Experimental performance optimization of a MAV-scale cycloidal rotor Conference Paper uri icon

abstract

  • This paper describes the systematic experimental studies performed to optimize the performance of a micro-scale cycloidal rotor. Parametric studies were conducted to determine the dependence of cycloidal rotor performance on rotational speed, blade pitching amplitude (symmetric and asymmetric pitching), blade airfoil profile, number of blades (at constant solidity) and the location of pitching axis. Higher blade pitch angles were found to improve thrust and increase the power loading of the cycloidal rotor. Asymmetric pitching with higher pitch angle at the top than at the bottom produced better power loading. The chordwise optimum pitching axis location was observed to be around 25-35% of the blade chord. For a constant solidity, the rotor with lesser number of blades produced higher thrust and the 2-bladed rotor had the best power loading. A hover-capable quad-cyclocopter was designed and built to demonstrate the flightworthiness of the cycloidal rotor concept. Copyright 2010 by the American Helicopter Society International, Inc. All rights reserved.

published proceedings

  • AHS Aeromechanics Specialists Conference 2010

author list (cited authors)

  • Benedict, M., Jarugumilli, T., & Chopra, I.

complete list of authors

  • Benedict, M||Jarugumilli, T||Chopra, I

publication date

  • June 2010