Composite wing structure of light amphibious airplane design, optimization, and experimental testing

Chinvorarat, Sinchai

doi:10.1016/j.heliyon.2021.e08410

Cited by 13 publications

(2 citation statements)

References 22 publications

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“…They fabricated radome structure by using kenaf/glass reinforced epoxy through hand-layup techniques. They studied hybrid composite structures and discovered that kenaf/glass hybrid composites had a lot of promise to replace metal radomes [ 183 ]. In addition, the metallic impeller fan blades are instead fabricated with glass fibre reinforced plastics (GFRP).…”

Section: Applicationsmentioning

confidence: 99%

Physical, Mechanical and Perforation Resistance of Natural-Synthetic Fiber Interply Laminate Hybrid Composites

et al. 2022

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Natural and synthetic fibres have emerged in high demand due to their excellent properties. Natural fibres have good mechanical properties and are less expensive, making them a viable substitute for synthetic fibers. Owing to certain drawbacks such as their inconsistent quality and hydrophilic nature, researchers focused on incorporating these two fibres as an alternative to improve the limitations of the single fibre. This review focused on the interply hybridisation of natural and synthetic fibres into composites. Natural fibres and their classifications are discussed. The physical and mechanical properties of these hybrid composites have also been included. A full discussion of the mechanical properties of natural/synthetic fibre hybrid composites such as tensile, flexural, impact, and perforation resistance, as well as their failure modes, is highlighted. Furthermore, the applications and future directions of hybrid composites have been described in details.

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Section: Applicationsmentioning

confidence: 99%

Physical, Mechanical and Perforation Resistance of Natural-Synthetic Fiber Interply Laminate Hybrid Composites

et al. 2022

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“…The utilization of composites to replace the conventional use of aluminum materials in the basic N219 aircraft is imperative. This is due to the weight increase resulting from the replacement of the landing gear with floaters [3]. To address this, the float components must employ composite materials to achieve a weight reduction of 200-300 kg.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Double Hole Composite Plate on the Floater Compartment of Amphibious Aircraft Using Taguchi Method

Nurrohmad,

Antares,

Nuranto

et al. 2024

war. ardhia

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A floater or pontoon is one of the most important components of amphibious aircraft to assist the take-off and landing operation. The inner structure of the floater consists of compartments to carry some payload and to reinforce the structural strength due to water and aerodynamic load that occurred during the aircraft operation. The composite material is chosen instead of metal to reduce the weight of the floater. One of the problems on the composite panel is the existence of some holes due to joint with another part or also to minimize its weight. In this study, the optimization of the composite plate with the existence of a double hole is done using the Taguchi Method. The objective of this optimization is to minimize the stress that happens due to the tensile load. The Finite Element Method is used to calculate the maximum stress and stress distribution on the plate. Tsai-Hill failure criterion is used to make sure that the optimum design does not fail. This optimization considers open hole configuration, the ratio between diameter, and hole distance, as well as the fiber orientation as the control factors. The Taguchi L9 Orthogonal Array is used to make 9 design variations from 3 control factors and 3 levels. This process also considers the thickness of the lamina and material strength as noise factors. The optimization process results in the optimum composite design as follows: 1st double hole configuration (in line with the load direction), the ratio between diameter and hole distance is 0.5, and the fiber direction is [0/90/45/-45]s. The maximum in-plane stress of the optimum design is 39.56 MPa with the Tsai-Hill value is 0.23, so the design does not fail. This optimum configuration of the composite plate can be used to make design considerations for an amphibious aircraft floater compartment.

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Finite element analysis of polymeric materials for industrial applications

Sivaraj,

Thanigachalam,

Mohankumar

et al. 2024

Finite Element Analysis of Polymers and Composites

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Composite wing structure of light amphibious airplane design, optimization, and experimental testing

Cited by 13 publications

References 22 publications

Physical, Mechanical and Perforation Resistance of Natural-Synthetic Fiber Interply Laminate Hybrid Composites

Physical, Mechanical and Perforation Resistance of Natural-Synthetic Fiber Interply Laminate Hybrid Composites

Optimization of Double Hole Composite Plate on the Floater Compartment of Amphibious Aircraft Using Taguchi Method

Finite element analysis of polymeric materials for industrial applications

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