低速风洞翼型测压实验系统开发

发布时间：2018-05-17 12:20

本文选题：虚拟仪器 + 翼型测压实验　；参考：《中国民航大学》2016年硕士论文

【摘要】：翼型测压实验是应用于教学和科研工作的最重要的空气动力学重要实验之一。翼型测压实验的重点是能够有一套准确可靠的数据采集系统。随着虚拟仪器技术的发展,研制一款基于相关硬件和虚拟仪器技术软件的翼型测压数据采集系统成为可能。本文利用Labview等软件,从基本原理、需求分析、实验过程、硬件采购、编制平台等多方面出发,进行了满足翼型测压实验需求的数据采集系统开发。文章首先从空气动力学和数据采集等方面的基本理论开始着手,介绍了系统开发所需要的基础知识,选出翼型的型号和尺寸。然后按照翼型实验的自然流程,通过二维数值仿真取到了表面的压力数据,为真实实验提供指导,接着以仿真数据为依据利用萤火虫算法和非均匀有理B样条拟合办法进行了测压孔的优化布置。与其他智能算法相比,萤火虫算法适应性明显高于其他智能算法,在控制顶点较少(n=4)时仍能只需10次迭代收敛,其他智能算法无法做到;萤火虫算法比传统方法在相同控制点数下,精度比传统方法高20%。研究过程中还解决了了可行域为高维单纯形时智能算法的初始化问题,接着通过计算确定翼型模型材料,并选择了相关的压力变送器和数据采集卡,最后使用Labview编制了数据采集平台系统,实现了了操作、采集、保存等系统功能。经过研发,一款基于虚拟仪器技术的翼型测压系统被研制出来,该系统经济性、实用性、可扩展性均符合要求,对中小型低速风洞具有实用和可推广价值。
[Abstract]:Airfoil pressure measurement is one of the most important aerodynamics experiments used in teaching and scientific research. The key point of airfoil pressure measurement experiment is to have a set of accurate and reliable data acquisition system. With the development of virtual instrument technology, it is possible to develop a data acquisition system for airfoil pressure measurement based on related hardware and virtual instrument technology software. In this paper, a data acquisition system for airfoil pressure measurement is developed based on Labview software, including basic principle, requirement analysis, experimental process, hardware purchase, programming platform and so on. This paper begins with the basic theories of aerodynamics and data acquisition, introduces the basic knowledge needed for the development of the system, and selects the model and size of the airfoil. Then according to the natural flow of airfoil experiment, the surface pressure data are obtained by two-dimensional numerical simulation, which provides guidance for the real experiment. Then, based on the simulation data, the optimal layout of the pressure hole is carried out by using the firefly algorithm and the non-uniform rational B-spline fitting method. Compared with other intelligent algorithms, the adaptability of firefly algorithm is obviously higher than that of other intelligent algorithms. It can only need 10 iterations to converge when the control vertices are less than 4), but other intelligent algorithms can not. The accuracy of the firefly algorithm is 20% higher than that of the traditional method under the same control points. In the course of the research, the initialization problem of intelligent algorithm when the feasible region is high dimensional simplex is solved, and then the airfoil model material is determined by calculation, and the relevant pressure transmitter and data acquisition card are selected. Finally, the system of data acquisition platform is programmed with Labview, and the system functions such as operation, collection and preservation are realized. Through the research and development, a pressure measuring system for airfoil based on virtual instrument technology has been developed. The system is economical, practical and extensible. It has practical and popularized value for medium and small low speed wind tunnel.
【学位授予单位】：中国民航大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V211.74

【相似文献】