Introduction

Giurgiutiu, Victor

doi:10.1016/b978-0-12-409605-9.00001-5

Cited by 24 publications

(26 citation statements)

References 1 publication

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“…Commercial aircraft industry has moved in the direction of polymer composite materials, replacing metallic materials, to produce lighter, less part-count and more complex structures, allowing to reduce fuel consumption and carbon dioxide emissions and ultimately decrease costs [1], [2]. Further cost savings may be achieved by composite manufacture through liquid composite moulding (LCM) techniques, replacing autoclave manufacturing [2].…”

Section: Introductionmentioning

confidence: 99%

Small-diameter optical fibre sensor embedment for ambient temperature cure monitoring and residual strain evaluation of CFRP composite laminates produced by vacuum-assisted resin infusion

2021

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Out of autoclave (OoA) processing techniques, such as liquid composite moulding techniques (LCM) and, particularly, the vacuum assisted resin infusion (VARI) technique, are being used, with increasing success, in replacement of prepreg/autoclave technologies to produce structural aircraft/aerospace polymer composite parts, due to its better cost effectiveness and competitiveness. This work aims to embed Fibre Bragg grating (FBG) sensors to monitor the VARI manufacturing of carbon fibre reinforced polymer (CFRP) composites and evaluate the associated phenomena: ambient curing and post curing reactions and resulting residual strains. The curing kinetics of the epoxy resin system alone was initially studied through isothermal differential scanning calorimetry (DSC) tests and applying the isoconversional Friedman method, and further studied by strain monitoring during ambient curing and post curing resorting to FBG sensors. The FBG sensors in the CFRP laminates were able to detect a subtle increase of strain as infusion of the CFRP started and to measure decreasing strain as resin filled in the dry fabric layers. Subtle strain decrease revealed forming crosslink bonds. Compressive strains measured by the FBG sensors during post curing show that further crosslink takes place. A comparison of resultant residual strains was made between specimens with embedded FBG sensors on small-diameter optical fibres (SDOF) and on large-diameter optical fibres (LDOF).

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Section: Introductionmentioning

confidence: 99%

Small-diameter optical fibre sensor embedment for ambient temperature cure monitoring and residual strain evaluation of CFRP composite laminates produced by vacuum-assisted resin infusion

2021

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“…The Bell-Boeing V-22 Osprey uses 50% composites, whereas Boeing's C-17 contains 7,300kg of structural composites. (2) Boeing 787 and Airbus A350 are two examples of large commercial aircraft in which more than 50% of the structural weight (more than 80% by volume) are made from composites. (2)(3)(4) In particular, thermoplastic composites have recently gained more interest in the aerospace industry due to their potential for recycling, fast forming and weldability, improved fatigue performance, impact properties and fire/smoke/toxicity properties compared to thermoset composites.…”

Section: Introductionmentioning

confidence: 99%

“…(2) Boeing 787 and Airbus A350 are two examples of large commercial aircraft in which more than 50% of the structural weight (more than 80% by volume) are made from composites. (2)(3)(4) In particular, thermoplastic composites have recently gained more interest in the aerospace industry due to their potential for recycling, fast forming and weldability, improved fatigue performance, impact properties and fire/smoke/toxicity properties compared to thermoset composites. (5) Moreover, their potential for out-of-autoclave (OOA) processing make thermoplastic composites more appealing for low-cost and high-rate production.…”

Section: Introductionmentioning

confidence: 99%

Static test of a variable stiffness thermoplastic composite wingbox under shear, bending and torsion

et al. 2020

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Automated 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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“…4,5 Examples in literature utilizing Lamb waves to detect, localize, or quantify damage in composites are abundant. 6–11…”

Section: Introductionmentioning

confidence: 99%

A comparative convergence and accuracy study of composite guided-ultrasonic wave solution methods: Comparing the unified analytic method, SAFE method and DISPERSE

Barazanchy

Giurgiutiu

2017

Proceedings of the Institution of Mechanical Engineers, Part C:

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Multiple approaches and programs are available to the public to predict ultrasonic guided-wave propagation dispersion curves in a material. Each approach and program will have its own advantage and disadvantage making it suitable for a specific end use and less suitable for others. This manuscript aims to compare three different guided-ultrasonic wave dispersion curves retrieval methods for multiple cases. First a single layer of isotropic, unidirectional, orthotropic and monoclinic material is examined, followed by a multi-layer case (consisting of 10 layers of the aforementioned materials) and finally four different laminates and one sandwich laminate are evaluated. The goal of this manuscript is to give a concise overview of the advantages and limitations of each approach to assist the end user in choosing the right program to use.

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Introduction

Cited by 24 publications

References 1 publication

Small-diameter optical fibre sensor embedment for ambient temperature cure monitoring and residual strain evaluation of CFRP composite laminates produced by vacuum-assisted resin infusion

Small-diameter optical fibre sensor embedment for ambient temperature cure monitoring and residual strain evaluation of CFRP composite laminates produced by vacuum-assisted resin infusion

Static test of a variable stiffness thermoplastic composite wingbox under shear, bending and torsion

A comparative convergence and accuracy study of composite guided-ultrasonic wave solution methods: Comparing the unified analytic method, SAFE method and DISPERSE

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