Active Vibration Control by Harmonic Input Compensation for Piezoelectric Stack Actuator Nonlinearity-Reference-Cited by-同舟云学术

Active Vibration Control by Harmonic Input Compensation for Piezoelectric Stack Actuator Nonlinearity

Published:2014-11 Issue:6 Volume:51 Page:2027-2031
ISSN:0021-8669
Container-title:Journal of Aircraft
language:en
Short-container-title:Journal of Aircraft

Author:

Song Laishou¹,Xia Pinqi¹

Affiliation:

1. Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People’s Republic of China

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.C032752

Reference14 articles.

1. Design of piezostack-driven trailing-edge flap actuator for helicopter rotors

2. Optimal Placement of Piezoelectric Actuated Trailing-Edge Flaps for Helicopter Vibration Control

3. Active Control of Helicopter Structural Response Using Piezoelectric Stack Actuators

4. HeverlyD.WangK. W.SmithE. C. “Optimal Actuator Placement and Active Structure Design for Control of Helicopter Airframe Vibrations,” Ph.D. Thesis, Dept. of Mechanical and Nuclear Engineering, Pennsylvania State Univ., State College, PA, 2002.

5. Effect of Piezoelectric Hysteresis on Helicopter Vibration Control Using Trailing-Edge Flaps

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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

3. Hybrid Active Vibration Control of Helicopter Fuselage Driven by Piezoelectric Stack Actuators;Journal of Aircraft;2019-03

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