期刊文献+

基于噪声激励及响应和模态分析的风洞引射器结构优化设计 被引量:1

Wind Tunnel Ejector Structural Optimization Design Based on Noise Excitation and Response and Modal Analysis
下载PDF
导出
摘要 为弄清噪声激励的大小、分布情况以及蒙皮响应(振动)的量值,对1.2m风洞引射器蒙皮噪声激励及响应测量实验和基于Abaqus软件模态进行优化设计。给出数据采集系统结构,介绍具体测量方法,并与现有结构(厚5 mm)和优化设计方案(厚8 mm)的有限元分析结果进行对比分析,得到结构优化方案参考数据。结果表明:该设计能有效避开气流脉动压力变化引起400、409、460、516、561、598Hz的结构剧烈振动频率,提高结构的刚度和强度,提升增量引射器的抗疲劳性能。 In order to find out the magnitude and distribution of noise excitation and the magnitude of skin response(vibration),the experiment of noise excitation and response measurement of ejector skin in 1.2 m wind tunnel and the optimization design based on Abaqus software mode were carried out.The structure of data acquisition system is given,measurement method is introduced,compared with the finite element analysis results of the existing structure(5 mm thick)and the optimized design scheme(8 mm thick).The reference data of structural optimization scheme are obtained.The results show that the design can effectively avoid the frequency of structure violent vibration caused by the change of air pulsation pressure:400,409,460,516,561,598 Hz,improve the rigidity and strength of the structure,improve the fatigue resistance of incremental ejector.
作者 夏明主 刘奇 Xia Mingzhu;Liu Qi(High Speed Institute,China Aerodynamics Research&Development Center,Mianyang 622661,China)
出处 《兵工自动化》 2020年第10期66-70,共5页 Ordnance Industry Automation
关键词 风洞 Abaques 噪声 模态分析 wind tunnel Abaques noise modal analysis
  • 相关文献

参考文献3

二级参考文献16

  • 1曹金凤,王旭春,孔亮.Python语言在Abaqus中的应用.北京:机械工业出版社,2011.
  • 2蔺法鹏.基于ABAQUS参数化二次开发的多管火箭炮建模与仿真研究[D].南京:南京理工大学,2011.
  • 3陈学叉.基于ABAQUS二次开发的多管火箭炮参数化建模与仿真研究[D].南京:南京理工大学,2012.
  • 4Sellers W L III, Meyers J F, Hepner T E. LDV surveys over a fighter model at moderate to high angles of attack [R]. SAE-88-1448,1988.
  • 5Moss S W, Cole S R, Doggett R V Jr. Some subsonic and transonic buffet characteristics of the twin vertical-tails of a fighter airplane configuration[R]. AIAA-91-1049, 1991.
  • 6Shah G H. Wind tunnel investigation of aerodynamic and tail buffet characteristics of leading-edge extension modifications to the F/A-18[R]. AAIA-91-2889,1991.
  • 7Healey M D. F/A-18 E/F vertical tail buffet design, analysis and test[R]. AIAA-2003-1886, 2003.
  • 8Pettit C L, Banford M, Brown D, et al. Full-scale wind-tunnel pressure measurements on an F/A-18 tail during buffet[J]. Journal of Aircraft, 1996, 33(6):1148-1156.
  • 9Dougherty N S. Influence of wind tunnel noise on the location of boundary-layer transition on a slender cone at Mach numbers from 0.2 to 5.5[R]. AEDC-TR-78-44, 1980.
  • 10吴东亚,邢宏光,崔军,邵思杰.基于有限元的某型坦克炮身管模态分析[J].科技导报,2008,26(23):44-47. 被引量:7

同被引文献6

引证文献1

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部