载人飞船密封舱漏热问题研究

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α_S和ε_h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α_S和ε_h 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/(m^2·K)附近。

Research on Heat Leakage Problem of Manned Spacecraft Sealed Module

Heat leakage is a key factor in thermal control design of manned spacecrafts,as well as an important parameter affecting thermal balance and module temperature.A thermal physical model for solving heat leakage is established.In addition,influence of several parameters on sealed module heat leakage is analyzed.The results indicate that:(1) Heat leak was approximately linear related to air temperature in the module within certain temperature range;(2) Heat leak of reentry module is higher than orbital module mostly due to lower conduction resistance value;(3) Heat leak decreases with the increasing of external heat flux mading the fluctuation of heat leak in reentry module relatively large.Additionally,adjustment in αS and εh values of thermal control coating on the surface of the reentry module would induce opposite changes in heat leakage and its fluctuation.In order to reduce heat leakage and heat leakage fluctuation synchronously,thermal coatings with lower αS and εh values are recommended.(4) Heat leak age of reentry module is affected greatly by heat convection coefficient between air and the module wall,especially near the value of 2W/(m2·K).