METHOD AND SYSTEM FOR MONITORING THE PERFORMANCE OF AN ELECTROMECHANICAL SWITCH INCLUDED IN A POWER DISTRIBUTION SYSTEM WITHIN AN AIRCRAFT

Abstract

A method is proposed for monitoring the performance of a given electromechanical switch among a plurality of electromechanical switches, of the contactor or relay type, included in an electrical power distribution system within an aircraft. The method comprises: detecting a change of state of the given electromechanical switch; verifying, for each linked electromechanical switch in a predetermined group, whether it has also undergone a change of state; considering the change of state of the given electromechanical switch to be normal if at least one linked electromechanical switch in the group has also undergone a change of state, or abnormal otherwise; and in the event of an abnormal change of state, triggering an alert.Thus, it is possible to monitor the performance of a given electromechanical switch in a simple and reliable manner, allowing for the anticipation of potential operational interruptions by triggering maintenance alerts well in advance. Figure to be published with the abbreviation: Fig. 3.

Description

Title of the invention: METHOD AND SYSTEM PERFORMANCE MONITORING OF AN ELECTROMECHANICAL SWITCH INCLUDED IN A POWER DISTRIBUTION SYSTEM WITHIN AN AIRCRAFT technical field

[0001] The field of the invention is that of health monitoring and aircraft maintenance.

[0002] More specifically, the present invention relates to a method for monitoring the performance of an electromechanical switch, of the contactor or relay type, included in an electrical power distribution system within an aircraft.

[0003] The present invention also relates to: a monitoring system adapted to the implementation of such a monitoring method; a computer program product and a storage medium enabling the implementation of such a monitoring method; and a maintenance method based on such a monitoring method. STATE OF PRIOR ART

[0004] Aircraft are subjected to extreme conditions when they are in the air, particularly in terms of variations in temperature, pressure and speed. The performance of their components must be regularly checked to ensure their proper functioning.

[0005] Preventive or predictive maintenance consists of carrying out checks and repairs before a breakdown occurs.

[0006] In the field of aeronautics, maintenance makes it possible in particular to improve the availability and performance of an aircraft by avoiding its immobilization on the ground (AOG, for "Aircraft On Ground" in English), and to reduce maintenance costs by making it possible to identify in advance maintenance operations based on the actual performance of the aircraft.

[0007] Monitoring the aircraft's health status for maintenance purposes includes collecting technical data from the moment the aircraft is powered on, then during flight and until it is shut down. The data thus collected is used in particular to calculate the various indicators on which maintenance is based, and therefore the scheduling of maintenance operations.

[0008] The use of data can take place during the flight (this is referred to as in-flight health monitoring) and / or after The flight (for example, if the volume of data to be processed requires greater computing resources). Calculations using the collected data can therefore be performed in the aircraft and / or in one or more ground-based devices. In the latter case, the ground-based devices (computers) receive the data collected in the aircraft, either in real time or with a delay.

[0009] Observing the condition of an aircraft over several flights allows ground personnel to make decisions and plan maintenance operations in advance, thus saving valuable execution time. Ground personnel can then make appropriate decisions based on criticality, logistics, and upcoming maintenance checks, and prepare repairs and replacements in advance.

[0010] As part of this maintenance, there is a particular need to monitor the performance of electromechanical switches, such as contactors or relays, included in an aircraft's electrical power distribution system. To this end, a reliable and easy-to-implement solution is required, one that allows for the anticipation of potential operational interruptions by triggering maintenance alerts sufficiently in advance. Description of the invention

[0011] A method for monitoring the performance of a given electromechanical switch among a plurality of electromechanical switches, of the contactor or relay type, included in an electrical power distribution system within an aircraft, the method being implemented by a monitoring system in the form of electronic circuitry, the method comprising:

[0012] a) detect a change of state of the given electromechanical switch, from an "open" state to a "closed" state or vice versa, based on collected data providing information on the state of the given electromechanical switch;

[0013] b) verify, for each linked electromechanical switch belonging to a predetermined group comprising one or more electromechanical switches that are linked to the given electromechanical switch and are part of the plurality of electromechanical switches, whether said linked electromechanical switch has also undergone a change of state, from an "open" state to a "closed" state or vice versa, based on collected data providing information on the state of the linked electromechanical switch, each linked electromechanical switch in the group being configured, by a control and reconfiguration logic, to change state if the given electromechanical switch changes state as part of a particular reconfiguration of the electrical power distribution system which is function of the availability of electrical sources in the electrical power distribution system;

[0014] c) consider the change of state of the given electromechanical switch to be normal, if at least one linked electromechanical switch in the group has also undergone a change of state, or abnormal, if no linked electromechanical switch in the group has undergone a change of state; and

[0015] d) in the event of an abnormal change of state of the given electromechanical switch, trigger an alert relating to the performance of the given electromechanical switch.

[0016] Thus, it is possible to monitor the performance of a given electromechanical switch, of the contactor or relay type, among a plurality of electromechanical switches included in an electrical power distribution system within an aircraft, thanks to a solution which is reliable and simple to implement, and which makes it possible to anticipate possible interruptions of operation by raising maintenance alerts sufficiently in advance.

[0017] According to a particular embodiment, the grouping comprises:

[0018] - at least one first linked electromechanical switch which is configured, by the control and reconfiguration logic, to change state if the given electromechanical switch changes state within the framework of a first particular reconfiguration of the electrical power distribution system which is a function of a first context of availability of the electrical sources of the electrical power distribution system; and

[0019] - at least one second linked electromechanical switch which is configured, by the control and reconfiguration logic, to change state if the given electromechanical switch changes state within the framework of a second particular reconfiguration of the electrical power distribution system which is a function of a second context of availability of the electrical sources of the electrical power distribution system.

[0020] According to a particular embodiment, operations a), b), and c) are executed N times in parallel, N>1, with data collected each time by a separate recorder. Furthermore, the alert regarding the performance of the given electromechanical switch is triggered if, after at least one of the N executions of steps a), b), and c), the change of state of the given electromechanical switch is considered abnormal.

[0021] Thus, it is possible to take into account an abnormal change of state of the given electromechanical switch, even if it is detected from the data collected by only one of the N recorders.

[0022] According to a particular embodiment, for at least a predetermined time period of data collection providing information on the state of the given electromechanical switch, operations b) and c) are executed after each detection of a change of state of the given electromechanical switch. Furthermore, the alert regarding the performance of the given electromechanical switch is triggered if the number of abnormal state changes due to the given electromechanical switch, over at least one predetermined time period of data collection, is greater than or equal to a predetermined threshold.

[0023] Thus, it is possible to work on data collected during one or more time periods of collection, and the choice of the threshold makes it possible to adapt the reactivity of triggering an alert.

[0024] According to a particular embodiment, each predetermined time period of collection is a part of a time range of an aircraft flight defined according to an aircraft flight phase parameter.

[0025] Thus, it is possible to retain the data collected during one or more flights of the aircraft, which are of the most interest in deciding whether an alert relating to the performance of the given electromechanical switch should be triggered.

[0026] According to a particular embodiment, the verification of a change of state, for each linked electromechanical switch belonging to the group, is limited to a verification time window, having a predetermined duration and surrounding an instant of detection of a change of state of the given electromechanical switch.

[0027] Thus, the decision taken regarding a possible abnormal change of state of the given electromechanical switch is improved.

[0028] A computer program product is also proposed, comprising instructions leading to the execution, by a processor, of the monitoring process mentioned above according to any of its embodiments, when said instructions are executed by the processor.

[0029] A storage medium is also proposed, storing such instructions.

[0030] A system for monitoring the performance of a switch is also proposed. electromechanical given among a plurality of electromechanical switches, of contactor or relay type, included in an electrical power distribution system within an aircraft, the monitoring system comprising electronic circuitry configured to implement the process mentioned above according to any one of its embodiments.

[0031] A method for maintaining a given electromechanical switch among a plurality of electromechanical switches, of the contactor or relay type, included in an electrical power distribution system within an aircraft, the method comprising:

[0032] - to execute the process mentioned above according to any one of its modes of implementation, to monitor the performance of the given electromechanical switch; and

[0033] - in the event of a triggering alert relating to the performance of the switch given electromechanical switch, perform at least one maintenance operation on the given electromechanical switch. Brief description of the drawings

[0034] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of at least one exemplary embodiment, said description being made in relation to the accompanying drawings, among which:

[0035] [Fig-1] schematically illustrates, in side view, an aircraft equipped with a system of monitoring the performance of an electromechanical switch, such as a contactor or relay, included in an electrical power distribution system within this aircraft;

[0036] [Fig.2] schematically illustrates an example of the hardware architecture of the system of monitoring the performance of an electromechanical switch;

[0037] [Fig.3] schematically illustrates a first example of an algorithm for monitoring the performance of an electromechanical switch;

[0038] [Fig.4] schematically illustrates an example of an energy distribution system electrical system comprising a plurality of electromechanical switches whose performance is to be monitored;

[0039] [Fig.5] schematically illustrates three examples of checking a possible change of state of a linked electromechanical switch, following a change of state of a given electromechanical switch;

[0040] [Fig.6] schematically illustrates a second example of an algorithm for monitoring the performance of an electromechanical switch;

[0041] [Fig.7] schematically illustrates a third example of a monitoring algorithm of the performance of an electromechanical switch; and

[0042] [Fig.8] schematically illustrates an example of a maintenance algorithm for an electromechanical switch included in an electrical power distribution system within this aircraft.

[0043] DETAILED DESCRIPTION OF EMBODIMENT METHODS

[0044] Fig. 1 schematically illustrates, in side view, an aircraft 100 equipped with an electrical power distribution system 101 and a performance monitoring system 200 for electromechanical switches, of the contactor or relay type, included in the electrical power distribution system 101.

[0045] The aircraft's electrical power distribution system 101 is, for example, contained within an electrical power distribution center (EPDC). It is typically responsible for distributing electrical power throughout the aircraft, including the engines, flight control systems, navigation equipment, and passenger systems. System 101 is, for example, divided into two main sections: the AC power distribution system and the DC power distribution system.The AC power distribution system is responsible for distributing alternating current (AC) power to the aircraft's various systems and equipment. This AC power is generated by different electrical sources, such as the aircraft's auxiliary power unit (APU), ground power unit (GPU), or generator (IGD, IDG, or VFG) when the aircraft's associated engine is running. The direct current (DC) power distribution system is responsible for distributing direct current produced by different electrical sources, such as batteries or transformer rectifier units (TRUs), to the aircraft's various systems and equipment.

[0046] The electrical power distribution system 101 comprises a plurality of electromechanical switches, of the contactor or relay type, each configured to switch from an "open" state to a "closed" state or vice versa, depending on a control signal. The electrical power distribution system 101 includes control and reconfiguration logic, generating the control signals for the various electromechanical switches. In normal operation, the electromechanical switches do not change state, except in the event of a desired reconfiguration of the electrical power distribution system. Each reconfiguration of the electrical power distribution system depends on the availability of the system's power sources (APU, GPU, IDG, VFG, batteries, TRU, etc.).

[0047] For example, the electrical power distribution system illustrated in [Fig.4] includes GLC1 and GLC2 contactors (generator line contactors, referenced 401 and 402) and BTC1 and BTC2 contactors (bus transfer contactors, referenced 403 and 404) which are controlled so that AC BUS 1 (referenced 405) is supplied by the GEN 1 power source (referenced 406) and AC BUS 2 (referenced 407) by the GEN 2 power source (referenced 408).

[0048] An electromechanical switch generally consists of a coil, contacts, and a protective housing. When the coil is energized, a field A magnetic field is created which brings the contacts closer together or further apart, thus closing or opening the circuit according to the design of the electromechanical switch, which allows control of the current flowing to a connected electrical load.

[0049] Two main types of electromechanical switch are known: contactors, designed to regulate the flow of electric current in high-power applications, and relays, designed to regulate the flow of electric current in low- to medium-power applications. In other words, contactors and relays share similar construction principles, and contactors are specifically optimized for high-power applications through design choices (e.g., larger contacts, higher-quality materials, more effective arc suppression, and a more robust mechanical construction).

[0050] An electromechanical switch can experience various failures, for example, due to a coil defect, causing an interruption of operation that may be temporary (for example, lasting a few milliseconds or a few seconds; this is sometimes referred to as a "micro-interruption," "micro-break," or "micro-switch") or permanent. Such an interruption of operation results in an unwanted (abnormal) change of state of the electromechanical switch, from an "open" state to a "closed" state or vice versa. In the case of a micro-interruption, there is also a second unwanted change of state, before returning to the initial correct state.

[0051] As detailed below, the 200 system for monitoring the performance of electromechanical switches, such as contactors or relays, can trigger an alert (for example, displaying information and / or sending a message to a maintenance service) if a triggering condition is met. Furthermore, as also detailed below, triggering an alert for a given electromechanical switch can be followed by at least one maintenance operation on that given electromechanical switch (for example, repairing or replacing it).

[0052] In a particular implementation, the electromechanical switch performance monitoring system 200 is an embedded electronic device. For example, it is part of the electronic circuitry of the aircraft avionics 100. Preferably, it is integrated into an aircraft computer 100.

[0053] In one variant, the electromechanical switch performance monitoring system 200 is not carried on board the aircraft 100 but is present on the ground.

[0054] In another embodiment, the electromechanical switch performance monitoring system 200 comprises a first part that is carried on board the aircraft 100 and a second part that is located on the ground. Thus, the calculations and The triggering of alerts can be distributed between the two parts of the 101 system.

[0055] In another variant, at least one 200 system for monitoring the performance of electromechanical switches is carried on board the aircraft and at least one 200 system for monitoring the performance of electromechanical switches is installed on the ground.

[0056] Fig. 2 schematically illustrates an example of the hardware architecture of the electromechanical switch performance monitoring system 200, which then comprises, connected by a communication bus 210: a processor or CPU (Central Processing Unit) 201; a RAM (Random Access Memory) 202; a ROM (Read Only Memory) 203, for example a Flash memory; a data storage device, such as a HDD (Hard Disk Drive), or a storage media reader, such as an SD (Secure Digital) card reader 204; at least one communication interface 205 allowing the electromechanical switch performance monitoring system 200 to interact in the avionics of the aircraft 100.

[0057] The processor 201 is capable of executing instructions loaded into RAM 202 from ROM 203, external memory (not shown), a storage medium such as an SD card, or a communication network (not shown). When the electromechanical switch performance monitoring system 200 is powered on, the processor 201 is capable of reading instructions from RAM 202 and executing them. These instructions form a computer program causing the processor 201 to implement the behaviors, steps, and algorithm described herein.

[0058] All or part of the behaviors, steps, and algorithm described herein can thus be implemented in software form by executing a set of instructions by a programmable machine, such as a DSP (Digital Signal Processor) or a microcontroller, or be implemented in hardware form by a dedicated machine or component (chip) or a dedicated set of components (chipset), such as an FPGA (Field-Programmable Gate Array) or an ASIC (Application-Specific Integrated Circuit). Generally speaking, the 200 electromechanical switch performance monitoring system comprises electronic circuitry arranged and configured to implement the behaviors, steps, and algorithms described herein.

[0059] Fig. 3 schematically illustrates a first example of an algorithm for monitoring the performance of an electromechanical switch, of the contactor or relay type, included in the electrical power distribution system 101 within an aircraft. The process is implemented by the monitoring system 200 discussed above in relation to [Fig. 1] and 2.

[0060] In a step 301, the monitoring system 200 detects a change of state of a given electromechanical switch, from an "open" state to a "closed" state or vice versa, according to collected data providing information on the state of the given electromechanical switch.

[0061] In a step 302, the monitoring system 200 checks, for each linked electromechanical switch belonging to a predetermined grouping (see definition below), whether the linked electromechanical switch has also undergone a change of state, from an "open" state to a "closed" state or vice versa, based on collected data providing information on the state of the linked electromechanical switch.

[0062] The predetermined grouping comprises one or more electromechanical switches that are linked to the given electromechanical switch and form part of the plurality of electromechanical switches. More precisely, each linked electromechanical switch in the grouping is configured, by the control and reconfiguration logic (already discussed above), to change state if the given electromechanical switch changes state within the framework of a particular reconfiguration of the electrical power distribution system that is a function of the availability of the electrical sources (APU, GPU, IDG, VFG, batteries, TRU...).

[0063] In the case where the control and reconfiguration logic manages several possible reconfigurations of the electrical power distribution system, the grouping includes:

[0064] - at least one first linked electromechanical switch which is configured, by the control and reconfiguration logic, to change state if the given electromechanical switch changes state within the framework of a first particular reconfiguration of the electrical power distribution system which is a function of a first context of availability of the electrical sources (for example, with the electrical power distribution system of [Fig. 4], in the event of loss of the electrical source GEN 1 while the electrical sources GEN 1 and GEN 2 were both switched on and in use, the reconfiguration will consist of using the electrical source GEN 2 but no longer the electrical source GEN 1); and

[0065] - at least one second linked electromechanical switch which is configured, by The control and reconfiguration logic, to change state if the given electromechanical switch changes state within the framework of a second particular reconfiguration of the electrical power distribution system which is a function of a second context of availability of electrical sources (for example, still with the electrical power distribution system of [Fig. 4], in the event of loss of the GEN 1 electrical source while the GEN 1 and APU electrical sources were With both powered on and in use, the reconfiguration will consist of switching to using the APU power source but no longer the GEN 1 power source.

[0066] It will be noted that, if the given electromechanical switch changes state in the context of the first particular reconfiguration of the electrical power distribution system, the at least one first linked electromechanical switch must normally also change state, but not the at least one second linked electromechanical switch.

[0067] Taking up again the example of the electrical power distribution system illustrated in [Fig.4]: for the GLC1 contactor (referenced 401), the associated group comprises a single linked contactor, namely the BTC1 contactor (referenced 403); and for the GLC2 contactor (referenced 402), the associated group comprises a single linked contactor, namely the BTC2 contactor (referenced 404).

[0068] If at least one linked electromechanical switch in the group has also undergone a change of state (response "yes" in test step 303), the monitoring system 200 executes a step 304, in which it considers that the change of state of the given electromechanical switch is normal, before proceeding to an end step 307. Indeed, if at least one linked electromechanical switch in the group has also undergone a change of state, it can be deduced that the given electromechanical switch is not defective because if it were defective there is a near-zero probability that an electromechanical switch in the group (the one that also changes state) would also be defective at the same time.It should be noted that it is sufficient for at least one of the electromechanical switches in the group to also change state to trigger the decision to change the normal state for the given electromechanical switch, because the current configuration of the power distribution system (and therefore the current state of all the electromechanical switches decided by the control and reconfiguration logic) is a function of a current context of availability of electrical sources.

[0069] Otherwise (response "no" in test step 303), i.e. if no linked electromechanical switch in the group has undergone a change of state, the monitoring system 200 executes a step 305 in which it considers the change of state of the given electromechanical switch to be abnormal, then a step 306 in which it triggers an alert relating to the performance of the given electromechanical switch, before proceeding to the end step 307.

[0070] In a particular implementation, the verification of a change of state (in step 302), for each linked electromechanical switch belonging to the group, is limited to a verification time window, having a predetermined duration and surrounding an instant of detection of a change of state of the given electromechanical switch.

[0071] This particular implementation is illustrated in [Fig. 5]. It is assumed that the electromechanical switch whose performance is being monitored is contactor GLC1 (referenced 401 in [Fig. 4]). Status line 501 represents the state of this contactor GLC1, with in this example a change of state (from the "open" state to the "closed" state) at a time referenced 502 (the time of detection of the change of state). For each linked electromechanical switch (i.e., belonging to the group associated with contactor GLC1), the verification of a change of state is limited to the verification time window referenced 503. As mentioned above, it is assumed that, for contactor GLC1, the associated group comprises only one linked contactor, namely contactor BTC1 (referenced 403 in [Fig. 4]). Three examples of checking for a possible change of state of contactor BTC1, following a change of state of contactor GLC1, are illustrated in [Fig.5]: - first example: the status line 504 represents the state of the contactor BTC1, with a change of state (from the "open" state to the "closed" state) at a referenced instant 505 which is included in the verification time window 503; therefore, the monitoring system 200 considers that the change of state of the contactor GLC1 is normal; - second example: the status line 506 represents the state of the contactor BTC1, with a change of state (from the "closed" state to the "open" state) at a referenced instant 507 which is included in the verification time window 503; therefore, the monitoring system 200 considers that the change of state of the contactor GLC1 is normal; - third example: the status line 508 represents the state of contactor BTC1 (the only linked contactor in the group), with no change of state in the verification time window 503; therefore, the monitoring system 200 considers the change of state of contactor GLC1 to be abnormal.

[0072] Fig. 6 schematically illustrates a second example of an algorithm for monitoring the performance of an electromechanical switch.

[0073] Steps 301 to 305 are identical to those of the first example algorithm in [Fig. 3]. This second example algorithm differs from the first in that, if the response to test step 303 is "no" (i.e., if no linked electromechanical switch in the group has undergone a change of state), and after execution of step 305 (in which it considers the change of state of the given electromechanical switch to be abnormal), the monitoring system 200 executes a step 601 in which it increments an abnormal change of state counter C, and then a step 602 in which it checks if a time period of data collection (of the data providing information on the state of electromechanical switches) has been fully analyzed.

[0074] In one embodiment, the predetermined time period of collection is a part of a time range of an aircraft flight, defined according to a flight phase parameter of the aircraft. For example, phases 2 to 9 in the case of a flight divided into ten phases (1: Takeoff Roll; 2: Takeoff; 3: Initial Climb; 4: On-Course Climb; 5: Cruise Climb; 6: Cruise; 7: Initial Descent; 8: Approach Descent; 9: Final Descent; 10: Landing).

[0075] In one variant, several flights of the aircraft are considered and the predetermined time period of collection is a concatenation of the time periods of collection (for example phases 2 to 9) of each flight.

[0076] If the time period of collection has not been fully analyzed, the monitoring system 200 returns to step 301 (in order to detect a new change of state of the given electromechanical switch, whose performance is being monitored).

[0077] If the collection time period has been fully analyzed, the monitoring system 200 executes a step 603 in which it checks whether the value of the counter C is greater than or equal to a predetermined threshold S. If the value of the counter C is greater than or equal to the predetermined threshold S, the monitoring system 200 executes a step 604 in which it triggers an alert regarding the performance of the given electromechanical switch, before proceeding to the end step 605. If the value of the counter C is less than the predetermined threshold S, the monitoring system 200 proceeds directly to the end step 605. In other words, the alert regarding the performance of the given electromechanical switch is triggered (step 604) if the number C of abnormal state changes of the given electromechanical switch, over the (at least one) predetermined collection time period, is greater than or equal to the predetermined threshold S. In one embodiment, S=1.Other embodiments are possible, with values ​​of S greater than 1.

[0078] Fig. 7 schematically illustrates a third example of an algorithm for monitoring the performance of an electromechanical switch.

[0079] We refer to the group of steps comprising steps 301 to 305, 601, and 602 of [Fig. 6] as A. We assume that the group of steps A is executed with data collected by a first recorder (for example, a first SDAC, for "System Data Acquisition Concentrator"). The group of steps A (and more specifically step 602 of this group) is followed by a step 603 in which the monitoring system 200 checks whether the value of the counter C is greater than or equal to a predetermined threshold S.

[0080] It is further assumed that a group of steps A', comprising the same steps as group A, is executed with data collected by a second recorder (for example, a second SD AC). By analogy with the counter C used in group of steps A, the counter used in group of steps A' is denoted C'. Group of steps A' (and more specifically step 602 of this group) is followed by a step 603' in which the monitoring system 200 checks whether the value of counter C' is greater than or equal to a predetermined threshold S'.

[0081] Following steps 603 and 603' (which are performed in parallel, as are groups of steps A and A'), the monitoring system 200 executes a step 701 in which it checks whether at least one of the tests in steps 603 and 603' is positive. If at least one of the tests in steps 603 and 603' is positive, the monitoring system 200 executes a step 702 in which it triggers an alert regarding the performance of the given electromechanical switch, before proceeding to the final step 703. Otherwise, the monitoring system 200 proceeds directly to the final step 703.

[0082] The embodiment of [Fig.7] can easily be generalized to N groups of steps A, A' etc. (with N>1), each followed by a step 603, 603' etc., then the common steps 701 and 702.

[0083] Fig. 8 schematically illustrates an example of a maintenance algorithm for an electromechanical switch included in an electrical power distribution system within this aircraft.

[0084] In a step 801, the monitoring system 200 executes an algorithm for monitoring the performance of an electromechanical switch, in one of the embodiments described above (see the description of [Fig.3], 6 and 7).

[0085] If an alert was triggered at the end of step 801 (result "yes" in test step 802), at least one maintenance operation is carried out on the given electromechanical switch (step 803).

Claims

Demands

1. A method for monitoring the performance of a given electromechanical switch (401) among a plurality of electromechanical switches, of the contactor or relay type, included in an electrical power distribution system (101) within an aircraft (100), the method being implemented by a monitoring system (200) in the form of electronic circuitry, the method comprising: a) detecting (301) a change of state of the given electromechanical switch (401), from an "open" state to a "closed" state or vice versa, based on collected data providing information on the state of the given electromechanical switch;(b) verify (302), for each linked electromechanical switch (402) belonging to a predetermined group comprising one or more electromechanical switches which are linked to the given electromechanical switch and are part of the plurality of electromechanical switches, whether said linked electromechanical switch has also undergone a change of state, from an 'open' state to a 'closed' state or vice versa, based on collected data informing about the state of the linked electromechanical switch, each linked electromechanical switch in the group being configured, by a control and reconfiguration logic, to change state if the given electromechanical switch changes state as part of a particular reconfiguration of the electrical power distribution system which is a function of the availability of electrical sources of the electrical power distribution system;(c) consider the change of state of the given electromechanical switch to be normal (304), if at least one linked electromechanical switch in the group has also undergone a change of state, or abnormal (305), if no linked electromechanical switch in the group has undergone a change of state; and (d) in the event of an abnormal change of state of the given electromechanical switch, trigger (306) an alert relating to the performance of the given electromechanical switch.

2. A method according to claim 1, wherein the grouping comprises: - at least one first linked electromechanical switch which is configured, by the control and reconfiguration logic, to change state if the given electromechanical switch changes state within the framework of a first particular reconfiguration of the electrical power distribution system which is a function of a first context of availability of the electrical sources of the electrical power distribution system; and - at least one second linked electromechanical switch which is configured, by the control and reconfiguration logic, to change state if the given electromechanical switch changes state within the framework of a second particular reconfiguration of the electrical power distribution system which is a function of a second context of availability of the electrical sources of the electrical power distribution system.

3. A method according to any one of claims 1 and 2, wherein operations a), b) and c) are performed N times in parallel (A, A'), N>1, with each time data collected by a separate recorder, and wherein the alert relating to the performance of the given electromechanical switch is triggered (702) if, at the end of at least one of the N executions of steps a), b) and c), the change of state of the given electromechanical switch is considered abnormal.

4. A method according to any one of claims 1 to 3, wherein, for at least a predetermined time period of data collection informing about the state of the given electromechanical switch, operations b) and c) are performed (302 to 305) after each detection (301) of a change of state of the given electromechanical switch, and wherein the alert relating to the performance of the given electromechanical switch is triggered (604) if the number of abnormal changes of state of the given electromechanical switch, over the at least a predetermined time period of collection, is greater than or equal to a predetermined threshold (603).

5. A method according to claim 4, wherein each predetermined time period of collection is a part of a time range of an aircraft flight defined according to an aircraft flight phase parameter.

6. A method according to any one of claims 1 to 5, wherein the verification (302) of a change of state, for each linked electromechanical switch belonging to the group, is limited to a verification time window (503), having a predetermined duration and surrounding a detection instant of a change of state (502) of the given electromechanical switch.

7. Product computer program, comprising instructions causing a processor (201) to execute the method according to any one of claims 1 to 6, when said instructions are executed by the processor.

8. Storage medium (203), storing a computer program comprising instructions causing a processor (201) to execute the method according to any one of claims 1 to 6, when said instructions are read and executed by the processor.

9. System (200) for monitoring the performance of a given electromechanical switch (401) among a plurality of electromechanical switches, of the contactor or relay type, included in an electrical power distribution system (101) within an aircraft (100), the monitoring system comprising electronic circuitry configured to implement: a) detect (301) a change of state of the given electromechanical switch (401), from an "open" state to a "closed" state or vice versa, based on collected data providing information on the state of the given electromechanical switch;(b) verify (302), for each linked electromechanical switch (402) belonging to a predetermined grouping comprising one or more electromechanical switches which are linked to the given electromechanical switch and are part of the plurality of electromechanical switches, whether said linked electromechanical switch has also undergone a change of state, from an 'open' state to a 'closed' state or vice versa, based on collected data informing about the state of the linked electromechanical switch, each linked electromechanical switch in the grouping being configured, by a control and reconfiguration logic, to change state if the given electromechanical switch changes state as part of a particular reconfiguration of the power distribution system; electrical which is a function of the availability of electrical sources in the electrical power distribution system; (c) consider the change of state of the given electromechanical switch to be normal (304), if at least one linked electromechanical switch in the group has also undergone a change of state, or abnormal (305), if no linked electromechanical switch in the group has undergone a change of state; and (d) in the event of an abnormal change of state of the given electromechanical switch, trigger (306) an alert relating to the performance of the given electromechanical switch.

10. A method for maintaining a given electromechanical switch (401) among a plurality of electromechanical switches, of the contactor or relay type, included in an electrical power distribution system (101) within an aircraft (100), the method comprising: - performing (801) the method according to any one of claims 1 to 6, to monitor the performance of the given electromechanical switch; and - in the event of an alert (802) being triggered relating to the performance of the given electromechanical switch, performing (803) at least one maintenance operation on the given electromechanical switch.

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