空间站核心舱轨控机组热设计及飞行验证

Thermal design and flight verification of orbit control unit in core cabin of space station

为验证核心舱轨控机组热控设计能满足空间站任务期间任何工况对机组温度的要求,运用I-DEAS/TMG软件,通过仿真分析确定了轨控机组低温工况下所需的加热功率,预示了高温工况下的最高温度。在轨飞行情况表明:轨控机组飞行温度验证了理论计算的正确性,二者之间的偏差约3.7%;喷管受太阳照射面积越大,头部及电磁阀温度越高,在太阳角58°时,喷管受照面积最大;低温工况下,有推进剂流道的机组头部和电磁阀温度高于6.8℃,满足高于0℃的指标要求;不同于以往热控包覆状态的轨控机组,被动包覆设计保证了电磁阀在极端高温工况下,温度低于40℃,离高温上限有较大裕度,为电磁阀在空间站15 a任务期间的可靠工作提供保障。

In order to verify whether the thermal control design of the orbit control unit in the core cabin can meet the requirements of the temperature under any working condition during the mission of the space station, I-DEAS/TMG software was used to determine the heating power required by the orbit control unit under extreme low temperature conditions, and the maximum temperature under extreme high temperature conditions was predicted.The on-orbit flight shows that the flight temperature of the orbit control unit verifies the correctness of the theoretical calculation, and the deviation between them is about 3.7%.The larger the area of nozzles exposed to the sun, the higher the temperature of the heads and solenoid valves.When the solar angle is equal to 58°, the illuminated area of the nozzle is the largest.Under low temperature conditions, the temperature of unit head with propellant flow and solenoid valve is higher than 6.8 ℃,which meets the index requirement higher than 0 ℃.Inertial flight attitude belongs to high temperature condition for the pitching unit, which is different from the thermal control coating state of the previous unit, ensures that the temperature of the solenoid valves is lower than 40 ℃ under extreme high temperature conditions, which provides guarantee for the reliable operation of the solenoid valves during the 15 year mission of the space station.