Helicopter pitch rate feedback bias for pitch axis maneuvering s

Details Helicopter pitch rate feedback bias for pitch axis maneuvering s Helicopter pitch rate feedback bias for pitch axis maneuvering s

1977-04-27

1978-11-28

Blix, Trygve M.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244 83D, 244 83E, 244 83F, 244 83J, 244179, 244181, B64C 1134

Patent

active

041272455

ABSTRACT:
The longitudinal cyclic pitch channel of a helicopter has a negative pitch rate feedback bias added thereto when flying at higher speeds, thereby to stabilize the pitch axis against aft-load maneuvering instability and/or to induce a requirement for the pilot to provide a countermanding longitudinal cyclic pitch input through his cyclic pitch stick, the normal feed force of which provides an indication to him of the loading of the rotor as a consequence of undergoing pitch rate maneuvers.

REFERENCES:
patent: 3482805 (1969-12-01), Knemeyer
patent: 3711042 (1973-01-01), Rempfer
patent: 3733039 (1973-05-01), O'Connor
patent: 3833189 (1974-09-01), Fowler
patent: 3920966 (1975-11-01), Knemeyer

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