IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0939928
(2007-11-14)
|
등록번호 |
US-7844373
(2011-01-31)
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우선권정보 |
FR-06 09938(2006-11-14) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Lowe Hauptman Ham & Berner, LLP
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
1 |
초록
▼
The present invention relates to a method and a system for monitoring the following of a reference trajectory by an aircraft. The values that flight parameters of the aircraft will have on completion of a time interval ΔT are extrapolated, the time interval ΔT corresponding to a duration
The present invention relates to a method and a system for monitoring the following of a reference trajectory by an aircraft. The values that flight parameters of the aircraft will have on completion of a time interval ΔT are extrapolated, the time interval ΔT corresponding to a duration less than the remaining duration of validity of a guidance instruction presently applied by the aircraft and during which the instruction remains unchanged, by measuring at the start of the time interval ΔT the actual values of the flight parameters as well as external conditions on which the performance of the aircraft depends, then by making the assumption that the instruction values of the flight parameters will remain constant throughout the time interval ΔT, an alarm being raised if the extrapolated values of the flight parameters are not substantially equal to theoretical values of the flight parameters deduced from the reference trajectory on completion of the time interval considered ΔT or if they are not compatible with the actual performance of the aircraft having regard to the measured external conditions.
대표청구항
▼
The invention claimed is: 1. A method for monitoring a following of a reference trajectory by an aircraft, wherein the values that flight parameters of the aircraft will have on completion of a time interval (ΔT) are extrapolated, the time interval (ΔT) corresponding to a duration less
The invention claimed is: 1. A method for monitoring a following of a reference trajectory by an aircraft, wherein the values that flight parameters of the aircraft will have on completion of a time interval (ΔT) are extrapolated, the time interval (ΔT) corresponding to a duration less than a remaining duration of validity of a guidance instruction presently applied by the aircraft and during which the instruction remains unchanged, extrapolating the values comprising the steps of: measuring at the start of the time interval (ΔT) actual values of the flight parameters as well as external conditions on which performances of the aircraft depends; considering that instruction values of the flight parameters will remain constant throughout the time interval (ΔT) ; raising an alarm if extrapolated values of the flight parameters are different from theoretical values of the flight parameters deduced from the reference trajectory on completion of the time interval considered (ΔT) or if they are not compatible with actual performances of the aircraft having regard to the measured external conditions. 2. The method as claimed in claim 1, wherein the flight parameters of the aircraft whose actual values are measured at the start of the time interval (ΔT), then whose instruction values are assumed constant throughout the interval (ΔT), include in a non-exhaustive manner a speed and/or an acceleration and/or a fuel consumption and/or a climb/descent rate and/or an air slope. 3. The method as claimed in claim 1, wherein the flight parameters of the aircraft whose values on completion of the time interval (ΔT) are extrapolated include in a non-exhaustive manner a position and/or an altitude and/or a speed and/or a ground slope and/or a quantity of fuel remaining. 4. The method as claimed in claim 1, wherein the external conditions whose actual values are measured at the start of the time interval (ΔT), then which are assumed constant throughout the interval (ΔT), include in a non-exhaustive manner a direction and a speed of the wind and/or a temperature of the air and/or a density of the air and/or an atmospheric pressure. 5. The method as claimed in claim 1, wherein new guidance instructions for converging and remaining on the reference trajectory are formulated in the case where the extrapolated values of the flight parameters are not substantially equal to the theoretical values deduced from the reference trajectory on completion of the time interval considered (ΔT). 6. The method as claimed in claim 1, wherein new guidance instructions for remaining compatible with the performance of the aircraft formulated in the case where the extrapolated values of the flight parameters are not compatible with the actual performance of the aircraft having regard to the measured external conditions. 7. The method as claimed in claim 1, wherein the measured values of the external conditions on which the performance of the aircraft depends are used as a function of their prospects of persisting throughout the time interval (ΔT) during which they are assumed constant. 8. The method as claimed in claim 1, wherein the duration of the time interval (ΔT) determines a type of alarm, each type of alarm corresponding to a pair comprising a minimum duration and a maximum duration. 9. The method as claimed in claim 1, wherein the values that the flight parameters of the aircraft will have on completion of the time interval (ΔT) are extrapolated by considering that the reference trajectory is a sequence of adjoining segments. 10. The system for monitoring the following of a reference trajectory by an aircraft, wherein a method as claimed in claim 1 is implemented. 11. The system as claimed in claim 10, comprising a short-term monitoring sub-module and a medium-term monitoring sub-module. 12. The system as claimed in claim 11, wherein each of the sub-modules filters out the events on which it extrapolates the values that the flight parameters of the aircraft will have on completion of the time interval (ΔT), as a function of their prospects of persisting during the time interval (ΔT), so as to limit false alarms. 13. The system as claimed in claim 11, wherein the extrapolations carried out by the medium-term monitoring sub-module are used to confirm or deny the extrapolations made by the short-term monitoring sub-module, so as to limit false alarms raised by the short-term monitoring sub-module. 14. The system as claimed in claim 10, wherein the flight parameters of the aircraft whose actual values are measured at the start of the time interval (ΔT), then whose instruction values are assumed constant throughout the interval (ΔT), include in a non-exhaustive manner a speed and/or an acceleration and/or a fuel consumption and/or a climb/descent rate and/or an air slope. 15. The system as claimed in claim 10, wherein the flight parameters of the aircraft whose values on completion of the time interval (ΔT) are extrapolated include in a non-exhaustive manner a position and/or an altitude and/or a speed and/or a ground slope and/or a quantity of fuel remaining. 16. The system as claimed in claim 10, wherein the external conditions whose actual values are measured at the start of the time interval (ΔT), then which are assumed constant throughout the interval (ΔT), include in a non-exhaustive manner a direction and a speed of the wind and/or a temperature of the air and/or a density of the air and/or an atmospheric pressure. 17. The system as claimed in claim 10, wherein new guidance instructions for converging and remaining on the reference trajectory are formulated in the case where the extrapolated values of the flight parameters are not substantially equal to the theoretical values deduced from the reference trajectory on completion of the time interval considered (ΔT). 18. The system as claimed in claim 10, wherein new guidance instructions for remaining compatible with the performance of the aircraft are formulated in the case where the extrapolated values of the flight parameters are not compatible with the actual performance of the aircraft having regard to the measured external conditions. 19. The system as claimed in claim 10, wherein the measured values of the external conditions on which the performance of the aircraft depends are used as a function of their prospects of persisting throughout the time interval (ΔT) during which they are assumed constant. 20. The system as claimed in claim 10, wherein the duration of the time interval (ΔT) determines a type of alarm, each type of alarm corresponding to a pair comprising a minimum duration and a maximum duration.
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