Performance analysis of composite ply orientation in aeronautical application of unmanned aerial vehicle (UAV) NACA4415 wing

Basri, Ernnie Illyani; Sultan, M. T. H.; Faizal, Mohd; Basri, Adi Azriff; Abas, Mohd Firdaus; Majid, M.S. Abdul; Mandeep, J. S.; Ahmad, Kamarul Arifin

doi:10.1016/j.jmrt.2019.06.044

Cited by 31 publications

(21 citation statements)

References 28 publications

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“…The Nomex honeycomb is commonly used in aircraft wing flaps and rudders due to its high specific stiffness and low weight. The mechanical characteristics of materials of wing skin are referred to elsewhere [13]. The physical characteristics of materials of a specimen size of 300 mm × 300 mm are shown in Table 2.…”

Section: Stage 1: Experimental Validationmentioning

confidence: 99%

“…The wing model with tubercles at the leading edge (TLE) is presented in Figure 6a. In a similar study by [13,21], the spherical pattern of tubercles at the leading edge of the TLE wing was designed by using optimum amplitude, A of 0.025 c and wavelength, λ of 0.25 c due to its remarkable effect on the airfoil performance [22][23][24]. The configuration of the TLE wing is depicted in Figure 6b.…”

Section: Geometrical Modeling Of Uav Wingmentioning

confidence: 99%

“…The bottom surface of the bracket is defined as fixed by using a screw and nut due to the fuselage not being included in the model. Hence, this defines that all the rotations and displacements of the bottom surface of the brackets are set to zero, UX = UY = UZ = ROTX = ROTY = ROTZ = 0 [13], [21]. The second boundary condition is the symmetrical condition of the wings, which considering that half of the wing that developed in FE analysis.…”

Section: Updating: Mesh Generation Boundary and Loading Conditionsmentioning

confidence: 99%

“…The spars of the wing are set as symmetrical about the XZ-plane. Hence, the rotation along Y-axis and Z-axis, as well as the displacement along X-axis were assigned as zero, UX = ROTY = ROTZ = 0 [13,21].…”

Section: Updating: Mesh Generation Boundary and Loading Conditionsmentioning

confidence: 99%

“…The notation and ply arrangement in the laminate are presented by considering the shell elements to model the wing structure. The modeling process for laminating composites is referred to as the construction of laminated composite materials [13]. In ACP (PrePost) module, the wing model is developed in the form of a shell element of SHELL181 that is assigned as a single sheet according to its thickness.…”

Section: Updating: Lamination Process and Composite Modelingmentioning

confidence: 99%

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Consideration of Lamination Structural Analysis in a Multi-Layered Composite and Failure Analysis on Wing Design Application

et al. 2021

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A finite element (FE) model is developed to study the structural performance on a composite wing of a UAV with a tubercle design at the leading edge of the wing. The experimental study of the designation of the composite at the wing skin is carried out to prove the simulation validity through material characteristics. In this paper, the numerical modeling for simulation is highlighted to correlate the process parameter setting of simulation replicating the actual experimental tests. The percentage difference was calculated to be 11.1% by tensile and 10.47% by flexural. The numerical work applied the study of FE analysis and developed a standardized numerical approach for structural optimization, known as FE-ACP simulation. The significant findings of deformation are obtained according to Schrenk’s aerodynamic loading, while the prediction of failure mode of Tsai–Wu under interaction among stresses and strains was acquired at the seventh and eighth layer of both spars.

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Section: Stage 1: Experimental Validationmentioning

confidence: 99%