Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/160502
Title: Aerodynamic design optimization of a staggered rotors octocopter based on surrogate model
Authors: Zhu, He
Nie, Hong
Zhang, Limao
Deng, Siqiang
Wei, Xiaohui
Keywords: Engineering::Civil engineering
Issue Date: 2021
Source: Zhu, H., Nie, H., Zhang, L., Deng, S. & Wei, X. (2021). Aerodynamic design optimization of a staggered rotors octocopter based on surrogate model. Journal of Aerospace Engineering, 34(4), 04021036-1-04021036-14. https://dx.doi.org/10.1061/(ASCE)AS.1943-5525.0001280
Journal: Journal of Aerospace Engineering
Abstract: Improving aerodynamic performance with limited dimensions is becoming more important in the design of multirotor aircraft. Complex coupling interactions exist between the structural parameters and aerodynamic performance of the double-layer staggered rotor octocopter. This paper develops an integrated aerostructural design optimization approach based on a surrogate model to reduce the high computation cost of computational fluid dynamics (CFD) simulation experiments, where the surrogate model is constructed by using the Latin Hypercube design, and different approximation methods are compared. Aiming to improve the global accuracy of the surrogate model, computer-aided design (CAD) modeling and CFD simulation experiments were carried out according to the sample points designed by the Latin Hypercube method. A radial basis function surrogate model was constructed based on 63 sample points obtained with CFD simulations after comparison with other approximation methods. The optimization for aerodynamic/structural design was formulated and solved by the multiisland genetic algorithm. The results show that the surrogate model has an accurate predictive ability, and the optimal solution obtained from the optimization has a better aerodynamic performance than the samplings. Compared with the initial optimum data, the optimum solution proposed in our study could generate 102.7% more thrust, and the objective function y is improved by 105.1% according to the CFD simulation results. The approximation and optimization approach effectively reduces the cost of many CFD calculations in aircraft design and provides a global prediction for the performance of the octocopter.
URI: https://hdl.handle.net/10356/160502
ISSN: 0893-1321
DOI: 10.1061/(ASCE)AS.1943-5525.0001280
Schools: School of Civil and Environmental Engineering 
Research Centres: Nanyang Environment and Water Research Institute 
Rights: © 2021 American Society of Civil Engineers. All rights reserved.
Fulltext Permission: none
Fulltext Availability: No Fulltext
Appears in Collections:CEE Journal Articles
NEWRI Journal Articles

SCOPUSTM   
Citations 50

1
Updated on Jun 3, 2023

Web of ScienceTM
Citations 50

1
Updated on Jun 5, 2023

Page view(s)

33
Updated on Jun 6, 2023

Google ScholarTM

Check

Altmetric


Plumx

Items in DR-NTU are protected by copyright, with all rights reserved, unless otherwise indicated.