摘要
微纳卫星低成本和方案快速迭代的特点,对其热控系统提出了简化、通用、快速设计等新要求。文章考察分析微纳卫星在热控系统设计方面所面临的困难和技术挑战,针对一般性椭圆地球轨道给出空间外热流随时间变化的计算方法;在此基础上,针对微纳卫星的结构和传热特点,提出整星热平衡方程对真近点角的连续积分方法和卫星温度场的多节点集总参数分析方法,并建立相应的数学模型,对微纳卫星算例进行计算分析和结果验证。结果表明,相对于传统商业软件网格划分建模的分析途径,该方法能对微纳卫星各主要部件的在轨温度变化进行快速建模和计算,可为微纳卫星热控系统的设计和优化提供便捷的初步评估手段。
The development of nanosatellites in recent years poses new challenges for the thermal control system with respect to the rapid iterative design and the low-cost manufacturing.This paper first assesses the technical requirements and the difficulties in the design of the nanosatellite thermal control systems.The calculation method for the external heat flux on the spacecraft on the common elliptical Earth orbits is proposed,as well as the method of the continuous integration of the spacecraft thermal balance equation and a simplified method for analyzing the lumped node-based temperature field,with consideration of the particular structural and heat transfer characteristics of the nanosatellites.A mathematical model based on these methods is built and implemented for a nanosatellite example,and the results are validated with the Thermal Desktop software.It is shown that compared with the tedious meshing and time-consuming calculation procedures in the conventional practice,our method can promptly model and determine the temperature in the main components on a nanosatellite.This paper provides an efficient evaluation tool for the early-stage design and the optimization of the thermal control system for nanosatellites.
作者
李志松
马昌健
毛云杰
郭涛
汪行
牟旭娜
LI Zhisong;MA Changjian;MAO Yunjie;GUO Tao;WANG Xing;MOU Xu’na(Shanghai Institute of Satellite Engineering,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)
出处
《航天器环境工程》
北大核心
2021年第2期122-129,共8页
Spacecraft Environment Engineering
基金
民用航天课题项目(编号:D020210)。
关键词
微纳卫星
热控系统
热平衡
温度场
数学建模
nanosatellites
thermal control system
thermal balance
temperature field
mathematical modeling
