Strength Analysis of Helicopter Tail Rotor Blades Made from Composite Materials

Maksimović, I. Vasović; Maksimović, Katarina; Maksimović, Mirko; Maksimović, Stevan

doi:10.1007/978-3-031-19499-3_5

Cited by 1 publication

(1 citation statement)

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“…The authors compared two variants of the blade, one made of aluminium and the other made of different composite materials like glass fabric/epoxy, carbon/epoxy, and kevlar149, and showed that carbon/epoxy with [0/90] and [−45/45] orientation has better strength than aluminium, being able to sustain higher loads. The strength analysis of composite tail rotor blades of a helicopter HT-40, tested under static and fatigue load spectra, is presented by Maksimovic et al [21]. The authors used two models to obtain the aerodynamic loads of helicopter tail rotor blades: an isolated tail rotor blade and a complete helicopter, modelled including the fuselage together with main and tail rotor blades.…”

Section: Introductionmentioning

confidence: 99%

A Novel Composite Helicopter Tail Rotor Blade with Enhanced Mechanical Properties

et al. 2023

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This paper describes the transition towards a composite structure, with the same overall aerodynamic characteristics, for a tail rotor blade of an IAR330 helicopter. The newly proposed structure of the composite blade is made of a carbon-roving spar embedded with epoxy resin, a hexagonal-cell honeycomb core manufactured by fused deposition modelling, and an outer skin made of multiple carbon-fibre-reinforced laminae. The blade was manufactured by the authors using the hand lay-up method at a scale of 1:3 with respect to the real one, and all stages of the manufacturing process are extensively described in the paper. The experimental tests were performed on an Instron 8872 testing machine by applying a bending force on its free edge, similar to the testing methodology employed by various composite blade manufacturers. A three-dimensional numerical model of the tail rotor blade was conceived, analysed using the finite element method, and validated by comparing the numerical and experimental values of the maximum bending force. Further, the model was used for a complex finite element analysis that showed the very good behaviour of the proposed composite blade during flight and emphasized the main advantages brought by the proposed composite structure.

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Section: Introductionmentioning

confidence: 99%