FR3079332A1 - METHOD FOR RECORDING AND ANALYZING OPERATING DATA OF AN AIRCRAFT AND ASSOCIATED RECORDING SYSTEM - Google Patents

Abstract

The present invention relates to a method and system (50) for recording and analyzing operating data of an aircraft (30), such a system (50) for identifying at least one cause of malfunction of a equipment (31) of the aircraft (30). This system 50 comprises a computer (33) configured to at least record a first set of operating data (J1) in a first memory (32), the computer (33) also being reconfigurable to record at least a second set of data of operation (J2) in the first memory (32) and thus confirm and / or specify the cause (s) of malfunction of the equipment (31).

Description

Method for recording and analyzing operating data of an aircraft and associated recording system

The present invention relates to the aeronautical field and more particularly to the recording of electronic data representative of the operation of at least one piece of equipment of an aircraft such as an airplane, a rotorcraft or even a drone. Recording and then analyzing this data, for example by a team in charge of aircraft maintenance, is essential in order to identify the cause (s) of any malfunction, even minor, of this (or these) equipment. (s).

In fact, when a minor malfunction of aircraft equipment is detected, an alarm can be generated, resulting in immobilization on the ground of the aircraft. An aircraft maintenance team may also have to go to where the aircraft may have landed in an emergency. Such a place can in particular be difficult to access, dangerous, even hostile.

Maintenance teams must therefore be constantly available and in sufficient numbers to be able to go wherever its aircraft perform missions. In addition, such maintenance teams can use very expensive means of transport to be able to quickly get to where an aircraft would have landed in an emergency.

Furthermore, even if the maintenance team is not required to travel to the site, it must nevertheless succeed in identifying the equipment of the aircraft that has had a malfunction, in replacing it, or even also recovering and analyzing aircraft operating data recorded in the aircraft at the time of the malfunction. In this way, the maintenance team can determine the cause (s) causing the malfunction to replace other aircraft equipment that has not experienced any malfunction.

Indeed, during the analysis of the recorded operating data, that is to say the extraction and analysis thereof via for example computer tools allowing graphical editing of these data, the maintenance team can make certain assumptions as to the cause (s) of the malfunction.

However, for obvious mass issues, the data storage space is limited on board the aircraft. Consequently, the number of variables to be analyzed representative of the data is also limited and an initial choice of the data to be recorded must be made. Indeed, the functions implemented by an aircraft being numerous, it is often judicious to privilege a broad panel of variables to record covering the whole of the functions rather than to target precisely a limited number of functions with a large number of variables to record dedicated to each function.

Obviously the choice of variables is made in a precise and relevant manner, but sometimes it is difficult if not impossible to identify precisely the cause of a malfunction when the variables allowing the unambiguous identification of this cause are not recorded. Therefore, the maintenance team is forced to make certain assumptions with different levels of uncertainty to determine one or more probable causes of the malfunction.

In addition, some aircraft operators are sometimes subject to very specific malfunctions caused by a very specific environment in which their aircraft sometimes operate.

In this case, the analysis of the recorded data does not always identify the cause (s) causing the malfunction. An aircraft operator may then be asked to retrieve new data later, many times after each aircraft mission, and to transmit this new data to the maintenance team. In addition, the operator of the aircraft may also be asked to perform special operations on the aircraft.

These limitations of the current operating mode therefore have a significant cost and consequences in terms of logistics. In addition, these limitations are also detrimental to the customer relationship between the operator and the aircraft manufacturer, the image of the aircraft manufacturer and / or the operator's trust. aircraft in control of maintenance by the manufacturer.

In addition, a dysfunction can occur only when the concordance of different very specific causes and therefore the repeatability of the cause and effect relationship can be uncertain. It is therefore difficult for the maintenance team to analyze the cause (s) of this dysfunction appearing sometimes at random. The resolution of this malfunction can then be long and also taint the customer relationship between the operator of the aircraft and the manufacturer.

In addition, document WO 2011/017812 describes an aircraft flight data delivery and management system. However, in this case, a memory that is an integral part of a computer contains the internal configuration parameters of the computer so as to store a predetermined list of variables. However, any change in the internal configuration of the computer necessarily results in a new identification number for the latter and therefore a new certification of the latter. Such an embodiment would then be incompatible with the commercial operation of an aircraft and would in no way allow a maintenance team to identify more quickly the cause (s) of equipment equipment malfunction. aircraft.

The object of the present invention is therefore to propose a method and a system making it possible to overcome the limitations mentioned above. Such a recording and analysis method in fact makes it possible to reduce, or even eliminate, the maintenance actions carried out by an operator of the aircraft in order to identify the (or the) cause (s) of malfunction of a aircraft equipment.

Furthermore, such a method can make it possible to avoid the displacement of a maintenance team on the site where the aircraft has landed and can at the very least considerably reduce the time necessary for this maintenance team to identify the (or the ) cause (s) of the malfunction.

The invention therefore relates to a method of recording and analyzing operating data of an aircraft, such a method making it possible to identify at least one cause of malfunction of equipment of the aircraft and comprising:

A first recording step making it possible to record in a first memory a first set of operating data of the aircraft over a first time interval, the first set of operating data being representative of the variations in time of at least at least a first variable, the first recording step being implemented by a computer configured to record the first set of operating data in the first memory, • a first transmission step to transmit the first set of operating data from the first memory to at least one ground station, and • a first analysis step for analyzing the first set of operating data, the first analysis step being implemented in the ground station (s) .

According to the invention, such a method is remarkable in that it comprises at least:

• a definition step to define at least one second variable distinct from the first variable (s), an analysis of the variations over time of the second variable (s) allowing confirm and / or specify the cause (s) of aircraft equipment malfunction, • a modification step allowing modification of an external configuration of the computer in order to allow the recording in the first memory of the variations in time of the second variable (s), a second recording step making it possible to record in the first memory a second set of operating data of the aircraft over a second interval of time, the second set of operating data being representative of the variations over time of the second variable (s), the second recording step being implemented by the computer newly configured for e n save the second data set in the first memory, • a second transmission step to transmit the second operating data set from the first memory to the ground station (s), and • a second analysis step for analyzing the second set of operating data, the second analysis step being implemented in the ground station (s).

In other words, such a method allows an aircraft manufacturer to carry out reconfiguration (s) remotely from a computer without requiring any action on the part of the operator of the aircraft. Thus, by reconfiguring the computer externally, the method makes it possible to record one (or more) second variable (s) distinct from the first variable (s).

In addition, such an external reconfiguration of a computer is particularly advantageous since it does not modify the identification number of the latter and therefore such a computer retains its current certification.

Advantageously, the modification step making it possible to modify the external configuration of the computer may consist in modifying all or part of an external table of values stored in a second memory, the second memory being distinct from the first memory.

Such an external table of values is then used by the computer, but its modification is very easy and it has no impact on one (or more) algorithm (s) implemented by the computer.

In practice, the modification step making it possible to modify the external configuration of the computer can be implemented once during an initialization of the computer, the computer implementing at least once a configuration algorithm making it possible to read all or part values contained in the table of values.

In other words, such a configuration algorithm can make it possible to first search in the table of values for the first variable (s) to be recorded by the computer, then in a second time the second variable (s) to be recorded by the computer.

According to an advantageous example of the invention, the modification step making it possible to modify the external configuration of the computer can be implemented cyclically several times to allow the variations in time of the (or) to be recorded in the first memory. second variable (s) distinct from the first variable (s).

In this way, the modification of the external configuration of the computer makes it possible to register at least one third variable distinct from the (or) first variable (s) and from the (or) second (s) variable (s). ) and / or to record at least the first variable (s) along with the second variable (s) according to several successive cycles.

Of course, the second memory containing the table of values representative of the external configuration of the computer can be of different types.

Thus, according to a first embodiment of the invention, the second memory can be a non-volatile memory arranged in the computer.

In other words, such a second memory is then non-temporary and retained if the computer is no longer supplied with electrical energy.

According to a second embodiment of the invention, the second memory can be separated from the computer. Such a second memory can for example be a random access memory connected to the computer.

In addition, the second memory can also be of the removable type. This second memory can then be formed by a removable hard disk, a memory card or even a USB key, for example.

Advantageously, at least one of the first transmission step and second transmission step can be carried out on the ground after an aircraft mission.

In this case, once the aircraft is on the ground, the first set of operating data and / or the second set of operating data is / are transmitted from the first memory to the ground station either by a wired connection electrically or optically connecting the first memory and the ground station, either by a wireless connection using, for example, radio frequency communication protocols of the Wi-Fi or Bluetooth type in particular.

In contrast, according to another exemplary embodiment of the invention, at least one of the first step of transmission and second step of transmission can be carried out in flight during a mission of the aircraft.

In this case, the transmission of the first set of operating data and / or of the second set of operating data will then be carried out by a wireless connection using, for example, radio frequency communication protocols such as Wi-Fi or Bluetooth in particular. The first transmission step and second transmission step can also be carried out in real time when recording in the first memory of the first operating data set and / or the second operating data set.

The present invention also relates to a system for recording and analyzing aircraft operating data, the system making it possible to identify at least one cause of malfunction of equipment of the aircraft and comprising:

• a first memory capable of storing a first set of operating data of the aircraft over a first time interval, the first set of operating data being representative of the variations over time of at least one first variable, • a computer configured to at least record the first set of operating data in the first memory, • a transmission interface for transmitting the first set of operating data from the first memory to at least one ground station, and • an analysis unit allowing analyze the first set of operating data, the analysis unit being included in the station (s) itself.

According to the invention, this system is remarkable in that it makes it possible to define at least one second variable distinct from the first variable (s), an analysis of the variations over time of the (or ) second variable (s) making it possible to confirm and / or to specify the cause (s) of malfunction of the aircraft equipment, the computer being reconfigured to record in the first memory the variations in the time of the second variable (s), the first memory being capable of storing a second set of operating data of the aircraft over a second time interval, the second set of operating data being representative of the variations in time of the second variable (s), the transmission interface transmitting the second set of operating data from the first memory to the ground station (s), and the unit of analysis for analyzing er the second set of operating data.

In other words, such a system allows an aircraft manufacturer to perform (or) reconfiguration (s) remotely of a computer without having to request the operator of the aircraft. Thus, by reconfiguring the computer externally, such a system makes it possible to record one (or more) second variable (s) distinct from the first variable (s).

As already mentioned, such an external reconfiguration of the computer is advantageous since it does not cause any modification in the identification number of this computer and therefore the current certification of the computer can be kept after each external reconfiguration of the computer.

Advantageously, the system can include a second memory capable of storing a table of values representative of an external configuration of the computer, the second memory being distinct from the first memory.

Thus, the table of values contained in this second memory can be modified without the algorithm implemented by the computer being modified. Such an arrangement of the external configuration of the computer then allows this computer to record in the first memory firstly the first set of operating data and then in a second time the second set of operating data.

The modified table of values is not subject to any constraints in terms of sizing. It could be equivalent to the initial table of values, which itself was dimensioned to have the best sizing in terms of size.

The analysis unit then makes it possible to confirm and / or specify the cause (s) of malfunction of the aircraft equipment.

Furthermore and as already mentioned, the second memory of such a system making it possible to contain the table of values representative of the external configuration of the computer can be in different forms. For example, this second memory can be a non-volatile memory arranged in the computer or alternatively be separated from the computer by being of the removable type.

The invention and its advantages will appear in more detail in the context of the description which follows with examples given by way of illustration with reference to the appended figures which represent:

FIG. 1, a block diagram illustrating a first variant of a system for recording and analyzing operating data of an aircraft, in accordance with the invention,

FIG. 2, another block diagram illustrating a second variant of a system for recording and analyzing operating data of an aircraft, in accordance with the invention,

FIG. 3, a flow diagram illustrating a first embodiment of a method for recording and analyzing operating data of an aircraft, in accordance with the invention, and

- Figure 4, another flowchart illustrating a second embodiment of a method of recording and analyzing operating data of an aircraft, according to the invention.

The elements present in several separate figures are assigned a single reference.

As already mentioned, the invention relates to the method and system for recording and analyzing operating data of an aircraft.

As shown in FIG. 1, a first variant of such a system 50 is associated with a first aircraft variant 30 capable of transmitting operating data sets J1, J2 from a first memory 32 to a ground station 34.

This system 50 includes an analysis unit 52 making it possible to analyze the operating data sets J1, J2 and to identify at least one cause of malfunction of aircraft equipment 31.

Thus, the first memory 32 makes it possible to store at least temporarily the first set of operating data J1 of the aircraft 30 over a first time interval t1. In addition, such a first set of operating data J1 is representative of the variations over time of at least one first variable V1 which may for example consist of a voltage or an intensity of an electric current at the output of a sensor.

A computer 33 arranged on the aircraft 30 is then initially configured to record the first set of operating data J1 in the first memory 32.

Furthermore, the aircraft 30 also includes a transmission interface 51 so as to be able to transmit this first set of operating data J1 to the ground station 34. The transmission interface 51 is thus connected at least to the first memory 32 directly or indirectly.

The analysis unit 52 of the ground station 34 then makes it possible to analyze the first set of operating data J1 and determines, as a function of this preliminary analysis, a second variable V2 distinct from the first variable V1.

In this way, the analysis unit 52 can subsequently carry out an additional analysis of the variations over time of the second variable V2 to confirm and / or specify the cause (s) of malfunction of the equipment 31.

To do this, the computer 33 is then reconfigured so as to record in the first memory 32 the variations over time of the second variable V2. Thus, the first memory 32 then makes it possible to store, in a second step, a second set of operating data J2 of the aircraft 30 over a second time interval t2. As before, such a second set of operating data J2 is then representative of the variations over time of the second variable V2.

According to this first variant, the system 50 includes a second memory 36 for storing a table of values representative of an external configuration 35 of the computer 33.

Such a second memory 36 is distinct from the first memory 32 and can consist of a non-volatile memory arranged in the computer 33. The external table of values contained in this second memory 36 can then be modified independently of the algorithm implemented by the calculator 33.

The transmission interface 51 is thus connected directly or indirectly to the second memory 36 to allow the ground station to modify the external configuration 35 of the computer 33.

Finally, the transmission interface 51 also makes it possible to transmit the second set of operating data J2 from the first memory 32 to the ground station 34. The analysis unit 52 then makes it possible to analyze this second set of operating data J2 so as to confirm and / or specify the cause (s) of equipment malfunction 31.

In addition, the analysis unit can comprise for example one or more computer (s), one (or more) processor (s), an integrated circuit, a programmable system, a logic circuit, these examples not limiting the scope given to the expression "unit of analysis".

According to the second variant of the system 60 illustrated in FIG. 2, the aircraft 40 can also include a computer 43 connected to a second external memory 46, 46 ’. For example, such a second memory 46 ′ can also be of the removable type and consist in particular of a hard disk, a memory card or a USB key capable of cooperating with a complementary connection member, not shown.

Once the aircraft 40 on the ground; the second memory 46, 46 'can in particular be read and the data it contains modified for example by using the transmission interface 51 or even directly by disconnecting this second removable memory 46' from its complementary connection member and by connecting it with ground station 34.

As already mentioned, and as shown in FIGS. 3 and 4, the invention also relates to a method 10, 20 allowing the recording and analysis of operating data of the aircraft 30, 40 to identify at least one cause of equipment malfunction 31.

Such a method 10, 20 thus comprises a first recording step 11, 21 making it possible to record in the first memory 32 the first set of operating data J1 of the aircraft 30, 40 over the first time interval t1 Furthermore , such a first recording step 11, 21 is implemented by the computer 33, 43 initially configured to record this first set of operating data J1 representative of the first variable V1.

The method 10, 20 then comprises a first transmission step 12, 22 making it possible to transmit the first set of operating data J1 from the first memory 32 to the ground station 34.

For example and according to the first embodiment of the method 10 as shown in FIG. 3, such a first transmission step 12 can be carried out on the ground after a mission from the aircraft 30, 40.

Furthermore, according to a second embodiment of the method 20 as shown in FIG. 4, the first transmission step 22 can also be carried out in flight during a mission of the aircraft 30, 40.

The method 10, 20 then comprises a first analysis step 13, 23 making it possible to analyze the first set of operating data J1. Such a first analysis step 13, 23 is then implemented by the analysis unit 52 in the ground station 34.

Once this first analysis step 13, 23 has finished, the method 10, 20 includes a definition step 14, 24 making it possible to define the second variable V2 whose analysis of variations over time will subsequently make it possible to confirm and / or to specify the cause (s) of malfunction of the aircraft equipment 31 30, 40.

The method 10, 20 then comprises a modification step 15, 25 making it possible to modify the external configuration 35 of the computer 33, 43 in order to allow the variations in time of the second variable V2 to be recorded in the first memory 32.

In addition, according to the first embodiment of the method 10 as shown in FIG. 3, the modification step 15 making it possible to modify the external configuration 35 of the computer 33, 43 can be implemented once during an initialization of the computer 33, 43. In this case, the computer 33, 43 implements at least once a configuration algorithm making it possible to read all or part of the values contained in the table of values.

According to the second embodiment of the method 20 as shown in FIG. 4, the modification step 25 making it possible to modify the external configuration 35 of the computer 33, 43 can also be implemented cyclically several times to allow recording in the first memory 32 the variations over time of the second variable V2.

The method 10, 20 then comprises a second recording step 16, 26 making it possible to record in the first memory 32 the second set of operating data J2 of the aircraft 30, 40 over the second time interval t2. Such a second recording step 16, 26 is thus implemented by the computer 33, 43 newly configured to store this second data set J2 in the first memory 32.

The method 10, 20 then comprises a second transmission step 17, 27 for transmitting the second set of operating data J2 from the first memory 32 to the ground station 34.

As before, according to the first embodiment of the method 10 as shown in FIG. 3, such a second transmission step 17 can be carried out on the ground after a mission from the aircraft 30, 40.

Furthermore, according to a second embodiment of the method 20 as shown in FIG. 4, the second transmission step 27 can also be carried out in flight during a mission of the aircraft 30, 40.

Finally, the method 10, 20 comprises a second analysis step 18, 28 making it possible to analyze the second set of operating data J2 so as to confirm and / or specify the (or the) cause (s) of the dysfunction of the equipment 31. This second analysis step 18, 28 is then implemented in the ground station 34 by the analysis unit 52.

Naturally, the present invention is subject to numerous variations as to its implementation. Although several embodiments have been described, it is understood that it is not conceivable to identify exhaustively all the possible modes. It is of course conceivable to replace a means described by an equivalent means without departing from the scope of the present invention.

Claims (14)

1. Method (10, 20) for recording and analyzing operating data of an aircraft (30, 40), said method (10, 20) making it possible to identify at least one cause of equipment malfunction (31) of said aircraft (30, 40) and comprising: A first recording step (11, 21) making it possible to record in a first memory (32) a first set of operating data (J1) of said aircraft (30, 40) over a first time interval (t1), said first set of operating data (J1) being representative of the variations over time of at least one first variable (V1), said first recording step (11, 21) being implemented by a computer (33, 43 ) configured to record said first set of operating data (J1) in said first memory (32), • a first transmission step (12, 22) to transmit said first set of operating data (J1) from said first memory ( 32) to at least one ground station (34), and • a first analysis step (13, 23) making it possible to analyze said first set of operating data (J1), said first analysis step (13, 23 ) being implemented in said at least ins a ground station (34), characterized in that said method (10, 20) comprises at least: • a definition step (14, 24) to define at least a second variable (V2) distinct from said at least one first variable (V1), an analysis of the variations over time of said at least one second variable (V2) allowing to confirm and / or specify said at least one cause of malfunction of said equipment (31) of said aircraft (30, 40), • a modification step (15, 25) making it possible to modify an external configuration (35) of said computer (33 , 43) to allow recording in said first memory (32) said variations in time of said at least one second variable (V2), • a second recording step (16, 26) making it possible to record in said first memory (32) a second set of operating data (J2) of said aircraft (30, 40) over a second time interval (t2), said second set of operating data (J2) being representative of said variations in time of said at least one second variable (V2), said second recording step (16, 26) being implemented by said computer (33, 43) newly configured to store said second data set (J2) in said first memory (32 ), • a second transmission step (17, 27) for transmitting said second set of operating data (J2) from said first memory (32) to said at least one ground station (34), and • a second step of analysis (18, 28) for analyzing said second set of operating data (J2), said second analysis step (18, 28) being implemented in said at least one ground station (34). 2. Method according to claim 1, characterized in that said modification step (15, 25) making it possible to modify said external configuration (35) of said computer (33, 43) consists in modifying all or part of an external table of values stored in a second memory (36, 46, 46 '), said second memory (36, 46, 46') being distinct from said first memory (32). 3. Method according to claim 2, characterized in that said modification step (15) making it possible to modify said external configuration (35) of said computer (33, 43) is implemented once during an initialization of said computer (33 , 43), said computer (33, 43) implementing at least once a configuration algorithm making it possible to read all or part of the values contained in said table of values. 4. Method according to any one of claims 1 to 3, characterized in that said modification step (25) making it possible to modify said external configuration (35) of said computer (33, 43) is implemented cyclically several times to allow recording in said first memory (32) said variations in time of said at least one second variable (V2) distinct from the at least one first variable (V1). 5. Method according to any one of claims 2 to 4, characterized in that said second memory (36) is a non-volatile memory arranged in said computer (33). 6. Method according to any one of claims 2 to 4, characterized in that said second memory (46, 46 ’) is separated from said computer (43). 7. Method according to claim 6, characterized in that said second memory (46 ’) is of removable type. 8. Method according to any one of claims 1 to 7, characterized in that at least one of said first transmission step (12) and second transmission step (17) is carried out on the ground after a mission of said aircraft (30 , 40). 9. Method according to any one of claims 1 to 7, characterized in that at least one of said first transmission step (22) and second transmission step (27) is carried out in flight during a mission of said aircraft (30, 40). 10. System (50, 60) for recording and analyzing aircraft operating data (30, 40), said system (50, 60) making it possible to identify at least one cause of equipment malfunction (31) of said aircraft (30, 40) and comprising: A first memory (32) capable of storing a first set of operating data (J1) of said aircraft (30, 40) over a first time interval (t1), said first set of operating data (J1) being representative of variations over time of at least a first variable (V1), • a computer (33, 43) configured to at least store said first set of operating data (J1) in said first memory (32), • an interface for transmission (51) for transmitting said first set of operating data (J1) from said first memory (32) to at least one ground station (34), and • an analysis unit (52) for analyzing said first set operating data (J1), said analysis unit (52) being included in said at least one ground station (34), characterized in that said system (50, 60) makes it possible to define at least one second variable (V2 ) distinct from said at least one first var iable (V1), an analysis of the variations over time of said at least one second variable (V2) making it possible to confirm and / or to specify said at least one cause of malfunction of said equipment (31) of said aircraft (30, 40), said computer (33, 43) being reconfigured to record in said first memory (32) said variations in time of said at least one second variable (V2), said first memory (32) being capable of storing a second data set of operation (J2) of said aircraft (30, 40) over a second time interval (t2), said second set of operating data (J2) being representative of said variations in time of said at least one second variable (V2), said transmission interface (51) transmitting said second set of operating data (J2) from said first memory (32) to said at least one ground station (34), and said analysis unit (52) for analyzing led it second set of operating data (J2). 11. System (50, 60) according to claim 10, characterized in that said system (50, 60) comprises a second memory (36, 46, 46 ') capable of storing a table of values representative of an external configuration ( 35) of said computer (33, 43), said second memory (36, 46, 46 ') being distinct from said first memory (32). 12. System (50) according to any one of claims 10 to 11, characterized in that said second memory (36) is a non-volatile memory arranged in said computer (33). 13. System (60) according to any one of claims 10 to 11, characterized in that said second memory (46, 46 ’) is separated from said computer (43). 5 14. System (60) according to claim 13, characterized in that said second memory (46 ’) is of removable type.