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Comparison of Several Methods for Predicting Loads on a Hypothetical Helicopter Rotor

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Several state‐of‐the‐art methods for predicting helicopter rotor loads were used by ten contributors to calculate rotor blade loads including airloads, bending moments, vibratory hub shears, and other parameters for a hypothetical helicopter rotor. Three different advance ratios were treated: μ = 0.1, 0.2, and 0.33. Comparisons of results obtained by the various contributors indicate significant differences for certain parameters and flight conditions. Trim parameters and flapwise bending moments show the smallest variations, while chordwise bending moments, torsional moments, and vibratory shears show moderate to large differences. Torsional moment variations were most sensitive to advance ratio. Analysis of the results indicates that the differences can be attributed to all three fundamental parts of the problem: numerical solution methods, structural dynamics, and aerodynamics.
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Document Type: Research Article

Affiliations: Ames Directorate, U.S. Army Air Mobility R&D Laboratory, Moffett Field, California 94035

Publication date: 1974-10-01

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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