摘要
针对气动/推进/结构耦合的吸气式高超声速飞行器纵向平面飞行控制问题,提出了基于反演的鲁棒控制器设计方法。利用曲线拟合模型将控制系统表示为反馈形式,采用反演方法设计虚拟和实际控制器,并引入鲁棒微分器估计虚拟控制量的导数,解决了虚拟控制量求导运算复杂的问题。为增强控制器应对不确定项的鲁棒性,设计了超扭曲滑模干扰观测器,实现了对系统模型不确定项的估计和补偿。对吸气式高超声速飞行器一体化原理模型的速度和高度指令跟踪仿真表明,该控制器对拟合误差和外加干扰等系统不确定项具有鲁棒性,系统状态量能够在指令跟踪过程中趋于平衡状态,从而验证了所提方案的有效性。
A robust controller based on backstepping design procedure is proposed for an air- breathing hypersonic vehicle with aerodynamic, propulsion and structural couplings. Expressing the control system as strict feedback form via the curve-fitted model, virtual and actual controllers are constructed for the velocity and altitude subsystems. To omit analytic calculation of the virtual control law derivatives, which is very difficult to evaluate in the traditional backstepping control, robust differentiators are introduced. Super-twisting sliding mode disturbance observers are designed to compensate uncertainties in the system dynamics. Trajectory tracking simulation performed on the first principle model of the vehicle＇s longitudinal dynamics shows that the designed controllers are robust to model fitting errors and outside disturbances, and the system states reach trimmed condition asymptotically.
出处
《西安交通大学学报》
EI
CAS
CSCD
北大核心
2013年第3期102-107,共6页
Journal of Xi'an Jiaotong University
基金
航空科学基金资助项目(20120196006
20110196005)
关键词
吸气式高超声速飞行器
反演控制
鲁棒微分器
干扰观测器
air-breathing hypersonic vehicle
backstepping control
robust differentiator
disturbance observer
