摘要
根据空间站尾部变轨发动机和被动式对接机构的结构特点,采用节点热网络法,建立空间站尾部组合系统(发动机组和对接机构)热分析的物理、数学模型,明确关键参数的计算方法,应用隐式R-K法,耦合求解非线性温度微分方程组;计算得到变轨期间组合系统的温度场,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。分析表明,发动机热影响范围大致在θ±Δθ=90°±30°和θ±Δθ=270°±30°区间;发动机相对安装距离和工作时间是影响对接机构温度的重要因素,而发动机安装倾角对对接机构温度的影响非常小。
Physical and mathematical models of thermal analysis on the combined system with engine group and docking mechanism at the end of space station have been set up by using node thermal network method, based on structural characteristics of transfer orbital engine at the end of space station and passive docking mechanism. An algorithm for key parameters calculation is defined. The implicit R-K method is used to solve the nonlinear differential equations. Temperature field of the combined system has been acquired during orbit transfer, focusing on the thermal effect of the engines at high temperature on docking latch system. It is shown that, the range of thermal effect of engines is about 0~A0=90~＋30~and 0~A0=270~~30~ ; Distance R and engine working time are important factors to influence the temperature of docking latch system, whereas, the installing obliquity of engine /3 has little influence on the temperature of docking latch system.
出处
《载人航天》
CSCD
2013年第1期21-26,共6页
Manned Spaceflight
关键词
温度场
数值模拟
对接机构
空间站
变轨
Temperature Field
Numerical Simulation
Docking Mechanism
Space Station
Orbit Transfer
