民用飞机顺气流襟翼机构故障工况动力学仿真研究  

Dynamics simulation research on fault conditions of deflecting to airflow flap mechanism of civil aircraft

作　　者：冯蕴雯[1] 何智宇 唐家强 薛小锋[1] 汪艳秋 FENG Yunwen;HE Zhiyu;TANG Jiaqiang;XUE Xiaofeng;WANG Yanqiu(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;Aircraft Structure and Stress Division,Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]上海飞机设计研究院飞机结构强度工程技术所,上海201210

出　　处：《航空工程进展》2023年第4期85-93,共9页Advances in Aeronautical Science and Engineering

摘　　要：民用飞机顺气流襟翼一般由空间复杂多铰机构驱动,按照适航条款CCAR25.671的要求需开展典型故障下的机构特性研究。构建机构运动数字样机,采用RBE2单元将刚性多铰机构铰链点关联至柔性襟翼本体,建立襟翼机构刚柔耦合动力学模型;在巡航、起飞、着陆三种气动载荷工况下,采用调节铰链摩擦系数和设置单侧驱动失效的方法分别模拟铰链卡滞和操纵系统单侧失效两种典型故障,并分析驱动力矩和铰链点载荷的变化规律。结果表明:铰链卡死时,内侧驱动连杆耳片发生拉伸破坏;内侧驱动失效时,外侧摇臂铰链点径向载荷提升明显,在实际中应重点关注该类襟翼外侧摇臂中关节轴承的径向和轴向承载能力,避免外侧机构出现单独操纵的情况,同时需要对整个驱动系统增加扭矩保护。The deflecting to airflow flap of civil aircraft are generally driven by complex multi-hinge mechanisms in space.According to the requirements of the airworthiness clause CCAR25.671,it is necessary to carry out research on the mechanism characteristics under typical faults.Firstly,a digital prototype of the mechanism motion is con‐structed,and the hinge point of the rigid multi-hinge mechanism is associated with the flexible flap body by using the RBE2 unit,and the rigid-flexible coupling dynamic model of the flap mechanism is established.Then,under three aerodynamic load conditions of cruise,take-off and landing,two typical faults,hinge jamming and one-side failure of control system,are simulated by adjusting the hinge friction coefficient and setting one-side driving fail‐ure.Finally,the variation law of driving torque and hinge point load is analyzed.The results show that:when the hinge is stuck,the inner drive link ear piece is stretched and damaged;when the inner drive fails,the radial load at the hinge point of the outer rocker arm increases significantly.In practice,we should focus on the middle joint of the outer rocker arm of this type of flap.The radial and axial load-bearing capacity of the bearing avoids the situation of separate manipulation of the outer mechanism,and at the same time,it is necessary to increase the torque protec‐tion for the entire drive system.

关 键 词：增升装置 刚柔耦合 动力学仿真 故障模拟 

分 类 号：V267[航空宇航科学与技术—航空宇航制造工程] V224.5