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.     

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.     

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.     

Tracking control for air-breathing hypersonic cruise vehicle based on tangent linearization approach

This paper is focused on developing a tracking controller for a hypersonic cruise vehicle using tangent linearization approach. The design of flight control systems for air-breathing hypersonic vehicles is a highly challenging task due to the unique characteristics of the vehicle dynamics. Motivated by recent results on tangent linearization control, the tracking control problem for the hypersonic cruise vehicle is reduced to that of a feedback stabilizing controller design for a linear time-varying system which can be accomplished by a standard design method of frozen-time control. Through a proper model transformation, it can be proven that the tracking error of the designed closed-loop system decays exponentially. Simulation studies are conducted for trimmed cruise conditions of 110 000 ft and Mach 15 where the responses of the vehicle to step changes in altitude and velocity are evaluated. The effectiveness of the controller is demonstrated by simulation results.     

Multiobjective fault detection and isolation for flexible air-breathing hypersonic vehicle

An application of the multiobjective fault detection and isolation (FDI) approach to an air-breathing hypersonic vehicle (HSV) longitudinal dynamics subject to disturbances is presented. Maintaining sustainable and safe flight of HSV is a challenging task due to its strong coupling effects, variable operating conditions and possible failures of system components. A common type of system faults for aircraft including HSV is the loss of effectiveness of its actuators and sensors. To detect and isolate multiple actuator/sensor failures, a faulty linear parameter-varying (LPV) model of HSV is derived by converting actuator/system component faults into equivalent sensor faults. Then a bank of LPV FDI observers is designed to track individual fault with minimum error and suppress the effects of disturbances and other fault signals. The simulation results based on the nonlinear flexible HSV model and a nominal LPV controller demonstrate the effectiveness of the fault estimation technique for HSV.     

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。     

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...     

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...     

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。     

考虑输入饱和的直升机机动飞行LPV控制

针对直升机机动飞行过程中存在的输入饱和问题,提出了一种基于参数依赖Lyapunov的状态反馈控制方法。首先根据直升机非线性模型建立纵向线性变参数(linear parameter varying, LPV)模型,并采用逆仿真数值分析方法对悬停机动科目进行轨迹建模。基于吸引域与不变集理论,利用参数化线性矩阵不等式(parameterized linear matrix inequalities, PLMI),分析闭环系统的稳定条件。利用松弛变量技术将控制器PLMI条件转化为易于求解的线性矩阵不等式(linear matrix inequalities, LMI)条件,求解悬停机动轨迹跟踪控制律。仿真结果表明了所提模型和控制方法的可行性和有效性。     

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...     

基于LPV模型的水面机器人鲁棒航向控制

针对水面机器人水动力学的强非线性,且容易受到风、浪与水流干扰的影响,提出了一种基于LPV(Linear Parameter Varying)模型的H_∞鲁棒航向保持控制器。LPV模型采用Froude数作为线性变参,用来反映水面机器人水动力学随Froude数变化的非线性特性,同时简化模型参数辨识与控制器设计。将Froude数作为调度变量,采用介实引理设计了H_∞鲁棒航向保持控制器,用来抑制扰动对控制器的影响。在三自由度欠驱动水面机器人仿真平台上进行了验证,证明了控制器的有效性与鲁棒性。     

Adaptive fault-tolerant controller design for airbreathing hypersonic vehicle with input saturation

The problem of fault-tolerant control is discussed for the longitudinal model of an airbreathing hypersonic vehicle(AHV) with actuator faults and external disturbances.Firstly,a fault-tolerant control strategy is presented for the longitudinal model of an AHV,which guarantees that velocity and altitude track their reference trajectories at an exponential convergence rate.However,this method needs to know the minimum value of the actuator efficiency factor and the upper bound of the external disturbances,which makes it not easy to implement.Then an improved adaptive fault-tolerant control scheme is proposed,where two adaptive laws are employed to estimate the upper bound of the external disturbances and the minimum value of the actuator efficiency factor,respectively.Secondly,the problem of designing a control scheme with control constraints is further considered,and a new adaptive fault-tolerant control strategy with input saturation is designed to guarantee that velocity and altitude track their reference trajectories.Finally,simulation results are given to show the effectiveness of the proposed methods.     

飞行器不确定系统鲁棒D-稳定控制分配策略

为降低建模误差及外部扰动对飞行器多变量不确定系统的影响,提出了一种闭环系统鲁棒D-稳定的动态混合控制分配策略。飞控系统采用模块化的设计思想,利用线性矩阵不等式方法设计了基于虚拟控制指令的鲁棒D-稳定输出反馈控制律;建立了多目标混合优化控制分配模型,推导并证明了该模型的等价实现形式,用于将虚拟控制指令协调分配到各个操纵面。仿真结果表明,该策略能够综合考虑各操纵面不同的物理约束和控制效能,具有较好的鲁棒性能。     

Novel l2-l∞ controller design for LPV discrete time-delay systems

One of the first attempts to derive energy-to-peak performance criteria and state-feedback controller design problem for linear parameter-varying discrete time systems with time delay is provided. Firstly, we present a parameterdependent l2-l∞ performance criterion using a parameter-dependent Lyapunov function. Upon the conditions addressed,an improved parameter-dependent l2-l∞ performance criterion is established by the introduction of a slack variable,which exhibits a kind of decoupling between Lyapunov functions and system matrices. This kind of decoupling enables us to obtain more easily tractable conditions for analysis and synthesis problems. Then, the corresponding parameter-dependent state-feedback controller design is investigated upon these performance criteria, with sufficient conditions obtained for the existence of admissible controllers in terms of parameterized linear matrix inequalities. Finally, a numerical example is provided to illustrate the feasibility and advantage of the proposed controller design procedure.     

基于RCMAC干扰观测器的高超声速飞行控制

利用自回归小脑模型神经网络(recurrent cerebella model neural network, RCMAC)良好的非线性逼近能力和自学习能力,结合反馈线性化和反演控制方法,提出了一种自适应非线性控制策略,用于高速再入飞行器控制系统的设计。该方案将RCMAC干扰观测器(recurrent cerebella disturbance observer, RCDO)用于估计系统模型的不确定项,同时采用反演控制方式设计伪线性控制项,并利用符号函数逼近误差的上界,根据Lyapunov稳定性理论设计了权值更新规则,保证闭环系统信号有界。高速再入飞行器的六自由度仿真结果验证了方法的有效性和鲁棒性。     

不确定离散切换系统的状态反馈鲁棒控制

针对同时具有模型参数不确定性和外部扰动的一类离散切换系统,研究H∞其鲁棒控制和H2/H∞混合鲁棒控制问题。首先,基于多Lyapunov函数法分析了含有状态反馈控制器的离散切换系统的稳定性和H∞鲁棒控制问题。其次,基于线性矩阵不等式,通过建立和求解一个凸优化问题,给出不确定H2/H∞鲁棒控制的具有更小保守性的求解方法。最后,仿真算例验证了所提出方案的可行性。     

基于T-S模型的非线性系统非脆弱保性能模糊控制

针对一类用T-S模糊模型描述的非线性系统,采用状态反馈的并行分布补偿方法研究其非脆弱保性能模糊控制问题,使得在控制器存在可加性摄动的情况下,其闭环性能指标值低于确定的上界。利用线性矩阵不等式处理方法,导出了非脆弱保性能模糊控制律的存在条件。通过建立和求解一个凸优化问题,给出了最优非脆弱保性能模糊控制律的设计方法,并用此方法设计一级倒立摆的非脆弱模糊控制律。仿真结果表明了方法的有效性。     

严格耗散广义系统的鲁棒性分析与控制

考虑不确定广义系统的鲁棒耗散性分析与控制,其中各不确定参数矩阵具有线性分式形式。针对确定广义系统建立耗散性与正实性之间的等价关系,将不确定广义系统的鲁棒耗散性分析与控制转化为确定广义系统的耗散性分析与控制,利用线性矩阵不等式,给出了不确定广义系统鲁棒严格耗散的充要条件及状态反馈鲁棒严格耗散控制器的设计方法。通过一个数值算例说明所给设计方法的有效性。