敏捷卫星高刚度太阳翼的设计与验证

基于对国内外敏捷卫星带辅助支撑式太阳翼现状及存在问题的分析，开展了太阳翼的构型设计与布局优化，设计一种基于带簧铰链与自适应锁定式铰链的单臂支撑式高刚度太阳翼。利用支撑臂中部带簧铰链在弯折后形态可变的特性，解决了多连杆闭环机构收拢状态下的杆长匹配问题；利用太阳翼根部自适应锁定式铰链可自动调节锁定状态的特性，解决了展开末了过约束锁定的技术难题，实现了带辅助支撑式太阳翼根部铰链的可靠锁定功能。开展太阳翼展开静力矩裕度分析、模态分析和展开动力学分析，结果表明，太阳翼展开力矩裕度大于1，展开状态下基频大于8 Hz，展开过程顺畅无死点，展开末了冲击力不超过750 N。开展了太阳翼地面试验验证和在轨飞行验证，结果表明，该高刚度太阳翼满足敏捷卫星在轨长时间快速机动的使用要求。

Design and Verification of High Stiffness Solar Wing on Agile Satellites

Based on the problem analysis about the current auxiliary support solar wings applied on the agile satellites, the configuration design and layout optimization of the solar wing on the agile satellites are conducted and a single-arm support high-stiffness solar wing is designed by using the spring hinges and adaptive locking hinges. The rod length matching problem existing in the folded configuration of the multi-linking closed-loop mechanism is solved with the deformable characteristic of the spring hinge located in middle of the support arm. Another technical problem about the over-constrained locking at the final step of deployment is solved with the adaptive characteristic of the locking hinges located at the root of this solar wing, thus realizing the reliable locking function of the root hinges in auxiliary support solar wings. The static torque margin, modal analysis and dynamics analysis of this deployable solar wing are respectively conducted. The analysis results show this solar wing has a static torque margin larger than 1, a fundamental frequency in deployed configuration larger than 8 Hz, a smooth deployment process without dead point and a locking impact force within 750 N. The ground test and the on-orbit flight verification of this solar wing are both carried out, which show this high-stiffness solar wing is capable of meeting the long-lasting and rapid-maneuvering application requirements for the agile satellites.