基于切换系统建模的倾转旋翼机过渡模式光滑跟踪控制

罗苛比; 史爽; 彭聪

doi:10.1631/FITEE.2300266

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基于切换系统建模的倾转旋翼机过渡模式光滑跟踪控制

常规文章 | Updated：2023-07-17

- 基于切换系统建模的倾转旋翼机过渡模式光滑跟踪控制
- Smooth tracking control for conversionmode of a tilt-rotor aircraft with switching modeling
- 信息与电子工程前沿（英文） 2023年24卷第11期页码：1591-1600
- Affiliations：
  
  College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
- Author bio：
  
  ‡Corresponding author
- Funds：
  
  National Natural Science Foundation of China(62103186;62122038);Natural Science Foundation of Jiangsu Province, China(BK20210285;BK20211565);China Postdoctoral Science Foundation(2021TQ0151;2021M691571)
- DOI：10.1631/FITEE.2300266
  中图分类号： TP18; V279
- 收稿：2023-04-13，
  
  录用：2023-07-06，
  
  纸质出版：2023-11-0
- Accepted：
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罗苛比, 史爽, 彭聪. 基于切换系统建模的倾转旋翼机过渡模式光滑跟踪控制[J]. 信息与电子工程前沿（英文）, 2023,24(11):1591-1600.

Kebi LUO, Shuang SHI, Cong PENG. Smooth tracking control for conversionmode of a tilt-rotor aircraft with switching modeling[J]. Frontiers of Information Technology & Electronic Engineering, 2023, 24(11): 1591-1600.
罗苛比, 史爽, 彭聪. 基于切换系统建模的倾转旋翼机过渡模式光滑跟踪控制[J]. 信息与电子工程前沿（英文）, 2023,24(11):1591-1600. DOI： 10.1631/FITEE.2300266.

Kebi LUO, Shuang SHI, Cong PENG. Smooth tracking control for conversionmode of a tilt-rotor aircraft with switching modeling[J]. Frontiers of Information Technology & Electronic Engineering, 2023, 24(11): 1591-1600. DOI： 10.1631/FITEE.2300266.

摘要

本文使用切换建模和光滑插值技术，研究倾转旋翼机过渡模式的状态跟踪控制问题。基于过渡模式的非线性动力学模型，采用Jacobi线性化方法，并根据倾转角设计切换信号，建立线性切换系统模型。在此基础上，设计

∞

状态跟踪控制方案解决过渡模式的控制问题。该方法不直接限制控制输入的幅值，而采用改进的光滑插值方法实现无扰切换。最后，以XV-15倾转旋翼机为例，验证该控制方案的有效性。

Abstract

This paper investigates the state-tracking control problem in conversion mode of a tilt-rotor aircraft with a switching modeling method and a smooth interpolation technique. Based on the nonlinear model of the conversion mode

a switched linear model is developed by using the Jacobian linearization method and designing the switching signal based on the mast angle. Furthermore

state-tracking control scheme is designed to deal with the conversion mode control issue. Moreover

instead of limiting the amplitude of control inputs

a smooth interpolation method is developed to create bumpless performance. Finally

the XV-15 tilt-rotor aircraft is chosen as a prototype to illustrate the effectiveness of this developed control method.

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references

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