Abstract

Micro Air Vehicles are the subject of continued interest and development over the last several years. The majority of current vehicle concepts rely on rigid fixed wings or rotors. An alternate design based on a flapping wing is being developed that exhibits extreme maneuverability. This paper concentrates on the effect of flap angle and flapping frequency on the lift characteristics of the flapping wing micro air vehicle. Experiments were conducted in open jet low Reynolds number wind tunnel having test section of 350x350 mm in size. A flapping mechanism powered by small D.C motor, which is used for experimental purpose was designed and fabricated, in this it is possible to change the flap angle and flapping frequency by adjusting the link size and supply voltage to the D.C motor respectively. In order to measure the lift force a strain gauge based load cell/instrument was exclusively designed and built. One pair of wing has been used for this experiment to avoid the influence of wing shape and airfoil shape. All the tests were carried out in full-scale model.

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