This paper describes a methodology for the treatment of rotor blade flexibility for helicopter flight dynamics applications. A coupled flap-lag-torsion elastic rotor model, previously used in aeroelasticity studies, is coupled with a blade-element-type flight dynamic simulation model. The methodology reduces the amount of symbolic manipulation and reduces the effort required for computer implementations. The treatment of selected terms of the equations of motion is presented in detail. The mathematical structure of flight dynamics equations is also discussed. Results are presented for the frequency response to pilot inputs of a UH-60 Blackhawk in hover and forward flight, including comparisons with flight data. The effects of blade flexibility are generally modest, at least for the articulated rotor configuration used in the illustrative examples.
Modeling of flexible rotor blades for helicopter flight dynamics applications
Modellierung von flexiblen Hubschrauberrotorblättern für flugdynamische Anwendungen
Journal of the American Helicopter Society ; 41 , 1 ; 52-66
1996
15 Seiten, 18 Bilder, 21 Quellen
Aufsatz (Zeitschrift)
Englisch
Modeling of flexible rotor blades for helicopter flight dynamics application
Online Contents | 1996
|Modeling of flexible rotor blades for helicopter flight dynamic application
Online Contents | 1996
|Structured Modeling Applied to Flexible Helicopter Rotor Blades
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The loading of helicopter rotor blades in forward flight
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