Experimental Study on Piezoelectric-Stack-Actuator-Driven Active Vibration Control of Helicopter Floor Structure
Author:
Affiliation:
1. Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People’s Republic of China
2. Pennsylvania State University, University Park, Pennsylvania 16802
Funder
National Natural Science Foundation of China
Funding of Jiangsu Innovation Program for Graduate Education
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference12 articles.
1. Active control of helicopter vibration
2. Vibration reduction in rotorcraft using active control - A comparison of various approaches
3. Active Vibration Control of the Lynx Helicopter Airframe
4. Design of piezostack-driven trailing-edge flap actuator for helicopter rotors
5. Modal Active Vibration Control of a Rotor Using Piezoelectric Stack Actuators
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2. Development of a High-Performance Low-Weight Hydraulic Damper for Active Vibration Control of the Main Rotor on Helicopters—Part 2: Preliminary Experimental Validation;Aerospace;2023-10-05
3. Active Global Vibration Control of Helicopter Fuselage;AIAA Journal;2023-08
4. MIMO Multi-Frequency Active Vibration Control for Aircraft Panel Structure Using Piezoelectric Actuators;International Journal of Structural Stability and Dynamics;2023-02-20
5. Progress of Study on the Application of Actuators in Helicopter Airframe ACSRs;Lecture Notes in Electrical Engineering;2023
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