A numerical parametric design study is conducted for a helicopter primary control system utilizing trailing-edge flaps. The swashplateless rotor design is implemented by modifying a production modern bearingless rotor using plain flaps on the blades, and by replacing the pitch link to fixed system control system assembly with a roof spring. A comprehensive rotorcraft analysis based on UMARC is carried out to obtain the results for both the swashplateless and a conventional baseline rotor configuration. The key parameters are blade pitch index angle, torsional frequency, flap location, length, chord and overhang. The predictions show that the blade pitch index angle is a key parameter in the reduction of flap deflections and actuation requirement. By lowering the blade roof spring stiffness, the control effectiveness of the trailing-edge flap is increased. A flap length of 22 % R with flap chord ratio of 0.30, overhang length of 15 % chord, and location around 83 % R, are found to generate an optimum design in terms of reducing actuation power while maintaining fIap control authority. Blade aeroelastic stability predictions indicate that the swashplateless rotor is stable and has higher damping in blade lag, flap, and torsional modes when compared with a conventional rotor for most of the cases studied.
A parametric design study for a swashplateless helicopter rotor with trailing-edge flaps
Eine parametrische Entwurfsstudie für einen Hubschrauberrotor ohne Taumelscheibe mit Hinterkantenklappen
Journal of the American Helicopter Society ; 49 , 1 ; 43-53
2004
11 Seiten, 15 Bilder, 2 Tabellen, 23 Quellen
Article (Journal)
English
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