带钢温度模型及其自适应修正

探讨了针对热轧过程中与温度相关的各种物理现象的数学模型。在此基础上，提出了一种通过在线自适应及神经网络修正物理模型的方法，从而使带钢的计算温度更接近于实际温度。     

New model reference adaptive control with input constraints

A new scheme of adaptive control is proposed for a class of linear time-invariant( LTI) dynamical systems,especially in aerospace,with matched parametric uncertainties and input constraints. Based on a typical and conventional direct model reference adaptive control scheme,various modifications have been employed to achieve the goal. "C omposite model reference adaptive control"of higher performance is seam-lessly combined with "positive μ-mod",which consequently results in a smooth tracking trajectory despite of the input constraints. In addition,bounded-gain forgetting is utilized to facilitate faster convergence of parameter estimates. The stability of the closed-loop systemcan be guaranteed by using Lyapunov theory.The merits and effectiveness of the proposed method are illustrated by a numerical example of the longitudinal dynamical systems of a fixed-wing airplane.     

带钢温度模型及其自适应修正

提出了带钢热轧的温度计算模型 ,并在此基础上 ,对数学模型进行在线自适应和神经网络学习修正 ,使计算温度更接近于实测值     

使用SEDRIS的环境数据表示与交换

在建模与仿真(M&S)领域,综合环境数据表示与交换规范(SEDRIS)促进了环境数据表示和交换机制的发展.回答了"为什么需要SEDRIS"问题,介绍了SEDRIS的技术构成以及如何使用SEDRIS实现环境数据的交换与共享.     

马钢CSP生产线带钢板形控制系统

马钢薄板坯连铸连轧生产线的板形控制系统数学模型包括与板凸和平直度控制相关的轧辊弯曲模型、轧辊热磨模型、工作辊压扁模型、材料流量模型的算法与相应数据接口,以这些模型为基础采用板形设定算法及其在线自适应算法,实现了对热轧带钢成品板形的精确控制。实际生产表明,采用该系统后,凸度命中率可达96.37%。     

基于自抗扰控制技术的实时飞行仿真研究(英文)

针对四旋翼无人机欠驱动、强耦合的非线性动力学特性,文中研究设计了基于自抗扰控制技术的闭环飞行控制系统。自抗扰控制技术中,扩张观测器与基于误差的非线性反馈控制是其重要的两个部分。扩张状态观测器估计外部干扰和模型不确定性,以实现干扰和模型不确定性的动态补偿;此外,采用基于误差的非线性反馈可以改善控制效果。为保证飞行任务中精确的航迹跟踪,文中分析设计了一种实用的制导策略,并构建实时可视化飞行仿真系统以实现对所设计的制导策略和自抗扰飞行控制系统更为严格有效的验证。仿真结果表明所研究设计的制导策略和闭环飞行控制系统具有良好的制导和控制性能。     

基于自适应模糊推理的平面形状控制模型的预报

为了使中厚板矩形化。减少切边量和切头尾置，提高成材率，平面形状控制成为解决其有效的方法。边部和头尾的预报模型是平面形状控制的基础，在已有的模型的基础上，分析边部和头尾变形的原因，根据实验数据，应用自适应神经模糊推理系统建立了边部和头尾的模型，并通过仿真验证了模型的正确性。     

基于VxWorks热连轧HAGC计算机实时控制系统

文章系统地介绍了某厂热连轧HAGC控制系统改造项目的计算机控制系统,硬件结构以嵌入式VxWorks实时操作系统为基础,针对轧钢过程影响厚度的各种因素,分别采用相应的补偿措施、现场数据说明了设计方法的实用性。     

Research on the attitude regulation of 3-DOF hover system

Quadrotor helicopter is emerging as a popular platform for unmanned aerial vehicle re- search, due to its simplicity of structure and maintenance as well as the capability of hovering and vertical take-off and landing. The attitude controller is an important feature of quadrotor helicopter since it allows the vehicle to keep balance and perform the desired maneuver. In this paper, nonlin- ear control strategies including active disturbance rejection control （ADRC）, sliding mode control （SMC） and backstepping method are studied and implemented to stabilize the attitude of a 3-DOF hover system. ADRC is an error-driven control law, with extended state observer （ESO） estimating the unmodeled inner dynamics and external disturbance to dynamically compensate their impacts. Meanwhile; both backstepping technique and SMC are developed based on the mathematical model, whose stability is ensured by Lyapunov global stability theorem. Furthermore, the performance of each control algorithm is evaluated by experiments. The results validate effectiveness of the strate- gies for attitude regulation. Finally, the respective characteristics of the three controllers are high- lighted by-comparison, and conclusions are drawn on the basis of the theoretical and experimental a- nalysis.     

缝合式复合材料夹芯板的动态特性

以典型缝合式复合材料夹芯板为研究对象,建立其动力学方程,开展该夹芯板的动态特性研究,探讨了缝合密度和缝合线角度对夹芯板模态特性、频响特性以及随机动响应的影响。研究结果表明:缝合线的存在增强了面板与夹芯层间的整体性,提高了夹芯板的固有频率,并约束了夹芯板的局部模态,降低了结构的模态密度,整体上降低了夹芯板在噪声载荷作用下的加速度及响应能量,但对结构应力响应影响较小;缝合线主要降低了上面板的动响应,对主承力板的动响应影响相对较小;随着缝合密度的增大,缝合式夹芯板的整体性逐渐提高,加速度及响应能量逐渐降低并收敛;缝合线角度则对结构总体动态特性影响不明显。