Off-axis coupling of a helicopter exhibits the opposite sign in flight tests as compared to simulations. lt has been shown that this effect may be attributable to the bending of the wake during a pitching maneuver, which introduces a fore-to-aft gradient in induced flow that can reverse the predicted sign of roll coupling. lt has been shown that this result can also be obtained with momentum and vortex theory. In the present work, a generalized mode for wake curvature in hover is developed using the exact relation derived from vortex tube theory. This model is coupled with a flop model to investigate the influence on dynamic coupling.
Helicopter rotor dynamic inflow modeling for maneuvering flight
Ein dynamisches Hubschrauberrotor-Einlaufströmungsmodell für Schwebeflugzustände
Journal of the American Helicopter Society ; 46 , 2 ; 129-139
2001
11 Seiten, 12 Bilder, 3 Tabellen, 34 Quellen
Article (Journal)
English
Hubschrauber , Rotor (Drehflügel) , Einlaufströmung , dynamisches Verhalten , Manövrierfähigkeit , Test (Prüfung) , numerische Simulation , Theorie-Experiment-Vergleich , Variationskurve , Variationskoeffizient , Variationsrechnung , zeitveränderliches System , Biegeschwingung , Rollen (Drehbewegung) , Kinematik , Rechenmodell , Flugverhalten
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