Optimal Placement of Piezoelectric Actuated Trailing-Edge Flaps for Helicopter Vibration Control
Author:
Affiliation:
1. Indian Institute of Science, Bangalore 560 012, India
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.38199
Reference44 articles.
1. Aeroelastic optimization of a helicopter rotor to reduce vibration and dynamic stresses
2. Helicopter Vibrations: A Technological Perspective
3. On Developing and Flight Testing a Higher Harmonic Control System
4. Dynamic response of rotating beams with piezoceramic actuation
5. Use of single crystal and soft piezoceramics for alleviation of flow separation induced vibration in a smart helicopter rotor
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2. Neural Network Based Hysteresis Compensation of Piezoelectric Stack Actuator Driven Active Control of Helicopter Vibration;Sensors and Actuators A: Physical;2020-02
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