Maneuver feel system for a rotary wing aircraft

Details Maneuver feel system for a rotary wing aircraft Maneuver feel system for a rotary wing aircraft

1991-08-28

1993-05-25

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244181, 244223, 244228, 364434, B64C 1346, B64C 1350, B64C 1134

Patent

active

052132820

ABSTRACT:
A helicopter fly-by-wire flight control system (21) includes a model following control system architecture which provides the pilot with maneuvering feel. Maneuvering feel is generated by varying the gain of a rate model (52) in the control system to schedule a constant sidearm controller force per g of load factor currently on the helicopter main rotor. This gain variation works in conjunction with control logic which requires the pilot to apply a nose up pitch command during steep banked turns in order to offset a control system induced downward (pitch) bias of the aircraft nose. The control system induced bias is generated only during steep banked turns, thus allowing the pilot to fly shallow banked coordinated turns without having to apply a nose up pitch command.

REFERENCES:
patent: 4129275 (1978-12-01), Gerstine et al.
patent: 4206891 (1980-06-01), Perez et al.
patent: 4313165 (1982-01-01), Clelford et al.
patent: 4420808 (1983-12-01), Diamond et al.
patent: 4563743 (1986-01-01), Murphy et al.
patent: 4849900 (1989-07-01), Blight et al.
patent: 5062583 (1991-11-01), Lipps et al.
patent: 5117362 (1992-05-01), Peckham et al.

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