초록 ▼

An electronic lead/lag damper algorithm implemented as part of the fly-by-wire flight control system to minimize or eliminate mechanical lead/lag dampers of a rotary wing aircraft. The electronic lead/lag damper algorithm uses a cross-feed control methodology that band-pass filters pitch and roll ra

An electronic lead/lag damper algorithm implemented as part of the fly-by-wire flight control system to minimize or eliminate mechanical lead/lag dampers of a rotary wing aircraft. The electronic lead/lag damper algorithm uses a cross-feed control methodology that band-pass filters pitch and roll rates and feeds back a signal to the lateral and longitudinal cyclic inputs to provide electronic stability to rotor lag modes.

대표청구항 ▼

1. A rotary-wing aircraft comprising: a rotor hub having at least one rotor blade assembly;a lead/lag damper mounted to said rotor hub and said at least one rotor blade assembly, said lead/lag damper provides a first damping value, said first damping value less than a required damping value of said

1. A rotary-wing aircraft comprising: a rotor hub having at least one rotor blade assembly;a lead/lag damper mounted to said rotor hub and said at least one rotor blade assembly, said lead/lag damper provides a first damping value, said first damping value less than a required damping value of said at least one rotor blade assembly; anda fly-by-wire flight control system having an electronic lead/lag damper algorithm which provides a damping value which defines at least the difference between said first damping value and said required damping value. 2. The aircraft as recited in claim 1, wherein said rotor hub includes a main rotor hub. 3. The aircraft as recited in claim 2, wherein said main rotor hub forms a part of an articulated rotor system of a rotary wing aircraft. 4. The aircraft as recited in claim 1, wherein said fly-by-wire type flight control system includes a model following control system. 5. The aircraft as recited in claim 1, wherein said electronic lead/lag damper algorithm provides a cross-feed control methodology that band-pass filters a pitch rate and a roll rate then feeds back these filtered signals to both a lateral cyclic input and a longitudinal cyclic input to said fly-by-wire type flight control system. 6. The aircraft as recited in claim 5, wherein said cross-feed control methodology band-pass filters said pitch rate and said roll rate in response to a rotor speed. 7. A fly-by-wire flight control system comprising: a memory storing instructions operable to cause said fly-by-wire flight control system to perform an electronic lead/lag damper method with a cross-feed control methodology that band-pass filters a pitch rate and a roll rate then feeds back the respective signals to a lateral cyclic input and a longitudinal cyclic input of said fly-by-wire type flight control system. 8. The system as recited in claim 7, wherein said cross-feed control methodology is filtered in response to a calculated frequency. 9. The system as recited in claim 8, wherein said cross-feed control methodology band-pass filters said pitch rate and said roll rate in response to a rotor speed. 10. A fly-by-wire flight control system implemented method of lead/lag damping for a rotary-wing aircraft rotor system comprising the steps of: (A) band pass filtering a pitch rate and a roll rate;(B) cross-feeding the pitch rate and the roll rate from said step (A);(C) feeding back the cross-feed signals from said step (B) to a lateral cyclic input and a longitudinal cyclic input of a fly-by-wire type flight control system. 11. A method as recited in claim 10, wherein said step (A) further comprises: (a) varying the band-pass filter in response to rotor speed. 12. A method as recited in claim 10, wherein said step (A) further comprises: (b) varying the band-pass filter center frequency in response to a calculated frequency. 13. A method as recited in claim 10, further comprising the steps of: (D) directly feeding a pitch rate and a roll rate to the lateral cyclic input and the longitudinal cyclic input of the fly-by-wire type flight control system. 14. The aircraft as recited in claim 1, wherein said lead/lag damper reacts in-plane edgewise motion of said at least one rotor blade assembly to dampen vibration. 15. The system as recited in claim 7, wherein said electronic lead/lag damper method supplements a lead/lag damper mounted to a rotor hub and at least one rotor blade assembly, the lead/lag damper provides a first damping value less than a required damping value of said at least one rotor blade assembly. 16. The system as recited in claim 15, wherein said electronic lead/lag damper method provides a damping value which defines at least the difference between the first damping value and a required damping value. 17. The system as recited in claim 16, wherein feeding back the cross-feed signals from said step (B) to the lateral cyclic input and the longitudinal cyclic input of the fly-by-wire type flight control system supplements a lead/lag damper mounted to a rotor hub and at least one rotor blade assembly, the lead/lag damper provides a first damping value less than a required damping value of the at least one rotor blade assembly. 18. The system as recited in claim 16, wherein feeding back the cross-feed signals from said step (B) provides a damping value which defines at least the difference between the first damping value and a required damping value.