摘要
针对特定小卫星对太阳翼高展开刚度的需求,设计了一种带单根辅助支撑臂的太阳翼。支撑臂中部采用带簧铰链实现弯折收拢,两端采用球关节铰链分别与太阳电池板、星体侧壁相连接。在太阳电池板与卫星侧壁连接处,采用自适应锁定式铰链,实现了带辅助支撑式太阳翼根部铰链的可靠锁定功能。开展了太阳翼基板承载能力分析、模态分析和展开动力学分析等。结果表明:太阳翼结构强度裕度满足使用要求,展开状态基频高达8 Hz以上,展开过程顺畅。模拟卫星发射过程及空间使用环境开展了太阳翼力学试验、展开试验、光照试验等,验证了太阳翼与飞行任务的匹配性。在轨飞行验证表明,该带辅助支撑式太阳翼功能、性能良好,满足高展开刚度的特殊任务需求。
Aiming at the special requirement of high stiffness in deployed configuration of solar wing for certain small satellites,a single-arm supported solar wing is designed.In the middle of the support arm,tape spring hinge is used to bend and straighten,and spherical joint hinges are used at both ends which connect with solar panel and sidewall of satellite respectively.Between the solar panel and satellite sidewall,a pair of selfadaptive locking root hinges are used to realize the reliable locking function of an auxiliary supported solar wing.The load bearing capacity of the substrate,modal analysis and deployment dynamics analysis of the solar wing are carried out.The results show that the strength margin of the solar wing meets the application requirements,the fundamental frequency of the deployed solar wing is up to 8 Hz,and the deployment process is smooth.The solar wing’s mechanical test,deployment test,lighting test,etc.which are designed to simulate the launching process and in orbit environment of the satellite are carried out,verifying the matching with the mission.In-orbit flight verification shows that the auxiliary-supported solar wing has good function and performance,and meets the special requirements of high stiffness.
作者
吴跃民
李大明
苏彬
解晓莉
WU Yuemin;LI Daming;SU Bin;XIE Xiaoli(Beijing Institute of Spacecraft System Engineering,Beijing,100094,China;Eighteenth Research Institute of China Electronics Technology Group Corporation,Tianjin,300384,China)
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2019年第S01期7-12,共6页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
太阳翼
辅助支撑
高刚度
电池电路
solar wing
auxiliary support arm
high-stiffness
solar cell circuit
作者简介
通信作者:吴跃民,男,高级工程师。E-mail:wiserobot@139.com。
