纳卫星散热面与隔热层的联合设计模型与算法  

Integrative design model and algorithm for nano-satellite's radiator surfaces and heat insulation layers

作　　者：李运泽[1] 宁献文[1] 王晓明[1] 庄达民[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2007年第4期414-417,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(50506003)

摘　　要：纳卫星的被动热控系统对卫星舱内的温度控制及其有效载荷的可靠工作具有重要意义.散热面与隔热层设计是被动热控设计的两大关键环节.在对其进行传热学分析的基础上,建立了纳卫星散热面面积及隔热层厚度的联合设计模型和求解算法,阐述了应用这一联合设计模型与算法的具体流程,并以一太阳同步轨道纳米卫星为例,在客观分析其轨道热环境特点的基础上,对其散热面面积和隔热层厚度进行了设计计算、结果分析和仿真验证,得出了各设计参数间的制约关系,设计结果的分析及仿真验证表明:采用散热面和隔热层的联合设计可以得到较好的被动热控效果,这一联合设计模型与算法为纳卫星的被动热控系统设计提供了简便的设计计算模型和求解算法.Passive thermal control system is very important for Nano-satellite＇s temperature control and its working safety. The calculations of radiator surface area and heat insulation layer thickness are necessary for the design of passive thermal control system. A set of integrative design equations and algorithms were developed and described for the calculation of radiator surface area and heat insulation layer thickness through the heat transfer analysis of nano-satellite＇s radiator surface and the multi layer heat insulation. The working flow of this integrative thermal design model and algorithm was also introduced. A sunsynchronous orbit Nano-satellites thermal design using this integrative model and algorithm was given as an example. The design example was analyzed and simulated. Result shows that the integrative design radiator surface and heat insulation layer can lead to a satisfactory thermal control effect, and a convenient design model and algorithm for nano-satellite＇s passive thermal control system design is provided.

关 键 词：纳卫星 被动热控系统 散热面 隔热层 设计模型与算法 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]