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Relevant bibliographies by topics / Composite wingbox

Academic literature on the topic 'Composite wingbox'

Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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Dissertations / Theses
Book chapters
Conference papers

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Journal articles on the topic "Composite wingbox"

1

Zucco, G., V. Oliveri, M. Rouhi, R. Telford, G. Clancy, C. McHale, R. O’Higgins, T. M. Young, P. M. Weaver, and D. Peeters. "Static test of a variable stiffness thermoplastic composite wingbox under shear, bending and torsion." Aeronautical Journal 124, no. 1275 (January 22, 2020): 635–66. http://dx.doi.org/10.1017/aer.2019.161.

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AbstractAutomated manufacturing of thermoplastic composites has found increased interest in aerospace applications over the past three decades because of its great potential in low-cost, high rate, repeatable production of high performance composite structures. Experimental validation is a key element in the development of structures made using this emerging technology. In this work, a $750\times640\times240$ mm variable-stiffness unitised integrated-stiffener out-of-autoclave thermoplastic composite wingbox is tested for a combined shear-bending-torsion induced buckling load. The wingbox is manufactured by in-situ consolidation using a laser-assisted automated tape placement technique. It is made and tested as a demonstrator section located at 85% of the wing semi-span of a B-737/A320 sized aircraft. A bespoke in-house test rig and two aluminium dummy wingboxes are also designed and manufactured for testing the wingbox assembly which spans more than 3m. Prior to testing, the wingbox assembly and the test rig were analysed using a high fidelity finite element method to minimise the failure risk due to the applied load case. The experimental test results of the wingbox are also compared with the predictions made by a numerical study performed by nonlinear finite element analysis showing less than 5% difference in load-displacement behaviour and buckling load and full agreement in predicting the buckling mode shape.

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2

Wang, Hua, and Jun Liu. "Tolerance simulation of composite wingbox assembly considering preloading-modified distribution." Assembly Automation 36, no. 3 (August 1, 2016): 224–32. http://dx.doi.org/10.1108/aa-08-2015-067.

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Purpose Tolerance simulation’s reliability depends on the concordance between the input probability distribution and the real variation. The prescribed clamp force introduced changes in parts’ variation, which should be reflected in the input probability distribution for the tolerance simulation. The paper aims to present a tolerance analysis process of the composite wingbox assembly considering the preloading-modified distribution and especially focuses on the spring-in deviation of the thin-walled C-section composite beam (TC2B). Design/methodology/approach Based on finite element analysis model of TC2B, the preloading-modified probability distribution function (PDF) of the spring-in deviation is obtained. Thickness variations of the TC2B are obtained from the data of the downscaled composite wingbox. These variations are input to the computer-aided tolerance tools, and the final assembly variations are obtained. The assembly of the downscaled wingbox illustrates the effect of preloading on the probability distribution of the spring-in deviation. Findings The results have shown that the final assembly variations estimated with the modified probability distribution is more reliable than the variation of the initial normal distribution. Originality/value The tolerance simulation work presented in the paper will enhance the understanding of the composite parts assembling with spring-in deviations, improve the chance to choose assembling processes that allow specifications to be met and help with tolerance allocation in composites assembly.

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Chen, Huan Guo, Yun Ju Yan, and Jie Sheng Jiang. "Vibration-Based Damage Detection of Composite Wingbox Structures Using Improved Hilbert-Huang Transform." Key Engineering Materials 324-325 (November 2006): 539–42. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.539.

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A vibration-based approach to detect crack damage in a cantilever composite wingbox is studied using the improved Hilbert-Huang Transform (HHT). The improved HHT is composed of HHT with Wavelet Packet Transform (WPT) and a simple but effective method for intrinsic mode function (IMF) selection. For different damage status, in order to obtain structural dynamic responses, which imply plentiful damage information, the composite wing boxes were excited by a contrived square wave signal. Then, the dynamic responses of intact wingbox and damaged wingbox are disposed using improved HHT. Finally, a feature index vector of structural damage, i.e. the ariation quantity of instantaneous energy, is constructed. The obtained results show that the proposed damage feature index vector is more sensitive to small damage than those in traditional signal processing.

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4

Grondel, S., J. Assaad, C. Delebarre, and E. Moulin. "Health monitoring of a composite wingbox structure." Ultrasonics 42, no. 1-9 (April 2004): 819–24. http://dx.doi.org/10.1016/j.ultras.2004.01.058.

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Chen, H. G., Y. J. Yan, and J. S. Jiang. "Vibration-based damage detection in composite wingbox structures by HHT." Mechanical Systems and Signal Processing 21, no. 1 (January 2007): 307–21. http://dx.doi.org/10.1016/j.ymssp.2006.03.013.

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Guerrero, José M., Aravind Sasikumar, Jordi Llobet, and Josep Costa. "Testing and simulation of a composite-aluminium wingbox subcomponent subjected to thermal loading." Composite Structures 296 (September 2022): 115887. http://dx.doi.org/10.1016/j.compstruct.2022.115887.

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Akbar, M., and J. L. Curiel-Sosa. "Piezoelectric energy harvester composite under dynamic bending with implementation to aircraft wingbox structure." Composite Structures 153 (October 2016): 193–203. http://dx.doi.org/10.1016/j.compstruct.2016.06.010.

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Chen, H. G., Y. J. Yan, W. H. Chen, J. S. Jiang, L. Yu, and Z. Y. Wu. "Early Damage Detection in Composite Wingbox Structures using Hilbert-Huang Transform and Genetic Algorithm." Structural Health Monitoring: An International Journal 6, no. 4 (December 2007): 281–97. http://dx.doi.org/10.1177/1475921707081970.

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Liguori, Francesco S., Giovanni Zucco, Antonio Madeo, Domenico Magisano, Leonardo Leonetti, Giovanni Garcea, and Paul M. Weaver. "Postbuckling optimisation of a variable angle tow composite wingbox using a multi-modal Koiter approach." Thin-Walled Structures 138 (May 2019): 183–98. http://dx.doi.org/10.1016/j.tws.2019.01.035.

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Yan, Yun Ju, Huan Guo Chen, and Jie Sheng Jiang. "Optimal Placement of Sensors for Damage Characterization Using Genetic Algorithms." Key Engineering Materials 334-335 (March 2007): 1033–36. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.1033.

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Sensor data are the basis for health assessment of complex structural systems. Careful selection and logical layout of sensors is critical to enable the high reliability of system health assessment. This paper presents a methodology how to use a minimum number of sensors, and what locations of them should be placed, so that the voltage signals received from the sensor can be used to detect both presence and extent of damage. In this study, an optimization procedure is developed using Genetic Algorithm (GA) to determine the location of piezoelectric sensor for damage detection in a composite wingbox. A new damage index using all differences in voltage signals decomposed by wavelet transform is proposed. Results show that the proposed method is available at determining number and location of sensors for structural damage detection using piezoelectric patch sensors.

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Dissertations / Theses on the topic "Composite wingbox"

1

Arsenyeva, Anna [Verfasser]. "Level-dependent Optimization Methods for Metal and Composite Wingbox Structures / Anna Arsenyeva." Düren : Shaker, 2020. http://d-nb.info/1206855622/34.

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Book chapters on the topic "Composite wingbox"

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Chen, Huan Guo, Yun Ju Yan, and Jie Sheng Jiang. "Vibration-Based Damage Detection of Composite Wingbox Structures Using Improved Hilbert-Huang Transform." In Fracture and Damage Mechanics V, 539–42. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-413-8.539.

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Conference papers on the topic "Composite wingbox"

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OLIVERI, VINCENZO, GIOVANNI ZUCCO, MOHAMMAD ROUHI, ENZO COSENTINO, RONAN O’HIGGINS, TREVOR M. YOUNG, and PAUL M. WEAVER. "DESIGN AND ANALYSIS OF AN INTEGRATED THREE- BAY THERMOPLASTIC COMPOSITE WINGBOX." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35766.

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The design of a multi-part aerospace structural component, such as a wingbox, is a challenging process because of the complexity arising from assembly and integration, and their associated limitations and considerations. In this study, a design process of a stiffeners-integrated variable stiffness three-bay wingbox is presented. The wingbox has been designed for a prescribed buckling and post-buckling performance (a prescribed real testing scenario) and made from thermoplastic composite material system (Carbon-PEEK) with the total length of three meters. The stiffeners and spars are integrated into the top and bottom panels of the wingbox resulting a single-piece blended structure with no fasteners or joints. The bottom skin also has an elliptical cut-out for access purposes. The composite tows are steered around this cutout for strain concentration reduction purposes. The fiber/tow steering in the top skin bays (compression side) has also been considered for improved compression-induced buckling load carrying capacity. The proposed design has been virtually verified via high fidelity finite element analysis.

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Priest, Drew, Christopher Floyd, Matthew P. Snyder, Hank Pyzdrowski, and Matthew B. Obenchain. "Design, Manufacturing and Testing of a Composite Wingbox." In AIAA SCITECH 2022 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-1629.

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De Baets, Peter, Dimitri Mavris, and Rupinder Battoo. "Aeroelastic analysis of a composite wingbox with varying root flexibility." In 41st Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-1623.

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4

Jiang, Jinshou, Huanguo Chen, Jianmin Li, Wenhua Chen, and Leitao Zhang. "Lifting scheme wavelet transform based damage detection of composite wingbox structures." In 2010 3rd International Congress on Image and Signal Processing (CISP). IEEE, 2010. http://dx.doi.org/10.1109/cisp.2010.5648111.

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Wang, Hua, and Jun Liu. "Tolerance Simulation of Thin-Walled C-Section Composite Beam in Wingbox Assembly Under Preloading." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-50273.

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Tolerance simulation’s reliability depends on the concordance between the input probability distribution and the practical situation. Pre-loading induced changes in the probability distribution should be considered in the structure’s tolerance simulation, especially for composite structures. The paper presents a tolerance simulation method for the thin-walled C-section composite beam (TC2B) assembling under preloading, that is prescribed clamping force. Based on FEA model of TC2B, the preloading-modified probability distribution function of the R angle spring-in deviation is proposed. Thickness variations of the TC2B are obtained from the data of the downscaled composite wingbox. These parts’ variations are input to the tolerance simulation software, and the final assembly variations are obtained. The assembly of the downscaled wingbox illustrates the effect of preloading on the probability distribution of the R angle spring-in deviation. The results have shown that tolerance simulation with the modified probability distribution is more accurate than the initial normal distribution. The tolerance simulation work presented in the paper will enhance the understanding of the composite parts assembling with spring-in deviations, and help systematically improving the precision control efficiency in civil aircraft industry.

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6

Zucco, Giovanni, Vincenzo Oliveri, Daniël Peeters, Robert Telford, Gearóid J. Clancy, Ciaran McHale, Mohammad Rouhi, Ronan O'Higgins, Trevor M. Young, and Paul M. Weaver. "Static Test of a Thermoplastic Composite Wingbox Under Shear and Bending Moment." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0482.

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Zucco, Giovanni, Vincenzo Oliveri, Daniël Peeters, Robert Telford, Gearóid J. Clancy, Ciaran McHale, Mohammad Rouhi, Ronan O'Higgins, Trevor M. Young, and Paul M. Weaver. "Correction: Static Test of a Thermoplastic Composite Wingbox Under Shear and Bending Moment." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0482.c1.

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Oliveri, Vincenzo, Giovanni Zucco, Mohammad Rouhi, Enzo Cosentino, Trevor Young, Ronan O'Higgins, and Paul Weaver. "Design of a unitized thermoplastic composite out-of-autoclave three-bay wingbox demonstrator." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-0919.

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OLIVERI, VINCENZO, GIOVANNI ZUCCO, DANIËL PEETERS, GEARÒID CLANCY, ROBERT TELFORD, MOHAMMAD ROUHI, CIARÀN MCHALE, RONAN M. O’HIGGINS, TREVOR M. YOUNG, and PAUL M. WEAVER. "Design, Manufacturing and Testing of an In-situ Consolidated Variable Stiffness Thermoplastic Composite Wingbox for Bending and Torsion." In American Society for Composites 2019. Lancaster, PA: DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/asc34/31332.

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ZUCCO, GIOVANNI, MOHAMMAD ROUHI, OLIVERI VINCENZO, ENZO COSENTINO, RONAN O’HIGGINS, and PAUL M. WEAVER. "DESIGN OF A COMPOSITE PANEL WITH CONTINUOUS TOW STEERING AROUND AN ELLIPTICAL CUT-OUT." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35768.

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Cut-outs are inevitable in many structural components such as in aircrafts to accommodate windows or openings for access purposes or fasteners. Engineers usually view cut-outs, especially in primary structures, with disfavour as they result in stress/strain concentration and consequently reduced load carrying capability. Local reinforcements usually increase cost and weight to the overall design which is not favourable in aerospace applications. In case of composite panels, emerging advanced manufacturing methods such as 3D printing of automated fiber placement made it possible to continuously steer fibers/tows around a cut-out to potentially alleviate stress/strain concentration problem. Another advantage of tow steering in this case is maintaining the continuity of fiber/tow paths without any fiber cut which precludes ply-level, 3D stress/strain concentration which could otherwise lead to delaminationinduced damage. In this study, potential capability of tow steering around an elliptical cut-out (manhole) in reducing stress/strain concentration in a composite wingbox is investigated Buckling response under compression loading together with stress and strain concentrations under both tensile and compression loads are examined. Under tensile loading, the maximum stress and strain concentration factors around the cut-out in the straight fiber design are shown to be approximately 29% and 32% larger than its counterpart with steered tows around the cut-out. For the compression loading condition, the direct strain of the panel with straight fiber orientations was found to be three times that of steered fiber trajectories in the vicinity of the cut-out.

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