基于梯度增强型Kriging模型的气动反设计方法

基于Kriging模型的代理优化算法目前在气动优化设计中得到了广泛应用。但在高维(设计变量大于30个)气动优化中,计算量过大的问题对其进一步发展产生了严重制约。将翼型和机翼气动反设计问题转化为优化问题,采用Adjoint方法进行快速梯度求解,利用基于梯度增强型Kriging(GEK)模型的代理优化算法分别开展了18、36和108个设计变量的气动反设计。首先,通过采用在设计空间局部建立GEK模型的方法成功地将基于代理优化算法的气动反设计问题的维度拓展到了100维以上。其次,研究了梯度计算精度对基于GEK模型的反设计的影响,发现梯度精度越高,反设计的最终效果越好,同时效率相当。最后,通过不同维度的气动反设计算例,比较了改进拟牛顿法(BFGS)、基于GEK模型和Kriging模型的代理气动反设计方法,结果表明基于GEK模型的代理优化算法的效率大幅度高于基于Kriging模型的代理优化算法,并且维度越高,效率优势越明显;同时,基于GEK模型的代理优化算法在优化效果及分析程序调用次数上相比于BFGS方法也略有优势。     

CR工艺参数对不锈钢焊接裂纹的检出率影响

焊接过程中在应力及其他致脆因素共同作用下,容易形成焊接裂纹,严重影响焊接构件的安全使用,是无损检测最关注的焊接构件严重缺陷之一。射线照相面对焊接裂纹具有尖锐的缺口和大的长宽比的特征,需要较高的检测灵敏度才能保证检测可靠性。本研究采用计算机射线照相(CR)技术,研究CR检测工艺参数对不锈钢焊接裂纹检出率的影响程度,验证了利用图像归一化信噪比衡量图像质量的合理性。     

基于TVS管的机载电子设备数据接口雷电防护设计

针对机载电子设备数据接口的雷电防护要求,本文介绍了机载电子设备雷电防护器件的选择依据,分析了基于TVS管的数据接口雷电防护方法和电路拓扑结构,给出了计算公式并指出了TVS管用于数据接口雷电防护设计中需要注意的问题。     

高速球轴承的生热分析

在结合球轴承的拟静力学和生热分析的基础上, 对球轴承各热源分别进行生热计算, 得到了高速球轴承各个单元间的局部生热和轴承总生热, 分析了输入转速、载荷等多种参数对轴承各单元间的局部生热和总生热的影响, 结果显示球轴承的生热绝大部分来自球与内圈滚道的自旋生热, 并且转速、轴向载荷和内圈沟曲率系数对生热的影响最大.同时将球轴承作为一个整体用现有经验公式计算轴承生热, 其结果严重偏离台架功耗试验结果, 而从局部热源出发计算轴承总生热更为准确, 为轴承的三维温度场计算、润滑油油量选择等奠定了良好的基础.      

基于 FPGA 的 DVI 视频接收器设计

针对目前 DVI 视频传输的大规模应用,给出了一个符合 DVI1.0规范的基于 Xilinx Virtex-5 FPGA的 DVI视频接收器的实现方法.该方法利用简单的电阻电容和 FPGA内置数字控制阻抗(DCI)功能来实现TMDS电平的转换,利用 FPGA 内置的 DDR 和 ISERDES 实现 DVI 数据的串并转换,利用 FPGA 内置时钟资源实现时钟恢复和相位调整,最后经过逻辑解码,输出并行带同步信号的视频数据     

复杂区域之间距离的计算与应用

复杂区域之间距离的计算平面布局,干涉检验,ＣＡＤ／ＣＡＭ等领域具有广泛的应用,本文提出了基于二元可微函数在矩形区域中最小值的距离计算方法,论述了基本思想及算法实现。算法不含迭代求解过程,计算量小,简便易行,符合应用实际,最后给出了ＣＡＤ／ＣＡＭ领域中,加工刀具半径的选取,螺旋式下刀方式参数的确定等应用实例。     

An Adaptive Transmission Scheme for Deep Space Communication

Deep space communication is quite different from conventional ground communication due to its time-varying,complexity and large signal delay,which consequently affects communication quality and system efficiency.Adjusting the transmission parameters when the channel environment changes during the communication can guarantee the performance index of the system,and therefore improve communication efficiency. An adaptive transmission scheme of transceiver based on Consultative Committee for Space Data Systems(CCSDS)protocols is proposed in this paper. According to the variation of the deep space channel,the symbol rate of transmission data is adjusted dynamically by estimating the signal-to-noise ratio(SNR) of the receiver in real time and adjusting the channel environment. This scheme can improve the channel utilization and system throughput under the premise of limiting the system bit error rate. Furthermore,this scheme is successfully implemented in Xilinx Virtex-5 FPGA board.     

A transition prediction method for flow over airfoils based on high-order dynamic mode decomposition

This article presents a novel approach for predicting transition locations over airfoils, which are used to activate turbulence model in a Reynolds-averaged Navier-Stokes flow solver. This approach combines Dynamic Mode Decomposition (DMD) with e^N criterion. The core idea is to use a spatial DMD analysis to extract the modes of unstable perturbations from a steady flowfield and substitute the local Linear Stability Theory (LST) analysis to quantify the spatial growth of Tollmien–Schlichting (TS) waves. Transition is assumed to take place at the stream-wise location where the most amplified mode’s N-factor reaches a prescribed threshold and a turbulence model is activated thereafter. To improve robustness, the high-order version of DMD technique (known as HODMD) is employed. A theoretical derivation is conducted to interpret how a spatial high-order DMD analysis can extract the growth rate of the unsteady perturbations. The new method is validated by transition predictions of flows over a low-speed Natural-Laminar-Flow (NLF) airfoil NLF0416 at various angles of attack and a transonic NLF airfoil NPU-LSC-72613. The transition locations predicted by our HODMD/e^N method agree well with experimental data and compare favorably to those obtained by some existing methods (LST/e^N or $\gamma -\stackrel{￣}{R{e}_{\theta \text{t}}}$). It is shown that the proposed method is able to predict transition locations for flows over different types of airfoils and offers the potential for application to 3D wings as well as more complex configurations.