电容传感器的信号处理及其在机床主轴热变形测量中的应用研究

利用电容式传感器,设计一个高精度位移测量系统,对机床主轴的热变形量进行非接触式测量.根据被测对象的特点,阐明了系统的工作原理和数据的处理方法,分析了影响传感器测量精度、稳定性的因素,提出了利用电子学技术和数字信号滤波技术提高传感器精度的技术手段,为机床主轴热变形的高精度、非接触式测量提供了一种技术途径.经长时间实验分析...     

电动汽车方向盘绝对角位置传感器的研究

方向盘±720°绝对角位置的测量是轮式驱动电动汽车转矩协调控制解决方案的关键之一.通过16位处理器dsPIC30F6010A与两片TLES012通信,设计了一种基于iGMR的+720°绝对角位置非接触式传感器,并可通过外部中断设置方向盘的回正零点.给出了该传感器的具体实现方案,包括2个从动齿轮的齿数设计,绝对角位置的计...     

CCD微米级圆钢光电测径仪设计

提出了线阵CCD微米级非接触式圆钢光电测径仪的设计方案,并以ARM微处理器和单片机为核心实现了设计;解决了传统圆钢测径方法接触式测量的局限问题,具有结构简单、小型化、非接触、精度高等特点。实验结果表明,该系统实现了CCD非接触式圆钢光电测径,测量结果准确、精度高、稳定性好,且可直接方便地显示测量结果。     

基于角度传感器的玻璃材料折射率的测定

在介绍根据布儒斯特定律测量玻璃材料折射率的方法和用磁阻式角度传感器测角原理的基础上,提出一种利用角度传感器测量材料折射率的新方法,实现了角度量和材料折射率的非电量电测。通过用此方法测量2种玻璃样品的折射率与理论值进行比较,发现在不考虑传感器温度漂移及装置的平整性等系统误差的条件下,折射率测量的相对误差小于3%。研究还表明:新型锑化铟磁阻角度传感器的线性范围约200°,为设计非接触式角度量及折射率的自动测量系统打下了基础。     

基于多传感器的机器人遥操作人机交互系统

为了增强机器人人机交互系统的自然性,提出了基于多种传感器的非接触式人机交互系统设计方案,系统通过检测操作者手部动作和手部位置姿态的变化实现机器人的遥操作。研制了肌电传感器,获取手臂上一对拮抗肌上的表面肌电信号,并以此来判断机器人操作者的部分手部动作;利用Kinect体感设备和惯性测量单元获取手臂三维位置和姿态角信息。通过网络将人手的动作及位置姿态发送至机器人控制系统,以完成对机器人的控制。系统综合多种传感器的优点,极大减小了传统接触式交互方式对操作者运动范围的限制,实现了自然交互,实验表明了其有效性。     

一种新的不规则实体密度测量方法研究

根据不规则实体密度检测技术的需求,在分析非接触式体积测量系统基本原理的基础上,结合不确定度理论,研究了非接触式体积测量系统的性能指标.探索了该系统应用于不规则实体密度测量的可行性,分析了基于该系统的不规则体密度测量不确定度.研究结果表明,基于非接触式体积测量系统的不规则体密度测量方法具有较高的测量精度,可实现不规则实体密度的智能化无损检测.     

新型电涡流位移传感器

对旋转机械的转轴进行在线监测,一般都采用非接触式位移传感器。非接触式位移传感器是基于电涡流原理设计制造的,整个系统是由探头、延伸电缆和前置器组成的一次仪表测量系统。最近,德国申克公司推出了一种新型传感器VIBRONECS,其设计思想是采用混合集成电路的方法,把延伸电缆和前置器的功能用一块电子线路板代替,和探头线圈封装在一起,     

振动电容式静电传感器设计

依据振动电容器原理,设计了非接触式静电传感器,阐述了传感器的工作原理与软件、硬件设计方案,并给出了测试结果.该传感器通过红外定位有效降低了测量误差,提高了测量准确度,通过单片机控制由液晶显示可直观得到测量结果,并同时显示其电压极性.试验结果表明:该传感器在-30～30 kV范围内,线性度良好,可以满足该范围静电场测量要求.     

基于螺管形差动变压器的非接触式扭矩传感器的研究

扭矩测量是传动线路中的重要内容之一,高精度、高稳定性的非接触式扭矩测量方法是当今各国机械量测量研究的热点之一,为此,提出了一种基于螺管形差动变压器的非接触式扭矩传感器的研究.系统介绍了该测量方法的原理与结构.经实验证实:该测量原理可行,所设计的扭矩传感器具有较好的线性度和一致性,重复精度0.5%.     

一种新型的水位检测系统

主要从系统原理的简单描述,硬件、软件的设计和介绍,数据采集处理方式及创新点几个方面介绍了一种新型水位检测系统。该系统采用非接触式测量,针对接触式水位检测系统的测量电路测量速度慢、测量精度低、要与水接触、测高温液体时会产生误差等不足之处进行了改善,利用新型的压力传感器,能在传感器不接触到水的情况下对水位进行测量,延长了系统寿命。并且添加了温度补偿的功能来减小误差,提高了系统测量高温液体液位时的测量精度。该系统结构简单,成本较低,速度比接触式测温更快且使用寿命较长,适用于对液位测量精度要求较高的场合。     

一种基于应力控制的金属薄壳结构变形修复方法研究

研究了一种基于应力控制的金属薄壳结构变形修复方法,通过应用该方法成功实现了飞机整体油箱金属结构变形故障的修复。该方法在能量原理研究的基础上,通过研究变形修复中的结构内应力控制,在变形部位施加反向应力,使变形的金属薄壳结构恢复至原始形貌,从而达到修复变形的目的。整体油箱作为典型的金属薄壳结构,在修复过程中还需要保证气动外形、隐身功能等飞机特有的功能特性,因此,该变形修复过程需要多结构系统协调平衡、多领域综合优化。在修复飞机整体油箱这一典型金属薄壳结构变形故障的实践过程中,研究基于应力控制的金属薄壳结构变形修复方法,实现了对整体油箱金属薄壳结构的变形修复,对金属薄壳结构变形修复的研究具有重要的指导意义,为相关领域的变形修复提供了新的思路。     

基于计算机视觉的飞机燃油非接触式测量系统

为了实现飞机在任意飞行姿态下燃油量的测量,提出了一种新型的飞机燃油测量 系统。首先采用基于计算机视觉的非接触性液位感测技术,测得油箱中油位高度。然后采用 CAD 技术对油箱建模,实现了飞行姿态误差的修正。实现在油箱外对当前液面进行实时观测和 三维重建,无需对油箱内燃油通电,避免了传统测量方式的电磁干扰、电路磨损问题,提升了 燃油系统的安全性和可靠性。实时精确地测量剩余燃油量,对飞机的加输油控制、系统状态监 控、故障诊断隔离等功能具有重要意义。该油量测量方式与传统方式相比具有数字化、智能化 程度高、抗干扰能力强、可靠性高等优点。     

Coupled adjoint aerostructural wing optimization using quasi-three-dimensional aerodynamic analysis

This paper presents a method for wing aerostructural analysis and optimization, which needs much lower computational costs, while computes the wing drag and structural deformation with a level of accuracy comparable to the higher fidelity CFD and FEM tools. A quasi-three-dimensional aerodynamic solver is developed and connected to a finite beam element model for wing aerostructural optimization. In a quasi-three-dimensional approach an inviscid incompressible vortex lattice method is coupled with a viscous compressible airfoil analysis code for drag prediction of a three dimensional wing. The accuracy of the proposed method for wing drag prediction is validated by comparing its results with the results of a higher fidelity CFD analysis. The wing structural deformation as well as the stress distribution in the wingbox structure is computed using a finite beam element model. The Newton method is used to solve the coupled system. The sensitivities of the outputs, for example the wing drag, with respect to the inputs, for example the wing geometry, is computed by a combined use of the coupled adjoint method, automatic differentiation and the chain rule of differentiation. A gradient based optimization is performed using the proposed tool for minimizing the fuel weight of an A320 class aircraft. The optimization resulted in more than 10 % reduction in the aircraft fuel weight by optimizing the wing planform and airfoils shape as well as the wing internal structure.     

基于电化学原理的飞机燃油箱氧浓度机载测量技术

飞机燃油箱惰化系统属飞机燃油系统设计中重要的分系统，为了准确评估燃油箱惰化系统的功能与性能，需要根据飞机实际使用剖面和惰化系统设计特点确定适用的飞行测试方法。提出了一种基于电化学原理的飞机燃油箱氧浓度机载测量方法，用于飞行实时测量运输类飞机油箱内无油空间或惰化管路的气体氧浓度，并对飞行中的实际影响因素进行模拟分析。经过分析飞行实际环境影响因素、关键传感器匹配性以及原理样机的试验验证等工作，将燃油箱氧浓度机载测量技术转化为专用的飞机燃油箱氧浓度机载测量系统，并通过了飞行实测考验。试飞结果表明，该项技术能够实时准确测量运输类飞机各种状态下的燃油箱氧浓度，满足飞机燃油箱惰化系统的效能评估要求。     

Subdivision elements for large deformation of liquid capsules enclosed by thin shells

This paper presents a numerical method for studying the large deformation of a liquid capsule enclosed by a thin shell in a simple shear flow. An implicit immersed boundary method is employed for calculating the hydrodynamics and fluid–structure interaction effects. A thin-shell model for computing the forces acting on the shell middle surface during the deformation is described within the framework of the Kirchhoff–Love theory of thin shells. This thin-shell model takes full account of finite-deformation kinematics which allows thickness stretching as well as large deflections and bending strains. The interpolation of the reference and deformed surfaces of the shell is accomplished through the use of Loop's subdivision surfaces. The resulting limit surface is C¹-continuous which significantly improves the ability of the method in simulating capsules enclosed by hyperelastic thin shells with different physical properties. The present numerical technique has been validated by several examples including an inflation of a spherical shell and deformations of spherical, oblate spheroidal and biconcave capsules in the shear flow. In addition, different types of motion such as tank-treading, tumbling and transition from tumbling to tank-treading have been studied over a range of shear rates and viscosity ratios.     

不同复合材料蒙皮机身段的适坠性研究

基于典型客机机身结构建立了三框两跨机身段有限元模型,模拟了金属蒙皮机身段和复合材料蒙皮机身段的坠撞过程,分析了机身结构变形、加速度响应、能量变化趋势和各结构吸能特征,研究了蒙皮对机身段适坠性的影响。结果表明,抗剪切能力较差的复合材料蒙皮会导致结构破坏不够充分引发较大的坠撞加速度进而对乘员安全造成威胁。复合材料蒙皮刚度较大会导致"三角区域"产生加速度过载。蒙皮作为飞机坠撞时的重要吸能结构之一,不仅会影响自身的吸能特性,还会显著影响各个结构的吸能特性和整个机身段的适坠性。     

飞机燃油箱无油空间氧气浓度测量系统研究和发展综述

为了降低飞机燃油箱可燃性,绝大部分民用和军用飞机都安装了油箱惰化系统,来控制油箱无油空间的氧气浓度,但却一直没有适用于机载燃油箱的氧浓度实时监测系统。根据多型机油箱惰化系统试飞经验,总结了基于电化学原理和光谱吸收原理测量系统使用中的问题。依据文献分析,认为基于荧光猝灭原理的传感器将成为下一代机载油箱氧浓度测量系统的核心,并详细介绍了荧光猝灭效应的原理、检测方法、受感部和测量系统框架的研究现状。最后,指出测量系统应该向着轻量化、智能化和高可靠性方向发展。     

Active vibration control of a fluid/plate system using a pole placement controller

We consider the problem of active reduction of the structural vibrations induced by the sloshing of large masses of fuel inside a partly full tank. The proposed study focuses on an experimental device mimicking an aircraft wing made of an aluminium rectangular plate equipped with piezoelectric patches at the clamped end and with a cylindrical tip tank, more or less filled with liquid. After deriving a representative finite-dimensional model of the complete system, containing the first five structural modes of the plate and the first three liquid sloshing modes, a controller is computed. Since our main scope is to control the most energetic mode of the structure, a full state-feedback method coupled with an observer is used. Finally, the controller is also tested for different initial conditions/perturbations and the results are compared with the ones obtained with an H _∞ controller. Experimental results illustrate the relevance of the chosen strategy.     

基于区域行进策略的飞机油箱检查机器人路径规划算法

针对类似于飞机油箱环境中连续型机器人的路径规划问题,设计基于区域行进策略的路径规划算法,结合机器人本体结构约束规划到达油箱内任意给定目标点的路径。连续型机器人具有运动灵活性,但超冗余自由度导致了三维空间规划的多解性,增加了算法的复杂度。采用降低维度的方式,通过将三维空间转化为二维平面进行规划,降低了算法的时间复杂度。将飞机油箱的单舱划分为两个区域,根据目标点所处区域位置确定规划策略。最后,基于Matlab对所提算法进行仿真,实验结果验证了算法的可行性和有效性。     

A time-varying geometry modeling method for parts with deformation during machining process

Deformation due to residual stress is a significant issue during the machining of thin-walled parts with low rigidity. If there are multiple processes with deformation during machining, some process suitability issues will appear. On this occasion, the actual geometric state of the deformed workpiece is needed for process adjustment. However, it is still a challenge to obtain the complete geometry information of deformed workpiece accurately and efficiently. In order to address this issue, a time-varying geometry modeling method, combining cutting simulation and in-process measurement, is proposed in this paper. The deformed workpiece model can be reconstructed via transforming the deformed workpiece with only a small amount of the measurement points by superimposing material removal and workpiece deformation simulation according to a time sequence, which takes advantage of the proposed Curved Surface Mapping based Geometric Representation Model (CSMGRM). Machining experiment of a typical structural part has shown that the deformed geometry model of the whole workpiece can be reconstructed within the error of 0.05mm, which is less than one tenth of the finish machining allowance in general cases, and it is sufficient to meet the accuracy requirements for interference or overcut/undercut analysis and process adjustment.