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Blending design of composite panels with lamination parameters

Published online by Cambridge University Press:  30 August 2016

P. Jin ,
X. Zhong ,
J. Yang  and
Z. Sun
P. Jin*
Affiliation:
School of Civil Engineering and Architecture Xi'an University of Technology Xi'an China
X. Zhong
Affiliation:
School of Aeronautics Northwestern Polytechnical University Xi'an China
J. Yang
Affiliation:
School of Aeronautics Northwestern Polytechnical University Xi'an China
Z. Sun
Affiliation:
School of Aeronautics Northwestern Polytechnical University Xi'an China
*
nwpu-jinpeng@163.com
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Abstract

In this paper, a new optimisation method incorporating lamination parameters and a guide-based blending model is proposed. Lamination parameters for a guide laminate and ply number of each panel are employed as design variables for optimisation with a parallel real-coded genetic algorithm incorporating structure behaviour and manufacturing constraints. During the optimisation process, with a form of least squares fitting adopted, another genetic algorithm is used to obtain the guide stacking sequence of the guide laminate from the guide lamination parameters, and then the laminate configurations of each panel are obtained from the guide stacking sequence and number of plies for each panel. The proposed framework is demonstrated via design of an 18-panel horseshoe configuration, where each panel is optimised individually with a buckling constraint. Numerical results indicate that the present algorithm is capable of obtaining fully blended designs.

Keywords

Blendinglamination parametersptimisation
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1233 , November 2016 , pp. 1710 - 1725
Copyright
Copyright © Royal Aeronautical Society 2016 

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