This paper describes the details of an experimental investigation focusing on the vibration characteristics of a composite fuselage structure of an ultralight unmanned aerial vehicle (UAV). The UAV has a total empty weight of 703 kg and 6.3 m in length. The fuselage structure consists of the fuselage body with an integrated vertical stabiliser. All structural components are fabricated from oven-cured laminated carbon composite materials using uniaxial and biaxial prepreg fabric. The modal characteristics of the fuselage structure are determined for a free-free configuration which is simulated by suspending the structure from its wing attachment points through the use of springs. A centrally located shaker system is used to induce vertical oscillations in the structure, which is instrumented with nineteen dual axis accelerometers. Dynamic properties such as the frequency, damping and associated mode shapes are obtained for aeroelastic analysis. The design and implementation of the vibration tests along with the experimental results are presented.
Vibration testing of a carbon composite fuselage
Schwingungsprüfung eines Flugzeugrumpfes aus Kohlenstoff-Komposit
International Journal of Vehicle Noise and Vibration ; 6 , 2-4 ; 149-162
2010
14 Seiten, 15 Bilder, 3 Tabellen, 13 Quellen
Aufsatz (Zeitschrift)
Englisch
Schwingungsprüfung , dynamisches Verhalten , Schwingungsverhalten , Anwendung in der Luft- und Raumfahrt , Anwendung in der Wehrtechnik , unbemanntes Luftfahrzeug , Flugzeugrumpf , Nanostruktur , Kohlenstofffaser , nanokristalliner Verbundwerkstoff , Schwingungsfrequenz , mechanische Schwingung , Prepreg , experimentelle Untersuchung , Verbundkonstruktion , dynamische Eigenschaft , Schwingungsdämpfung
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