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密封舱漏热是载人飞船热控系统设计中必须考虑的一个关键因素,是影响飞船热平衡和舱内温度的一项重要参数。建立了求解密封舱漏热的热物理模型,分析了各种参数对密封舱漏热的影响。结果表明:(1)在一定温度范围内,密封舱漏热与舱内空气温度近似呈线性关系;(2)返回舱漏热高于轨道舱,主要原因是导热热阻的基数偏小;(3)漏热随外热流增大而减小,返回舱漏热波动较大,调节其热控涂层的αS和εh值将导致返回舱漏热和漏热波动出现相反变化,为同时减小漏热和漏热波动,推荐采用较低αS和εh值的热控涂层;(4)返回舱漏热受舱内壁对流换热系数影响较大,特别在2W/(m2.K)附近。
Leakage of the ballast tank is one of the key factors that must be considered in the design of manned spacecraft thermal control system. It is an important parameter that affects the thermal balance and temperature of the spacecraft. A thermophysical model to solve the heat leak in the sealed chamber was established and the influence of various parameters on the heat leak in the sealed chamber was analyzed. The results show that: (1) Within a certain temperature range, the heat leak in the sealed chamber is approximately linear with the air temperature in the cabin; (2) the leakage heat of the return chamber is higher than that of the orbital chamber, mainly due to the small thermal conductivity base; 3) The heat loss decreases with the increase of external heat flux, and the leakage heat leakage in the return capsule is large. Adjusting the αS and εh values of the thermal control coating will result in the opposite change of leakage and leakage heat leakage in the return chamber, Leakage and leakage heat fluctuations, thermal control coatings with lower αS and εh values are recommended. (4) The leakage heat of the return chamber is greatly affected by the convective heat transfer coefficient of the inner wall of the tank, especially around 2W / (m2.K).