考虑冲击负载的非线性气弹性翼段的分数级快速终端滑动模式控制
Xing-Zhi Xu1,2
1Key Laboratory of Advanced Manufacturing and Automation Technology (Guilin University of Technology), Education Department of Guangxi Zhuang Autonomous Region, Guilin, China. xuxingzhi@glut.edu.cn.
Scientific reports
|July 2, 2025
概括
这项研究为非线性气弹性系统提供了一个新的控制框架,增强了飞减轻效果. 这种创新方法提高了对振动的抑制和系统在干扰和参数变化的适应性.
科学领域:
- 航空和航空航天工程
- 控制系统工程 控制系统工程
- 非线性动力学是一种非线性动力学.
背景情况:
- 浮动是飞机中关键的空气弹性不稳定性,构成重大安全风险.
- 现有的控制策略经常与非线性动态,参数不确定性和外部干扰作斗争.
- 需要先进的控制方法来确保复杂的气弹性系统的稳定性和性能.
研究的目的:
- 开发和验证一个创新的控制框架,以减轻非线性空气弹性系统中的动.
- 为了提高系统的稳定性,对抗参数变化和外部干扰.
- 与传统的控制方法相比,改进振动抑制和融合速度.
主要方法:
- 集成自动调节分数顺序快速终端滑动模式控制 (AFOFTSMC) 策略.
- 整合有限时间干扰观察器 (FTDO) 以提高稳定性.
- 使用模糊逻辑推理方案 (FLIS) 进行动态增强调整.
- 使用Lyapunov定理进行有限时间稳定性分析.
主要成果:
- 拟议的FTDO-AFOFTSMC方案展示了优越的抑制振动的能力.
- 控制框架表现出对参数不确定性和外部干扰的增强适应能力.
- 模拟结果证实了与整数顺序FTSMC相比的快速趋同和改进的控制性能.
- 该系统在不同的外部负载和参数条件下保持了强度.
结论:
- 开发的控制框架为非线性空气弹性系统中的飞减轻提供了高度有效的解决方案.
- 整合FTDO和FLIS显著提高了系统的稳定性和适应性.
- 这种方法代表了控制复杂的气弹性现象的重大进步.
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