翼尖悬挂物结构动强度设计与分析  

Structure Dynamic Strength Design and Analysis for Wing-tip Pod of Electronic Warfare Aircraft

作　　者：周敏亮[1] 王虎寅 曹奇凯[1] ZHOU Minliang;WANG Huyin;CAO Qikai(Shenyang Aircraft Design&Research Institute,Shenyang 110035,China)

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞机设计》2020年第3期26-29,39,共5页Aircraft Design

摘　　要：翼尖悬挂物是飞机平台的1种基本构型,可装置电子设备,实现某些特定功能,飞行过程中,由于受到各种静、动载荷的作用,翼尖舱结构易产生极高的应力水平,从而降低结构使用寿命,影响飞机飞行安全。文中选取某型翼尖舱,开展了结构模态分析、动响应分析,以及振动疲劳寿命分析,通过全机地面共振试验和振动试验验证,计算结果与试验结果相吻合,结果表明翼尖舱结构设计合理,满足动强度在飞机设计上的要求。ECM equipments are often internally installed in wing-tip pod.During flight,the wing-tip pod will generate extremely high dynamic stress due to various dynamic loads,which reduce the fatigue life of the structure and thus affect flight safety.In this paper,the structural modal analysis,dynamic response analysis and vibration fatigue life analysis of wing-tip pod are carried out.The analysis results coincide with the test results by the GVT and vibration test,which shows that the wing-tip pod design of electronic warfare aircraft is reasonable and can meet the dynamic strength requirement in the aircraft design.

关 键 词：翼尖舱 固有频率 振动疲劳 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]