基于落震试验的油—气式起落架气体压缩多变指数变化规律研究

气体压缩多变指数是油气式起落架缓冲性能计算中的重要参数。通过对某型飞机油气式起落架落震试验中气腔压力数据的监测,对不同落震投放高度下气体压缩多变指数进行识别。利用最小二乘法,对多变指数变化曲线进行三次拟合,得出活塞杆压缩过程中气体多变指数的变化规律。本文建立了某型飞机起落架落震试验仿真分析模型,将拟合曲线引入仿真计算模型,对比了定常多变指数计算模型和非定常多变指数计算模型仿真结果。相对于定常多变指数模型,非定常多变指数计算模型仿真结果和试验对比误差小于定常多变指数计算模型,提高了仿真分析精度。     

应用单相流量计测量油水两相流

为探讨单相流量计用于液液两相流参数测量的可行性和有效性,本文对文丘里管、涡轮流量计和椭圆齿轮流量计用于油水两相流测量的响应特性进行了实验研究.文丘里管和涡轮流量计的实验管径为15 mm,25 mm,40 mm,椭圆齿轮流量计的实验管径为25 mm和40 mm.油水两相流总体积流量范围为1～5 m3/h,油含率范围为15%～85%.实验结果表明,文丘里管在高油含率时测得的油水两相流流量比实际流量偏大4%～5%.涡轮流量计的测量误差随油含率升高呈现增大的趋势,最大测量洪差小于5%.椭圆齿轮流量计用于油水两相流测量时相对测量误差小于1.0%且基本不受油含率影响.     

圆波导劈形端口辐射器的数值分析

高功率微波运用的圆波导劈形端口辐射器(Vlasov-Nakajima辐射器)的辐射场可视为由平开口圆波导的辐射场和在该辐射场中的劈形圆波导段的散射场叠加而成。运用等效电磁流原理数值求解Kirchhoff-kottler积分获得圆波导TM01模的辐射场,再应用物理光学方法计算劈形段的散射场,并将计算的远场方向图与实验结果比较,获得较满意的一致。     

双联齿轮断裂分析

机床传动系统双联直齿轮投入运行不久即发生齿面断裂事故,造成较大经济损失.传动系统所用双联齿轮未达到设计使用寿命,属于早期断裂失效.对现场收集到的断裂齿轮残块进行化学成分分析和硬度测试,对齿廓工作面及断裂形成的断口用扫描电镜进行微观观察,对齿轮残块上出现的裂纹用光学金相显微镜观察其形貌和微观特征,依据检测实验数据和结果,...     

飞机主起落架收放摇臂的动力学分析

本地运七飞机主起薄架系统，在接近收上位置到碰锁的过程建立了简化的流固耦合的有限元总体模型。利用动态增量非线性有限元程序（ＡＤＩＮＡ８４年版），对主起落架系统收上碰锁过程进行了动力学流固耦合的有限元分析，在此基础上对摇臂建立了更为精细的有限元地其进行了静力分析，无论总体模型还是精细模型均能够起初地反映实际情况，且模型中的有关参数的选取也是合理的，计算结果与试验结果也是吻合的，这说明本文关于飞机主起落     

Effect of non-linearities in the identification and fault detection of gear-pair systems

This study investigates issues related to parametric identification and health monitoring of dynamical systems with non-linear characteristics. In the first part, a gear-pair system supported on bearings with rolling elements is selected as an example mechanical model and the corresponding equations of motion are set up. This model possesses strongly non-linear characteristics, accounting for gear backlash and bearing stiffness non-linearities. Then, the basic steps of the parametric identification and fault detection procedure employed are outlined briefly. In particular, a Bayesian statistical framework is adopted in order to estimate the optimal values of the gear and bearing model parameters. This is achieved by combining experimental information from vibration measurements with theoretical information built into a parametric mathematical model of the system. In the second part of the study, characteristic numerical results are presented. First, based on the effect of the system parameters on its dynamics, a solid basis is created for explaining some of the peculiar results obtained by applying classical gradient-based optimization methodologies for the strongly non-linear system examined. Some serious difficulties, associated with the existence of irregular response or the coexistence of multiple motions, are first pointed out. A solution to some of these problems, through the application of a suitable genetic algorithm, is then presented. Special problems, related to more classical identification issues associated with the presence of measurement noise and model error, are also investigated.     

The effect of proximity of the landing gear lights on its turbulent wake

A simplified model of a landing gear is tested in a wind tunnel to investigate the effect of the landing light location on the resulting noise generation. Examination of the near-field pressure fluctuations, combined with phase-locked stereoscopic particle imaging velocimetry of the unsteady wake identified two distinct sources of pressure fluctuations. The higher frequency source has a wide frequency band and is situated in the outer regions of the wake near the lights. On the other hand, the lower frequency source is found to be stronger, has a narrower frequency band and is developed further downstream in the wake, closer to the wake centreline. The lower frequency source is observed to be rather robust as it is hardly affected by the location of the landing lights, whereas the higher frequency source becomes weaker as the spacing between the lights is reduced. The effect of a splitter plate positioned downstream of the landing gear strut is also investigated as a means of reducing the lower frequency pressure fluctuations. Although the lower frequency source is considerably weakened by the splitter plate, substantial enhancement of the higher frequency source is observed.     

基于自适应阈值的齿轮干涉图像前景区域提取方法

齿面物体像灰度法是激光移相干涉测量中提取齿轮干涉图像前景区域的重要方法之一,针对该方法因人工设定阈值且忽略不同图像边缘特征从而导致的测量效率及精度受限问题,提出了一种基于自适应阈值的齿轮干涉图像前景区域提取方法。首先分析齿轮齿面形貌特征与各边缘顶点差异,对图像进行区域划分;然后根据边缘灰度变化规律通过邻域窗口筛选合格像素点并获取掩模结果,实现前景区域提取;最后根据5类图像评价指标分别对4组算法分割结果与传统方法分割结果进行数据对比。结果表明：算法在实现图像自动处理的基础上与参考结果匹配精确度提升约3.5%～4.5%,PRI(probabilistic rand index)提升约3%～4%,VOI(variation of information)提高约15%～25%,GCE(global consistency error)降低约2.5%～3.5%,最终相位信息准确度提升9μm～15μm。结果符合精度要求,该方法可广泛应用于齿轮干涉图像前景提取中。     

渐开线齿轮传动非牛顿润滑介质的线弹流数值分析研究

采用适合各种流变模型的广义Reynolds方程，通过数值联立求解非牛顿介质的线弹流润滑基本方程组，获得了渐开线齿轮啮合过程的油膜压力、膜厚、表面剪应力分布，并分析了啮合过程中非牛顿效应对齿轮传动最小油膜厚度的影响。在数值计算方向引入延拓方法，使表面煎应力迭代具有大范围收敛性。     

A NEW STATIC MECHANICS MODEL TO SOLVE CONTACT PROBLEMS IN MECHANICAL SYSTEMS

The coupling of the local contact problems between the components and the deformation of the components in the mechanical system were discovered. A series of coordinate systems have been founded to describe the mechanical system with the contact proble.ms. The method of isolating the boundary of contact body from others has been used to describe the constraint between the contacting points. A more generalized static mechanics model of the mechanical system with the contact problems has been founded through the principle of virtual work, As an application, the model was used to study the multi-teeth engagement problems in the inner meshed planet gear systems. The stress distribution of contact gears was got. A test has verified that the static contact model and the computational method are right.