Active integral twist control for vibration reduction of helicopter rotors during forward flight is investigated. The twist deformation is obtained using embedded anisotropic piezocomposite actuators. An analytical framework is developed to examine integrally-twisted blades and their aeroelastic response during different flight conditions: frequency domain analysis for hover, and time domain analysis for forward flight. Both stem from the same three-dimensional electroelastic beam formulation with geometrical-exactness, and axe coupled with a finite-state dynamic inflow aerodynamics model. A prototype Active Twist Rotor blade was designed with this framework using Active Fiber Composites as the actuator. The ATR prototype blade was successfully tested under non-rotating conditions. Hover testing was conducted to evaluate structural integrity and dynamic response. In both conditions, a very good correlation was obtained against the analysis. Finally, a four-bladed ATR system is built and tested to demonstrate its concept in forward flight.
Integral Twist Actuation of Helicopter Rotor Blades for Vibration Reduction
2001
87 pages
Report
No indication
English
Aircraft , Test Facilities & Equipment , Rotary wings , Vibration damping , Frequency domain analysis , Time domain analysis , Active control , Aeroelasticity , Dynamic response , Piezoelectric actuators , Feedback control , Harmonic functions , Dynamic models , Horizontal flight , System identification , Controllers , Aerodynamic stability , Hovering stability , Helicopters
Helicopter Vibration Reduction Using Active Twist Control of Composite Rotor Blades
British Library Conference Proceedings | 2008
|British Library Online Contents | 1996
|British Library Conference Proceedings | 1996
|Helicopter vibration reduction using active twist control of composite rotor blades
Tema Archive | 2008
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