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
Helicopter Longitudinal Stability
Some Contributions to Existing Theory
Aircraft Engineering and Aerospace Technology ; 29 , 6 ; 178-183
1957-06-01
6 pages
Article (Journal)
Electronic Resource
English
Helicopter Longitudinal Stability
Emerald Group Publishing | 1957
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