某无人直升机框架内压支撑杆的有限元分析  

The finite element analysis of internal pressure- support bar for unmanned helicopter

作　　者：吴高强 宋军 姜年朝[1,2] 唐军军 焦志文 

机构地区：[1]总参六十所,江苏南京210016 [2]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《现代机械》2014年第2期25-28,39,共5页Modern Machinery

摘　　要：某无人直升机机身框架结构是由缘杆、立柱、横杆和支撑杆等杆件焊接而成的空间桁架结构。基于ANSYS软件,首先分析了机身框架内压支撑杆的强度、刚度,得到支撑杆在有无内压情况下的对比值,然后计算了有无内压情况下整个机身框架的固有频率和振型,全面评估了内压对框架的影响,指导和优化机身框架设计。这种有内压支撑杆的框架结构已成功应用于该无人直升机,外场飞行时间达到400多小时,框架结构未发生疲劳破坏。The fuselage frame of an unmanned helicopter is composed of edge bars, columns, beams and the internal pres- sure - support bars. Based on ANSYS software, the strength and stiffness of the internal pressure - support bar has been ana lyzed and the comparison values about the strength and stiffness in the inner pressure and without pressure condition has been calculated. Then the natural frequency and natural shape has been computed too. A comprehensive assessment of the effect of internal pressure on the fuselage frame and the optimal design about the fuselage frame has been given by the results of these calculations. The frame structure of internal pressure of the supporting bar has been successfully used to the un- manned helieonte.r which fliuht time to reach 400 houm_ and no fuselaue frame has the fatimm failure.

关 键 词：内压支撑杆 无人直升机 有限元分析 机身框架 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]