Design and development of a hover-capable cyclocopter micro air vehicle
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Optimization of a MAV-scale cycloidal rotor (cyclocopter) was carried out using performance measurements. Detailed parametric studies were conducted to determine the effects of rotational speed, amplitude of the blade pitch angle, and the number of blades on cycloidal rotor performance. The 4- and 5-bladed cycloidal rotors operating at 40 pitching amplitude produced the best power loading (thrust per unit power), with a figure of merit of 0.45. Thrust measurements suggested the presence of a sideward force apart from the vertical lift, similar to that found in rotating circular cylinders. This was confirmed earlier using particle image velocimetry (PIV) measurements, which verified the presence of wake skewness. The optimized rotors were implemented on two different cyclocopter MAVs - twin-rotor and quad-rotor cyclocopters which are capable of tethered hover. The control strategies for the attitude control of the quad-rotor cyclocopter were developed and implemented. Copyright 2009.
Annual Forum Proceedings - AHS International
author list (cited authors)
Benedict, M., Jarugumillr, T., & Chopra, I.
complete list of authors
Benedict, M||Jarugumillr, T||Chopra, I