低氧环境热强度试验舱研制及性能验证  

Research and Capability Verification of Inert Atmosphere Heat Test Chamber

作　　者：尹涛[1] 高飞[1] 刘玥[1] 李红[1] 王晓晖[1] Yin Tao;Gao Fei;Liu Yue;Li Hong;Wang Xiao-Hui(Beijing Institute of Structure and Environment Engineering,Beijing,100076)

机构地区：[1]北京强度环境研究所,北京100076

出　　处：《导弹与航天运载技术》2018年第4期116-120,共5页Missiles and Space Vehicles

摘　　要：研制一套大型低氧环境试验舱,用于整弹试件的低氧环境热强度试验,提供模拟高空低氧环境的密封试验空间,对快速降氧能力和舱内温度、压力的控制能力进行试验验证,结果表明该试验舱可实现1h内达到并保持2%以下的低氧浓度、舱壁温度不超过50℃、舱内平均压力100±20Pa的控制效果,满足飞行器高空低氧环境模拟试验的要求,可为大型低氧环境模拟试验系统的研制提供参考。One large inert atmosphere test chamber is researched and established,for inert thermal environment test of entire missile,providing a inert sealed test chamber.The control capability of oxygen concentration,temperature,pressure has been validated.The test results shows that the test chamber can achieve and maintain the oxygen concentration of less than 2%within one hour,the temperature in the chamber not exceed 50℃,the chamber average pressure on 100±20Pa.This control effort satisfied aircraft high-altitude inert atmosphere simulation test requirements.Provide reference for the research of large inert atmosphere simulation test system.

关 键 词：高超声速飞行器 低氧环境 热环境 试验舱 性能验证 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]