FEA Method for the Critical Buckling Load of Aeroengine Composite Case

QI Hong-yu; WEN Wei-dong; QI Hong-yuan; WANG Lin-jiang

Volume 16 Issue 4

Oct. 2001

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Article Navigation > Journal of Aerospace Power > 2001 > 16(4): 335-339

QI Hong-yu, WEN Wei-dong, QI Hong-yuan, WANG Lin-jiang. FEA Method for the Critical Buckling Load of Aeroengine Composite Case[J]. Journal of Aerospace Power, 2001, 16(4): 335-339.

Citation:

QI Hong-yu, WEN Wei-dong, QI Hong-yuan, WANG Lin-jiang. FEA Method for the Critical Buckling Load of Aeroengine Composite Case[J]. Journal of Aerospace Power, 2001, 16(4): 335-339.

QI Hong-yu, WEN Wei-dong, QI Hong-yuan, WANG Lin-jiang. FEA Method for the Critical Buckling Load of Aeroengine Composite Case[J]. Journal of Aerospace Power, 2001, 16(4): 335-339.

Citation:

QI Hong-yu, WEN Wei-dong, QI Hong-yuan, WANG Lin-jiang. FEA Method for the Critical Buckling Load of Aeroengine Composite Case[J]. Journal of Aerospace Power, 2001, 16(4): 335-339.

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FEA Method for the Critical Buckling Load of Aeroengine Composite Case

1.
Department of Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing210016, China
2.
College of Mechanical & Electric Engineering, Northern Jiaotong University, Beijing100044, China

Received Date: 2000-11-23
Rev Recd Date: 2001-05-14
Publish Date: 2001-10-28

Abstract

Abstract

The advanced composite material as a new material has been developed since 1960′s.Now laminated continuous fiber-reinforced composite materials are being used in some primary components in aircraft structures.Using linear shell and buckling theory and modeling finite element,this paper analyses the buckling of laminated plate and composite aeroengine case.At the same time some advice on engineering design is given.
- composite material,
- aero-engine case,
- finite element analysis,
- buckling