Optimal design of composite lateral wing upper covers. Part I: Linear buckling analysis

Barkanov, E.; Ozoliņš, Olģerts; Eglītis, Edgars; Almeida, F.; Bowering, M. C.; Watson, G.

doi:10.1016/j.ast.2014.07.010

Cited by 28 publications

(20 citation statements)

References 14 publications

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“…The flexibility λ of variable cross-section sandwich beam reinforced by CFRP stiffeners can be constructed from Eqs. (1), (4) and (5).…”

Section: Theoretical and Numerical Methodsmentioning

confidence: 99%

“…A large number of smaller parts such as skin panels, cores, ribs and stringers need to be joined together to fabricate as a single integral structure [3]. Fortunately, the increasing application of advanced composites gives the possibility and convenience to realize the weight saving potential and reduce the manufacturing costs and subsequent product maintenance costs in aircraft structures such as wing panels [4].…”

Section: Introductionmentioning

confidence: 99%

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Structural design of composite stiffened panel for a flat wing micro-aircraft

et al. 2020

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In this study, the integral micro-sized composite wings are designed and manufactured by using carbon fiber reinforced plastics and low-density foam. The analytical expressions of bending stiffness of a multilayer sandwich structures for variable cross-section panel are determined. The obtained analytical bending stiffness is numerically verified using results of compressive buckling modes on wing panels from a numerical FE program and experimental tests by a series of stiffened structures which are empirically designed. Contrastive results demonstrate that the stiffener configuration tremendously affects the global buckling of the wing panels and the shapes, locations and intervals of the stiffeners which should be adjusted to construct a structure with maximum bending stiffness. Finally, with the use of the bi-directional evolutionary structural optimization method, the optimum design of the wing cross-section was determined by topology optimization method to pursue the best weight/stiffness. Compared with the initial structure, the optimum material layout of the topology structure performs better at reducing stress concentration and improving load carrying capacity of wing panels.

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“…The flexibility λ of variable cross-section sandwich beam reinforced by CFRP stiffeners can be constructed from Eqs. (1), (4) and (5).…”

Section: Theoretical and Numerical Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Structural design of composite stiffened panel for a flat wing micro-aircraft

et al. 2020

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show abstract

“…Thin plates or thin-walled structures are used in sports and automotive industry, aerospace and civil engineering. Snowboards, skis or poles, as well as all kinds of crane girders [29], structural components of automobiles [1] (car body sheathing and all longitudinal members), aircraft fuselages [26] and wings [3], supporting structures of walls and roofs of large halls and warehouses [4] can be mentioned as examples of such structural elements.…”

Section: Introductionmentioning

confidence: 99%

Selected problems concerning determination of the buckling load of channel section beams and columns

Paszkiewicz

Kubiak

2015

Thin-Walled Structures

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“…For structures made of isotropic homogeneous materials, like steel or aluminium, the failure mechanism is quite well described in the worldwide literature (e.g., [1][2][3]). Recently, different types of composites (unidirectional fibre reinforcement polymers, fabric reinforcement polymers, fibre metal laminates, functionally graded materials and many others) are more and more widely used in different branches of industry and final products (e.g., [4][5][6][7][8]). Engineers want to know the behaviour of composite structures in a full range of loading till their collapse.…”

Section: Introductionmentioning

confidence: 99%