| 飞行器切换多胞系统抗干扰控制 |
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| 引用本文： | 王青,后德龙,陈彬,董朝阳. 飞行器切换多胞系统抗干扰控制[J]. 宇航学报, 2015, 36(2): 186-195. DOI: 10.3873/j.issn.1000-1328.2015.02.009 |
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| 作者姓名： | 王青 后德龙 陈彬 董朝阳 |
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| 作者单位： | 1. 北京航空航天大学飞行器控制一体化技术重点实验室，北京100191；2. 北京宇航系统工程研究所，北京100080；3. 北京航空航天大学航空科学与工程学院，北京100191 |
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| 基金项目： | 国家自然科学基金（61273083,61374012） |
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| 摘 要： | 针对存在参数不确定和外部扰动的飞行器切换多胞系统跟踪控制问题，提出了一种基于改进微分器的抗干扰控制方法。该方法将参数不确定和外部扰动带来的影响均视为干扰，提出一种改进微分器实现对干扰的精确光滑估计并设计控制器进行补偿，抑制干扰对系统的影响。与H∞等传统鲁棒方法相比，本文所提方法避免了对不确定满足凸包形式的假设，且在名义情况和不确定情况下均具有良好的性能。结合微分不等式理论和平均驻留时间方法证明了闭环系统的稳定性。为了验证本文所提方法的良好性能，将其应用到一类高超声速飞行器的轨迹跟踪控制问题中，仿真结果表明该方法能够有效抑制干扰，实现对参考信号的精确跟踪。
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| 关 键 词： | 不确定性 干扰抑制 切换多胞系统 鲁棒跟踪 高超声速飞行器 |
| 收稿时间： | 2013-12-18 |
Disturbance Attenuation Control for Flight Vehicle Switched Polytopic System |
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| WANG Qing,HOU De long,CHEN Bin,DONG Chao yang. Disturbance Attenuation Control for Flight Vehicle Switched Polytopic System[J]. Journal of Astronautics, 2015, 36(2): 186-195. DOI: 10.3873/j.issn.1000-1328.2015.02.009 |
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| Authors: | WANG Qing HOU De long CHEN Bin DONG Chao yang |
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| Affiliation: | 1. Science and Technology on Aircraft Control Laboratory，Beihang University，Beijing 100191，China；2. Beijing Astronautics Systems Engineering Institute，Beijing 100080，China;3. School of Aeronautic Science and Engineering，Beihang University，Beijing 100191，China |
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| Abstract: | Aiming at the flight vehicle switched polytopic system in the present of parameters uncertainties and external disturbances, a disturbance attenuation control scheme is proposed in this paper. Both parameter uncertainties and external disturbances are considered as equivalent disturbances to the system. A kind of improved differentiator is put forwarded to estimate the equivalent disturbances, and the disturbances are compensated in the controller. Compared with the traditional robust control method such as H∞, the method proposed in this paper avoids the convex hypothesis of system uncertainties, and the closed loop system represents good performance both in nominal and uncertain condition. The stability of the closed loop system is proved by the method combining differential inequality with average dwell time. The proposed method is applied to the trajectory tracking control of hypersonic flight vehicle, which validates the advantage of the proposed method. |
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| Keywords: | Uncertainty Disturbance attenuation Switched polytopic system Robust tracking Hypersonic flight vehicle |
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