【摘要】 为了对载人航天器应急状况下密封舱进行压力控制,保障航天员的生命安全,采用集总参数法建立了密封舱压力控制物理数学模型,分析了长期飞行任务中载人航天器应急状况下的舱内压力变化;提出了一种舱压控制方案,计算了不同漏孔通径所需补气速率以及舱压复压变化规律。结果表明:密封舱内总压和氧分压的变化呈现指数递减,泄漏速率随着泄漏时间的增加而减小,漏孔通径越大,密封舱容积越小,泄漏速率变化梯度越大;随着漏孔通径的增大,恢复舱内压力所需要的补气速率呈线性趋势增加,复压模式维持7天飞行时间的供气量相比较维持舱压模式减少高达82.1%。更多还原

【Abstract】 To control the cabin pressure of manned spacecraft under emergency situation and thus to ensure the safety of astronauts, the physical mathematical model was established to analyze the pressure changes in the cabin under emergency conditions during long-term flights. A pressure control scheme was proposed to calculate the gas filling rate for different leaking sizes and the variation of cabin pressure was analyzed. The results showed that the changes of total pressure and oxygen partial pressure in the sealed cabin tended to decrease exponentially, and the leaking rate decreased with the leaking time. The larger the diameter of the leaking hole and the smaller the volume of the sealed chamber, the greater the gradient of the leaking rate. The analysis also showed that with the increase of the leaking hole diameter, the filling rate required to repressurize the cabin increased linearly. Re-pressurization mode can reduce the air supply as much as 82.1% as compared with the maintaining mode for 7-day flight time.更多还原