Analysis and testing of Mach scaled rotor model with piezoelectric bender actuated trailing-edge flaps for helicopter vibration control-Reference-Cited by-同舟云学术

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Analysis and testing of Mach scaled rotor model with piezoelectric bender actuated trailing-edge flaps for helicopter vibration control

Published:1999-04-12 Issue: Volume: Page:
ISSN:
Container-title:40th Structures, Structural Dynamics, and Materials Conference and Exhibit
language:
Short-container-title:

Author:

Koratkar Nikhil¹,Chopra Inderjit¹

Affiliation:

1. Maryland, Univ., College Park

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1999-1501

Reference15 articles.

1. Shaw, J., Albion, N., Hanker, E. J., and Teal, R.S,"Higher Harmonic Control : Wind Tunnel Demonstration of Fully Effective Vibratory Hub Forces Suppression0022, Journal of American Helicopter Society, Vol. 34.,No.l,January 89, pp14-25. [31

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1. A comparative assessment of vibration control capabilities of a L-shaped Gurney flap;The Aeronautical Journal;2016-11

2. Closed-Loop Neurocontroller Tests on Piezoactuated Smart Rotor Blades in Hover;AIAA Journal;2002-08

3. Aeroelastic stability of smart trailing-edge flap helicopter rotors;19th AIAA Applied Aerodynamics Conference;2001-06-11

4. Induced-shear piezoelectric actuators for rotor blade trailing edge flaps and active tips;19th AIAA Applied Aerodynamics Conference;2001-06-11

5. Design and experimental testing of an induced-shear piezoelectric actuator for rotor blade trailing edge flaps;41st Structures, Structural Dynamics, and Materials Conference and Exhibit;2000-04-03

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