Three-dimensional structural topology optimization of aerial vehicles under aerodynamic loads

Oktay, E.; Akay, H. U.; Sehitoglu, Onur Tolga

doi:10.1016/j.compfluid.2013.11.018

Cited by 17 publications

(18 citation statements)

References 12 publications

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“…A separate stage of rib pitch optimization is then used to prevent skin buckling. There are also examples of SIMP being used to explore optimal internal wing structures (Krog et al 2009;Oktay et al 2014). The aim of this paper is to consider the entire 3D wing box space as the design domain for topology optimization to explore novel configurations for the entire wing box structure.…”

Section: Topology Optimization In Aircraft Designmentioning

confidence: 99%

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Dunning

Stanford

Kim

2014

Struct Multidisc Optim

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The purpose of this work is to develop a level set topology optimization method for an unstructured threedimensional mesh and apply it to wing box design for coupled aerostructural considerations. The paper develops fast marching and upwind schemes suitable for unstructured meshes, which make the level set method robust and efficient. The method is applied to optimize a representative wing box internal structure for the NASA Common Research Model. The objective is to minimize the total compliance of the wing box. The trim condition that aerodynamic lift must balance the total weight of the aircraft is enforced by allowing the root angle of attack to change. The adjoint method is used to obtain the coupled shape sensitivities required to perform aerostructural optimization of the wing box. Optimum solutions for several aerodynamic and body force load cases, as well as a ground load case, are presented.

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Section: Topology Optimization In Aircraft Designmentioning

confidence: 99%

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Dunning

Stanford

Kim

2014

Struct Multidisc Optim

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“…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. Further analysis needed for developing manufacturable structures was not made.…”

Section: Resultsmentioning

confidence: 99%

“…The optimization process itself was conducted on one of the cross sections selected by the authors. Oktay et al [11] also used the solid isotropic material with penalization (SIMP) method for optimization of the entire wing box space, looking for new possible configurations.…”

Section: State Of the Artmentioning

confidence: 99%

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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“…Recently, National Institute of Aeronautics and Space or Lembaga Penerbangan dan Antariksa Nasional (LAPAN) as an institution which conducts research and development in the field of aerospace technology also developsunmanned aerial vehicles (UAV) with a simple configuration. The high wing and twin-boom vertical stabilizer configuration is favorable around unmanned aircraft designer because of the simplicity of design and high stability flying characteristics (Kurukularachchi, Prince, & Munasinghe, 2014) One of the aerodynamics characteristics to be analyzed in order to meet these requirements is the aerodynamics load characteristics, particularly the aerodynamic load on main aircraft lifting surfaces (Oktay, Akay, & Sehitoglu, 2014).…”

Section: Introductionmentioning

confidence: 99%

Verification of Schrenk Method for Wing Loading Analysis of Small Unmanned Aircraft Using Navierstokes Based CFD Simulation

Soemaryanto

Rosid

2018

Jutekgan

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Prediction of an aerodynamic load acting on a wing or usually called wing loading becomes an important stage for structural analysis. Several methods have been used in estimating the wing loading. Schrenk approximation method is commonly used to achieve the fast estimation of lift distribution along wingspan, but in order to achieve a high level accuracy of aerodynamic prediction, computational fluid dynamics (CFD) with Navier Stokes-based equation can be used. LAPAN Surveillance UAV (LSU series) has been chosen to represent an aerodynamics analysis on generic small unmanned aircraft with twinboom vertical stabilizer configuration. This study was focused to verify the Schrenk approximation method using high accuracy numerical simulation (CFD). The goal of this study was to determine the lift distribution along wingspan and a number of errors between Schrenk approximation and CFD method. In this study, Schrenk approximation result showed similarity with the CFX simulation. So the two results have been verified in analysis of wing loading. ABSTRAKPrediksi dari beban aerodinamika yang terjadi pada sayap menjadi salah satu tahap yang penting dalam analisis struktur perancangan pesawat. Beberapa metode telah digunakan untuk mengestimasi besarnya beban aerodinamika pada sayap. Metode Schrenk umum digunakan untuk estimasi cepat perhitungan besar distribusi gaya angkat di sepanjang sayap. Guna mencapai tingkat akurasi yang tinggi dari prediksi aerodinamika, simulasi Computational Fluid Dynamics (CFD) dengan berbasis persamaan Navier-Stokes dapat digunakan. Pesawat nirawak LSU dipilih untuk merepresentasikan analisis aerodinamika pada pesawat nirawak dengan konfigurasi twin-tailboom pusher. Fokus dari studi yang dilakukan adalah untuk memverifikasi dari metode pendekatan dari Schrenk dengan menggunakan metode yang memiliki akurasi tinggi seperti simulasi CFD. Tujuan dari studi adalah untuk menghitung distribusi gaya angkat sepanjang sayap dan menentukan seberapa besar error dari kedua metode.

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Three-dimensional structural topology optimization of aerial vehicles under aerodynamic loads

Cited by 17 publications

References 12 publications

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

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

Verification of Schrenk Method for Wing Loading Analysis of Small Unmanned Aircraft Using Navierstokes Based CFD Simulation

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