IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0704650
(2003-11-12)
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우선권정보 |
FR-02 14871(2002-11-27) |
발명자
/ 주소 |
- D'Ouince,Arnaud
- Ley,Bruno
- Gaucheron,Philippe
- Bellier,Arnaud
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출원인 / 주소 |
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대리인 / 주소 |
Stevens, Davis, Miller &
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인용정보 |
피인용 횟수 :
2 인용 특허 :
2 |
초록
▼
Detection of the failure of a pressure sensor of an air data system of an aircraft having at least two pressure sensors includes measuring first and second pressure values with the aid of the two pressure sensors, respectively. The deviation between the first and second pressure values is calculated
Detection of the failure of a pressure sensor of an air data system of an aircraft having at least two pressure sensors includes measuring first and second pressure values with the aid of the two pressure sensors, respectively. The deviation between the first and second pressure values is calculated, and this deviation is compared with a predetermined threshold value. If the deviation is greater than the threshold value, a failure cue relating to the air data system is displayed on a display device that is mounted in the aircraft.
대표청구항
▼
The invention claimed is: 1. A process for detecting the failure of a pressure sensor of an air data system of an aircraft, which comprises at least two pressure sensors, wherein at least the following first series of steps is carried out: A1) making pressure measurements with the aid of said two p
The invention claimed is: 1. A process for detecting the failure of a pressure sensor of an air data system of an aircraft, which comprises at least two pressure sensors, wherein at least the following first series of steps is carried out: A1) making pressure measurements with the aid of said two pressure sensors so as to obtain, respectively, first and second pressure values; A2) calculating the deviation between said first and second pressure values; A3) comparing and deviation with a predetermined threshold value; and A4) if said deviation is greater than said threshold value, displaying a failure cue relating to said air data system on a display device which is mounted on said aircraft. 2. The process as claimed in claim 1, wherein the following steps are moreover carried out: measuring the speed of the aircraft relative to the air in such a way as to obtain an air speed value; comparing the air speed value with a predetermined speed threshold; and displaying a failure cue in step A4), only if said air speed value is greater than said speed threshold. 3. The process as claimed in claim 2, wherein said speed threshold is substantially equal to 25 m/s. 4. The process as claimed in claim 1, wherein said threshold value is substantially equal to 30 mbar. 5. The process as claimed in claim 1, wherein said two pressure sensors are mounted on either side of the longitudinal axis of the aircraft, on the fuselage of the latter. 6. The process as claimed in claim 1, wherein at least three pressure sensors are provided for said air data system, wherein in step A1), pressure measurements are made with the aid of said three pressure sensors, wherein in step A2), all the possible deviations between the various pressure values taken pairwise are calculated, wherein in step A3) , all the deviations thus calculated are compared with said threshold value, and wherein in step A4), a failure cue is or is not displayed depending on the various comparisons thus carried out. 7. The process as claimed in claim 6, wherein in step A4), a failure cue is displayed if at least one of said deviations is greater than said threshold value. 8. The process as claimed in claim 6, wherein in step A4), a failure cue is displayed only if all said deviations are greater than said threshold value. 9. The process as claimed in claim 1, wherein at least the following second series of steps is moreover carried out: B1) making pressure measurements with the aid of at least one pressure sensor of the air data system, on the aircraft which is on the ground and the cabin of which is not pressurized, so as to obtain a third pressure value; B2) on the basis of this third pressure value, calculating a first altitude corresponding to the ground altitude; B3) pressurizing the cabin of the aircraft; B4) causing the aircraft to take off; B5) at a predetermined time after takeoff, making pressure measurements with the aid of said one pressure sensor so as to obtain a fourth pressure value; B6) on the basis of this fourth pressure value, calculating a second altitude corresponding to the aircraft's altitude; B7) calculating a third altitude corresponding to the aircraft's altitude with respect to the ground, from said first and second altitudes; B8) comparing said third altitude with a predetermined altitude threshold; and B9) if said third altitude is less than said predetermined altitude threshold, displaying a failure cue relating to said air data system on the display device. 10. The process as claimed in claim 9, wherein, in the case of an aircraft fitted with at least two engines, said altitude threshold is less than the altitude reached by the aircraft, at said predetermined time after takeoff, should there be a fault with at least one of said engines. 11. The process as claimed in claim 10, wherein said predetermined time after takeoff is substantially equal to 30 seconds, and wherein said altitude threshold is substantially equal to 30 meters. 12. The process as claimed in claim 9, wherein the following steps are moreover carried out: monitoring the operation of engines of the aircraft; and when a malfunction of at least one of the engines of the aircraft is detected, a failure cue is not displayed if appropriate in step B9). 13. The process as claimed in claim 1, wherein at least the following third series of steps is moreover carried out: C1) providing on at least one of the pressure sensors at least one detector that is able to detect a failed coupling between the corresponding pressure sensor and a probe of the air data system, which is associated with said correspoinding pressure sensor; C2) performing acquisition on the ground, before takeoff, of cues relating to said coupling, which emanate from said detectors; and C3) if at least one of said detectors signals a failed coupling, displaying a failure cue relating to said air data system on the display device. 14. The process as claimed in claim 13, wherein at least one of said detectors is integrated into a pneumatic connector intended to join a pneumatic tube, associated with the corresponding probe, to the corresponding pressure sensor. 15. A device for detecting a failure of the process sensor of an air data system of an aircraft, which comprises at least two pressure sensors, said device comprising: an acquisition section that acquires values of measurements made by said pressure sensors so as to obtain, respectively, first and second pressure values; a calculation section that calculates the deviation between said first and second pressure values; a comparison section that compares said deviation with a predetermined threshold value; a selection section that outputs an order to display a failure cue, if said deviation is greater than said threshold value; and a display section that displays, on at least one display unit which is mounted on said aircraft, a failure cue relating to said air data system. 16. A device for detecting a failure of a pressure sensor of an air data system of an aircraft, which comprises at least two pressure sensors, said device comprising: means for acquiring values of measurements made by said pressure sensors so as to obtain, respectively, first and second pressure values; means for calculating the deviation between said first and second pressure values; means for comparing said deviation with a predetermined threshold value; means for selecting and outputting an order to display a failure cue; if said deviation is greater than said threshold value; and means for displaying, on at least one display device which is mounted on said aircraft, a failure cue relating to said air data system.
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