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Development of crack detection and length estimation software system.

机译:裂缝检测与长度估算软件系统的开发。

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摘要

Structural integrity is an important topic in the discussion of aircrafts. As an aircraft is in flight it undergoes a variety of structural disturbances. The occurrences can create undue stress on the structure of the aircraft which can impact flight safety, stability, and even the efficiency of the engines. Structural Health Monitoring is the process of implementing a damage detection and characterization strategy for engineering structures. In this thesis, a crack detection and crack length estimation software system was developed, implemented and tested. The feature extraction method for the crack detection was chosen by the University of Dayton Research Institute (UDRI) and it fit the proposed technique of statistical analysis for feature extraction for this thesis. The feature extraction for crack length estimation was developed and tested in this thesis. The crack detection subsystem was developed using extracted features provided by the UDRI and were implemented using an artificial neural network on MATLAB software environment. The crack length estimation subsystem was developed using correlation coefficient for feature extraction and were implemented using adaptive neuro-fuzzy inference system on MATLAB software environment. The experimental data was then used to test the accuracy of the crack detection and crack length estimation software system. The developed software system was tested for accuracy on four aluminum dog-bone coupons to simulate the structure of an aircraft. The data used to simulate a crack was provided by the UDRI in conjunction with the AFRL. The crack detection subsystem testing produced an accuracy of detection of 85% or better for all coupons tested. The crack length estimation subsystem testing provided an 85% accuracy of estimation with an error no greater than 5% of estimation. The data was tested for error then divided by the number of actual recorded lengths. The observed results from testing show that the requirements were met as expected. The system developments, the simulation results and testing of the crack detection and crack length estimation software will be presented in this thesis report.
机译:结构完整性是飞机讨论中的重要主题。飞机在飞行中会遭受各种结构性干扰。这些事件会在飞机的结构上产生不适当的应力,从而影响飞行安全性,稳定性,甚至影响发动机的效率。结构健康监测是对工程结构实施损伤检测和特征化策略的过程。本文开发,实现和测试了裂纹检测和裂纹长度估计软件系统。代顿大学研究所(UDRI)选择了用于裂缝检测的特征提取方法,该方法适合本文提出的统计分析技术,用于特征提取。本文开发并测试了用于裂纹长度估计的特征提取。裂纹检测子系统是使用UDRI提供的提取功能开发的,并使用MATLAB软件环境上的人工神经网络来实现。裂纹长度估计子系统是使用相关系数进行特征提取而开发的,并且是在MATLAB软件环境下使用自适应神经模糊推理系统实现的。然后将实验数据用于测试裂纹检测和裂纹长度估计软件系统的准确性。所开发的软件系统在四个铝制狗骨形试样上进行了准确性测试,以模拟飞机的结构。 UDRI与AFRL一起提供了用于模拟裂纹的数据。裂纹检测子系统测试对所有测试的试样产生了85%或更高的检测精度。裂纹长度估算子系统测试提供了85%的估算精度,而误差不大于估算值的5%。测试数据是否有错误,然后除以实际记录的长度数。从测试中观察到的结果表明,符合要求。本文将介绍系统的发展,裂纹检测和裂纹长度估计软件的仿真结果和测试。

著录项

  • 作者

    Terrell, Kevin.;

  • 作者单位

    Tennessee State University.;

  • 授予单位 Tennessee State University.;
  • 学科 Electrical engineering.;Computer engineering.
  • 学位 M.S.
  • 年度 2012
  • 页码 89 p.
  • 总页数 89
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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