背部进入式舱外航天服穿脱口铰链配置优化研究  

Optimization of Configuration of the Hatch Closure Hinges of the Rear Entry Spacesuit Used for EVA

作　　者：周仕明[1] 李道奎[1] 唐国金[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2010年第2期7-11,共5页Journal of National University of Defense Technology

基　　金：国家部委资助项目(513270301);高等学校博士学科点专项科研基金项目(20069998002);国防科学技术大学科研计划项目(JC06-01-01)

摘　　要：应用有限元方法对内压作用下舱外航天服穿脱口密封结构进行了受力分析,针对服装泄压后穿脱口残余内力和变形过大问题,建立了铰链配置优化模型,得到了一种更为合理的铰链配置方案。研究结果表明,对舱外航天服这类几何结构不规则压力容器,优化铰链配置可以改善结构内力分布,减小由结构发生局部塑性变形而引起的结构残余内力。Based on the finite element method, the strength and stiffness of spacesuit hatch closure under internal pressure are calculated. The optimization model of the hinges configuration is established to reduce residual internal force of the hinges. An improvement configuration of the hinges is obtained. The results demonstrate that the optimal configuration of the hinges of the irregular shaped pressure vessel can reduce the residual internal force as a result of the structural plastic deformation.

关 键 词：舱外航天服 密封结构 结构分析 有限元法 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]