A new wind tunnel test environment to determine the aerodynamic properties of 1:1 scale micro air vehicles (MAV) is introduced. The development of such small vehicles needs investigations of their behavior under realistic but also clearly defined, repeatable flow conditions that may encounter the vessels during real life flight. The new setup is capable to measure the aerodynamic forces and their derivatives whilst performing a controlled motion with 3 degrees of freedom in the upright Y=0 plane like for example the typical flapping wing motions plunging, pitching and their combinations or motions that simulate sudden gusts. For the first run of measurements two types of micro vehicle models have been built. The first type is a set of two flat plate wings varying in aspect ratio. The second type is a shoulder wing vehicle with a quick exchange for several elastic wings to study the interaction between aerodynamics and wing deformation during the occurrence of gusts. Static and dynamic measurements were conducted with the MAV models. Plunge and pitch motion have been performed to determine the dynamic damping coefficients of the flat plate models.
Experimental investigation of the aerodynamic properties of mirco aerial vehicles in motion
2008
8 Seiten, 17 Bilder, 3 Tabellen, 20 Quellen
Aufsatz (Konferenz)
Datenträger
Englisch
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