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The adverse cyclic and collective pitch effect in a rotor

Published online by Cambridge University Press:  07 June 2019

Hak Yoon Kim Open the ORCID record for Hak Yoon Kim [Opens in a new window]
Hak Yoon Kim*
Affiliation:
Hanseo University, Taean, Chung-nam, S Korea
*
heligyro@hanseo.ac.kr
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Abstract

Numerical simulations have been carried out for a 32.16-ft-diameter rotor in autorotational forward flight. Coupled flapping and rotational equations were solved using the transient simulation method (TSM) to ascertain the quasistatic torque equilibrium conditions. The Pitt/Peters inflow theory was adopted in the simulations, and an airfoil look-up table made by a compressible Navier-Stokes solver was used. The adverse cyclic and collective pitch inputs were introduced in a similar fashion to helicopter control in that the cyclic lever is pulled back and the collective lever is pushed down for increasing airspeeds. The simulation results showed that the longitudinal cyclic pitch input combined with a lowered collective pitch increases the rotating torque for a low shaft angle and an advance ratio greater than one, producing both high lift and a high lift-to-drag ratio. Upon introducing the adverse cyclic and collective pitch inputs, the control range broadened, and a torque equilibrium condition was detected at 414.7kt (700ft/s) of airspeed in the simulation.

Keywords

TSMautorotationcyclic pitchcollective pitchhigh advance ratio
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1264 , June 2019 , pp. 805 - 827
Copyright
© Royal Aeronautical Society 2019 

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