This research has resulted in an experimental demonstration of aircraft vibration and flutter suppression using piezoelectric materials. Open and closed loop vibration and flutter tests were conducted in the wind tunnel and in flight, with excellent correlation achieved by computational predictions. The wings were constructed using carbon fibre, balsa wood and fiber glass. The piezoelectric actuators were mounted in the internal part of the carbon fibre plates. In the active skin wing, they have been glued along the span of the upper and lower skins. The adaptive skin wing proved that both the average displacement and the maximum displacement were generally lower with the active wing than with the passive one, making the active wing an improved wing version compared with the passive wing, in the majority of flight conditions. The best improvement, in terms of average displacement, is 22.1% at 10 m/s, and in terms of maximum displacement, is 13.6% at 35 m/s. In terms of structural damping associated with the tail vibration, the damping values of the wing in the active mode are higher than in the passive mode in almost all the flying conditions. These results demonstrate that the controller is improving the aeroelastic characteristics of the wing and decreasing forced vibrations induced to the structure by the tail. For the flutter analysis, the damping associated with 7th wing mode was studied. It was concluded that the wing damping for the 7th mode is always higher in the active mode than in passive one. Then, it can be concluded that the active wing has a higher flutter speed when compared with passive wing. Using these results, the experimental flutter speed of the wing in the passive mode is 47.95 m/s and in the active mode is 53.99 m/s. This represents an increase in flutter speed of 12.59%, meaning that with a given wing and a control system like this, one can fly 12.59% faster without structural reinforcements of the structure and without suffering the aeroelastic effects of flutter. Finally, comparing the flutter speed of 44.87 m/s calculated in computational analysis, with the experimental value of47.95 m/s, there is an 6.86% error comparing the experimental value with the computational one error of 12.28%. A study on the application of shunted piezoelectric actuators on an aeroelastic structure was also presented. The piezo shunts were tested and were found to respond only to very specific frequencies. Nevertheless, the piezo shunts can be used in a very simple and inexpensive way to damp the vibration of the structure are pre-determined frequencies.
Aeroelastic control of a wing with active skins using piezoelectric patches
Aeroelastische Regelung eines Tragflügels mit aktiven Außenhäuten unter Verwendung piezoelektrischer Einlagen
2007
10 Seiten, 11 Bilder, 7 Tabellen, 9 Quellen
Conference paper
English
Tragfläche (Aerodynamik) , Schwingungsdämpfung , piezoelektrischer Aktor , carbonfaserverstärkter Kunststoff , Fluggeschwindigkeit (Luft) , Erhöhung , Digitalsteuerung und -regelung , Turbulenzunterdrückung , aktive Steuerung und Regelung , Sensor-Aktor-System , Flügeloberseite , Flügelunterseite , Außenhaut , piezoelektrischer Vibrationsaufnehmer , Tragflügelumströmung
ENGINEERING NOTES - On Active Aeroelastic Control of an Adaptive Wing Using Piezoelectric Actuators
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