基于多滑模控制器融合的高超声速飞行器再入段跟踪控制方法  

Multi-Sliding Mode Based Tracking Control for Hypersonic Aircraft During Reentry

作　　者：宋飞飞[1] 顾金媛[1] 李萌萌[1] 王晓冬[1] SONG Feifei;GU Jinyuan;LI Mengmeng;WANG Xiaodong(Kangda College of Nanjing Medical University,Lianyungang 222000,China)

机构地区：[1]南京医科大学康达学院,连云港222000

出　　处：《空间控制技术与应用》2023年第1期130-136,共7页Aerospace Control and Application

基　　金：南京医科大学康达学院科研重点项目(KD2020KYJJZD071);南京医科大学科技发展基金一般项目(NMUB2020040);江苏省第十六批“六大人才高峰”高层次人才选拔培养C类资助项目(XYDXX-245);江苏省教育厅高校哲学社会科学研究项目(2021SJA2492);教育部产学合作协同育人项目(202102311004)。

摘　　要：针对高超声速飞行器再入段滑模跟踪控制存在的抖振剧烈问题,提出一种基于多滑模控制器融合的跟踪控制方法.该方法采用动力学模型对高超声速飞行器再入过程进行描述,建立高超声速飞行器的攻角、侧滑角和倾斜角跟踪控制方程,结合准二阶连续滑模控制器和超螺旋滑模控制器对再入段进行分阶段的跟踪控制,分别削弱抖振影响,提高跟踪控制性能.通过模型仿真对所提跟踪控制方法的有效性和可行性进行验证,结果表明该控制方法可有效实现高超声速飞行器的轨迹跟踪,在控制力矩响应和姿态角速度跟踪误差积分值上较传统方法具备明显优势,可有效抑制抖振,提升飞行稳定性.In view of the problem of chattering when sliding mode approaches are implemented for tracking control of hypersonic aircraft during reentry, a tracking control method based on multi-slide mode controller fusion is proposed in this paper. The method first describes the hypersonic vehicle reentry process using a kinetic model, and establishes the angle of attack, side slip angle, and tilt angle tracking control equations. Then the quasi-second order continuous sliding mode controller and super-spiral sliding mode controller are combined to realize the tracking control in stages and respectively weaken the influence of shaking vibration, which helps to improve the tracking control performance during reentry. The paper verifies the effectiveness and feasibility of the proposed tracking control method through model simulation and shows that the control method can not only realize the track tracking of hypersonic aircraft, but also improve the performance of control torque response and attitude angle speed tracking error integration, which can effectively inhibit the chattering and improve the flight stability.

关 键 词：高超声速飞行器 轨迹跟踪控制 多滑模控制器融合 抖振 

分 类 号：V217.1[航空宇航科学与技术—航空宇航推进理论与工程]