面向服务的智能建筑软件框架研究

建筑管理系统(BMS)、能源管理系统(EMS)、物联网设备、建筑信息模型(BIM)、电网及气象服务等多元信息系统是有效支撑由数据驱动的智能建筑软件高效运行的关键。然而,这些由不同开发商提供的系统之间缺乏统一且明确界定的程序接口与标准,这已成为制约应用程序在模块开发、可扩展性及重用性上进一步发展的主要障碍。为增强云环境下智能建筑系统对需求和技术变化的适应能力,提出一个优化的端到端实现架构。该架构以Zachman框架为基础,通过符合MACH原则的微服务、API和基于云的组件来确保整个系统的高灵活性、可扩展性以及向前兼容能力。为了验证所提优化方法的有效性,以某高校工程实训中心为案例,开发了一套智能建筑应用程序。经过一年多的实际运行,该程序充分展示了传感器数据与BIM模型集成的数字孪生应用、基于事件驱动的实时传感器数据与建模分析等先进功能,不仅证明了所提方法的前瞻性和兼容性,同时也展现了其应对不断变化的需求和挑战的能力。

Mach数和壁面温度对HyTRV边界层转捩的影响

典型的高超声速飞行器流场存在着复杂的转捩现象,其对飞行器的性能有着显著的影响。针对HyTRV这款接近真实高超声速飞行器的升力体模型,采用数值模拟方法,研究Mach数和壁面温度对HyTRV转捩的影响规律。采用课题组自研软件开展数值计算,Mach数的范围为3~8,壁面温度的范围为150~900 K。首先对■转捩模型和SST湍流模型进行了高超声速修正:将压力梯度系数修正、高速横流修正引入到■转捩模型,并对SST湍流模型闭合系数β~*和β进行可压缩修正;然后开展了网格无关性验证,通过与实验结果对比,确认了修正后的数值方法和软件平台;最终开展Mach数和壁面温度对HyTRV边界层转捩规律的影响研究。计算结果表明,转捩区域主要集中在上表面两侧、下表面中心线两侧;增大来流Mach数,上下表面转捩起始位置均大幅后移,湍流区大幅缩小,但仍会存在,同时上表面层流区摩阻系数不断增大,下表面湍流区摩阻系数不断减小;升高壁面温度,上下表面转捩起始位置先前移,然后快速后移,最终湍流区先后几乎消失。

高马赫数球状气泡动力学理论研究

The compressibility of fluids has a profound influence on oscillating bubble dynamics,as characterized by the Mach number.However,current theoretical frameworks for bubbles,whether at the first or second order of the Mach number,are primarily confined to scenarios characterized by weak compressibility.Thus,a critical need to elucidate the precise range of applicability for both first-and second-order bubble theories arises.Herein,we investigate the suitability and constraints of bubble theories with different orders through a comparative analysis involving experimental data and numerical simulations.The focal point of our investigation encompasses theories such as the Rayleigh–Plesset,Keller,Herring,and second-order bubble equations.Furthermore,the impact of parameters inherent in the second-order equations is examined.For spherical oscillating bubble dynamics in a free field,our findings reveal that the first-and second-order bubble theories are applicable when Ma≤0.3 and 0.4,respectively.For a single sonoluminescence bubble,we define an instantaneous Mach number,Mai.The second-order theory shows abnormal sensibility when Mai is high,which is negligible when Mai≤0.4.The results of this study can serve as a valuable reference for studying compressible bubble dynamics.

Phase sensitivity with a coherent beam and twin beams via intensity difference detection

We focus on the Mach–Zehnder interferometer(MZI) with the input of a coherent beam and one of the bright entangled twin beams with an external power reference beam employed for measurement. The results show that the phase sensitivity can reach sub-Heisenberg limit and approach quantum Cramer–Rao bound by changing the squeezing parameters and the photon number of the coherent beam, under the phase-matching condition. The absence of the external power reference beam will degrade the performance of the phase sensitivity. Meanwhile, this scheme shows good robustness against the losses of the photon detectors. We present a detailed discussion about the phase sensitivities when the inputs are two coherent beams, or a coherent beam plus a single-mode squeezed vacuum beam based on the MZI. This scenario can be applied in the field of phase precision measurements and other optical sensors.

Effect of Sweptback Angle of a Delta Wing on Surface Pressure Distribution at Supersonic Mach Numbers

The purpose of this work is to shed light on the effect of the pivot position on the surface pressure distribution over a 3D wing in different flight conditions.The study is intended to support the design and development of aerospace vehicles where stability analysis,performance optimization,and aircraft design are of primary importance.The following parameters are considered:Mach numbers(M)of 1.3,1.8,2.3,2.8,3.3,and 3.8,angle of incidence(θ)in the range from 5°to 25°,pivot position from h=0.2 to 1.The results of the CFD numerical simulations match available analytical data,thereby providing evidence for the reliability of the used approach.The findings provide valuable insights into the relationship between the surface pressure distribution,the Mach number and the angle of incidence.

Base Pressure Control with Semi-Circular Ribs at Critical Mach Number

When better fuel-air mixing in the combustion chamber or a reduction in base drag are required in vehicles,rockets,and aeroplanes,the base pressure control is activated.Controlling the base pressure and drag is necessary in both scenarios.In this work,semi-circular ribs with varying diameters(2,4,and 6 mm)positioned at six distinct positions(0.5D,1D,1.5D,2D,3D,and 4D)inside a square duct with a side of 15 mm are proposed as an efficient way to apply the passive control technique.In-depth research is done on optimising rib size for various rib sites.According to this study,the base pressure rises as rib height increases.Furthermore,the optimal location for the semi-circular ribs with a diameter of 2 mm is at 0.5D.The 1D location appears to be optimal for the 4 mm size as well.For the 6 mm size,however,the 4D position fills this function.

Momentum as Translations at Conformal Infinity

Although General Relativity is the classic example of a physical theory based on differential geometry, the momentum tensor is the only part of the field equation that is not derived from or interpreted with differential geometry. This work extends General Relativity and Einstein-Cartan theory by augmenting the Poincaré group with projective (special) conformal transformations, which are translations at conformal infinity. Momentum becomes a part of the differential geometry of spacetime. The Lie algebra of these transformations is represented by vectorfields on an associated Minkowski fiber space. Variation of projective conformal scalar curvature generates a 2-index tensor that serves as linear momentum in the field equations of General Relativity. The computation yields a constructive realization of Mach’s principle: local inertia is determined by local motion relative to mass at conformal infinity in each fiber. The vectorfields have a cellular structure that is similar to that of turbulent fluids.

圆柱及切割圆柱低Mach数绕流气动声辐射

以柱体绕流声辐射为研究对象,探讨低Mach数流动气动声定量预测方法。首先,理论分析Lighthill声类比理论与基于流体动力学压力对时间求导的扰动分离模型之间内在联系。其次,利用计算流体动力学对圆柱及其尾部切割后的亚临界流态绕流进行二维数值求解,分析两种湍流模型的流场计算效果。最后,分别使用声类比理论FW-H方程及扰动分离模型进行柱体绕流气动声辐射定量预测,分析声指向性及频谱特性。数值结果表明声类比理论与扰动分离模型预测的声辐射频谱相似,但前者的幅值略高;圆柱尾部切割使尾流脉动增强,导致声辐射变大。

发动机进气道内激波主导流动专题序言

进气道是吸气式发动机的核心气动部件之一。高Mach数进气道的通流总增压比可达30倍以上,极限增压比则更是高达数百倍,如此高的增压比主要依靠各类形式的强激波实现。与此同时,管道四壁都存在边界层,使得高Mach数进气道内存在大量由强激波和边界层主导的强特征流动现象。

防腐管道法兰面衬里自动磨平设备设计

用于石油化工等行业的钢基体管道,在生产时需在其内壁铺设防腐胶板(橡胶衬里),为保证密封性能,在对接管口法兰处需留余料,目前法兰面橡胶衬里余料采用的是人工打磨法,该方法工作效率低,磨平到钢基本体精度难以保证,产生的胶粒碎屑、灰尘影响工人健康。针对此,设计三轴设备驱动砂轮进行自动加工,采用滚珠丝杆滑台组成三轴运动平台,采用Mach3系统运动控制卡、步进电机进行控制,实现自动磨平,提高了中小企业的自动化生产程度。

Numerical Analysis of Cavity-Based Control of Base Pressure Variations at Supersonic Mach Numbers

In the present study,the base pressure variations induced by the presence of a cavity,known to have a strong influence of the behaviour of supersonic projectiles,are investigated through numerical solution of the balance equations for mass,momentum,and energy.An area ratio of four is considered and numerical simulations are carried out at Mach M=1.2,1.4,1.6,and 1.8 assuming no cavity or cavity locations 0.5D,1D,1.5D,and 2D.The inlet pressure of the nozzle is considered as a flow variable.The Taguchi method is also used,and the considered cases are then analyzed using a full factorial experimental design.The results show that the cavity is effective in increasing the base pressure for the conditions examined.For other nozzle pressure ratios,cavities do not lead to passive control due the change in the reattachment length.The distribution of wall pressure reveals that,in general,a cavity used to implement passive control of the base pressure does not adversely influence the flow pattern in the domain.

Modeling and Validation of Base Pressure for Aerodynamic Vehicles Based on Machine Learning Models

The application of abruptly enlarged flows to adjust the drag of aerodynamic vehicles using machine learning models has not been investigated previously.The process variables(Mach number(M),nozzle pressure ratio(η),area ratio(α),and length to diameter ratio(γ))were numerically explored to address several aspects of this process,namely base pressure(β)and base pressure with cavity(βcav).In this work,the optimal base pressure is determined using the PCA-BAS-ENN based algorithm to modify the base pressure presetting accuracy,thereby regulating the base drag required for smooth flow of aerodynamic vehicles.Based on the identical dataset,the GA-BP and PSO-BP algorithms are also compared to thePCA-BAS-ENNalgorithm.The data for training and testing the algorithmswas derived using the regression equation developed using the Box-Behnken Design(BBD).The results show that the PCA-BAS-ENN model delivered highly accurate predictions when compared to the other two models.As a result,the advantages of these results are two-fold,providing:(i)a detailed examination of the efficiency of different neural network algorithms in dealing with a genuine aerodynamic problem,and(ii)helpful insights for regulating process variables to improve technological,operational,and financial factors,simultaneously.

来流Mach数连续变化下的激波串运动特性

为了研究入射激波变化的隔离段内激波串的运动特性,设计并搭建了直连式变Mach数实验系统,捕捉了相同来流Mach数变化速率、不同背压变化速率下激波串的运动行为,揭示了入射激波与背压同时变化对激波串运动的影响机理。入射激波与背压同时变化时,共有3个方面的因素会影响激波串整体的上下游运动趋势,其一,Mach数变化,Mach数增大导致激波串向下游运动,该影响随Mach数增大逐渐减弱;其二,背景波系移动,背景激波反射点靠近激波串前缘时,可能引起激波串的突跳;其三,背压压比变化,背压压比增大时激波串向上游运动,该影响随背压压比增大逐渐增强。三方面因素共同作用下激波串表现出复杂的运动。

桌面式五轴联动数控加工中心

当前数控加工向高精度、高速度、高柔性、体系开放化方向发展。五轴联动数控机床可以加工工艺复杂的零件,但因技术难度大、造价昂贵,致使大多数高等院校无法购买,这阻碍了五轴联动数控机床先进制造技术在国内的普及,也阻碍了中国制造业的快速发展。本产品作为新一代桌面式微小型数控机床,主要运用于高校教学和实验等场景。

Computation of Stiffness and Damping Derivatives of an Ogive in a Limiting Case of Mach Number and Specific Heat Ratio

This work aims to compute stability derivatives in the Newtonian limit in pitch when the Mach number tends to infinity.In such conditions,these stability derivatives depend on the Ogive’s shape and not the Mach number.Generally,the Mach number independence principle becomes effective from M=10 and above.The Ogive nose is obtained through a circular arc on the cone surface.Accordingly,the following arc slopes are consideredλ=5,10,15,−5,−10,and−15.It is found that the stability derivatives decrease due to the growth inλfrom 5 to 15 and vice versa.Forλ=5 and 10,the damping derivative declines with an increase inλfrom 5 to 10.Yet,for the damping derivatives,the minimum location remains at a pivot position,h=0.75 for large values ofλ.Hence,whenλ=−15,the damping derivatives are independent of the cone angles for most pivot positions except in the early twenty percent of the leading edge.

Computational Analysis of Surface Pressure Distribution over a 2D Wedge in the Supersonic and Hypersonic Flow Regimes

The complex fluid-dynamic instabilities and shock waves occurring along the surface of a two-dimensional wedge at high values of the Mach number are studied here through numerical solution of the governing equations.Moreover,a regression model is implemented to determine the pressure distribution for various Mach numbers and angles of incidence.The Mach number spans the interval from 1.5 to 12.The wedge angles(θ)are from 5°to 25°.The pressure ratio(P2/P1)is reported at various locations(x/L)along the 2D wedge.The results of the numerical simulations are compared with the regression model showing good agreement.

THE LOW MACH NUMBER LIMIT FOR ISENTROPIC COMPRESSIBLE NAVIER-STOKES EQUATIONS WITH A REVISED MAXWELL'S LAW

We investigate the low Mach number limit for the isentropic compressible NavierStokes equations with a revised Maxwell's law(with Galilean invariance) in R^(3). By applying the uniform estimates of the error system, it is proven that the solutions of the isentropic Navier-Stokes equations with a revised Maxwell's law converge to that of the incompressible Navier-Stokes equations as the Mach number tends to zero. Moreover, the convergence rates are also obtained.

Quantum-enhanced optical precision measurement assisted by low-frequency squeezed vacuum states

Stable low-frequency squeezed vacuum states at a wavelength of 1550 nm were generated.By controlling the squeezing angle of the squeezed vacuum states,two types of low-frequency quadrature-phase squeezed vacuum states and quadrature-amplitude squeezed vacuum states were obtained using one setup respectively.A quantum-enhanced fiber Mach–Zehnder interferometer(FMZI)was demonstrated for low-frequency phase measurement using the generated quadrature-phase squeezed vacuum states that were injected.When phase modulation was measured with the quantumenhanced FMZI,there were above 3 dB quantum improvements beyond the shot-noise limit(SNL)from 40 kHz to 200 kHz,and 2.3 dB quantum improvement beyond the SNL at 20 kHz was obtained.The generated quadrature-amplitude squeezed vacuum state was applied to perform low-frequency amplitude modulation measurement for sensitivity beyond the SNL based on optical fiber construction.There were about 2 dB quantum improvements beyond the SNL from 60 kHz to 200 kHz.The current scheme proves that quantum-enhanced fiber-based sensors are feasible and have potential applications in high-precision measurements based on fiber,particularly in the low-frequency range.

A Low Mach Number IMEX Flux Splitting for the Level Set Ghost Fluid Method

Considering droplet phenomena at low Mach numbers,large differences in the magnitude of the occurring characteristic waves are presented.As acoustic phenomena often play a minor role in such applications,classical explicit schemes which resolve these waves suffer from a very restrictive timestep restriction.In this work,a novel scheme based on a specific level set ghost fluid method and an implicit-explicit(IMEX)flux splitting is proposed to overcome this timestep restriction.A fully implicit narrow band around the sharp phase interface is combined with a splitting of the convective and acoustic phenomena away from the interface.In this part of the domain,the IMEX Runge-Kutta time discretization and the high order discontinuous Galerkin spectral element method are applied to achieve high accuracies in the bulk phases.It is shown that for low Mach numbers a significant gain in computational time can be achieved compared to a fully explicit method.Applica-tions to typical droplet dynamic phenomena validate the proposed method and illustrate its capabilities.

莱迪思加强低功耗FPGA产品系列

莱迪思半导体公司推出先进的系统控制FPGA——莱迪思MachXO5T-NX系列,旨在帮助客户应对日益复杂的系统管理设计。MachXO5T-NX FPGA是基于莱迪思Nexus平台的最新低功耗FPGA,具有PCIe先进互连、更多的逻辑和存储资源以及更强大的安全性。这些全新的低功耗器件结合了莱迪思行业领先的低功耗、小尺寸和可靠性,旨在将莱迪思在控制FPGA领域的长期以来的优势赋予企业网络、机器视觉和工业物联网等领域更广泛的控制功能设计和应用中。