Design and Analysis of an Aircraft Composite Hinge Bracket Using Finite Element Approach

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The use of composite materials in aircraft structures have been increasing for the past decade. The anisotropic and heterogeneous nature of composites remains a major challenge to the design and analysis of composite aircraft structures. Composite structures require a different design approach compared to the design of metallic structures. This paper aims to provide a step by step definitive guide to design and analyze composite structures using finite element approach. A simplified design model for the composite structural design was used to analyze an aircraft composite hinge bracket. The composite hinge bracket which is made of IM7/8552 laminated composite plates was successfully designed with a margin of safety of 0.216 and a weight savings of 43.77 percent was estimated.

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Periodical:

Edited by:

R. Varatharajoo, F.I. Romli, K.A. Ahmad, D.L. Majid and F. Mustapha

Pages:

158-163

Citation:

W. C. Mun et al., "Design and Analysis of an Aircraft Composite Hinge Bracket Using Finite Element Approach", Applied Mechanics and Materials, Vol. 629, pp. 158-163, 2014

Online since:

October 2014

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$38.00

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