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CORC

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Time-Domain Aeroelasticity Analysis by a Tightly Coupled Fluid-Structure Interaction Methodology 期刊论文
APPLIED SCIENCES-BASEL, 12, 2021, 卷号: 11, 页码: 5389
作者:  Liu ZY(刘忠宇);  Nie XY(聂雪媛);  Zheng GN(郑冠男);  Yang GW(杨国伟)
收藏  |  浏览/下载：7/0  |  提交时间：2022/10/25
Efficient aeroelastic reduced order model with global structural modifications 期刊论文
AEROSPACE SCIENCE AND TECHNOLOGY, 2018, 卷号: 76, 页码: 1-13
作者:  Chen, Gang;  Li, Dongfeng;  Zhou, Qiang;  Da Ronch, Andrea;  Li, Yueming
收藏  |  浏览/下载：3/0  |  提交时间：2019/11/26
CBS finite element method with approximate boundary conditions for panel flutter 期刊论文
Hangkong Dongli Xuebao/Journal of Aerospace Power, 2015, 卷号: 30, 期号: [db:dc_citation_issue], 页码: 2848-2856
作者:  Li, Kai-Lun;  Wei, Yun;  Zhang, Mei-Lin;  Zhang, Jia-Zhong
收藏  |  浏览/下载：4/0  |  提交时间：2019/12/02
Experimental and computational investigation of a full aircraft flutter at transonic speeds 会议论文
Bristol, United kingdom, June 24, 2013 - June 27, 2013
作者:  Qian W;  Yang GW(杨国伟);  Luo JG;  Yang R;  Zhang GJ
收藏  |  浏览/下载：18/0  |  提交时间：2018/11/08
鲁棒稳定性分析及其在飞行颤振试验中的应用 期刊论文
飞行力学, 2013, 卷号: 31, 页码: 372-375
作者:  王东森;  吴志刚;  周友明
收藏  |  浏览/下载：2/0  |  提交时间：2020/01/06
A strong coupled CFD-CSD method on computational aeroelastity (EI CONFERENCE) 会议论文
2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China
Xi R.; Jia H.
收藏  |  浏览/下载：61/0  |  提交时间：2013/03/25
In this paper  a strong coupled CFD-CSD method is developed to simulate the aeroelastic phenomena. The CFD solver is based on the finite-volume algorithm for the Navier-Stokes equations on unstructured grid. The CSD solver solves the aeroelastic governing equations in the modal space. Their coupling is realized by a dual-time method. The spring-based smoothing method is adopted to deform and regenerate the aerodynamic grid. Two test cases are selected to validate the authors' method for static and dynamic aeroelastity .The results of the simulation for the static aeroelastic problems of a missile wing show that the Lift Coefficient and Drag Coefficient are severally 7% and 5% lower than those don't consider the elasticity of the wing. The results for the flutter boundary prediction of the AGARD 445.6 wing have been proved much closer to the experiment than using the DLM. This method can describe the effects of fluid viscosity more exactly for highly nonlinear transonic flight conditions. The calculation has proved reliable in the subsonic regime  but not accurate enough in the supersonic regime. 2011 IEEE.  
Flutter prediction in turbomachinery with energy method 期刊论文
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, 2011, 卷号: 225, 页码: 995-1002
作者:  Zhang, X. W.;  Wang, Y. R.;  Xu, K. N.
收藏  |  浏览/下载：3/0  |  提交时间：2020/01/06
Analysis of hydroelastic instabilities of rectangular parallel-plate assemblies 期刊论文
American Society of Mechanical Engineers, Pressure Vessels and Piping Division (Publication) PVP, 2000, 卷号: 122, 期号: 4, 页码: 502-508
作者:  Guo, CQ;  Paidoussis, MP*
收藏  |  浏览/下载：3/0  |  提交时间：2019/12/27

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