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21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017

作者： Yang, Jing Zhang, Baoqiang Chen, Qing Su, Guoqiang Qin, Qiang School of Aerospace Engineering Xiamen University Xiamen361005 China Aeronautics Science and Technology Key Laboratory of full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China Xian710065 China

ISBN: (纸本)9781624104633

Aerodynamic heating is inevitable in hypersonic flight. The flutter boundary of a hypersonic vehicle is sensitive to structural material variations caused by heating. In this paper, a pratical quantification of margins and uncertainties (QMU) framework methodology is introduced to aerothermoelastic analysis considering uncertainty. Uncertainty propagation using point collocation Non-intrusive Polynomial Chaos Method (NIPC) of a low-aspect-ratio wing in aerothermoelastic analyses is presented first. Within the analysis, aleatory uncertainty quantification is conducted to prove the effectiveness and efficiency of NIPC, then mixed (aleatory and epistemic) uncertainty quantification is accomplished. For both cases, the QMU methodology is applied to illustrate the capability of the developed framework. © 2017, American Institute of aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Hypersonic vehicles

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Study on aircraft structure strain-gage loads-monitoring method 2nd

Study on aircraft structure strain-gage loads-monitoring met...

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2nd International Conference of Structural Health Monitoring and Integrity Management, ICSHMIM 2014

作者： Tian, Yuan Xiao, Yingchun Aeronautics Science and Technology Key Laboratory Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute China

ISBN: (纸本)9781138027763

A method of aircraft structure load monitoring based on strain gages has been developed by taking the composite materials box as the object of study. To obtain load equation, the mechanics model of composite materials box is established, sensor network layout and load test are designed using the multiple liner regression method to process, experimental data are optimized and inspected, and finally the structural load calibration measurement is conducted. The validation test result indicates the error of the real load value and the calculated loads is less than 10%. © 2015 Taylor & Francis Group, London.

关键词： Strain gages

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Opportunities and challenges of aircraft shm 2nd

Opportunities and challenges of aircraft shm

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2nd International Conference of Structural Health Monitoring and Integrity Management, ICSHMIM 2014

作者： Xiao, Yingchun Sun, Xiasheng Aeronautics Science and Technology Key Laboratory Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute China

ISBN: (纸本)9781138027763

From the viewpoint of the evolution of aircraft Structural Integrity Program and of the change of aircraft structure design philosophy, the necessity of aircraft Structural Health Monitoring (SHM) technology was analyzed. aircraft structure design requirements and safe control system were discussed. The evidence strongly proves that the SHM technology, with great potential for improving the safety and reliability of aircraft structural level, reducing maintenance costs for future aircraft structures, will bring a revolutionary impact on aircraft structure design. Also China partner’s recent research work for SHM was presented. © 2015 Taylor & Francis Group, London.

关键词： Airframes

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*** on continuum damage mechanics model for high cycle fatigue

*** on continuum damage mechanics model for high cycle fatig...

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The 2015 2nd International Conference on Advanced Engineering technology(ICAET 2015)

作者： Xin-Tong Shi Ying-Chun Xiao Hong Chen Bo Huang Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China

A continuum damage mechanics model was proposed to predict the high cycle fatigue life. The Walker correction was introduced in the proposed model to consider mean stress effects. The proposed model was verified by some experimental data on LC4 and LY12 CZ aluminum alloy under high cycle fatigue loading. The results showed that the predicted life of the proposed model well correlated with experimental data.

关键词： cycle Study on continuum damage mechanics model for high cycle fatigue

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The Application Research of ID Chip for Strain Measurement in full scale aircraft structure Strength Static Test

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Procedia Engineering 2015年 99卷 1443-1447页

作者： Jia Zuo Gang Wang Full scale aircraft static/fatigue structure aviation science and technology key laboratory Aircraft Strength Research Institute of China Xi’an China

There are three main practical challenges must be faced when ID chip was introduced to increase the operating efficiency in a full scale static structure test. The first problem is how to protect ID Chip which is easily damaged at the complex test site; the second problem is what connection type should be adopted when ID Chip is connected with the wires; the last and most important issue is how to establish and record the one-one correspondences rapidly between strain gauge numbers and ID chip identification information. Against these existing the problems, some technical improvement solutions were proposed to refine the ID Chip applying conditions. And these solutions were employed and tested in a large scale aircraft static structure test. The test results show that the efficiency of test preparation cycle is increased by 40%, and the period and times of the test is greatly reduced. In a sense, the successful solution of these three practical issues makes the application value of ID Chip to be truly achieved and accelerate the automatic process of strain measurement.

关键词： ID Chip TEDS full scale static structure test Identifying information

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Kernel based digital image correlation

International Journal of Signal Processing, Image Processing...

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International Journal of Signal Processing, Image Processing and Pattern Recognition 2015年第3期8卷 261-272页

作者： Shen, Huan Zhang, Peize Shen, Xiang Energy and Power College Nanjing University of Aeronautics and Astronautics No. 29 Yudao Street Baixia District Nanjing China Aeronautics Science and Technology Key Laboratory of full scale aircraft structure and fatigue No. 85 Dianzi 2nd Road Yanta District Xi’an China

Digital image correlation (DIC) is an effective displacement field measurement method featuring non-contact and full-field, which has been successfully applied in lots of fields, especially in the field of experimental mechanics. Unfortunately, the traditional DIC technique (TDIC) depends on the output values of image sensor heavily that usually noised in practical imaging system. So, TDIC cannot deal with bias error introduced by the image noise effectively. In this paper, a kernel based DIC is proposed to help reduce the bias error by establishing and optimizing a weighted correlation function. Compared with the methods of low-pass filtering, KDIC preserves the high frequency information well but reduces the bias error caused by image noise effectively. To demonstrate, two kinds of kernel function are analyzed. One is Epanechnikov kernel, with which KDIC is equivalent to TDIC. The other is Gaussian kernel, which can be used to improve the anti-noise performance of TDIC and get more accurate subpixel displacements. Both simulation analyses and experimental results validate the effectiveness of this new method. 2015 SERSC.

关键词： Image correlation

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Influence of Strain Gauge Bonding-Process on Measurement Data Accuracy of Composite Material structure

Influence of Strain Gauge Bonding-Process on Measurement Dat...

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2nd International Conference on Advanced Composite Materials and Manufacturing Engineering, CMME 2014

作者： Zuo, Jia Zhang, Jian Feng Full scale aircraft static/fatigue structure aviation science and technology key laboratory Aircraft Strength Research Institute of China Xi'an 710061 China

ISBN: (纸本)9783038350651

With the extensive application of composite materials in aircraft structure, effect of the installing process of strain gauge on the strain measuring results of composite structure need to be researched experimentally. In this paper, the composite (T700/LT-03A) was selected to made specimens, and the different grinding manners, surface cleaning agents and bonding agents were adopted respectively as one of strain gauge installing processes. In order to identify influence of the different installing processes on the measuring data accuracy, measured strain data repeatability, linearity and characteristics of measured value oscillation are served as test standard. The compared test results show that the strain installing processes adopted in strength test on traditional metal also apply to the composite (T700/LT-03A) structures strength test. © (2014) Trans Tech Publications, Switzerland.

关键词： Composite materials

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Research on strain gauge protecting-process to measurement data accuracy of composite material structure

Research on strain gauge protecting-process to measurement d...

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4th International Conference on Information science, Automation and Material System, ISAM 2014

作者： Zuo, Jia Chen, Ge Wang, Gang Full Scale Aircraft Static/Fatigue Structure Aviation Science and Technology Key Laboratory Aircraft Strength Research Institute of China Xi'an 710061 China

ISBN: (纸本)9783038352501

With the extensive application of composite materials in aircraft structure, the test technologies of strain gauge are more important. But the installed strain gauge must to be protected against some influence. Because the protecting-process of strain gauge affected the strain measuring results of composite structure. In this paper, the composite (T700/LT-03A) was selected to made specimens, and the three different protective agents: protective glue, protective grume and protective grummet were adopted. In order to identify influence of the different protecting processes on the measuring data accuracy, comparison of repeatability and linearity before-and-after measured strain data are served as test standard. The compared test results show that the different strain protecting processes adopted in strength test can make different results of the measuring data accuracy. © (2014) Trans Tech Publications, Switzerland.

关键词： Strain gages

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Design and development of calibration data processing system for the structure strength test data acquisition equipment

Design and development of calibration data processing system...

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2014 International Conference on Computer, Intelligent Computing and Education technology, CICET 2014

作者： Zuo, J. Zhang, J.F. Liu, J.L. Full Scale Aircraft Static/Fatigue Structure Aviation Science and Technology Key Laboratory Aircraft Strength Research Institute of China Xi'an China Department of Aeronautical Structure Engineering School of Aeronautics Northwestern Polytechnical University Xi'an China

ISBN: (纸本)9781138026391

With the scale of static structure test increasing, the calibration workload of data acquisition device channel will rising, and artificial processing data has lot of problems about low efficiency, high error rate, and the long processing cycle. In order to deal with these problems, based on Delphi program development environment, the mass calibration data processing system was designed and developed. The system through the template of Excel realized interaction between Delphi and data. Batches of calibration data are processed automatically including data extraction, analysis, discrimination for standards compliance, and automatically generate data according to demands for the calibration table. This system greatly simplified the calibration data processing work, and improved the degree of automation for the structure strength test acquisition system calibrating. © 2014 Taylor & Francis Group, London, UK.

关键词： Calibration

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aircraft structure Strain-Gage Loads Monitoring Method Study

Aircraft Structure Strain-Gage Loads Monitoring Method Study

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The 2nd International Conference on Structural Health Monitoring and Integrity Management(第二届国际结构健康监测与完整性管理会议)

作者： TIAN Yuan XIAO Ying-chun Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of ChinaXi''anChina

A method of aircraft structurc load monitoring based on strain gages has been developed by taking the composite materials box as the object of *** order to obtain load equation,the mechanics model of composite materials box was established,sensor network layout and load test was designed,using the multiple liner regression method to process,optimize and inspection experimental data,finally conduct the structural load calibration *** validation test result indicates the error of the real load value and the calculated loads is less than 10%.

关键词： composite box train-gage method calibration test styling load equation

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