IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0883783
(2004-07-06)
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등록번호 |
US-7415396
(2008-08-19)
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우선권정보 |
FR-03 08269(2003-07-07) |
발명자
/ 주소 |
- D'Ouince,Arnaud
- Andreoletti,R��mi
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출원인 / 주소 |
|
대리인 / 주소 |
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인용정보 |
피인용 횟수 :
2 인용 특허 :
4 |
초록
▼
A method and device for monitoring the validity of a parameter calculated by an anemometric unit of an aircraft may employ a first section for taking into account n first data, each dependent on the parameter being monitored and n being greater than or equal to 1. A second section takes into account
A method and device for monitoring the validity of a parameter calculated by an anemometric unit of an aircraft may employ a first section for taking into account n first data, each dependent on the parameter being monitored and n being greater than or equal to 1. A second section takes into account p second data that each depends on a value obtained from a data source external to the anemometric unit, where P is greater than or equal to 2. A calculator calculates, for each of the second data, a difference between this second datum and a first datum of the same type. A comparator compares the absolute value of each of the calculated differences with a threshold value. A deducing section deduces from the comparisons that the monitored parameter is invalid if the absolute values of two of the various differences are greater than the corresponding threshold values.
대표청구항
▼
The invention claimed is: 1. A method for monitoring the validity of a parameter calculated by an anemometric unit of an aircraft having three engines, the method comprising: (a) determining a first datum based on the parameter calculated by the anemometric unit; (b) determining three second datums
The invention claimed is: 1. A method for monitoring the validity of a parameter calculated by an anemometric unit of an aircraft having three engines, the method comprising: (a) determining a first datum based on the parameter calculated by the anemometric unit; (b) determining three second datums corresponding to the first datum, each of the second datums being determined from a measured value obtained from a separate probe associated with a separate one of the engines; (c) calculating, for each of the second datums, a difference between the second datum and the corresponding first datum; (d) comparing the absolute value of each of the calculated differences with a predetermined threshold value corresponding to the monitored parameter; and (e) determining from the comparisons for the monitored parameter: that the parameter is invalid if the absolute values of the three calculated differences are greater than the predetermined threshold value, and that the parameter is valid if the absolute values of the three calculated differences are not greater than the predetermined threshold value. 2. A method for monitoring the validity of a parameter calculated by an anemometric unit of an aircraft having two engines, the method comprising: (a) determining a first datum based on the parameter calculated by the anemometric unit; (b) determining two second datums corresponding to the first datum, each of the second datums being determined from a measured value obtained from a separate probe associated with a separate one of the engines; (c) calculating, for each of the second datums, a difference between the second datum and the corresponding first datum; (d) comparing the absolute value of each of the calculated differences with a predetermined threshold value corresponding to the monitored parameter; (e) determining from the comparisons for the monitored parameter: that the parameter is invalid if the absolute values of the two calculated differences are greater than the predetermined threshold value, and that the parameter is valid if the absolute values of the two calculated differences are not greater than the predetermined threshold value; and (f) disregarding the determination of the validity or invalidity of the parameter in the event of an engine malfunction. 3. A method for monitoring the validity of a parameter generated by an anemometric unit of an aircraft, the method comprising: (a) determining a first datum based on the parameter generated by the anemometric unit; (b) determining two second datums corresponding to the first datum, each of the second datums being obtained from a separate source that is external to the anemometric unit; (c) calculating, for each of the second datums, a difference between the second datum and the corresponding first datum; (d) comparing the absolute value of each of the calculated differences with a predetermined threshold value corresponding to the monitored parameter; and (e) determining from the comparisons for the monitored parameter: that the parameter is invalid if the absolute values of the two calculated differences are greater than the predetermined threshold value, and that the parameter is valid if the absolute values of the two calculated differences are not greater than the predetermined threshold value. 4. The method of claim 3, wherein the first datum is calculated from the generated parameter. 5. The method of claim 3, wherein the first datum corresponds to the generated parameter. 6. The method of claim 3, wherein at least one of the second datums is calculated from a measured value obtained from an engine probe. 7. The method of claim 3, wherein at least one of the second datums corresponds to a measured value obtained from an engine probe. 8. The method of claim 3, wherein: operations (a) through (e) are performed for each of two parameters, and the first datum obtained for one of the parameters depends simultaneously on the two parameters. 9. The method of claim 3, wherein the generated parameter monitored by the anemometric unit is one of a total pressure, a static pressure, and a total temperature. 10. The method of claim 9, wherein: operations (a) through (e) are performed for either one parameter or each of two parameters, and the first datum is one of: (i) a barometric altitude calculated from a static pressure that is being monitored, and (ii) a velocity of the aircraft with respect to the air calculated from static and total pressures that are being monitored. 11. The method of claim 3, wherein one of the second datums corresponds to one of: an altitude value provided by a satellite positioning system, a total pressure value measured by an engine probe, a static pressure value measured by an engine probe, a total temperature value measured by an engine probe, a velocity value provided by a velocity estimation section, a static pressure value measured by a multi-functional probe, a static pressure value measured by a standby instrument, and a total pressure value measured by a standby instrument. 12. The method of claim 3, wherein the following differences are calculated in operation (c) so as to monitor a static pressure generated by the anemometric unit: the difference between a barometric altitude, calculated from the static pressure, and an altitude value provided by a satellite positioning system, the difference between a barometric altitude, calculated from the static pressure, and an altitude calculated from a static pressure value measured by a standby instrument, the difference between the static pressure and a static pressure value measured by an engine probe, the difference between the static pressure and a static pressure value measured by a multi-functional probe, and the difference between a velocity of the aircraft with respect to the air, calculated from the static pressure, and a velocity value provided by a velocity estimation section. 13. The method of claim 3, wherein the following differences are calculated in operation (c) so as to monitor a total pressure generated by the anemometric unit: the difference between the total pressure and a total pressure value measured by an engine probe, the difference between a velocity of the aircraft with respect to the air, calculated from the total pressure, and a velocity value provided by a velocity estimation section, and the difference between a velocity of the aircraft with respect to the air, calculated from the total pressure, and a velocity calculated from a total pressure value measured by a standby instrument. 14. The method of claim 3, wherein the following differences are calculated in operation (c) so as to monitor a total temperature generated by the anemometric unit: the difference between a barometric altitude, corrected with the aid of the total temperature, and an altitude value provided by a satellite positioning system; the difference between the total temperature and a total temperature value measured by an engine probe, and the difference between a velocity of the aircraft with respect to the air, calculated from the total temperature, and a velocity value provided by a velocity estimation section. 15. The method of claim 3, wherein the monitoring of the validity of the parameter is disabled when the aircraft is in a particular flight phase. 16. An apparatus that monitors the validity of a parameter, the apparatus comprising: an aircraft anemometric unit that generates the parameter; a first determining section that determines a first datum based on the parameter generated by the anemometric unit; a second determining section that determines two second datums corresponding to the first datum, each of the second datums being obtained from a separate source that is external to the anemometric unit; a calculator that calculates, for each of the second datums, a difference between the second datum and the corresponding first datum; a comparator that compares the absolute value of each of the calculated differences with a predetermined threshold value corresponding to the monitored parameter; and a determining section that determines from the comparisons for the monitored parameter: that the parameter is invalid if the absolute values of the two calculated differences are greater than the predetermined threshold value, and that the parameter is valid if the absolute values of the two calculated differences are not greater than the predetermined threshold value.
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