Coupled rotor-fuselage vibration reduction using open-loop blade pitch control
- 1 August 1993
- journal article
- Published by Elsevier in Mathematical and Computer Modelling
- Vol. 18 (3), 131-156
- https://doi.org/10.1016/0895-7177(93)90109-c
Abstract
No abstract availableKeywords
This publication has 2 references indexed in Scilit:
- Coupled rotor-flexible fuselage vibration reduction using open loop higher harmonic controlPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1991
- Response Characteristics of a Linear Rotorcraft Vibration ModelJournal of Aircraft, 1982