变轨高温发动机热辐射对空间站尾部对接机构的热影响

Thermal Effect of Radiation of High-Temperature Engine on Docking Mechanism at Space Station Tail

根据空间站尾部变轨发动机和被动式对接机构的几何特点和航天器热控理论,提出一种组合系统的热分析物理、数学模型,着重研究高温变轨发动机热辐射对邻近对接机构的热影响.计算表明,2个高温变轨发动机热辐射对空间站尾部对接机构的热影响范围大致在周向角θ=(90°±30°)^(270°±30°),材料表面的发射率dε是影响对接机构组件温度的重要因素.在整个变轨期间,对接框的周向温差和最高温度已升到90°C,温度绝对增幅高达83°C,均大大超出对接机构温度的设计值,严重威胁机构部件的运动和固定功能,空间站尾部对接机构的热控措施将必不可缺.

The physical and mathematical models were presented for thermal analysis of the combined system according to the geometrical characteristics of engine group and docking mechanism at the space station tail and the thermal network theory of spacecraft. The thermal effect of engine radiation at high temperature on docking mechanism was put emphasis on. It is shown from the calculational results that the circular range in which thermal effect works is from θ= 90°±30± to 0=270°±30°. Emissivity is an important factor that will influence the temperature of docking mechanism. In the course of changing the orbit the circular temperature difference and maximum temperature of docking frame both reach 90℃, moreover, the absolute temperature amplitude comes to 83℃, which are all in excess of acceptable value and will threaten the movement and fixation functions. So the effective thermal control measures should be adopted.