空间实验室尾部对接机构变轨期间热分析研究

Thermal Analysis of Docking Mechanism at the Tail of Space Laboratory During Orbit Changing

根据辐射传热基本原理和计算对象的几何物理特点，采用节点热网络方法，提出空间实验室尾部变轨发动机组和对接机构组合系统的热分析数学模型。利用龙格一库塔法，求得变轨飞行期间变轨发动机瞬态温度的变化历程和对接机构主体结构—对接框架周向、轴向温度的变化规律，着重分析对接机构组件表面辐射特性εd、液体发动机倾角β和间距R对对接机构温度分布的影响，指出两个高温发动机热辐射对尾部对接机构造成的热影响范围，大致在周向角θ=90°±30°和θ=270°±30°区域，最高温度位于对接框底部，其值介于30-90℃之间，温度随发射率的变化率△T／△εd≈96℃，表明发射率εd和发动机间距R是影响对接机构温度水平的重要因素。热分析工作是提出并改进对接机构热控设计方案的技术依据，具有十分重要的工程应用价值。

The mathematical model for thermal analysis of combined system with engines and docking mechanism at the tail of space laboratory by node thermal network method according to the principle of radiation heat transfer and geometry and physical features of calculation objects. Transient temperature field of maneuvering engine and circular, axial temperature variation of docking ring have been acquired by R-K method. Effects of radiant properties ea of docking mechanism and obliquity β, distance R and retrofire moment of engine on temperature distribution of docking mechanism. It is shown that from calculation results that the cir- cular ranges in which thermal effect works are θ=90°±30°and θ=270°±30°. Maximum temperature is at the bottom of docking ring which ranges from 30℃to 90℃. The ratio of temperature variation to surface emissivity variation equals approximately to 95℃, △T/△εd≈96℃.εd and R are important influence factors of docking mechanism temperature. Thermal analysis is technique reference to present and perfect thermal control design that has important engineering value.