METHOD FOR MONITORING THE CONSISTENCY OF AN ATMOSPHERIC PRESSURE VALUE USED TO CONFIGURE ON-BOARD INSTRUMENTS OF AN AIRCRAFT

Abstract

A method for monitoring the consistency of an atmospheric pressure value intended to be used to configure on-board instruments of an aircraft comprises: querying (101) a database to obtain an altitude value of a selected airport; obtaining (102) a static pressure value, a static temperature value, and a geometric altitude value, which correspond to a current situation of the aircraft; deducing therefrom an estimate (104) of a static pressure value at the selected airport; evaluating (105) a level of consistency between said estimate and the atmospheric pressure value intended to be used to configure the on-board instruments of the aircraft; and generating (107) an alert if said level of consistency is lower than a predefined threshold. Figure to be published with the abstract: Fig. 1

Description

Title of the invention: METHOD FOR MONITORING THE COHERENCE OF AN ATMOSPHERIC PRESSURE VALUE USED TO CONFIGURE ON-BOARD INSTRUMENTS OF AN AIRCRAFT Technical field

[0001] The present invention relates to a coherence monitoring of an atmospheric pressure value, QFE or QNH (typically, entered by the pilot of the aircraft in a human-machine interface of on-board instruments of the aircraft), intended to be used to configure on-board instruments of an aircraft. 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 "transition altitude") in climb, and called "transition flight level" in 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 destination airfield / airport (the atmospheric pressure reference is then designated by the international code “QFE”), or to the atmospheric pressure measured at 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 the transition flight level, the value of the atmospheric pressure QNH or QFE has a major importance because it directly influences the vertical position of the aircraft, therefore its trajectory in maintaining level flight, climb or descent and approach. An atmospheric pressure value, QFE or QNH, is entered by the pilot via a human-machine interface of the aircraft's on-board instruments, for example of the EFISCP type ("Electronic Flight Instrument System Control Panel" in English) just before crossing the transition altitude or the transition flight level.

[0004] It is then desirable to provide a solution which makes it possible to monitor 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. Statement of the invention

[0005] A method for monitoring the consistency of an atmospheric pressure value intended to be used to configure on-board instruments of an aircraft is proposed herein, the method being executed by a monitoring system in the form of electronic circuitry, the method comprising the following steps: querying a database providing reference information on a set of airports and obtaining in return an altitude value of a selected airport; obtaining 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;performing an estimation of a static pressure value at the selected airport, from the static pressure value, the static temperature value, and the geometric altitude value of the aircraft, which correspond to the current situation of the aircraft, as well as from the altitude of the selected airport which was obtained by querying the database; evaluating a level of consistency between said estimation of the static pressure value at the selected airport and the atmospheric pressure value intended to be used to configure the on-board instruments of the aircraft; and generating an alert if said level of consistency is below a predefined threshold.

[0006] Thus, the atmospheric pressure value, typically of the QFE or QNH type, intended to be used to configure the aircraft's on-board instruments (eg, 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-sraz 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 estimate the static pressure value at the selected airport, the method comprises:

[0011] - obtain an estimate Testim 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 by 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 method 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 altitude ZA value of the selected airport which was obtained by querying the database:

[0017] = -ZA)

[0018] where H St / Pestin^ represents the standard function of barometric altitude 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 atmospheric pressure value, of type QNH, intended to be used to configure the aircraft instruments QNH;

[0020] QNHaff= \QNH^-QNH^

[0021] - compare the difference QNH with a predefined threshold THqNh, and 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 method comprises the following steps:

[0023] - calculate a first altitude difference Zdel[a between a Zcalc value of a standard barometric altitude function which is obtained from the estimated static pressure at the selected airport Pextim, and the altitude value ZA 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 function of barometric altitude 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 derived from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's on-board instruments QNH;

[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 method comprises the following steps:

[0030] - calculate a barometric altitude estimate Zestim of the selected airport at from the estimated static pressure at the selected airport Pestim, and from an altitude value deduced from the atmospheric pressure value, of type QNH, intended to be used to configure the aircraft's on-board 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 estimate of the barometric altitude Zestim and from 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 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 method 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 instruments QNH and the altitude value ZA 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 P'stat thus calculated and the 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 Pspyiff ​​static pressure difference 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 method involves the following steps:

[0044] - calculate a difference between the atmospheric pressure value, of type QFE, intended to be used to configure the aircraft instruments QFE 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 on-board instruments of the aircraft is entered by the pilot of the aircraft in a human-machine interface of the on-board instruments of the aircraft.

[0048] Also provided herein is a monitoring system configured to perform consistency monitoring of an atmospheric pressure value intended to be used to configure onboard instruments of an aircraft, 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;performing an estimation of a static pressure value at the selected airport, from the static pressure value, the static temperature value, and the geometric altitude value of the aircraft, which correspond to the current situation of the aircraft, as well as from the altitude of the selected airport which was obtained by querying the database; evaluating a level of consistency between said estimation of the static pressure value at the selected airport and the atmospheric pressure value intended to be used to configure the on-board instruments of the aircraft; and generating an alert if said level of consistency is below a predefined threshold.

[0049] Also provided herein is an aircraft comprising the above surveillance system. Brief description of the drawings

[0050] The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of at least one exemplary embodiment, said description being made in relation to the attached drawings, among which:

[0051] [Fig-1] schematically illustrates a consistency monitoring algorithm of a atmospheric pressure value, QFE or QNH, intended to be used for configure aircraft instruments;

[0052] [Fig.2] schematically illustrates a context of use of a monitoring system comprising electronic circuitry configured to execute the method of [Fig.l]; and

[0053] [Fig.3] schematically illustrates a hardware platform suitable for implementing the monitoring system.

[0054] DETAILED DESCRIPTION OF EMBODIMENTS

[0055] It is proposed here, and detailed in different embodiments below, to carry out an estimation of static pressure at a selected airport, which may be a departure airport or a destination airport, for an aircraft, from:

[0056] - a static pressure value, a static temperature value, and a value geometric altitude, for example a GPS altitude (acronym for Global Positioning System), which are provided by instruments on board 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 to be a destination airport, but the same steps apply to a departure airport.

[0059] In a non-limiting manner, the geometric altitude can be obtained from a radiometric altitude RA (acronym for “Radio Altitude”) with terrain database, or from an IRS-GPS hybridization (where 1RS is an acronym for “Inertial Reference System”).

[0060] Next, it is proposed to evaluate whether information representative of an atmospheric pressure value, QFE or QNH, which is intended to be used to configure on-board instruments of the aircraft (typically, entered by the pilot of the aircraft in a human-machine interface of the on-board instruments of the aircraft) is consistent with the static pressure estimation carried out. If a sufficient level of consistency (threshold) is not reached, then an alert is generated.

[0061] [Fig.l] thus schematically illustrates an algorithm for monitoring the consistency of an atmospheric pressure value, QFE or QNH, intended to be used to configure on-board instruments of an aircraft.

[0062] The algorithm schematically illustrated in [Fig.l] 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 avionics of the aircraft, and is for example part of a FWS type system (“Flight Warning System” in English).

[0063] In a step 101, the surveillance system obtains a selection of an airport from destination. For example, a human-machine interface on the aircraft's flight instruments displays a list of several candidate destination airports, and the pilot selects a destination airport from this list. In another example, the pilot enters an airport name into a human-machine interface on the aircraft's flight instruments. In yet another example, aircraft avionics equipment automatically determines a destination airport (e.g., an alternate airport).

[0064] Then, from the selection of the destination airport, the monitoring system queries a database providing reference information on a set of airports (the name of the airport, its geographical coordinates, its altitude above sea level, etc.). The system then obtains in return an altitude value of the destination airport, as previously stored for reference in the database in question.

[0065] In a 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 current situation of the aircraft and are provided by on-board instruments of an aircraft.

[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 flight equipment of the aircraft.

[0067] In a particular embodiment, as schematically illustrated in [Fig.2], the atmospheric pressure value is received by air-ground communication 220 from a control center of the destination airport 210 to the aircraft 200. The value thus received is entered by the pilot of the aircraft 200 in a human-machine interface of the on-board instruments of the aircraft 200. 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 makes an estimate of a static pressure value at the destination airport selected in step 101. The estimate is made 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 an estimate TeSfim 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 which 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 which 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 area, 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 therefore, equivalently, g P -P *( ttZAlcZA)*KT] \ *A / C_STAT [ta / cs1at+((Zak-Za)*Kt) + 1 / where: - Pa / c_stat is the static pressure value that was 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 developments, 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 a step 106, the monitoring system checks whether the consistency level evaluated in step 105 is greater than or equal to a predefined threshold. If this is the case, a step 108 is performed, in which the algorithm of [Fig.l] is terminated. The atmospheric pressure value obtained in step 103 (typically entered by the pilot of the aircraft) can then be used to configure the on-board instruments of the aircraft. Otherwise (consistency level lower than the predefined threshold), before performing step 108, a step 107 is performed, in which an alert (for example, visual and / or audible in the cockpit of the aircraft) is generated. It is up to the pilot to perform the checks regulations accordingly, before confirming or denying the atmospheric pressure value to be used to configure the aircraft's on-board instruments.

[0088] Different embodiments of steps 105 and 106 are presented below.

[0089] In a first embodiment, the system calculates an estimate QNHe^.m of atmospheric pressure of type QNH, from the estimated static pressure 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 function of barometric altitude 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. of 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] either [°09S] QNHKf / = -ZA)-QNHix\

[0096] In this first embodiment, this difference QNHD.ff of atmospheric pressure value defines the level of coherence between the values ​​of steps 103 (QNH) and 104 (Pestim) - The higher the difference QNHn.ff, the lower said level of coherence. The monitoring system then compares the difference QNH with a first predefined threshold THqnh, and if the difference QNHp.jj. is greater than the first predefined threshold THqnh (insufficient level of coherence), then an alert is generated.

[0097] In a second embodiment, the monitoring system calculates a first altitude difference Z delta between a value ZCalc of a standard barometric altitude function which is obtained from the estimated static pressure at the destination airport Pestim, and the altitude value ZA 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 Hstd function already mentioned, 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 coherence between the values ​​of steps 103 (QNH) and 104 (Pestim). The higher this second altitude difference Z^ff, the lower said level of coherence. 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 level of coherence), 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 from 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 estimate of the barometric altitude Zestim and the barometric altitude deduced from the altitude value ZA 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 coherence between the values ​​of steps 103 (QNHjn) and 104 (PesUm) - The higher this altitude difference Z'pyy is, the lower said level of coherence is. 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 level of coherence), 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 defines the level of consistency between the values ​​of steps 103 (QNH ) and 104 (Pestim ). The higher this difference Ps^iff of static pressure, the lower the said level of consistency. The monitoring system then compares the difference Ps^ff of static pressure with a fourth predefined threshold THP^ and if the difference Ps^ff of static pressure is higher than the fourth predefined threshold THPs (insufficient level of consistency), then 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 pilot of the aircraft). The monitoring system then calculates a difference between the static pressure value QFE entered and the static pressure Pestim estimated 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 ​​of steps 103 (QFEIN) and 104 (Pestim). The higher this static pressure difference Ps^ff, the lower said level of consistency. 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 level of consistency), then an alert is generated.

[0115] The aforementioned thresholds THqnHi THSTd, THalt and THPs are determined upstream so as to represent an acceptable margin of potential error concerning the atmospheric pressure value, QFE or QNH, used to configure the aircraft's on-board instruments.

[0116] [Fig.3] schematically illustrates a SYS 300 hardware platform suitable for implementing the monitoring system, and executing the method of the algorithm of [Fig.l].

[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 the ROM (Read Only Memory) or EEPROM (Electrically Erasable Programmable ROM) type or of the Flash type; a storage unit, such as a hard disk 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 alert signals, etc.), and aircraft on-board instruments.

[0119] The processor 301 is capable of executing instructions loaded into the RAM 302 from the ROM 303, an external memory, a storage medium (such as an SD card), or a communications network. When the SYS hardware platform 300 is powered on, the processor 301 is capable of reading instructions from the RAM 302 and executing them. These instructions form a computer program causing the processor 301 to implement some or all of the steps and methods described herein.

[0120] All or part of the steps and methods described herein may thus be implemented in software form by executing a set of instructions by a programmable machine, for example a DSP (Digital Signal Processor) type processor or a microcontroller, or be implemented in hardware form by a machine or a dedicated electronic component (chip) or a set of dedicated electronic components (chipset). Generally speaking, the monitoring system thus comprises electronic circuitry adapted and configured to implement the steps and methods described herein.

Claims

Claims

1. A method for monitoring the consistency of an atmospheric pressure value for use in configuring on-board instruments of an aircraft (200), the method being performed 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);- performing (104) an estimation of a static pressure value at the selected airport (210), from the static pressure value, the static temperature value, and the geometric altitude value of the aircraft (200), which correspond to the current situation of the aircraft (200), as well as from the altitude of the selected airport (210) which was obtained by querying the database; - evaluating (105) a level of consistency between said estimation of the static pressure value at the selected airport (210) and the atmospheric pressure value intended to be used to configure the on-board instruments of the aircraft (200); and - generating (107) an alert if said level of consistency is lower 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 the static temperature value corresponding to the current situation of the aircraft (200), ^a / c is the geometric altitude value of the aircraft (200) corresponding to the current situation of the aircraft, Pa / C_stat is the static pressure value corresponding to the current situation of the aircraft (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 constant of air 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 estimation Testim of the static temperature at the selected airport (210), by applying the following formula: Testim “ TAjc STAT + ( (^A / C'^a) ^t) - obtaining the estimation 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 an estimate QNH of atmospheric pressure of type QNH, from the estimated static pressure at the selected airport (210) and the altitude value ZA 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 difference QNH^yj-of atmospheric pressure value between the estimate QNH^ and the atmospheric pressure value, of type QNH, intended to be used to configure the on-board instruments of the aircraft QNH; QNH™ ff = I QNH . - QNH^ | - comparing the difference QNH^.^ with a predefined threshold TH on H, and if the difference QNH^.^ 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 which is 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 on-board instruments QNH^; 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: - calculating a barometric altitude estimate Zesam 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 on-board instruments of the aircraft 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 estimate of the barometric altitude Zestim and a barometric altitude value deduced from the altitude value ZA of the selected airport (210): Z Diff | Zesdm - ZA | - compare the altitude difference Z'Diff with a predefined threshold THet if the altitude difference Z'Diff is greater than the predefined threshold then the alert is generated by the monitoring system surveillance.

7. The method according to any one of claims 1 to 3, in which, to evaluate said level of consistency, the method comprises the following steps: - calculating 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 on-board instruments of the aircraft QNH 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: - calculating a difference between the atmospheric pressure value, of type QFE, intended to be used to configure the on-board instruments of the aircraft QFEJN and the static pressure P is™ estimated at the selected airport (210): PSDiff = | QFE1N " Pestim 1 - comparing 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 of any one of claims 1 to 8, wherein the atmospheric pressure value to be used to configure the on-board instruments of the aircraft (200) is entered by the pilot of the aircraft (200) into a human-machine interface of the on-board instruments of the aircraft (200).

10. A monitoring system configured to perform consistency monitoring of an atmospheric pressure value for use in configuring onboard instruments of an aircraft (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);- performing (104) an estimation of a static pressure value at the selected airport (210), from the static pressure value, the static temperature value, and the geometric altitude value of the aircraft (200), which correspond to the current situation of the aircraft (200), as well as from the altitude of the selected airport (210) which was obtained by querying the database; - evaluating (105) a level of consistency between said estimation of the static pressure value at the selected airport (210) and the atmospheric pressure value intended to be used to configure the on-board instruments of the aircraft (200); and - generating (107) an alert if said level of consistency is lower than a predefined threshold.;

11. An aircraft (200) comprising the surveillance system of claim 10.

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