论文部分内容阅读
采用节点热网络法,建立了目标飞行器尾部组合系统(发动机组和对接机构)温度场数值模拟的物理、数学模型,明确了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。着重研究变轨期间对接锁系受高温变轨发动机的热影响。分析表明,发动机高温热辐射对邻近对接锁系的热影响很大,发动机热影响范围大致在θ±Δθ=(90±30)°和θ±Δ=θ(270±30)°区间,发动机相对安装距离R、变轨起始时刻和工作时间是影响对接锁系温度的重要因素,而发动机安装倾角对对接锁系温度的影响非常小。
By using the node thermal network method, the physical and mathematical models for the numerical simulation of the temperature field of the tail assembly system (engine block and docking mechanism) of the target aircraft are established. The calculation method of the key parameters is established. Implicit RK method is used to solve the nonlinear temperature differential equation set. Emphasis is placed on the thermal effects of the butt-lock system subjected to high-temperature orbit-changing engines during orbit change. The analysis shows that the thermal effects of engine high temperature heat radiation on the adjacent butt-lock system are very large, and the heat-affected range of the engine is approximately in the range of θ ± Δθ = (90 ± 30) ° and θ ± Δ = θ (270 ± 30) °. Installation distance R, change orbit start time and working time are important factors that influence the temperature of butt-lock system, and the influence of engine mounting angle on the temperature of butt-lock system is very small.