Coupled rotor-flexible fuselage vibration reduction using open loop higher harmonic control
Author:
Affiliation:
1. California, University, Los Angeles
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1991-1217
Reference51 articles.
1. Technological Perspective,"AHS JournalVol.29, October 1984,pp.4-30.' 3. Staley,J.A.and Sciarra,J.J. 'Coupled
2. Rotor-Airframe Vibration Prediction Methods," Rotorcraft Dynamics, A S A SP-352, 1974.
Cited by 3 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献
1. Using adaptive structures to attenuate rotary wing aeroelastic response;Journal of Aircraft;1994-09
2. Coupled rotor-fuselage vibration reduction using open-loop blade pitch control;Mathematical and Computer Modelling;1993-08
3. A study on the feasibility of using adaptive structures in the attenuation of vibration characteristics of rotary wings;33rd Structures, Structural Dynamics and Materials Conference;1992-04-13
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