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

Published online by Cambridge University Press:  04 July 2016

J.W. Lim
J.W. Lim*
Affiliation:
US Army Aviation Development Directorate – AFDD, Aviation & Missile Research, Development & Engineering Center, Research Development and Engineering, Command (RDECOM), Ames Research Center, Moffett Field, California, USA
*
[email protected]
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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.

Keywords

Passive Rotor Blade DesignPerformanceStructural ConstraintsOptimisationAerodynamicsAircraft DesignFlight simulationPerformanceRotorcraft
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1232 , October 2016 , pp. 1604 - 1631
Copyright
Copyright © Royal Aeronautical Society 2016 

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