<div class="htmlview paragraph">The paper discusses an improved control system for a helicopter or VTOL aircraft equipped with a rigid lift rotor integral with a flexible hub.</div> <div class="htmlview paragraph">The proposed method consists in suitably arranging the knuckle joints on the ends of the blade pitch control levers to create a complementary cyclic deflection effect which is dependent upon the rotor's attitude and is superimposed upon the pilot's control.</div> <div class="htmlview paragraph">The reduced dynamic instability of the helicopter with the control column locked, and the calculated improvement in the rotor's response to the control column facilitates piloting.</div> <div class="htmlview paragraph">The control of such a helicopter compares with driving an automobile equipped with servo-assisted controls.</div>