| 大跨域条件下的自适应滚转稳定容错控制方法 |
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| 引用本文： | 王雨辰,林德福,王伟,纪毅. 大跨域条件下的自适应滚转稳定容错控制方法[J]. 航空学报, 2021, 42(3): 324368-324368. DOI: 10.7527/S1000-6893.2020.24368 |
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| 作者姓名： | 王雨辰 林德福 王伟 纪毅 |
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| 作者单位： | 北京理工大学宇航学院,北京100081;无人机自主控制技术北京重点实验室,北京100081;北京理工大学宇航学院,北京100081;无人机自主控制技术北京重点实验室,北京100081;北京理工大学宇航学院,北京100081;无人机自主控制技术北京重点实验室,北京100081;北京理工大学宇航学院,北京100081;无人机自主控制技术北京重点实验室,北京100081 |
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| 基金项目： | 国家自然科学基金（U1613225） |
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| 摘 要： | 制导弹药在执行大跨域飞行任务时，其滚转扰动系数随速度、高度和攻角高频大幅值非线性变化，对制导弹药滚转通道稳定性造成了恶劣的影响。此外，时间滞后与控制失效等执行机构动力学特性进一步增加了滚转通道稳定性的控制难度。针对上述问题，设计了一种强鲁棒性的自适应滚转稳定容错控制方法。首先，在考虑执行机构失效动力学特性条件下建立了制导弹药滚转通道的数学模型，将系统不确定性和扰动项视为外部扰动，设计一种基于自适应滑模控制理论的强鲁棒滚转稳定控制方法，以补偿非线性变化项及执行机构失效。在此基础上，进一步考虑了执行机构动力学滞后特性，利用反步法设计了一种考虑执行机构动力学的控制方法，以补偿执行机构动力学滞后特性，提高弹体的响应速度。仿真结果表明所设计控制方法对气动扰动有较强鲁棒性以及在故障处理方面的优势。
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| 关 键 词： | 制导弹药 滚转通道 自适应滑模控制 执行机构失效 执行机构动力学滞后 backstepping技术 |
| 收稿时间： | 2020-06-04 |
| 修稿时间： | 2020-07-20 |
Adaptive fault-tolerance control method for roll stability during phase of large span flight |
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| WANG Yuchen,LIN Defu,WANG Wei,JI Yi. Adaptive fault-tolerance control method for roll stability during phase of large span flight[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(3): 324368-324368. DOI: 10.7527/S1000-6893.2020.24368 |
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| Authors: | WANG Yuchen LIN Defu WANG Wei JI Yi |
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| Affiliation: | 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2. Beijing key laboratory of UAV Autonomous Control, Beijing 100081, China |
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| Abstract: | During the phase of large span flight, aerodynamic parameters of guided-munitions have a large-amplitude high-frequency nonlinear chattering accompanied by varying velocity, altitude and angle of attack, adversely affecting the roll stability. Moreover, the failure and time-lag features of the actuator increase the difficulty in roll stability control. To address these problems, this paper proposes a robust adaptive fault-tolerant roll stability control method. A mathematical model of the roll channel considering the actuator fault is first established. Taking the nonlinear term and model uncertainties as external disturbances, a robust roll stability control method based on the adaptive sliding mode control theory is then presented to compensate the severe influence resulted from the nonlinear term and actuator fault. Additionally, the actuator time-lag is considered and the backstepping method implemented to suppress the actuator lag and increase the roll response speed. Simulation results show strong robustness of the proposed control method in aerodynamic disturbances and fault handling. |
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| Keywords: | guided-munition roll stability adaptive sliding mode control actuator faults actuator dynamic lag backstepping technique |
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