An autopilot is applied to helicopter rotor flap-lag-torsion equations to obtain the control settings for a trimmed flight condition. The rotor aerodynamic description includes a stage-space dynamic stall model for lift and for pitching moments. Thus, the rotor is trimmed for flight conditions in which significant stall and torsional deformations are present. The autopilot is extended to Q-bladed rotors by a series of time-delay terms. As a result, the optimum gains and time constants depend upon the number of blades as well as upon the torsional stiffness.
Helicopter trim with flap-lag-torsion and stall by an optimized controller
1990-10-01
Sonstige
Keine Angabe
Englisch
Influence of Dynamic Stall and DynamicWake Effects on Helicopter Trim and Rotor Loads
Online Contents | 2009
|Influence of Dynamic Stall and Dynamic Wake Effects on Helicopter Trim and Rotor Loads
British Library Conference Proceedings | 2008
|