新型扩张状态观测器及其噪声抑制的特性分析（英文）

为了提升对快变干扰的估计性能,把输出估计误差的非线性项和切换项作为反馈设计一种新型非线性扩张状态观测器.在对干扰具有相同的估计性能下,新型非线性扩张状态观测器的增益相对较小,因而该新型非线性扩张状态观测器比传统扩张状态观测器拥有更好的噪声抑制性能。仿真结果表明新型扩张状态观测器对干扰的估计误差是传统方法的1/4。     

格网坐标系下自适应反馈增益阻尼方法

针对格网坐标系下传统阻尼网络参数选择的复杂性和固定性的问题,以及考虑到外速度阻尼时外界速度的有效性,提出了一种自适应反馈增益阻尼方法。首先,设计了一种新的反馈增益阻尼回路。再引入自适应滤波评估外速度信息,从而实时求解阻尼回路反馈增益,使反馈增益具有自适应性,实现阻尼系统周期震荡误差的同时抑制系统超调。最后仿真实验表明,所提出的自适应反馈增益阻尼方法加快了惯导系统误差的收敛速度,能够自主进行不同阻尼状态间的优化切换,而且比传统外速度水平阻尼误差超调量减小了15%,提高了舰船在极区航行时的导航性能。     

基于状态观测器的扰动补偿在转台控制中的应用

为了减小干扰力矩对转台性能的影响,提出了基于观测器的扰动补偿控制来抑制干扰力矩的方法.首先采用传递函数的方法分析了状态观测器中各观测状态与观测器输入之间的关系,利用观测器获得角加速度信号构造扰动补偿器对外部扰动进行补偿控制,设计了具有扰动补偿的转台控制系统,并分析了加入扰动补偿后对控制系统的影响.分析和试验结果表明,此基于状态观测器的扰动补偿可以对低频的扰动进行有效的抑制,能够显著的提高转台低频小信号振动时的失真度和三轴联动精度,同时对瞬态扰动也有一定的抑制作用.     

基于新息自适应卡尔曼滤波算法的多类型结构响应重构

为改善传统卡尔曼滤波KF(Kalman filter)算法在过程噪声方差和测量噪声方差未知的情况下响应重构精度降低甚至发散的问题，提出了一种基于新息自适应卡尔曼滤波IAKF(innovation-based adaptive Kalman filter)算法的多类型响应重构方法。首先根据新息统计特性对卡尔曼滤波增益和状态估计误差协方差矩阵进行实时自适应调整；然后利用有限测点的加速度传感器的测量数据，结合模态法对结构各个位置的加速度、速度、位移以及应变进行响应重构；最后对起重机桁架和简支梁分别进行数值模拟和试验分析。结果表明，该方法能够有效地调整过程噪声方差并估计测量噪声方差，未测点的重构响应时程曲线与计算响应或测量响应时程曲线吻合良好。     

基于观测器的离散广义分段仿射系统H_∞控制

针对一类当前所处作用域未知的离散时间广义分段仿射系统,考虑其具有范数有界形式的时变参数不确定性,而且不能从测量输出获得的问题,研究此类系统基于观测器H_∞控制器的设计方法。闭环系统反馈控制器设计从离散广义分段仿射Lyapunov判据出发,应用相关基本引理将控制器存在条件转化为包含参变量的线性矩阵不等式形式,并采用投影定理进一步降低系统保守性,使得基于观测器的闭环系统满足一定的鲁棒H_∞性能指标。通过求解一组包含参变量的线性矩阵不等式组,得到保证此闭环系统具有鲁棒H_∞性能指标的反馈控制器增益和基于输出的观测器增益,并完成了基于Matlab 7.0线性矩阵不等式工具箱的数值仿真。仿真结果表明基于定理1所提控制器设计方法得到的闭环系统干扰抑制度γ=21.4254,且在系统矩阵取值不同的情况下,定理1较传统控制器设计方法具有更好的保守性。     

大型液体火箭姿控与跷振大回路耦合动力学建模与分析

大型液体火箭结构模态的空间化分布特征导致结构振动、姿态运动和推进系统液路脉动存在相互耦合,进而影响传统姿控回路的稳定性. 针对大型液体火箭, 充分考虑姿态控制系统对箭体姿态动力学和弹性振动的影响, 以及箭体结构弹性振动与推进系统的耦合作用(跷振(POGO)), 建立了姿控与跷振大回路耦合模型. 该模型包含了推进系统、结构系统与姿控系统之间的耦合因素, 可进行姿控-结构-推进大回路耦合机理研究. 该模型具有非奇异的优点, 可以直接用于频域分析和时域仿真. 基于该模型研究了我国某型号液体捆绑火箭推进系统参数——泵增益和蓄压器能量值对姿态运动与结构振动稳定性的影响. 研究得出, 泵增益和蓄压器能量值的变化不仅导致了结构振动的不稳定, 而且也导致了姿态运动的发散. 因此, 对于大型液体捆绑火箭, 推进系统与姿控系统之间存在不可忽略的耦合作用, 在设计姿控系统时, 有必要考虑推进系统对姿控系统稳定性的影响.      

基于线性矩阵不等式的离散系统集成故障估计与容错控制

离散系统在进行故障估计与容错控制时,由于两者相互耦合,会产生较大的故障估计误差和系统输出误差。针对这一问题,提出了一种基于线性矩阵不等式的集成故障估计与容错控制方法。首先为系统设计了故障观测器和容错控制器,然后基于两者的耦合关系,建立了系统误差和状态的增广系统模型;其次,基于D-稳定引理和H_∞控制理论为增广系统设计控制器,进而利用线性矩阵不等式求得故障观测器和容错控制器的增益矩阵,实现多性能约束条件下的集成故障估计与容错控制。最后以飞行控制系统验证了所提方法的有效性,与传统分离设计方法相比,故障估计误差减小了66.7%,估计的快速性提升了70%。     

地震作用下结构的AMTMD主动控制策略

提出了一种新的控制策略——主动多重调谐质量阻尼器(AMTMD)．AMTMD控制系统频率呈线性分布．AMTMD保持相同的刚度和阻尼但质量变化．AMTMD的主动控制力采用Roorda(1975)提出的生成模式．基于结构的广义振型模型，导出了设置AMTMD时结构的动力放大系数(DMF)．于是AMTMD优化准则选择为结构最大动力放大系数的最小值的最小化．分别使用位移、速度和加速度传感器，通过最优搜寻，研究了反映AMTMD有效性和鲁棒性的参数．这些参数包括：频率间隔、平均阻尼比、调谐频率比、Min．Min．Max．DMF、标准化反馈增益系数和环增益系数．为比较，同时考虑了多重调谐质量阻尼器和主动调谐质量阻尼器．而且，数值结果表明：AMTMD比MTMD具有更高的有效性和鲁棒性且ATMD也有更高的有效性．     

MR阻尼器的状态跳跃控制参数

对MR阻尼器实施状态跳跃控制可以有效地减少结构的地震响应，状态跳跃控制参数对半主动控制效果有很大的影响。本文对状态跳跃控制的相关参数进行了研究。利用两个数值算例，对采用不同类型的控制参数(位移、速度、加速度)、控制参数的大小、输入地震动的大小等相关因素对结构地震响应的控制效果进行了对比，发现采用速度响应作为状态跳跃控制变量对于减少绝对加速度响应是有利的；建议采用试算法确定合适的速度控制参数，通过和LQG控制相联系的方法给出了该控制参数最优值的估算方法。     

结构主动开闭环多重调谐质量阻尼器（AMTMD）新控制策略

提出了一种新控制策略——主动开闭环多重调谐质量阻尼器(AMTMD)。AMTMD控制系统频率呈线性分布。AMTMD中的MTMD保持相同的刚度和阻尼系数但质量变化。基于TMD的工作原理定义了AMTMD的主动控制力构成即保持相同的位移和速度反馈增益系数但变化结构和地震加速度反馈增益系数。基于结构的广义振型模型，导出了设置AMTMD时结构的动力放大系数(DMF)，于是优化准则可定义为：Min．Min．Max．DMF．通过最优搜寻，研究了反映AMTMD有效性和鲁棒性的参数。这些参数包括：频率间隔、平均阻尼比、调谐频率比、总数、质量比和标准化加速度反馈增益系数。为了比较，多重调谐质量阻尼器(MTMD)和主动开闭环调谐质量阻尼器(ATMD)也被考虑。     

Exceedance probability criterion based stochastic optimal polynomial control of Duffing oscillators

An optimal polynomial control strategy is developed in the context of the physical stochastic optimal control scheme of structures that is well-adapted to randomly-driven non-linear dynamical systems. A class of Duffing oscillators with polynomial active tendons subjected to random ground motions is investigated for illustrative purposes. Numerical studies reveal that using an exceedance probability criterion with the minimum of the failure probability of system quantities in energy trade-off sense, a linear control with the 1st-order controller suffices even for strongly non-linear systems. This bypasses the need to utilize non-linear controls with the higher-order controller which may be associated with dynamical instabilities due to time delay and computational dynamics. The statistical variability, meanwhile, of system responses gains an obvious reduction, and the system performance is significantly improved. The 1st-order controller, however, does not have the same control effect to the higher-order controller when control criteria currently in used are employed, e.g. system second-order statistics evaluation and Lyapunov asymptotic stability condition, as indicated in the comparative studies of the exceedance probability criterion against the two control criteria. Besides, the proposed optimal polynomial control is insensitive to the non-linearity strength of the class of base-excited non-linear oscillators whereby a robust control of systems can be implemented, while the LQG control in conjunction with the statistical linearization technique, using a band-limited white noise input, does not have this advantage.     

Precise integration method for LQG optimal measurement feedback control problem

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基于LQG最优控制法的压电智能结构独立模态空间控制

采用压电材料作为传感器和驱动器对智能结构振动主动控制进行研究,基于机电耦合的压电智能结构传感和驱动方程,将振动控制动力学方程变换到模态空间对方程进行解耦。通过计算结构最大应变,确定压电元件的最佳粘贴位置。考虑到系统过程噪声和量测噪声的影响,设计Kalman滤波器,采用基于线性二次型高斯(LQG)最优控制的独立模态空间控制方法对压电智能结构的振动进行控制。最后以压电智能悬臂梁为例进行控制仿真,验证了此方法的有效性。     

Adaptive fuzzy output-feedback control of uncertain SISO nonlinear systems

The output-feedback control problem of a class of uncertain SISO nonlinear systems is investigated based on an indirect adaptive fuzzy approach. Because the system states are not required to be available for measurement, an observer is designed to estimate the system states. Compared with the existing results in the observer design, the main advantages of the proposed adaptive fuzzy output-feedback control approach are as follows: (1) It does not require to assume that the sign of the control gain coefficient is known and Nussbaum-gain technique is utilized to control the nonlinear systems with both the unknown control direction and the unmeasured states; (2) The observer in this paper is designed for the states rather than the tracking errors, then it is convenient to compute; (3) The controller singularity problem is perfectly avoided. The stability of the closed-loop system is analyzed by using Lyapunov method. A simulation example is given to verify the feasibility of the proposed approach.     

On the wave-cancelling nature of boundary layer flow control

This work deals with the feedforward active control of Tollmien–Schlichting instability waves over incompressible 2D and 3D boundary layers. Through an extensive numerical study, two strategies are evaluated; the optimal linear–quadratic–Gaussian (LQG) controller, designed using the Eigensystem realization algorithm, is compared to a wave-cancellation scheme, which is obtained using the direct inversion of frequency-domain transfer functions of the system. For the evaluated cases, it is shown that LQG leads to a similar control law and presents a comparable performance to the simpler, wave-cancellation scheme, indicating that the former acts via a destructive interference of the incoming wavepacket downstream of actuation. The results allow further insight into the physics behind flow control of convectively unstable flows permitting, for instance, the optimization of the transverse position for actuation. Using concepts of linear stability theory and the derived transfer function, a more efficient actuation for flow control is chosen, leading to similar attenuation of Tollmien–Schlichting waves with only about 10% of the actuation power in the baseline case.     

Finite time integral sliding mode control of hypersonic vehicles

This study investigates the tracking control problem for the longitudinal model of an airbreathing hypersonic vehicle (AHV) with external disturbances. By introducing finite time integral sliding mode manifolds, a novel finite time control method is designed for the longitudinal model of an AHV. This control method makes the velocity and altitude track the reference signals in finite time. Meanwhile, considering the large chattering phenomenon caused by high switching gains, an improved sliding mode control method based on nonlinear disturbance observer is proposed to reduce chattering. Through disturbance estimation for feedforward compensation, the improved sliding mode controller may take a smaller value for the switching gain without sacrificing disturbance rejection performance. Simulation results are provided to confirm the effectiveness of the proposed approach.     

Two-state dynamic gain scheduling control applied to an F16 aircraft model

The feasibility and benefits of applying a novel multi-variable dynamic gain scheduling (DGS) approach to a complex ‘industry-scale’ aircraft model are investigated; the latter model being a non-linear representation of the intrinsically unstable F16 aircraft incorporating detailed aerodynamic data. DGS is a novel control approach, which involves scheduling controller gains with one (or more) of the system states whilst accounting for the ‘hidden coupling terms’ ensuring a near-ideal response. It is effective for non-linear systems exhibiting rapid dynamic changes between operating points. Recently, this approach has been extended to a multi-variable and multi-input context. Hence, unlike previous DGS work on realistic aircraft models, relevant feedback gains are to be scheduled with all (i.e. two) state variables in order to demonstrate the ability of the approach to compensate for non-linearity during rapid manoeuvres and consequently achieving better flying qualities over a range of conditions than standard gain scheduling. Time history simulations are used to draw comparisons with the more traditional ‘static’ gain scheduling and input gain scheduling methods.     

Sensitivity analysis of closed-loop control systems on flexible structures

Local-velocity feedback (LVF) and linear-quadratic Gaussain (LQG) control schemes are implemented on passively tuned reaction mass actuators to control the vibrations of a flexible structure. The structure is lightly damped and possesses closely coupled low-frequency resonant modes. Both LVF and LQG controllers successfully eliminate the structure's vibrations. However, if the passive tuning parameters of the actuators are slightly mistuned, implementing LVF control actually results in an unstable system. On the other hand, LQG control proves to be insensitive to large changes in the passive tuning parameters of the actuators. In fact, the system with LQG control is never unstable, no matter what the actuator's passive tuning parameters are.     

Active vortex-induced vibration control of a circular cylinder at low Reynolds numbers using an adaptive fuzzy sliding mode controller

An adaptive fuzzy sliding mode control (AFSMC) scheme is applied to actively suppress the two-dimensional vortex-induced vibrations (VIV) of an elastically mounted circular cylinder, free to move in in-line and cross-flow directions. Laminar flow regime at Re=90, low non-dimensional mass with equal natural frequencies in both directions, and zero structural damping coefficients, are considered. The natural oscillator frequency is matched with the vortex shedding frequency of a stationary cylinder at Re=100. The strongly coupled unsteady fluid/cylinder interactions are captured by implementing the moving mesh technology through integration of an in-house developed User Define Function (UDF) into the main code of the commercial CFD solver Fluent. The AFSMC approach comprises of a fuzzy system designed to mimic an ideal sliding-mode controller, and a robust controller intended to compensate for the difference between the fuzzy controller and the ideal one. The fuzzy system parameters as well as the uncertainty bound of the robust controller are adaptively tuned online. A collaborative simulation scheme is realized by coupling the control model implemented in Matlab/Simulink to the plant model constructed in Fluent, aiming at determination of the transverse control force required for complete suppression of the cylinder streamwise and cross-flow oscillations. The simulation results demonstrate the high performance and effectiveness of the adopted control algorithm in attenuating the 2D-VIV of the elastic cylinder over a certain flow velocity range. Also, the enhanced transient performance of the AFSM control strategy in comparison with a conventional PID control law is demonstrated. Furthermore, the effect of control action on the time evolution of vortex shedding from the cylinder is discussed. In particular, it is observed that the coalesced vortices in the far wake region of the uncontrolled cylinder, featuring the C(2S)-type vortex shedding characteristic mode, are ultimately forced to switch to the classical von Kármán vortex street of 2S-type mode, displaying wake vortices of moderately weaker strengths very similar to those of the stationary cylinder. Lastly, robustness of AFSMC is verified against relatively large structural uncertainties as well as with respect to a moderate deviation in the uniform inlet flow velocity.     

Adaptive fuzzy control of uncertain MIMO non-linear systems in block-triangular forms

Adaptive control of a class of uncertain multi-input/multi-output (MIMO) non-linear systems in block-triangular forms is considered in this paper. By incorporating dynamic surface approach and ??minimal learning parameters?? algorithm, a systematic procedure for the synthesis of stable adaptive fuzzy tracking controllers with less tuning parameters is developed. Takagi?CSugeno (T-S) fuzzy logic systems (FLSs) are used to approximate those unstructured system functions rather than the unknown virtual control gain functions. Consequently, the potential controller singularity problem can be overcome. Moreover, both problems of ??explosion of learning parameters?? and ??explosion of complexity?? are avoided. The computational burden has thus been greatly reduced. The stability in the sense of semi-globally uniform ultimate boundedness (SGUUB) of the closed-loop MIMO systems is established via Lyapunov stability theorem. Finally, simulation results are presented to demonstrate the effectiveness and the advantages of the proposed control approach.