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Relevant bibliographies by topics / Skin-Stringer

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Academic literature on the topic 'Skin-Stringer'

Author: Grafiati

Published: 4 June 2021

Last updated: 8 February 2022

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Journal articles on the topic "Skin-Stringer"

1

Li, Yi, and Sheng Nan Wang. "Study on the Damage Tolerance of a Stiffened Panel with a Skin Pad." Advanced Materials Research 33-37 (March 2008): 297–300. http://dx.doi.org/10.4028/www.scientific.net/amr.33-37.297.

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During the development of an aircraft structure design, designers draw out a skin-stringer panel with a skin pad on the basis of a conventional skin-stringer panel(skin is directly connected with stringer by rivets or there was a sheet betweeen skin and stringers) to reduce the manufacturing cost. In this paper, we calculated the SIF of three kinds of skin-stringer panels by FE. And then, we analyze the damage tolerance of these structures by fortran program. Especially we carried out a crack propagation experiment of a skin-stringer panel with a skin pad and compared it with the results of a

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2

Russo, Angela, Andrea Sellitto, Salvatore Saputo, Valerio Acanfora, and Aniello Riccio. "Cross-Influence between Intra-Laminar Damages and Fibre Bridging at the Skin–Stringer Interface in Stiffened Composite Panels under Compression." Materials 12, no. 11 (2019): 1856. http://dx.doi.org/10.3390/ma12111856.

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In this paper, the skin–stringer separation phenomenon that occurs in stiffened composite panels under compression is numerically studied. Since the mode I fracture toughness and, consequently, the skin–stringer separation can be influenced by the fibre bridging phenomenon at the skin–stringer interface, in this study, comparisons among three different material systems with different fibre bridging sensitivities have been carried out. Indeed, a reference material system has been compared, in terms of toughness performance, against two materials with different degrees of sensitivity to fibre br

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3

Castagnola, G., Antonio Squillace, M. Montuori, et al. "LBW of Similar and Dissimilar Skin-Stringer Joints Part II: Electrochemical Characterization." Advanced Materials Research 38 (March 2008): 320–34. http://dx.doi.org/10.4028/www.scientific.net/amr.38.320.

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The durability of metal structures depends most upon the corrosion behaviour of its materials as well as the on the electrochemical behaviour of joints and the technology employed to construct the joints itself. This work describes the effect of Laser Beam Welding (LBW) technology on the electrochemical and corrosion behaviour of parent materials and bead of several aluminium alloy joints. Investigation was carried out by using dc electrochemical techniques (open circuit potential monitoring, OCP, and anodic polarization) on selected micro areas of parent materials and bead by means of a suita

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4

Zhou, Guang, Xin Qi Yang, and Xiao Dong Xu. "Study on Mechanical Behaviors in Friction Stir Welding of 6061-T4 T-Joints." Advanced Materials Research 418-420 (December 2011): 1092–96. http://dx.doi.org/10.4028/www.scientific.net/amr.418-420.1092.

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Friction stir welding (FSW) of T-joints composed by 3mm thick 6061-T4 alloy was presented and the influences of process parameters on hardness profiles and tensile strength were discussed specifically. Two low hardness zones on the skin and one low hardness zone on the stringer were found. Tensile behaviors of T-joints were examined in two directions—in skin direction and in stringer direction. It was found that the tensile strength ranged from 170~180MPa for all specimens in the skin direction. And the specimens failed in heat affected zone (HAZ) corresponding to the lowest hardness. In the s

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5

Sellitto, Andrea, S. Della Corte, and Aniello Riccio. "Numerical Investigation of the Stringer Termination Debonding in Composite Stiffened Panels." Key Engineering Materials 713 (September 2016): 42–45. http://dx.doi.org/10.4028/www.scientific.net/kem.713.42.

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The purpose of this work is the numerical investigation of the stringer termination debonding in composite stiffened panels, subjected to a traction load. A parametric analysis has been carried out, considering the influence of the plies’ number and of the stringer width on the delamination initiation load as well as on the skin-stringer complete separation load.

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6

Masood, S. Nadeem, SR Viswamurthy, Arun Kumar Singh, M. Muthukumar, and Kotresh M. Gaddikeri. "Simulation and validation of disbond growth in co-cured composite skin–stringer specimens using cohesive elements." Journal of Composite Materials 52, no. 6 (2017): 807–22. http://dx.doi.org/10.1177/0021998317715505.

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Separation of skin and stringer is likely to be a failure mode in co-cured composites stiffened panels where there is considerable out-of-plane deformation. Such deformations are possible when a stiffened skin structure is loaded in compression/shear beyond buckling or in structures which contain a disbond/delamination at the skin–stringer interface. Prediction of damage initiation and progressive growth in numerical simulations require parameters such as interface fracture toughness which have to be obtained through specimen tests. Since interface toughness is generally mode dependent, this s

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7

Takeda, Nobuo, Y. Okabe, J. Kuwahara, Toshimichi Ogisu, and Seiji Kojima. "Damage Detection in CFRP Bonded Structures by Using Fiber Bragg Grating Sensors as Ultrasonic Wave Receivers." Key Engineering Materials 334-335 (March 2007): 1137–40. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.1137.

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The authors developed a damage detection system that generates ultrasonic waves with a piezo-ceramic actuator and receives them by a fiber Bragg grating (FBG) sensor. In this research, this system was applied to evaluate debonding progress in CFRP skin/stringer bonded structures. FBG sensors were bonded on the stringer or embedded in the adhesive layer. Then, ultrasonic wave at 300kHz was propagated through the debonded region, and the wavelet transform was applied to the received waveform. After that, a new damage indexand a correlation coefficient were calculated from the distribution of the

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8

Yang, Kun Yu, Hui Gan, and Hong Yi Qu. "Comparative Research on Damping Effects of Shock Absorders Relatively Made in Russian and China on the Fuel-Lubricating Oil Heat Exchanger of Aeroengine." Advanced Materials Research 791-793 (September 2013): 699–703. http://dx.doi.org/10.4028/www.scientific.net/amr.791-793.699.

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To enhance the strength of the skin-stringer structures for aircraft, comparative tests between single-pass and double-pass welding by friction stir welding (FSW) were implemented. 1.8mm 2524-T3 aluminum alloy was used as the skin and 2.4mm 7150-T77511 aluminum alloy was used as the stringer with equilateral right-angle structure, and perfect joints without internal defects were obtained. Moreover, the tensile, peel and metallographic tests were implemented, and the results show that the average peel strength of double-pass FSW is 2 times or more than single-pass FSW. Therefore double-pass FSW

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9

Dubé, M., P. Hubert, A. Yousefpour, and J. Denault. "Resistance welding of thermoplastic composites skin/stringer joints." Composites Part A: Applied Science and Manufacturing 38, no. 12 (2007): 2541–52. http://dx.doi.org/10.1016/j.compositesa.2007.07.014.

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10

Bai, Yujiao, Zhonghai Xu, Jieren Song, et al. "Experimental and numerical analyses of stiffened composite panels with delamination under a compressive load." Journal of Composite Materials 54, no. 9 (2019): 1197–216. http://dx.doi.org/10.1177/0021998319875209.

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L-shaped stiffened composite panels provide an efficient structure for engineering applications. However, they often produce delamination in the preparation and service process due to a series of factors. To study the effect of different types of delamination on the compressive strength of stiffened composite panels, ABAQUS finite element software was used in combine with the progressive damage subroutine user-defined field variable (USDFLD), and the finite element model was established based on cohesive theory to realize the prediction of the progressive failure process and strength of the st

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Dissertations / Theses on the topic "Skin-Stringer"

1

Rajamanickam, Rajkumar. "Study of delamination of composite hat skin stringer interface failure." Thesis, Blekinge Tekniska Högskola, Institutionen för maskinteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:bth-18837.

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The use of composite materials brought a tremendous breakthrough in the scientific world of aerospace engineering. The lack of understanding of the failure of composite materials can be disastrous. Composite laminated structures need to be thoroughly studied and investigated in the design stage. In this thesis, formed-hat skin stringer made of composite laminates is investigated. Delamination is the most common failure of laminated composites, which has two stages delamination onset and delamination propagation. In the preliminary design phase, firstly the structures need to be investigated fo

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2

Shi, Zhijun. "Predicting fatigue crack growth life in integral metallic skin-stringer panels." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7281.

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During the past few years, in comparison to traditional riveted structures, integral metallic skin stringer structures have played more and more important roles in aircraft design due to the fact they are economical and also have the ability to reduce weight. Their wide application in aircraft, especially large integral structures is limited because of the fact that they have shortcomings in damage tolerance performance. Hence, calculating the crack growth lives and improving the damage tolerance performance of integral structures by selecting appropriate materials or choosing rational structu

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3

Akterskaia, Margarita [Verfasser]. "Global-local progressive failure analysis of composite panels including skin-stringer debonding and intralaminar damage / Margarita Akterskaia." Hannover : Gottfried Wilhelm Leibniz Universität Hannover, 2019. http://d-nb.info/1193177200/34.

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Books on the topic "Skin-Stringer"

1

Kevin, O'Brien T., Minguet Pierre J, and Langley Research Center, eds. Fatigue debonding characterization in composite skin/stringer configurations. National Aeronautics and Space Administration, Langley Research Center, 1997.

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2

Ronald, Krueger, and Langley Research Center, eds. Fatigue life methodology for bonded composite skin/stringer configurations. National Aeronautics and Space Administration, Langley Research Center, 2001.

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3

Ronald, Krueger, and Langley Research Center, eds. Fatigue life methodology for bonded composite skin/stringer configurations. National Aeronautics and Space Administration, Langley Research Center, 2001.

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4

Ronald, Krueger, and Langley Research Center, eds. Testing and analysis of composite skin/stringer debonding under multi-axial loading. National Aeronautics and Space Administration, Langley Research Center, 1999.

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5

J, Minguet Pierre, O'Brien T. Kevin, and Langley Research Center, eds. A method for calculating strain energy release rates in preliminary design of composite skin/stringer debonding under multi-axial loading. National Aeronautics and Space Administration, Langley Research Center, 1999.

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6

A method for calculating strain energy release rates in preliminary design of composite skin/stringer debonding under multi-axial loading. National Aeronautics and Space Administration, Langley Research Center, 1999.

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Book chapters on the topic "Skin-Stringer"

1

Aldanondo, Egoitz, Ekaitz Arruti, Alberto Echeverria, and Iñaki Hurtado. "Friction Stir Welding of Lap Joints Using New Al–Li Alloys for Stringer-Skin Joints." In Friction Stir Welding and Processing X. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-05752-7_8.

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2

Milanoski, Dimitrios, Georgios Galanopoulos, Agnes Broer, Dimitrios Zarouchas, and Theodoros Loutas. "A Strain-Based Health Indicator for the SHM of Skin-to-Stringer Disbond Growth of Composite Stiffened Panels in Fatigue." In Lecture Notes in Civil Engineering. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-64594-6_61.

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3

Lynch, F., M. Price, A. Murphy, A. Gibson, K. Poston, and G. Moore. "Analysis of Weld Configuration for Laser Welded Skin-Stringer Fuselage Sub-Panels in Compression." In Thin-Walled Structures. CRC Press, 2018. http://dx.doi.org/10.1201/9781351077309-13.

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Conference papers on the topic "Skin-Stringer"

1

GALASSO, BERNARDINO, MONICA CIMINELLO, FRANCESCA MARIA PISANO, and ANTONIO CONCILIO. "Statistical Based Features Vector for Skin-stringer Debonding Detection." In Structural Health Monitoring 2017. DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/shm2017/13896.

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2

Young, R., C. Rose, and K. Starnes, Jr. "Skin, stringer, and fastener loads in buckled fuselage panels." In 19th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-1326.

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3

Okul, Aydin, and Ercan Gurses. "Development of Structural Neural Network Design Tool for Buckling Behaviour of Skin-Stringer Structures Under Combined Compression and Shear Loading." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-87970.

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Stiffened panels are commonly used in aircraft structures in order to resist high compression and shear forces with minimum total weight. Minimization of the weight is obtained by combining the optimum design parameters. The panel length, the stringer spacing, the skin thickness, the stringer section type and the stringer dimensions are some of the critical parameters which affect the global buckling allowable of the stiffened panel. The aim of this study is to develop a design tool and carry out a geometric optimization for panels having a large number of stringers. The panel length and the a

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4

KOOTTE, LUC, CHIARA BISAGNI, CARLOS DAVILA, and VIPUL RANATUNGA. "Study of Skin-Stringer Separation in Postbuckled Composite Aeronautical Structures." In American Society for Composites 2018. DEStech Publications, Inc., 2018. http://dx.doi.org/10.12783/asc33/26048.

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5

Curran, Richard, Alan Rothwell, and S. Castagne. "A Numerical Method for Cost-Weight Optimisation of Stringer-Skin Panels." In 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference. American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2018.

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6

SHERAFAT, MOHAMMAD, ROBIN GUITEL, NICOLAS QUAEGEBEUR, LARRY LESSARD, PASCAL HUBERT, and PATRICE MASSON. "Characterization of Guided Waves Propagation in a Composite Skin-stringer Assembly." In Structural Health Monitoring 2015. Destech Publications, 2015. http://dx.doi.org/10.12783/shm2015/227.

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7

COMTE-BELLOT, G., B. GAY, and C. FRANCO. "Vibration analysis of flat skin-stringer structures by the super matrix method." In 11th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2734.

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8

Kootte, Lucas, and Chiara Bisagni. "A Methodology to Investigate Skin-Stringer Separation in Postbuckled Composite Stiffened Panels." In AIAA Scitech 2020 Forum. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-0477.

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9

Kootte, Lucas, Chiara Bisagni, Vipul Ranatunga, Stephen B. Clay, Carlos G. Davila, and Cheryl A. Rose. "Effect of Composite Stiffened Panel Design on Skin-Stringer Separation in Postbuckling." In AIAA Scitech 2021 Forum. American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-0441.

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10

PISANO, FRANCESCA MARIA, MONICA CIMINELLO, FULVIO ROMANO, and UMBERTO MERCURIO. "Visual Analysis for PCA-based Skin-stringer Debonding of Composite Stiffened Panels." In Structural Health Monitoring 2019. DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/shm2019/32480.

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