Mechanical Behavior of a Fuselage Stiffened Carbon-Epoxy Panel under Debonding Load

Torres, Mauricio; Ea, Franco-Urquiza; Hernández-Moreno, Hilario; Ma, González-Villa

doi:10.4172/2168-9792.1000209

Cited by 3 publications

(3 citation statements)

References 12 publications

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“…The lack in the performance of the beam can be attributed to the intrinsic errors during the manufacturing process. As reported in literature [29], stiffened structure commonly fails at components interface. For woven composites, warp-weft sliding, fabric distortion and fiber decohesion are expected.…”

Section: Verification Of the Manufacturing Process Of The Aileron Maimentioning

confidence: 55%

Manufacturing Process of High Performance–Low Cost Composite Structures for Light Sport Aircrafts

Torres

Piedra

Ledesma³

et al. 2019

Aerospace

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This work describes the technological and scientific efforts on designing, manufacturing and testing validation for high performance-low cost composite structures for Light Sport Aircrafts (LSA). A Mexican initiative to conceive, manufacture and assembly a Light Sport Aircraft has been developed by using Computational Fluid Dynamics (CFD), Finite Element Analysis (FEA) and Liquid Composite Manufacturing (LCM). These consolidated techniques are used to characterize novel approaches to manufacturing and assembly carbon-fiber based structural components. As large structures are manufactured via Vacuum Assisted Resin Infusion (VARI), impregnation strategies are studied to minimize inner flaws and also to improve the manufacturing time and surface quality of each component. The first case of study, to validate this methodology, involves non-structural components such as the cowling. Control surfaces (ailerons, rudder, elevator and flaps) have been manufactured, each of them having common issues but also unique challenges. As an example, a second case of study, the aileron main beam is analyzed. Furthermore, test portfolio will be developed with the goal to perform 1-to-1 scale mechanical tests for validation in compliance with ASTM standards.

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Section: Verification Of the Manufacturing Process Of The Aileron Maimentioning

confidence: 55%

Manufacturing Process of High Performance–Low Cost Composite Structures for Light Sport Aircrafts

Torres

Piedra

Ledesma³

et al. 2019

Aerospace

View full text Add to dashboard Cite

show abstract

“…The aircraft interior panels are floor panels, roof panels, side panels, and cabin dividers [1,[6][7][8]. The requirements of the aircraft cabin interior panels present a good balance between strength, low density, high stiffness, and durability [9][10][11][12][13]. In addition, most panels require contoured forms, which lead to several defects induced during the manufacturing process.…”

Section: Introductionmentioning

confidence: 99%

Innovation in Aircraft Cabin Interior Panels. Part II: Technical Assessment on Replacing Glass Fiber with Thermoplastic Polymers and Panels Fabricated Using Vacuum Forming Process

et al. 2021

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The manufacturing process of the aircraft cabin interior panels is expensive and time-consuming, and the resulting panel requires rework due to damages that occurred during their fabrication. The aircraft interior panels must meet structural requirements; hence sandwich composites of a honeycomb core covered with two layers of pre-impregnated fiberglass skin are used. Flat sandwich composites are transformed into panels with complex shapes or geometries using the compression molding process, leading to advanced manufacturing challenges. Some aircraft interior panels are required for non-structural applications; hence sandwich composites can be substituted by cheaper alternative materials and transformed using disruptive manufacturing techniques. This paper evaluates the feasibility of replacing the honeycomb and fiberglass skin layers core with rigid polyurethane foams and thermoplastic polymers. The results show that the structural composites have higher mechanical performances than the proposed sandwich composites, but they are compatible with non-structural applications. Sandwich composite fabrication using the vacuum forming process is feasible for developing non-structural panels. This manufacturing technique is fast, easy, economical, and ecological as it uses recyclable materials. The vacuum forming also covers the entire panel, thus eliminating tapestries, paints, or finishes to the aircraft interior panels. The conclusion of the article describes the focus of future research.

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“…Other industries such as automobiles, trains, and components such as tanks or pressure vessels, require these materials with excellent mechanical properties [1]. The extraordinary characteristics of composite materials, also known as fiber-reinforced polymer (FRP) composites, provide new approaches in designing and fabricating complex structures [2][3][4][5]. These composites are already ingrained in current engineering, but research is still in its infancy.…”

Section: Introductionmentioning

confidence: 99%

Innovation in Aircraft Cabin Interior Panels Part I: Technical Assessment on Replacing the Honeycomb with Structural Foams and Evaluation of Optimal Curing of Prepreg Fiberglass

et al. 2021

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Sandwich composites are widely used in the manufacture of aircraft cabin interior panels for commercial aircraft, mainly due to the light weight of the composites and their high strength-to-weight ratio. Panels are used for floors, ceilings, kitchen walls, cabinets, seats, and cabin dividers. The honeycomb core of the panels is a very light structure that provides high rigidity, which is considerably increased with fiberglass face sheets. The panels are manufactured using the compression molding process, where the honeycomb core is crushed up to the desired thickness. The crushed core breaks fiberglass face sheets and causes other damage, so the panel must be reworked. Some damage is associated with excessive build-up of resin in localized areas, incomplete curing of the pre-impregnated fiberglass during the manufacturing process, and excessive temperature or residence time during the compression molding. This work evaluates the feasibility of using rigid polyurethane foams as a substitute for the honeycomb core. The thermal and viscoelastic behavior of the cured prepreg fiberglass under different manufacturing conditions is studied. The first part of this work presents the influence of the manufacturing parameters and the feasibility of using rigid foams in manufacturing flat panels oriented to non-structural applications. The conclusion of the article describes the focus of future research.

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Mechanical Behavior of a Fuselage Stiffened Carbon-Epoxy Panel under Debonding Load

Cited by 3 publications

References 12 publications

Manufacturing Process of High Performance–Low Cost Composite Structures for Light Sport Aircrafts

Manufacturing Process of High Performance–Low Cost Composite Structures for Light Sport Aircrafts

Innovation in Aircraft Cabin Interior Panels. Part II: Technical Assessment on Replacing Glass Fiber with Thermoplastic Polymers and Panels Fabricated Using Vacuum Forming Process

Innovation in Aircraft Cabin Interior Panels Part I: Technical Assessment on Replacing the Honeycomb with Structural Foams and Evaluation of Optimal Curing of Prepreg Fiberglass

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