Design Allowable Considerations for use of Laminated Composites in Aircraft Structures

Prakash D Mangalgiri

Abstract


Carbon fibre polymer composites have evolved over the years to become major structural materials for primary structures of the aircraft today. The paper reviews the work carried out over last four decades on carbon fiber polymer composites to create an understanding of their behaviour in order to set up a philosophy of design and arriving at design allowable values for strength so as to ensure safety and performance of aircraft with minimum weight penalty. The rationale behind the choice of allowable values and the process to arrive at them is explained. While several issues are discussed, three major aspects are emphasised: the environmental (hygrothermal) effect, the effect of holes and fasteners and impact damage. The directions of the current improvements and course of future developments are indicated in relation to their influence on the design allowables.

Keywords


Carbon Fibre Composites; Laminates; Aircraft Structures; Design Allowable; Structural Design; Impact Damage; Holes in composites; Fastener joints; Hygrothermal effect

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