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Spatial motion aircraft lift-rising structure fatigue life verification method with coupled multiparameter

Hangkong Dongli Xuebao/Journal of Aerospace Power 2025年第5期40卷

作者： Wang, Yupeng He, Qian Xia, Feng Xu, Fei Song, Pengfei Zhang, Chao National Key Laboratory of Strength and Structural Integrity Aircraft Strength Research Institute Xi’an710068 China Key Laboratory of Aviation Science and Technology on Full Scale Aircraft Structure Static and Fatigue Strength Aircraft Strength Research Institute Xi’an710068 China College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Nanjing210016 China

A structure fatigue life verification method for large aircraft lift-rising components was presented considering the spatial complex motion flap, the real-time direction of the load, multisystem and multiparameter cooperation control and system operation security. A spatial trajectory simulation method based on differential flatness theory was employed to ensure accurate real-time load direction during the flap unfixed-axis rotation. A velocity optimization model of following mechanism and a sequential control method were built to realize multiparameter accurate and dynamic cooperative control. To ensure the operation security of test system, a linkage protection mechanism combined with a communication monitoring method based on high-frequency polling pattern were established for abnormal condition of coupled test system. A spatial motion aircraft lift-rising structure life verification method with coupled multiparameter was established based on accurate load of spatial complex motion flap, multisystem and multiparameter cooperative control and complicated system security protection and the method was validated by a large transport aircraft flap fatigue test. The result showed that the maximum angle error of the load was 1.8°, relative dynamic error of the load was 2.69%, response time of subsystem security protection was 18 ms. The method can meet the requirements of flap fatigue life verification in load accuracy and system operation security protection, and provide a technical support for major project. The method can also provide referential technologies for motion mechanism fatigue life and reliability verification. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Flight paths

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Buckling and Post-buckling Analysis of Composite Hat Stiffened Panels under Axial Compression Loads

Buckling and Post-buckling Analysis of Composite Hat Stiffen...

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2022 International Conference on Aerospace and Control Engineering, ICoACE 2022

作者： Wang, Zhe Wang, Binwen Bao, Rui Chen, Xiangming Liang, Qingxianglong Yu, Fei School of Aeronautic Science and Engineering Beihang University Beijing China Aeronautics Science and Technology Key Laboratory of Full-Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China Shaanxi Xi'an China

Owing to their unique material design-ability and excellent weight reduction properties of carbon fibre reinforced polymers(CFRP), commercial aircraft OEMs have been innovating design and manufacturing approaches to wider the application of advanced composites. In this paper, the bearing capacity of composite hat-stiffened panels is determined by an improved engineering calculation method and numerical analysis method. The effectiveness of both methods is verified by the test. The advantage of the engineering estimation method is simple and fast, which is suitable for the parametric analysis of the structure in the preliminary design phase. The finite element method can better simulate the test process and is suitable for the comprehensive evaluation of structural strength. The combination of the two methods has a high reference value for rapid design and selection. © Published under licence by IOP Publishing Ltd.

关键词： Numerical methods

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An improved engineering method for bearing capacity calculation of stiffened curved composite panels 8

An improved engineering method for bearing capacity calculat...

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2022 8th International Conference on Applied Materials and Manufacturing technology, ICAMMT 2022

作者： Wang, Zhe Chen, Xiangming Li, Xinxiang Zou, Peng Yang, Junchao Bi, Xue Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China Shaanxi Xi'an China

The application of composite materials in the primary structures of large aircraft fuselage is a development trend in recent years. As an indispensable structure in design and structure selection, accurate and efficient evaluation of its performance is of great significance to reduce the research cost. In this paper, the bearing capacity of stiffened curved composite panel is calculated through an improved engineering calculation method, and the effectiveness of the method is verified by test, which provides technical support for the rapidly design and selection of stiffened curved composite panels. © Published under licence by IOP Publishing Ltd.

关键词： Bearing capacity

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Application Of Acoustic Emission Technique On Strength Test Of Composite Fuselage Ring

Application Of Acoustic Emission Technique On Strength Test ...

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SPAWDA Symposium on Piezoelectricity, Acoustic Waves, and Device Applications

作者： Yuan-Da Ma Qian Wang Lian-Jie Pei Jian-Feng Zhang Aviation Key Laboratory of Science and Technology on Full-Scale Aircraft Structure Static and Fatigue Strength Aircraft Strength Research Institute of China Xi'an China

ISBN: (纸本)9798350320817

The process of initiation expansion and destruction of damage is discussed by acoustic emission technique. Besides, analysis of damage’s evolution process, the type of damage and characteristics of acoustic emission signal are stated in this paper. The result can provide damage forecast for strength test of composite material structure and contribute to development of acoustic emission technique.

关键词： Composite materials Deformation Acoustic emission Piezoelectricity aircraft manufacture aircraft Monitoring

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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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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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Design and Implementation of Massive Test Metrical Information Management System in static Structural Test of aircraft

Design and Implementation of Massive Test Metrical Informati...

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2013 IEEE 11th International Conference on Electronic Measurement & Instruments

作者： Zuo Jia Zhang Jianfeng He Qian Full scale aircraft static/fatigue structure aviation science and technology key laboratory Aircraft Strength Research Institute of China

ISBN: (纸本)9781479907571

A massive test metrical information management system was designed and implemented,against the characteristic of massive test metrical information and the present status of lack of governing. The development platform for the system is Delphi 7.0,which is combined with Microsoft SQL Server 2000 database,and the Client/Server (c/s) structure was applied. In order to implement all functions of the system,firstly,function requirements analysis and division of functional module were performed;and then database modeling was executed;finally,the database structure and their applications were designed. The application of the system in practice proves that management system is an effective,accurate and convenient tool for mass test information management and processing,with which the productivity effect can be significantly improved.

关键词： Massive metrical information, Database, Management system, Delphi

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