Adaptive dynamic surface control for air-breathing hypersonic vehicle

This paper describes an adaptive control approach for an air-breathing hypersonic vehicle.The control objective is to provide robust altitudes and velocity tracking in the presence of model uncertainties and varying disturbances.A fuzzy-neural disturbance observer is developed to estimate uncertainties and disturbances,and the adaptive controller is synthesized by the dynamic surface approach combing with the observer.The tracking error at the steady state can be guaranteed to converge to inside of a small residue set which the size of the set can be an arbitrary small value.Simulation results demonstrate the effectiveness of the presented approach.     

高超飞行器自适应动态规划的控制系统设计

针对高超声速飞行器的控制问题,提出一种基于自适应动态规划的非线性优化学习控制方法,设计了速度和高度自适应控制系统.首先,将控制器分解为稳态控制项和最优反馈控制项,同时借助反步法,将原高超声速动力学模型转化为兼顾速度跟踪误差和高度跟踪误差的统一的误差控制模型.其次,利用自适应动态规划法,通过自适应调节评价网络的权值,设计...     

Fault tolerant control for near space vehicle: a survey and some new results

A review on fault-tolerant control(FTC) for near space vehicle(NSV) is presented.First,the concept of near space is introduced,the background of NSV is emphasized,and the model characteristics of NSV in faulty case are investigated.Then,a comparison of different existing approaches is briefly carried out,and achievements on the current research in this field are also presented in the view of the practical application.Furthermore,several existing advanced FTC results for nonlinear flight control systems are given.Finally,the recent literature of NSV are presented to provide an overall view of future developments in this area.     

不确定时滞系统多目标约束下的满意容错控制

针对一类具有不确定参数、干扰输入和时滞特性的非线性系统,研究了当执行器发生故障时的满意容错控制问题。在更实际、更一般的执行器连续增益故障模型下,采用一种含有时滞记忆的状态反馈控制律,分析了鲁棒稳定性能与H∞指标的相容性,并在相容指标约束下,给出了鲁棒H∞满意容错控制器存在的充分条件和设计方法。仿真算例验证了该方法的有效性。     

高超声速飞行器自抗扰姿态控制器设计

针对高超声速飞行器无动力再入过程中具有强耦合、气动参数摄动及不确定性的非线性姿态模型,结合自抗扰控制中的扩张状态观测器(extended state observer, ESO)及非线性状态误差反馈律(nonlinear law state error feedback, NLSEF),分别设计了高超声速飞行器内环和外环自抗扰姿态控制器。将不确定性、耦合及参数摄动等干扰作为“总和干扰”利用扩张状态观测器进行估计并动态反馈补偿,再利用NLSEF抑制补偿残差。自抗扰控制器(active disturbance rejection control, ADRC)设计无需精确的飞行器被控模型,也无需精确的气动参数及摄动界限。仿真结果表明,控制系统能够克服干扰及气动参数大范围摄动的影响,在获取良好的动态品质和跟踪性能的同时,具有较强的鲁棒性。     

Progress in reentry trajectory planning for hypersonic vehicle

The reentry trajectory planning for hypersonic vehicles is critical and challenging in the presence of numerous nonlinear equations of motion and path constraints, as well as guaranteed satisfaction of accuracy in meeting all the specified boundary conditions. In the last ten years, many researchers have investigated various strategies to generate a feasible or optimal constrained reentry trajectory for hypersonic vehicles. This paper briefly reviews the new research efforts to promote the capability of reentry trajectory planning. The progress of the onboard reentry trajectory planning, reentry trajectory optimization, and landing footprint is summarized. The main challenges of reentry trajectory planning for hypersonic vehicles are analyzed, focusing on the rapid reentry trajectory optimization, complex geographic constraints, and coop- erative strategies.     

Reference tracking control for flexible air-breathing hypersonic vehicle with actuator delay and uncertainty

This paper considers the problem of reference tracking control for the flexible air-breathing hypersonic flight vehicle with actuator delay and uncertainty.By constructing the Lyapunov functional including the lower and upper bounds of the time-varying delay,the non-fragile controller is designed such that the resulting closed-loop system is asymptotically stable and satisfies a prescribed performance cost index.The simulation results are given to show the effectiveness of the proposed control method,which is validated by excellent output reference altitude and velocity tracking performance.     

Adaptive augmentation of gain-scheduled controller for aerospace vehicles

This paper proposes an adaptive augmentation control design approach of the gain-scheduled controller.This extension is motivated by the need for augmentation of the baseline gainscheduled controller.The proposed approach can be utilized to design flight control systems for advanced aerospace vehicles with a large parameter variation.The flight dynamics within the flight envelope is described by a switched nonlinear system,which is essentially a switched polytopic system with uncertainties.The flight control system consists of a baseline gain-scheduled controller and a model reference adaptive augmentation controller,while the latter can recover the nominal performance of the gainscheduled controlled system under large uncertainties.By the multiple Lyapunov functions method,it is proved that the switched nonlinear system is uniformly ultimately bounded.To validate the effectiveness of the proposed approach,this approach is applied to a generic hypersonic vehicle,and the simulation results show that the system output tracks the command signal well even when large uncertainties exist.     

含非线性输入的非线性系统自适应模糊控制

讨论一类含非线性输入的非线性系统的自适应模糊控制问题。首先运用隐函数存在定理证明系统的理想控制器的存在性,利用I型模糊逻辑系统对该理想控制器进行在线逼近,提出了一种具有监督器的自适应模糊滑模控制器设计的新方案。该方案通过直接自适应模糊控制器与监督控制器的适当切换,保证了闭环系统的稳定性,由此确定出建模的有界区域,而且通过引入最优逼近误差的自适应补偿项,保证跟踪误差收敛到零。仿真结果表明了该方法的有效性。     

弹性高超声速飞行器智能控制系统设计

针对气动舵受限下的弹性高超声速飞行器控制问题, 提出一种基于神经自适应的智能控制方案。在速度子系统的设计过程中, 为了降低对模型参数的依赖程度, 应用强化学习算法在线调整比例积分微分(proportional integral derivative, PID)控制参数, 给出智能PID控制策略。对于高度子系统, 考虑气动舵的动态特性, 利用神经自适应方法对模型未知函数及不确定项进行逼近。为了处理气动舵的约束问题, 以非线性模型预测控制为优化分配模板生成大量样本数据集, 经离线训练得到深度神经网络代替求解复杂优化问题和控制分配的过程。此外, 通过引入自适应超螺旋微分器处理外部扰动, 增强了系统的鲁棒性。利用Lyapunov方法证明了所设计控制器的稳定性, 并通过仿真验证了所设计控制方案能够快速计算控制指令, 实现高精度跟踪控制。     

Polytopic LPV modeling and gain-scheduled switching control for a flexible air-breathing hypersonic vehicle

A novel gain-scheduled switching control method for the longitudinal motion of a flexible air-breathing hypersonic vehicle (FAHV) is proposed.Firstly,velocity and altitude are selected as scheduling variables,a polytopic linear parameter varying(LPV) model is developed to represent the complex nonlinear longitudinal dynamics of the FAHV.Secondly,based on the obtained polytopic LPV model,the flight envelope is divided into four smaller subregions, and four gain-scheduled controllers are designed for these parameter subregions.Then,by the defined switching characteristic function,these gain-scheduled controllers are switched in order to guarantee the closed-loop FAHV system to be asymptotically stable and satisfy a given tracking error performance criterion.The condition of gain-scheduled switching controller synthesis is given in terms of linear matrix inequalities(LMIs) which can be easily solved by using standard software packages.Finally,simulation results show the effectiveness of the presented method.     

Flight control for a flexible air-breathing hypersonic vehicle based on quasi-continuous high-order sliding mode

The focus of this paper is on control design and simulation for the longitudinal model of a flexible air-breathing hypersonic vehicle(FAHV).The model of interest includes flexibility effects and intricate couplings between the engine dynamics and flight dynamics.To overcome the analytical intractability of this model,a nominal control-oriented model is constructed for the purpose of feedback control design in the first place.Secondly,the multi-input multi-output(MIMO) quasi-continuous high-order sliding mode(HOSM) controller is proposed to track step changes in velocity and altitude,which is based on full state feedback.The simulation results are presented to verify the effectiveness of the proposed control strategy.     

执行器饱和时的SISO系统模型参考自适应控制

针对大多数执行器不可避免地会出现饱和现象,尤其是工作范围大、非线性特性严重的被控制对象,提出了一种模型参考自适应设计方法,把输入过饱和部分看作干扰信号,并用可调参数和跟踪误差函数对饱和干扰进行估计,通过参数调节消除饱和现象,针对不同相对阶的系统分别进行讨论,使本方法更具普遍性。仿真结果表明,本方法能够使系统有较好的跟踪能力和抗饱和能力。     

高超声速飞行器新型攻角约束反演控制

针对考虑攻角约束的高超声速飞行器控制问题,提出一种受限指令滤波器与预设性能方法相结合的反演控制方案.首先,从高超声速飞行器运动模型中划分出高度子系统并基于反演控制方法设计控制器.为了解决攻角约束问题,构造受限指令滤波器对攻角虚拟指令限幅并保证指令的可导性.然后,利用预设性能方法预先设定约束范围,保证攻角跟踪误差始终满足...     

Intelligent vehicle lateral controller design based on genetic algorithmand T-S fuzzy-neural network

1.INTRODUCTION Effectivelateralcontrolisthepremiseofintelligent vehicle(IV)tracking.However,duetothenon lin earityandparameterstime variety,thelateralcon trollerdesignisadifficulttask.Manyworkshad beendoneforvehiclelateralcontrollerdesign.Ref.[1]usingstandardlinearquadraticcontrolapproach,Ref.[2]usingsliding modelapproach,Refs.[3～5]usingH infinityapproach,Ref.[6]usingnonlinear gain optimizedapproach,Refs.[7,8]usingfuzzy logicalapproach,studythelateralcontrolproblem,respectively.Refere…     

微型涵道飞行器的自适应逆控制方法

微型涵道飞行器可以悬停、垂直起降和前飞,且安全性高、结构紧凑、噪声低。但是,微型涵道飞行器由于大飞行包线、特殊气动布局、低速度、小尺寸和复杂飞行环境,所以具有明显的非定常和非线性飞行力学特性。针对这一问题,研究了应用动态逆控制律的新方法--神经网络自适应逆。采用动态逆控制器、神经网络补偿器、比例微分(proportion-derivative,PD)补偿器和伪控制补偿器构建了微型涵道飞行器飞行控制系统。仿真结果表明,相比动态逆 比例积分微分(proportion-integral-derivative,PID控制系统,本文设计的自适应逆控制系统具有更强的稳定性和鲁棒性。     

弹性高超声速飞行器动态面制导控制一体化设计方法

面向弹性高超声速飞行器滑翔段制导控制系统设计问题,应用动态面控制理论设计了两种制导控制一体化方法.建立了弹性高超声速飞行器滑翔段纵向运动模型,并推导了具有严格反馈形式的弹性高超声速飞行器制导控制一体化设计模型.将弹性状态视为不确定项,分别基于自适应方法和非线性干扰观测器(nonlinear disturbance ob...     

无人机鲁棒轨迹线性化控制航迹跟踪设计

研究一种鲁棒轨迹线性化控制方法并将其应用于无人机(unmanned aerial vehicle, UAV)航迹跟踪控制设计。通过理论分析指明传统轨迹线性化控制方法对系统中的不确定性存在鲁棒性不足的问题,采用改进隐层自适应神经网络对不确定性进行补偿,并利用Lyapunov理论证明了跟踪误差的有界性,最后将该方法应用到无人机三维航迹跟踪控制中。仿真结果表明,当参数摄动在20%时,该控制方法仍能使UAV很好地跟踪理想航迹,从而验证了该方法的有效性。     

Adaptive variable structure control for large-scale time-delayed systems with unknown nonlinear dead-zone

The problem of adaptive fuzzy control for a class of large-scale, time-delayed systems with unknown nonlinear dead-zone is discussed here. Based on the principle of variable structure control, a design scheme of adaptive, decentralized, variable structure control is proposed. The approach removes the conditions that the dead-zone slopes and boundaries are equal and symmetric, respectively. In addition, it does not require that the assumptions that all parameters of the nonlinear dead-zone model and the lumped uncertainty are known constants. The adaptive compensation terms of the approximation errors are adopted to minimize the inuence of modeling errors and parameter estimation errors. By theoretical analysis, the closed-loop control system is proved to be semi-globally uniformly ultimately bounded, with tracking errors converging to zero. Simulation results demonstrate the effectiveness of the approach.