The vibrational behavior of cantilevered aircraft wings modeled as thin-walled beams and incorporating piezoelectric effects is investigated. Based on the direct and converse piezoelectric effects, the system of piezoelectric sensors and actuators conveniently located on the wing yield the control of its associated vertical and lateral bending eigenfrequencies. The possibility revealed by this study enabling one to increase adpatively the eigenfrequencies of thin-walled cantilevered beams could play a significant role in the control of the dynamic response and flutter of wing and rotor lade structures.
Vibrational behavior of adaptive aircraft wing structures modelled as composite thin-walled beams
Schwingungsverhalten von adaptiven Tragflächenkonstruktionen in Form von dünnwandigen Verbundträgern
1991
10 Seiten, 7 Bilder, 19 Quellen
Aufsatz (Konferenz)
Englisch
British Library Conference Proceedings | 2016
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