• 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:
    A system for monitoring an aircraft equipment (1), comprising a master electronic module and a slave electronic module each equipped with first wireless communication means (5), the slave electronic module further comprising measurement means (8). ) for performing measurements of a parameter of the aircraft equipment, and supply means making the electronic slave module energy-independent, the master electronic module further comprising detection means adapted to detect a phase of flight in which the aircraft is located, and control means for controlling the measuring means (8) of the slave electronic module via the first wireless communication means (5) to adapt to the detected flight phase the measurements made by the measuring means.
    公开号:FR3052585A1
    申请号:FR1655462
    申请日:2016-06-13
    公开日:2017-12-15
    发明作者:Nicolas Fanton；Pierre-Jean Tine；Sebastien Nouchi
    申请人:Safran Electronics and Defense SAS；Aircelle SA；
    IPC主号:
    专利说明:

    The invention relates to the field of aircraft equipment monitoring (of an engine nacelle for example).
    BACKGROUND OF THE INVENTION
    Many aircraft equipment are subject to significant environmental constraints: temperature, pressure, vibration, shock, electromagnetic disturbance, etc.
    Most of these aircraft equipment are constantly monitored by sensors that measure parameters representative of the state of this equipment in order to detect the occurrence of a fault or a fault. and, on the other hand, to detect an abnormal change in a parameter to anticipate such a failure or such a defect.
    However, some equipment, such as engine nacelles, for example, are not equipped (or only partially equipped) such sensors, because the integration of these sensors raises a number of difficulties.
    However, engine nacelles are highly stressed during certain phases of flight. In particular, a nacelle experiences significant temperature variations and vibration levels during the take-off and climb phases of the aircraft, and significant pressure variations during the descent, approach and landing phases of the aircraft. the aircraft. These temperatures, vibrations and pressures force the nacelle, accelerate its aging and can create mechanical defects in the structure of the nacelle.
    Currently, the detection of such mechanical defects is achieved by visual inspections during maintenance operations. However, between each visual inspection, one or more mechanical defects may appear or worsen. The state of the nacelle then requires either a major repair of the nacelle or the replacement of the nacelle.
    It has of course been envisaged to equip the nacelle with sensors for temperature, acceleration and pressure, to better detect and anticipate the appearance of such mechanical defects, and to better understand the origin and causes of the occurrence of these mechanical defects. However, integration on the nacelle of these sensors and more particularly their connection to the avionics network have been found to be too complex to implement.
    OBJECT OF THE INVENTION The object of the invention is to reduce the complexity of the integration of a surveillance system with aircraft equipment, such as an engine nacelle.
    SUMMARY OF THE INVENTION
    In order to achieve this goal, an aircraft equipment monitoring system is proposed, comprising a master electronic module and a slave electronic module each equipped with first wireless communication means for communicating with each other, the electronic module. slave further comprising measuring means comprising a sensor and intended to perform measurements of a parameter of the aircraft equipment, and supply means making the slave electronic module energy-independent, the master electronic module further comprising detection means adapted to detect a flight phase in which the aircraft is located, and control means for controlling the measurement means of the slave electronic module via the first wireless communication means to adapt to the detected flight phase the measurements made by the measuring means.
    The master electronic module and the slave electronic module communicate via the first wireless communication means. No wired connection for the communication thus connects the master electronic module and the slave electronic module, which reduces the complexity of the integration on the aircraft equipment of the surveillance system according to the invention. The slave electronic module is controlled by the master electronic module via the first wireless communication means. The control of the slave electronic module therefore does not require the slave electronic module to be connected to the avionics network.
    Similarly, the power supply means of the slave electronic module make the slave electronic module energy-autonomous: it is therefore not necessary to connect the slave electronic module to the avionics network for its power supply.
    Finally, it is noted that the adaptation to the flight phase of the measurements made by the measurement means makes it possible in particular to reduce the sampling frequency of the sensor of the slave electronic module when the flight phase in question does not require measurements at a frequency high, which reduces the power consumption of the slave electronic module and thus increase the duration of its autonomy. The invention will be better understood in the light of the following description of a particular non-limiting embodiment of the invention. BRIEF DESCRIPTION OF THE DRAWINGS Reference will be made to the accompanying drawings, in which: FIG. 1 represents an electronic module of a surveillance system according to the invention; - Figure 2 schematically shows the operation of the monitoring system according to the invention.
    DETAILED DESCRIPTION OF THE INVENTION
    With reference to FIG. 1, the monitoring system according to the invention is here intended to monitor a nacelle 1 of an aircraft engine 2.
    The monitoring system according to the invention comprises electronic modules 3 distributed over the structure of the nacelle 1. The electronic modules 3 comprise a master electronic module and a plurality of slave electronic modules.
    Here, each module Eleetronic 3 (master or slave) is identical from a point of view "hardware" (or hardware, in English), that is to say that each electronic module 3, whether master or slave, comprises the same electrical components. The master electronic module and the slave electronic modules differ by software programmed in a microcontroller 4 of each of these electronic modules 3. Thus, the master electronic module comprises a microcontroller 4 in which is programmed a software allowing it to perform functions specific to a master electronic module, and each slave electronic module comprises a microcontroller 4 in which is programmed a software allowing it to perform functions specific to a slave electronic module.
    In addition to the microcontroller 4, each electronic module 3 comprises first wireless communication means 5, second wireless communication means 6, a power supply module 7, measurement means 8 and a memory 9.
    The first wireless communication means 5 comprise an antenna and a radiofrequency transmitter / receiver. The first wireless communication means 5 allow the master electronic module to communicate with each slave electronic module through radio frequency communication. The first wireless communication means 5 here use a proprietary communication protocol at a frequency and power compatible certification issues. The frequency used here is equal to 2.4 GHz.
    The second wireless communication means 6 also include an antenna and a radiofrequency transmitter / receiver. The second wireless communication means 6 are used here only by the master electronic module (and are therefore deactivated on the slave electronic modules). The second wireless communication means 6 allow the master electronic module to transmit various data to a ground receiving terminal 11 located outside the aircraft in the airport area. The monitoring system according to the invention forms with the ground receiving terminal 11 an LPWAN (Low-Power Wide-Area Network) network using a technology designed for the Internet of Things (or loT for the Internet domain). of Things, in English). The technology used here is narrow band (or Narrow Band) or ultra narrow band (or UNE) type technology. The second wireless communication means 6 operate at a frequency adapted to local regulations. The frequency used here is equal to 2.4 GHz. Thanks to the implementation of the LPWAN network, the second wireless communication means 6 have a relatively low power consumption and emit a relatively low radiofrequency energy. The communication rate is also relatively low, which is not problematic because it is not necessary that the communications between the master electronic module and the ground receiving terminal 11 are particularly fast.
    The first wireless communication means 5 and the second wireless communication means 6 are compatible with all international standards relating to the use of radio frequencies.
    The first wireless communication means 5 and the second wireless communication means 6 are in particular sized to communicate using limited power so as not to disturb the other equipment of the aircraft and the equipment on the ground. The first wireless communication means 5 and the second wireless communication means 6 are in particular compatible with the RTCA standard DO-160, and in particular with section 21 which deals with the emission of radiofrequency energy.
    The first wireless communication means 5 and the second wireless communication means 6 are otherwise insensitive to the different electromagnetic disturbances generated by the aircraft equipment or from various sources of ground disturbances.
    It should be noted that the first wireless communication means 5 and the second wireless communication means 6 (for the master electronic module) make the monitoring system according to the invention completely autonomous in terms of communication. None of the electronic modules 3 (master or slave) is connected to the avionics network · Moreover, no electronic module 3 (master or slave) is connected by a wired connection to another electronic module 3 (or to another equipment ) to communicate with this other electronic module 3 or this other equipment.
    The power supply module 7 comprises energy storage means comprising energy harvesting means, a battery (another storage medium, such as a supercapacitor, could also be used), and energy management means.
    The energy recovery means here transform the vibrations generated by the motor 2 into electrical energy which is used to power the electronic module 3 and to charge the battery. It would of course also have been possible to transform another source of energy into electrical energy, including the heat produced by the engine 2 or an electromagnetic field produced by the rotation of the engine 2.
    The energy management means power the electronic module 3 using the electrical energy stored in the battery. The energy recovery means are used to charge the battery. The energy management means adapt the power supply of the electronic module 3 to the different modes of operation which will be discussed later in this description.
    It is noted that the power supply module 7 makes the electronic module 3 (master or slave) completely energy independent. In particular, each electronic module 3 is not connected by a wired connection to any onboard external energy source.
    The measuring means 8 comprise a temperature sensor 12, an acceleration sensor 13 and a pressure sensor 14. The temperature sensor 12 measures the temperature of the platform 1 (at the place where it is positioned), the sensor acceleration 13 measures the vibration experienced by the pod 1, and the pressure sensor 14 measures the pressure undergone by the pod 1.
    The memory 9 of the electronic module 3 is used to record and store a certain number of data: measurements made by the sensors, results of processing carried out by the monitoring system according to the invention, triggering thresholds, identification data, parameters of configuration including configuration data of nacelle 1, etc.
    The operation of the monitoring system according to the invention will now be described in more detail with reference to FIGS. 1 and 2.
    The monitoring system of the invention operates in five modes of operation: a non-operational mode of operation and four operational modes of operation. The four operating modes of operation include a mode called "taxi mode" 16, a mode called "take-off and climb mode" 17, a mode called "cruise mode" 18, and a mode called "descent mode," 'approached and landing' 19.
    The non-operational operating mode 15 is associated with a phase during which the aircraft is stationary, on the ground, with the engines off (the aircraft is for example at the parking lot in a hangar). By "associated with a phase" is meant that the monitoring system according to the invention operates according to said mode when said phase is detected.
    Each operating mode of operation is associated with one or more phases of flight of the aircraft, during which or during which it is implemented.
    The driving mode 16 is associated with an exit taxi phase (or Taxi-Out, in English, which is a taxiing phase preceding a take-off) and a taxi-in phase, or Taxi-In, which is a taxiing phase following a landing).
    The take-off and climb mode 17 is associated with a take-off phase (or Take-Off) and a climb phase (or Climb).
    The cruise mode 18 is associated with a cruise phase (or Cruise).
    The descent, approach and landing mode 19 is associated with a descent phase (or Descent, in English), an approach phase (or Approach, in English), and a landing phase ( or Landing, in English).
    When the monitoring system according to the invention is in the non-operational operating mode (that is to say, when the aircraft is stationary, on the ground, with the engines off), each slave electronic module is in a sleep mode, in which the electrical power consumption of the slave electronic module is almost zero.
    The master electronic module is in a low power consumption mode: only the microcontroller 4, the temperature sensor 12 and the acceleration sensor 13 of the master electronic module are active.
    The non-operational mode of operation of the monitoring system according to the invention is therefore a low-energy mode.
    When the engine 2 of the aircraft starts, the temperature of the nacelle 1 and the vibrations experienced by the nacelle 1 increase. The temperature sensor 12 of the master electronic module and the acceleration sensor 13 of the master electronic module detect that the engine 2 of the aircraft has just been activated by measuring the temperature and the vibrations experienced by the platform 1. temperature 12 of the master electronic module and the acceleration sensor 13 of the master electronic module thus detect that the aircraft is about to be in the phase of rolling out.
    The master electronics module then switches from low power mode to normal mode. The master electronic module controls the slave electronic modules to switch the slave electronic modules from the standby mode to a normal mode. The control of the slave electronic modules is carried out via the microcontroller 4 of the master electronic module and the first wireless communication means 5 of the master electronic module (which therefore act as control means), and via the first communication means. wireless 5 of each slave electronic module.
    The master electronic module synchronizes the slave electronic modules on the running mode 16, since the flight phase following the start of the engine 2 is the output taxiing phase.
    The temperature sensor 12 and the acceleration sensor 13 of the master electronic module thus play the role of detection means adapted to detect the flight phase in which the aircraft is located.
    The master electronic module controls the measuring means 8 of the slave electronic modules (again via the microcontroller 4 and the first wireless communication means 5 of the master electronic module which act as control means) to adapt to the driving phase. The measurements made by the measurement means 8 are output here. In this case, the temperature sensor 12 and the acceleration sensor 13 of each slave electronic module are activated with a sampling frequency of one measurement per minute. The measurements made by the temperature sensor 12 and the acceleration sensor 13 of each slave electronic module are transmitted via the first wireless communication means 5 to the master electronic module which stores these measurements in its memory 9.
    When the aircraft takes off, the vibrations experienced by the nacelle 1 increase. The acceleration sensor 13 of the master electronic module detects that the aircraft is in the takeoff phase.
    The master electronic module synchronizes the slave electronic modules in the take-off and climb mode.
    The acceleration sensor 13 of the master electronic module thus plays the role of detection means adapted to detect the flight phase in which the aircraft is located.
    The master electronic module controls the measuring means 8 of the slave electronic module via the first wireless communication means 5 to adapt to the take-off phase and to the rise phase the measurements made by the measuring means 8.
    In this case, the temperature sensor 12 and the acceleration sensor 13 of each slave electronic module are activated with a sampling frequency of three measurements per minute, and the pressure sensor 14 of each slave electronic module is activated with a sampling frequency of one measurement per minute.
    The measurements made by the temperature sensor 12, the acceleration sensor 13 and the pressure sensor 14 of each slave electronic module are transmitted via the first wireless communication means 5 to the master electronic module which stores these measurements in its memory 9 At the end of the climb, the altitude of the aircraft is high and the atmospheric pressure is relatively low. The pressure sensor 14 of the master electronic module (also activated with a sampling frequency of one measurement per minute) detects the end of the rise phase and therefore the beginning of the cruise phase.
    The master electronic module synchronizes the slave electronic modules in cruising mode.
    The pressure sensor 13 of the master electronic module thus plays the role of detection means adapted to detect the flight phase in which the aircraft is located.
    The master electronic module controls the measuring means 8 of the slave electronic module to adapt to the cruise phase the measurements made by the measuring means 8.
    In this case, the temperature sensor 12 and the acceleration sensor 13 of each slave electronic module are activated with a sampling frequency of one measurement per minute, and the pressure sensor 14 of each slave electronic module is activated. with a frequency sampling one measurement per minute. The sampling frequency of the temperature sensor 12 and the sampling frequency of the acceleration sensor 13 are low because the cruise phase requires only reduced monitoring. The electrical energy consumption of the monitoring system according to the invention is therefore reduced. The measurements made by the temperature sensor-12, the acceleration sensor 13 and the pressure sensor 14 of each slave electronic module are transmitted via the first wireless communication means 5 to the master electronic module which stores these measurements in its memory 9.
    Following the end of the cruise phase, the descent phase begins. The descent phase is detected by the pressure sensor 14 of the master electronic module which detects an increase in the pressure experienced by the nacelle 1 and therefore a decrease in altitude of the aircraft.
    The master electronic module synchronizes the slave electronic modules in the descent, approach and landing mode.
    The pressure sensor 14 of the master electronic module thus plays the role of detection means adapted to detect the flight phase in which the aircraft is located.
    The master electronic module controls the measuring means · 8 of the slave electronic module to adapt to the cruise phase the measurements made by the measuring means 8.
    In this case, the temperature sensor 12 and the acceleration sensor 13 of each slave electronic module are activated with a sampling frequency of three measurements per minute, and the pressure sensor 14 of each slave electronic module is activated with a sampling frequency of IkHz. The high sampling frequency of the pressure sensor 14 makes it possible effectively to detect events of the sudden pressure variation type likely to damage the structure of the nacelle 1. Such events occur mainly during the descent and approach phases. and landing.
    The measurements made by the temperature sensor 12, the acceleration sensor 13 and the pressure sensor 14 of each slave electronic module are transmitted via the first wireless communication means 5 to the master electronic module which stores these measurements in its memory 9 At the end of the flight, the pressure sensor 14 of the master electronic module detects that the nacelle 1 no longer undergoes the vibrations generated by the engine 2. The master electronic module controls the slave electronic modules so that they pass into the mode Eve. The monitoring system according to the invention is then again in the non-operational operating mode 15.
    When the flight is over, all the measurements stored in the memory 9 of the master electronic module and acquired during the various flight phases are transmitted by the master electronic module to the ground receiving terminal 11 via the second wireless communication means. 6 of the master electronic module. The master electronic module also transmits to the ground receiving terminal 11 other information stored in its memory 9: results of processing carried out by the monitoring system according to the invention, identification data, configuration parameters including data configuration of the nacelle 1, etc.
    It should be noted that, in order to optimize the electrical consumption of the monitoring system according to the invention, the second wireless communication means 6 of the master electronic module which allow communication to the ground receiving terminal 11 are activated only when the phase of landing has been detected. In the other flight phases of the aircraft, the communication to the ground is not allowed and the second wireless communication means 6 of the master electronic module are not powered.
    Of course, the invention is not limited to the embodiment described but encompasses any variant within the scope of the invention as defined by the claims.
    It has been indicated here that the electronic modules, whether "masters" or "slaves", are all identical from a material point of view. Of course, it is possible to use master and slave electronic modules which are different from a hardware point of view, and even of different electronic slave modules from a hardware point of view.
    The slave electronic modules may for example include different measuring means according to their position on the equipment.
    For example, it is possible for the second wireless communication means not to be mounted on the slave electronic modules. It can also be provided that only the slave electronic modules are energy independent: the slave electronic modules then comprise a battery, and advantageously energy recovery means, while the master electronic module is connected to an onboard power source.
    It can also be provided that certain slave electronic modules are dedicated to the measurement of the temperature, and therefore comprise only one temperature sensor, that other slave electronic modules are dedicated to the measurement of vibrations, and therefore only include an acceleration sensor, and that some electronic slave modules are dedicated to the measurement of pressure, and therefore comprise only one pressure sensor. In this case, the master electronic module, for a given operational mode of operation, activates only the slave electronic modules that can perform measurements during this given operational mode of operation.
    The sensors mentioned can of course be different; for example, it is possible to provide a master or slave electronic module with a speed sensor, a sensor with an electrical parameter (current, voltage, etc.), a force sensor, etc.
    Although a particular architecture has been described here in which the nacelle is equipped with a master electronic sensor and a plurality of slave electronic sensors, it is possible to provide a different architecture. One could in particular have several electronic master modules for a single nacelle, or a single master electronic module for several nacelles. The electronic modules (and, in particular, the master electronic module) are not necessarily positioned on the monitored equipment.
    The role of each master or slave electronic module in the monitoring system according to the invention may also be slightly different from that described. For example, it is possible to imagine that certain electronic slave modules are used to relay data from other slave electronic modules to the master electronic module.
    Although for the second wireless communication means the implementation of narrow-band or ultra narrow-band technology for the LPWAN network, it is perfectly possible to use a different technology, for example example a LoRa or SigFox technology. It is also possible to use a frequency different from the frequency of 2.4GHz, including a frequency included in the band WAIC (for Wireless Avionics Intra-Communications, in English). The frequencies 868MHz, 915MHz or 4.2GHz can for example be used. Similarly, for the first wireless communication means, it is possible to use a frequency different from the frequency of 2.4GHz, and in particular the frequencies 868MHz, 915MHz or 4.2GHz.
    The sampling frequencies may also be different from the sampling frequencies mentioned in the description.
    It has been described that the transition from the non-operational operating mode to the running mode of the monitoring system according to the invention is controlled by the master electronic module following the detection by the sensors (temperature, acceleration) of the master electronic module of a elevation of temperature and vibration experienced by the nacelle.
    It is alternatively possible to provide for the master electronic module to be in standby mode when the monitoring system according to the invention is in the non-operational operating mode, as are the slave electronic modules. The master electronic module is then "awakened" by the energy recovery means which recover the vibrations resulting from the starting of the motor to produce an electrical energy and therefore a supply voltage which supplies the master electronic module.
    Finally, the monitoring system according to the invention can perfectly be used to monitor aircraft equipment other than a nacelle, for example an element of the wing or landing gear of the aircraft.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    A system for monitoring an aircraft equipment (1), comprising a master electronic module and a slave electronic module each equipped with first wireless communication means (5) for communicating with each other, the slave electronic module further comprising measuring means (8) comprising a sensor and intended to perform measurements of a parameter of the aircraft equipment, and supply means making the slave electronic module energy-independent, the master electronic module further comprising detection means adapted to detect a flight phase in which the aircraft is located, and control means for controlling the measuring means (8) of the slave electronic module via the first wireless communication means (5) to adapt to the flight phase detected the measurements made by the measuring means.
    [2" id="c-fr-0002]
    2. Monitoring system according to claim 1, wherein the measuring means of the slave electronic module and / or the detection means of the master electronic module comprise a temperature sensor (12) and / or an acceleration sensor (13). and / or a pressure sensor (14).
    [3" id="c-fr-0003]
    3. The monitoring system according to claim 1, wherein the adaptation of the measurements consists in using another sensor to make measurements of another parameter and / or to modify a sampling frequency of the sensor.
    [4" id="c-fr-0004]
    4. Monitoring system according to claim 1, the monitoring system being adapted to operate in a non-operational mode of operation with low energy consumption and a normal operating mode according to the detected flight phase.
    [5" id="c-fr-0005]
    5. Monitoring system according to claim 4f wherein the control means of the master electronic module are adapted to control the slave electronic module from a standby mode to a normal mode so as to pass the system. monitoring the non-operational operating mode to the operational operating mode.
    [6" id="c-fr-0006]
    6. Monitoring system according to claim If in which the detected flight phase is a phase among an exit taxi phase, a take-off phase, a climb phase, a cruise phase, a descent phase, a flight phase. approach, a landing phase, a re-entry phase.
    [7" id="c-fr-0007]
    7. Monitoring system according to claim 6, wherein the detection means detect that an engine of the aircraft has just been started and therefore that the aircraft is about to be in the exit taxi phase by measuring vibrations or a temperature experienced by aircraft equipment.
    [8" id="c-fr-0008]
    8. Monitoring system according to claim 6, wherein the detecting means detects that the aircraft is in the take-off phase or in the landing phase by measuring vibrations experienced by the aircraft equipment.
    [9" id="c-fr-0009]
    9. Monitoring system according to claim 6, wherein the detecting means detects that the aircraft is in a cruising phase by measuring a pressure experienced by the aircraft equipment.
    [10" id="c-fr-0010]
    10. Monitoring system according to claim 1, wherein the supply means of the slave electronic module comprise energy recovery means.
    [11" id="c-fr-0011]
    The monitoring system of claim 1, wherein the master electronics module includes second wireless communications means (6) for transmitting the measurements to a ground receiving terminal (11).
    [12" id="c-fr-0012]
    The monitoring system of claim 11, wherein the second wireless communications means (6) is activated only after detecting a landing phase.
    [13" id="c-fr-0013]
    13. Engine nacelle comprising a monitoring system according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    US20190118978A1|2019-04-25|
    FR3052585B1|2018-06-15|
    ES2786624T3|2020-10-13|
    EP3469805A1|2019-04-17|
    WO2017216119A1|2017-12-21|
    CN109565622B|2020-03-06|
    RU2690026C1|2019-05-30|
    CN109565622A|2019-04-02|
    US10589877B2|2020-03-17|
    EP3469805B1|2020-03-18|
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    法律状态:
    2017-05-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-15| PLSC| Search report ready|Effective date: 20171215 |
    2018-05-25| PLFP| Fee payment|Year of fee payment: 3 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1655462|2016-06-13|
    FR1655462A|FR3052585B1|2016-06-13|2016-06-13|SYSTEM FOR MONITORING AN AIRCRAFT EQUIPMENT|FR1655462A| FR3052585B1|2016-06-13|2016-06-13|SYSTEM FOR MONITORING AN AIRCRAFT EQUIPMENT|
    CN201780035852.6A| CN109565622B|2016-06-13|2017-06-12|System for monitoring aircraft equipment|
    ES17728581T| ES2786624T3|2016-06-13|2017-06-12|Supervision system of an aircraft equipment|
    US16/309,340| US10589877B2|2016-06-13|2017-06-12|System for monitoring an aircraft device|
    PCT/EP2017/064318| WO2017216119A1|2016-06-13|2017-06-12|System for monitoring an aircraft device|
    EP17728581.4A| EP3469805B1|2016-06-13|2017-06-12|System for monitoring an aircraft device|
    RU2019100217A| RU2690026C1|2016-06-13|2017-06-12|Aircraft equipment monitoring system|
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