| 迎角受限的高超声速飞行器固定时间鲁棒控制 |
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| 引用本文： | 董泽洪,李颖晖,吕茂隆,赵子龙,裴彬彬.迎角受限的高超声速飞行器固定时间鲁棒控制[J].宇航学报,2022,43(12):1708-1721. |
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| 作者姓名： | 董泽洪 李颖晖 吕茂隆 赵子龙 裴彬彬 |
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| 作者单位： | 1. 空军工程大学航空工程学院，西安 710038； 2. 空军工程大学研究生院，西安 710038 3. 空军工程大学空管领航学院，西安 710051； 4. 荷兰代尔夫特理工大学电气工程、数学和计算机科学学院，代尔夫特 999025 |
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| 基金项目： | 国家自然科学基金（62103440）；陕西省科协青年人才托举计划项目（20220101） |
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| 摘 要： | 针对高超声速飞行器动力学模型强耦合、非对称时变迎角限制、气动参数高度不确定以及跟踪误差收敛速率要求高等问题，设计了一种考虑非对称时变迎角限制的高超声速飞行器固定时间非奇异切换控制策略。为了解决非对称时变迎角限制问题，首先限制迎角虚拟控制器的幅值并设计固定时间误差补偿系统补偿迎角虚拟控制器饱和带来的不利影响，然后设计了一种新的光滑切换的非对称时变障碍函数限制迎角跟踪误差，从而使迎角满足非对称时变限制。光滑切换技术以及固定时间收敛技术也应用于其他虚拟控制律和实际控制律的设计中，以避免奇异值问题并且保证闭环系统的固定时间稳定。此外，设计了一种固定时间稳定的鲁棒补偿器用以补偿系统不确定性带来的不利影响。严格的数学推导证明了本文方法的正确性，仿真结果验证了本文方法的有效性和优越性。
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| 关 键 词： | 高超声速飞行器 迎角限制 非奇异切换 鲁棒控制 |
| 收稿时间： | 2022-05-05 |
Fixed time Robust Control for Hypersonic Flight Vehicle with Constrained Angle of Attack |
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| DONG Zehong,LI Yinghui,LV Maolong,ZHAO Zilong,PEI Binbin.Fixed time Robust Control for Hypersonic Flight Vehicle with Constrained Angle of Attack[J].Journal of Astronautics,2022,43(12):1708-1721. |
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| Authors: | DONG Zehong LI Yinghui LV Maolong ZHAO Zilong PEI Binbin |
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| Affiliation: | 1. Aviation Engineering School, Air Force Engineering University, Xi ’an 710038, China; 2. Graduate School, Air Force Engineering University, Xi ’an 710038, China; 3. Air Traffic Control and Navigation School, Air Force Engineering University, Xi ’an 710051, China; 4. Faculty of Electrical Engineering, Mathematics and Computer Science, Delft University of Technology, Delft 999025, The Netherlands |
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| Abstract: | Aiming at the problems of strong coupling of hypersonic flight vehicle (HFV) dynamics model, asymmetric time varying angle of attack (AOA) constraint, highly uncertain aerodynamic parameters, and high convergence rate requirement of the tracking error, a fixed time non singular switching control strategy for HFV considering asymmetric time varying AOA constraint is designed. In order to solve the issue of the asymmetric time varying AOA constraint, the virtual controller of AOA is limited in certain amplitude and the fixed time error compensation system is designed to compensate the adverse effects. A new smooth switching of asymmetric time varying barrier function is utilized to limit the AOA tracking error, so that AOA meets the asymmetric time varying constraint. Smooth switching technology and fixed time convergence technology are also applied to the design of other virtual laws and actual control laws to avoid singular value problem and ensure the fixed time stability of closed loop system. In addition, the fixed time stable robust compensator is designed to compensate the adverse effects of system uncertainty. Rigorous mathematical derivation proves the correctness of the proposed method, and the effectiveness and superiority of the proposed method are verified by the simulation results. |
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| Keywords: | Hypersonic flight vehicle Angle of attack constraint Nonsingular switching Robust control |
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