Spring-in prediction for carbon/epoxy aerospace composite structure

被引：41

作者：

Fiorin, M. ^{[1
]}

Seman, A. ^{[2
]}

Castanie, B. ^{[1
]}

Ali, K. M. ^{[3
]}

Schwob, C. ^{[4
]}

Mezeix, L. ^{[5
]}

机构：

[1] Univ Toulouse, UPS, INSA, ISAE,ICA,Inst Clement Ader, 135 Ave Rangueil, F-31077 Toulouse, France

[2] CTRM, Composites Technol City, Melaka 75350, Malaysia

[3] Aerospace Malaysia Innovat Ctr, Level 1,MIGHT Bldg,3517,Jalan Teknokrat 5, Cyberjaya 63000, Selangor, Malaysia

[4] Airbus Grp Singapore, 110 Seletar Aerosp View, Singapore 787562, Singapore

[5] Burapha Univ, Fac Engn, 169 Long Hard Bangsaen Rd, Chon Buri 20131, Thailand

来源：

COMPOSITE STRUCTURES | 2017年 / 168卷

关键词：

Composite structures; Spring-back; Finite element analysis; PROCESS-INDUCED DISTORTIONS; RESIDUAL-STRESSES; WARPAGE; SIMULATION; PROFILES;

D O I：

10.1016/j.compstruct.2017.02.074

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

This paper presents an engineering method to predict the spring-back of aircraft thick composite structures produced through an autoclaving process. The model previously developed by the same authors is firstly enhanced to be used in an aeronautic case study: an Airbus A350 rib. Results show that the out-of plane shear stress distribution in the interface and the through-thickness in-plane normal stress gradient of the laminate are correctly represented. The interface is shown to have only a small influence on the final deformation and therefore a global model of the structure can be proposed. Finally a methodology is proposed to predict complex structures through a global-local approach. (C) 2017 Elsevier Ltd. All rights reserved.

引用

页码：739 / 745

页数：7

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