GENERAL PANEL SIZING COMPUTER CODE AND ITS APPLICATION TO COMPOSITE STRUCTURAL PANELS

被引：43

作者：

ANDERSON, MS ^{[1
]}

STROUD, WJ ^{[1
]}

机构：

[1] NASA,LANGLEY RES CTR,DIV STRUCT & DYNAM,STRUCT MECH BRANCH,HAMPTON,VA 23665

来源：

AIAA JOURNAL | 1979年 / 17卷 / 08期

关键词：

D O I：

10.2514/3.61242

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A computer code for obtaining the dimensions of optimum (least mass) stiffened composite structural panels is described. The procedure, which is based on nonlinear mathematical programming and a rigorous buckling analysis, is applicable to general cross sections under general loading conditions causing buckling. A simplified method of accounting for bow-type imperfections is also included. Design studies in the form of structural efficiency charts for axial compression loading are made with the code for blade and hat stiffened panels. The effects on panel mass of imperfections, material strength limitations, and panel stiffness requirements are also examined. Comparisons with previously published experimental data show that accounting for imperfections improves correlation between theory and experiment. © 1979 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

引用

页码：892 / 897

页数：6