Modal density of composite honeycomb sandwich panels

被引：65

作者：

Renji, K

Nair, PS

Narayanan, S

机构：

[1] INDIAN INST TECHNOL,DEPT APPL MECH,MADRAS 600036,TAMIL NADU,INDIA

[2] ISRO,SATELLITE CTR,STRUCTURES GRP,BANGALORE 560017,KARNATAKA,INDIA

来源：

JOURNAL OF SOUND AND VIBRATION | 1996年 / 195卷 / 05期

关键词：

D O I：

10.1006/jsvi.1996.0456

中图分类号：

O42 [声学];

学科分类号：

070206 ; 082403 ;

摘要：

Honeycomb sandwich panels with composite face sheets are widely used in spacecraft applications. It is necessary to obtain the modal density of such panels to study their behaviour under acoustic excitation. The governing differential equation, with consideration of the shear flexibility of the core, is derived. From this equation the expression for the modal density is derived. Experimental results for a typical panel are also presented. These results match well with those obtained from theory. (C) 1996 Academic Press Limited

引用

页码：687 / 699

页数：13

共 12 条

[1] SOME COMMENTS ON THE EXPERIMENTAL-DETERMINATION OF MODAL DENSITIES AND LOSS FACTORS FOR STATISTICAL ENERGY ANALYSIS APPLICATIONS [J].