Parameterization of Curvilinear Spars and Ribs for Optimum Wing Structural Design

Locatelli, Davide; Mulani, Sameer B.; Kapania, Rakesh K.

doi:10.2514/1.c032249

Cited by 12 publications

(7 citation statements)

References 14 publications

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“…Similarly the RF of the sequential iteration ( + 1) is given by the first part of Equation (5). In the present analysis, the critical buckling compressive load is calculated using the analytical solution of Equation (1) [31];…”

Section: Upper and Lower Skin Panelsmentioning

confidence: 99%

“…Equation (3) arises from Equations (4) and (5), which express the RFs of two subsequent iterations (i) and (i + 1). The RF of the i th iteration is RF i and is calculated as a function of the applied load P i and panel thickness t i , as:…”

Section: Upper and Lower Skin Panelsmentioning

confidence: 99%

“…Most of the wing studies focus on the wing structural optimization, in order to determine the lightest and strongest internal wing structure. Characteristic studies are carried out, by several researchers, by employing optimization routines regarding the stiffened panels [2][3][4][5], the position of the spars and ribs [6,7]. Furthermore, topology optimization is frequently employed to determine the optimum location of certain structural components under static and aeroelastic loads [8,9].…”

Section: Introductionmentioning

confidence: 99%

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Towards the Design of a Multispar Composite Wing

Stamatelos

Labeas

2020

Computation

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In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.

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Section: Upper and Lower Skin Panelsmentioning

confidence: 99%

Section: Upper and Lower Skin Panelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Towards the Design of a Multispar Composite Wing

Stamatelos

Labeas

2020

Computation

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“…No matter which design method is used, the sizing design must include optimal thickness allocation of different body components: spars, ribs, stringers, and skin [23]. There exist significant interconnections between these two types of design factors (topology and sizing/layout) that are substantial, especially when skin-buckling metrics are considered.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4

et al. 2022

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This paper is a follow-up to earlier work on applying multidisciplinary numerical optimization to develop a morphing variable span of a tapered wing (MVSTW) to reduce its weight by using composite materials. This study creates a numerical environment of multidisciplinary optimization by integrating material selection, structural sizing, and topological optimization following aerodynamic optimization results with the aim to assess whether morphing wing optimization is feasible. This sophisticated technology is suggested for developing MVSTWs. As a first step, a problem-specific optimization approach is described for specifying the weight-saving structure of wing components using composite materials. The optimization was performed using several approaches; for example, aerodynamic optimization was performed with CFD and XFLR5 codes, the material selection was conducted using MATLAB code, and sizing and topology optimization was carried out using Altair’s OptiStruct and SolidThinking Inspire solvers. The goal of this research is to achieve the MVSTW’s structural rigidity standards by minimizing wing components’ weight while maximizing stiffness. According to the results of this optimization, the weight of the MVSTW was reduced significantly to 5.5 kg in comparison to the original UAS-S4 wing weight of 6.5kg. The optimization and Finite Element Method results also indicate that the developedmorphing variable span of a tapered wing can complete specified flight missions perfectly and without any mechanical breakdown.

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“…Recent improvements in computational enabled the study of advanced concepts in stiffened panel design such as the use of curvilinear stiffening members [13][14][15]. Furthermore, the use of parallel processing [13,16] or response surfaces [17] has been used to cope with the optimization aspects of individual stiffened panels [13,14,17] or entire wings [15,16]. Topology optimization has been used to determine the location of wing sub-structure under aeroelastic loads [18,19] or minimizing compliance of a wing modelled as truss structure [20].…”

Section: Introductionmentioning

confidence: 99%

Weight trades in the design of a composite wing box: effect of various design choices

et al. 2018

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A process to efficiently design composite wing boxes is presented. It uses analytical and semi-empirical equations for failure modes such as material strength, plate buckling, stiffener column buckling and stiffener flange or web crippling. Laminate layups for the different components are selected in accordance with basic engineering rules and guidelines and are updated as necessary to meet the local loads. The emphasis is in allowing buckling of skins at any fraction of the ultimate load and allowing local load redistribution from buckled to non-buckled panels to save weight. The design process is automated and the design can be automatically transferred over to a commercial finite-element code for detailed design and validation. The effects on weight of number of spars, ribs, and stiffeners as well as the fraction of ultimate load at which buckling is allowed are examined and insight is gained to which of these the weight is most sensitive to. In addition, the effect of minimum gage on weight was found to be a driver.

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Parameterization of Curvilinear Spars and Ribs for Optimum Wing Structural Design

Cited by 12 publications

References 14 publications

Towards the Design of a Multispar Composite Wing

Towards the Design of a Multispar Composite Wing

Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4

Weight trades in the design of a composite wing box: effect of various design choices

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