A coupled rotor/fuselage helicopter analysis is presented. The accuracy of the model is illustrated by comparing it with experimental data. The sensitivity of the open loop damping of the unstable resonance mode to such modeling effects as blade torsional flexibility, unsteady aerodynamics, forward flight, periodic terms, and trim solution is illustrated by numerous examples. Subsequently, the model is used in conjunction with linear optimal control theory to stabilize the air resonance mode. The influence of the modeling effects mentioned before on active resonance control is then investigated.
Active control of helicopter air resonance in hover and forward flight
Structures, Structural Dynamics and Materials Conference ; 1988 ; Williamsburg, VA, United States
1988-01-01
Conference paper
No indication
English
Field Measurements of Helicopter Rotor Wash in Hover and Forward Flight
British Library Conference Proceedings | 1995
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