Conceptual design of UAV using Kriging based multi-objective genetic algorithm

Rajagopal, S.; Ganguli, Ranjan

doi:10.1017/s0001924000002621

Cited by 24 publications

(9 citation statements)

References 17 publications

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“…[ [1][2] proposed a multi-disciplinary design optimization (MDO) for optimizing the conceptual design of a long-endurance UAV with the panel method code, XFLR5. Park et al [3] employed a simple multi-objective genetic algorithm to find an optimum airfoil shape for a long-endurance UAV.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, design optimization techniques for long-endurance UAVs have been investigated to improve their flight performance and to reduce the development effort. Rajagopal et al [1][2] proposed a multidisciplinary design optimization (MDO) for optimizing the conceptual design of a long-endurance UAV with the panel method code, XFLR5. Park et al [3] employed a simple multi-objective genetic algorithm to find an optimum airfoil shape for a long-endurance UAV.…”

Section: Introductionmentioning

confidence: 99%

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Wing Design Optimization for a Long-Endurance UAV using FSI Analysis and the Kriging Method

Son¹,

Choi²,

Jin³

et al. 2016

International Journal of Aeronautical and Space Sciences

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In this study, wing design optimization for long-endurance unmanned aerial vehicles (UAVs) is investigated. The fluidstructure integration (FSI) analysis is carried out to simulate the aeroelastic characteristics of a high-aspect ratio wing for a long-endurance UAV. High-fidelity computational codes, FLUENT and DIAMOND/IPSAP, are employed for the loose coupling FSI optimization. In addition, this optimization procedure is improved by adopting the design of experiment (DOE) and Kriging model. A design optimization tool, PIAnO, integrates with an in-house codes, CAE simulation and an optimization process for generating the wing geometry/computational mesh, transferring information, and finding the optimum solution. The goal of this optimization is to find the best high-aspect ratio wing shape that generates minimum drag at a cruise condition of CL = 1.0. The result shows that the optimal wing shape produced 5.95 % less drag compared to the initial wing shape. best high-aspect ratio wing shape that generates minimum drag at a cruise condit result shows that the optimal wing shape produced 5.95 % less drag compared shape.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Wing Design Optimization for a Long-Endurance UAV using FSI Analysis and the Kriging Method

Son¹,

Choi²,

Jin³

et al. 2016

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

show abstract

“…Moreover, if the numerical simulation of each iteration requires a significant amount of computational resources, a direct application of expensive numerical simulation to the design optimization would be nearly impossible. For this reason, the surrogate model has been actively used in the design optimization field [10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

A trended Kriging model withR2indicator and application to design optimization

Kwon

Choi

2015

Aerospace Science and Technology

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“…Rajagopal et al [5,6] formulated a preliminary wing design for a low-speed, long-endurance UAV as a two-step optimization problem. Their first step included a singleobjective aerodynamic optimization process, and the second step involved interactive dual-objective aerodynamic and structural optimization.…”

Section: Introductionmentioning

confidence: 99%

Wing Design Optimization of a Solar-HALE Aircraft

Lim¹,

Choi²,

Shin³

et al. 2014

International Journal of Aeronautical and Space Sciences

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We develop a preliminary design optimization procedure in this paper regarding the wing planform in a solar-powered highaltitude long-endurance unmanned aerial vehicle. A high-aspect-ratio wing has been widely adopted in this type of a vehicle, due to both the high lift-to-drag ratio and lightweight design. In the preliminary design, its characteristics need to be addressed correctly, and analyzed in an appropriate manner. In this paper, we use the three-dimensional Euler equation to analyze the wing aerodynamics. We also use an advanced structural modeling approach based on a geometrically exact one-dimensional beam analysis. Regarding the structural integrity of the wing, we determine detailed configuration parameters, specifically the taper ratio and the span length. Next, we conduct a multi-objective optimization scheme based on the response surface method, using the present baseline configuration. We consider the structural integrity as one of the constraints. We reduce the wing weight by approximately 25.3 % from that in the baseline configuration, and also decrease the power required approximately 3.4 %. We confirm that the optimized wing has sufficient flutter margin and improved static longitudinal/ directional stability characteristics, as compared to those of the baseline configuration. A preliminary design optimization procedure was developed in this paper regarding the wing planform in a solar-powered high-altitude long-endurance unmanned aerial vehicle. Due to both a high lift-to-drag ratio and a lightweight design, a high-aspect-ratio wing has been widely adopted in this type of a vehicle. Its characteristics need to be addressed correctly and analyzed in an appropriate manner in the preliminary design. In this paper, the three-dimensional Euler equation was used to analyze the wing aerodynamics. An advanced structural modeling approach based on a geometrically exact one-dimensional beam analysis was also used. Regarding the structural integrity of the wing, detailed configuration parameters were determined, specifically the taper ratio and the span length. Next, a multi-objective optimization scheme based on the response surface method was conducted using the present baseline configuration. The structural integrity was considered as one of the constraints.

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Conceptual design of UAV using Kriging based multi-objective genetic algorithm

Cited by 24 publications

References 17 publications

Wing Design Optimization for a Long-Endurance UAV using FSI Analysis and the Kriging Method

Wing Design Optimization for a Long-Endurance UAV using FSI Analysis and the Kriging Method

A trended Kriging model withR2indicator and application to design optimization

Wing Design Optimization of a Solar-HALE Aircraft

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