后缘襟翼机构动力学仿真研究  

Dynamic Simulation Study of Trailing Edge Flap Mechanism

作　　者：罗望 肖文耀 党万腾 LUO Wang;XIAO Wenyao;DANG Wanteng(AVIC Chengdu Aircraft Industrial(Group)Co,Ltd,Chengdu 610092,China)

机构地区：[1]航空工业成都飞机工业(集团)有限责任公司,成都610092

出　　处：《成都航空职业技术学院学报》2023年第3期25-28,共4页Journal of Chengdu Aeronautic Polytechnic

摘　　要：根据气动专业对某机型后缘襟翼气动要求及输入条件,采用空间位移矩阵方法完成后缘襟翼滑轨设计。对后缘襟翼各类机构驱动方式进行了对比研究,选择了滚珠螺旋丝杠驱动机构作为后缘襟翼驱动机构,满足了机构内埋的要求,并对该后缘襟翼机构进行了运动分析,研究其运动的合理性。最后,基于LMS Virtual.Lab Motion模块,对后缘襟翼机构进行了动力学分析,研究后缘襟翼机构在襟翼气动工况下的运动情况及受力情况。According to the aerodynamic requirements of the trailing edge flaps of a certain type of aircraft,the space displacement matrix method is used to design the trailing edge flaps mechanism.In this paper,various driving modes of trailing edge flaps mechanism are compared,and the ball screw driving mechanism is selected as the driving mechanism of trailing edge flaps,which meets the aerodynamic requirements,and the motion of the trailing edge flaps is analyzed to study the rationality of its motion.Finally,based on the LMS Virtual.Lab Motion module,the dynamics analysis of the trailing edge flap mechanism is carried out to study the movement and force of the trailing edge flap mechanism under certain aerodynamic conditions.

关 键 词：空间位移矩阵 后缘襟翼机构 Virtual.LabMotion 动力学仿真 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]