中国航空学报(英文版)
中國航空學報(英文版)
중국항공학보(영문판)
CHINESE JOURNAL OF AERONAUTICS
2002年
4期
213-221
,共9页
复合材料叠层结构%边缘效应%翘曲修正%升阶谱
複閤材料疊層結構%邊緣效應%翹麯脩正%升階譜
복합재료첩층결구%변연효응%교곡수정%승계보
composite laminates%boundary-layer effects%sectional warping theory%hierarchical finite element methods
研究复合材料叠层结构在单轴拉伸状态下的边缘应力问题.在厚度方向,利用翘曲修正理论,推导出了叠层板三个方向的位移分布规律;在宽度方向,采用升阶谱位移模式;应用虚功原理,给出了叠层板边缘应力分析的特殊有限元模型.通过典型例题的计算表明:边缘应力计算结果与精确弹性解符合很好,还进行了收敛性的研究.本文方法的自由度度少,方法简单,优于差分法、常规有限元法,适用于解决边缘效应问题.
研究複閤材料疊層結構在單軸拉伸狀態下的邊緣應力問題.在厚度方嚮,利用翹麯脩正理論,推導齣瞭疊層闆三箇方嚮的位移分佈規律;在寬度方嚮,採用升階譜位移模式;應用虛功原理,給齣瞭疊層闆邊緣應力分析的特殊有限元模型.通過典型例題的計算錶明:邊緣應力計算結果與精確彈性解符閤很好,還進行瞭收斂性的研究.本文方法的自由度度少,方法簡單,優于差分法、常規有限元法,適用于解決邊緣效應問題.
연구복합재료첩층결구재단축랍신상태하적변연응력문제.재후도방향,이용교곡수정이론,추도출료첩층판삼개방향적위이분포규률;재관도방향,채용승계보위이모식;응용허공원리,급출료첩층판변연응력분석적특수유한원모형.통과전형례제적계산표명:변연응력계산결과여정학탄성해부합흔호,환진행료수렴성적연구.본문방법적자유도도소,방법간단,우우차분법、상규유한원법,괄용우해결변연효응문제.
The edge stress problem in composite laminates under uniform axial extension is analyzed. The displacement distribution in three directions along the thickness are derived respectively by use of the sectional warping corrective theory,and the hierarchical displacement functions are adopted in the width direction. Finally, based on the principle of virtual work,a special finite element model present results are compared with those of the existing finite difference and conventional finite element methods. It is shown that the present stresses result is in good agreement with the exact solution, and the effectiveness of the present model for analyzing free edge stresses is ascertained. The present model is simple while the degree of freedom is lower than that of the other numerical methods.