延迟器级联型偏振控制器算法研究

利用邦加球图示法,推导了45°-0°-45°型偏振控制器的算法,得到偏振态变换时延迟量对应的计算公式。通过仿真对该算法进行验证,仿真结果表明:不论输入椭圆偏振光,线偏振光还是圆偏振光,该算法得到的输出偏振态与期望得到的输出偏振态一致,证明了该算法的合理性。     

零重力模拟气动悬挂系统的建模及恒压控制

为模拟空间结构地面动力学测试时的零重力环境,针对研制的气动悬挂装置(PSD)采用比例流量阀开发了高精度的恒定气压控制系统.在分析了系统原理的基础上,建立压力控制系统的非线性数学模型.模型包含了比例阀的动力学特性、阀口流动的非线性、气缸容腔的压力动态和由实验结果拟合的气体泄漏.针对实现恒压控制的目标,采用输入输出线性化方法得到相对阶为2的等价系统,由于模型具有参数不确定和未建模动态特性,设计了基于观测器和等效控制的模糊滑模变结构控制器(FSMC).实验结果表明,设计的控制器对负载变化、气源压力变化、活塞运动和外部干扰均具有较强的鲁棒性,稳态压力波动小于26 Pa,实现了高精度的恒压控制.     

基于哈密顿系统原理的PMSM自适应阻尼注入控制

基于能量成形和端口受控哈密顿（PCH）系统原理,针对永磁同步电机（PMSM）参数不确定性所引起的转速误差,利用自适应阻尼注入控制方法,设计了负载转矩恒定已知和未知情况下的控制器。采用最大转矩/电流（MTPA）控制原理确定系统期望平衡点,并分析其稳定性。仿真结果表明,将自适应阻尼注入控制方法应用到PMSM的PCH控制中,对参数不确定性所引起的转速误差具有很好的抑制作用,从而使系统具有较好的转速跟踪性能。     

一种应用于隔爆试验装置中的新型自动配气系统

针对应用于隔爆试验装置中的传统配气方法存在配气速度慢、系统体积较大的问题,设计了一种基于质量流量法的自动配气系统。该系统采用质量流量控制器精确控制多种不同气体的流量,输出的多种气体经混合装置均匀混合后,由O2分析仪和H2分析仪实时监测混合气体的体积分数。测试结果表明,该配气系统配气速度快、结构简单,配制的多种气体体积分数精度能满足GB 3836.2—2010的要求。     

改进教与学优化算法的LQR控制器优化设计

为了快速有效地确定线性二次最优控制(linear quadratic regulator,LQR)问题中的加权矩阵Q和R,针对主动悬架LQR控制器权系数设计问题,提出一种改进的教与学优化算法进行LQR优化设计。算法对基本教与学优化算法中的"教"与"学"阶段进行了进一步的改进,同时提出一种"自我学习"策略。通过仿真实验表明,和基本教与学算法、粒子群算法、遗传算法相比,本文算法在对主动悬架LQR控制器优化时,具有收敛速度快,求解精度高和稳定性强等优势。     

Fixed‐time synchronization for complex‐valued BAM neural networks with time delays

In this paper, the fixed‐time synchronization for complex‐valued bidirectional associative memory (BAM) neural networks with time delays is studied. Based on the fixed‐time stability, the Lyapunov functional method and some inequality techniques, a new criterion is presented to guarantee that the addressed systems achieve synchronization in fixed time and a more accurate estimation independent of the initial conditions is given for the settling time. Meanwhile, a new nonlinear delayed controller different from the existing ones is designed. In the end, two numerical examples are provided to illustrate the effectiveness of the obtained result.     

Hierarchical inversion‐based output tracking control for uncertain autonomous underwater vehicles using extended Kalman filter

In this study, a hierarchical inversion‐based output tracking controller (HIOTC) is developed for an autonomous underwater vehicle (AUV) subject to random uncertainties (e.g., current disturbances, unmodeled dynamics, and parameter variations) and noises (e.g., process and measurement noises). The proposed HIOTC respectively utilizes a combination of feedforward and feedback controls in a hierarchical structure based on the kinematic and dynamic models of the system. Moreover, to obtain uncontaminated or unavailable states for implementing the proposed control law, the extended Kalman filter (EKF) is employed to estimate the system states. Then, the position outputs, orientation, and velocity of the AUV are reached with guaranteed asymptotic stability. The robustness of the proposed HIOTC is verified through injection of random uncertainties into the system model. The closed‐loop stability of the proposed individual subsystems is respectively guaranteed to have uniformly ultimately bounded (UUB) performance based on the Lyapunov stability criteria. In addition, the asymptotic tracking of the overall system is demonstrated using Barbalat's lemma. Finally, the feasibility and effectiveness of the proposed control scheme are evaluated through computer simulations and it is shown that the overall system achieves good asymptotic tracking performance.     

改进Otsu算法的镀锌板表面缺陷检测方法

针对镀锌板在生产工艺和传输过程中对镀锌板表面造成缺陷的问题;文章应用了基于Otsu算法的镀锌板表面缺陷检测系统,由数字光源控制器、高速CCD相机、同步触发器和编码器等硬件设备共同连接组成,采集到镀锌板表面的图像,然后将图像传输给基于Otsu算法的图像处理系统;改进优化了Ostu算法,在一维直方图求解最佳截距阈值,利用该阈值和二维信息完成图像的分割,提高了图像的抗噪能力;使用分块检验所发初步判定镀锌板表面缺陷,再逐个排查确认缺陷区域,对缺陷特征进行分类并保存在缺陷数据库中,同时发出预警;实验结果显示文章研究的检测系统对镀锌板表面缺陷检出率最高可高达98％,检测出缺陷镀锌板的数量最多,系统的检测精度高.     

任务序列强度感知的大规模集群服务器控制模型

异构云数据中心各类服务器的控制成本和性能上的差异将影响其运维管理成本及QoS博弈平衡关系,针对任务序列强度具有的时效性,提出了任务序列强度感知的大规模任务调度模型。依据当前到达数据中心的任务序列的强度以及集群中服务器的当前状态,在任务调度中强调节约服务器运维管理成本和各服务器负载均衡的基础上实现优化数据中心对任务序列处理的平均响应时间和系统的吞吐量。通过对实验结果的分析,验证了集群服务器控制模型在任务调度中的可信度大于95%,同时通过与当前应用广且具代表性的算法——最短任务优先,公平分发机制进行比较分析,其效果是三者中最好的,也验证了模型的有效性和可行性。     

Robust Near-Hovering Flight Controller for Model-Scale Helicopters Via Parametric Approach

This paper aims to provide a parametric design for robust flight controller of the model-scale helicopter. The main contributions lie in two aspects. Firstly, under near-hovering condition, a procedure is presented for simplification of the highly nonlinear and under-actuated model of the model-scale helicopter. This nonlinear system is linearized around the trim values of the chosen flight mode, followed by decomposing this high-order linear model into three lower-order subsystems according to the coupling properties among channels. After decomposition, the three subsystems are obtained which include the coupling subsystem between the roll (pitch) motion and the lateral (longitudinal) motion, the subsystem of the yaw motion and the subsystem of the vertical motion. Secondly, by using eigenstructure assignment, the problem of flight controller design can be converted into solving two optimization problems and the linear robust controllers of these subsystems are designed through solving these optimization problems. Besides, this paper contrasts and analyzed the performances of the LQR controller and the parametric controller. The results demonstrate the effectiveness and the robustness against the parametric perturbations of the parametric controller.