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Consideration of structural constraints in passive rotor blade design for improved performance

Consideration of structural constraints in passive rotor blade design for improved performance ABSTRACT This design study applied parameterisation to rotor blade for improved performance. In the design, parametric equations were used to represent blade planform changes over the existing rotor blade model. Design variables included blade twist, sweep, dihedral and the radial control point. Updates to the blade structural properties with changes in the design variables allowed accurate evaluation of performance objectives and realistic structural constraints – blade stability, steady moments (flap bending, chord bending and torsion) and the high-g manoeuvre pitch link loads. Performance improvement was demonstrated with multiple parametric designs. Using a parametric design with advanced aerofoils, the predicted power reduction was 1.0% in hover, 10.0% at μ = 0.30 and 17.0% at μ = 0.40, relative to the baseline UH-60A rotor, but these were obtained with a 35% increase in the steady chord bending moment at μ = 0.30 and a 20% increase in the half peak-to-peak pitch link load during the UH-60A UTTAS manoeuvre. Low vibration was maintained for this design. More rigorous design efforts, such as chord tapering and/or structural redesign of the blade cross section, would enlarge the feasible design space and likely provide significant performance improvement. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png The Aeronautical Journal Cambridge University Press

Consideration of structural constraints in passive rotor blade design for improved performance

The Aeronautical Journal , Volume 120 (1232): 28 – Jul 4, 2016

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References (27)

Publisher
Cambridge University Press
Copyright
Copyright © Royal Aeronautical Society 2016 
ISSN
0001-9240
eISSN
2059-6464
DOI
10.1017/aer.2016.77
Publisher site
See Article on Publisher Site

Abstract

ABSTRACT This design study applied parameterisation to rotor blade for improved performance. In the design, parametric equations were used to represent blade planform changes over the existing rotor blade model. Design variables included blade twist, sweep, dihedral and the radial control point. Updates to the blade structural properties with changes in the design variables allowed accurate evaluation of performance objectives and realistic structural constraints – blade stability, steady moments (flap bending, chord bending and torsion) and the high-g manoeuvre pitch link loads. Performance improvement was demonstrated with multiple parametric designs. Using a parametric design with advanced aerofoils, the predicted power reduction was 1.0% in hover, 10.0% at μ = 0.30 and 17.0% at μ = 0.40, relative to the baseline UH-60A rotor, but these were obtained with a 35% increase in the steady chord bending moment at μ = 0.30 and a 20% increase in the half peak-to-peak pitch link load during the UH-60A UTTAS manoeuvre. Low vibration was maintained for this design. More rigorous design efforts, such as chord tapering and/or structural redesign of the blade cross section, would enlarge the feasible design space and likely provide significant performance improvement.

Journal

The Aeronautical JournalCambridge University Press

Published: Jul 4, 2016

Keywords: Passive Rotor Blade Design; Performance; Structural Constraints; Optimisation; Aerodynamics; Aircraft Design; Flight simulation; Performance; Rotorcraft

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