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Relevant bibliographies by topics / Stiffened Composite Wing

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Journal articles

Academic literature on the topic 'Stiffened Composite Wing'

Author: Grafiati

Published: 6 September 2023

Last updated: 7 September 2023

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Journal articles on the topic "Stiffened Composite Wing"

1

Sahadevan, Vijay, Yoann Bonnefon, and Tim Edwards. "A Meta-Heuristic Based Weight Optimisation for Composite Wing Structural Analysis." Applied Mechanics and Materials 5-6 (October 2006): 305–14. http://dx.doi.org/10.4028/www.scientific.net/amm.5-6.305.

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This paper presents a two-stage meta-heuristic approach to producing weight-optimised solutions needed prior to the detailed finite element analysis of composite wing. Composite wing covers are assumed to take the form of a group of stiffened sub-panels with varying skin and stiffener geometries according to the wing layout and loads. A population of limited solutions satisfying various design constraints was created using layout (skin and stiffener geometry), selected lay-ups, rule based stacking sequence and various assumed loads. The closed form analytical solutions of flat stiffened orthot

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2

Butler, R. "Optimum design of composite stiffened wing panels — a parametric study." Aeronautical Journal 99, no. 985 (1995): 169–77. http://dx.doi.org/10.1017/s0001924000028335.

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AbstractThe program VICONOPT is used to find the optimum (least mass) dimensions of a range of stiffened wing panels which are subject to buckling and material strength constraints and are loaded in axial compression with a sinusoidal manufacturing imperfection. Design plots are presented to show the effects that various rib spacings and stiffener types have on optimum design mass. A simplified model of a complete wing box is used to illustrate the design of a full wing panel and plots of optimum values of design variables at various stations along the wing have been obtained. The results were

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3

Liu, Tie Jun, Yong Zhang, Gang Li, and Feng Hui Wang. "Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer." Applied Mechanics and Materials 105-107 (September 2011): 491–94. http://dx.doi.org/10.4028/www.scientific.net/amm.105-107.491.

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In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are low

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4

Hwu, Chyanbin, and Z. S. Tsai. "Aeroelastic Divergence of Stiffened Composite Multicell Wing Structures." Journal of Aircraft 39, no. 2 (2002): 242–51. http://dx.doi.org/10.2514/2.2945.

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5

Bhowmik, Krishnendu, Shamim Akhtar, Raj Kumar Kalshyan, Niloy Khutia, and Amit Roy Choudhury. "CNT Reinforced Laminated Composite under In-Plane Tensile Loading: A Finite Element Study." Materials Science Forum 978 (February 2020): 323–29. http://dx.doi.org/10.4028/www.scientific.net/msf.978.323.

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The present study is mainly aimed at investigating the distribution of in-plane stresses of a rectangular plate under localized uniform in-plane tensile loading through finite element analysis. The configuration used in the analysis is analogous to the case of premature failure of stiffened panel due to the termination of a stiffener in aircraft wing structure. In this current work, three different types of materials namely, isotropic, plain woven and transversely isotropic materials are being considered. Aluminium is taken as isotropic; high strength carbon/epoxy is being assigned as plain wo

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6

KATO, Yoko, Ning HU, Masaki KAMEYAMA, and Hisao FUKUNAGA. "Optimum Design of Composite Wing Considering Stiffened Panel Buckling." Proceedings of Conference of Tohoku Branch 2002.37 (2002): 208–9. http://dx.doi.org/10.1299/jsmeth.2002.37.208.

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7

KATO, Yoko, Masaki KAMEYAMA, Ning HU, and Hisao FUKUNAGA. "Optimum Design of Composite Wing Considering Stiffened Panel Buckling." Transactions of the Japan Society of Mechanical Engineers Series A 70, no. 691 (2004): 479–86. http://dx.doi.org/10.1299/kikaia.70.479.

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8

Yang, Xue-Yong, and Jun Xiao. "Research Progress on Analytical and Numerical Prediction of Curing Deformation in Thermoset for Large Composite Parts." Science of Advanced Materials 14, no. 4 (2022): 669–81. http://dx.doi.org/10.1166/sam.2022.4247.

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Solidification deformation will produce certain drawbacks, so that a composite material part may not meet the requirements of a stress-free assembly for a modern aircraft. This issue holds particularly in the composite material part of large aircrafts. To predict and control this deformation, a novel method is applied for shifting the relaxation times of the composite based on its temperature and degree of cure. The choice of a suitable material model to simulate induced distortions is important to achieve the right-first-time approach. This work investigates the ability of the multi-physics m

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9

Romano, Fulvio, Monica Ciminello, Assunta Sorrentino, and Umberto Mercurio. "Application of structural health monitoring techniques to composite wing panels." Journal of Composite Materials 53, no. 25 (2019): 3515–33. http://dx.doi.org/10.1177/0021998319843333.

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This detailed study proposes a structural health monitoring system which enables the identification, localisation, and correct measurement analysis, in relation to the damage and debonding induced by low energy impacts within aircraft composite wing panels. The said system has been envisaged as an offline system which aims to be considered as a valid alternative method in relation to the current first two maintenance approach levels: visual inspection, which is to be followed if necessary by ultrasonic scanning techniques. The architecture includes two different technologies which act at diffe

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10

De Angelis, Giovanni, Michele Meo, D. P. Almond, S. G. Pickering, and U. Polimeno. "Impact Damage Detection in a Stiffened Composite Wing Panel Using Digital Shearography and Thermosonics." Key Engineering Materials 471-472 (February 2011): 904–9. http://dx.doi.org/10.4028/www.scientific.net/kem.471-472.904.

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There has been a growing interest in the use of composites especially in structural application ranging from aerospace to automotive and marine sectors. However, their performances under impact loading represent one of the major concerns as impacts may occur during manufacture, normal operations and maintenance. This paper presents two novel NDT techniques, thermosonics and digital shearography (DISH) to detect and assess barely visible impact damage (BVID) produced on a stiffened composite wing panel by unknown low energy impacts. Thermosonics is based on synchronized infrared imaging and ult

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