Design and Analysis of an Aircraft Composite Hinge Bracket Using Finite Element Approach
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.
R. Varatharajoo, F.I. Romli, K.A. Ahmad, D.L. Majid and F. Mustapha
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