DGLR-Publikationsdatenbank - Detailansicht
Titel:
Helicopter Tail Rotor Flutter
Autor(en):
M.G. Rozhdestvensky
Zusammenfassung:
Stall flutter occurring on helicopter tail rotor blades in hovering and showing an abrupt growth in the value of the pitching moment variable component is investigated in the paper. The values of the measured loads exceed the ordinary level encountered in operation by several times. The analytical and theoretical investigation of stall flutter has been carried out on a basis of unsteady aerodyanmics, using a model of the blade elastic in bending and torsion. The mechanism of the evolution of self-oscillations and the influence of various design parameters have been investigated. Good qualitative and quantitative agreement of analytical and experimental data has been obtained; means to reduce the pitching moment have been found. Full-scale tests of the Mi-26 tail rotor have confirmed the efficiency of the implemented design solutions aimed at eliminating stall flutter.
Veranstaltung:
17th European Rotorcraft Forum 1991, Berlin
Medientyp:
Conference Paper
Sprache:
englisch
Format:
21,0 x 29,7 cm, 16 Seiten
Veröffentlicht:
DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; S.125-140; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn
Preis:
NA
ISBN:
ISSN:
Kommentar:
Klassifikation:
Stichworte zum Inhalt:
rotor blades, helicopters, rotor aerodynamics, tail rotors
Verfügbarkeit:
Bestellbar
Veröffentlicht:
1991
Dieses Dokument ist Teil einer übergeordneten Publikation:
17th European Rotorcraft Forum Proceedings