基于表面再现 Marching cubes算法改进与实现

从医学体数据中得到对象的三维可视图像有广泛的应用领域,例如医学诊断、法医学、古人类学等.本文讨论并分析了一种基于表面再现的 Marching cubes算法的优点及存在的不足,给出了算法在时空开销、不确定性等方面的改进和解决方案,改进后的算法在实际系统中取得了良好的效果.     

软件测试的度量方法及其应用

软件测试是找出软件中的错误,它是保证软件质量的关键,软件测试的度量是对影响软件测试的属性所进行的定量测量.本文简述了应用软件测试度量技术时所应具有的基本知识,通过一个实例,介绍并讨论了一种实用的关于软件测试进度安排和软件错误数的度量方法.     

小孔法测量非均匀残余应力的数据处理与误差分析

讨论了逐层钻孔法测量非均匀残余应力的释放应变处理和测量误差对残余应力计算精度的影响。利用转换应力、转换应变,可方便地计算残余应力值。受小孔法本身缺陷的限制,计算所得残余应力误差随孔深增加而加大,测量深度约为应变片平均半径的一半。     

压气机叶片外物损伤模拟的撞击能量当量法

在分析外物与叶片间的运动态势后,提出压气机叶片外物员伤模拟的撞击能当量法,即使得摆锤的势能与外物摘击叶片时可能达到的功能相等。据此,设计并制作了摆锤装置,并实验观察到钛制压气机叶片损伤形态与撞击能量间的变化关系,即随着撞击能量的增加,损伤形态产生的顺序为,压痕→突缘→裂纹→突缘呈４５°剪切破坏,这与外场收集到的叶片的前缘损伤形态一致,同时,采用了ＴＣ４压气机叶片进行了相应的高周疲劳试验,验证了方法     

计算大型实对称特征问题的 Lanczos-QR 算法

为了计算大型实对称特征值问题Ｋｘ＝λＭｘ的少数低阶特征值对,本文给出Ｌａｎｃｚｏｓ－ＱＲ迭代方法。首先,给定初始迭代向量ｖ１,作ｍ步Ｌａｎｃｚｏｓ分解：ＫＶｍ＝ＭＶｍＴｍ＋ｈｍｅｍＴ。取Ｔｍ的ｄ个最大特征值为移位量,对Ｔｍ进行ｄ步带原点位移的ＱＲ分解。然后,修改初始迭代向量ｖ１。迭代地重新开始这一过程,迫使初始迭代向量ｖ１进入需求的特征子空间,从而使残量‖Ｋｘ－θＭｘ‖→０。数值例子表明,该方法收敛性强,且稳定、有效。     

Double-decoupled inverse design of natural laminar flow nacelle under transonic conditions

The inverse design based on the pressure distribution is an essential approach to realize the improvement of Natural Laminar Flow(NLF) performance for nacelles. However, the direct definition of target pressure distribution at design point is challenging for the dilemma to consider the constraints of shock wave and laminar flow at the same time. In addition, the universality of method will be limited when the inverse design is strongly coupled with the solver. Thus, a double-decoupled methodolog...     

基于叶端定时的转子叶片动应变重构不确定性量化

基于叶片非接触式动应变重构理论,开展动应变重构不确定性量化方法研究。基于方差合成定理建立重构叶片动应变不确定性量化分析模型;以模拟转子叶片为研究对象,开展旋转叶片叶端定时试验,利用周向傅里叶算法获取不同叶端定时传感器布局下的测点振幅,通过最大熵方法拟合振幅分布概率密度函数,确定叶端定时测振的不确定性参数;结合Kriging代理模型和试验共振频率数据对叶片有限元模型进行修正,获取关键测点位移-应变转换因子,并获取考虑共振转速以及测点位置不确定性的转换因子不确定性参数;获取重构动应变的均值、标准不确定度和包含区间,与应变片测量数据作对比。结果表明,除5号叶片A测点外,测量动应变均位于重构动应变的95%置信度下的包含区间内,且所有叶片的应变片测点动应变重构误差不超过15%。     

航空鼓形花键设计及其不对中接触特性

针对鼓形花键设计方法不完善、修形量范围无法确定的问题,提出利用花键齿面许用应力与内外花键配合干涉确定鼓形花键鼓形量的范围。以某航空发动机中央传动杆花键为例,开展鼓形花键设计;进而对比研究对中与不对中状态下普通花键和鼓形花键的接触特性。结果表明:对中状态下,普通花键接触应力集中于齿向加载端,而鼓形花键则集中于齿向中部且接触应力增大;不对中状态下,普通花键接触齿对数目显著减小且接触应力显著提高,而鼓形花键的均载性显著且接触应力降低;随着不对中的增大,普通花键因干涉而存在断齿风险,而鼓形花键仍能够啮合但脱开齿对数目增加,接触应力也急剧提高。所确定的鼓形花键修形量范围合理,能够将齿侧间隙、不对中补偿能力、与修形量定量耦合起来,为航空鼓形花键设计、不对中控制、承载能力与寿命提升提供了重要理论参考。      

Revisiting the space-time gradient method: A time-clocking perspective,high order difference time discretization and comparison with the harmonic balance method

This paper revisits the Space-Time Gradient (STG) method which was developed for efficient analysis of unsteady flows due to rotor–stator interaction and presents the method from an alternative time-clocking perspective. The STG method requires reordering of blade passages according to their relative clocking positions with respect to blades of an adjacent blade row. As the space-clocking is linked to an equivalent time-clocking, the passage reordering can be performed according to the alternative time-clocking. With the time-clocking perspective, unsteady flow solutions from different passages of the same blade row are mapped to flow solutions of the same passage at different time instants or phase angles. Accordingly, the time derivative of the unsteady flow equation is discretized in time directly, which is more natural than transforming the time derivative to a spatial one as with the original STG method. To improve the solution accuracy, a ninth order difference scheme has been investigated for discretizing the time derivative. To achieve a stable solution for the high order scheme, the implicit solution method of Lower-Upper Symmetric Gauss-Seidel/Gauss-Seidel (LU-SGS/GS) has been employed. The NASA Stage 35 and its blade-count-reduced variant are used to demonstrate the validity of the time-clocking based passage reordering and the advantages of the high order difference scheme for the STG method. Results from an existing harmonic balance flow solver are also provided to contrast the two methods in terms of solution stability and computational cost.     

基于无限元方法的直升机外部噪声仿真分析

为了准确地模拟直升机飞行中的外部噪声,建立了耦合计算流体力学/计算气动声学(Computational fluid dynamics/Computational aeroacoustics,CFD/CAA)的直升机机外噪声预测方法。气动计算采用CFD方法模拟旋翼、尾桨气动力以及气动干扰;噪声计算采用声学无限元方法,考虑固体边界的声散射效应和大气传播中的声衰减特性。以AC311A直升机为例,开展适航规范要求下的飞越噪声计算和分析。飞行试验结果对比分析验证了本文方法能够有效地用于直升机机外噪声的评估与分析。最后进行了误差分析,为直升机外部噪声评估算法和仿真模型的优化提供参考。