Semi-analytical model for flat indentation of metal materials and its applications

The increasing use of small material components in a wide range of industrial fields necessitates the development of an accurate and robust indentation testing method. To this end, this paper proposes an Energy-density-equivalence for a Flat Indentation (E-FI) model based on the energy density equivalent principle. The proposed model describes the relationships among the material parameters of Hollomon’s power law (H-law), flat indenter diameter, energy, and indentation displacement. An E-FI Method (E-FIM) that determines the H-law parameters of materials through the indentation test is also developed. The energy-displacement curves forward-predicted by the E-FI model (based on known H-law parameters of materials) and the H-law parameters of materials given by the E-FIM (based on known energy-displacement curves) are consistent with the results of Finite Element Analysis (FEA) and the H-law parameters of materials used as the input for FEA, respectively. Using E-FIM, the goodness of fit for both stress–strain curves with H-law, predicted based on the displacement with 2% signal interference, and that for stress–strain curves without interference is more than 0.98. The stress–strain relations predicted by E-FIM were consistent with the results obtained via uniaxial tensile tests of ten ductile materials.     

CHANG'E-2 lunar escape maneuvers to the Sun–Earth L2 libration point mission

This paper addresses lunar escape maneuvers of the first Chinese Sun–Earth L2 libration point mission by the CHANG'E-2 satellite, which is also the world's first satellite to reach the L2 point from a lunar orbit. The lunar escape maneuvers are heavily constrained by the remaining propellant and the condition of telemetry, track and command, among others. First, these constraints are analyzed and summarized to design a target L2 Lissajous orbit and an initial transfer trajectory. Second, the maneuver mathematical models are studied. The multilevel maneuver schemes which consist of phasing maneuvers and a final lunar escape maneuver are designed for actual operations. Based on the scheme analysis and comparison, the 2-maneuver scheme with a 5.3-h-period phasing orbit is ultimately selected. Finally, the mission status based on the scheme is presented and the control operation results are discussed in detail. The methodology in this paper is especially beneficial and applicable to a future multi-mission instance in the deep space exploration.     

Multi-scale thermodynamic analysis method for 2D SiC/SiC composite turbine guide vanes

Ceramic Matrix Composite (CMC) turbine guide vanes possess multi-scale stress and strain with inhomogeneity at the microscopic scale. Given that the macroscopic distribution cannot reflect the microscopic stress fluctuation, the macroscopic method fails to meet the requirements of stress and strain analysis of CMC turbine guide vanes. Furthermore, the complete thermodynamic properties of 2D woven SiC/SiC-CMC cannot be obtained through experimentation. Accordingly, a method to calculate the thermodynamic properties of CMC and analyze multi-scale stress and strain of the turbine guide vanes should be established. In this study, the multi-scale thermodynamic analysis is investigated. The thermodynamic properties of Chemical Vapor Infiltration (CVI) processed SiC/SiC-CMC are predicted by a Representative Volume Element (RVE) model with porosity, leading to the result that the relative error between the calculated in-plane tensile modulus and the experimental value is 4.2%. The macroscopic response of a guide vane under given conditions is predicted. The relative error between the predicted strain on the trailing edge and the experimental value is 9.7%. The calculation of the stress distribution of micro-scale RVE shows that the maximum value of microscopic stress, which is located in the interlayer matrix, is more than 1.5 times that of macroscopic stress in the same direction and the microscopic stress distribution of the interlayer matrix is related to the pore distribution of the composite.     

本钢物资量检斤状况的图形分析系统

本文介绍针对本钢集团公司全部计量器具，采用Visual FoxPro6.0，实现对物资量检斤状况的图形分析。     

球面镜偏心测量的数字化评价方法

运用数字图像处理技术和最小二乘拟合技术,通过Matlab软件编程实现了球面偏心的计算和评价,并将该方法的结果与传统测量方法的结果进行比较,证明了该评价方法的有效性。     

厚板铝合金静止轴肩搅拌摩擦焊热过程及受力状态数值分析

基于Deform–3D软件建立了12mm板厚6061–T6铝合金静止轴肩搅拌摩擦焊接(Stationary Shoulder Friction Stir Welding,SSFSW)过程热力耦合数值模型,探讨了焊接工艺对SSFSW温度场、热循环及受力状态的影响规律。计算结果表明:焊接转速增加50%将引起焊核最高温度增加21.6%以上;焊接速度增加50%分别导致高温停留时间和冷却时间降低50%和60%以上;对给定转速1000~1500r/min及焊接速度100~150mm/min范围,静止轴肩的轴向力为28.2~24.3kN,前进阻力为17.4~15.3kN,焊接转速增加50%其轴向压力降低13.8%,焊接速度增加50%其前进阻力增加13.7%;搅拌针扭矩最高值在27.3~25N·m范围。上述数值模拟结果为厚板铝合金SSFSW搅拌工具设计及工艺优化提供重要理论依据。     

基于工程图学投影变换板图构建的研究

培养人们对三维几何形体及相关位置的空间逻辑思维能力和形象思维能力,是工程图学研究的主要任务之一。用投影变换来帮助学习者培养空间想象能力是学习中必用的手段和方法。讨论了工程图学研究过程中投影变换时如何合理、有效地利用有限空间来构建板图、如何恰当选择例图的方法等问题,同时提出了书中用图的不足及改进方法。     

基于多传感器的空间遥操作机器人虚拟预测环境建模

虚拟预测环境技术是解决遥操作系统中时延问题的有力手段,但其有效性依赖于环境模型的精度。为了提高虚拟预测环境的建模精度,提出了基于多传感器信息融合的建模方法。首先根据CCD摄像机采集的图像建立虚拟环境模型的初始模型,再利用远地力觉和位置传感器信息对初始模型进行校验。为了观察命令在虚拟环境中的执行情况,采用一种简单有效的注册方法,将图形模型叠加在摄像机视频图像上,以便操作者进行对比分析。实验表明利用本文算法建立的虚拟环境模型是准确可靠的,有利于提高基于虚拟预测环境技术的遥操作系统的有效性和可操作性。     

智能高分辨率彩色图形系统NHGCB的软件

本文介绍了自行设计研制的NHGCB高分辨率彩色图形系统。该系统以INTEL82720为核心,并自含MCS-51单片机子系统,既可独立进行图形显示,又可与IBM等微机相连构成多处理机图形处理系统。NHGCB支持最高分辨率为1024×1024,可同时显示16/4096种麒色。本文重点介绍该系统的软件结构及绘图程序设计方法,包括NHGCB的工作方式、主机与单片机子系统的通讯与控制程序,以及GDC的编程方法等。     

基于图像卷积的地图匹配算法

地图匹配定位是一种主流的车载导航定位方法,其以车辆轨迹数据和路网地图为基础,将车辆位置估计输出到路网地图上。该过程可对车辆定位结果进行修正,是车辆导航、交通诱导、交通预测等应用的基础。针对现有地图匹配算法存在的一些问题,如算法流程依赖路口匹配精度,在较大初始误差场景下寻路正确率较低,以及寻路结果错误易影响后续匹配精度等,提出了一种基于图像卷积的地图匹配方法。利用图像卷积方式对比了车辆轨迹与道路的几何特征,以实现匹配定位,从而确保了初始误差较大场景下的匹配精度,并且避免了由寻路错误所引发的相关问题。