[특허]Method for determining a state of credibility of measurements made by sensors of an aircraft and corresponding system

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Method for determining a state of credibility of measurements made by sensors of an aircraft and corresponding system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G06F-019/00 G01P-021/00 G01P-013/02 G01P-005/16 B64D-043/02 G01B-021/00 G01G-023/01 G01M-009/06 G01P-003/80
출원번호	US-0388781 (2013-03-26)
등록번호	US-10078100 (2018-09-18)
우선권정보	FR-12 00924 (2012-03-28)
국제출원번호	PCT/EP2013/056368 (2013-03-26)
국제공개번호	WO2013/144126 (2013-10-03)
발명자 / 주소	Dupont De Dinechin, Sebastien
출원인 / 주소	DASSAULT AVIATION
대리인 / 주소	Davidson, Davidson & Kappel, LLC
인용정보	피인용 횟수 : 0 인용 특허 : 3

초록
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A method for determining a state of credibility of measurements made by sensors of an aircraft is provided. This method includes determining a speed of the aircraft, from static and total pressure measurements, determining a coefficient of lift of the aircraft from an incidence measurement and from said speed, determining a weight of the aircraft, determining if an equation of lift of the aircraft is satisfied, activating a state of optimal credibility, wherein the measurements made by said sensors are considered to be reliable if the said equation of li...

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1. A method for determining a state of credibility of measurements made by sensors of an aircraft during a flight of the aircraft, the sensors comprising static pressure sensors, total pressure sensors and incidence sensors, the method comprising: determining a speed related data value of the aircraft from measurements of static pressure and total pressure from the static pressure sensor and total pressure sensor;determining a first coefficient of lift of the aircraft from a measurement of incidence from the incidence sensor and from the speed data value,determining an estimated weight of the aircraft;determining whether an equation of lift of the aircraft is satisfied, based on the estimated weight, a data value representative of the load factor of the aircraft, the speed value and the first coefficient of lift of the aircraft, with a first predetermined tolerance;activating a state of optimal credibility, wherein the measurements made by the static pressure sensor, total pressure sensor and incidence sensor are considered to be reliable, if the equation of lift is satisfied with the first tolerance;activating at least one state of non-optimal credibility, wherein the measurements made by at least one sensor from among the static pressure sensor, total pressure sensor and incidence sensor are considered to be unreliable, if the equation of lift is not satisfied with the first tolerance. 2. The method as recited in claim 1 wherein the speed data value is a Mach number Ma, the determining whether an equation of lift of the aircraft is satisfied including verifying if the equivalence 0.7SPSMa2{tilde over (C)}Z=nZ{tilde over (m)}g holds with the first predetermined tolerance, wherein S represents a reference surface of the aircraft, the first coefficient of lift {tilde over (C)}z is a projection along a selected axis Z, for a coefficient of lift of the aircraft along an axis orthogonal to the velocity vector of the aircraft and a drag coefficient parallel to this velocity vector, nZ designates the data value representative of the load factor of the aircraft along the axis Z, and g the acceleration due to gravity. 3. The method as recited in claim 2 wherein the selected axis Z is an axis Z perpendicular to the longitudinal axis of the aircraft defined in particular as the mean axis of thrust of the engines. 4. The method as recited in claim 1 wherein the first coefficient of lift is determined from a lookup correlation table providing an estimate of the value of the first coefficient of lift based on the speed data value, the incidence measurement and a flight configuration of the aircraft. 5. The method as recited in claim 1 wherein the determination of the estimated weight of the aircraft includes: determining a first weight of the aircraft, based on characteristics of the aircraft determined prior to or during the take off of the aircraft;determining a second weight of the aircraft during the flight of the aircraft, based on an equation of lift of the aircraft expressing the weight of the aircraft as a function of a data value representative of the load factor of the aircraft, a second coefficient of lift of the aircraft, a speed data value of the aircraft and a static pressure of an air mass through which the aircraft passes, determined from measurements made by the sensors of the aircraft during the flight of the aircraft; andassessing the estimated weight, based on a weight calculated taking into account the first and second weights. 6. The method as recited in claim 5 wherein the weight calculated taking into account the first and second weights is based on the weighted average of the first and second weights. 7. The method as recited in claim 5 wherein the first and second weights are weights of the aircraft at an initial instant of time at the ramp, the assessing the estimated weight including determining the weight calculated on the basis of the first and second weights, determining a weight of fuel consumed from the initial instant of time, the estimated weight being assessed by subtracting the weight of fuel consumed from the calculated weight. 8. The method as recited in claim 1 further comprising determining an auxiliary altitude of the aircraft based on at least one measurement of geographical altitude obtained independently of a pressure sensor; and making available to a crew of the aircraft the auxiliary altitude, at least when a state of non-optimal credibility is activated. 9. The method as recited in claim 8 wherein the at least one measurement of geographical altitude obtained independently of a pressure sensor is derived from a satellite positioning sensor. 10. The method as recited in claim 8 wherein the auxiliary altitude is determined based on an altitude ZGPS determined independently of a pressure sensor of the aircraft, in the form of: ZP**(t)=ZGPS(t)−ΔZ**(j)where ΔZ**(j) is a correction term adjusted periodically, in order to correct a variation between the standard atmosphere and the actual atmosphere of the flight of the aircraft, the correction term taking a fixed value when the state of non-optimal credibility is activated. 11. The method as recited in claim 1 further comprising, at least when the state of non-optimal credibility s activated, determining at least one auxiliary speed data value based on at least one measurement from a geographical position sensor of the aircraft; and making available to a crew of the aircraft the auxiliary speed data value. 12. The method as recited in claim 1 wherein the state of non-optimal credibility is selected from: a state of high credibility, in which the measurements of at least one sensor from the static pressure sensor and total pressure sensor are considered to be unreliable and the measurements of the incidence sensor are considered to be reliable, anda state of low credibility in which the measurements of the incidence sensor are considered to be unreliable. 13. The method as recited in claim 12 wherein at least in the state of high credibility, the method includes determining an auxiliary speed data value of high credibility, based on the measurement of incidence made by the incidence sensor, as a function of a static pressure estimator determined based on at least one measurement obtained independently of a pressure sensor of the aircraft. 14. The method as recited in claim 13 wherein the high credibility auxiliary speed data value is determined periodically at each instant of time based on a high credibility auxiliary speed data value obtained at a preceding instant of time, with the use of a recursive series. 15. The method as recited in claim 12 further comprising: determining a state of reliability of the measurements made by the incidence sensor, the determining the state of reliability of the measurements made by the incidence sensor comprising: determining a static pressure estimator based on at least one measurement obtained independently of a pressure sensor of the aircraft;determining an auxiliary speed data value, based on the static pressure estimator,determining a second coefficient of lift of the aircraft, based on a measurement of incidence of the incidence sensor and the auxiliary speed data value;determining whether the equation of lift of the aircraft is satisfied, based on the estimated weight, the auxiliary speed data value and the second coefficient of lift of the aircraft, with a second predetermined tolerance;confirming the state of low credibility, in which the measurements of the incidence sensor are considered to be unreliable, if the equation of lift is not satisfied with the second predetermined tolerance;activating the state of high credibility, in which the measurements of at least one sensor from the static pressure sensor and total pressure sensor are considered to be unreliable and the measurements of the incidence sensor are considered to be reliable, if the equation of lift is satisfied with the predetermined tolerance. 16. The method as recited in claim 1 further comprising estimating the speed of wind, the wind speed being determined periodically based on the speed data values derived from a geographical position sensor. 17. The method as recited in claim 16 wherein, at least in the state of low credibility, the method further comprising determining an auxiliary speed data value of reliable credibility, comprising: determining speed data values of the aircraft relative to the ground based on measurements made by a geographical position sensor of the aircraft;estimating a wind speed; anddetermining the low credibility auxiliary speed data value relative to the air, based on the speed data values of the aircraft relative to the ground and the estimate of the wind speed. 18. The method as recited in claim 1 further comprising, in the state of non-optimal credibility, displaying a warning—alert message for a crew of the aircraft, indicating that the measurements made by at least one sensor selected from among the static pressure sensor, total pressure sensor and incidence sensor are not reliable. 19. A system for determination of a state of credibility of measurements made by sensors of an aircraft during a flight of the aircraft, the sensors comprising the static pressure sensor, total pressure sensor and incidence sensor, the system comprising: a computer configured for determining a speed data value of the aircraft, based on measurements of static pressure PS and total pressure PT made by the static pressure and total pressure sensors,the computer being configured for determining a first coefficient of lift of the aircraft based on a measurement of incidence from the incidence sensor and the speed data value,the computer being configured for determining an estimated weight of the aircraft,the computer being configured for determining whether the equation of lift of the aircraft is satisfied, based on the estimated weight, a data value representative of the load factor, the speed data value and the coefficient of lift of the aircraft, with a first predetermined tolerance,the computer being configured for activating a state of optimal credibility, in which the measurements made by the static pressure sensor, total pressure sensor and incidence sensor are considered to be reliable, if the equation of lift is satisfied with the first tolerance,the computer being configured for activating at least one state of non optimal credibility, in which the measurements made by at least one sensor from among the static pressure sensor, total pressure sensor and incidence sensor are considered to be unreliable, if the equation of lift is not satisfied with the first tolerance.

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Method for determining a state of credibility of measurements made by sensors of an aircraft and corresponding system

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Method for determining a state of credibility of measurements made by sensors of an aircraft and corresponding system

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