| 引用本文: | 丰志伟,张永合,刘志超,等.基于路径规划的敏捷卫星姿态机动反馈控制方法.[J].国防科技大学学报,2013,35(4):1-6.[点击复制] |
| FENG Zhiwei,ZHANG Yonghe,LIU Zhichao,et al.Feedback control method for attitude maneuver of agile satellite based on trajectory optimization[J].Journal of National University of Defense Technology,2013,35(4):1-6[点击复制] |
|
| |
|
|
| 本文已被：浏览 7782次 下载 7014次 |
| 基于路径规划的敏捷卫星姿态机动反馈控制方法 |
| 丰志伟1, 张永合2, 刘志超1, 张青斌1, 唐乾刚1 |
|
(1.国防科技大学 航天科学与工程学院，湖南 长沙 410073;2.中国科学院 上海微系统与信息技术研究所，上海 200050)
|
| 摘要: |
| 为了避免奇异状态，单框架控制力矩陀螺（SGCMG）操纵律要求框架角进行快速转动，需要消耗较多的能量，并会对SGCMG和卫星系统带来一系列潜在危害。针对该问题，提出基于路径规划和反馈控制相结合的姿态机动控制方法。根据固定时间姿态机动的任务需求，以能量为优化指标，采用伪谱法优化机动路径并回避奇异状态；将最优控制量作为参考数输入，并利用基于系统限制状态的反馈控制方法消除不确定性和扰动的影响。反馈控制基于名义输入进行数值积分得到的预测状态量，并与期望终端状态比较形成控制误差信号。该方法将卫星和SGCMG作为整体规划姿态运动，能够有效避免奇异状态。结合工程实际，在闭环控制仿真中考虑了卫星角速度和SGCMG框架角的初始偏差。仿真结果表明：本文算法能够有限避免奇异状态，且能消除初始姿态角速度和框架角不确定的影响。 |
| 关键词: 姿态机动 控制力矩陀螺 伪谱法 混合方法 |
| DOI： |
| 投稿日期：2013-03-28 |
| 基金项目:国家自然科学基金资助项目（11272345） |
|
| Feedback control method for attitude maneuver of agile satellite based on trajectory optimization |
| FENG Zhiwei1, ZHANG Yonghe2, LIU Zhichao1, ZHANG Qingbin1, TANG Qiangang1 |
|
(1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;2.Shanghai Institute of Microsystem and Information, Chinese Academy of Science, Shanghai 200050, China)
|
| Abstract: |
| Rapid actuation is needed to avoid singularity state in the single-gimbal control moment gyros (SGCMG) steering logic. It consumes significant energy and produces danger for system. A novel control method for attitude maneuver combined trajectory and feedback control is proposed. Firstly, to avoid the singularity state, the pseudospectral method was used to solve the energy optimization issue. Then optimal solution of control acted as reference input, and feedback control method based on the system's limit state was used to consider the effect of uncertainty and disturbances. Feedback control predicted the state based on the numerical integration of reference input, and the error was based on the comparison of the designed state and the predicted state. Numerical simulation was carried out to verify the feasibility of the proposed method, which shows that it can avoid the singularity state, and is valid to overcome the error of the initial velocity of satellite and gimbal angular of SGCMGs. |
| Keywords: attitude maneuver control moment gyro pseudospectral method hybrid method |
|
|
|
|
|
