초록 ▼

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

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.

대표청구항 ▼

A rotary wing aircraft flight control system which receives signals indicative of aircraft pitch rate, pitch attitude, bank angle and airspeed, and responds to a pitch command from a sidearm controller to control the pitch of an aircraft, comprising: (a) means responsive to the airspeed signal and t

A rotary wing aircraft flight control system which receives signals indicative of aircraft pitch rate, pitch attitude, bank angle and airspeed, and responds to a pitch command from a sidearm controller to control the pitch of an aircraft, comprising: (a) means responsive to the airspeed signal and the pitch signal, for scheduling and providing a set point signal indicative of the desired aircraft pitch rate of change, which provides a constant sidearm controller force as a function of load factor on the main rotor; (b) means for computing the difference between said set point signal and the pitch rate signal, and for providing a pitch rate error signal indicative thereof; (c) inverse model means responsive to said set point signal for scheduling a feedforward command signal to drive the aircraft to respond in a manner which is essentially equal to said set point signal; (d) means responsive to said set point signal and the pitch attitude signal, comprising (1) means for providing maneuvering feel on the sidearm controller when the bank angle of the aircraft exceeds a predetermined value by conditioning said set point signal; (2) means for integrating over time said conditioned set point signal to provide a desired pitch attitude set point, for comparing said desired pitch attitude set point and the pitch attitude signal and providing a pitch attitude error signal indicative of the difference; and (e) means responsive to said pitch rate error signal, said feedforward command signal, and said pitch attitude error signal, for providing a pitch command signal to the main rotor of the aircraft.