Analysis of the non-isothermal resin impregnation process of carbon fibre reinforced composite wing spar structure

AbstractThe paper discusses the problem of possibility of the detecting surface defects in carbon fibre reinforced plastics (CFRP) materials on the basis of the milling time series. First, the special defects in the hole-shaped with various depth were made. Next, the cutting forces are measured during the milling machining. Finally, the recurrence plot and quantification analysis was applied. The obtained results show that the depth defect influences the selected recurrence quantifications, which can be used as the simple defect indicators. The conducted research allow to determine the percentage share of the detectable defects. The novelty of the work and an unresolved problem is the selection of recurrence quantifications with the simultaneous use of them to detect the size of defects in carbon fibre reinforced plastics.

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Carbon fibre reinforced composite waste: An environmental assessment of recycling, energy recovery and landfilling

Composites Part A Applied Science and Manufacturing ◽

10.1016/j.compositesa.2013.02.009 ◽

2013 ◽

Vol 49 ◽

pp. 89-99 ◽

Cited By ~ 125

Author(s):

Robert A. Witik ◽

Remy Teuscher ◽

Véronique Michaud ◽

Christian Ludwig ◽

Jan-Anders E. Månson

Keyword(s):

Carbon Fibre ◽

Environmental Assessment ◽

Energy Recovery ◽

Reinforced Composite

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Structural Optimization Design of an Aircraft Metal-Composite Wing

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.341-342.519 ◽

2013 ◽

Vol 341-342 ◽

pp. 519-523

Author(s):

Ya Hui Zhang ◽

Ji Hong Zhu ◽

Jun Shuo Li ◽

Wei Hong Zhang

Keyword(s):

Structural Optimization ◽

Optimization Design ◽

Optimization Method ◽

Design Solution ◽

Metal Composite ◽

Concept Design ◽

Obvious Effect ◽

Reinforced Composite ◽

Three Phase ◽

Composite Wing

The problem of metal-composite wing structural optimization is discussed and a strategy is presented. Topology optimization method is applied to provide load transferring path of structure for concept design. Size, shape and other optimization method are used to provide detailed design for individual components. A three-phase optimization method is discussed for fiber reinforced composite laminate skin. Optimal parameters include ply angle, percentage, thickness, layer shape and sequence. The design of laminate for ease of manufacture is based on a set of manufacturing constraints. This paper deals with a total optimal design solution for aileron structure of an aircraft. The result satisfies all the requirements of strength and stability, and has obvious effect of weight loss.

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Biaxial test results for strength and deformation of a range of E-glass and carbon fibre reinforced composite laminates

Failure Criteria in Fibre-Reinforced-Polymer Composites ◽

10.1016/b978-008044475-8/50004-4 ◽

2004 ◽

pp. 52-96 ◽

Cited By ~ 6

Author(s):

P.D. Soden ◽

M.J. Hinton ◽

A.S. Kaddour

Keyword(s):

Carbon Fibre ◽

Composite Laminates ◽

Biaxial Test ◽

Test Results ◽

Reinforced Composite ◽

Strength And Deformation

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Damage Development in Carbon Fibre Reinforced Composite Laminates under Compressive Static and Fatigue Loading

Developments in the Science and Technology of Composite Materials ◽

10.1007/978-94-009-1123-9_69 ◽

1989 ◽

pp. 501-507

Author(s):

K. Schulte ◽

J. J. Masson

Keyword(s):

Carbon Fibre ◽

Composite Laminates ◽

Fatigue Loading ◽

Damage Development ◽

Reinforced Composite

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Experimental Analysis for the Effect of Impactor Geometry on Carbon Reinforced Composite Materials

Polymers and Polymer Composites ◽

10.1177/096739111702500905 ◽

2017 ◽

Vol 25 (9) ◽

pp. 677-682 ◽

Cited By ~ 2

Author(s):

Faruk Elaldi ◽

Busra Baykan ◽

Can Akto

Keyword(s):

Composite Materials ◽

Carbon Fibre ◽

Composite Plates ◽

High Strength ◽

Low Velocity Impact ◽

Low Velocity ◽

Damage Area ◽

Reinforced Composite ◽

Contact Surfaces ◽

The Impact

For the last three decades, composites have become very preferable materials to be used in the automotive industry, structural parts of aircraft and military systems and spacecraft, due to their high strength and modulus. Composite materials are sometimes exposed to invisible or visible damage due to impact loading during their service life. In this study, the effect of impactor geometry with four different contact surfaces on woven carbon fibre-reinforced composite plates having three different thicknesses are investigated. In the first stage, composite plates were manufactured with the ply orientations of [45/-45/0/90/45/-45]2s, [45/-45/0/90/45/-45]3s, [45/-45/0/90/45/-45]4s based on conventional usage. In the second stage, carbon fibre-reinforced composite test panels were exposed to low velocity impact tests to obtain force-time, energy-time and force-displacement curves. Finally, semi and full penetration of composite panels and damage magnitude were determined. It was found that the impactor geometries with lower contact surfaces such as conical and ogive types were much more penetrative on composite plates than the other geometries, but they caused larger damage area in the vicinity of the impact point.

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