Full-Text Search:
Home|Journal Papers|About CNKI|User Service|FAQ|Contact Us|中文
《Acta Materiae Compositae Sinica》 2017-01
Add to Favorite Get Latest Update

Application of buckling/post-buckling analysis for composite stiffened panels

SONG Gang;CUI Degang;DONG Lijun;Shool of Aeronautic Science and Engineering,Beihang University;Science and Technology Commission,AVIC;Chinese Aeronautical Establishment;  
The problem of stability for wing surface structure made of composite stiffened panels was studied,and stability safety margin of stiffened panels under compression and shear loads was analyzed.A method of calculating buckling and post-buckling loading capacity of composite stiffened panels was presented and used to check the structural stability under complex loading conditions.The object for check is an optimized wing made of composites which satisfies the requirement of strength,stiffness and manufacture process.The internal force distribution of the wing under various load cases was obtained by MSC.NASTRAN,and the stability loading capacity of each skin block was acquired by the method proposed in this paper.Then the buckling and post-buckling safety margin calculation principles for composite laminated plates under complex loading were given to verify whether the stiffened panels of the optimized wing meet the stability design requirements.This method can be integrated into a structure optimization platform as a constraint.
【Fund】: 国家自然科学基金(91330206)
【CateGory Index】: V214.8
Download(CAJ format) Download(PDF format)
CAJViewer7.0 supports all the CNKI file formats; AdobeReader only supports the PDF format.
©2006 Tsinghua Tongfang Knowledge Network Technology Co., Ltd.(Beijing)(TTKN) All rights reserved