Three dimensional aeroelastic analyses considering free-play nonlinearity using computational fluid dynamics/computational structural dynamics coupling

doi:10.1016/j.jsv.2020.115896

CORC > 力学研究所 > 中国科学院力学研究所 > 流固耦合系统力学重点实验室(2012-)

	Three dimensional aeroelastic analyses considering free-play nonlinearity using computational fluid dynamics/computational structural dynamics coupling
	Huang CD(黄程德); Huang J(黄杰); Song X(宋鑫); Zheng GN(郑冠男); Yang GW(杨国伟)
刊名	JOURNAL OF SOUND AND VIBRATION
	2021-03
卷号	494 页码:115896
关键词	Free-play Transonic dip Flutter Limit cycle oscillation Aeroelastic
ISSN号	0022-460X
DOI	10.1016/j.jsv.2020.115896
英文摘要	Most of the previous studies on free-play aeroelasticity were based on the linear aerodynamic theory, which cannot consider the aerodynamic nonlinear effects. This paper proposes a framework of computational fluid dynamics/computational structural dynamics (CFD/CSD) coupling approach that can deal with the three dimensional aeroelastic problems with both the free-play nonlinearity and the aerodynamic nonlinearity. The fictitious mass method is used to construct the reduced structural equations of motion and the switching point is detected using the bisection method. The adaptive time step obtained by the bisection method is returned to the CFD solver so that both the structural and the fluid equations are integrated using the same time step. An all-movable wing with free-play at the root is considered for numerical studies. Results demonstrate the CFD/CSD coupling method can predict the stable limit cycle oscillation (LCO) effectively. The initial condition study shows that the LCO behavior is subcritical and the hysteresis response can be predicted in time domain effectively by the presented method. The viscous effect is shown to increase the LCO boundary and shift the LCO amplitude to a larger velocity in transonic regime. The LCO boundary is determined from subsonic to transonic Mach numbers. The transonic dip in LCO boundary is found by the CFD/CSD coupling method, but the equivalent linearization with doublet lattice method fails to predict this phenomenon. From the results of this study, the LCO boundary is shown to be 43.5% below the flutter boundary at most. (C) 2020 Elsevier Ltd. All rights reserved.
学科主题	Acoustics ; Engineering, Mechanical ; Mechanics
分类号	二类/Q1
语种	英语
WOS记录号	WOS:000609162900012
资助机构	National Natural Science Foundation of China [11702298, 11672303]
其他责任者	Yang, GW (corresponding author), Chinese Acad Sci, LMFS Inst Mech, Beijing 100190, Peoples R China. ; Yang, GW (corresponding author), Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China.
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/90247]
专题	力学研究所_流固耦合系统力学重点实验室(2012-)
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, LMFS Inst Mech, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Huang CD,Huang J,Song X,et al. Three dimensional aeroelastic analyses considering free-play nonlinearity using computational fluid dynamics/computational structural dynamics coupling[J]. JOURNAL OF SOUND AND VIBRATION,2021,494:115896.
APA	黄程德,黄杰,宋鑫,郑冠男,&杨国伟.(2021).Three dimensional aeroelastic analyses considering free-play nonlinearity using computational fluid dynamics/computational structural dynamics coupling.JOURNAL OF SOUND AND VIBRATION,494,115896.
MLA	黄程德,et al."Three dimensional aeroelastic analyses considering free-play nonlinearity using computational fluid dynamics/computational structural dynamics coupling".JOURNAL OF SOUND AND VIBRATION 494(2021):115896.