An Experimental Investigation into the Effect of Flap Angles for a Piezo-Driven Wing

摘要: This article presents a comparison of results from six degree freedom force and moment measurements Particle Image Velocimetry (PIV) data taken on the Air Force Institute Technology's (AFIT) piezoelectrically actuated, biomimetically designed Hawkmoth, Manduca Sexta, class engineered wing, at varying amplitudes flapping frequencies, for both trimmed asymmetric conditions to assess control changes. To preserve test specimen integrity, wing was driven voltage amplitude 50% below maximum necessary achieve maximal Hawkmoth total stroke angle. 86° 65° angles were achieved tests respectively. Flapping performed system structural resonance, ±10% off resonance single amplitude, PZT power consumption calculated each condition. Two-dimensional PIV visualization transverse planform, recorded mid-span, frequency am...