CAJ | 학술논문

对交会对接目标飞行器控制力矩陀螺的热特性进行了分析,建立了控制力矩陀螺的热分析模型,并结合其热平衡试验结果对热模型进行了修正,结果表明,模型计算温度与热平衡试验温度吻合较好。文章利用修正后的热数学模型,对控制力矩陀螺在轨运行时在不同热边界条件下的温度场分布进行了求解,并得出了陀螺辐射传热与导热传热的比例关系,以及辐射传热是其主要散热途径的结论。
대교회대접목표비행기공제력구타라적열특성진행료분석,건립료공제력구타라적열분석모형,병결합기열평형시험결과대열모형진행료수정,결과표명,모형계산온도여열평형시험온도문합교호。문장이용수정후적열수학모형,대공제력구타라재궤운행시재불동열변계조건하적온도장분포진행료구해,병득출료타라복사전열여도열전열적비례관계,이급복사전열시기주요산열도경적결론。
In this paper, the thermal characteristics of a CMG used in target spacecraft of rendezvous and docking are investigated. Thermal analysis model of CMG is built and then revised by using its ground thermal balance test data, which shows high agreement between computation temperature and test temperature of CMG. Based on the revised thermal mathematical model （TMM）, the temperature distribution of CMG is obtained under several orbital thermal boundary conditions, and the proportion of thermal radiation and thermal conduction in the whole heat transfer of CMG is obtained as well, which shows thermal radiation is the primary way of heat rejection.