Active Control of Helicopter Structural Response Using Piezoelectric Stack Actuators
Author:
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.C031758
Reference12 articles.
1. Active Vibration Control of Scaled Wing Box Model Using Piezoelectric Stack Actuators
2. Controllability measures and actuator placement in oscillatory systems
3. Integrated optimal design of vibration control system for smart beams using genetic algorithms
4. A computational scheme for the optimal sensor/actuator placement of flexible structures using spatial H2 measures
5. Optimal vibration control of smart fiber reinforced composite shell structures using improved genetic algorithm
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