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A Meta-Heuristic Based Weight Optimisation for Composite Wing Structural Analysis

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Abstract:

This paper presents a two-stage meta-heuristic approach to producing weight-optimised solutions needed prior to the detailed finite element analysis of composite wing. Composite wing covers are assumed to take the form of a group of stiffened sub-panels with varying skin and stiffener geometries according to the wing layout and loads. A population of limited solutions satisfying various design constraints was created using layout (skin and stiffener geometry), selected lay-ups, rule based stacking sequence and various assumed loads. The closed form analytical solutions of flat stiffened orthotropic plates are used for calculating buckling reserve factors and strength margins. For each sub-panel, a meta-heuristic rule was imposed to search for a suitable combination of skin and stiffener geometry. The criterion used was minimum weight satisfying laminate continuity accounting for manufacturability. Later, the optimised solutions for each sub-panel are converted into a format supported by the conventional finite element tool (NASTRAN). The use of meta-heuristic approach and their automation in Visual Basic for Applications resulted in fast convergence and potential time-saving compared to genetic algorithms.

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Periodical:

Applied Mechanics and Materials (Volumes 5-6)

Pages:

305-314

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.5-6.305

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Online since:

October 2006

Authors:

Vijay Sahadevan, Yoann Bonnefon, Tim Edwards

Keywords:

Buckling Stability, Heuristic Algorithm , Optimization, Stiffened Composite Wing Panels

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© 2006 Trans Tech Publications Ltd. All Rights Reserved

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References

[1] M.C.Y. Niu: Airframe Structural Design (Conmilit Press Ltd, Hong Kong, 2 e , 1999).

Google Scholar

[2] B. Liu, R.T. Haftka and M.A. Akgun: Composite wing structural optimisation using genetic algorithms and response surfaces, Proc. 39 th AIAA-SDM Conf., California, 20-23 April 1998, Paper 4854.

DOI: 10.2514/6.1998-4854

Google Scholar

[3] J.F. Wiggenread, P. Arendsen and J.M.S. Pereira: Design optimisation of stiffened composite panels with buckling and damage tolerance constraints, Proc. 39 th AIAA-SDM Conf., California, 20-23 April 1998, Paper-4853.

DOI: 10.2514/6.1998-1750

Google Scholar

[4] L. Lamberti, S. Venkataraman , R.T. Haftka and T.F. Johnson: Preliminary design optimisation of stiffened panels using approximate analysis models, Int. J. Numer. Methods in Engng, Vol. 57. No. 10 (2003), pp.1351-1380.

DOI: 10.1002/nme.781

Google Scholar

[5] T. Edwards: Covers Optimisation for Composite Wing Structures (Technical Report 5032278/04/001, ATKINS, UK, 2004). a) In-board panel global buckling λg = 1. 92 b) In-board panel local buckling λl = 1. 84 c) Out-board panel global buckling λg = 2. 16 d) Out-board panel local buckling λl = 1. 86 Fig. 7. Buckling mode shapes from finite element analysis results using 1200 kN.

DOI: 10.2514/6.2021-1171.vid

Google Scholar

[6] S. Venkataraman and R.T. Haftka: Structural Optimization: What has Moore's law done for us? Proc. 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Colorado, 2002, Paper: 1342.

DOI: 10.2514/6.2002-1342

Google Scholar

[7] W.J. Stroud: Minimum mass design of filamentary composite panels under combined loads: Design procedures based on simplified buckling equations, (Technical Report, NASA-TN8257, 1976).

Google Scholar

[8] B. Liu and R.T. Haftka: Composite wing structural design optimization with continuity constraints, Proc. 42 nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit, Seattle, 2001, Paper: 25021.

DOI: 10.2514/6.1998-1830

Google Scholar

[9] A. Mukherjee and B. Varughese B: Design guidelines for ply drop-off in laminated composite structures, Composites- Part B: Engineering, Vol. 32 (2001), pp.153-164.

DOI: 10.1016/s1359-8368(00)00038-x

Google Scholar

[10] S.W. Tsai and H.A.T. Hahn: Introduction to Composite Materials (Technomic Publications, USA, 1980).

Google Scholar

[11] R. Muzzolini, S. Veen, A.P. Duarte and J.C. Ehrstrom: Stability analysis of stiffened panels: Analytical and finite element methods, Proc. Worldwide Aerospace Conf. and Techno Showcase, 8-10 April 2002, Toulouse, Paper-164.

Google Scholar

[12] C. Blum and A. Roli: Meta-heuristics in combinatorial optimization: Overview and conceptual comparison, ACM computing Surveys, Vol. 35, No. 3 (2003), pp.268-303.

DOI: 10.1145/937503.937505

Google Scholar

[13] O. Saarela: Design system of composite laminates (Technical Report A-2, Helsinki University of Technology, Finland, 2005).

Google Scholar

[14] S. Vijayakumar: Heuristic Approach based Composite wing Covers Optimisation Tool - Users Manual (ATKINS Aerospace, UK, 2005).

Google Scholar

[15] ACAT - Residual Strength after Impact Tool, Version 16, Airbus UK.

Google Scholar