| 基于自抗扰控制的空间飞行器姿态控制研究 |
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| 引用本文： | 王坤,蔡远利.基于自抗扰控制的空间飞行器姿态控制研究[J].黑龙江电子技术,2014(7):53-57,61. |
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| 作者姓名： | 王坤 蔡远利 |
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| 作者单位： | [1]西安工业大学电子信息工程学院,西安710032 [2]西安交通大学电子与信息工程学院,西安710049 |
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| 基金项目： | 西安工业大学校长基金资助项目（XAGDXJJ0617） |
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| 摘 要： | 空间飞行器姿态控制的主流方法是基于经典控制理论的，但它要求建立对象精确的数学模型。当对象模型不精确或是具有非线性、时变特性时，经典控制方法将很难满足实际的设计要求。在分析了空间飞行器姿态运动特性的基础上，引入自抗扰技术，设计了两种姿态控制系统，并将两者的结果进行对比，验证了自抗扰控制方法的有效性，同时指出了在实际应用中需注意的问题。
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| 关 键 词： | 空间飞行器 姿态控制 自抗扰控制 |
Research on spacecraft attitude control based on active disturbance rejection control |
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| Authors: | WANG Kun CAI Yuan-li |
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| Affiliation: | 1. School of Electronic and Information Engineering, Xi＇ an Technology University, Xi＇ an 710032, China; 2. School of Electronic and Information Engineering, Xi＇ an Jiaotong University, Xi＇ an 710049, China) |
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| Abstract: | The popular approach in the design of spacecraft attitude control system is the traditionalcontrol theory, which could get good results in the practical application. However, it needs exactmathematical model of the vehicles. If the system is imprecise, nonlinear and time-variable, thetraditional method will decrease the control precision. Based on the dynamic and kinematic equations ofspacecraft attitude system, two different controllers are constructed. One is the traditional controller, andthe other is the new type controller that is the so-called active disturbance rejection controller. Bycomparing the simulation results, the validity and the merits of the new method are well shown. |
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| Keywords: | spacecraft attitude control active disturban rejection control |
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