空空导弹典型部位密封优化设计与试验验证  

Seal Optimization and Test Verification of Air-to-air Missile Typical Parts

作　　者：梁子豪 刘仙名[1] 黄帅军[1] LIANG Zi-hao;LIU Xian-ming;HUANG Shuai-jun(China Air-borne Missile Academy,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院

出　　处：《液压气动与密封》2019年第11期42-46,49,共6页Hydraulics Pneumatics & Seals

摘　　要：上舰空空导弹要求结构设计做到气密,电子舱作为控制中枢,对密封要求较高。工程实践表明,电子舱壳体开矩形口的部位是密封薄弱环节,如引信窗口、数据链窗口处,原有的矩形密封圈和单螺钉连接方式无法满足舰载环境下的气密要求。该文基于MSC Patran/Nastran分析了连接螺钉造成的结构变形,总结出原方案气密失效的原因,提出针对性的优化方案,并加工电子舱模拟件,开展气密性能试验,结果证明优化方案可行。The air-to-air missile of the navy requires structural design to be airtight,and the electronic cabin as the control center has high requirements for sealing.The engineering practice shows that the part of the electronic compartment shell that opens the rectangular mouth is the weak part of the seal.For example,the fuse windows and the data link windows,the original rectangular seal ring and the single screw connection method cannot meet the airtight requirements under the shipboard environment.Based on MSC Patran/Nastran,this paper analyzes the structural deformation caused by the connecting screws,summarizes the causes of the airtight failure of the original scheme,proposes a targeted optimization scheme,and processes the electronic cabin simulation parts to carry out the airtight performance test.The results prove that the optimization scheme is feasible.

关 键 词：气密优化 矩形密封圈 变形仿真 气密试验 

分 类 号：TB42[一般工业技术]