Automatic gain control for stability augmentation systems

Details Automatic gain control for stability augmentation systems Automatic gain control for stability augmentation systems

1976-04-12

1977-06-28

Kunin, Stephen G.

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

73 65, 73178H, 2351502, 244178, B64C 1144

Patent

active

040320839

ABSTRACT:
The gain of a stability augmentation system for an aircraft, particularly a helicopter, is automatically varied in accordance with the gross weight and deviations of the center of gravity of the aircraft. Gross weight and center of gravity are identified from in-flight measurements of collective and cyclic pitch stick position and airspeed. The gain of the stability augmentation system will not be changed during periods when the aircraft is being maneuvered.

REFERENCES:
patent: 3071335 (1963-01-01), Carter, Jr.
patent: 3194058 (1965-07-01), Kurkjian
patent: 3701279 (1972-10-01), Harris et al.
Hawkins, B.J., "Stan-for Aircraft Take-off Weight and Balance", Instruments & Control Systems, 2-1965, pp. 89-93.

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