Helicopter Longitudinal Stability: Some Contributions to Existing Theory Available to Purchase

CONSIDER a single rotor helicopter disturbed from the hovering condition as in FIG. 16. It has acquired a small forward velocity V ft./sec. and a nose‐up angular velocity of q rads./sec. For simplicity we consider the centre of gravity of the fuselage to be on the shaft axis, since its actual position can be shown to have a negligible effect in hovering. Resolving moments about the centre of gravity, the important terms are