Method for validating aerodynamic measurements and associated validation device

Abstract

Method for validating aerodynamic measurements and associated validation device. The present invention relates to a method for validating aerodynamic measurements implemented by an architecture comprising N separate measurement channels, each comprising Pm probes, comprising the following steps: - acquisition (110) of an elementary measurement from each probe; - for each measurement channel, determination (120) of a resultant measurement from the probes belonging to that channel; - comparison (130) of the resultant measurements: + when the resultant measurements are consistent, validation (140) of the measurements; + when a resultant measurement relating to channel k is inconsistent: - selection (170) of a measurement channel i; - determination (180) of Pi+Pk consistency values; - determination (190) of an inconsistent value from among the set of consistency values; - invalidation (200) of any elementary measurement from the probe corresponding to the inconsistent value.Figure for the abbreviation: Figure 3.

Description

Title of the invention: Method for validating aerodynamic measurements and associated validation device

[0001] The present invention relates to a method for validating aerodynamic measurements.

[0002] The present invention also relates to a validation device implementing such a process.

[0003] The field of the invention is that of critical systems known as "Air Data" ("Air Data" in French), and in particular of supervision and safety ("safety" in English) of such systems.

[0004] For many years, critical Air Data system architectures have allowed the calculation of static pressures and associated secondary parameters by averaging pressures measured by passive sensors located on each side (right / left) of aircraft. This average directly accounts for the effects of sideslip and has historically been calculated pneumatically using hoses connected to a single measurement electronics unit housed in a computer often called an Air Data Unit (ADU), which contains a single pressure sensor and the associated electronics.

[0005] Digital probes, which have appeared more recently, have the advantage of reducing (or even eliminating) pipes but have the disadvantage of increasing the number of sensors and associated electronics (which will be called "Air Data Electronic Measurement", AD EM) required to calculate a right / left static pressure average.

[0006] In particular, digital probes generally require at least two ADEMs to perform an average calculation, whereas in older architectures, a single ADU was sufficient.

[0007] Indeed, in older architectures with passive probes (without measurement electronics in the probe), the sensor, which calculates the static pressure, actually measures the right / left pneumatic average collected by the two passive probes. Physically, this corresponds to averaging the pressures on both sides of the aircraft and thus taking into account the disruptive effects of sideslip. Therefore, one ADU per measurement channel was sufficient.

[0008] In digital architectures, the probes have locally the electronics necessary for calculating static pressure; therefore, they measure the right and left pressures independently. As such, each probe must integrate a sensor and its associated electronics (ADEM), which, at a minimum, doubles the number of ADEMs compared to previous systems with "passive" probes. This necessitates, by calculation, The pressure measurements on both sides of the aircraft are averaged. Therefore, at least two ADEMs per measurement channel are required. For example, in such a case, given that it is a critical system, at least three measurement channels, each with at least two ADEMs, are necessary. This reduces the total number of ADEMs required to six.

[0009] It is therefore understandable that the use of digital probes leads to an increase in their number compared to the pneumatic solution. This thus reduces the advantages of digital probes.

[0010] The present invention aims to overcome this drawback of digital probes. In particular, the present invention aims to provide a solution for using digital probes while reducing the number of probes required for operation with a critical system.

[0011] To this end, the invention aims at a method for validating aerodynamic measurements implemented by an aeronautical measurement architecture embedded at least partially in an aircraft and comprising N separate measurement channels, each measurement channel comprising Pm probes, the index m varying from 1 to N, the method comprising the following steps:

[0012] - acquisition of an elementary measurement of each probe;

[0013] - for each measurement channel, determination of a resulting measurement from the elementary measurements of the probes belonging to this measurement channel;

[0014] - comparison of the resulting measurements with each other:

[0015] + when the resulting measures are consistent with each other, validation of the whole basic measures;

[0016] + when a resulting measure relating to channel k is inconsistent with the others resulting measures:

[0017] - selection of a measurement channel i whose number of probes Pi is equal to at least 2;

[0018] - determination of Pi+Pk consistency values, each consistency value being determined by a coherence function on a subset of elementary measurements of the probes of channels i and k excluding the elementary measurement relating to one of the probes belonging to one of the channels;

[0019] - determination of an inconsistent value among the set of consistent values, said inconsistent value being calculated on the subset of elementary measurements excluding the elementary measurement relating to probe j;

[0020] - invalidation of any elementary measurement from probe j.

[0021] According to other advantageous aspects of the invention, the method comprises one or more of the following features, taken individually or in all technically possible combinations:

[0022] - the method further comprising a step of analyzing the consistency of the measures elementary to each other, originating from the probes of channel k when the number of probes Pk in this channel k is strictly greater than 2;

[0023] - the consistency function is defined beforehand as a function of at least one parameter chosen from the group including:

[0024] - aircraft speed;

[0025] - aircraft shape;

[0026] - aerodynamic configuration of the aircraft;

[0027] - placement of the corresponding probes;

[0028] - nature of the corresponding probes.

[0029] - the probes of the same measurement channel are arranged on different sides of the aircraft;

[0030] - each measurement channel m comprises Pm / 2 probes arranged on one side of the aircraft and Pm / 2 probes positioned on the other side of the aircraft;

[0031] - each probe is a static pressure probe;

[0032] - the consistency function is defined according to SSEC laws (from the English "Static Source Error Correction") of the corresponding probes;

[0033] - all the probes are of the same type;

[0034] - N=2 and Pm=2 for any index m.

[0035] The invention also relates to a computer program comprising software instructions which, when executed by a computer, implement the process as defined above.

[0036] The invention also relates to a validation device comprising technical means configured to implement the process as defined below.

[0037] The invention will become clearer upon reading the following description, given solely by way of non-limiting example, and made with reference to the drawings in which:

[0038] - [Fig. 1] [Fig. 1] is a schematic view of a measurement architecture aeronautics, the architecture comprising a validation device according to the invention;

[0039] - [Fig.2] [Fig.2] is a detailed schematic view of the validation device [Fig. 1] ; and

[0040] - [Fig.3] [Fig.3] is a flowchart of a validation process according to the invention, the process being implemented by the validation device of [Fig.2].

[0041] Fig. 1 illustrates an aeronautical measurement architecture 10. This architecture 10 is advantageously at least partially embedded in an aircraft.

[0042] The term aircraft means any pilotable, remotely piloted, or autonomous machine capable of moving through the air. In particular, an aircraft may refer to an airplane or to a helicopter or a drone. The aircraft can be piloted by a pilot from its cockpit and / or by any other operator from a remote control center.

[0043] With reference to [Fig.1], the aeronautical measurement architecture 10 comprises N measurement channels 12, a processing system 14 and a validation device 16.

[0044] The measurement channels 12 are independent of each other and allow aerodynamic measurements, such as static pressure, to be provided independently.

[0045] In particular, each measurement channel 12 comprises Pm probes 21, the index m varying from 1 to N. Each number Pm is greater than or equal to 1.

[0046] Each probe 21 has a digital sensor for providing an aerodynamic measurement, such as static pressure, in the form of a numerical value. For this purpose, each probe 21 is advantageously located outside the aircraft. Each probe 21 is, for example, attached to the aircraft fuselage.

[0047] The probes 21 of the same measuring channel 12 are advantageously arranged on different sides of the aircraft. For example, Pm / 2 probes 21 of each measuring channel 12 are arranged on the right side of the aircraft and the other Pm / 2 probes 21 of that same measuring channel 12 are arranged on the left side.

[0048] Furthermore, advantageously, the probes 21 within the same measurement channel 12 are all of the same type. In other words, these probes 21 allow the measurement of the same physical quantity. It is further assumed hereafter, without loss of generality, that probes 21 belonging to different channels also allow the measurement of the same physical quantity.

[0049] In the example of [Fig. 1], two measurement channels 12, each comprising two probes 21, are shown. In other words, in such a case, the number N is equal to 2 and each number Pm (m=1 or 2) is equal to 2. Furthermore, the probes 21 of each measurement channel 12 are arranged on different sides of the aircraft, namely the right side and the left side. Thus, in the example of [Fig. 1], each measurement channel 12 comprises a left probe and a right probe.

[0050] According to another example, the architecture 10 comprises N measuring channels 12 and the different measuring channels comprise a different number of probes. For example, in such a case, P1=2, P2=3, P3=1, ..., P1=4.

[0051] The probes 21 are connected to the processing device 14 and are configured to provide the corresponding aerodynamic measurements to this device 14.

[0052] The processing device 14 receives all the aerodynamic measurements generated by the measurement channels 12 and processes them appropriately in order to provide a result of such processing to any interested system. Such an interested system may, for example, include a human-machine interface, a piloting system (e.g., an autopilot), or a flight planning system (e.g., an FMS, or Flight Management System). Management System"), etc. In addition, the processing device 14 allows each received aerodynamic measurement to be processed according to the measurement channel that generated this measurement.

[0053] In particular, the processing device 14 may include a separate computer for each measurement channel 12 to implement independent processing of the aerodynamic measurements from the independent measurement channels 12. The processing device 14 may, in particular, include a computer of the "Air Data Computer" type, known per se.

[0054] The validation device 16 according to the invention allows each aerodynamic measurement from each probe 21 to be validated / invalidated. This validation device 16 is, for example, connected between each probe 21 and the processing device 14.

[0055] The validation device 14 is illustrated in more detail in [Fig.2].

[0056] With reference to this [Fig.2], the validation device 14 includes in particular a input module 31, a processing module 32 and an output module 33.

[0057] The input module 31 is connected to the set of probes 21 and allows to receive each aerodynamic measurement from each probe 21.

[0058] The processing module 32 allows the processing of all aerodynamic measurements to validate or invalidate each of them, as will be explained in more detail later.

[0059] In addition, the processing module 32 allows each validated aerodynamic measurement to be transmitted to the output module 33.

[0060] The output module 33 allows each aerodynamic measurement validated by the processing module 32 to be transmitted to any interested external system and in particular to the processing device 14 as explained previously.

[0061] Each of these modules 31 to 33 is implemented, for example, at least partially in the form of software.

[0062] In such a case, the validation device 14 further includes a memory for storing such software and a processor for executing this software.

[0063] Alternatively or in addition, at least one of these modules 31 to 33 presents at least partially a programmable logic circuit such as an FPGA (Field-Programmable Gate Array) circuit.

[0064] Other embodiments of the validation device 16 are also possible. Thus, for example, this validation device 16 may include a processing chain for each measurement channel allowing the aerodynamic measurements from that measurement channel to be processed separately and a shared area allowing the aerodynamic measurements from different measurement channels to be analyzed and compared.

[0065] The validation device 16 allows for the implementation of a validation process for aerodynamic measurements which will henceforth be explained with reference to [Fig.3] presenting a flowchart of its steps.

[0066] Initially, it is considered that each probe 21 generates an aerodynamic measurement and transmits it to the validation device 16. Such a measurement will be called an elementary measurement thereafter.

[0067] During an initial step 110 of the process, the input module 31 acquires each elementary measurement and transmits it to the processing module 32. Thus, for each measurement channel, Pm elementary measurements are transmitted to the processing module 32.

[0068] In the example of [Fig.1], four elementary measurements, namely Psl_1, Psl_r, Ps2_1 and Ps2_r, corresponding to the measurements generated respectively by the left probe of the first channel, the right probe of the first channel, the left probe of the second channel and the right probe of the second channel, are then generated.

[0069] In a subsequent step 120, for each measurement channel 12, the processing module 32 determines a resulting measurement from the set of elementary measurements from the probes 21 belonging to that measurement channel 12.

[0070] The resulting measurement for each measurement channel is calculated, for example, using the same function F on all the elementary measurements corresponding to that channel. This function F can correspond, for example, to an average or any other function known in itself for calculating a resulting value from a plurality of samples.

[0071] In other words, during this step, N resulting measures are calculated.

[0072] In the example of [Fig. 1], during this step 120, two resulting measurements, at knowing the measurements Psi and Ps2 corresponding respectively to the averages of the values ​​Psl_l and Psl_r, and Ps2_l and Ps2_r are determined.

[0073] In a subsequent step 130, the processing module 32 compares all the resulting measurements to determine their consistency. A specific function, known per se, can be used for this purpose. For example, two resulting measurements can be considered consistent when the difference between them is less than a predetermined threshold. Otherwise, these measurements are inconsistent.

[0074] Consistency analysis can be carried out, for example, by comparing the measurements two by two.

[0075] Thus, when N>2, the processing module 32 can determine an inconsistent resulting measure when it is inconsistent with each other resulting measure given that these other resulting measures are consistent with each other.

[0076] When N=2, the processing module 32 concludes that when the two resulting measurements are sufficiently different, each of these resulting measurements is inconsistent.

[0077] In the example of [Fig.1], the measurements Psi and Ps2 can be consistent when their difference is less than a threshold.

[0078] When, following the implementation of the consistency analysis, the processing module 32 concludes that all the resulting measures are consistent with each other, in the following step 140, it validates all the elementary measures (or resulting measures) and transmits them to the output module 33. This output module 33 in turn transmits these measures to the processing device 14.

[0079] Conversely, when the processing module 32 determines a resulting measure that is inconsistent with the others, it proceeds to execute step 150 and the subsequent steps related to that measure. The inconsistent measure is then considered to originate from the measurement path with index k.

[0080] In the next step 150, the processing module 32 first attempts to analyze the consistency of the elementary measurements with each other within the measurement channel k.

[0081] When possible (particularly when Pk>2), the processing module 32 determines the probe with index j that provides the elementary measurement causing the inconsistency and excludes from consideration any elementary measurement from probe j. Then, in the following step 160, the processing module 32 validates all the elementary measurements except the one from probe j and transmits them to the output module 33. This output module 33 in turn transmits these measurements to the processing device 14.

[0082] When this is not possible (in particular when Pk<2), the processing module 32 proceeds to the execution of a subsequent step 170.

[0083] During step 170, the processing module 32 selects a measurement channel i, different from the measurement channel k, whose number of probes Pi is equal to at least 2.

[0084] In a subsequent step 180, the processing module 32 determines Pi+Pk coherence values.

[0085] Each coherence value corresponds to the value of a coherence function calculated on a subset of elementary measurements of channels i and k, excluding the elementary measurement relating to one of the probes belonging to one of the channels. Thus, each coherence value is determined from Pi+Pk-1 elementary measurements and is associated with the probe 21 whose elementary measurement was excluded from its calculation.

[0086] According to a particular embodiment, the consistency function is defined beforehand as a function of at least one parameter chosen from the group comprising:

[0087] - aircraft speed;

[0088] - aircraft shape;

[0089] - aerodynamic configuration of the aircraft;

[0090] - placement of the corresponding probes;

[0091] - nature of the corresponding probes.

[0092] For example, the consistency function can be defined according to the SSEC (Static Source Error Correction) laws of the corresponding probes. These SSEC laws can be defined during dedicated flight tests.

[0093] In the example in [Fig. 1], a consistency value is determined for each subset of three elementary measures.

[0094] In other words, the following consistency values ​​are determined:

[0095] F3(Ps 1_1,Ps l_r,Ps2_l) = Ps l_3_inf

[0096] F3(Ps 1_1,Ps l_r,Ps2_r) = Ps2_3_inf

[0097] F3(Ps2_l,Ps2_r,Ps 1_1) = Ps3_3_inf

[0098] F3(Ps2_l,Ps2_r,Ps l_r) = Ps4_3_inf

[0099] where F3(...) is the coherence function applicable in this example.

[0100] In a subsequent step 190, the processing module 32 determines, from among the set of coherence values, a value that is inconsistent with the other coherence values. In other words, it is a value that is inconsistent with respect to the other Pi+Pk-2 values.

[0101] In particular, to determine such an inconsistent value, the processing module 32 analyzes all the consistency values ​​and selects the value that differs most from the others. Various techniques known per se can be used for this purpose. For example, the inconsistent value may be closer to the resulting measurement provided by one of the measurement channels other than measurement channel k than the other consistency values. In this context, the inconsistent value may correspond to a non-erroneous measured value, while all the other consistency values ​​may correspond to an erroneous measurement.

[0102] Then, the processing module 32 determines the probe j corresponding to this inconsistent value. In other words, the processing module 32 determines the probe j whose elementary measurement was excluded from the calculation of the inconsistent value.

[0103] In the example in [Fig. 1], the consistency value Psl_3_inf may be closer to the value Psi than the other consistency values ​​Ps2_3_inf, Ps3_3_inf, and Ps4_3_inf. Therefore, the consistency value Psl_3_inf may correspond to a non-erroneous measurement, while the other consistency values ​​Ps2_3_inf, Ps3_3_inf, and Ps4_3_inf may correspond to an erroneous measurement. In such a case, during this step 190, the value Psl_3_inf is considered the inconsistent value.

[0104] During the next step 200, the processing module 32 validates all the elementary measurements except for the one from probe j and transmits them to the output module 33. This output module 33 in turn transmits these measurements to the processing device 14.

[0105] According to one embodiment, the processing module 32 can apply further techniques to validate / invalidate an elementary measurement. These techniques can be applicable when, for example, two probes are found to be faulty. These techniques can include the use of yaw information (or even other information from the Fly-by-Wire Control System - VTCS) combined with consistency checking. This operation is facilitated if the Air Data function is hosted in a partition of the VTCS or 1RS (Inertial Reference System) computer.

[0106] It is therefore conceivable that the present invention offers a number of advantages. In particular, it is clear that the invention makes it possible to reduce the number of measurement channels required to operate with a critical system. Specifically, two measurement channels, each comprising two probes, may be sufficient to operate with a critical system. Of course, it remains possible to increase the number of measurement channels and / or probes to further increase the reliability / availability of the architecture.

Claims

Demands

1. A method for validating aerodynamic measurements implemented by an aeronautical measurement architecture (10) carried at least partially in an aircraft and comprising N separate measurement channels (12), each measurement channel (12) comprising Pm probes (21), the index m varying from 1 to N, the method comprising the following steps: - acquisition (110) of an elementary measurement from each probe (21); - for each measurement channel (12), determination (120) of a resultant measurement from the elementary measurements of the probes (21) belonging to that measurement channel (12); - comparison (130) of the resultant measurements with each other: + when the resultant measurements are consistent with each other, validation (140) of all the elementary measurements; + when a resulting measurement relating to channel k is inconsistent with the other resulting measurements: - selection (170) of a measurement channel i whose number of probes Pi is equal to at least 2;- determination (180) of Pi+Pk coherence values, each coherence value being determined by a coherence function on a subset of elementary measurements of the probes (21) of channels i and k excluding the elementary measurement relating to one of the probes (21) belonging to one of the channels (12); - determination (190) of an inconsistent value among the set of coherence values, said inconsistent value being calculated on the subset of elementary measurements excluding the elementary measurement relating to probe j; - invalidation (200) of any elementary measurement from probe j.;

2. A method according to claim 1, further comprising a step of analyzing the consistency of the elementary measurements with each other, from the probes (21) of channel k when the number of probes Pk in this channel k is strictly greater than 2.

3. A method according to any one of the preceding claims, wherein the consistency function is defined beforehand as a function of at least one parameter chosen from the group comprising: - aircraft speed; - aircraft shape;

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10. - aerodynamic configuration of the aircraft; - placement of the corresponding probes; - nature of the corresponding probes. A method according to any one of the preceding claims, wherein the probes (21) of the same measurement channel (12) are arranged on different sides of the aircraft. Method according to claim 4, wherein each measurement channel m comprises Pm / 2 probes disposed on one side of the aircraft and Pm / 2 probes disposed on the other side of the aircraft. Method according to any one of the preceding claims, wherein each probe (21) is a static pressure probe. A method according to claim 6, wherein the consistency function is defined according to the SSEC (Static Source Error Correction) laws of the corresponding probes. A method according to any one of the preceding claims, wherein all the probes (21) are of the same nature. A method according to any one of the preceding claims, wherein N=2 and Pm=2 for any index m. Aerodynamic measurement validation device (16) comprising technical means (31, 32, 33) configured to implement the method according to any one of the preceding claims.

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