New conceptual design of aeroelastic wing structures by multi-objective optimization

Sleesongsom, Suwin; Bureerat, Sujin

doi:10.1080/0305215x.2012.661728

Cited by 23 publications

(22 citation statements)

References 24 publications

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“…Additionally, the configuration resulting from the multi-load case optimization, combining different flow conditions simultaneously, has been presented. The results obtained are similar to the solution presented by Sleesongsom and Bureerat [12], however this paper presents a discrete solution, using the ground structure. On the other hand, Oktay [11] presented optimum topology of the internal wing structure with assumed volume fraction.…”

Section: Discussionsupporting

confidence: 72%

“…Presented algorithm contributes new possibilities for optimization due to unique features including simultaneous size, shape, and topology optimization. The volume resulting from the presented optimization procedure is not assumed before optimization, but is related to the assumed strain energy density and material strength properties, as opposed to the method presented by Sleesongsom and Bureerat [12]. Moreover, the method presented herein merges multiple load configurations without overlapping results.…”

Section: State Of the Artmentioning

confidence: 99%

“…The procedure, developed in opposition to standard optimization techniques, is capable of obtaining proper results (well known from literature [1]) without depending on the starting (12) With the assumption of a constant volume the necessary condition for optimality:…”

Section: Numerical Examplementioning

confidence: 99%

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New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

Gaweł

Nowak

Hausa

et al. 2017

Bulletin of the Polish Academy of Sciences Technical Sciences

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Abstract. This paper presents a new biomimetic approach to the structural design. For the purpose of aircraft wing design the numerical environment combining simultaneous structural size, shape, and topology optimization based on aeroelastic analysis was developed. For the design of aircraft elements the optimization process must be treated as a multi-load case task, because during the fluid structure interaction analysis each step represents a different structural load case. Also, considering different angles of attack, during the CFD computation each result is considered. The method-specific features (such as domain independence, functional configurations during the process of optimization, and multiple load case solution implemented in the optimization scenario) enable the optimal structural form. To illustrate the algorithm functionality, the problem of determining the optimal internal wing structure was presented. The optimal internal wing structure resulting from aeroelastic computation with different angles of attack has been presented. ture of a wing. Their solution computed the pressure distribution for an analyzed shape, but missed coupling. Another approach to wing optimization refers to the reduction of skin thickness, which was done by Wang and Williams [3]. The wing was divided into dozens of panels, modeled as membranes. The wing՚s weight was reduced along with the increased stiffness of the whole model, stemming from the modification of the membranes thickness.In the papers of Krog [4, 5] the optimization of Airbus A380 ribs was treated as a two-step process. Potential geometry was reduced using standard topology optimization, and then the geometrical model was created for structural optimization purposes. Finally, the optimal structure was transformed into a CAD model which was afterwards verified.Stettner and Schuhmacher [6] also referred to topological and structural optimizations for designing the rear part of a military transport aircraft fuselage. The whole assembly as well as its frame has been analyzed with the same optimization methods within a two-stage process. The results were obtained separately for bending load, torsional load, and pressure exerted on side walls. Additionally, authors attempted to compile the individual results into a single form. However, it has to be emphasized that presented solution did not result from multi-load case calculations.Maute and Allen [7] suggested implementation of structural optimization methods in combination with an aeroelastic simulation. The problem was presented on the example of a slim wing model used for the two-dimensional topological optimization. The obtained configuration presented a conceptual distribution of the material inside the wing subjected to the impact of surrounding flow. The internal structure significantly differed from one we might expect on the basis of an analysis of the regular pressure distribution over a wing surface.

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Section: Discussionsupporting

confidence: 72%

Section: State Of the Artmentioning

confidence: 99%

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New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

Gaweł

Nowak

Hausa

et al. 2017

Bulletin of the Polish Academy of Sciences Technical Sciences

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“…Later, an alternative optimizer is evolutionary algorithms due to the fact they are robust, simple to use, derivative-free, and free from intermediate pseudo densities [8]. Complicated problems, such as partial topology, simultaneous topology, shape, and sizing optimization, can be performed within one optimization run [3,8,16,17] by using such algorithms. In this paper [8], they presented the comparative performance of multi-objective evolutionary algorithms (MOEAs) for solving structural topology optimization test problems based on ground element filtering technique.…”

Section: Topological Designs With Ground Element Filteringmentioning

confidence: 99%

Topology Optimisation Using MPBILs and Multi-Grid Ground Element

Sleesongsom

Bureerat

2018

Applied Sciences

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This paper aims to study the comparative performance of original multi-objective population-based incremental learning (MPBIL) and three improvements of MPBIL. The first improvement of original MPBIL is an opposite-based concept, whereas the second and third method enhance the performance of MPBIL using the multi and adaptive learning rate, respectively. Four classic multi-objective structural topology optimization problems are used for testing the performance. Furthermore, these topology optimization problems are improved by the method of multiple resolutions of ground elements, which is called a multi-grid approach (MG). Multi-objective design problems with MG design variables are then posed and tackled by the traditional MPBIL and its improved variants. The results show that using MPBIL with opposite-based concept and MG approach can outperform other MPBIL versions.

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“…Such control has been principally achieved through the use of composite materials where the stiffness tailoring is achieved through the design of the fibre orientations [4][5][6][7][8][9] . More recently, research work [10][11][12][13][14][15][16][17][18][19][20][21] focusing on the development of lighter wing structure has shown that the use of novel wing structural designs can control the aeroelastic performance and reduce the wing structural mass. These results have been highlighted by research in wing structure topology which encompasses the study of the number, position, size and shape of structural features.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Tailoring using the Spars and Stringers Planform Geometry

François

Cooper

2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. The aeroelastic performance of a wing, including static aeroelastic shape, flutter/divergence speed and gust load response, has a significant influence on aircraft design. The tailoring of aeroelastic responses therefore offers potential weight savings. In this paper, the spars and stringers planform geometry (i.e. shape and root/tip chord wise location) on a representative wind tunnel model aircraft wing are used to modify the wing aeroelastic performance. Several optimisations are performed to illustrate the ability of the spars and stringers planform geometrical features to change the wing vibrational mode natural frequencies, deformation under a static tip load and aerodynamic load, gust response and aeroelastic instability speed. Changing the stringers planform geometry is shown to offer minor variation in the wing deformation and loads. Changing the spars planform geometry is shown to enable a reduction in root bending moment under static aerodynamic loading greater than 10%, a reduction in maximum root bending moment encounter during a worst case scenario gust event greater than 10% and a 25% increase in flutter speed. The improvements due to a change in the spar planform geometry are compared to the effect of changing the wing sweep angle. A framework to characterise Euler-Bernoulli beam properties on wings with geometric coupling is then developed and validated to relate the stiffness and bend/twist coupling parameter to the full 3D FE models.

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New conceptual design of aeroelastic wing structures by multi-objective optimization

Cited by 23 publications

References 24 publications

New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

Topology Optimisation Using MPBILs and Multi-Grid Ground Element

Aeroelastic Tailoring using the Spars and Stringers Planform Geometry

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