1. 北京理工大学 空天科学与技术学院
2. ,北京,100081
3. 中国兵器科学研究院
纸质出版:2025
移动端阅览
王伟, 刘佳琪, 林时尧, 朱泽军, 纪毅. 考虑预设性能约束的飞行器自适应神经网络姿态控制器[J]. 兵工学报, 2025, 46(S1): 250401-.
王伟, 刘佳琪, 林时尧, et al. Adaptive Neural Network-based Flight Vehicle Attitude Controller with Prescribed Performance Constraint[J]. Acta Armamentarii, 2025, 46(S1): 133-144.
王伟, 刘佳琪, 林时尧, 朱泽军, 纪毅. 考虑预设性能约束的飞行器自适应神经网络姿态控制器[J]. 兵工学报, 2025, 46(S1): 250401-. DOI: 10.12382/bgxb.2025.0401.
王伟, 刘佳琪, 林时尧, et al. Adaptive Neural Network-based Flight Vehicle Attitude Controller with Prescribed Performance Constraint[J]. Acta Armamentarii, 2025, 46(S1): 133-144. DOI: 10.12382/bgxb.2025.0401.
针对存在模型不确定性的高速飞行器刚体动力学,考虑执行机构故障情况下的姿态预设性能控制问题,提出了一种基于自适应故障失效估计策略和有限时间预设性能控制的姿态控制器。采用动态有限时间预设性能控制和时变障碍Lyapunov控制技术,保证了姿态跟踪误差的瞬态性能及稳态的有限时间收敛;同时,采用径向基函数自适应神经网络对模型不确定性进行估计。引入指令滤波器,避免了对复杂虚拟控制量的直接求导。通过设计自适应算法,对模型逼近误差、外部扰动以及滤波器估计误差的上界进行估计和补偿。针对执行机构的故障失效问题,设计了自适应复合容错控制策略,有效补偿了执行机构失效的影响。基于Lyapunov理论,验证了闭环系统的半全局一致有界性。通过数值仿真实验,验证了所设计姿态控制器的有效性。
In the presence of model uncertainties for the rigid body dynamics of high-speed vehicle ,and considering actuator faults,an attitude control strategy based on an adaptive fault estimation approach and an attitude controller for finite-time prescribed performance control are proposed by considering the attitude preset performance control under the condition of actuator failure.By employing the dynamic finite-time prescribed performance control and time-varying barrier Lyapunov control techniques,both the transient attitude tracking error performance and the finite-time convergence of steady-state errors are ensured.Moreover,a radial basis function neural network is used to estimate the model uncertainties.In addition,a command filter is introduced to avoid the direct differentiation of complex virtual control quantities.An adaptive algorithm is also designed to estimate and compensate for the upper bounds of model approximation errors,external disturbances,and command filter estimation errors.To address actuator faults,an adaptive composite fault-tolerant control strategy is proposed to effectively compensate for the impact of actuator fault.The semi-global uniform boundedness of the closed-loop system is verified based on Lyapunov theory.Finally,the effectiveness of the proposed attitude controller is verified through numerical simulation.
0
浏览量
30
下载量
0
CNKI被引量
关联资源
相关文章
相关作者
相关机构
京公网安备11010802024360号