Structural optimization of an aeroelastically tailored composite flat plate made of woven fiberglass/epoxy

Attaran, Abdolhamid; Majid, Dayang Laila Abang Abdul; Basri, Shahnor; Rafie, Azmin Shakrine Mohd; Abdullah, Ermira Junita

doi:10.1016/j.ast.2010.09.005

Cited by 14 publications

(7 citation statements)

References 14 publications

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“…Librescu [9] thoroughly investigated the theoretical foundations of composite TWBs and derived the necessary relations. The key point in the composite TWBs is that the desired mechanical and aeroelastic behavior of the structure can be achieved by optimizing and tailoring the directional strength and stiffness of the composite material [14][15][16][17][18][19]. Initially, the curved fibers were used by Gurdal et al [20] to vary stiffnesses of rectangular composite plates.…”

Section: Introductionmentioning

confidence: 99%

Eğrisel Fiber Yollu İkili Motorlu-Kanat Sisteminin Aeroelastik Enerji Optimizasyonu

Farsadi

Asadi

2020

Journal of Aviation

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In the present study, the aeroelastic energy response of a twin-engine composite wing system is optimized based on sequential quadratic programming (SQP) method. The variable stiffness is acquired by constructing laminates of thin wall beam (TWB) with curvilinear fibers having prescribed paths. In order to account the effect of spanwise locations and mass of the engines on the aeroelastic characteristics of TWB, the novel governing equations of motion are obtained using Hamilton's variational principle. The paper aims to exploit desirable fiber paths with improved aeroelastic properties for different twin-engine wing configuration. Ritz based solution methodology is employed to solve the equations with coupled incompressible unsteady aerodynamic model based on Wagner's function. A novel optimization strategy based on the total energy of the aeroelastic system is introduced. The proposed total energy, as a cost function, is minimized in terms of four optimization variables of two engine's locations and wing structure curvilinear fiber angle with two design parameters. The total energy is obtained by integrating responses of kinetic and potential energy in a specific time interval. The minimum total energy is an indication of ideal optimization variables which leads to the optimum flutter performance. Numerical results demonstrate the effectiveness of the optimization variables on the total energy of the aeroelastic system and determine the optimal values of introduced variables in case of minimum total energy and improved aeroelastic characteristics.

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Section: Introductionmentioning

confidence: 99%

Eğrisel Fiber Yollu İkili Motorlu-Kanat Sisteminin Aeroelastik Enerji Optimizasyonu

Farsadi

Asadi

2020

Journal of Aviation

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“…In many of these studies, plain fiber-reinforced laminated composite plates were considered for optimization; besides, others types of composite structures were optimized: Structures reinforced with short or long fibers, 6,70,113,300,545,618,696,899,958 particulate fillers, 352,425,737,821 braided or woven fibers, 291,326,336,347,425,530,531,710,880,884,923,1006 or carbon nanotubes, 993 laminates with layers having variable fiber orientation, 149,173,219,243,247,271,311,325,355,359,446,564,633,709,720,730,732,771,787,796,797,814,831,877,885,900,906,910,951–954 or variable fiber density, 325,472,…”

Section: Introductionmentioning

confidence: 99%

“…damping,86,129,148,256,292,400 sound transmission loss,1004 coefficient of moisture expansion, 408 maximum temperature,352,872 reliability target,136,151,305,411,501,520,685,762,809,887,903,955 stiffness,86,194,982 center of mass, 241 twist angle of a wing, 36,42,166 aerodynamic stability features like flutter, flapping,33,59,192,279,314,333,351,436,442,451,455,485,487,605,623,625,668,714,741,840,861,880,892 or aerodynamic performance parameters. 111,241 Special constraints are sometimes imposed on bending stiffness terms to avoid excessive error arising due to negligence of bending-twisting coupling.268,303,388,559,606,645,646,738,739,807,808,940 The number of contiguous plies with the same fiber orientation may be limited to prevent matrix damage propagation and thus avoid large matrix cracks.198,226,248,249,254,255,286,328,335,430,473,477,494, 495,508,555,559,600,612,620,645,646,659,678,679,692,716,...…”

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confidence: 99%

Optimum Design of Composite Structures: A Literature Survey (1969–2009)

Sonmez

2016

Journal of Reinforced Plastics and Composites

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Optimum structural design of composites is a research subject that has drawn the attention of many researchers for more than 40 years with a growing interest. In this study, a review of the literature on this subject is presented. The papers are classified according to the type of the composite structure optimized in those studies, the loading conditions, the objective function, the structural analysis method, the design variables, the constraints, the failure criteria, and the search algorithm used by the researchers.

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“…Aeroelastic phenomena are the result of the mutual interaction of elastic and aerodynamic forces, the occurrence of which during the flight can be destructive and lead to the loss of the aircraft [1]. The stiffness and mass distribution of the wing structure both have effects on the aeroelastic properties.…”

Section: Introductionmentioning

confidence: 99%

Flutter Characteristic Study of Composite Sandwich Panel with Functionally Graded Foam Core

Jin¹,

Zhong²

2016

International Journal of Aerospace Engineering

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This paper attempts to investigate the flutter characteristic of sandwich panel composed of laminated facesheets and a functionally graded foam core. The macroscopic properties of the foam core change continuously along this direction parallel to the facesheet lamina. The model used in the study is a simple sandwich panel-wing clamped at the root, with three simple types of grading strategies for FGM core: (1) linear grading strategy in the chord-wise direction, (2) linear grading strategy in the span-wise direction, and (3) bilinear grading of properties of foam core across the panel. The results show that use of FGM core has the potential to increase the flutter speed of the sandwich panel. Finally, a minimum weight design of composite sandwich panel with lamination parameters of facesheet and density distribution of foam core as design variables is conducted using particle swarm optimization (PSO).

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Structural optimization of an aeroelastically tailored composite flat plate made of woven fiberglass/epoxy

Cited by 14 publications

References 14 publications

Eğrisel Fiber Yollu İkili Motorlu-Kanat Sisteminin Aeroelastik Enerji Optimizasyonu

Eğrisel Fiber Yollu İkili Motorlu-Kanat Sisteminin Aeroelastik Enerji Optimizasyonu

Optimum Design of Composite Structures: A Literature Survey (1969–2009)

Flutter Characteristic Study of Composite Sandwich Panel with Functionally Graded Foam Core

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