Simultaneous cost and weight minimization of composite-stiffened panels under compression and shear

被引:42
作者
Kassapoglou, C
机构
关键词
cost and weight optimization minimization; compression and shear; stiffened panel;
D O I
10.1016/S1359-835X(96)00141-8
中图分类号
T [工业技术];
学科分类号
08 ;
摘要
An approach is presented to determine the part configuration that minimizes the cost and weight of composite-stiffened panels under combined compression and shear loads. The stiffened panel is designed so that no overall, bay, or stiffener buckling occurs under the applied loads. Skin and stiffener material failure conditions and manufacturing constraints are also imposed. The stiffened panel cost and weight are minimized for a variety of stiffener cross-sectional shapes. A set of near-optimum (in a Pareto sense) configurations is determined. The final optimum configuration is selected from this set by minimizing a weight and cost penalty function. (C) 1997 Elsevier Science Limited.
引用
收藏
页码:419 / 435
页数:17
相关论文
共 16 条
[1]  
BRUHN E.F., 1973, Analysis and Design Of Flight Vehicle Structures"
[2]  
BUSHNELL D, 1993, P 34 AIAAASMEASCEAHS, P2194
[3]  
GUTOWSKI T, 1994, COMPOS MANUF, V5, P231, DOI DOI 10.1016/0956-7143(94)90138-4
[4]   THE BUCKLING PERFORMANCE OF COMPOSITE STIFFENED PANEL STRUCTURES SUBJECTED TO COMBINED INPLANE COMPRESSION AND SHEAR LOADING [J].
LOUGHLAN, J .
COMPOSITE STRUCTURES, 1994, 29 (02) :197-212
[5]  
MABSON GE, 1994, P 35 AIAAASMEASASCE
[6]  
MCGETTRICK M, 1993, P 10 DODNASAFAA C FI, V1, pR5
[7]   THE ULTIMATE STRENGTH OF ALUMINUM-ALLOY FORMED STRUCTURAL SHAPES IN COMPRESSION [J].
NEEDHAM, RA .
JOURNAL OF THE AERONAUTICAL SCIENCES, 1954, 21 (04) :217-229
[8]  
OLSON JT, 1991, P 10 DODNASAFAA C FI
[9]  
PARETO B, 1896, COURS EC POLITIQUE
[10]   BUCKLING AND VIBRATION OF FINITE-LENGTH COMPOSITE PRISMATIC PLATE STRUCTURES WITH DIAPHRAGM ENDS .2. COMPUTER-PROGRAMS AND BUCKLING APPLICATIONS [J].
PESHKAM, V ;
DAWE, DJ .
COMPUTER METHODS IN APPLIED MECHANICS AND ENGINEERING, 1989, 77 (03) :227-252