纳卫星热系统的在轨动态特性分析与建模  

Analysis and Modeling for the in-Orbit Dynamics of Nano-Satellite's Thermal System

作　　者：李运泽[1] 宁献文[1] 王晓明[1] 石晓波[1] 庄达民[1] 王浚[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：《空间科学学报》2007年第3期233-238,共6页Chinese Journal of Space Science

基　　金：国家自然科学基金项目资助(50506003)

摘　　要：纳卫星热系统是在复杂空间热环境下实现纳卫星被动热控制任务的基本技术途径,对其进行在轨动态特性分析与建模对纳卫星的热控方法与效果研究及评价具有重要意义．通过详尽的机理分析建立了描述纳卫星热系统在轨飞行过程中瞬态温度变化的3维非线性动态特性模型,阐述了与之配套的外热流分析与轨道运动计算方法,并以一太阳同步轨道纳卫星为例,对其飞行过程中的外热流变化、在轨温度变化响应等动态特性进行了详细的分析和讨论,为进一步深入研究纳卫星热控制、热管理理论及技术提供了简便的分析计算模型与方法．Nano-satellite＇s thermal system is fundamental for its passive thermal control. The analysis and modeling of its in-orbit dynamical performance are necessary for nano-satellite＇s thermal control scheme design and evaluation. A three-dimension nonlinear dynamical model of satellite＇s temperature change was built up by dividing the typical passive thermal control system of nano- satellite into three representative functional node, the in-orbit temperature changes of satellite surface and indoor environment can be calculated conveniently from this model. A set of equations for the in-orbit calculations of nano-satellite＇s external space heat flow and flight position were also introduced. These equations are based on nano-satellite＇s body-reference frame and share same solving algorithm with the three-dimension nonlinear dynamical model. These provide a new transient analytical model and simplified in-orbit calculating method for the developing of advanced nano-satellite thermal control and thermal management technologies. The in-orbit dynamical performance of a sunsynchronous orbit nano-satellite thermal system had been calculated as an example. The results and its discussion were described at end of this article.

关 键 词：纳卫星 热系统 被动热控制 在轨动态特性 

分 类 号：V444[航空宇航科学与技术—飞行器设计]