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CORC

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An Architecture and Joint Robot Group for a Long-Range Dynamic Combinatorial Flying Complex Based on Cloud Sea Computing in 5G OGCE 会议论文
Changsha, Hunan, China, September 24-26, 2021
作者:  Lv Z(吕志);  Yuan MZ(苑明哲);  Lv Y(吕毅);  Wang ZF(王忠锋)
收藏  |  浏览/下载：15/0  |  提交时间：2022/04/13
基于模态综合法实现某导弹弹翼试验模态边界的转化 期刊论文
中国科技论文, 2018, 卷号: 13, 期号: 16, 页码: 1885-1888
作者:  冯松;  葛永娇;  高博;  戴晨
收藏  |  浏览/下载：64/0  |  提交时间：2019/01/03
Application of Free Interface Modal Synthesis Method on Modal Test Boundary Transformation of One Missile Wing 会议论文
Phuket, THAILAND, 2017-08-06
作者:  Feng, Song;  He, Yun;  Wen, Yan;  Feng, S (reprint author), XiAn Inst Opt & Precis Mech, Xian, Shaanxi, Peoples R China.
收藏  |  浏览/下载：16/0  |  提交时间：2018/04/03
导弹大迎角下非线性诱导滚转力矩数值研究 期刊论文
2016, 2016
徐柯哲; 张宇飞; 陈海昕; 李斌; 刘仙名; 符松; XU Kezhe; ZHANG Yufei; CHEN Haixin; LI Bin; LIU Xianming; FU Song
收藏  |  浏览/下载：9/0
舵机折叠舵展开性能分析及试验 学位论文
硕士: 中国科学院大学, 2015
作者:  刘断尘
收藏  |  浏览/下载：38/0  |  提交时间：2016/04/11
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：62/0  |  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.  

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