摘要
针对微小卫星热设计需求,基于球形双层集总参数模型,解析求解了双节点动态热平衡方程。提出使用多个类谐波近似处理周期性外热流边界的手段,消除外热流近似带来的计算误差。通过单次线性化处理,直接求解动态热平衡方程,得到高精度的动态温度解析解,使用四阶Runge-Kutta方法进行了数值验证。基于高精度解析解,设计了航天器导热-辐射双参数直接调控计算程序,对某小卫星模型进行热设计,对设计结果进行热仿真计算,验证了设计方案的可行性与准确性。
For the thermal design requirements of microsatellites,the two-node dynamic thermal equilibrium equations are solved analytically based on a spherical two-layer lumped parameter model.Multiple harmonic approximations are used to deal with periodic outer heat flux boundaries to eliminate computational errors due to heat flux approximations.With a single linearization,the dynamic thermal equilibrium equations are solved directly and the analytical solution of the dynamic temperature is obtained with high accuracy.Numerical verification is performed using the fourthorder Runge-Kutta method.Based on the high-precision analytical solution,a design procedure for direct control of the spacecraft thermal condition-radiation parameters Is compiled and applied to the thermal design of a specific small satellite model.Simulations are performed to verify the feasibility and accuracy of the design scheme.
作者
汪文卓
艾青
张笑昕
帅永
谢鸣
WANG Wenzhuo;AI Qing;ZHANG Xiaoxin;SHUAI Yong;XIE Ming(Harbin Institute of Technology,Harbin 150000,China)
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2023年第5期1395-1399,共5页
Journal of Engineering Thermophysics
基金
科技部“引力波探测”重点专项(No.2022YFC2204300)
国家自然科学基金国家重大科研仪器研制项目(No.52227813)。
关键词
航天器
热设计
温度预测
高精度
spacecraft
thermal design
temperature prediction
high precision
