A model for active control of helicopter air resonance in hover and forward flightA coupled rotor/fuselage helicopter analysis is presented. The accuracy of the model is verified by comparing it with the experimental data. The sensitivity of the open loop damping of the unstable air 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 air resonance control is then investigated.
Document ID
19900055407
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Takahashi, M. D. (California Univ. Los Angeles, CA, United States)
Friedmann, P. P. (California, University Los Angeles, United States)