攻角约束的敏捷机动自适应滑模控制方法  

Adaptive Sliding Mode Agile Maneuver Control Method with Attack Angle Constraints

作　　者：张旋[1] 陈升泽[1] 王子晗 ZHANG Xuan;CHEN Shengze;WANG Zihan(China Academy of Launch Vehicle Technology,Beijing,100076;Beijing Institute of Technology,Beijing,100081)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京理工大学,北京100081

出　　处：《导弹与航天运载技术(中英文)》2025年第1期78-84,共7页Missiles and Space Vehicles

摘　　要：针对航天器大攻角敏捷机动控制问题,基于直接力/气动力复合控制策略,提出攻角约束下航天器自适应滑模姿态控制方法。首先,建立纵向直接力/气动力复合控制模型和侧向喷流干扰模型,通过设计考虑攻角约束的预设性能非线性映射函数,将攻角约束的俯仰通道姿态控制问题转换为无约束的攻角误差调节控制问题;其次,设计攻角误差启发的非线性积分型滑模面,在反演控制框架下,提出侧向喷流干扰自适应估计的积分反演滑模控制方法,保证对侧向喷流干扰上界的在线估计,实现大攻角敏捷精准控制。最后,基于Lyapunov稳定性理论,证明了所设计的闭环控制系统的渐近稳定性。数值仿真表明:所提方法相比经典滑模控制方法,稳态时间缩短了79.16%,超调量减小了24.68%,舵偏能量消耗减小了34.54%。An adaptive sliding mode control method for spacecraft with attack angle constraints is proposed based on a direct force/aerodynamic composite control strategy for agile maneuvering control at high angles of attack.Firstly,a longitudinal direct force/aerodynamic composite control model and a lateral jet interference model are established respectively.By designing a prescribed performance nonlinear mapping function,the attitude control problem of the missile body pitch channel with attack angle constraints can be transformed into an unconstrained angle of attack error adjustment control problem.Secondly,an attack angle error-based nonlinear integral sliding mode surface is designed.Under the framework of Backstepping control,an integral Backstepping sliding mode control method for adaptive estimation of lateral jet interference is proposed,in which the upper bound of lateral jet interference can be estimated online to achieve agile and accurate control.Finally,based on Lyapunov stability theory,the asymptotic stability of the designed closed-loop control system is analyzed.Numerical simulation results demonstrate that compared to the classical sliding mode control method,the proposed method reduces steady-state time by 79.16%,overshoot by 24.68%,and energy consumption by 34.54%.

关 键 词：直接力/气动力 预设性能 自适应滑模 姿态控制 敏捷控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] V448