神舟七号飞船气闸舱热试验方法  

Thermal Test Method for Airlock Cabin of Shenzhou-7 Spaceship

作　　者：黄家荣[1] 范宇峰[1] 刘炳清[1] 金岩[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《宇航学报》2009年第5期2086-2091,共6页Journal of Astronautics

摘　　要：简要介绍了神舟七号出舱活动飞船气闸舱单舱热试验(包括热平衡试验和泄复压热试验)情况,分别给出了试验技术状态、试验工况、试验过程及典型的试验结果等,重点论述了舱段级热试验所采取的通风对流换热模拟、流体回路换热模拟、固体传热边界模拟的关键技术。将试验结果与飞行遥测数据进行了比对分析,两者一致性很好,表明所采取的热边界模拟方法合理正确,舱段级热试验获得了成功,达到了缩短研制周期、节约研制经费的预期目的。This paper briefly describes Shenzhou-7 extra-vehicular activity （EVA） spaceship Airlock Cabin thermal test, including thermal balance test and pressure relief and recovery thermal test, respectively provides the test technical status, thermal test case, test procedure, the typical test results,etc. Emphatically, it discusses a series of module-level thermal test key technologies, such as aeration convection simulation, fluid loop heat transfer simulation and solid heat conduction simulation. It also makes a comparison analysis of the test results and the on-orbit flight data, there is a very marginal difference between them, and this shows that the thermal boundary simulation method is logical and correct. The Module-level thermal test is successful, and the expectant purpose for shortening development period and saving fund is achieved.

关 键 词：出舱活动 气闸舱 热平衡试验 泄复压热试验 舱段级热试验 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]