太阳翼联动可脱开装置设计与验证  

Design and Verification for Linkage Detachable Device of Solar Array

作　　者：贾文文 杨淑利[1] 任守志[1] 周志清[1] JIA Wenwen;YANG Shuli;REN Shouzhi;ZHOU Zhiqing(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2022年第4期46-53,共8页Spacecraft Engineering

摘　　要：针对大倾角轨道航天器双轴驱动太阳翼无法实现在轨联动脱开的问题,提出了一种联动可脱开装置的设计方法,并对应用该方法的太阳翼进行了仿真分析和试验验证。由此方法得到的联动可脱开装置,已在“鸿雁”星座首发星太阳翼上验证,经受了地面力学环境载荷及发射载荷,太阳翼多次地面展开数据正常,在轨展开过程中联动功能正常,联动顺利脱开,铰链均锁定,太阳翼摆动功能正常,在光照季(轨道角β=70°),S轴摆动角度为70°时,可调节太阳光与太阳翼法线夹角为0°~40°之间。Aiming at the problem that the dual-axis solar array of the spacecraft with high inclination orbit cannot realize the on-orbit linkage detachment,this paper proposes a design of the linkage detachable device,and carries out the simulation analysis and experimental verification of the solar array applying this method.The linkage detachable device obtained by this method had been verified on the solar array of the first satellite of Hongyan Constellation,and had withstood the ground mechanical environment load and the launch load.Ground deployment data of the solar array was normal during several tests.The linkage function was also normal during the orbital unfolding process.The linkage,hinges,and the solar array swing function were all normally performed on orbit.During the light season(orbit angle=70°),the angle between the sunlight and the normal line of the solar array can be adjusted to 0~40°by setting swing angle of the S-axis to 70°.

关 键 词：太阳翼 双轴驱动 联动可脱开装置 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]