Speed and collective pitch bias of helicopter longitudinal cycli

Details Speed and collective pitch bias of helicopter longitudinal cycli Speed and collective pitch bias of helicopter longitudinal cycli

1978-02-28

1979-09-18

Kunin, Stephen G.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244 83G, 244178, 244182, 244196, B64C 1134

Patent

active

041680456

ABSTRACT:
A bias actuator, such as an extensible link, in the longitudinal cyclic pitch channel of a helicopter is provided with inputs as a function of airspeed multiplied inversely with collective pitch, and as a function of the rate of change of collective pitch stick position, so as to enforce positive angle of attack and speed stability and positive static pitch trim gradient and to decouple collective pitch from the longitudinal cyclic pitch channel at cruise airspeeds, the invention compensates, inter alia, adverse control effects of tail stabilizer surfaces at cruise speeds. A pair of indicators display bias commands and actual bias responses.

REFERENCES:
patent: 3620488 (1971-11-01), Miller
patent: 3733039 (1973-05-01), O'Connor et al.
patent: 4103848 (1978-08-01), Johnson, Jr. et al.
patent: 4127245 (1978-11-01), Tefft et al.

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