• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    In an aircraft (1) comprising a maintenance computer (12), a flight information monitoring system (14) and a communication unit (16) for communication with a ground station (8), the device ( 10) comprises a processing unit (18) configured to: - memorize a trigger condition according to at least one maintenance information of the aircraft and / or at least one flight information of the aircraft; - Acquire first information from the maintenance computer and / or second information from the flight information monitoring system of the aircraft; - check whether the trigger condition is fulfilled, based on the first information and / or second information; and if the triggering condition is fulfilled, sending to the communication unit a set of information including maintenance information from the maintenance computer and flight information from the aircraft information monitoring system. flight of the aircraft.
    公开号:FR3032545A1
    申请号:FR1550966
    申请日:2015-02-06
    公开日:2016-08-12
    发明作者:Bigot Philippe Le；Samuel Grossiord；Christophe Figueras
    申请人:Airbus SAS；
    IPC主号:
    专利说明:

    [0001] 1 Device, system and method for assisting the maintenance of an aircraft. The invention relates to the field of aircraft maintenance and more particularly to the transmission of data between an aircraft and a ground station in order to facilitate maintenance operations of the aircraft. Aircraft, in particular modern transport aircraft, generally comprise a maintenance computer, for example of the CMS type ("Central Maintenance System" in English). This maintenance calculator is connected to a set of other on-board computers of the aircraft relating to different systems of the aircraft, such as, for example, flight control, engine control and monitoring, fuel management systems. etc. The maintenance computer receives from said other onboard computers information relating to failures of said systems, generally by means of BITE type signals ("Built In Test Equipment" in English). The maintenance computer thus centralises a set of information relating to the state of various systems of the aircraft, in particular relating to possible failures of said systems. During a flight of the aircraft, the maintenance computer records the failure information relating to the systems of the aircraft, and produces a maintenance report. This maintenance report comprises at least a significant part of said information relating to the state of said aircraft systems. The maintenance computer records the maintenance report at the end of the flight (usually called "Post Flight Report"). This maintenance report at the end of the flight is generally used by a maintenance operator to determine maintenance operations to be performed on the aircraft. During maintenance operations, the maintenance operator can also consult the current state of the aircraft systems, in particular their possible failures, by means of a screen interfaced to the maintenance computer. During the flight of the aircraft, a subset of the maintenance report being recorded may also be sent to a ground station, for example a maintenance center of the airline operating the aircraft. The sending of said subset is generally performed by means of a communication type ACARS ("Aircraft 3032545 2 Communications Addressing and Reporting System"). This sending is done cyclically, according to a predetermined time interval may depend on the aircraft model, usually every 15 minutes. This dispatch is limited to said subset of the maintenance report so as to limit the amount of data to be transmitted from the aircraft to the ground station, given the high cost of ACARS type communications. This subset corresponds to a predetermined selection of information from the information recorded in the maintenance report. This subset will be referred to as the maintenance report 10 in the following description. An aircraft generally also comprises a flight information monitoring system of the aircraft, for example of the ACMS ("Aircraft Condition Monitoring System") type. This flight information of the aircraft can correspond to data coming from sensors 15 or other equipment of the aircraft, for example current performance of the aircraft, information on the speed of the aircraft, information relating to the aircraft. operation of the engines of the aircraft (temperature ...), etc. An ACMS type system is configured to generate reports corresponding to a predetermined set of aircraft information. These reports may be defined by the aircraft manufacturer or by the airline operating the aircraft, by means of dedicated programming requiring installation by an operator on board the aircraft. The ACMS type system may further be configured to send these reports to a ground station, generally by means of ACARS type communication. In particular, these reports can be produced by the ACMS type system and sent to the ground station, when a condition on said information is verified, for example an anomaly on values of some of said information. However, in the event of a system failure of the aircraft, such reports only show the consequences of the failure on the flight information of the aircraft, but they do not always contain information allowing directly identify the origin of the failure. On the basis of an ACMS report, generally, an operator of the ground station can at most suspect a number of systems of the aircraft, but without having certainty on that of said systems which is actually down. To try to identify a system that has failed, the operator usually consults the last current maintenance report (s) sent by the CMS maintenance computer to the ground station. . However, as previously indicated, the current maintenance reports sent by the CMS maintenance computer contain only a subset of the maintenance report information. Therefore, they may not contain information that would have been useful to the operator to understand the origin of a failure. In addition, since the current maintenance reports sent by the maintenance computer CMS are sent cyclically, in particular every 15 minutes, the information contained in a current maintenance report sent by the maintenance computer CMS is not not synchronized with the information contained in the report sent by the ACMS type system. Since these different pieces of information correspond to different times, it can be difficult for the operator to correlate them to identify the origin of a failure. In addition, as already indicated, the usual interval between two successive transmissions of routine maintenance reports by the CMS maintenance computer to the ground station is relatively large, of the order of 15 minutes. Therefore, the data contained in such a report may be obsolete upon receipt by the ground station of a report from the ACMS type system. Moreover, even if the information contained in the following report makes it possible to identify the origin of the fault, the waiting of said next report by the maintenance operator may cause a significant delay in the analysis of the information by this operator. of maintenance. SUMMARY OF THE INVENTION The object of the present invention is in particular to provide a solution to these problems. It relates to a device for aiding maintenance of an aircraft, the device being embedded in the aircraft, this aircraft comprising: - a maintenance computer; A flight information monitoring system of the aircraft; and 3032545 4 - a communication unit configured to allow communications between the aircraft and a ground station. The device is remarkable in that it comprises: a first interface configured to communicate with the maintenance computer by means of a first communication link of the aircraft; a second interface configured to communicate with the flight information monitoring system of the aircraft by means of a second communication link of the aircraft; A third interface configured to communicate with the communication unit by means of a third communication link of the aircraft; and a processing unit configured to: store a triggering condition according to at least one maintenance information of the aircraft and / or at least one flight information of the aircraft; . acquiring first information from the maintenance computer, through the first interface and / or second information from the flight information monitoring system 20 of the aircraft, through the second interface; . checking whether the triggering condition is fulfilled, on the basis of the first information and / or the second information; and. if the trigger condition is fulfilled, send to the communication unit, through the third interface, a set of information including maintenance information from the maintenance computer and flight information from the aircraft from the system flight information monitoring system of the aircraft.
    [0002] Thus, the device makes it possible to monitor the occurrence of a trigger condition relating to the information from the maintenance computer and / or the information from the flight information monitoring system of the aircraft. This triggering condition can in particular correspond to the occurrence of a failure of a device 35 embedded in the aircraft, requiring intervention of a maintenance operator 3032545 5. When this triggering condition is fulfilled, the device sends said set of information to the communication unit, which transmits it to a ground station. A maintenance operator of a ground maintenance center can therefore take cognizance of said set of information at the earliest after the triggering of said condition. In addition, the set of information includes both maintenance information from the maintenance computer and flight information of the aircraft from the flight information monitoring system of the aircraft, these various information being 10 synchronous since collected substantially at the same time, after the triggering of said condition or when triggering said condition. This allows the maintenance operator to appreciate the state of the aircraft in order to understand the origin of a possible failure already identified, or even to prevent the occurrence of a possible failure by identifying a drift of settings. According to one embodiment, the processing unit is configured to send said set of information to the communication unit repetitively. In particular, the processing unit is configured to repeat sending said set of information to the communication unit: a predetermined number of times; - for a predetermined duration; or - until the processing unit receives an order to stop said sending, this stop command from the communication unit through the third interface. Repetitively sending the information set allows the maintenance operator to analyze the evolution of the different information over time and, therefore, to better appreciate the origin of a possible failure. already identified, or even to prevent the possible occurrence of a failure by identifying a drift of parameters. Advantageously, the processing unit is configured for: when the triggering condition is not fulfilled, recording said set of information in a memory of the device, in a repetitive manner; and 3032545 6 - when the trigger condition is fulfilled, send at least a part of the information stored in this memory, to the communication unit, through the third interface. This allows the set of information to be pre-recorded repeatedly before the condition is triggered, and then to send pre-recorded information to the ground station following the triggering of the condition. The maintenance operator thus has information corresponding to moments prior to the triggering of the condition, which can help him understand the occurrence and therefore the origin of a failure.
    [0003] Advantageously, the processing unit is configured to receive the trigger condition from the communication unit through the third interface. Thus, an operator of a maintenance center can define a trigger condition for which he wishes to obtain the set of information, then send this triggering condition to the aircraft via a communication link between the ground station and the communication unit of the aircraft. Thus, the maintenance operator can easily set the trip condition in the maintenance assistance device, without requiring the intervention of an operator on board the aircraft. The setting of the trigger condition can therefore be achieved easily and in a very short time, both for an isolated aircraft and for all the aircraft of an airline. According to a particular embodiment, the processing unit is configured to: - receive a sending command, from the communication unit, through the third interface; and - when receiving a send command, send the set of information to the communication unit, through the third interface. This allows an operator of a maintenance center to send a request to the aircraft for sending the set of information to the ground station, regardless of the activation of the trigger condition. The invention also relates to an aircraft maintenance support system, the system being embedded in the aircraft, this aircraft comprising a communication unit configured to allow communications between the aircraft and a vehicle. ground station. The maintenance assistance system is remarkable in that it comprises: - a maintenance calculator; A flight information monitoring system of the aircraft; and a maintenance assistance device as mentioned above. In a particular embodiment, the maintenance computer, the flight information monitoring system of the aircraft and the maintenance assistance device are integrated in the same physical unit. The invention also relates to an aircraft comprising a maintenance assistance system as mentioned above.
    [0004] The invention also relates to a method of assisting the maintenance of an aircraft comprising: a maintenance computer; a flight information monitoring system of the aircraft; and a communication unit configured to allow communications between the aircraft and a ground station. The method is remarkable in that the aircraft further comprises a maintenance assistance device comprising: a first interface configured to communicate with the maintenance computer by means of a first communication link of the aircraft ; a second interface configured to communicate with the flight information monitoring system of the aircraft by means of a second communication link of the aircraft; a third interface configured to communicate with the communication unit by means of a third communication link of the aircraft; and a processing unit, the method comprises the following steps implemented by the processing unit: storing a triggering condition according to at least one maintenance information of the aircraft and / or from less flight information from the aircraft; - Acquire first information from the maintenance computer, through the first interface and / or second information from the flight information monitoring system of the aircraft, through the second interface; - check whether the trigger condition is fulfilled, based on the first information and / or second information; and 10 - if the triggering condition is fulfilled, send to the communication unit, through the third interface, a set of information including maintenance information from the maintenance computer and flight information of the aircraft from the flight information monitoring system of the aircraft.
    [0005] The invention will be better understood on reading the description which follows and on examining the appended figures. Figure 1 schematically illustrates an aircraft having a maintenance assistance system. Figure 2 schematically shows a maintenance assistance system according to an embodiment of the invention. The aircraft 1 shown in FIG. 1 comprises a cockpit 3, as well as an avionics bay 2 receiving a maintenance assistance system for the aircraft. The maintenance assistance system is provided to communicate with a ground station 8 via a wireless link. The ground station is connected to a computer (not shown) of a maintenance operator. This computer can be located in the ground station 8, or in a remote maintenance center of the ground station and connected thereto by a communication network, for example the Internet or a dedicated network. In an embodiment shown in FIG. 2, the maintenance assistance system 20 comprises a maintenance computer 12, a flight information monitoring system 14 of the aircraft, a communication unit 16, and A maintenance aid device may be used in an onboard computer of the aircraft. The maintenance assistance device 10 can for example correspond to a dedicated computer or be hosted in an IMA-type modular computer ("Integrated 5 Modular Avionics"). The maintenance assistance device 10 comprises a first communication interface 32 configured to communicate with the maintenance computer 12 by means of a first communication link 22. It also comprises a second communication interface 34 configured to communicate with the communication computer. Flight information monitoring system 14 by means of a second communication link 24, as well as a third communication interface 36 configured to communicate with the communication unit 16 by means of a third communication link 26 In particular, the maintenance computer 12 may correspond to a maintenance computer of the CMS type and the flight information monitoring system 14 may correspond to an ACMS type system. The communication unit 16 may in particular correspond to a computer or an on-board communications management server between the aircraft and the ground, configured to allow communications between the aircraft and the ground station 8 by means of a or several antennas of the aircraft. This communications management calculator can in particular support satellite communications, a WiFi® type network, or a 3G or 4G type of telecommunications network, etc. Preferably, although not exclusively, these communications may implement an IP protocol ("Internet Protocol" in English). In a particular embodiment, the first interface 32, the second interface 34 and the third interface 36 correspond to communication ports of the maintenance assistance device 10, these communication ports being for example compatible with the ARINC 429 standard. The first link 22, the second link 24 and the third link 26 then correspond to ARINC 429 communication buses. In another embodiment, the maintenance assistance device 10, the maintenance computer 12 the flight information monitoring system 14 and the communication unit 16 are connected to a deterministic full-duplex Ethernet communication network, for example an AFDX® communication network. The first interface 32, the second interface 34 and the third interface 36 can then be implemented by means of the same physical communication port of the maintenance assistance device 10. The first link 22, the second link 24 and the third link 26 5 then correspond to virtual links of the communication network. The maintenance assistance device 10 further comprises a processing unit 18. This processing unit can in particular correspond to a processor or a microprocessor connected to one or more memories. In operation, in a first step, an operator of a maintenance center sends a triggering condition to the aircraft, via the ground station 8. This triggering condition is a function of at least one information item. maintenance of the aircraft and / or at least one flight information of the aircraft. In the aircraft, this triggering condition is received by the communication unit 16 which sends it to the maintenance assistance device 10 by way of the link 26. The maintenance assistance device 10 stores this trigger condition in a memory. Since the triggering condition is a function of at least one aircraft maintenance information and / or flight information of the aircraft, it may correspond to a condition relating to one or more maintenance information of the aircraft. aircraft, either at a condition relating to one or more flight information of the aircraft, or again to a condition combining at least one maintenance information of the aircraft and at least one flight information of the aircraft. The maintenance operator can thus define, and send to the maintenance aid device, a trigger condition corresponding to any combination of maintenance information and flight information of the aircraft. This allows it to define a trigger condition particularly suitable for monitoring a given failure likely to occur in the aircraft.
    [0006] In particular, the triggering condition may correspond to a combination, by means of logical operators, of elementary conditions relating to maintenance information and / or flight information of the aircraft. Logical operators can be AND, OR, NOT. The elementary conditions may correspond to comparisons, for example using comparison operators such as <,>, =, #, 3032545, and so on. The elementary conditions may also include arithmetic operators such as +, x, / connecting numerical values. The elementary conditions may also include a time variation operator, making it possible to monitor the evolution of the value of a parameter over time. An elementary condition including a variation operator with time can be for example: "a temperature drops more than 10 ° C in less than 5 seconds". It is thus possible to define complex combinations of elementary conditions, which may include conditions relating to the evolution of maintenance and / or flight information of the aircraft. A trigger condition may for example be: ((temp1> temp2 + 30) AND valve_position) OR (calc_fail) in which temp1, temp2 and valve_position are flight information of the aircraft and calciail is maintenance information of the aircraft, such that - time1 and temp2 are two temperature values measured on board the aircraft; valve_position is logical information associated with a valve, the value of which is true when the valve is open and false when the valve is closed; and - calc_fail is a logical information associated with a computer of the aircraft, whose value is true when the computer is down. Once the trip condition is memorized by the maintenance aid device 10, the latter monitors the eventual occurrence of said triggering condition. For this, the processing unit 18 repeatedly interrogates the maintenance computer 12, through the first interface 32 and the link 22, to request first information, and / or the flight information monitoring system 14. The aircraft, through the second interface 34 and the link 24, to request second information. In return, the processing unit 18 receives first information from the maintenance computer 12, through the first interface 32 and / or second information from the flight information monitoring system 14 of the aircraft, through the second interface 34. The first and / or second information required by the processing unit 18 corresponds at least to said maintenance information of the aircraft and / or to said flight information of the aircraft whose function is the trigger condition. According to a first alternative, this information is limited to the information necessary to evaluate the triggering condition. According to a second alternative, the information corresponds to a first set of maintenance information and to a second set of flight information of the aircraft, these two sets being independent of the triggering condition. Without departing from the scope of the invention, the processing unit 18 can also receive, automatically and repetitively, the first information and / or the second information from the maintenance computer 12 and / or the monitoring system 14. flight information. In this case, the maintenance computer 12 and / or the flight information monitoring system 14 are configured to send this information automatically and repetitively to the processing unit 18, which then does not need to interrogate this calculator and / or this system. After acquiring the first and / or second information, the processing unit 18 checks whether the triggering condition is satisfied, based on the first and / or second information.
    [0007] In the case where the tripping condition is fulfilled, the processing unit 18 sends, to the communication unit, through the third interface 36 and the link 26, a set of information including maintenance information from the maintenance computer 12 and flight information of the aircraft from the flight information monitoring system 14 of the aircraft. According to a first variant, this set of information is independent of the trigger condition: when the trigger condition is fulfilled, the same types of information are sent to the ground station regardless of the triggering condition. In a second variant, the set of information 30 is set: a maintenance operator can define the set of information that he wishes to receive when the trigger condition is fulfilled. The parameterization of the set of information is packaged with the triggering condition when it is sent from the maintenance center to the aircraft, the parameterization being memorized by the maintenance assistance device, together with the trigger condition. Advantageously, in the case of the aforementioned second alternative, the set of information comprising maintenance information from the maintenance computer 12 and flight information from the aircraft 14 from the information monitoring system 14. flight of the aircraft corresponds to all or part of the first set of maintenance information and the second set of flight information of the aircraft. Thus, information in the information set is synchronous with the information used to evaluate the trigger condition. Communications between the aircraft and the ground station are possible both during the flight of the aircraft than when it is on the ground, for example during a maintenance phase between two flights. According to one embodiment, from the moment the processing unit 18 detects that the triggering condition is fulfilled, it sends said set of information to the communication unit 16 repetitively at a determined frequency. For example, it sends the set of information every minute. This allows the maintenance operator to monitor the evolution of the different information over time, which can help him to determine the origin of a possible failure. According to one possibility, the processing unit 18 sends the set of information repeatedly for a predetermined number of times or for a predetermined duration. Alternatively, the processing unit 18 sends the information set repetitively until it receives a stop order of sending information, this stop command from the communication unit 16 through the third interface 36. In such a case, when the processing unit 18 detects that the triggering condition is fulfilled, the maintenance operator receives the set of information in a repetitive manner until it sends a stop command to the aircraft, this stop command being then transmitted to the processing unit 18 by the communication unit 16 as previously indicated. Advantageously, the repetitive sending of the information is optimized by sending at a given moment a subset of the set of information, this subset corresponding to the information which has varied since the previous sending 3032545 14. This limits the volume of information transmitted from the aircraft to the ground station. In an advantageous embodiment, when the processing unit 18 detects that the trigger condition is not fulfilled, it records said set of information in a memory. The recording of the set of information is performed repeatedly, at a determined frequency, for example every minute, as long as the trigger condition is not met. If the processing unit detects that the triggering condition is fulfilled, then it sends at least a portion of the information stored in this memory to the communication unit 16. Thus, when the triggering condition is fulfilled, the maintenance operator receives maintenance information and flight information from the aircraft corresponding to moments prior to the instant at which the trigger condition is fulfilled. This may allow him to better appreciate the evolution of certain information before this moment, in order to more easily identify a possible failure. Preferably, the processing unit 18 sends said at least a portion of the recorded information before sending the set of information when the trigger condition is fulfilled. This makes it possible to send the various information in chronological order. The memory is managed according to the principle of a circular queue in which the most recent information replaces the oldest information as long as the triggering condition is not fulfilled. The size of the memory is determined so that a history of the set of information corresponding to at least a desired history duration can be maintained. In a particular embodiment, the processing unit 18 is further configured to receive a sending command, from the communication unit 16, through the third interface 36. This sending order can notably correspond to to a dispatch order received from a maintenance operator. Upon receipt of a sending order, the processing unit 18 sends said set of information to the communication unit 16, through the third interface 36. This allows a maintenance operator to request the dispatch of the aircraft maintenance information and flight information set even when the trip condition is not fulfilled.
    [0008] Although for the sake of clarity the invention has been described with reference to a single triggering condition, in practice the processing unit 18 can store and monitor a plurality of triggering conditions each corresponding, for example, to the monitoring one or more fault situations on board the aircraft. Furthermore, although the invention has been described in the context of the fault detection of the aircraft, it is not limited to this application. It can also, in particular, be used for monitoring operational events of the aircraft. These operational events may, for example, correspond to the opening of a door when the aircraft is parked on the ground, or to the detection of particular flight conditions of the aircraft for which it may be advantageous to transmit said set of information to the ground station.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Device (10) for the maintenance of an aircraft (1), the device 5 being embedded in the aircraft, this aircraft comprising: - a maintenance computer (12); a system (14) for monitoring the flight information of the aircraft; and - a communication unit (16) configured to allow communications between the aircraft (1) and a ground station (8), characterized in that the device (10) comprises: - a first configured interface (32) communicating with the maintenance computer by means of a first communication link (22) of the aircraft; a second interface (34) configured to communicate with the flight information monitoring system (14) of the aircraft by means of a second communication link (24) of the aircraft; a third interface (36) configured to communicate with the communication unit (16) by means of a third communication link (26) of the aircraft; and - a processing unit (18) configured to: store a trigger condition according to at least one aircraft maintenance information and / or at least one flight information of the aircraft; acquiring first information from the maintenance computer, through the first interface and / or second information from the flight information monitoring system of the aircraft, through the second interface; . checking whether the triggering condition is fulfilled, on the basis of the first information and / or the second information; and 30. if the triggering condition is fulfilled, send to the communication unit, through the third interface, a set of information including maintenance information from the maintenance computer and flight information from the aircraft system. flight information monitoring of the aircraft. 3032545 17
    [0002]
    2- Device according to claim 1, characterized in that the processing unit (18) is configured to send said set of information to the communication unit (16), repetitively.
    [0003]
    3- Device according to claim 2, characterized in that the processing unit is configured to repeat the sending of said set of information to the communication unit: a predetermined number of times; - for a predetermined duration; or - until the reception, by the processing unit, of an order to stop said sending, this stop command coming from the communication unit through the third interface.
    [0004]
    4- Device according to any one of the preceding claims characterized in that the processing unit (18) is configured for: - when the trigger condition is not met, record said set of information in a device memory , repetitively; and when the triggering condition is fulfilled, sending at least a part of the information stored in this memory to the communication unit (16) through the third interface (36).
    [0005]
    5- Device according to any one of the preceding claims, characterized in that the processing unit is configured to receive the trigger condition, from the communication unit, through the third interface.
    [0006]
    6. Device according to any one of the preceding claims, characterized in that the processing unit is configured to: - receive a sending command from the communication unit through the third interface; and - when receiving a send command, send the set of information to the communication unit, through the third interface. 3032545 18
    [0007]
    7- System (20) for the maintenance of an aircraft (1), the system being embedded in the aircraft, this aircraft comprising a communication unit (16) configured to allow communications between the aircraft and a ground station (8), characterized in that the system comprises: - a maintenance computer (12); a system (14) for monitoring the flight information of the aircraft; and a maintenance aid device (10) according to any one of the preceding claims. 10
    [0008]
    8- System according to claim 7 characterized in that the maintenance computer, the flight information monitoring system of the aircraft and the maintenance assistance device are integrated in the same physical unit. 15
    [0009]
    9- Aircraft (1) characterized in that it comprises a maintenance aid system according to one of claims 7 or 8.
    [0010]
    10- A method of assisting the maintenance of an aircraft (1) comprising: - a maintenance computer (12); a system (14) for monitoring the flight information of the aircraft; and - a communication unit (16) configured to allow communications between the aircraft and a ground station (8); characterized in that the aircraft further comprises a maintenance aid device (10) comprising: - a first interface (32) configured to communicate with the maintenance computer by means of a first communication link (22); ) the aircraft; a second interface (34) configured to communicate with the flight information monitoring system (14) of the aircraft by means of a second communication link (24) of the aircraft; a third interface (36) configured to communicate with the communication unit (16) by means of a third communication link (26) of the aircraft; and a processing unit (18), the method comprises the following steps implemented by the processing unit: - storing a triggering condition according to at least one maintenance information of the aircraft and / or at least one flight information of the aircraft; - Acquire first information from the maintenance computer, through the first interface and / or second information from the flight information monitoring system of the aircraft, through the second interface; 10 - checking whether the triggering condition is fulfilled, on the basis of the first information and / or the second information; and if the trip condition is fulfilled, send to the communication unit, through the third interface, a set of information including maintenance information from the maintenance computer and flight information from the aircraft the flight information monitoring system of the aircraft.
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    同族专利:
    公开号 | 公开日
    US20160233948A1|2016-08-11|
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    法律状态:
    2016-02-18| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-12| PLSC| Publication of the preliminary search report|Effective date: 20160812 |
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    2018-02-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550966A|FR3032545B1|2015-02-06|2015-02-06|DEVICE, SYSTEM AND METHOD FOR AIDING THE MAINTENANCE OF AN AIRCRAFT|
    FR1550966|2015-02-06|FR1550966A| FR3032545B1|2015-02-06|2015-02-06|DEVICE, SYSTEM AND METHOD FOR AIDING THE MAINTENANCE OF AN AIRCRAFT|
    US15/013,126| US9887762B2|2015-02-06|2016-02-02|Device, system and method to assist with aircraft maintenance|
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