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Interaction formulae for buckling and failure of orthotropic plates under combined axial compression/tension and shear

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Chinese Journal of aeronautics 2022年第3期35卷 272-280页

作者： Binwen WANG Xiangming CHEN Xiasheng SUN Puhui CHEN Zhe WANG Ya’nan CHAI Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of ChinaXi’an 710065China Chinese Aeronautical Establishment Beijing 100029China State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China

An interaction function was constructed based on the axial compression/tension and shear loads of orthotropic *** coefficients of the polynomial function were determined by uniaxial test *** interaction and failure interaction formulae under combined axial tension/compression and shear loads were *** on the uniaxial load test results of orthotropic plates,the buckling load and bearing capacity under any proportion of the combined loads could be predicted by using the proposed interaction *** buckling interaction curves and failure envelopes predicted by the proposed interaction formulae were in excellent agreement with the test results.

关键词： Buckling Combined loads Failure Interaction formulae Orthotropic plate

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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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Study on shear stability of composite stiffened panels based on digital image correlation method

Study on shear stability of composite stiffened panels based...

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2022 International Conference on Advanced Manufacturing technology and Manufacturing Systems, ICAMTMS 2022

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

ISBN: (纸本)9781510656840

Based on digital image correlation method (DIC), the shear stability of two configurations of composite stiffened plates was experimentally studied. The test results show that the buckling load and failure load of I-stiffened panels are 158.2 kN and 282.1 kN respectively, and the main failure models are the debonding of the truss skin interface and skin folding;the buckling load and failure load of M-stiffened panels are 181.9 kN and 292.3 kN respectively, and the main failure modes are consistent with that of T-stiffened panels. Then, a progressive damage failure model of stiffened panels was established to simulate the buckling and post-buckling behaviour. The results show that the buckling mode, buckling load, failure load and failure mode are consistent with the experimental results. © 2022 SPIE.

关键词： Image correlation

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

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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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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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Numerical Model and Simulation Analysis of Composite Stringer Docking structures

Numerical Model and Simulation Analysis of Composite Stringe...

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2019 International Conference on Advanced Material Research and Processing technology, AMRPT 2019

作者： Wei, Jingchao Wang, Gang Cao, Su Chen, Xiangming Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China Xi'an710065 China

Due to the manufacturing restrictions or design requirements, composite structures are usually connected in the form of butt joint near the wing rib or fuselage frame to solve the problem of discontinuity of load transfer. In this paper, the finite element model of butt joint structure is established by simulating the engineering model of metal fasteners and common joint connected by beam element under the action of in-plane load, and the mechanical simulation analysis of typical butt joint configuration is carried out. In the engineering model, the allowable stress value is used to predict the failure of composite material and the classical strength theory is used to predict the fracture failure of metal fasteners. The result show that the strength prediction obtained by the engineering model is in good agreement with the test results, and the application of this method can improve the calculation efficiency of connection strength with complicated multi-fastened composite structures. © 2019 Published under licence by IOP Publishing Ltd.

关键词： Numerical models

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Numerical Model and Simulation Analysis of Composite Stringer Docking structures

Numerical Model and Simulation Analysis of Composite Stringe...

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作者： Jingchao Wei Gang Wang Su Cao Xiangming Chen Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China

关键词： numerical model simulation analysis strength prediction composite structure

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Numerical Model and Simulation Analysis of Composite Stringer Docking structures

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IOP Conference Series: Materials science and Engineering 2019年第1期611卷

作者： Jingchao Wei Gang Wang Su Cao Xiangming Chen Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue Aircraft Strength Research Institute of China Xi'an 710065 China

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Model updating and uncertainty propagation in aerothermoelastic analysis for C/SiC panel of ceramic matrix composite 21

Model updating and uncertainty propagation in aerothermoelas...

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

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

ISBN: (数字)9781624104633

ISBN: (纸本)9781624104633

Hypersonic vehicles are exposed to a severe flight environment. The aerothermoelastic analysis of its components demands numerous simplifying approximations. Accurately establish the finite element model of the structure and quantifying the uncertainty in aerothermoelastic response for hypersonic aircraft structures is a significant challenge. The primary objective of this study is to propose a new thermal model updating and uncertainty quantification framework based on the Genetic Algorithm and p-box to propagate the effects of uncertainties on the performance of a C/SiC composite panel. The thermal conductivity of the material is expressed as a polynomial function of temperature, and the coefficients of the polynomial is updated for transient heat conduction analysis. The model updating method based on Genetic Algorithm are employed for thermal model validation. The results demonstrate that the model predictive precision can be significantly improved. Randomness associated with an uncertain input is modeled by Gaussian distributions. Finally, the uncertainty is propagated to the thermal flutter velocity. © 2017, American Institute of aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Hypersonic vehicles

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