Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile

In order to improve the accuracy of calculation, it is often necessary to calculate the aerodynamic parameters of the projectile iteratively through computational fluid dynamics simulation, so the optimization efficiency is low. In this paper, a rapid aerodynamic shape ptimization method based on mu...

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Autor principal:	Zhao Xuan, Chang Sijiang, Ni Yi
Formato:	article
Lenguaje:	ZH
Publicado:	Editorial Office of Aero Weaponry 2021
Materias:	\|gliding guided projectile\|aerodynamic shape\|co-kriging surrogate model\|cfd\|genetic algorithm\|optimal design Motor vehicles. Aeronautics. Astronautics TL1-4050
Acceso en línea:	https://doaj.org/article/4b308f2369f740278cfa47d6d3046653
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id	oai:doaj.org-article:4b308f2369f740278cfa47d6d3046653
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spelling	oai:doaj.org-article:4b308f2369f740278cfa47d6d30466532021-11-30T00:13:23ZResearch on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile1673-504810.12132/ISSN.1673-5048.2021.0045https://doaj.org/article/4b308f2369f740278cfa47d6d30466532021-10-01T00:00:00Zhttps://www.aeroweaponry.avic.com/fileup/1673-5048/PDF/1636698978665-1601373203.pdfhttps://doaj.org/toc/1673-5048In order to improve the accuracy of calculation, it is often necessary to calculate the aerodynamic parameters of the projectile iteratively through computational fluid dynamics simulation, so the optimization efficiency is low. In this paper, a rapid aerodynamic shape ptimization method based on multi-fidelity surrogate model is proposed, which improves the calculation efficiency greatly under the condition of ensuring the calculation accuracy. Taking the canard shape optimization of gliding guided projectile as an example, the multi-fidelity surrogate is trained by two kinds of reliability samples to replace the computational fluid dynamics simulation process to calculate the aerodynamic parameters. According to the design requirements of maximum gliding lift-to-drag ratio, matching stability and maneuverability, the genetic algorithm is used to search for the optimal design of canard aerodynamic shape. Compared with the initial scheme, the lift-to-drag ratio of the optimized scheme are improved significantly. Compared with the results of numerical simulation, the average error of the method for the lift-to-drag ratio prediction is 1.94%, the accuracy is higher, and the amount of calculation is greatly reduced, which verifies the feasibility and effectiveness of the method.Zhao Xuan, Chang Sijiang, Ni YiEditorial Office of Aero Weaponryarticle\|gliding guided projectile\|aerodynamic shape\|co-kriging surrogate model\|cfd\|genetic algorithm\|optimal designMotor vehicles. Aeronautics. AstronauticsTL1-4050ZHHangkong bingqi, Vol 28, Iss 5, Pp 99-105 (2021)
institution	DOAJ
collection	DOAJ
language	ZH
topic	\|gliding guided projectile\|aerodynamic shape\|co-kriging surrogate model\|cfd\|genetic algorithm\|optimal design Motor vehicles. Aeronautics. Astronautics TL1-4050
spellingShingle	\|gliding guided projectile\|aerodynamic shape\|co-kriging surrogate model\|cfd\|genetic algorithm\|optimal design Motor vehicles. Aeronautics. Astronautics TL1-4050 Zhao Xuan, Chang Sijiang, Ni Yi Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile
description	In order to improve the accuracy of calculation, it is often necessary to calculate the aerodynamic parameters of the projectile iteratively through computational fluid dynamics simulation, so the optimization efficiency is low. In this paper, a rapid aerodynamic shape ptimization method based on multi-fidelity surrogate model is proposed, which improves the calculation efficiency greatly under the condition of ensuring the calculation accuracy. Taking the canard shape optimization of gliding guided projectile as an example, the multi-fidelity surrogate is trained by two kinds of reliability samples to replace the computational fluid dynamics simulation process to calculate the aerodynamic parameters. According to the design requirements of maximum gliding lift-to-drag ratio, matching stability and maneuverability, the genetic algorithm is used to search for the optimal design of canard aerodynamic shape. Compared with the initial scheme, the lift-to-drag ratio of the optimized scheme are improved significantly. Compared with the results of numerical simulation, the average error of the method for the lift-to-drag ratio prediction is 1.94%, the accuracy is higher, and the amount of calculation is greatly reduced, which verifies the feasibility and effectiveness of the method.
format	article
author	Zhao Xuan, Chang Sijiang, Ni Yi
author_facet	Zhao Xuan, Chang Sijiang, Ni Yi
author_sort	Zhao Xuan, Chang Sijiang, Ni Yi
title	Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile
title_short	Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile
title_full	Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile
title_fullStr	Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile
title_full_unstemmed	Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile
title_sort	research on the rapid aerodynamic shape optimization of canards of gliding guided projectile
publisher	Editorial Office of Aero Weaponry
publishDate	2021
url	https://doaj.org/article/4b308f2369f740278cfa47d6d3046653
work_keys_str_mv	AT zhaoxuanchangsijiangniyi researchontherapidaerodynamicshapeoptimizationofcanardsofglidingguidedprojectile
_version_	1718406861699416064

Research on the Rapid Aerodynamic Shape Optimization of Canards of Gliding Guided Projectile

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