Abstract:
This work discusses the possibility to use the cycloidal rotor technology to provide anti-torque to otherwise conventional helicopter designs. A simple analytical model of cycloidal rotor aeromechanics is provided to support its sizing. The analytical model is validated using other approaches of increasing complexity and experimental results. Three anti-torque configurations are considered: a single vertical axis rotor at the tail, a single longitudinal axis rotor at the tail, and two sideways axis rotors at both sides of the airframe. The first and the last configurations are analyzed in more detail. The required power for anti-torque capabilities is compared to that of a conventional rotor and possible advantages are discussed in terms of added lift and thrust and better control capabilities.