The Effect of Rotorcraft CG Offset on Aerodynamic Stability Aiming to Obtain Vibration Reduction

Author:

Yoshizaki Yuji1,Sunada Shigeru2

Affiliation:

1. 連絡先著者(Corresponding author):pennstate_hammond@yahoo.co.jp

2. 名古屋大学工学部

Publisher

Japan Society for Aeronautical and Space Sciences

Subject

General Medicine

Reference11 articles.

1. 1) Bielawa, R. L.: Rotary Wing Structural Dynamics and Aeroelasticity, American Institute of Aeronautics and Astronautics, Renton, Virginia, 2006, pp. 239-274.

2. 2) Andrews, J., Welsh, W., Altieri, R. and DiOttavio, J.: Ground and Flight Testing of a Hub Mounted Vibration Suppression System, American Helicopter Society 70th Annual Forum, Montreal, Quebec, Canada, May 20-22, 2014.

3. 3) Swanson, D., Black, P., Girondin, V., Bachmeyer, P. and Jolly, M.: Active Vibration Control Using Circular Force Generators, Proceedings of 41st European Rotorcraft Forum 2015, Germany.

4. 4) Millott, T. A., Goodman, R. K., Wong, J. K., Welsh, W. A., Correia, J. R. and Cassil, C. E.: Risk Reduction Flight Test of a Pre-production Active Vibration Control System for the UH-60 M, Proceedings of the American Helicopter Society 59th Annual Forum, Phoenix, Arizona, May 6-8, 2003.

5. 5) Friedmann, P. P. and Millott, T. A.: Vibration Reduction in Rotorcraft Using Active Control: A Comparison of Various Approaches, J. Guid. Control Dynam., 18, 4 (1995), pp. 664-673.

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