载人航天器密封舱泄漏时舱压控制分析
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摘要
针对载人航天器在密封舱体发生泄露时总压和氧分压的变化规律,建立了载人航天器舱压控制系统仿真模型,利用该模型分析了舱体容积、漏孔通径对总压和氧分压变化趋势的影响。结果表明,随着漏孔通径的增加或舱体容积的减小,总压和氧分压下降至指标下限所需的时间越来越短。随着漏孔通径的增加,舱体的初始漏气速率越高,但漏气速率下降得也越快。在分析的基础上提出了一种确定舱体应急补气速率取值范围的确定方法,综合考虑了舱体容积、漏孔通径、氧分压和总压下限要求、氧分压和总压维持时间需求,并通过两个算例验证了该方法的有效性。
To study the changes of the oxygen partial pressure and the total pressure in the pressurized cabin of manned spacecraft during cabin leaking,a simulation model of the air pressure control system was established. The effects of the pressurized cabin volume and the diameter of the leaking orifice on the changes of the oxygen partial pressure and the total pressure were analyzed with this model. The results showed that the time needed for the oxygen partial pressure and the total pressure to descend to the lower limit was shorter when the cabin volume was smaller or the diameter of the leaking orifice was bigger. The bigger the diameter of the leaking orifice,the higher the initial leaking flux,however,the descent of the rate of the leaking flux was also higher. A method to determine the emergency gas makeup flux range was proposed with comprehensive consideration of the cabin volume,the diameter of the leaking orifice,the lower limit of the total pressure and the oxygen partial pressure,and the time constraint to maintain the air pressure. The validity of the method was proved by two case studies.
To study the changes of the oxygen partial pressure and the total pressure in the pressurized cabin of manned spacecraft during cabin leaking,a simulation model of the air pressure control system was established. The effects of the pressurized cabin volume and the diameter of the leaking orifice on the changes of the oxygen partial pressure and the total pressure were analyzed with this model. The results showed that the time needed for the oxygen partial pressure and the total pressure to descend to the lower limit was shorter when the cabin volume was smaller or the diameter of the leaking orifice was bigger. The bigger the diameter of the leaking orifice,the higher the initial leaking flux,however,the descent of the rate of the leaking flux was also higher. A method to determine the emergency gas makeup flux range was proposed with comprehensive consideration of the cabin volume,the diameter of the leaking orifice,the lower limit of the total pressure and the oxygen partial pressure,and the time constraint to maintain the air pressure. The validity of the method was proved by two case studies.
引文
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[2]戚发轫..载人航天器技术[M].北京:国防工业出版社,1999:82-95.Qi Faren.Manned Spacecraft Technoloty[M].Beijing:National Defense Industry Press,1999:82-95.(in Chinese)
[3]范剑峰,黄祖蔚.载人飞船工程概论[M].北京:国防工业出版社,2000:52-70.Fan Jianfeng,Huang Zuwei.Introduction of Manned Spaceship Engineering[M].Beijing:National Defense Industry Press,2000:52-70.(in Chinese)
[4]Mitchell K L,Bagdigian R M,Carrasquillo R L,et al.Technical assessment of MIR-1 life support hardware for the international space station[R].NASA-TM-108441,NAS 1.15:108441,1994.
[5]Wieland P O.Living together in space:the design and operation of the life support systems on the International Space Station[R].NASA/TM1998-206956,1998.
[6]付仕明,裴一飞,郄殿福.国际空间站集成ECLSS/TCS试验综述[J].航天器环境工程,2010,27(4):447-451.Fu Shiming,Pei Yifei,Qie Dianfu.Review of integrated ECLSS/TCS tests for ISS[J].Spacecraft Environment Engineering,2010,27(4):447-451.(in Chinese)
[7]徐向华,任建勋,梁新刚,等.载人航天器密封舱内气体压力的动态分析[J].清华大学学报,2002,42(11):1492-1495.Xu Xianghua,Ren Jianxun,Liang Xingang,et al.Dynamic analysis of the cabin atmosphere in a manned spacecraft[J].Tsinghua Science and Technology,2002,42(11):1492-1495.(in Chinese)
[8]芮嘉白,郑传先,王普秀.载人航天器密封舱压控制规律解析解及其实验验证[J].航天医学与医学工程,2001,14(4):264-267.Rui Jiabai,Zheng Chuanxian,Wang Puxiu.Analysis solution and experimental verification of pressure control function of the sealed module of manned space vehicle[J].Space Medicine&Medical Engineering,2001,14(4):264-267.(in Chinese)
[9]Ramon P V,Sergio M,Olivier P,et al.Overview of European applications of Ecosim Pro to ECLSS,CELSS,and ATCS[R].SAE 031CES-405,2003.
[10]Almudena R,Raul A,Pedro C,et al.Modelling environmental control and life support systems(ECLSS)and loop heat pipes with Ecosim Pro[R].ICES_2010,2010.
[11]梁志伟,尹永利,朱艳芳.载人航天器压力应急情况下舱压变化的仿真研究[J].航天医学与医学工程,2000,13(2):128-131.Liang Zhiwei,Yin Yongli,Zheng Yanfang.A simulation study of cabin pressure changes under accidental leakage[J].Space Medicine&Medical Engineering,2000,13(2):128-131.(in Chinese)
[12]靳健,杨晨,侯永青.一种载人航天器气压控制系统仿真模型[J].航天器工程,2015,24(3):51-57.Jjn Jian,Yang Chen,Hou Yongqing.Simulation model for air pressure control system of manned spacecraft[J].Beijing:Spacecraft Engineering,2015,24(3):51-57.(in Chinese)
[13]Perez J A R,Persson J,Witt J,et al.Mode transition analyses of the attached pressurized module cabin air loop with Ecosim Pro[R].SAE 2000-01-2366,2000.
[14]王欲知,陈旭.真空技术[M].北京:北京航空航天大学出版社,2007:100-108.Wang Yuzhi,Chen Xu.Vacuum Technology[M].Beijing:Beihang University Press,2007:100-108.(in Chinese)
[15]EA International.Ecosimpro ECLSS library reference manual[M].Madrid:EA International,2008:316-319.
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