Particle Swarm Optimization of Aerodynamic Shapes with Nonuniform Shape Parameter–Based Radial Basis Function

Xia, Chenchao; Chen, Weifang

doi:10.1061/(asce)as.1943-5525.0000686

Cited by 18 publications

(8 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Taking the optimization process of the shape parameter for the RBF surrogate model based on LOOCV as an example, a nonuniform shape parameter, randomly based on the selecting strategy for different sample points was proposed as follows [42],…”

Section: ) Parameter Optimization For Surrogate Modelsmentioning

confidence: 99%

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

et al. 2021

View full text Add to dashboard Cite

Multi-objective optimization of aerodynamic configuration for a tandem-wing unmanned aerial vehicle (UAV) via a surrogate model is appropriate in the primary stages of aircraft design. This study presents an adaptive sequential sampling strategy, which takes into account the principle of entropy rank and selection pooling based on a sigmoid function (ESP), in order to save time and construct a surrogate model database with considerable approximation accuracy. The entire procedure of optimization is divided into four parts, involving problem formulation for design variables and objectives, database construction for the surrogate model, multi-objective optimization with the surrogate models, and ESP adaptive sequential sampling to update the database. Firstly, a comparative study of the different surrogate models is carried out to assess their approximation performance. This verifies that the radial basis function (RBF) surrogate model outperforms the other models across the board. Then, we conduct two tests with typical mathematical problems to validate the effectiveness and applicability of the proposed method. We also develop a multiobjective optimization of the aerodynamic configuration for a tandem-wing UAV, aiming to maximize the lifting coefficient at the ascent (C Lascent ) and the lift-drag ratio (K cruise ) during the cruise. In this case, the RBF surrogate model is proven more suitable than the other common methods to replace the real values calculated by the non-planar vortex-lattice method (VLM) during the process of optimization. Furthermore, a comparison with large minimal distance (LMD) sequential sampling and disposable Latin hypercube sampling (LHS) is carried out alongside the optimization. These results show that the approximation precision achieved using ESP strategy is greater, highlighting the superiority of the ESP adaptive sequential sampling strategy in reducing the number of samples and raising the approximation accuracy. Finally, after the refinement of the database, an optimal Pareto front set is obtained to guide the primary design of the aerodynamic configuration for the tandem-wing UAV. Then, it is verified that the selected trade-off optimal design point has a better aerodynamic performance than the initial reference point, improving C Lascent and K cruise by 6.44% and 10.85%, respectively.

show abstract

Section: ) Parameter Optimization For Surrogate Modelsmentioning

confidence: 99%

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

et al. 2021

View full text Add to dashboard Cite

show abstract

“…AUSMPWþ is the improved version of the AUSMPW scheme and is developed to increase the accuracy and computational efficiency without compromising robustness, which is also popular in aerodynamic heating calculation (Xia et al, 2016). AUSMPWþ is tested from Mach 22 to 32 with Definition 1 and 3 of sound speed.…”

Section: Performance Of Ausmpwþmentioning

confidence: 99%

Study on the performance of spatial discretization schemes for hypersonic flow

Huang

2018

HFF

View full text Add to dashboard Cite

Purpose With the continuous increase of space activities and insight into space exploration, the velocity of near space hypersonic vehicles becomes higher and higher, which leads to the aerothermodynamic phenomenon getting worse around a vehicle; therefore, the exploration of numerical scheme applicability is essential for hypersonic flow simulations. Design/methodology/approach The implicit finite volume schemes are derived from axisymmetric Navier–Stokes equations for chemical equilibrium flow and programmed in Fortran. Taking the atmosphere at 30 km as an example, the performance of spatial discretization schemes such as AUSMPW and AUSMPW+ are analyzed in a range of Mach numbers from 17 to 32. Findings The AUSMPW scheme appears pressure jump near the stagnation if the Mach number is over 18, but AUSMPW+ scheme shows better performance in comparison. Originality/value This study will help the aerothermodynamic design in near space hypersonic vehicles.

show abstract

“…Optimum değeri, problemin ve kullanılan RTF'nin türünden, sınır koşullarından, nokta dağılımından ve nokta sayısından oldukça etkilenmektedir. Dolayısıyla, optimum değerinin belirlenmesi günümüzde üzerinde araştırma yapılan konulardan biridir [15][16][17].…”

Section: Introductionunclassified

Ağsız Yöntem Uygulamaları için Trigonometri Tabanlı Radyal Özelliğe Sahip Yeni Bir Temel Fonksiyon

Altınkaynak

2020

International Journal of Advances in Engineering and Pure Sciences

View full text Add to dashboard Cite

Bu çalışmada, ağsız yöntemler için radyal özelliğe sahip yeni bir temel fonksiyon önerilmiştir. Önerilen fonksiyon, iki boyutta, dört farklı problemde, ağsız yöntemlerde sıklıkla kullanılan Ters Multikuadrik ve Gauss fonksiyonlarıyla birlikte test edilmiştir. Test problemlerinin üç tanesi 2. mertebeden mühendislik problemlerini içerirken son test problemi 4. mertebeden bir mühendislik problemi uygulaması olmuştur. 2. mertebeden test problemlerinde farklı sınır koşulları ve problem türleri incelenmiştir. Yapılan sayısal deneyler, önerilen fonksiyonun Ters Multikuadrik ve Gauss fonksiyonlarına kıyasla daha az nokta sayılarında benzer mertebedeki hatalara ulaşabildiğini göstermiştir. Ayrıca nokta sayısının artmasıyla aynı mertebedeki hatalar için kullanılabilecek şekil/ölçek parametresinin () diğer iki fonksiyona kıyasla daha geniş bir aralıkta seçilebildiği gösterilmiştir. Dolayısıyla, önerilen fonksiyon, ağsız yöntem uygulamalarında bir alternatif olarak kullanılabilecektir.

show abstract

Particle Swarm Optimization of Aerodynamic Shapes with Nonuniform Shape Parameter–Based Radial Basis Function

Cited by 18 publications

References 28 publications

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

An Adaptive Sequential Sampling Strategy-Based Multi-Objective Optimization of Aerodynamic Configuration for a Tandem-Wing UAV via a Surrogate Model

Study on the performance of spatial discretization schemes for hypersonic flow

Ağsız Yöntem Uygulamaları için Trigonometri Tabanlı Radyal Özelliğe Sahip Yeni Bir Temel Fonksiyon

Contact Info

Product

Resources

About