Aeroelastic modeling procedures used in the design of a piezoelectric controllable twist helicopter rotor wind tunnel model are described. Two aeroelastic analysis methods developed for active twist rotor studies, and used in the design of the model blade, are described in this paper. The first procedure uses a simple flap-torsion dynamic representation of the active twist blade, and is intended for rapid and efficient control law and design optimization studies. The second technique employs a commercially available comprehensive rotor analysis package, and is used for more detailed analytical studies. Analytical predictions of hovering flight twist actuation frequency responses are presented for both techniques. Forward flight fixed system nP vibration suppression capabilities of the model active twist rotor system are also presented. Frequency responses predicted using both analytical procedures agree qualitatively for all design cases considered, with best correlation for cases where uniform blade properties are assumed.
Aeroelastic analysis of the NASA/Army/MIT active twist rotor
1999
13 Seiten, 31 Quellen
Aufsatz (Konferenz)
Englisch
Aeroelastic Analysis of Active Twist Helicopter Rotor Blades
British Library Conference Proceedings | 2000
|Aeroelastic and Acoustic Analysis of an Active Twist Rotor
British Library Conference Proceedings | 2005
|Hover Testing of the NASA/Army/MIT Active Twist Rotor Prototype Blade
British Library Conference Proceedings | 2000
|Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor
Tema Archiv | 2002
|Vibratory Loads Reduction Testing of te NASA-Army-MIT Active Twist Rotor
Online Contents | 2002
|