초록 ▼

The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at leas

The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at least one threshold value; if said current value exceeds said threshold, determining a new flaps setting capable of producing an improvement in at least one of a selected aft body contact margin and a selected nose gear contact margin for the aircraft; and adjusting the flaps to said new flaps setting.

대표청구항 ▼

1. A method of modifying a pitch attitude of an aircraft during landing comprising: commanding trailing edge flaps to move to a landing setting;providing a current value for a flight condition parameter;providing a current trailing edge flaps setting;comparing said current value of the flight condit

1. A method of modifying a pitch attitude of an aircraft during landing comprising: commanding trailing edge flaps to move to a landing setting;providing a current value for a flight condition parameter;providing a current trailing edge flaps setting;comparing said current value of the flight condition parameter to a plurality of thresholds having an acceptable range between said plurality of thresholds; andif said current value of the flight condition parameter is outside the acceptable range:(1) adjusting the trailing edge flaps to a new flaps setting;(2) keeping the trailing edge flaps in the new flaps setting for a predetermined time period; and(3) after the predetermined time period if said current value of the flight condition parameter is outside the acceptable range and the trailing edge flaps are not in final trailing edge flap positions then repeating (1), (2), and (3) until the current value of the flight condition parameter is within the acceptable range or the trailing edge flaps are in the final trailing edge flap positions. 2. The method of claim 1, wherein said flight condition parameter is a current approach angle of attack αCUR. 3. The method of claim 2, wherein said plurality of thresholds comprise an upper threshold angle αMAX and a lower threshold angle αMIN. 4. The method of claim 3, wherein if αCUR is greater than αMAX the new flaps setting is adjusted higher so that the trailing edge flaps are extended away from wings of the aircraft. 5. The method of claim 3, wherein if αCUR is less than αMIN the new flaps setting is adjusted lower so that the trailing edge flaps are retracted towards the wings of the aircraft. 6. The method of claim 3, wherein αMAX is 6.5 degrees. 7. The method of claim 3, wherein αmin is 4.5 degrees. 8. The method of claim 1, wherein said flight condition parameter is a current airspeed V. 9. The method of claim 8, wherein said plurality of thresholds comprise a first threshold which comprises a first airspeed which is above a reference speed VREF by a first amount and a second threshold which comprises a second airspeed which is above the reference speed VREF by a second amount which is less than the first amount. 10. The method of claim 9, wherein if the current airspeed V is below the second threshold the new flaps setting is adjusted higher so that the trailing edge flaps are extended away from wings of the aircraft. 11. The method of claim 9, wherein if the current airspeed V is above the first threshold the new flaps setting is adjusted lower so that the trailing edge flaps are retracted towards the wings of the aircraft. 12. The method of claim 9, wherein the plurality of thresholds comprise 3, 8, 13, and 20, knots above VREF. 13. The method of claim 1 wherein the acceptable range applies a hysteresis to each of the plurality of the thresholds. 14. The method of claim 13 wherein the hysteresis applied to each of the plurality of the thresholds is 0.4 degrees. 15. A method of reducing acoustic noise during a landing of an aircraft comprising: providing a computer readable memory medium, at least one processor, and program instructions stored by the computer readable memory medium;executing the program instructions with the at least one processor to modify a pitch attitude of the aircraft during landing by:commanding trailing edge flaps to move to a landing setting;providing a current value for a flight condition parameter;providing a current trailing edge flaps setting;comparing said current value of the flight condition parameter to a plurality of thresholds having an acceptable range between said plurality of thresholds; andif said current value of the flight condition parameter is outside the acceptable range:(1) adjusting the trailing edge flaps to a new flaps setting;(2) keeping the trailing edge flaps in the new flaps setting for a predetermined time period; and(3) after the predetermined time period if said current value of the flight condition parameter is outside the acceptable range and the trailing edge flaps are not in final trailing edge flap positions then repeating (1), (2), and (3) until the current value of the flight condition parameter is within the acceptable range or the trailing edge flaps are in the final trailing edge flap positions. 16. The method of claim 15, wherein said flight condition parameter is a current approach angle of attack αCUR. 17. The method of claim 15, wherein said flight condition parameter is a current aircraft airspeed V. 18. The method of claim 15 further comprising the program instructions causing the at least one processor to apply a hysteresis to each of the plurality of the thresholds to obtain the acceptable range. 19. A means of transportation comprising: an aircraft;a computer readable memory medium stored on the aircraft;program instructions stored by the computer readable memory medium; andat least one processor configured to execute the program instructions to modify a pitch attitude of the aircraft during landing;wherein the program instructions are configured to: command trailing edge flaps to move to a landing setting; provide a current value for a flight condition parameter; provide a current trailing edge flaps setting; compare said current value of the flight condition parameter to a plurality of thresholds having an acceptable range between said plurality of thresholds; and if said current value of the flight condition parameter is outside the acceptable range then: (1) adjust the trailing edge flaps to a new flaps setting; (2) keep the trailing edge flaps in the new flaps setting for a predetermined time period; and (3) after the predetermined time period if said current value of the flight condition parameter is outside the acceptable range and the trailing edge flaps are not in final trailing edge flap positions then repeat (1), (2), and (3) until the current value of the flight condition parameter is within the acceptable range or the trailing edge flaps are in the final trailing edge flap positions. 20. The means of transportation of claim 19, wherein said flight condition parameter is a current approach angle of attack αCUR. 21. The means of transportation of claim 19, wherein said flight condition parameter is a current aircraft airspeed V. 22. The means of transportation of claim 19, wherein the program instructions are further configured to apply a hysteresis to each of the plurality of the thresholds to obtain the acceptable range.