基于惯性释放的某型无人直升机有限元分析  

Finite element analysis on unmanned helicopter based on inertia relief

作　　者：路林华 姜年朝 王克选 张逊 LU Linhua;JIANG Nianzhao;WANG Kexuan;ZHANG Xun(Nanjing Research Institute of Simulation Technology, Nanjing 210016, China)

机构地区：[1]南京模拟技术研究所,南京210016

出　　处：《计算机辅助工程》2018年第2期57-60,共4页Computer Aided Engineering

摘　　要：基于惯性释放理论,对某型无人直升机的整机强度和刚度进行仿真。与传统计算方法相比,惯性释放法能有效避免边界条件对结构传力路径的影响,更加精确地反映结构的真实应力情况。根据直升机的结构和载荷特点,总结虚约束的施加方法,使结构的变形状况更加直观、真实。该方法可以为相似结构直升机的刚度分析提供参考。The strength and stiffness of a unmanned helicopter is simulated based on inertia relief theory.Compared with the traditional calculation method,the influence of boundary conditions on transmission path of structure can be avoided by inertia relief method. The real stress situation of structure can be reflected more accurately. According to the structure and load characteristics of the helicopter,a method of applying virtual constraint is summarized,which makes the structure deformation more visually and exactly. The method can provide reference for the stiffness analysis of the helicopters with similar structure.

关 键 词：无人直升机 惯性释放 虚约束 强度 刚度 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程] V275.1