METHOD AND SYSTEM FOR MONITORING STATIC PRESSURE PROBE MEASUREMENTS ON AN AIRCRAFT

Abstract

To detect a measurement error in a pair of right-left static pressure sensors of an aircraft, a system in the form of electronic circuitry is configured to: obtain (102) right / left static pressure measurements from the pair of right-left static pressure sensors; calculate (104) a right-left static pressure differential from the measurements obtained; determine (106) a theoretical right-left static pressure differential using data from other aircraft equipment; perform (108) a comparison between the difference between the calculated right-left differential and the determined theoretical right-left differential with a predetermined threshold; and when the comparison shows that the difference between the calculated right-left differential and the determined theoretical right-left differential is greater than the predetermined threshold, generate (112) a static pressure measurement error alert.Thus, it is possible to precisely detect any errors in static pressure measurements. Figure to be published with the abbreviation: Fig. 1.

Description

Title of the invention: METHOD AND SYSTEM FOR MONITORING MEASUREMENTS FROM STATIC PRESSURE PROBES OF AN AIRCRAFT Technical field

[0001] The present invention relates to a method and a system for monitoring measurements of static pressure probes of an aircraft, more particularly to detect possible measurement errors of these static pressure probes. STATE OF PRIOR ART

[0002] On aircraft, static pressure is measured using a pair of probes installed symmetrically on either side of the fuselage of the aircraft in question. These are called right-left static pressure probes.

[0003] Some ADIRU (Air Data Inertial Reference Unit) type systems monitor in real time the right-left differential existing between the static pressure measurements taken. When this differential exceeds a predefined threshold, for example 30 millibars, the ADIRU type system in question considers that it is in the presence of static pressure measurement errors.

[0004] However, although this approach allows measurement errors to be correctly detected, it would be desirable to provide a solution which allows possible static pressure measurement errors to be detected even more precisely. Statement of the invention

[0005] Thus, a method is proposed here for detecting a measurement error in a pair of right-left static pressure probes of an aircraft, the method being implemented by a system in the form of electronic circuitry, the method comprising the following steps: obtaining right / left static pressure measurements from the pair of right-left static pressure probes which forms a first set of equipment of the aircraft; calculating a right-left static pressure differential APsi from the measurements obtained; determining a theoretical right-left static pressure differential APsitheo, from a second set of equipment of the aircraft which is distinct from the first set of equipment; performing a comparison between the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsitheo with a predetermined threshold;and when the comparison shows that the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsitheo is greater than the predetermined threshold, generate a static pressure measurement error alert. ;

[0006] Thus, it is possible to finely detect possible errors in static pressure measurements.

[0007] In a particular embodiment, determining the theoretical right-left static pressure differential APsitheo comprises applying a function F for estimating the theoretical right-left static pressure differential.

[0008] In a particular embodiment, the function F for estimating the theoretical right-left differential of static pressure is such that the theoretical right-left differential of static pressure APsitheo is calculated in the following way: [°009] APsitheo = -kp- ny +Pdyn--^-Ôr j

[0010] where:

[0011] - kp represents a coefficient such that AKp^ = -kp . , where ^Kp^ represents a dif differential of lateral sliding effect between the right and left of the aircraft fuselage;

[0012] - m represents the mass of the aircraft and * represents the gravitational acceleration;

[0013] - 5 represents the surface of a wing of the aircraft;

[0014] - Pdyn represents the dynamic pressure;

[0015] - Cy represents the gradient of the aerodynamic coefficient of lateral lift which is due to the deflection of the aircraft's rudder;

[0016] - Cy^ represents the gradient of the aerodynamic coefficient of lateral lift which is due to aircraft skidding;

[0017] - n> represents the lateral load factor; and

[0018] - ôr represents the rudder deflection angle.

[0019] In a particular embodiment, the function F for estimating the theoretical right-left differential of static pressure is such that the theoretical right-left differential of static pressure APsi1heo is calculated as follows:

[0020] . (Cz.si)4+CySr-5r)

[0021] where:

[0022] - kp represents a coefficient such that AKp^ = -kp . fi , where AKp^ represents a dif differential of lateral sliding effect between the right and left of the aircraft fuselage;

[0023] - Pciyn represents the dynamic pressure;

[0024] - Cy represents the gradient of the aerodynamic coefficient of lateral lift which is due to the deflection of the aircraft's rudder;

[0025] - Cz represents the vertical lift coefficient; and

[0026] - represents the angle of inclination of the aircraft.

[0027] In a particular embodiment, determining a theoretical right-left differential of APsitheo static pressure involves using a trained neural network taking as input the following data set:

[0028] - ny • m , where ny represents the lateral load factor and m represents the mass of the aircraft;

[0029] - the angle of attack a of the aircraft;

[0030] - the deflection angle of the rudder 5r of the aircraft;

[0031] - the engine speed differential zWl between an engine on the right of the fuselage and a engine on the left side of the aircraft fuselage; and

[0032] - the Mach number.

[0033] Also provided herein is a computer program product comprising instructions causing an implementation of the method according to any one of the embodiments presented above, when the instructions are executed by a processor. Also provided herein is an information storage medium on which are stored instructions causing an implementation of the method according to any one of the embodiments presented above, when the instructions are read from the information storage medium and executed by a processor.

[0034] Also proposed here is a system for monitoring measurements of the pair of right-left static pressure probes of an aircraft, said system being in the form of electronic circuitry configured to: obtain right / left static pressure measurements from the pair of right-left static pressure probes which forms a first set of equipment of the aircraft; calculate a right-left static pressure differential ^Psi from the measurements obtained; determine a theoretical right-left static pressure differential APsitheo, from a second set of equipment of the aircraft which is distinct from the first set of equipment; perform a comparison between the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsitheo with a predetermined threshold;and when the comparison shows that the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsitheo is greater than the predetermined threshold, generate a static pressure measurement error alert. ;

[0035] Also proposed here is an aircraft comprising at least one pair of right-left static pressure probes placed on either side of the fuselage, and at least one system for monitoring measurements of the pair of right-left static pressure probes as presented above. Brief description of the drawings

[0036] The above-mentioned and other features of the invention appear will become more clearly apparent from reading the following description of at least one exemplary embodiment, said description being made in relation to the attached drawings, among which:

[0037] [Fig.l] schematically illustrates an algorithm for monitoring measurements of static pressure probes;

[0038] [Fig.2] schematically illustrates a first particular embodiment of a system for monitoring measurements of static pressure probes;

[0039] [Fig.3] schematically illustrates a second particular embodiment of the system for monitoring static pressure probe measurements;

[0040] [Fig.4] schematically illustrates an example of a hardware arrangement suitable for implementing the algorithm of [Fig.l]; and

[0041] [Fig.5] schematically illustrates, in side view, an aircraft equipped with a static pressure probe measurement monitoring system.

[0042] DETAILED DESCRIPTION OF EMBODIMENTS

[0043] Subsequently, various embodiments of a system for monitoring measurements of static pressure probes of an aircraft are disclosed.

[0044] Such a static pressure probe measurement monitoring system is intended to be used to monitor measurements made by right and left static pressure probes of the aircraft. Such an aircraft 500 is schematically illustrated, in side view, in [Fig. 5].

[0045] Such a system for monitoring measurements of static pressure probes is preferably integrated into an ADIRU (“Air Data Inertial Reference Unit”) type system connected to such right and left static pressure probes of the aircraft 500, i.e. placed symmetrically to the right and left of the fuselage of the aircraft 500. The ADIRU type system is a system providing speed and altitude information, as well as inertial references.

[0046] Detailed static pressure probe measurement monitoring is typically supplemented by other static pressure probe measurement monitoring mechanisms.

[0047] [Fig.l] schematically illustrates an algorithm for monitoring static pressure probe measurements. The algorithm of [Fig.l] is implemented by the aforementioned static pressure probe measurement monitoring system.

[0048] In a step 102, the static pressure probe measurement monitoring system obtains left and right measurements from the static pressure probes. These measurements are thus obtained in real time from a first set of sensors formed by the static pressure probes on the left and right of the fuselage.

[0049] In a step 104, the static pressure probe measurement monitoring system calculates a right-left static pressure differential ( / IPsi) from the measurements obtained in step 102.

[0050] In a step 106, the static pressure probe measurement monitoring system determines a theoretical right-left static pressure differential (APsithe(^ from measurements and data obtained from a second set of sensors or equipment of the aircraft 500 which is distinct from the first set of sensors.

[0051] In a first embodiment, the static pressure probe measurement monitoring system incorporates a calculator for determining the theoretical right-left static pressure differential (APsithe„). This first embodiment is presented below in relation to [Fig.2].

[0052] In a second embodiment, the static pressure probe measurement monitoring system integrates a trained neural network to determine the theoretical right-left differential of static pressure (^shheo) - This second embodiment is presented below in relation to [Fig.3].

[0053] In a step 108, the static pressure probe measurement monitoring system compares the difference between the right-left differential calculated in step 104 (APsi) and that determined in step 106 (APsitheo) with a predetermined threshold TH.

[0054] In a step 110, the static pressure probe measurement monitoring system checks whether the difference between the right-left differential calculated in step 104 and that determined in step 106 is greater than the predetermined threshold TH. If this is the case, a step 112 is performed; otherwise, step 102 is repeated for a new real-time cycle of monitoring the static pressure probe measurements.

[0055] In step 112, the static pressure probe measurement monitoring system generates a static pressure measurement error alert. For example, the alert is an avionics, audible, and / or visual signal. In another example, the alert is a signal or message indicating that the measurements from the static pressure probes are potentially erroneous.

[0056] [Fig.2] schematically illustrates the system for monitoring measurements of static pressure probes, in a first embodiment.

[0057] In [Fig.2], the static pressure probe measurement monitoring system comprises a first differential circuit DI 203 configured to provide as output a difference, in absolute value, between a first static pressure measurement provided as input by a right static pressure probe SP_R 201 and a second static pressure measurement provided as input by a left static pressure probe SP_L 202.

[0058] The static pressure probe measurement monitoring system further comprises a computer 210 taking as input data (eg, measurements) from

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[0075] different sensors or equipment SI 221, S2 222 ... Sn 22n of the aircraft 500. The computer 210 applies a function F for estimating the theoretical right-left differential of static pressure. The theoretical right-left differential of static pressure is thus provided at the output of the computer 210. In a particular embodiment, the function F is such that the theoretical right-left differential of static pressure APsitheo is calculated as follows: = Al ( + Pdyn--^-ôr ) Or : - kp represents a coefficient such that AKp^ = -kp. / 3 , where ^Kp^ represents a side slip effect differential between the right and left of the fuselage; - m represents the mass of the aircraft 500 and & represents the gravitational acceleration; - 5 represents the surface of a wing of the aircraft (note that this surface of the wing serves as a common reference for determining the aerodynamic coefficients); - Pdyn represents the dynamic pressure; - Cy represents the gradient of the aerodynamic coefficient of lateral lift which is due to the deflection of the aircraft's rudder; - Cy' represents the gradient of the aerodynamic coefficient of lateral lift which is P due to skidding (also called sideslip) of the aircraft; - n> represents the lateral load factor; and - ôr represents the aircraft's rudder deflection angle. For example, the coefficient is obtained by flight tests, or by wind tunnel tests, or by calculations, or by theoretical analysis. It is known that in aircraft, the dynamic pressure Pdyn is calculated from the static pressure measurement and the total pressure measurement Ptot. It must be understood that here we are focusing on the differential of static pressure measurements between the right and left of the fuselage. Thus, even if a measurement is tainted with error, this results in a small error in dynamic pressure, which does not call into question the ability to detect the difference between the two static pressure measurements. In another embodiment, the function F is such that the theoretical right-left differential of static pressure APsitheo is calculated as follows: ^theo^ ■ (Cz-sinÿ +Cyô / ôr) Or : - Cz represents the aerodynamic coefficient of vertical lift; and

[0076] - represents the angle of inclination of the aircraft.

[0077] The static pressure probe measurement monitoring system further comprises a second differential circuit D2 230 configured to provide as output the difference, in absolute value, between the output of the first differential circuit DI 203 and the output of the computer 210 (i.e., the difference between the right-left differential calculated in step 104 and that determined in step 106).

[0078] The static pressure probe measurement monitoring system further comprises a comparator C 240 configured to compare the output of the second differential circuit D2 230 and a predetermined threshold TH. In this first embodiment, the predetermined threshold TH is for example equal to a value TH1 of 10 millibars.

[0079] The static pressure probe measurement monitoring system further comprises a warning generator circuit WG (Warning Generator in English) 250 configured to generate a static pressure measurement error alert, as described above, when the comparator output C 240 indicates that the output of the second differential circuit D2 230 is greater than the predetermined threshold TH.

[0080] [Fig.3] schematically illustrates the probe measurement monitoring system of static pressure, in a second embodiment.

[0081] In [Fig.3], the static pressure probe measurement monitoring system comprises the first differential circuit DI 203 and the static pressure probes SP_R 201 and SP_L 202, as described above in relation to [Fig.2].

[0082] The static pressure probe measurement monitoring system further comprises a neural network NN 211 trained to provide as output an estimate of the theoretical right-left differential of static pressure as a function of a set of data from different sensors or equipment S'1 321, S'2 322 ... Sn 32n of the aircraft 500.

[0083] The NN 211 neural network thus takes the following data set as input:

[0084] - ny • m , where it is recalled that ny represents the lateral load factor and m re presents the mass of the aircraft 500;

[0085] - the angle of attack a of the aircraft 500;

[0086] - 5r, the rudder deflection angle of the aircraft;

[0087] - H / V1, the engine speed differential between an engine on the right of the fuselage and a engine on the left side of the fuselage; and

[0088] - the Mach number.

[0089] A learning phase can be carried out by collecting these different data, as well as consolidated static pressure measurements, in order to train the NN neural network 211 to evaluate the value of the theoretical right-left static pressure differential APsithe() as a function of the parameters listed above.

[0090] Once the training of the NN 211 neural network is validated, the trained NN 211 neural network can be used in flight to determine the theoretical right-left differential of APsitheo static pressure as a function of the real-time values ​​of the parameters listed above.

[0091] The static pressure probe measurement monitoring system also comprises the second differential circuit D2 230, the comparator C 240 and the alert generator circuit WG 250, as described above in relation to [Fig. 2]. Thus, the second differential circuit D2 230 is configured to provide as output the difference, in absolute value, between the output of the first differential circuit DI 203 and the output of the neural network NN 211 (ze, the difference between the right-left differential calculated in step 104 and that determined in step 106).

[0092] In this second embodiment, the predetermined threshold TH is for example equal to a value TH2 of 5 millibars.

[0093] In an exemplary embodiment, the NN 211 neural network comprises a hidden layer with 15 nodes.

[0094] The arrangements presented above in relation to Figs. 2 and 3 make it possible to implement in the form of electronic circuits a method in accordance with the algorithm of [Fig. 2]. The algorithm of [Fig. 2] can also be implemented in software form for execution by a processor, as described below in relation to [Fig. 4].

[0095] [Fig.4] thus schematically illustrates an example of a hardware platform suitable for implementing the static pressure probe measurement monitoring system (referenced SYS 400 in [Fig.4]) in the form of electronic circuitry.

[0096] The hardware platform then comprises, connected by a communication bus 410: a processor or CPU (Central Processing Unit) 401; a RAM (Random Access Memory) 402; a read-only memory 403, 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) 404, or a storage media reader, such as an SD (Secure Digital) card reader; and an interface manager 1 / 1' 405.

[0097] The I / f interface manager 405 allows the hardware platform to interact with sensors of the aircraft 500. In one embodiment, the I / f interface manager 405 allows the hardware platform to interact with peripherals, such as human-machine interface peripherals (cockpit screen, etc.) of the aircraft 500.

[0098] The processor 401 is capable of executing instructions loaded into the RAM 402 from the ROM 403, an external memory, a storage medium (such as an SD card), or a communications network. When the When the hardware platform is powered on, the processor 401 is capable of reading instructions from the RAM 402 and executing them. These instructions form a computer program causing the processor 401 to implement all or part of the steps described herein.

[0099] All or part of the steps described here can 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 dedicated set of electronic components (chipset). Generally speaking, the SYS 400 system comprises electronic circuitry adapted and configured to implement the steps described here.

Claims

Claims

1. Method for detecting a measurement error in a pair of right-left static pressure probes of an aircraft (500), the method being implemented by a system in the form of electronic circuitry, the method comprising: - obtaining (102) right / left static pressure measurements from the pair of right-left static pressure probes which forms a first set of equipment of the aircraft (500); - calculating (104) a right-left static pressure differential APsi from the measurements obtained; - determining (106) a theoretical right-left static pressure differential APsithem from a second set of equipment of the aircraft (500) which is distinct from the first set of equipment; - performing (108) a comparison between the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsi^^ with a predetermined threshold;- when the comparison shows that the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsitheo is greater than the predetermined threshold, generate (112) a static pressure measurement error alert.;

2. Method according to claim 1, in which determining a theoretical right-left differential of static pressure APsithea comprises applying a function F for estimating the theoretical right-left differential of static pressure.

3. Method according to claim 2, in which the function F for estimating the theoretical right-left differential of static pressure is such that the theoretical right-left differential of static pressure APsithe(> is calculated as follows: = "V +Pdyn--~-Ôr j where: - kp represents a coefficient such that AKpp = -kg.fi, where AKp re-represents a differential of lateral slip effect between the right and the left of the fuselage of the aircraft; - m represents the mass of the aircraft and 8 represents the gravitational acceleration; - 5 represents the surface of a wing of the aircraft; - Pdyn represents the dynamic pressure; - Cy represents the gradient of the aerodynamic coefficient of lateral lift which is due to the deflection of the aircraft's rudder; - Cy^ represents the gradient of the aerodynamic coefficient of lateral lift which is due to the sideslip of the aircraft; - represents the lateral load factor; and - ôr represents the rudder deflection angle of the aircraft.

4. Method according to claim 2, in which the function F for estimating the theoretical right-left differential of static pressure is such that the theoretical right-left differential of static pressure APsitheo is calculated as follows: where: - kp represents a coefficient such that AK= -kp . 0 ,where AKPp represents a lateral slip effect differential between the right and the left of the fuselage of the aircraft; - Pdyn represents the dynamic pressure; - Cy represents the gradient of the aerodynamic coefficient of lateral lift which is due to the deflection of the rudder of the aircraft; - represents the aerodynamic coefficient of vertical lift; and - 0 represents the angle of inclination of the aircraft.

5. The method of claim 2, wherein determining a theoretical right-left static pressure differential APsitheo comprises using a trained neural network (211) taking as inputs the following data set: _ ny . m , where ny represents the lateral load factor and m represents the mass of the aircraft; - the angle of attack a of the aircraft; - the rudder deflection angle ôr of the aircraft; - the engine speed differential zWl between an engine on the right of the fuselage and an engine on the left of the fuselage of the aircraft; and - the Mach number.

6. A computer program product comprising instructions causing an implementation of the method according to any one of claims 1 to 5, when the instructions are executed by a processor.

7. An information storage medium on which are stored instructions causing an implementation of the method according to any one of claims 1 to 5, when the instructions are read from the information storage medium and executed by a processor.

8. System for monitoring measurements of the pair of right-left static pressure probes of an aircraft (500), said system being in the form of electronic circuitry configured to: - obtain (102) right / left static pressure measurements from the pair of right-left static pressure probes which forms a first set of equipment of the aircraft; - calculate (104) a right-left static pressure differential APsi from the measurements obtained; - determine (106) a theoretical right-left static pressure differential APsirheo, from a second set of equipment of the aircraft which is distinct from the first set of equipment; - perform (108) a comparison between the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsi^) with a predetermined threshold;- when the comparison shows that the difference between the calculated right-left differential APsi and the determined theoretical right-left differential APsithe„ is greater than the predetermined threshold, generate (112) a static pressure measurement error alert.;

9. Aircraft (500) comprising at least one pair of right-left static pressure probes placed on either side of the fuselage, and at least one system for monitoring measurements of the pair of right-left static pressure probes according to claim 8.

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