Design of High Altitude Propeller Using Multilevel Optimization

doi:10.1142/S021987621950004X

CORC > 力学研究所 > 中国科学院力学研究所 > 非线性力学国家重点实验室

	Design of High Altitude Propeller Using Multilevel Optimization
	Liu XQ 1; He WL 1; Wei FM(魏凤美)2
刊名	INTERNATIONAL JOURNAL OF COMPUTATIONAL METHODS
	2020-05-01
卷号	17 期号:4 页码:32
关键词	High altitude propeller multilevel optimization blade element momentum theory MIGA NSGA-II CFD simulation
ISSN号	0219-8762
DOI	10.1142/S021987621950004X
通讯作者	Liu, Xinqiang(buaa_lxq@163.com)
英文摘要	An improved D'Angelo optimization framework based on the surrogate model and optimization algorithm is proposed to design and optimize a new high altitude propeller which is applied to the propulsion system of the stratospheric aircraft. The framework adopts a multilevel optimization strategy to determine a high efficiency and light weight propeller. The aerodynamic characteristics of S1223 airfoil are calculated by Computational Fluid Dynamics (CFD) method. The aerodynamic performance of the D'Angelo propeller which is obtained by the first-level optimization is predicted by Blade element momentum (BEM) theory. Then the D'Angelo propeller chord and twist angle, which are regarded as the initial conditions of the second-level optimization, are optimized to achieve the maximum efficiency by Multi-island genetic algorithm (MIGA). In addition, the non-dominated sorting genetic algorithm II (NSGA-II) is applied to maximize the propeller efficiency and minimize the propeller weight. And the Pareto frontier solutions about the efficiency and the blade area are obtained by NSGA-II. What is more, the aerodynamic characteristics of the D'Angelo propeller, the optimization propeller by MIGA, and the optimization propeller by NSGA-II are calculated by CFD simulation and compared with BEM results. It is shown that the CFD results are in fair agreement with BEM results and the aerodynamic performance of the NSGA-II propeller is prior to the MIGA propeller and is close to the D'Angelo propeller. Besides, the NSGA-II propeller is the lightest among them and can satisfy the cruise requirements of the high altitude propeller.
分类号	Q3
WOS关键词	BLADE ; VALIDATION
WOS研究方向	Engineering ; Mathematics
语种	英语
WOS记录号	WOS:000500190300011
其他责任者	Liu, Xinqiang
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/81212]
专题	力学研究所_非线性力学国家重点实验室
作者单位	1.Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China; 2.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Liu XQ,He WL,Wei FM. Design of High Altitude Propeller Using Multilevel Optimization[J]. INTERNATIONAL JOURNAL OF COMPUTATIONAL METHODS,2020,17(4):32.
APA	Liu XQ,He WL,&魏凤美.(2020).Design of High Altitude Propeller Using Multilevel Optimization.INTERNATIONAL JOURNAL OF COMPUTATIONAL METHODS,17(4),32.
MLA	Liu XQ,et al."Design of High Altitude Propeller Using Multilevel Optimization".INTERNATIONAL JOURNAL OF COMPUTATIONAL METHODS 17.4(2020):32.