Helicopter Longitudinal Stability: Some Contributions to Existing Theory

Abstract

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

Citation

Payne, P.R. (1957), "Helicopter Longitudinal Stability: Some Contributions to Existing Theory", Aircraft Engineering and Aerospace Technology, Vol. 29 No. 6, pp. 178-183. https://doi.org/10.1108/eb032840