时滞线性系统振动主动控制的滑移模态方法

直接从时滞微分方程求解控制律，对时滞线性系统振动主动控制的滑移模态方法进行了研究，并给出了控制具体实现过程。推导出的切换面和控制律表达式中，除了包含有当前的状态反馈外，还包含有前若干步控制的线性组合。算例结果显示，所提控制方法能够较好地控制系统的峰值响应。且能够保证控制系统的稳定性；若按无时滞控制设计对地滞系统进行振动控制，系统响应有可能出现发散。     

一种改进的延时反馈混沌控制方法

基于Pyragas延时反馈混沌控制方法和相空间压缩法（限制器），提出了一种改进的延时控制方法，即将空间压缩作为系统状态变量的一种约束施加到延时反馈混沌控制中。以Roessler系统为例数值验证了此方法。结果表明此方法可以将混沌系统很快控制到一个期望的周期轨道上，与原始的延时反馈方法相比缩短了控制时间。     

基于能量准则的板振动控制的LQR法

针对压电层合结构振动的主动控制问题，为了优化控制效果，本文基于现代控制理论提出了选用结构振动能量和控制信号能量作为控制目标函数的LQR法。首先，按能量准则推导了控制目标函数中权系数矩阵(Q矩阵和R矩阵)的理论计算公式，为权系数矩阵的选取提供了一定的理论依据。然后，运用该算法，分析了压电层合板受到初始位移激励和冲击载荷作用下的控制过程，用Matlab进行系统仿真，得到了板中心点的位移和控制电压大小随时间变化的曲线。数值模拟的结果表明，该方法能达到更有效控制结构振动和减小控制能量消耗的目的，与一般的LQR控制方法相比，能满足系统多方面的设计要求且控制效果更优，从而验证了该LQR方法运用到结构振动主动控制中的可行性。     

考虑时滞的框架结构控制可靠性研究

提出了一种适合于确定框架结构可靠性计算方法．利用模态变换，把系统变为模态独立的振动方程，根据Field提出的假设，先定义阈值，假设控制后系统响应对阚值的穿阚率服从泊松分布，然后根据各模态的控制结果确定相应的可靠性．最后根据Veneziano提出的方法给出系统的可靠性。本文提出针对框架重点部位的控制输出来确定系统可靠性概念。考虑到实际情况，在控制方法选择针对系统不确定性具有较好控制效果的广义预测控制并考虑时滞影响。本文最后给出了计算实例。     

离散神经网络中的分岔,混沌及控制混沌

本文通过数值方法研究了一类离散神经网络中“内依马克－沙克分岔”、混沌及控制混沌问题。在分岔出现后，随着参数的改变发现不变吉Γβ湮来现象。对一类混沌给出其活动区域的。研究了周期比例脉冲方法（ＧＭ方法）控制混沌在离散神经网络中的应用，讨论了其控制混沌的策略与机制，提出一种变幅值冲控制方法，比ＧＭ方法有明显优点。     

混沌系统的自适应延迟控制

本文结合Ｐｙｒａｇａｓ的延迟反旬控制思想，提出了镇定混沌吸引子中嵌入的不稳定周期轨道的自适应延迟控制法。避免了常规自适应控制方法需要设计参圪模型或确定目标状态的麻烦，字种自适应延迟控制方法，控制器简单，实时性好，数值仿真结果验证了这种方法的有效性。     

结构振动的滑模变结构半主动控制

研究应用磁流变阻尼器(MRD)对结构振动半主动控制的算法和原理。研制并对磁流变阻尼器进行了阻尼特性实验，采用非线性滞回双粘性模型描述磁流变阻尼器的阻尼特性，模型结果与实验结果非常一致。采用滑模控制算法和趋近律方法设计了半主动控制器。利用滑模控制方法所建立的控制器，本文给出了地震激励下结构振动半主动控制算例。计算分析表明，半主动滑模控制具有控制效果明显、鲁棒性好等优点，是一种非常有发展前途的控制方法。     

控制存在时滞的线性系统主动控制的滑移模态方法

本文研究控制存在时滞的线性系统的滑模控制方法。在控制时滞量为采样周期的整数倍和非整数倍的两种情况下，通过采用零阶保持器，将包含时滞的连续系统转化为形式上不包含时滞的标准离散线性系统，然后分别进行切换函数和控制律的设计。所得出的切换面和控制律表达式中，除了含有当前的状态反馈外，还包含有前若干步控制项的线形组合。最后对某三自由度结构模型进行仿真计算，验证了所给控制方法的有效性。     

非线性振动和振动控制研究的新方向：控制混沌

概述了近年来在控制混沌这一非线性振动和振动控制新的研究方向上的进展，首先介绍了控制混沌的内容和意义，然后阐述了控制混沌的几类主要方法，包括输送控制、镇定控制和非线性系统理论应用的原理和发展。最后展望了控制混沌的发展趋势。     

一种重复控制律的设计与实现

本文提出了一种重复控制律的设计方法，该方法将反馈控制律设计与重复控制律设计相结合，在反馈控制的基础上引入重复控制回路，以此提高系统对周期输入信号的跟踪能力和对周期扰动的抑制能力。文中给出了系统稳定的充分条件和该方法的实现方式，通过对三轴仿真转台的实验验证了该方法的有效性。     

超声速多喷流干扰流场特性研究

研究了旋成体上超声速来流与超声速横向多喷流相撞产生的层流干扰流场特性. 数 值方法针对三维可压缩Navier-Stokes方程按二阶精度Roe格式进行离散,采用基于多区对 接网格技术的有限体积法. 数值模拟结果描述了多喷流干扰流场的空间结构以及激波/边界层 干扰引起的分离范围,探讨了沿流向等间距排列的喷口个数对表面和空间流场结构以及压力 分布的影响规律. 结果表明,第一喷口对多喷流干扰流场主要结构和喷口上游表面分离范围 起主导作用. 其中三喷流流场数值模拟的对称面激波结构与实验纹影结果进行对比,符合较 好.     

Minimum Time Control of Flexible Spacecraft by Hamilton's Principle

Modern space vehicles structure requisites are getting more and more stringent and complex as mission tasks become more sophisticated. This leads to the necessity of developing analysis methods that take into account structure flexibility and the need of reducing manoeuvre time as much as possible. In this work, a method based on the Hamilton Principle in its weak mixed form is developed, in which co-ordinates derivatives do not appear, but only their virtual variations. The proposed formulation is able to take into account system flexibility and saturation constraints on control torques and forces. A non-linear variational condition is obtained, which can be solved by means of a time-finite-element technique to give the minimum-time solutions of the control problem. The solutions for slewing manoeuvres are given, along with a new solution of the distributed optimal control problem.     

航天器动力学与控制的研究进展与展望

开展航天器动力学与控制的研究在航天技术的发展中起到举足轻重的作用, 其目的在于发展有效的方法促使航天器在各阶段平稳可靠地运行. 航天器技术发展迅速, 其形式日趋多样化, 功能与构造日趋复杂,已经向大型空间站、微小卫星、深空探测等方向发展. 航天器结构表现出多耦合、非线性、极端外界环境, 以及大尺度柔性结构等特征, 由此激发起航天器动力学与控制领域各方向的深入研究. 航天器动力学与控制的研究方法覆盖理论分析、数值仿真, 以及实验模拟等诸多方面, 研究内容十分丰富. 本文概括介绍了近年来航天器动力学与控制研究方面的发展状况, 综述了跨航天器动力学与控制、航天器系统级动力学与振动控制、航天器部件级动力学与振动控制等航天领域中的若干基础问题. 内容主要集中于航天领域中不同应用范围、不同层次结构的航天器动力学模型的建立和动力学响应与振动控制的研究方法及已取得的成果. 最后, 提出了该领域中值得进一步考虑的科学问题及未来的发展方向.      

四旋翼飞行器建模及位置跟踪控制(英文)

相对其他无人飞行器平台,四旋翼飞行器有其独特的优势,因而受到广泛的关注。位置跟踪控制对四旋翼飞行器的应用非常重要。在阐述四旋翼飞行器的飞行原理和操控机制的基础上,研究了其动力学模型,并提出了一种简化的数学模型。四旋翼飞行器是欠驱动耦合系统,为了实现系统解耦并得到清晰的控制回路,设计了多回路PID控制方案,其控制目标是位置和偏航角,而姿态角和横滚角由位置误差调节。最后,通过仿真验证了控制方法的有效性。     

主动磁悬浮控制力矩陀螺的系统仿真

以刚体动力学为基础，考虑功放延时、转子不平衡、磁轴承非线性等因素，建立了磁轴承反馈控制控制系统模型，对不同的控制律进行了仿真分析。仿真结果表明，应用状态反馈进行解耦控制能够有效抑制转子系统的陀螺效应对系统稳定性的影响，且在初始偏差下可以快速线性收敛，稳定性很好。     

The existence problem of optimal control for nonlinear processes

The existence problem of optimal control systemsdescribed by z=f(t,x.u)is discussed in this paper,where f(f,x,u)is a more general function and theclass of admissible control functions are generalenough to contain those control functions which arefrequently used in engineering.The problem for anoptimal control approximated by a sequence of controlfunctions being part of certain function classes isconsidered here,an example in contradiction with theconclusion of ref.[1]about this problem is given,and a correct conclusion is presented.     

Analysis of second outbreak of COVID-19 after relaxation of control measures in India

At present, more and more countries have entered the parallel stage of fighting the epidemic and restoring the economy after reaching the inflection point. Due to economic pressure, the government of India had to implement a policy of relaxing control during the rising period of the epidemic. This paper proposes a compartment model to study the development of COVID-19 in India after relaxing control. The Sigmoid function reflecting the cumulative effect is used to characterize the model-based diagnosis rate, cure rate and mortality rate. Considering the influence of the lockdown on the model parameters, the data are fitted using the method of least squares before and after the lockdown. According to numerical simulation and model analysis, the impact of India’s relaxation of control before and after the inflection point is studied. Research shows that adopting a relaxation policy prematurely will have disastrous consequences. Even if the degree of relaxation is only 5% before the inflection point, it will increase the number of deaths by 15.03%. If the control is relaxed after the inflection point, the higher degree of relaxation, the more likely a secondary outbreak will occur, which will extend the duration of the pandemic, leading to more deaths and put more pressure on the health care system. It is found that after the implementation of the relaxation policy, medical quarantine capability and public cooperation are two vital indicators. The results show that if the supply of kits and detection speed can be increased after the control is relaxed, the secondary outbreak can be effectively avoided. Meanwhile, the increase in public cooperation can significantly reduce the spread of the virus, suppress the second outbreak of the pandemic and reduce the death toll. It is of reference significance to the government’s policy formulation.

     

一种弧形高强钢车身零件冲压回弹控制方法

高强度钢板材料冲压性能对冲压成形后零件精度的影响较大,主要表现在成形性能不稳定和回弹控制复杂.弧形零件具有典型的回弹特征,且回弹量较大,难以获取回弹的具体运动规律,给回弹控制和补偿带来了困难.本文在分析弧形高强钢零件回弹特征规律的基础上,开发典型截面回弹运动规律分析程序,定量分析回弹截面整体和局部的平动与转动量,采用反...     

On initial,boundary conditions and viscosity coefficient control for Burgers' equation

In order to use the optimal control techniques in models of geophysical flow circulation, an application to a 1D advection–diffusion equation, the so-called Burgers' equation, is described. The aim of optimal control is to find the best parameters of the model which ensure the closest simulation to the observed values. In a more general case, the continuous problem and the corresponding discrete form are formulated. Three kinds of simulation are realized to validate the method. Optimal control processes by initial and boundary conditions require an implicit discretization scheme on the first time step and a decentered one for the non-linear advection term on boundaries. The robustness of the method is tested with a noised dataset and random values of the initial controls. The optimization process of the viscosity coefficient as a time- and space-dependent variable is more difficult. A numerical study of the model sensitivity is carried out. Finally, the numerical application of the simultaneous control by the initial conditions, the boundary conditions and the viscosity coefficient allows a possible influence between controls to be taken into account. These numerical experiments give methodological rules for applications to more complex situations. © 1998 John Wiley & Sons, Ltd.     

Control of the corner separation in a compressor cascade by steady and unsteady plasma aerodynamic actuation

This paper reports experimental results on using steady and unsteady plasma aerodynamic actuation to control the corner separation, which forms over the suction surface and end wall corner of a compressor cascade blade passage. Total pressure recovery coefficient distribution was adopted to evaluate the corner separation. Corner separation causes significant total pressure loss even when the angle of attack is 0°. Both steady and unsteady plasma aerodynamic actuations suppress the corner separation effectively. The control effect obtained by the electrode pair at 25% chord length is as effective as that obtained by all four electrode pairs. Increasing the applied voltage improves the control effect while it augments the power requirement. Increasing the Reynolds number or the angle of attack makes the corner separation more difficult to control. The unsteady actuation is much more effective and requires less power due to the coupling between the unsteady actuation and the separated flow. Duty cycle and excitation frequency are key parameters in unsteady plasma flow control. There are thresholds in both the duty cycle and the excitation frequency, above which the control effect saturates. The maximum relative reduction in total pressure loss coefficient achieved is up to 28% at 70% blade span. The obvious difference between steady and unsteady actuation may be that wall jet governs the flow control effect of steady actuation, while much more vortex induced by unsteady actuation is the reason for better control effect.