraft manufacturers such as Airbus and Boeing have designed many kinds of ICS for the large transport aircraft like A320,B737.Meanwhile,there is some study on ICS in China,which is still in its infancy.In this paper,the design method of ICS is studied,and the important design parameters of ICS are proposed.A new kind of ICS is designed,and the validity and rationality of ICS design are verified.Firstly,the multi⁃body dynamic model for the flap system is established and the working principle and important design parameters of ICS between flaps are stud⁃ied;and then the energy absorbing characteristics of ICS energy absorbing elements are studied;finally,a new ICS is designed,and its mechanical properties and mitigation effect on flap system failure are simulated to verify the effectiveness and rationality of the design.

关 键 词：襟翼系统 交联系统 脱开故障 抑制作用 多体动力学 

分 类 号：V2[航空宇航科学技术]