METHOD FOR MONITORING THE CONSISTENCY OF AN ATMOSPHERIC PRESSURE VALUE USED TO CONFIGURE ON-BOARD INSTRUMENTS OF AN AIRCRAFT
The method and system address the issue of erroneous atmospheric pressure entries in aircraft instruments by estimating and comparing pressure values with predefined thresholds, ensuring accurate configuration and enhancing flight safety.
Patent Information
- Application Number
- FR2023013847
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2023-12-08
- Publication Date
- 2026-01-16
- Estimated Expiration
- 2043-12-08
AI Technical Summary
Existing systems fail to effectively monitor and alert pilots when erroneous atmospheric pressure values, such as QFE or QNH, are entered into aircraft instruments, which can significantly impact flight trajectory and safety.
A method and system that estimate the static pressure at a selected airport using aircraft's current static pressure, temperature, and geometric altitude, and compare it with the entered pressure value to generate alerts if inconsistencies exceed predefined thresholds.
Ensures the accuracy of atmospheric pressure values used for aircraft instruments by generating alerts for inconsistent entries, thereby enhancing flight safety and reducing the risk of navigational errors.
Smart Images
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Abstract
Description
Title of the invention: METHOD FOR MONITORING THE CONSISTENCY OF AN ATMOSPHERIC PRESSURE VALUE USED TO CONFIGURE ON-BOARD INSTRUMENTS OF AN AIRCRAFT technical field
[0001] The present invention relates to consistency monitoring of an atmospheric pressure value, QFE or QNH (typically, entered by the aircraft pilot in an aircraft instrument human-machine interface), intended to be used to configure aircraft instruments. STATE OF PRIOR ART
[0002] In barometric navigation, an aircraft is guided by means of a barometric vertical positioning (altitude) dependent on isobaric / barometric pressure lines. This barometric navigation can be used in all phases of flight (climb, cruise, descent, and approach). The barometric altitude is calculated relative to an atmospheric pressure reference. Above a reference altitude (called the "transition altitude") during climb, and called the "transition flight level" during descent), the atmospheric pressure reference considered is 1013 hPa.Below this reference altitude, the atmospheric pressure reference is either equal to the atmospheric pressure measured at the level of the destination airfield / airport (the atmospheric pressure reference is then designated by the international code "QFE"), or to the atmospheric pressure measured at the level of the destination airfield / airport then reduced to sea level (the atmospheric pressure reference is then designated by the international code "QNH").
[0003] Below the transition altitude or transition flight level, the atmospheric pressure value QNH or QFE is of major importance because it directly influences the aircraft's vertical position, and therefore its trajectory during level flight, climb, descent, and approach. An atmospheric pressure value, QFE or QNH, is entered by the pilot via a human-machine interface of the aircraft's flight instruments, for example, an EFISCP (Electronic Flight Instrument System Control Panel), just before crossing the transition altitude or transition flight level.
[0004] It is therefore desirable to provide a solution which allows monitoring of the atmospheric pressure value, QFE or QNH, which is entered by the pilot and to automatically generate an alert when the entered value appears to be erroneous. Description of the invention
[0005] A method for monitoring the consistency of an atmospheric pressure value intended for use in configuring aircraft flight instruments is proposed herein, the method being executed by a monitoring system in the form of an electronic circuit, the method comprising the following steps: querying a database providing reference information on a set of airports and obtaining in return an altitude value for a selected airport; obtaining a static pressure value, a static temperature value, and a geometric altitude value for the aircraft, these values corresponding to a current situation of the aircraft;To estimate a static pressure value at the selected airport, based on the aircraft's current static pressure, static temperature, and geometric altitude, as well as the altitude of the selected airport obtained by querying the database; to assess the level of consistency between this estimate of the static pressure value at the selected airport and the atmospheric pressure value intended for use in configuring the aircraft's flight instruments; and to generate an alert if this level of consistency falls below a predefined threshold.
[0006] Thus, the atmospheric pressure value, typically of type QFE or QNH, intended to be used to configure the aircraft's flight instruments (e.g., entered by the pilot) is monitored, and an alert is automatically generated when this value appears to be erroneous.
[0007]
[0008] According to a particular embodiment, the estimation of the static pressure value at the selected airport Pextim is such that: , _ p H Zaic-zà) vk t ) estim- A / C-STAT [ TA / CJiTAJ+( (Z^
[0009] where: Ta / c-srazest is the static temperature value corresponding to the current situation of the aircraft, Z Aie is the geometric altitude value of the aircraft corresponding to the current situation of the aircraft, Pa / C_stat is the static pressure value corresponding to the current situation of the aircraft, ZA is the altitude of the selected airport which was obtained by querying the database, KT is a temperature gradient coefficient, g is the gravitational acceleration and R is the specific constant of dry air.
[0010] According to a particular embodiment, to perform the estimation of the static pressure value at the selected airport, the method comprises:
[0011] - obtain a Testim estimate of the static temperature at the selected airport, in applying the following formula:
[0012] Testim = TAic~57Ur + ((Z^-Z^Kr)
[0013] - obtain the Pestim estimate of the static pressure at the selected airport, in ap applying the following formula or an approximation thereof:
[0014] > -P ^ / ((¾¾)^) estim — ' A / C STAT l T -' — yx emim
[0015] According to a particular embodiment, to evaluate said level of consistency, the process comprises the following steps:
[0016] - calculate a QNH estimate of atmospheric pressure of type QNH, from of the estimated static pressure at the selected airport and the ZA altitude value of the selected airport which was obtained by querying the database:
[0017] = -ZA)
[0018] where H St / Pestin^ represents the standard barometric altitude function as a function of the estimated static pressure at the selected airport Pextim, and H represents the inverse function of Hstd;
[0019] - calculate a difference QNH atmospheric pressure value between the QNH estimate and the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's QNH flight instruments;
[0020] QNHaff= \QNH^-QNH^
[0021] - compare the difference QNH with a predefined threshold THqNh, and if the If the difference QNHDi^ is greater than the predefined threshold THqNH, then the alert is generated by the monitoring system.
[0022] According to a first alternative for evaluating said level of consistency, the process comprises the following steps:
[0023] - calculate a first altitude difference Zdel[a between a value Zcalc of a standard barometric altitude function which is obtained from the estimated static pressure at the selected airport Pextim, and the ZA altitude value of the selected airport which was obtained by querying the database: l«»*l zMla = - ZA = H «AP^ ) - ZA
[0025] where H St / Pestin^ represents the standard barometric altitude function as a function of the estimated static pressure of the selected airport;
[0026] - calculate a second altitude difference ^Diff between the first difference altitude ZdeUa and an altitude value deduced from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's QNH flight instruments;
[0027] zDiff= |
[0028] - compare the second altitude difference with a predefined threshold THstd^ and if the second altitude difference is greater than the predefined threshold THSTEh then the alert is generated by the monitoring system.
[0029] According to a second alternative for evaluating said level of consistency, the process comprises the following steps:
[0030] - calculate a Zestim barometric altitude estimate of the selected airport at starting from the estimated static pressure at the selected airport Pestim, and an altitude value deduced from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's onboard instruments QNHfN; [«»11 Z^. = ) - Hm (QNHIN)
[0032] where Hm represents the standard function of barometric altitude as a function of static pressure;
[0033] - calculate a difference Z'^ff between the barometric altitude estimate Zestim and of a barometric altitude value deduced from the ZA altitude value of the selected airport which was obtained by querying the database:
[0034] Z'Diff=\Zestim-ZA\
[0035] - compare the altitude difference Z'jjiff with a predefined threshold THALr and if the If the altitude difference Z'^ff is greater than the predefined threshold TH ALT, then the alert is generated by the monitoring system.
[0036] According to a third alternative for evaluating said level of consistency, the process comprises the following steps:
[0037] - calculate a static pressure value P'stat at the selected airport from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's QNH flight instruments and the ZA altitude value of the selected airport which was obtained by querying the database:
[0038] P'stat = Hm\Hm(QNHin) + Za)
[0039] where Hstd represents the standard function of barometric altitude as a function of static pressure, and H represents the inverse function of HAd;
[0040] - calculate a static pressure difference P$Diff from the pressure value static pressure P'stat thus calculated and static pressure Pestim estimated at the selected airport:
[0041] PsDiff=\P STAT "Pestim |
[0042] - compare the difference PSi)iff of static pressure with a predefined threshold THp^ and If the static pressure difference (Pspyiff) is greater than the predefined threshold (TH), then the alert is generated by the monitoring system.
[0043] According to a fourth alternative for evaluating said level of consistency, the process It involves the following steps:
[0044] - calculate a difference between the atmospheric pressure value, of type QFE, intended for use in configuring the aircraft's QFE onboard instruments and the estimated static pressure (Pestim) at the selected airport:
[0045] PsDlff=\QFElK-P„,„\
[0046] - compare the static pressure difference Ps^ff with a predefined threshold THp^ and if the static pressure difference Ps^ff is greater than the predefined threshold THp^ then the alert is generated by the monitoring system.
[0047] According to a particular embodiment, the atmospheric pressure value intended to be used to configure the aircraft's onboard instruments is entered by the aircraft pilot in a Human-Machine Interface of the aircraft's onboard instruments.
[0048] Also proposed here is a monitoring system configured to perform consistency monitoring of an atmospheric pressure value intended to be used to configure aircraft flight instruments, the monitoring system comprising electronic circuitry configured to: query a database providing reference information on a set of airports and obtain in return an altitude value of a selected airport; obtain a static pressure value, a static temperature value, and a geometric altitude value of the aircraft, these values corresponding to a current situation of the aircraft;To estimate a static pressure value at the selected airport, based on the aircraft's current static pressure, static temperature, and geometric altitude, as well as the altitude of the selected airport obtained by querying the database; to assess the level of consistency between this estimate of the static pressure value at the selected airport and the atmospheric pressure value intended for use in configuring the aircraft's flight instruments; and to generate an alert if this level of consistency falls below a predefined threshold.
[0049] An aircraft incorporating the above surveillance system is also proposed here. Brief description of the drawings
[0050] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of at least one exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
[0051] [Fig-1] schematically illustrates a consistency monitoring algorithm for a atmospheric pressure value, QFE or QNH, intended to be used for configure aircraft onboard instruments;
[0052] [Fig.2] schematically illustrates a context of use of a monitoring system comprising electronic circuitry configured to perform the process of [Fig.1]; and
[0053] [Fig.3] schematically illustrates a hardware platform suitable for implementing the monitoring system.
[0054] DETAILED DESCRIPTION OF EMBODIMENT METHODS
[0055] It is proposed here, and detailed in different embodiments below, to perform a static pressure estimation at a selected airport, which may be a departure airport or a destination airport, for an aircraft, based on:
[0056] - a static pressure value, a static temperature value, and a value geometric altitude, for example a GPS altitude (acronym for the English "Global Positioning System", meaning Global Positioning System or Satellite Geopositioning), which are provided by onboard instruments of an aircraft;
[0057] -an altitude of the selected airport, as obtained from a database providing reference information on a set of airports.
[0058] In the remainder of the description, the selected airport will be considered as a destination airport, but the same steps apply to a departure airport.
[0059] By way of non-limitation, the geometric altitude can be obtained from a radiometric altitude RA (acronym for the English "Radio Altitude") with a field database, or from an IRS-GPS hybridization (where 1RS is an acronym for the English "Inertial Reference System" meaning "inertial reference system").
[0060] Next, it is proposed to evaluate whether information representing an atmospheric pressure value, QFE or QNH, which is intended to be used to configure aircraft instruments (typically, entered by the aircraft pilot in an aircraft instrument human-machine interface), is consistent with the static pressure estimate performed. If a sufficient level of consistency (threshold) is not reached, then an alert is generated.
[0061] Fig. 1 thus schematically illustrates an algorithm for monitoring the consistency of an atmospheric pressure value, QFE or QNH, intended to be used to configure onboard instruments of an aircraft.
[0062] The algorithm schematically illustrated in [Fig. 1] is implemented by a system, called a monitoring system, in the form of electronic circuitry, embodiments of which are presented below in relation to [Fig. 3]. This monitoring system is preferably integrated into the aircraft's avionics, and is, for example, part of an FWS (Flight Warning System).
[0063] In step 101, the monitoring system obtains a selection of an airport from destination. For example, an aircraft instrument human-machine interface (HMI) displays a list of several candidate destination airports, and the pilot selects one from this list. In another example, the pilot enters an airport name into an aircraft instrument HMI. Yet another example involves aircraft avionics equipment that automatically determines a destination airport (e.g., a diversion airport).
[0064] Next, after selecting the destination airport, the monitoring system queries a database providing reference information on a set of airports (airport name, geographical coordinates, altitude above sea level, etc.). The system then obtains in return an altitude value for the destination airport, as previously stored for reference in the database in question.
[0065] In step 102, the monitoring system obtains a static pressure value, a static temperature value, and a geometric altitude value of the aircraft. These values correspond to the aircraft's current situation and are provided by the aircraft's onboard instruments.
[0066] In a step 103, the monitoring system obtains an atmospheric pressure value at the destination airport, QFE or QNH, which is intended to be used to configure aircraft flight equipment.
[0067] In a particular embodiment, as schematically illustrated in [Fig.2], the atmospheric pressure value is received by air-to-ground communication 220 from a control center at the destination airport 210 to the aircraft 200. The value thus received is entered by the pilot of the aircraft 200 into a Human-Machine Interface of the aircraft's instruments. The aircraft 200 includes the monitoring system, which then monitors the value thus entered by the pilot.
[0068] Thus, in a step 104, the monitoring system performs an estimation of a static pressure value at the destination airport selected in step 101. The estimation is performed from the static pressure value, the static temperature value, and the geometric altitude value of the aircraft, which were obtained in step 102, as well as from the altitude of the destination airport which was obtained by querying the database in step 101.
[0069] More specifically, in a particular embodiment, the monitoring system first obtains a TeSfim estimate of the static temperature at the destination airport, by applying the following formula:
[0070] Testim = Ta!cstat + ((ZAIC - ZA) *KT)
[0071] where:
[0072] - Ta / cjta^I the static temperature value that was obtained in step 102;
[0073]
[0074]
[0075]
[0076]
[0077]
[0078]
[0079]
[0080]
[0081]
[0082]
[0083]
[0084]
[0085]
[0086]
[0087] - ^a / c is the geometric altitude value of the aircraft that was obtained in step 102; - ZA is the altitude of the destination airport which was obtained in step 101; - Kt is a temperature gradient coefficient, which is either the temperature gradient of the standard atmosphere, or comes from a database storing temperature gradient information from meteorological statistics by geographical areas, the KT coefficient then being selected from this database according to the date on which the calculation is carried out and the geographical position of the destination airport. For a departure airport, it is considered that ZA[C is equal to ZA, and therefore that the difference (Za / c - Z^ is zero, and therefore that Testim is equal to T^cst^. The system then obtains the Pesiim estimate of the static pressure at the destination airport, by applying the following formula or an approximation thereof: restim ~ .AlC STAT I r~ *■ 1 I or, equivalently, g P -P *( ttZAlcZA)*KT] \ *A / C_STAT [ta / cs1at+((Zak-Za)*Kt) + 1 / where: - Pa / c_stat is the static pressure value obtained in step 102; and - g represents the gravitational acceleration and R represents the specific constant of dry air. For a departure airport, it is considered that ZA / c is equal to ZA, and therefore that Pestim is equal to P^_STAT- An approximation can be obtained by limited expansions, or by polynomial regressions, or by linear interpolations. In a step 105, the monitoring system evaluates a level of consistency between the values of steps 103 and 104. Thus, in a particular embodiment, the monitoring system evaluates the level of consistency between the estimated value (step 104) and the value (QNH or QFE) entered by the pilot (step 103). In step 106, the monitoring system checks whether the consistency level evaluated in step 105 is greater than or equal to a predefined threshold. If so, step 108 is performed, in which the algorithm of [Fig. 1] is terminated. The atmospheric pressure value obtained in step 103 (typically entered by the aircraft pilot) can then be used to configure the aircraft's flight instruments. Otherwise (consistency level below the predefined threshold), before performing step 108, step 107 is performed, in which an alert (e.g., visual and / or audible in the aircraft cockpit) is generated. It is up to the pilot to perform the checks. appropriate usage instructions, before confirming or refuting the atmospheric pressure value to be used to configure the aircraft's onboard instruments.
[0088] Different embodiments of steps 105 and 106 are presented below.
[0089] In a first embodiment, the system calculates an atmospheric pressure estimate QNHe^.m of type QNH, from the static pressure estimated at the destination airport Pestim and the altitude value ZA of the destination airport obtained in step 101:
[0090] = (P.^-ZA)
[0091] where Hstd represents the standard barometric altitude function as a function of the static pressure (standard atmosphere), and represents the inverse function of Hsid-
[0092] The system then calculates a difference QNHp.fj.de atmospheric pressure value QNH between the estimate QNHestim and an atmospheric pressure value QNHjn (of type QNH) obtained in step 103:
[0093] QNHnff = \QNH -QNH \
[0094] or [°09S] QNHKf / = -ZA)-QNHix\
[0096] In this first embodiment, this difference QNHD.ff in atmospheric pressure value defines the level of consistency between the values in steps 103 (QNH) and 104 (Pestim). The higher the difference QNHn.ff, the lower the consistency level. The monitoring system then compares the QNH difference with a first predefined threshold THqnh, and if the difference QNHp.jj is greater than the first predefined threshold THqnh (insufficient consistency level), then an alert is generated.
[0097] In a second embodiment, the monitoring system calculates a first altitude difference Z delta between a ZCalc value of a standard barometric altitude function which is obtained from the estimated static pressure at the destination airport Pestim, and the ZA altitude value of the destination airport which was obtained in step 101:
[0098] Zdd-ZA
[0099] The monitoring system then calculates a second altitude difference ^Diff between the first altitude difference Z delta and an altitude value deduced, using the aforementioned Hstd function, from an atmospheric pressure value QNHjn (of type QNH) obtained in step 103: 101001 Z;w= \Zmu-Hm(QNH,n) I
[0101] In this second embodiment, this second altitude difference Zpyy defines the level of consistency between the values of steps 103 (QNH) and 104 (Pestim). The higher this second altitude difference Z^ff is, the lower the consistency level. The monitoring system then compares the second altitude difference Z^ff with a second predefined threshold THstd, and if the second altitude difference Z Diff is greater than the second predefined threshold THstd (insufficient consistency level), then an alert is generated.
[0102] In a third embodiment, the monitoring system calculates an estimate of the barometric altitude Zestim of the destination airport from the estimated static pressure at the destination airport Pestim, and an altitude value deduced from an atmospheric pressure value QNHjn (of type QNH) obtained in step 103: [01031 Z^
[0104] The monitoring system calculates a difference Z'^ff between the barometric altitude estimate Zestim and the barometric altitude deduced from the ZA altitude value of the destination airport obtained in step 101:
[0105] Z'Diff^\Zestim-ZA\
[0106] In this third embodiment, this altitude difference Z'pyy defines the level of consistency between the values of steps 103 (QNHjn) and 104 (PesUm). The higher this altitude difference Z'pyy, the lower the consistency level. The monitoring system then compares the altitude difference Z'piff with a third predefined threshold TH^-^ and if the altitude difference Z'Diff is greater than the third predefined threshold (insufficient consistency level), then an alert is generated.
[0107] In a fourth embodiment, the system calculates a static pressure value P'stat at the destination airport from an atmospheric pressure value QNH obtained in step 103 and the altitude value ZA of the destination airport obtained in step 101:
[0108] )+Zj * STAT **std ** jn y ~ /
[0109] The system calculates a static pressure difference PSDiff from the static pressure value P'stat thus obtained and the static pressure Pestim estimated at the destination airport:
[0110] P SDiff = | P'STAT "Pestim I
[0111] In this fourth embodiment, this difference Ps^ff of static pressure This defines the level of consistency between the values in steps 103 (QNH) and 104 (Pestim). The higher this static pressure difference (Ps^ff), the lower the consistency level. The monitoring system then compares the static pressure difference (Ps^ff) with a fourth predefined threshold (THP^), and if the static pressure difference (Ps^ff) exceeds this threshold (THPs) (insufficient consistency level), an alert is generated.
[0112] In a fifth embodiment, a static pressure value QFEJN (of type QFE) is obtained in step 103 (typically entered by the aircraft pilot). The monitoring system then calculates the difference between the entered static pressure value QFE and the estimated static pressure Pestim at the destination airport. [0H3] PsDiff=\QFEJN "Festim 1
[0114] In this fifth embodiment, this static pressure difference PSjjiff defines the level of consistency between the values in steps 103 (QFEIN) and 104 (Pestim). The higher this static pressure difference Ps^ff, the lower the consistency level. The monitoring system then compares the static pressure difference PSjjiff with the fourth predefined threshold THPs already mentioned, and if the static pressure difference PSfuff is greater than the fourth predefined threshold THPs (insufficient consistency level), then an alert is generated.
[0115] The aforementioned THqnHi, THSTd, THalt and THPs thresholds are determined upstream so as to represent an acceptable margin of potential error regarding the atmospheric pressure value, QFE or QNH, used to configure the aircraft's flight instruments.
[0116] Fig. 3 schematically illustrates a SYS 300 hardware platform adapted to implement the monitoring system and execute the algorithm process of Fig. 1.
[0117] The SYS 300 hardware platform then comprises, connected by a communication bus 310: a processor or CPU (Central Processing Unit) 301; a RAM (Random Access Memory) 302; a read-only memory 303, for example of ROM (Read Only Memory) or EEPROM (Electrically-Erasable Programmable ROM) or Flash type; a storage unit, such as a HDD (Hard Disk Drive) 304, or a storage media reader, such as an SD (Secure Digital) card reader; and an I / F interface manager 305.
[0118] The I / F interface manager 305 allows the SYS 300 hardware platform to interact with peripherals, such as Human-Interface devices machine (input, display, broadcasting of warning signals...), and aircraft onboard instruments.
[0119] The processor 301 is capable of executing instructions loaded into RAM 302 from ROM 303, external memory, a storage medium (such as an SD card), or a communication network. When the SYS 300 hardware platform is powered on, the processor 301 is capable of reading instructions from RAM 302 and executing them. These instructions form a computer program causing the processor 301 to implement all or part of the steps and processes described herein.
[0120] All or part of the steps and processes described herein can thus be implemented in software form by the execution of a set of instructions by a programmable machine, for example a DSP (Digital Signal Processor) or a microcontroller, or be implemented in hardware form by a dedicated machine or electronic component (chip) or a dedicated set of electronic components (chipset). Generally speaking, the monitoring system thus comprises electronic circuitry adapted and configured to implement the steps and processes described herein.
Claims
Demands
1. A method for monitoring the consistency of an atmospheric pressure value intended to be used to configure flight instruments of an aircraft (200), the method being carried out by a monitoring system in the form of electronic circuitry, the method comprising the following steps: - querying (101) a database providing reference information on a set of airports and obtaining in return an altitude value of a selected airport (210); - obtaining (102) a static pressure value, a static temperature value, and a geometric altitude value of the aircraft (200), these values corresponding to a current situation of the aircraft (200);- perform (104) an estimate of a static pressure value at the selected airport (210), based on the static pressure value, static temperature value, and geometric altitude value of the aircraft (200), which correspond to the current situation of the aircraft (200), as well as the altitude of the selected airport (210) which was obtained by querying the database; - evaluate (105) a level of consistency between said estimate of the static pressure value at the selected airport (210) and the atmospheric pressure value intended to be used to configure the aircraft's (200) flight instruments; and - generate (107) an alert if said level of consistency is less than a predefined threshold.
2. The method according to claim 1, wherein the estimation of the static pressure value at the selected airport Peaim is such that: 1 A / C_STA1 T^c stat+{ (Zw-Za where: Ta / ^sta^I is the static temperature value corresponding to the aircraft's current situation (200), ^a / c is the geometric altitude value of the aircraft (200) corresponding to the aircraft's current situation, Pa / C_stat is the static pressure value corresponding to the aircraft's current situation (200), ZA is the altitude of the selected airport (210) which was obtained by querying the database, KT is a temperature gradient coefficient, g is the gravitational acceleration and R is the specific air constant dry.
3. The method according to claim 2, wherein, to perform the estimation of the static pressure value at the selected airport (210), the method comprises: - obtaining an estimate Testim of the static temperature at the selected airport (210), by applying the following formula: Testim “ TAjc STAT + ( (^A / C'^a) ^t) - obtaining the estimate Pestim of the static pressure at the selected airport (210), by applying the following formula or an approximation thereof: p — p za / c~za ) i \Kr R ^estim * AfC STAT 1 y ' 1
4. The method according to any one of claims 1 to 3, wherein, to evaluate said level of consistency, the method comprises the following steps: - calculating a QNH atmospheric pressure estimate of type QNH, from the estimated static pressure at the selected airport (210) and the ZA altitude value of the selected airport (210): -za) where Hst^Pestim) represents the standard function of barometric altitude as a function of the estimated static pressure at the selected airport, and H^ represents the inverse function of Hstd; - calculating a QNH^yj-de atmospheric pressure difference between the QNH^ estimate and the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's QNH onboard instruments; QNH™ ff = I QNH . - QNH^ | - comparing the QNH^.^ difference with a predefined threshold TH on H, and if the QNH^ difference.^ is greater than the predefined threshold THqnh, then the alert is generated by the monitoring system.
5. The method according to any one of claims 1 to 3, wherein, to evaluate said level of consistency, the method comprises the following steps: - calculating a first altitude difference ^deita between a value Zcaic of a standard barometric altitude function obtained from the estimated static pressure at the selected airport Pestim, and the ZA altitude value of the selected airport (210) obtained by querying the database: Z delta ~ ^calc " A ~ std ( ^estim ) " ^A where Hdd(Pestim) represents the standard function of barometric altitude as a function of the estimated static pressure at the selected airport; - calculate a second altitude difference Züiff between the first altitude difference Z delta and an altitude value deduced from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's QNH^ flight instruments; 2lW=\Zdd,.,-Had[QNHIN}\ - compare the second altitude difference Z^f with a predefined threshold THstd, and if the second altitude difference Zj^ff is greater than the predefined threshold then the alert is generated by the surveillance system.
6. A method according to any one of claims 1 to 3, wherein, to evaluate said level of consistency, the method comprises the following steps: - calculate a Zesam barometric altitude estimate of the selected airport (210) from the estimated static pressure at the selected airport Pestim, and an altitude value deduced from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's onboard instruments QNHjn; Z^estim H std ( ^estim ) " std ( QN H) where Hstd represents the standard function of barometric altitude as a function of static pressure; - calculate a difference Z^yy between the barometric altitude estimate Zesdm and a barometric altitude value deduced from the ZA altitude value of the selected airport (210): Z Diff | Zesdm - ZA | - compare the altitude difference Z'Diff with a predefined threshold TH and if the altitude difference Z'Diff is greater than the predefined threshold then the alert is generated by the system on vigilance.
7. The method according to any one of claims 1 to 3, in which, to evaluate said level of consistency, the process includes the following steps: - calculate a static pressure value P'stat at the selected airport (210) from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's QNH flight instruments and the altitude value ZA of the selected airport (210): P'stat = ) + ZA ) where Hstd represents the standard function of barometric altitude as a function of static pressure, and Hddl represents the inverse function of Hstd;- calculate a static pressure difference Ps^f from the static pressure value P'stat thus calculated and the static pressure Pestim estimated at the selected airport (210): P^Diff — IP 'STAT " Pestim 1 - compare the static pressure difference Ps^ f with a predefined threshold PHp^ and if the static pressure difference Ps^ff is greater than the predefined threshold THPs, then the alert is generated by the monitoring system.;
8. The method according to any one of claims 1 to 3, wherein, to evaluate said level of consistency, the method comprises the following steps: - calculate a difference between the atmospheric pressure value, of type QFE, intended to be used to configure the aircraft's on-board instruments QFEJN and the static pressure P is estimated at the selected airport (210): PSDiff = | QFE1N " Pestim 1 - compare the static pressure difference Ps^ff with a predefined threshold THps, and if the static pressure difference Ps^ff is greater than the predefined threshold THps, then the alert is generated by the monitoring system.
9. The method according to any one of claims 1 to 8, wherein the atmospheric pressure value intended to be used to configure the aircraft's flight instruments (200) is entered by the pilot of the aircraft (200) in a Human-Machine Interface of the aircraft's flight instruments (200).
10. A monitoring system configured to perform consistency monitoring of an atmospheric pressure value intended for use in configuring aircraft flight instruments (200), the monitoring system comprising electronic circuitry configured to: - query (101) a database providing reference information on a set of airports and obtain in return an altitude value of a selected airport (210); - obtain (102) a static pressure value, a static temperature value, and a geometric altitude value of the aircraft (200), these values corresponding to a current situation of the aircraft (200);- perform (104) an estimate of a static pressure value at the selected airport (210), based on the static pressure value, static temperature value, and geometric altitude value of the aircraft (200), which correspond to the current situation of the aircraft (200), as well as the altitude of the selected airport (210) which was obtained by querying the database; - evaluate (105) a level of consistency between said estimate of the static pressure value at the selected airport (210) and the atmospheric pressure value intended to be used to configure the aircraft's (200) flight instruments; and - generate (107) an alert if said level of consistency is less than a predefined threshold.
11. An aircraft (200) comprising the surveillance system according to claim 10.