Simultaneous Active Damping and Health Monitoring of Aircraft Panels

摘要: This paper reports on an experimental implementation of active control methods using smart structures for the purpose performing simultaneous health monitoring and damping panels characteristic aircraft components. Here refers to integrated use piezoelectric actuators fiber optic sensors as measurement transducers required actively damp a panel provide its structural integrity. The experiments focus flat aluminum with fundamental frequency range. performance will be designed work across range temperatures from 70° 120° F. aspects are impedance based frequencies in kilohertz avoid interacting that is targeted include first six or seven modes. Both theoretical considerations verification given. major goal here show experimentally possible.