摘要
当飞机发生非对称结构损伤时,飞机的质量、重心位置和气动特性都会发生突变,飞机机体的对称性遭到破坏,致使飞机的横纵向间运动产生强烈的耦合。针对飞机发生非对称结构损伤时导致的飞行控制问题,建立了非对称结构损伤飞机的损伤模型,并基于一种新型鲁棒容损控制策略,采用非线性扩张状态观测器和非线性动态逆相结合的方法,对飞机的姿态控制器进行了设计,兼顾了飞机系统的性能和对损伤的鲁棒性。最后,基于NASA的通用运输机模型,对所设计控制器的控制效果进行了仿真验证。仿真结果表明,设计的姿态控制器有效地抑制了非对称结构损伤给飞机控制系统带来的不确定性和扰动,具有较好的控制性能。
Asymmetric structural damage will cause unknown changes to the aircraft mass,center of gravity and aerodynamic characteristics,which will destroy the body longitudinal symmetry and bring strong coupling effects.Focusing on the flight control problem of the aircraft with asymmetric structure damage,this paper presents a robust fault-tolerant control strategy based on nonlinear extended state observer and nonlinear dynamic inverse,which well balances the system performance and the tolerance of damage.Firstly,the dynamic model of the aircraft with asymmetric structure damage was established.Then,an attitude controller was designed based on the proposed strategy.Finally,simulations were carried out to demonstrate the control effect with NASA Generic Transport Model.Results show that the flight performance is well ensured after asymmetric structure damage occurring.
出处
《导航定位与授时》
2017年第6期56-60,共5页
Navigation Positioning and Timing
基金
国家自然科学基金(61503009
61333011
61421063)
关键词
非对称结构损伤
鲁棒容损控制
非线性动态逆
非线性扩张状态观测器
Asymmetric structural damage
Robust fault-tolerant control
Nonlinear dynamic in-verse
Nonlinear extended state observer
