| 引用本文: | 范国伟,王绍举,徐 伟,常 琳,杨秀彬,王 旻.挠性卫星姿态机动三段式轨迹规划与滚动跟踪控制[J].控制理论与应用,2018,35(9):1260~1271.[点击复制] |
| FAN Guo-wei,WANG Shao-ju,XU Wei,CHANG Lin,YANG Xiu-bin,WANG Min.Three-segment trajectory plan and moving horizon tracking control of flexible satellite attitude maneuver[J].Control Theory and Technology,2018,35(9):1260~1271.[点击复制] |
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| 挠性卫星姿态机动三段式轨迹规划与滚动跟踪控制 |
| Three-segment trajectory plan and moving horizon tracking control of flexible satellite attitude maneuver |
| 摘要点击 2438 全文点击 1137 投稿时间：2017-03-15 修订日期：2018-03-07 |
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| DOI编号 10.7641/CTA.2018.70157 |
| 2018,35(9):1260-1271 |
| 中文关键词 挠性卫星 金字塔构型CMG群 快速机动 姿态路径规划 滚动跟踪控制 |
| 英文关键词 Flexible satellite Pyramid configuration CMGs Rapid maneuver Attitude path planning Moving horizon track control |
| 基金项目 国家自然青年科学基金(61503360，61705222)，吉林省优秀青年人才基金项目（20180520216JH） |
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| 中文摘要 |
| 以新颖成像模式对挠性敏捷卫星姿态的快速机动控制为需求,本文针对金字塔构型控制力矩陀螺(CMG)群为执行机构的挠性卫星,提出基于三段式正弦角加速度的姿态路径规划方法及具有滚动优化思想的跟踪算法。在姿态路径规划方法设计中,融合谱分析及非线性优化方法,设计了兼顾卫星姿态机动快速性及抑制挠性附件振动性能的姿态轨迹；为实现对规划姿态轨迹的高精度跟踪,综合加权优化指标及奇异性、执行机构能力等约束,设计了金字塔构型CMG群框架角速度的非线性模型预测(NMPC)跟踪控制律。在转动惯量存在测量误差及空间干扰情况下,多种姿态机动仿真表明,本文提出的控制方法是有效的,且表现出较强的鲁棒性。 |
| 英文摘要 |
| To satisfy the attitude rapid maneuver control requirements of various imaging modes, in this paper, the flexible satellite with the pyramid configuration control moment gyroscope (CMG) is considered, then the three-segment sine attitude path planning method of angular acceleration and tracking algorithm with rolling optimization are proposed. In the design of attitude path planning method, combining the spectrum analysis and nonlinear optimization, the attitude trajectory which considers the rapid performance of attitude maneuver and vibration suppression performance is designed. To track the planed attitude trajectory accurately, taken the weighted optimization function, singularities of CMG and capacity of actuator as the constraints, the tracking control law based on nonlinear model predictive control (NMPC) is presented for frame angular velocity of CMG group. In the present of inertia with error and space disturbances, a variety of attitude maneuver simulations are given. The results illustrate that, the proposed control method is effective and has the strong robustness. |
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