一类非线性系统的输出反馈半局鲁棒镇定

从半局镇定角度研究了一类非线性系统的输出反馈镇定问题,这类系统具有较强的非线性增长特征.利用高增益观测器,把非分离设计原则应用于输出反馈半局镇定控制器设计.在不需系统具有一个一致完全可观状态反馈控制器情况下,给出了输出反馈控制器的设计方法.对任意给定紧子集,所设计的反馈控制器使闭环系统是渐近稳定的且吸引域包含指定的紧子集.最后的仿真实例说明了设计方法的有效性.     

Lur'e多非线性系统的镇定与L2-增益控制的MI方法

考虑Lur'e多非线性系统的镇定与L2-增益控制问题.对Lur'e多非线性系统表示 控制对象,设计状态反馈和输出反馈控制器使闭环系统分别是绝对稳定和L2增益有限的.基 于矩阵不等式(MI)方法给出了镇定与L2-增益控制问题的可解条件,并讨论了控制器的设计 方法.     

自抗扰控制对边界带有干扰的非线性sine-Gordon方程的镇定

本文讨论边界具有内部不确定和外部扰动的非线性sine-Gordon方程的镇定问题. 为处理sine-Gordon方程中的非线性项, 文章给出一个新的总扰动观测器在线估计未知扰动, 并通过自抗扰控制方法, 设计一个控制器使得在反馈控制中实时补偿(消除)总扰动. 闭环系统被证明适定的并且受控系统是指数稳定而扰动观测器是有界的. 数值模拟说明提出方法的有效性.     

有未知控制系数和零动态的高阶非线性系统的自适应控制设计

主要研究一类控制系数未知和有不可测零动态的高阶非线性系统的全局自适应镇定问题. 进一步放宽了对零动态的约束条件, 通过定义一个恰当的未知参数, 把连续自适应状态反馈控制器的动态阶数降到最低(仅一维). 通过结合增加幂次积分方法, 相关的自适应技术以及交换能量函数思想, 给出控制器的设计步骤. 所设计的控制器确保闭环系统的所有状态是全局一致有界的, 且原系统的状态收敛到零.     

具有参数不确定性的非线性系统的鲁棒输出跟踪

研究具有非线性参数化的非线性系统的输出跟踪问题.采用时变状态反馈控制律, 指数镇定输出跟踪误差,并保证非线性系统的所有状态是有界的.为了实现时变状态反馈控 制律,设计高增益鲁棒观测器观测构造该控制律所需要的状态,使得整个闭环系统的输出能 渐近跟踪期望输出,且该闭环系统中所有信号都是有界的.     

带动态边界的非均匀Timoshenko梁的反馈镇定

对于一端具负载的非均质Timoshenko梁, 研究了其边界反馈镇定问题. 首先提出了一种边界反馈控制方案, 建立了相应的闭环系统的适定性. 然后利用乘子法证明了, 当两个边界反馈控制同时作用于梁的负载端时, 闭环系统是指数稳定的.     

Euler-Bernoulli梁的反馈镇定

讨论端点带负荷的Bernoulli梁的横向振动的控制问题.分析了系统的谱结构,提出一 种非线性边界反馈来镇定梁的横向振动,并证明了相应的闭环系统的渐近稳定性,最后给出 了一些数值模拟结果.     

非线性时滞系统输出反馈镇定

该文首次研究了一类非线性时滞系统的镇定问题.用Backstepping技术,给出了输出 反馈控制器的构造性设计方法.     

具有自适应内模的一类非线性系统输出调节问题

研究一类包含未知非线性项的非线性系统的鲁棒输出调节问题.此类非线性系统由一包含未知参数的线性中性稳定的外系统驱动.首先运用调节器方程组解和标准内模将输出调节问题转化为镇定问题;然后给出控制律镇定闭环系统,同时利用镇定输入项和外系统信息设计出自适应内模方程.控制律使得闭环系统的信号全局最终有界,且误差被调节至预先设定的任意小的精度值.仿真结果验证了所提出设计方法的有效性.     

仿射非线性系统的动态输出反馈镇定

对能用状态反馈镇定且完全能观的仿射非线性系统,给出了保证闭环系统渐近稳定 的动态补偿器的设计方法.     

Euler－Bernoulli梁的反馈镇定

讨论端点带负荷的Ｂｅｒｎｏｕｌｌｉ梁的横向振动的控制问题．分析了系统的谱结构，提出一种非线性边界反馈来镇定梁的横向振动，并证明了相应的闭环系统的渐近稳定性，最后给出了一些数值模拟结果．     

Stabilisation of Timoshenko beam system with a tip payload under the unknown boundary external disturbances

This paper is concerned with the boundary stabilisation of a Timoshenko beam with a tip payload under the boundary external disturbances. Nonlinear feedback control laws are designed to reduce the effects of the external disturbances. Since the controlled system is nonlinear, the well posedness of the nonlinear closed-loop system is investigated using the theory of nonlinear maximal monotone operators and the variational principle. In addition, we show the exponential stability of the nonlinear controlled system using the Lyapunov direct method. In the end, the numerical simulations are displayed to illustrate the effectiveness of the proposed boundary controls.     

非线性相似组合大系统最优控制的逐次逼近过程

研究一类仿射非线性相似组合大系统关于二次型性能指标的最优控制问题．首先通过模型简化，将非线性相似组合大系统化为若干个准解耦的子系统；然后利用非线性系统最优控制的逐次逼近设计方法，将求解高阶强耦合的非线性两点边值问题简化为求解一族解耦的线性两点边值问题序列．该线性两点边值问题序列的解一致收敛于非线性相似组合大系统的最优控制，得到的最优控制律由线性最优控制的解析项与非线性补偿序列的极限项组成．通过截取最优控制非线性补偿序列的有限次逼近值．得到了非线性组合大系统的次优控制律．     

非线性时滞系统次优控制的逐次逼近法

对状态变量含有时滞的非线性系统的次优控制问题进行了研究，提出了一种次优控制的逐次逼近设计方法．针对由最优控制理论导出的既含有时滞项又含有超前项的非线性两点边值问题，构造了其解序列一致收敛于原问题最优解的非齐次线性两点边值问题序列．从而将两点边值问题解序列的有限次迭代结果作为系统的次优控制律．仿真结果表明了所提出方法的有效性．     

步进加热炉经济燃烧操作的研究开发和实现

本文给出了一种以线性规划搜索来求解加热炉操作中的非线性多约束优化问题及基于以上算法和辅以动态反馈所实现的加热炉递阶控制系统。本文所提出的优化算法具有计算量小、收敛速度快、且稳定可靠的优点,故易于在线实时运行.动态反馈又充分考虑了炉子复杂多变的加热环境.实时后的控制效果表明可提高出炉钢坯加热的均匀性而使生产工况趋于平稳,并有较大的节能和节约钢原材料的潜力.     

Robust adaptive boundary control of a perturbed hybrid Euler-Bernoulli beam with coupled rigid and flexible motion

In this paper, a robust adaptive boundary controller is proposed to stabilize the coupled rigid-flexible motion of an Euler-Bernoulli beam in presence of boundary and distributed perturbations. Applying Hamilton’s principle, the dynamics of the hybrid beam model, including the actuators hub and the payload at its ends, is represented through four nonhomogeneous nonlinear partial differential equations (PDEs) subject to ordinary differential equations (ODEs) of boundary conditions. Using a Lyapunov-based control synthesis procedure, a robust nonlinear boundary controller is established that asymptotically stabilizes the perturbed beam vibration while regulating the rigid motion coordinates. A redesign of the proposed control laws produces a robust adaptive boundary controller that achieves control objectives in the presence of both parametric and modelling uncertainties. Control design is directly based on system PDEs without truncating the model so that instabilities from spillover effects are mitigated. The control inputs to the beam consist of three forces/torque applied to the actuators hub and a transverse force applied to the tip payload. Simulation results are used to investigate the efficiency of the proposed approach.

     

受扰非线性离散系统的前馈反馈最优控制

利用逐次逼近法研究含外部扰动的非线性离散系统的线性二次型前馈反馈最优控制问题.首先将系统的最优控制问题转化为非线性两点边值问题族.其次,构造了该问题族的由精确线性项和非线性补偿项组成的解序列,并证明了解序列一致收敛到系统的最优解.最后,通过截取最优控制序列解中非线性补偿项的有限项,得到系统的前馈反馈次优控制(FFSOC)律及设计算法.仿真算例表明,该算法容易实现,且对抑制外部扰动的鲁棒性优于经典的反馈次优控制(FSOC).     

Regulation of a geometrically exact flexible beam manipulator

The rest-to-rest maneuver of a single-link flexible manipulator using the geometrically exact nonlinear beam model is considered. It is shown that, with the joint torque only, a simple linear feedback law derived based on a Lyapunov-type method stabilizes the highly nonlinear coupled system described by a set of integro-partial differential equations with coupled nonlinear boundary conditions.     

MIMO conditional integrator control for unmanned airlaunch

A nonlinear MIMO controller based on the conditional integrator technique is designed for the robust stabilization of a new satellite launching strategy called (unmanned) airlaunch. This control technique concerns an integrator performing similar to a sliding mode controller when the system is outside a boundary layer defined by the controller, and performing as a linear controler that provides the integral term when the system enters into the boundary layer. Satellite airlaunch strategy consists in using a two‐stage launching system. The first stage is composed of an airplane (manned or unmanned) that carries a rocket launcher, which constitute the subsequent stages. The control objective is to stabilize the aircraft in the launch phase. It is developed separately for the two nonlinear (one MIMO and one SISO) motion modes of the model, the longitudinal mode and lateral mode, and is then applied to the full model of the aircraft. The considered system is highly nonlinear, mostly as a consequence of a possible large angle of attack, sideslip, and roll angle. Finally, the present work illustrates through simulations, the good performance of the proposed control algorithm. Copyright © 2013 John Wiley & Sons, Ltd.