基于改进快速终端滑模的高超声速飞行器姿态控制  

Attitude Control of Hypersonic Vehicle Based on Improved Fast Terminal Sliding Mode

作　　者：魏铭志 曾凡琳[1] 张秀云 WEI Mingzhi;ZENG Fanlin;ZHANG Xiuyun(School of Automation and Electrical Engineering,Tianjin University of Technology and Education,Tianjin 300222,China;School of Electrical and Information Engineering,Tianjin University,Tianjin 300072,China)

机构地区：[1]天津职业技术师范大学自动化与电气工程学院,天津300222 [2]天津大学电气自动化与信息工程学院,天津300072

出　　处：《佳木斯大学学报(自然科学版)》2024年第12期83-86,共4页Journal of Jiamusi University:Natural Science Edition

基　　金：国家自然科学基金项目(62373273)。

摘　　要：针对高超声速飞行器存在复合扰动的姿态控制问题,设计了一种改进快速终端滑模控制方法。建立弹性影响下的飞行器模型,定义姿态角误差向量,得到再入模型的误差动态方程;然后设计了三阶滑模观测器对复合扰动进行估计;又引入双曲正切函数改进终端滑模控制方法,并证明了所提策略的稳定性;最后,通过仿真实验,能够高精度快速地跟踪指令,验证了设计策略的有效性和优越性。Aiming at the attitude control problem of hypersonic vehicle with complex disturbance,an improved fast terminal sliding mode control method is designed.The vehicle model under the influence of elasticity is established,the attitude angle error vector is defined,the error dynamic equation of the reentry model is obtained.Then a third-order sliding mode observer is designed to estimate the complex disturbance.The hyperbolic tangent function is introduced to improve the terminal sliding mode control method,and the stability of the proposed strategy is proved.Finally,the system can quickly track instructions with high precision through simulation experiments,and the effectiveness and superiority of the strategy are verified.

关 键 词：高超声速飞行器 再入模型 快速终端滑模控制 三阶滑模观测器 姿态控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]