摘要
载人航天器的压力舱一旦被空间碎片击穿,可造成舱内气体的泄漏,进而导致航天员缺氧。文章对微流星体/空间碎片环境下压力舱的气体泄漏进行了分析。首先利用弹丸超高速正撞击下Whipple防护结构后墙的穿孔经验公式获得后墙的有效穿孔直径;然后将舱壁穿孔简化为音速喷管,通过对舱内气体的泄漏分析获得舱内压力的变化规律,进而得到供航天员逃逸的有效时间。分析结果可为载人航天器长期在轨工作的设计提供参考。
Meteoroid/Orbital Debris (M/OD) could penetrate the manned module and cause crew hypoxia because of the gas leak. The process of gas leak of pressure cabins is simulated and analyzed in this paper. The diameter of perforation on the wall of the module is obtained by using the empirical hole size model for Whipple shield under projectile normal hypervelocityimpact. The hole is then assumed to be a sonic nozzle to simulate the depressurizing leak process inside the module, and to obtain the escape duration of crew. The results can be used in the mission analysis of long-termed manned spacecraft.
出处
《航天器环境工程》
2008年第4期310-314,297,共5页
Spacecraft Environment Engineering
关键词
微流星体及空间碎片
超高速撞击
压力舱
气体泄漏
meteoroid/orbital debris
hypervelocity impact
manned module
depressurizing leak
