摘要
针对飞机大迎角机动存在的模型参数不确定问题,提出了一种考虑作动器动态补偿的增量滤波非线性控制方法.基于推力矢量飞机姿态控制模型,利用Taylor级数展开和状态导数反馈分别设计了增量形式的气流角和角速度控制器.针对低通滤波求取状态导数产生的延迟,通过对控制量进行滤波补偿保证了状态导数反馈和控制量反馈的时间同步性.在此基础上分析了作动器动态对角速度闭环控制性能的影响,通过补偿器设计使系统具有期望的作动器动态,克服了增量式控制方法对作动器高带宽的限制.仿真结果表明本文提出的增量滤波非线性控制方法具有强鲁棒性和快速动态响应能力.
To deal with the model uncertainties existed in high angle-of-attack maneuvers situation, a novel incremental filtered nonlinear control approach with considering the compensation for actuator dynamics is proposed. Based on the attitude dynamics of thrust vector aircraft, incremental controllers are designed to regulate incidence angles and angular rates via the Taylor expansion and state derivatives feedback. To handle the delay caused by the acquirement of state derivatives using low-pass filter, the same filter process is applied to compensate the inputs to guarantee synchronization of the feedback of state derivatives and control variables. In addition, the closed-loop analysis for angular rates is carried out to illustrate the effects of actuator dynamics. Moreover, a compensator is developed to achieve the desired actuator dynamics,which removes the requirements for high-bandwidth actuator inherent in incremental control. The strong robustness and fast dynamic response performance of the proposed control approach are verified by numerical simulations.
出处
《控制理论与应用》
EI
CAS
CSCD
北大核心
2017年第5期594-600,共7页
Control Theory & Applications
基金
国家自然科学基金项目(61573374
61503408)资助~~
关键词
大迎角机动
增量式控制
低通滤波
作动器动态
鲁棒性
high angle-of-attack maneuver
incremental control
low-pass filter
actuator dynamics
robustness
