Active Damping of Resonant Modes in Unmanned Air Vehicles
Abstract
Poor handling characteristics associated with non-rigid aircraft structures can be improved by the use of an active damping system. The active system described here entails combined piezo-actuators and sensors that communicate with a processor to effectively take the structural vibration modes out of the pilot loop. The active system is integrated onto an existing simulation to predict the impact on handling qualities of an aircraft with a non-rigid structure. The objectives of this research are to design, implement, and test active vibration controls consisting of integrated piezo actuators and sensors on flyable, scale-model aircraft. This is done to promote good handling qualities in design through an understanding of sensor dynamics and the effects of sensor and actuator location. Methods of determining shape functions from finite-element analyses were examined and compared to wind tunnel tests. The resulting capability will allow a better prediction of the impact of structural dynamics and sensor and actuator location on the predicted stability and flight handling qualities, thus increasing both the efficiency and safety of unmanned air vehicles in flight.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2001
- Accession Number
- ADA397430
Entities
People
- Daniel Biezed
Organizations
- California Polytechnic State University