Numerical Modelling of a Composite Fuselage Manufactured by Liquid Resin Infusion


Article Preview

FUSCOMP (FUSelage COMPosite) is a Research & Development program which has received the label from the Aerospace Valley competitiveness cluster. It will lead to a test of a composite fuselage demonstrator manufactured by the Liquid Resin Infusion (LRI) process. LRI is based on the moulding of high performance composite parts by infusing liquid resin on dry fibers instead of prepreg fabrics. The study of this proof of concept is based on the TBM 850 airframe, a pressurized business turboprop aircraft currently produced by DAHER-SOCATA. Technical achievements will concern numerical methods and finite elements analysis to be used for the modelling of this aircraft composite fuselage structure. Actual industrial projects face composite integrated structure issues as a number of structures (stiffeners,...) are more and more integrated onto the skins of aircraft fuselage. Indeed the main benefit of LRI is to reduce assembly steps which lead to cycle time gain and thus cost reduction. In particular, infusing components and sub-components at the same time avoids riveting parts altogether. However it is necessary to validate the dimensioning of the studied composite structure.



Edited by:

Moussa Karama






A. Perret et al., "Numerical Modelling of a Composite Fuselage Manufactured by Liquid Resin Infusion", Applied Mechanics and Materials, Vol. 62, pp. 49-56, 2011

Online since:

June 2011




[1] R. Zimmermann and R. Rolfes. Posicoss - improved postbuckling simulation for design of fibre composite stiffened fuselage structures. Composite Structures, 73: 171–174, (2006).

DOI: 10.1016/j.compstruct.2005.11.041

[2] R. Degenhardt, R. Rolfes, R. Zimmermann, and K. Rohwer. Cocomat material exploitation of composite airframe structures simulation of postbuckling and collapse. Composite Structures, 73: 175–178, (2006).

DOI: 10.1016/j.compstruct.2005.11.042

[3] J. Bertolini. Contribution à l'analyse expérimentale et théorique des ruptures de structures composites en post-flambement par décollement des raidisseurs. PhD thesis, UPS, (2008).

[4] A.C. Orifici, S.A. Shah, I. Herszberg, A. Kotler, and T. Weller. Failure analysis in postbuckled composite t-sections. Composite Structures, 86: 146–153, (2008).

DOI: 10.1016/j.compstruct.2008.03.022

[5] L. Fielder, S. Barré, J.I. Molina, and C. Voto. Tango composite fuselage platform. SAMPE Journal, 39(1): 57–63, January/February (2003).

[6] 2nd conference on buckling and postbuckling behaviour of composite laminated shell structures with cocomat workshop. September (2008).

[7] J.E. Herencia, P.M. Weaver, and M.I. Friswell. Optimization of long anisotropic laminated fiber composite panels with t-shaped stiffeners. AIAA Journal, 45(10): 2497–2509, October (2007).

DOI: 10.2514/1.26321

[8] R. Zimmermann, H. Klein, and A. Kling. Buckling and postbuckling of stringer stiffened fibre composite curved panels - tests and computations. Composite Structures, 73: 150–161, (2006).

DOI: 10.1016/j.compstruct.2005.11.050

[9] K. Mason. Autoclave quality outside the autoclave? High Performance Composites, March (2006).

[10] L.W. Davies, R.J. Day, D. Bond, A. Nesbitt, J. Ellis and E. Gardon. Effect of cure cycle heat transfer rates on the physical and mechanical properties of an epoxy matrix composite. Composites Science and Technology, 67: 1892–1899, (2007).

DOI: 10.1016/j.compscitech.2006.10.014

[11] M.G. Bader. Selection of composite materials and manufacturing routes for cost-effective performance. Composites: Part A, 33: 913–934, (2002).

DOI: 10.1016/s1359-835x(02)00044-1

[12] D.R. Ambur and M. Rouse. Design and evaluation of composite fuselage panels subjected to combined loading conditions. Journal of Aircraft, 42(4): 1037–1045, (2005).

DOI: 10.2514/1.18994

[13] M. Rouse, D.R. Ambur, B. Dopker, and B. Shah. Response of composite fuselage sandwich side panels subjected to internal pressure and axial tension. Journal of Aircraft, 43(5): 1440–1447, (2006).

DOI: 10.2514/1.22397

[14] A.C. Orifici, I. Herszberg, and R.S. Thomson. Review of methodologies for composite material modelling incorporating failure. Composite Structures, 86: 194–210, (2008).

DOI: 10.1016/j.compstruct.2008.03.007

[15] Z. Hashin. Failure criteria for unidirectional fiber composites. Journal of Applied Mechanics, 47: 329–334, (1980).

[16] S.E. Yamada and C.T. Sun. Analysis of Laminate Strength and its distribution. Journal of Composite Materials, 12: 275–284, (1978).

[17] S.W. Tsai and E.M. Wu. A general theory of strength for anisotropic materials. Journal of Composite Materials, 5: 58–80, (1971).

[18] JM. Berthelot. Matériaux Composites - Comportement mécanique et analyse des structures 4ème édition. Editions TEC&DOC, (2005).

[19] M.P. Nemeth. Importance of Anisotropy on Buckling of Compression-Loaded Symmetric Composite Plates. AIAA Journal, 24: 1831–1835, (1986).

DOI: 10.2514/3.9531

[20] P.M. Weaver. Approximate Analysis for Buckling of Compression Loaded Long Rectangular Plates with Flexural/Twist Anisotropy. Philosophical Transactions of the Royal Society of London, Series A: Mathematical and Physical Sciences, 462: 59–74, (2006).

DOI: 10.1098/rspa.2005.1552

In order to see related information, you need to Login.