襟翼运动机构全尺寸疲劳试验技术研究  

Research on Full-Scale Fatigue Test Technology of Flap Mechanism

作　　者：刘玮[1] 刘冰[1] 郑建军[1] Liu Wei;Liu Bing;Zheng Jianjun(Aircraft Strength Research Institute of China,Full Scale Aircraft Static/Fatigue Laboratory for Large Airliner,Shanghai 200120,China)

机构地区：[1]中国飞机强度研究所,全尺寸飞机结构静力/疲劳航空科技重点实验室,上海200120

出　　处：《工程与试验》2022年第2期37-38,106,共3页Engineering and Test

摘　　要：根据大型客机富勒式襟翼运动机构适航验证的需要,对襟翼运动机构疲劳试验方案及技术进行了研究。通过对襟翼及其运动机构的解构,识别出运动机构的位移与载荷边界条件,提出了对单独运动机构进行约束、驱动与加载的试验方案,并通过运动仿真与有限元分析加以验证,形成了富勒襟翼运动机构疲劳试验技术,并将其成功应用于型号试验。新技术实现了对试验件及分析模型更清晰有效的验证,同时也大幅减少了试验件制造成本与试验资源占用。Aiming at the need of airworthiness verification of Fuller flap mechanism of large civil aircraft,the fatigue test scheme and technology of flap mechanism are studied.Through the deconstruction of the flap and its motion mechanism,the displacement and load boundary conditions of the motion mechanism are identified,and the test scheme of restraining,driving and loading for individual motion mechanism is put forward.The fatigue test technology of Fuller flap mechanism is formed through the motion simulation and finite element analysis,and it has been successfully applied to model test.The new technology not only realizes the clearer and effective verification of the test piece and analysis model,but also greatly reduces the manufacturing cost of the test piece and the occupation of test resources.

关 键 词：襟翼运动机构 疲劳试验 试验技术 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]