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低轨纳卫星质量矩姿态控制技术研究

胡远东 陆正亮 廖文和

胡远东, 陆正亮, 廖文和. 低轨纳卫星质量矩姿态控制技术研究[J]. 力学学报, 2020, 52(6): 1599-1609. doi: 10.6052/0459-1879-20-116
引用本文: 胡远东, 陆正亮, 廖文和. 低轨纳卫星质量矩姿态控制技术研究[J]. 力学学报, 2020, 52(6): 1599-1609. doi: 10.6052/0459-1879-20-116
Hu Yu, Lu Zhengliang. ATTITUDE CONTROL TECHNOLOGY FOR MASS MOMENT NANO-SATELLITE IN LOW EARTH ORBIT[J]. Chinese Journal of Theoretical and Applied Mechanics, 2020, 52(6): 1599-1609. doi: 10.6052/0459-1879-20-116
Citation: Hu Yu, Lu Zhengliang. ATTITUDE CONTROL TECHNOLOGY FOR MASS MOMENT NANO-SATELLITE IN LOW EARTH ORBIT[J]. Chinese Journal of Theoretical and Applied Mechanics, 2020, 52(6): 1599-1609. doi: 10.6052/0459-1879-20-116

低轨纳卫星质量矩姿态控制技术研究

doi: 10.6052/0459-1879-20-116
基金项目: 1) 国家自然科学基金(61803204);江苏省研究生科研与实践创新计划(KYCX20_0304)
详细信息
    作者简介:

    2) 陆正亮, 讲师, 主要研究方向: 微纳卫星姿态确定与控制系统. E-mail: 112010115@njust.edu.cn

    通讯作者:

    陆正亮

  • 中图分类号: V448.22+2

ATTITUDE CONTROL TECHNOLOGY FOR MASS MOMENT NANO-SATELLITE IN LOW EARTH ORBIT

  • 摘要: 针对气动力矩严重影响低轨纳卫星姿态控制效果的问题,创新性地提出了利用质量矩技术将气动干扰转化为控制力矩的解决方法.由于气动力矩矢量垂直于大气来流速度方向,因而采用质量矩与磁力矩相结合的方式三轴全驱动控制卫星姿态,从而避免系统欠驱动. 建立双执行机构控制方式的姿态动力学模型,并根据各干扰项的影响简化了控制方程.针对气动力不确定、星体参数误差、未知环境影响等复杂干扰,设计了针对理想控制力矩基于干扰观测器的滑模控制器. 为减小滑块附加干扰力矩,研究了理想控制力矩的最优分配策略. 最后, 为双执行机构搭建了半物理仿真平台,结果表明: 姿态机动过程中, 与滑块加速度相关的附加惯性力矩远大于其他干扰项,最优力矩分配策略能够大幅减小快时变的附加干扰, 优化效果明显; 姿态保持过程中,干扰观测器能有效观测系统慢时变干扰, 提高滑模控制律的姿态控制精度,姿态角收敛误差小于$\pm $0.1$^\circ$.最终验证了在低轨纳卫星上利用质量矩技术控制姿态的可行性.

     

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出版历程
  • 收稿日期:  2020-04-14
  • 刊出日期:  2020-12-10

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