| 引用本文: | 陈晨,吴锦杰,王小雨,等.基于对偶四元数的航天器六自由度相对运动输入有界控制.[J].国防科技大学学报,2017,39(4):6-14.[点击复制] |
| CHEN Chen,WU Jinjie,WANG Xiaoyu,et al.Control for 6-DOF relative motion of spacecraft with input saturation constraint using dual quaternion[J].Journal of National University of Defense Technology,2017,39(4):6-14[点击复制] |
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| 基于对偶四元数的航天器六自由度相对运动输入有界控制 |
| 陈晨1, 吴锦杰2, 王小雨3, 李东旭4, 郑伟5 |
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(1. 吉林大学 仪器科学与电气工程学院， 吉林 长春 130061;2. 中国人民解放军78009部队， 四川 成都 610000;3. 中国电子科技集团第二十九研究所， 四川 成都 610036;4. 空军航空大学 飞行基础训练基地， 吉林 长春 130022;5. 中国人民解放军61251部队， 河北 秦皇岛 066000)
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| 摘要: |
| 利用对偶四元数的理论来分析航天器六自由度的相对运动，设计了一种考虑输入有界的姿轨一体化控制器。在介绍对偶数和对偶四元数的基础上推导六自由度相对运动的姿轨耦合模型；利用双曲正切函数绝对值小于1的特性来显式地构造有界控制器，分别设计两个相互耦合的自适应调节律来动态地改变控制器的输出，并基于李雅普诺夫稳定性理论严格证明了闭环系统的全局渐近稳定性；利用数学仿真实验来验证该控制器和控制力满足给定的约束条件，能够实现航天器六自由度相对运动的精确稳定控制，并且对模型参数不确定性和外界扰动具有鲁棒性。与其他方法相比，由该控制器计算得到的控制力矩器的收敛速度更快，输出的控制力矩和控制力的最大幅值更小，且消耗的能量也更少。 |
| 关键词: 输入有界 耦合的自适应调节律 李雅普诺夫稳定性理论 航天器六自由度相对运动 对偶四元数 |
| DOI：10.11887/j.cn.201704002 |
| 投稿日期：2016-03-05 |
| 基金项目:国家自然科学基金资助项目(61403160)；第55批中国博士后面上基金资助项目(2014M551194)；吉林省科技厅资助项目(20150414052GH，20140520118JH) |
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| Control for 6-DOF relative motion of spacecraft with input saturation constraint using dual quaternion |
| CHEN Chen1, WU Jinjie2, WANG Xiaoyu3, LI Dongxu4, ZHENG Wei5 |
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(1. College of Instrumentation & Electrical Engineering, Jilin University, Changchun 130061, China;2. The PLA Unit 78009, Chengdu 610000, China;3. Southwest China Research Institute of Electronic Equipment, Chengdu 610036, China;4. Basic Flight Training Base, Air Force Aviation University, Changchun 130022, China;5. The PLA Unit 61251, Qinhuangdao 066000, China)
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| Abstract: |
| The dual quaternion was used to investigate the 6-DOF (six degree-of-freedom) relative motion of spacecraft, and an integrated controller of attitude and orbit with input saturation constraint was designed. Firstly, the dual number and dual quaternion followed by the derivation of 6-DOF relative motion of attitude and orbit coupled model were introduced. Then, an explicitly bounded controller was proposed by using the property that the absolute value of hyperbolic tangent function was less than 1. Two coupled adaptive regulators were respectively designed to adjust the outputs of the controller dynamically. Thirdly, it is proved by a rigorous theoretical analysis that the closed loop system is globally and asymptotically stable. Finally, numerical simulation experiment is implemented to demonstrate the validity and effectiveness of the proposed controller. Experimental results show that both the obtained control torque and control force satisfy the given constraints, the 6-DOF relative motion of spacecraft can be controlled accurately and the method is robust to parameter uncertainties and external disturbance. Compared with other methods, the proposed method has the following advantages: the convergence rate is faster, the max magnitude of output control torque and control force are both smaller, and the consumed energy is less. |
| Keywords: input saturation constraint coupled adaptive regulators theory of Lyapunov stability six degree-of-freedom relative motion of spacecraft dual quaternion |
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