计算机仿真2024,Vol.41Issue(11) :30-35,155.

基于AFNTSM的四旋翼飞行器姿态抗扰控制

Adaptive Fast Non-singular Terminal Sliding Mode Attitude Disturbance Rejection Control for a Quadrotor

李子修 潘健 易深华 柳仟雨
计算机仿真2024,Vol.41Issue(11) :30-35,155.

基于AFNTSM的四旋翼飞行器姿态抗扰控制

Adaptive Fast Non-singular Terminal Sliding Mode Attitude Disturbance Rejection Control for a Quadrotor

李子修 1潘健 1易深华 1柳仟雨1
扫码查看

作者信息

  • 1. 湖北工业大学电气与电子工程学院,湖北 武汉 430068
  • 折叠

摘要

模型不确定性、传感器测量噪声和环境风干扰等因素会影响四旋翼飞行器的控制性能.针对多源干扰影响下的四旋翼飞行器姿态控制问题,提出了一种基于线性扩张状态观测器(LESO)的自适应快速非奇异终端滑模控制(AFNTSMC)器.首先,引入LESO对未知扰动进行估计并应用于前馈补偿.然后,提出了一种能实时改变切换项增益的自适应算法,用可变增益切换项实时补偿LESO的干扰估计误差,减小了系统突加干扰情况下LESO估计误差较大对控制系统抗扰性能的影响,同时提高了控制器精度.此外,设计了一种快速非奇异终端滑模控制(FNTSMC)器,实现了有限时间控制.通过Lyapunov理论证明了系统稳定性.最后,仿真结果表明所提控制器提升了四旋翼飞行器的姿态跟踪和抗扰性能.

Abstract

Model uncertainty,sensor measurement noise and ambient wind disturbances can affect the control per-formance of quadrotors.For the problem of quadrotor attitude control under the influence of multi-source disturb-ances,an adaptive fast non-singular terminal sliding mode(AFNTSM)controller based on linear extended state ob-server(LESO)is proposed in this paper.First,LESO is introduced to estimate the unknown disturbances and applied to feedforward compensation.Then,an adaptive algorithm that can change the gain of the switching term in real time is proposed to compensate for the disturbance estimation error of LESO with variable gain switching term in real-time,which reduces the impact of large LESO estimation error on the disturbance rejection performance of the control system under the sudden addition of disturbance to the system and improves the controller accuracy at the same time.In addition,a fast non-singular terminal sliding mode(FNTSM)controller is designed to achieve finite-time control.The system stability is demonstrated by Lyapunov theory.Finally,simulation results show that the proposed controller improves the attitude tracking and disturbance rejection performance of the quadrotor.

关键词

四旋翼飞行器/姿态控制/滑模控制/扩张状态观测器/自适应控制

Key words

Quadrotor/Attitude control/Sliding mode control/Extended state observer/Adaptive control

引用本文复制引用

出版年

2024
计算机仿真
中国航天科工集团公司第十七研究所

计算机仿真

CSTPCD
影响因子:0.518
ISSN:1006-9348
段落导航相关论文