Design and analysis of an aircraft composite hinge bracket using finite element approach

• Main Authors: Wai, Chee Mun, Rivai, Ahmad, Bapokutty, Omar
• Format: Article
• Language: English
• Published: Trans Tech Publications 2014
• Online Access: http://eprints.utem.edu.my/id/eprint/14170/1/AMM.629.158.pdf; http://eprints.utem.edu.my/id/eprint/14170/; http://www.scientific.net
• Institution: Universiti Teknikal Malaysia Melaka

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.