Sage Journals: Discover world-class research

Abstract

The metallic airplane structure fuselage design is characterized by skin, frames, stiffeners, and attachments. In most airplanes, the attachments between these components are made by rivets. The influence of the attachments in the panel behavior under diagonal tension can be verified in the metallic Wagner beam. For stiffened composite panels, like metallic Wagner beams, there is insufficient data about attachment design. In order to design and build lightweight composite structures, the analyst must consider different ways in which the skin is connected to the stiffeners and frames. Therefore, the objective of this paper is to investigate different conceptions of a real-reinforced composite panel used in the aeronautical industry. Experimental and numerical results for strains showed good agreement. The finite element model and the criteria used in the failure analysis are also presented. Comparisons between different panel configurations are made, and conclusions are drawn about attachment efficiency.

Keywords

Composite panel design postbuckling attachment conception co-cured secondary bonding panel failure load

Get full access to this article

View all access options for this article.

References

Polland DR, et al. Global cost and weight evaluation of fuselage side panel design concepts. NASA Contractor Report 4730, LRC, April 1997.

Wilmes H, Kolesnikov B, Fink A, et al. New design concepts for a CFRP fuselage. German Aerospace Center (DLR), Institute of Structures Mechanics, 2001.

Matsui N and Sato K. Research work of the all-composite fuselage structure. In: Proceedings of 14th international conference on composite materials – ICCM14, Vol. 1, ID 0900, July 2003, p.270.

Bisagni C, Abramovich H and Weller T. Buckling behavior of composite laminated stiffened panels under combined shear and axial compression. In: 46th AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics and materials conference, April 2005, pp.18–21. Austin, Texas: American Institute of Aeronautics and Astronautics (AIAA) Publisher.

Romeo

Frulla

. Post-buckling behaviour of graphite/epoxy stiffened panels with initial imperfections subjected to eccentric biaxial compression loading. Int J Non-Linear Mech 1997; 32: 1017–1033.

Degenhardt

Rolfes

Zimmermann

. COCOMAT – improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse. Compos Struct 2006; 73: 175–178.

Degenhardt R and Tessmer J. Improved design scenario for composite airframe structures. In: 48th AIAA/ASME/ASCE/AHS/ASC, Honolulu, Hawaii, April 2007.

Wagner H. Structures of thin sheet metal, their design and construction. NACA (National Advisory Committee for Aeronautics) Memo, 1928, p.490.

Bruhn EF. Analysis and design of flight vehicle structures. Tri-State Offset Company, USA, 1973.

10.

Arakaki FK and Gavazzi A. Composite stiffened panel post buckling test proposal. In: EMRAER Technical Report DT1CSZ013 Rev, November 2007.

11.

MSC Nastran 2008 r1. Quick Reference Guide. MSC Software Corporation, Santa Ana, CA.

12.

Dávila CG, Camanho PP and Turon A. Cohesive elements for shells. NASA/TP-2007-214869, April 2007.

13.

Hashin

. Failure criteria for unidirectional fiber composites. J Appl Mech 1980; 47: 329–334.

14.

ABAQUS 6.10-EF. Getting started, interactive edition. 3DS Dassault Systèmes, 2010.

15.

Benzeggagh

Kenane

. Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus. Compos Sci Technol 1996; 56: 439–449.

16.

Kim

Choi

Kweon

. Manufacture and performance evaluation of the composite hat-stiffened panel. Compos Struct 2010; 92: 2276–2284.

17.

CMH-17-3G. Composite materials handbook, Vol. 3: Polymer matrix composites materials usage, design, and analysis. Wichita, Kansas: SAE International Publication, 2012.

18.

Cândido

Rezende

Donadon

. Fractografia de compósito estrutural aeronáutico submetido ao ensaio de tenacidade à fratura interlaminar em modo II. Polímeros 2014; 24: 65–71.

19.

Bardis J and Kedward K. Effects of surface preparation on long-term durability of composite adhesive bonds. DOT/FAA/AR-01/8, April 2001.

20.

Ata

Soutis

. Application of cohesive zone elements in damage analysis of composites: strength prediction of a single-bolted joint in CFRP laminates. Int J Non-Linear Mech 2014; 66: 96–104.

21.

Flatscher

Wolfahrt

Pinter

. Simulations and experiments of open hole tension tests – assessment of intra-ply plasticity, damage, and localization. Compos Sci Technol 2012; 72: 1090–1095.

22.

Camanho

Matthews

. Delamination onset prediction in mechanically fastened joints in composite laminates. J Compos Mater 1999; 33: 906–927.

Composite-stiffened panel design under shear postbuckling behavior

Abstract

Keywords

Get full access to this article

References