舱外航天服空间热流分析计算  

Space heat flux calculation of extravehicular space suit

作　　者：邱义芬[1] 袁修干[1] 陈拥华[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2005年第9期985-988,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家863基金资助项目(2002AA743033)

摘　　要：进行了舱外航天服的被动热防护性设计,了解其空间辐射换热及空间热流.分析了舱外航天服空间热交换的特点及其真空屏蔽绝热层的隔热性能,确定了航天服、地球、飞船及太阳照射方向的4种典型相对位置关系,对各相对位置下航天服的空间辐射外热流进行了分析,并建立了空间热流的计算方法,对航天服表面最大得热与漏热进行了求解.最终计算结果表明:航天服被动热防护性能对空间热流的影响很大.进行被动热防护设计首先应提高隔热性能,并适当减小表面太阳辐射吸收率与表面黑度的比值.Space radiation heat transfer and heat flux through extravehicular spacesuit must be solved for the design of the spacesuit passive thermal protection. Characteristic of space heat exchange and performance of the vacuum shielding thermal insulation layer for the extravehicular spacesuit were analyzed, four typical position relations among spacesuit, earth, airship, and the solar direction were given, space external radiation heat flow of the spacesuit was analyzed under each of the four conditions, a method of calculating the space heat flux was established, then the maximum calculated heat gain and the maximum heat loss were solved. The final computation results indicate that the capability of the passive thermal protection for the spacesuit has immense influence on space heat flux. The spacesuit thermal insulation is most important to reduce the heat flux, and the ratio of the spaeesuit surface solar absorptivity to emissivity should be properly reduced for fear of larger leakage heat flow from the spacesuit.

关 键 词：热控制 空间热流 舱外航天服 真空屏蔽绝热 热流计算 

分 类 号：V445.3[航空宇航科学与技术—飞行器设计]