摘要
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。
The physical and mathematical models are established for numerical simulation of temperature field by combining system with engine group and docking mechanism at the end of object spacecraft using node thermal network method.Calculational methods for key parameters are explained.The implicit R-K method is used to solve the nonlinear differential equations.The thermal effect of the engines at the high temperature in docking latch system is studied.The analysis shows that the thermal radiation of engines at high temperature influences greatly the docking latch system.Distance R,orbit transfer beginning moment and engine working time are important factors to influence the temperature of the docking latch system,and the installing obliquity of engine β has a little influence at the temperature.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2010年第4期461-465,共5页
Journal of Nanjing University of Aeronautics & Astronautics
基金
上海市科学技术委员会重点(08R21420300)资助项目
上海市空间飞行器机构重点实验室开放课题基金(06DZ22105)资助项目
关键词
温度场
数值模拟
对接锁系
对接机构
目标飞行器
变轨
temperature field
numerical simulation
docking latch system
docking mechanism
object spacecraft
orbit transfer
