High speed yaw control system for rotary wing aircraft

Details High speed yaw control system for rotary wing aircraft High speed yaw control system for rotary wing aircraft

1991-08-28

1993-01-12

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244184, 364434, B64C 1144, G06F 1550

Patent

active

051783070

ABSTRACT:
A helicopter flight control system includes a model following control system architecture to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output command signal to the tail rotor. Yaw control is accomplished by applying a force on a sidearm controller which provides a yaw axis command signal that is used to schedule a desired yaw rate of change. The lateral acceleration and airspeed signals are used to compute a synthesized yaw rate signal which is compared against the desired yaw rate of change, thus allowing the pilot to control lateral acceleration when he applies force on the sidearm controller.

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