A surrogate-based integrated framework for the aerodynamic design optimization of a subsonic wing planform shape

Benaouali, Abdelkader; Kachel, Stanisław

doi:10.1177/0954410017699007

Cited by 7 publications

(6 citation statements)

References 45 publications

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“…''0'' denotes the initial design and ''1'' denotes the best design. The limited stresses are calculated according to equations (28) and (29). It can be founded that the whole truss-type structure keeps adjusting during each optimization iteration as well as the internal stresses.…”

Section: Solving the Stress Within Each Elementmentioning

confidence: 99%

“…16 With respect to three types of design variables, structural design optimization can be classified into three categories, namely, size optimization, shape optimization, and topology optimization. And different types of optimization problems solved by different stochastic search algorithms have been presented by researches, such as size optimization, 3,4,8,12,[16][17][18][19] size and shape optimization, [20][21][22][23][24][25][26][27][28][29] or size, shape, and topology optimization. [30][31][32][33][34][35] This paper is a subsequent research of the studies of Li and Au, 12 Li, 13 and Li and Ma.…”

Section: Introductionmentioning

confidence: 99%

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Combined size and shape optimization of truss structures using subset simulation optimization

Tee

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents an approach to solve the combined size and shape design optimization problems using recently developed subset simulation optimization for both continuous and discrete design variables. Except for the componentwise Metropolis–Hasting algorithm, a recently developed adaptive conditional sampling algorithm is also employed as an alternative approach for generating new conditional samples (candidate designs) for each simulation level, which enhances the accuracy and stability of the optimization process. Besides, a double-criterion sorting algorithm is used to handle the design constraints and integrate them in the generation of conditional samples during the Markov Chain Monte Carlo simulation, and the inverse transform method is employed to deal with the discrete design variables. Totally, four numerical examples are considered, including a 15-bar 2D truss, an 18-bar 2D truss, a 39-bar 3D truss and a truss-type landing gear of an unmanned aerial vehicle. The optimal designs obtained from subset simulation optimization using either the componentwise Metropolis–Hasting algorithm or the adaptive conditional sampling algorithm succeed in substantially reducing the weights of the truss-type structures under design constraints in terms of the member stress, the Euler buckling and the nodal displacement. The computational results indicate the proposed method can be taken as an alternative tool for structural optimization design on truss structures when involving the combined size and shape design.

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Section: Solving the Stress Within Each Elementmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Combined size and shape optimization of truss structures using subset simulation optimization

Tee

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Aerodynamic shape optimization is aimed at improving the performance of aircraft including drag reduction [1], range improvement [2], and weight minimization [3], by changing its shape while satisfying specified constraints. In the early phase, the optimization mainly relies on wind tunnel experiments and flight tests.…”

Section: Introductionmentioning

confidence: 99%

Study on a Rapid Aerodynamic Optimization Method of Flying Wing Aircraft for Conceptual Design

Wei

Huang

Song

2022

International Journal of Aerospace Engineering

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Searching for a design scheme satisfying the requirements in aircraft conceptual design can be a time-consuming work because of the multipeak and nonlinearity of the design space. This paper proposed a rapid aerodynamic optimization method for flying wing aircraft conceptual design. This method is aimed at reducing the induced drag at the design point by adjusting the camber and twist angle of spanwise airfoil. Firstly, the mean camber surface of the flying wing aircraft was parameterized. Secondly, the surrogate model was constructed based on the points selected by the optimization Latin square method. Thirdly, the surrogate model combined with a multi-island genetic algorithm was used for the preliminary solution of global optimum, and then, the Nonlinear Programming by Quadratic Lagrangian method combined with a vortex lattice method was used for searching the nearest exact best point from the initial best point. Finally, connecting with manual selection, the optimized flying wing layout scheme was obtained. The optimized results show that the induced drag coefficient is reduced by 10%, the pitching moment coefficient is reduced by an order of magnitude, and the lift drag ratio is increased from 26.3 to 27.3. The proposed optimization method decreases the time cost in aircraft conceptual design while achieving sufficient calculation accuracy. By using this method, the design space can be explored rapidly to search for the best design scheme satisfying the constraints.

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“…Many examples of multidisciplinary optimization can be shown, especially with coupled aerodynamics and structure analyses. Starting from airliners optimization 1,2 through supersonic aircrafts 3 and ending up even with morphing structures. 4,5 Although variety of examples is very wide, only a few of design examples consider dynamic stability effects in the conceptual and preliminary design.…”

Section: Introductionmentioning

confidence: 99%

Numerical multidisciplinary optimization of aircraft with flight dynamic stability constraints

Mieloszyk

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Classical approach to conceptual and preliminary design in aerospace sciences reaches limits. To go further and achieve better, competitive results’ use of optimization methods becomes mandatory. The trend is clearly visible in professional software for simulations equipped with optimization tools, which was not standard just decade ago. Many examples of multidisciplinary optimization were shown, especially with coupled aerodynamics and structure analyses, but only few of them consider dynamic stability effects in the conceptual and preliminary design. The article shows successful example of multidisciplinary design and optimization of Vertical Takeoff and Landing aircraft, which includes coupling of aerodynamics, mass analyses and innovative approach of constraints from flight dynamic stability. Presented optimization framework revealed potential for more efficient conceptual and preliminary design with the result of known dynamic stability characteristics of the aircraft. Obtaining the dynamic stability characteristics is not common on the early stages of the design yet crucial for the aircraft flight performance.

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A surrogate-based integrated framework for the aerodynamic design optimization of a subsonic wing planform shape

Cited by 7 publications

References 45 publications

Combined size and shape optimization of truss structures using subset simulation optimization

Combined size and shape optimization of truss structures using subset simulation optimization

Study on a Rapid Aerodynamic Optimization Method of Flying Wing Aircraft for Conceptual Design

Numerical multidisciplinary optimization of aircraft with flight dynamic stability constraints

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