高稳定一体化星敏支架机热协同设计及试验验证  

Collaborative Design of Mechanical and Thermal Properties and Test Verification of Highly Stable Integrated Bracket for Star Sensors

作　　者：张宗华[1] 徐文杰 顾志悦 周晓宁[1] 程尧 许斌 杜嘉旻 魏致坤[1] ZHANG Zonghua;XU Wenjie;GU Zhiyue;ZHOU Xiaoning;CHENG Yao;XU Bin;DU Jiamin;WEI Zhikun(Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]上海卫星工程研究所,上海201109

出　　处：《上海航天（中英文）》2023年第3期137-143,共7页Aerospace Shanghai（Chinese&English）

摘　　要：随着空间技术的发展,对卫星姿态测量精度的要求越来越高。星敏支架作为星敏感器与卫星之间的主要连接结构,其热稳定性直接影响星敏感器的测量精度与有效载荷的成像质量。因此,保证星敏支架的热稳定性成为卫星结构研究的重点。基于高体份铝基碳化硅新材料,利用其低膨胀、高导热性等特点,设计了一种适用于多头星敏感器安装的仪器支架,通过外加温控罩和精密温控等措施,对一体化星敏支架进行等温化控制,实现了星敏支架的热稳定性设计,并通过数值仿真和试验验证了设计方案的有效性。With the development of space technology,the demand for satellite attitude measurement accuracy is getting higher and higher.The bracket for star sensors is the main joint structure between the star sensors and the satellite body.Its thermal stability directly affects the measurement accuracy of the star sensors,which will decrease the image quality of the payload.Therefore,ensuring the thermal stability of the bracket for star sensors has become the emphasis for satellite structure research.In this paper,an innovative bracket is proposed for multiple heads of star sensors,which is made of SiCp/Al composites with low thermal expansion and high heat conductivity.An outside temperature protection cover and a precise temperature controller are applied on the bracket to achieve the isothermal distribution.Finally,the effectiveness of the design scheme is verified by numerical simulations and thermal tests.

关 键 词：星敏支架 机热协同设计 热稳定性 铝基碳化硅 试验验证 

分 类 号：V448.153[航空宇航科学与技术—飞行器设计] V416.5