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Статті в журналах з теми "Composite wingbox"

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Автор: Grafiati
Опубліковано: 10 грудня 2022
Оновлено: 28 січня 2023

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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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Анотація:
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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Анотація:
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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3

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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Анотація:
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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5

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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6

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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7

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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8

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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9

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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10

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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Анотація:
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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11

Marzani, Alessandro, Nicola Testoni, Luca De Marchi, Marco Messina, Ernesto Monaco, and Alfonso Apicella. "An open database for benchmarking guided waves structural health monitoring algorithms on a composite full-scale outer wing demonstrator." Structural Health Monitoring 19, no. 5 (November 28, 2019): 1524–41. http://dx.doi.org/10.1177/1475921719889029.

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Анотація:
This article reports on the creation of an open database of piezo-actuated and piezo-received guided wave signals propagating in a composite panel of a full-scale aeronautical structure. The composite panel closes the bottom part of a wingbox that, along with the leading edge, the trailing edge, and the wingtip, forms an outer wing demonstrator approximately 4.5 m long and from 1.2 to 2.3 m wide. To create the database, a structural health monitoring system, composed of a software/hardware central unit capable of controlling a network of 160 piezoelectric transducers secondarily bonded on the composite panel, has been realized. The structural health monitoring system has been designed to (1) perform electromechanical impedance measurement at each transducer, in order to check for their reliability and bonding strength, and (2) to operate an active guided wave screening for damage detection in the composite panel. Electromechanical impedance and guided wave measurements were performed at four different testing stages: before loading, before fatigue, before impacts, and after impacts. The database, freely available at http://shm.ing.unibo.it/ , can thus be used to benchmarking, on real-scale structural data, guided wave algorithms for loading, fatigue, as well as damage detection, characterization, and sizing. As an example, in this work, a delay and sum algorithm is applied on the post-impact data to illustrate how the database can be exploited.
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12

Giżyński, Maciej. "Effect of transverse reinforcement on cracking of CFRP composite laminates under static and fatigue loads." Journal of Composite Materials 54, no. 25 (April 21, 2020): 3755–66. http://dx.doi.org/10.1177/0021998320919801.

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Анотація:
Several CFRP laminates with various layups, possessing two distinctive forms of transverse reinforcement either UD 90° or fabric 0°/90°, were tested in both static and fatigue tests. All examined layups were considered to be used in the wingbox design of the multipurpose turboprop aircraft. In-situ microscopic observations were carried out during the tests. Static tensile tests allowed to find the strength of the laminas, stress, and strains at which cracks started to propagate, crack density during the test. The microscopic observations allowed to establish cracks’ growth paths. The first crack in laminates having fabric 0°/90° laminas usually was observed for higher stress and strain than in laminates with UD 90° laminas. Also, the later ones showed a tendency to significantly delaminate along the interface between UD 90° and UD 45° laminas. The fatigue test was carried out in order to find how to distinguish damage growth in both families of laminates that affects their fatigue life. As an outcome, S-N lines were determined. During the test the microscopic observations were made, which allowed to show crack and delamination growth during successive load cycles. The microscopic observations showed that cyclic loading leads to the fast growth of delaminations at the interface of fabric 0°/90°ply or UD 90° laminas.
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13

Koundouros, Michael, Brian G. Falzon, Costas Soutis, and Steven J. Lord. "Predicting the ultimate load of a CFRP wingbox." Composites Part A: Applied Science and Manufacturing 35, no. 7-8 (July 2004): 895–903. http://dx.doi.org/10.1016/j.compositesa.2004.01.016.

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14

Akbar, M., and J. L. Curiel-Sosa. "Implementation of multiphase piezoelectric composites energy harvester on aircraft wingbox structure with fuel saving evaluation." Composite Structures 202 (October 2018): 1000–1020. http://dx.doi.org/10.1016/j.compstruct.2018.05.020.

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15

Jariyah, Jariyah, Wicaksono L. A, and Septi N. D. "Corn Wingko Processing Optimization Using Response Surface Methodology." International Journal on Food, Agriculture and Natural Resources 1, no. 2 (December 20, 2020): 28–33. http://dx.doi.org/10.46676/ij-fanres.v1i2.19.

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Анотація:
Wingko is semi-wet food from Indonesia made from grated coconut, glutinous rice flour, sugar and other additives that form a distinctive taste and aroma. Utilization of corn in the form of flour aims to reduce the use of glutinous rice flour as the main composition of wingko because in addition to being an economic commodity, corn contains fiber which is useful for digestion. This study aims to determine the effect of the proportion of corn flour, sticky rice flour and tapioca on the physical and chemical properties of wingko. This study uses the Response Surface Methodology (RSM) method with the experimental design of the Central Composite Design (CCD) using 3 factors of 5 levels, namely the proportion of corn flour (43.18; 50; 60; 70; 76.82) (w / w), flour sticky rice (23,18; 30; 40; 50; 56,82) (w / w), tapioca flour (6,59; 10; 15; 20; 23,41) (w / w) are then processed using Design Expert software 7.1.5. The parameters observed were corn flour including water content, ash, starch, amylose, crude fiber and yield, in glutinous rice flour and tapioca including starch and amylose content, while in wingko products included water content, aw, starch, crude fiber and texture. The results showed that corn flour had a moisture content of 7.12%, ash 0.34%, starch 84.72%, amylose 21.22% of the total ingredients, crude fiber 1.15% and yield of 79.8%. Glutinous rice flour has a starch content of 81.98% and amylose 1.02% of the total ingredients while tapioca flour has a starch content of 78.71% and amylose 20.63% of the total ingredients. The optimum conditions of wingko products were obtained in the proportion of corn flour: sticky rice: tapioca 50:38:20 (w / w) with 23.46% moisture content, aw 0.881, starch content 50.87%, crude fiber 2.78% and texture 0.01194 mm / gs had desirability 0.831.
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16

Toffol, Francesco, and Sergio Ricci. "A Meta-Model for Composite Wingbox Sizing in Aircraft Conceptual Design." Composite Structures, December 2022, 116557. http://dx.doi.org/10.1016/j.compstruct.2022.116557.

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