纳型卫星热控系统设计与仿真  

Design and Simulation for Thermal Control System of Nanosatellite

作　　者：丁延卫[1] 付俊明[2] 尤政[2] 

机构地区：[1]中国科学院光电研究院,北京100080 [2]清华大学精密仪器与机械学系,北京100084

出　　处：《系统仿真学报》2006年第1期169-172,共4页Journal of System Simulation

基　　金：中国博士后科学基金(2003034170)

摘　　要：现代微小卫星是当前航天技术发展的重要方向之一,热控分系统的功能是为星上仪器设备提供合适的温度环境。针对一颗纳型卫星,介绍其功能和构成。以获得最佳热耦合机制为目标,对纳型卫星本体及各分系统进行了全被动热控系统设计。通过I-DEASTMG软件,建立卫星热分析模型,对卫星的在轨稳态和瞬态温度状态上进行了仿真分析。仿真结果满足卫星总体要求,表明所提出的热设计思想和所采取的热设计措施可行。Modem microsateUite and small satellite is one of important aspects of space technology development nowadays, and its thermal control system is to provide appropriate temperature environment for instruments and equipments. The structure and function of a nanosatellite were introduced. Under the optimal thermal coupling mechanism, all-passive thermal design was carried out for nanosatellite system and subsystems. By I-DEAS TMG software, thermal model of the nanosatellite was founded, and the on-orbit steady and transient temperature distributions of nanosatellite were simulated. Temperature data met the need of the mission. Results show that the idea and measures of thermal design for nanosatellite are feasible.

关 键 词：纳型卫星 热设计 仿真:热耦合 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]