• 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:
    Electrical distribution system for an aircraft comprising at least one power supply channel comprising at least one power unit able to open or close the connection between at least one source of electrical energy and at least one member of the aircraft. The system comprises protection cards (2b, 2n) each comprising at least two microcontrollers each capable of transmitting a command to each power unit of the power supply channels protected by each protection card, and, among the set microcontrollers protection cards, at least two microcontrollers are provided with a communication function and calculation with all the microcontrollers protection cards (2b, 2n).
    公开号:FR3024927A1
    申请号:FR1457844
    申请日:2014-08-14
    公开日:2016-02-19
    发明作者:Jean-Clair Pradier
    申请人:Zodiac Aero Electric SAS；
    IPC主号:
    专利说明:

    [0001] The technical field of the invention is the electrical distribution systems for aircraft, and more particularly the control of such systems. An aircraft generally has an electrical system including a primary electrical power distribution system and a secondary distribution system. This secondary distribution system is used to protect and distribute electrical power from internal sources, such as generators or batteries, or from external sources, such as park groups. The secondary distribution system consists of several electronic cards, including communication and calculation cards (EDMU) and protection cards (SSPC). Figure 1 illustrates a secondary distribution system according to the state of the art. The system has two types of cards, communication and calculation cards, called EDMU (Electrical Distribution Management Unit) and referenced (la, lb), and protection cards, called SSPC (acronym for "Solid State Power Controller ") and referenced (2a, 2b, 2n). The different cards can be integrated in a single rack or be distributed in the aircraft in different physical subsets including at least one card. The purpose of a communication and calculation card is to determine the controls (open or closed) of the power switches integrated in the protection cards, also called power devices, controlling the powering up of lines that convey electrical energy to the loads. from the plane. By charge of the aircraft is meant electrical equipment consuming the electric power provided.
    [0002] More specifically, the communication and calculation card performs the functions of communication with the aircraft via an airplane bus (3a, 3b), in particular according to the ARINC 429, AFDX, CAN and Ethernet standards and protocols, as well as the communication functions. acquisition of the discrete inputs, calculation of the commands of the protected channels (power units) from the discrete inputs and / or data received on the airplane bus, communication with the protection cards via an internal bus (4a, 4b) ), in particular of the CAN or RS485 type, and of the programming of protection cards (size, type of protection curve, fallback mode in the event of a communication failure). The acquisition means are arranged directly on the communication and calculation card or are located on an additional specific input card, called EDIU (acronym for "Electrical Distribution Inputs Unit").
    [0003] The communication with the protection cards comprises the sending of the commands to the protected channel power devices known as SSPC channels and the reading of the states of the protection cards, in particular the state of the organs, measurements of currents and voltages, or self test results.
    [0004] The commands of the protected channels are usually calculated by the use of a centralized database in each communication and calculation card, which contains, for each output, the list of contributing inputs (discrete inputs or via the airplane bus) and the control logic in the form of a truth table for example.
    [0005] At each cycle, the communication and calculation card acquires all the inputs that can be used by the control logic, calculates each protected channel command and sends it to the protection cards (2a, 2b, 2n) via the internal communication bus (4a, 4b).
    [0006] The communication and calculation card also provides each protection card with the data necessary for the protection, in particular the size, the type of curve, the order of activation or non-activation of the protection functions (example: arc detection). , the fallback mode, that is to say the state in which switches the protected channel in case of total failure of the internal communication buses (open, closed or the previous state for example). These data are transmitted in particular modes (ground loading, at power up for example) and are no longer considered in the following description. In order to ensure good availability of the secondary distribution function, the communication and calculation card is redundant. Each protection card is managed by default by a first communication card and calculates it. In case of failure of the first communication card and calculating it, the protection card automatically switches to a second communication card and calculation lb. The purpose of a protection card is to determine the occurrence of anomalies in the power units and / or the power supply lines. In such a case, a protection card controls the opening of the power devices in order to avoid damage to the connected loads. More specifically, the protection card provides the communication functions with the communication cards and calculation via the internal bus (usually: CAN, RS485 ...), the reception of the commands of the power organs of the protected channels, the transmission status of the protection cards (state of the switches, currents, voltage, self test results), the control of the power units of the protected channels, the protection of the protected channels (overcurrent, short circuit, differential protection, arc. .) according to the specific needs of the aircraft and the acquisition of the internal parameters of the protected channels (state of the switches, currents, voltage, self test results). This architecture according to the state of the prior art allows a good separation of computing and protection functions, with good reliability and good availability. The processors and memories used for the design of the communication and calculation boards make it possible to house a complete database for an entire aircraft, while the processors used for the protection cards are smaller (a microprocessor 3024927 per protected path). . Each microprocessor is therefore used at its maximum potential. However, this architecture has a certain number of disadvantages, such as the need to dedicate a card to the calculation of the commands. This increases the mass and cost of the system and requires a specific reference, with additional development. For example, on a "business jet" type aircraft, the secondary distribution system comprises four racks, each incorporating eight protection cards and two communication cards and 10 calculating. These communication and calculation cards therefore represent a complete study of the hardware environment and the software environment, which doubles the cost of electronic development, plus an additional production cost equivalent to 20% of the production cost of 15%. set of cards required. In case of modification of the system, in development or during the life of the aircraft, the two types of cards are to be modified and possibly upgraded by the aircraft manufacturer or by the operators, which each time doubling the amounts of the aircraft. studies and logistics. An object of the invention is an electrical distribution system for an aircraft comprising at least one power supply channel comprising at least one power unit able to open or close the connection between at least one source of electrical energy and at least one power supply unit. least one organ of the aircraft. The system comprises protection cards each comprising at least two microcontrollers each capable of transmitting a command to each power unit of the power supply channels protected by each protection card and, among all the microcontrollers of the protection cards. protection, at least two microcontrollers are provided with a function of communication and calculation with all the microcontrollers of the protection cards. Microcontrollers equipped with a communication and calculation function can be arranged on the same protection card, the microcontrollers provided with a communication and calculation function each having an interface with an airplane bus. Microcontrollers provided with a communication and calculation function can be arranged on different protection cards, microcontrollers equipped with a communication and calculation function each having an interface with an airplane bus. Microcontrollers equipped with a communication and calculation function can be protection cards equipped with a daughter card including the interfaces with the airplane bus.
    [0007] The system may include at least two locations capable of receiving a protection card, each location including power supplies and data connections for operation of the card, the daughter card being secured to a protection card slot.
    [0008] The daughter card can be connected and arranged in solidarity with a protection card. The system may comprise at least two locations capable of receiving a protection card, each slot comprising power supplies and data connections for operating the card, the protection cards including microprocessors provided with a communication function and calculation are protection cards configured to have the communication and calculation function when they are arranged in a predetermined protection card slot.
    [0009] The microcontrollers provided with a communication and calculation function can be arranged on the same protection card concentrating all the information coming from the airplane bus and the discrete inputs of all the protection cards of the system, the microcontrollers being able to calculate all the controls of the power units of the protection cards via the internal bus. The microcontrollers of each protection card can receive information from the discrete inputs directly connected to each protection card, the microcontrollers being able to determine and issue the commands of the power organs according to the information from the discrete inputs read. The microcontrollers of each protection card can receive information coming from the discrete inputs directly connected to each protection card, the microcontrollers being able either to determine and transmit the commands of the power organs according to the information coming from the discrete inputs read, or receiving commands calculated by at least one protection card including microcontrollers provided with a communication function. Other objects, features and advantages of the invention will become apparent on reading the following description, given solely by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 illustrates a distribution system secondary circuit according to the state of the art, - Figure 2 illustrates the main elements of a protection card with two microprocessors, - Figure 3 illustrates a distribution system without communication card and calculation, - Figure 4 illustrates a distribution system comprising redundant EDMU functions and connection to the airplane bus on two protection cards; FIG. 5 illustrates the main elements of a protection card integrating the EDMU function; FIG. 6 illustrates a distribution system comprising redundant EDMU functions and additional internal communication buses. The current evolution in the structures of the protection cards now makes it possible to consider replacing the microprocessors used up to now unitarily for each protected channel (ie, for example, 16 microprocessors for a 16-channel protection card). , by a set of at least two microprocessors used to drive all the channels. Figure 2 illustrates the main elements of such a protection card. It can be seen that two redundant microprocessors (5a, 5b) control the control members (6a, 6b, 6n) of the power devices of the protected channels by means of command determining means to be transmitted (7a, 7b, 7n). ) able to determine which microprocessor control is to be transmitted. The microprocessors are each connected to means for measuring the state of the protected channel and to the airplane buses (4a, 4b). Such a protection card allows a significant reduction in the number of microprocessors used (with a gain in mass, volume and cost) and is made possible by the very significant increase in the computing power of the most recent microprocessors. It is possible by taking advantage of the current capabilities of microprocessors, and by making some modifications, to develop this architecture to integrate EDMU functions or communication functions and calculation of the electrical distribution system, within a protection card . It is then possible to dispense with the presence of separate communication and calculation cards.
    [0010] A distribution system without a communication and calculation board is illustrated in FIG. 3. It can be seen that, unlike the architecture illustrated in FIG. 1, the communication and calculation boards have been removed. In addition, the aircraft buses (3a, 3b) are directly connected to a first protection card comprising the EDMU function, referenced 8, the first protection card comprising the EDMU function 8 being connected to the other protection cards (2b, 2n). ) by at least one internal bus (4a, 4b). The two microprocessors of the protection card including the EDMU function are used, in order to offer an availability equivalent to that of the distribution systems using separate communication and calculation cards. It is also possible to redundate the EDMU functions and the connection to the airplane bus on two protection cards. Figure 4 illustrates such an embodiment. It can be seen that, in the difference of the distribution system illustrated in FIG. 3, the present system comprises two protection cards comprising the EDMU function, referenced 8a and 8b, each connected to an airplane bus, respectively referenced 3a and 3b. The two protection cards 5 comprising the EDMU function are connected to the other protection cards (2b, 2n) by at least one internal bus (4a, 4b). In this case, on each protection card including the EDMU function, only the processor on which the airplane bus is connected is used for the EDMU function.
    [0011] This solution has the advantage of carrying out the EDMU function on two physically distinct cards, which eliminates any common point (connector, printed circuit, power supply) whose failure could render the entire system unavailable. A protection card incorporating the EDMU function is illustrated in FIG. 5. With respect to FIG. 2, it can be seen that a first interface 9a of the first microprocessor 5a has been added with an airplane bus 3a and a second interface 9b. of the second microprocessor 5b with another airplane bus 3b. In this case, all the EDMU functions are reported on the protection card. This corresponds to the architecture of the system illustrated in FIG. 3. In addition, the protection cards interact with the microprocessors of the protection card integrating the EDMU functions as with discrete communication and calculation cards.
    [0012] In other words, the protection cards dialogue with the EDMU functions executed by the first processor 5a of the protection card integrating the EDMU functions, then with the second processor Sb of the protection card integrating the EDMU functions in the event of failure of the first processor 5a.
    [0013] In the case where all the EDMU functions are transferred to two separate protection cards, a single interface 9 is added, compared to FIG. 2, between one of the two microprocessors 5a, Sb and at least one of the airplane buses 3a, 3b. . Such a case is not illustrated. However, it corresponds to the architecture of the system illustrated in FIG. 4. The EDMU function is executed in each of the first microprocessors 5a of each protection card integrating the EDMU functions. The protection cards communicate with the first microprocessor of the first protection card integrating the EDMU functions and then with the first processor of the second protection card integrating the EDMU functions in the event of failure of the first processor of the first protection card integrating the 10 EDMU functions. In all cases, a discrete input interface is also added to the microprocessors supporting the EDMU functions. Each protection card incorporating the EDMU functions thus receives a portion of the discrete inputs (DSI) required for the system. The interface 9a, 9b with the airplane bus (3a, 3b), according to its complexity and its cost, can be implemented on all the cards, whether it is a protection card (2a, 2b, 2n) or protection cards incorporating EDMU functions (8a, 8b). In this case, these cards are identical, the card (s) incorporating the EDMU functions is determined by its position in the card rack. In other words, the protection cards incorporating the EDMU functions (8a, 8b) are configured by "pin-programming". The "pin-programming" corresponds to an identification and a programming of the card 25 when it is inserted in a predefined card slot. In this case, the identification of the card (s) incorporating the EDMU functions activates the EDMU functions. present on the map. Only the protection card functions are enabled for this same card if it does not have this identification. . The card slot 30 may be disposed on a motherboard among other card slots. This solution is chosen in cases where the interface with the aircraft bus is integrable at a very low cost into the microprocessor of the protection card. This is the case when the bus is CAN or SCI 3024927 and is integrated in the microprocessor. This is also the case when the microprocessor has a dual core making it possible to dedicate a core to the SSPC function and a core to the communication function (ARINC 429 emulation, software stack that can support the Ethernet protocol). The interface 9a, 9b with the plane bus (3a, 3b), depending on its complexity and cost, can be added to one of the protection cards in the form of a daughter card. The protection card thus equipped takes the function EDMU. The protection card incorporating the 10 EDMU functions is a standard protection card equipped with a communication module (mountable in the workshop). She therefore has a dedicated reference. The protection card integrating the EDMU functions is recognized by the presence of the communication module and / or by pin-programming. The daughter card can be connected either directly to a protection card which thus takes the EDMU function, or to a protection card slot, for example a card slot on a motherboard, so that a protection card inserted in this location takes the function EDMU. In the latter case, the motherboard provides the connection of the signals between the daughter card and the protection card. These signals are the power supplies of the daughter card and the dialogue signals between the communication function of the daughter card and the microcontroller of the protection card. This solution is chosen in cases where the interface with the airplane bus represents a prohibitive cost for systematic implementation in all the protection cards. This is the case, for example, when the bus is ARINC 429 type requiring expensive specialized circuit. This is also the case when the bus is AFDX type requiring expensive specialized circuit. In this case, it is a dedicated processor combining a DSP, an Ethernet interface and an AFDX software stack, the dedicated processor being combined with a dedicated avionics circuit. The interface (9a, 9b) with the airplane bus (3a, 3b), according to its complexity and cost, can be added (in mini-mezzanine) on the motherboard of the rack which houses the SSPC. All the protection cards 3024927 11 are then identical. The protection card integrating the EDMU functions is recognized by the presence of the communication module and / or by pin-programming. This solution is chosen in cases where the interface with the airplane bus represents a prohibitive cost for systematic implementation in all the protection cards. This is the case, for example when the bus is ARINC 429 type requiring expensive specialized circuit. This is also the case when the mezzanine added to the rack must contain the minimum of components in order to be very compact and therefore contains only the communication circuit. The software management then remains assured by the microprocessor of the protection card. The EDMU functions are then distributed over all the protection cards as follows: Communication with the airplane Protective card via an EDMU airplane bus Acquisition of the inputs Protection card to discrete protection card with EDMU function Communication with the cards Between protection protection card via a bus and protection card with internal EDMU function Calculation of commands from protection card or discrete inputs and / or protection card with data received on the bus plane EDMU function Sending of commands Protective card with EDMU function Reading the states of the protection cards From protection card to protection card with EDMU function Programming of cards From protection protection card with EDMU function to protection card 15 3024927 12 In the case of the calculation of commands from the discrete inputs and / or data received on the airplane bus and the dispatch orders, two solutions are possible. In a first embodiment, the protection card 5 incorporating the EDMU functions concentrates all the information coming from the airplane bus and the discrete inputs of all the protection cards of the system, calculates all the commands and sends them to the protection cards via the internal bus. In a second embodiment, each protection card reads the information from discrete inputs directly connected to each protection card, determines and emits the controls of the power devices according to the information from the discrete inputs read. In a third embodiment, each protection card reads information from discrete inputs directly connected to each protection card. Each card can either determine the commands of the power organs according to the information from the discrete inputs read or receive commands calculated by at least one protection card 20 provided with the EDMU function. In addition, the protection card incorporating the EDMU functions manages at least one internal communication bus (4a, 4b). The internal communication bus (4a, 4b) has a minor cycle and a major cycle.
    [0014] During each minor cycle, the protection card incorporating the EDMU functions issues the command for a given protection card and receives the information concerning said card in return. After (n-1) minor cycles with n representing the number of protection cards connected to the internal bus, a major cycle is completed. At the end of the major cycle, the protection card incorporating the EDMU functions calculates all the commands for the next cycle.
    [0015] The sequence is as follows for a CAN type internal bus having a bit rate of 500 Kbits / s and comprising eight protection cards, ie a protection card integrating the EDMU functions and seven standard protection cards.
    [0016] 5 Each minor cycle lasts 3 ms. The major cycle lasts 21 ms. The transmission of a message lasts 0.3 ms. The transmission of the protection card command integrating the EDMU functions to a protection card requires a CAN message, ie 0.3 ms.
    [0017] The transmission of the data back from a protection card to the protection card incorporating the EDMU functions requires four CAN messages, ie 1.2 ms. The dialogue is repeated seven times, since the protection card incorporating the EDMU functions does not need to talk on the internal bus with itself. In the example, the response time between the request for activation of a SSPC by discrete input and the actual activation 0.3 D 33 83 9, 3 12 12.3, 15.3 1B 18 , 3 'Cmi md ::' Td UD Ulda E: IF, D3b.-'..-. '= PC7' "; Pf: .7 SSPC8 requires about 40 ms At t = Oms, we see that there is an activation of an entry on the eighth protection card At t = 18.3 ms, there is a reading by the protection card incorporating the EDMU functions of the inputs of the eighth protection card At t = 21 ms, there is a calculation of the SSPC commands. At t = 39 ms, there is a transmission of a command to the eighth protection card At t = 39.3s, the control is applied by the eighth protection card 8.
    [0018] This architecture is viable if the number of protection cards managed by a protection card incorporating the EDMU functions is limited. If the protection card incorporating the EDMU functions must handle a very large number of protection cards, the performance of the internal bus may be insufficient to keep an acceptable response time. This time depends on each aircraft manufacturer. The usual acceptable times are from 50 to 100ms. In this case, it is possible to provide more protection cards integrating the EDMU functions. This solution does not increase the total number of cards, but it requires redunding the aircraft bus interfaces for each protection card cluster integrating the EDMU functions connected to an internal bus. Each cluster of protection cards incorporating the EDMU functions is independent, which is an advantage for security, since there is no common point liable to breakdown. It can also be provided that the interface with the airplane bus of the protection card integrating the EDMU functions, integrates additional internal buses, referenced 11a, 11b, 11c, 11d in Figure 6, to manage more protection cards 20 The distribution system then interfaces with the single aircraft bus and requires the deployment of additional internal communication buses (ADCs) in the aircraft. Such a case is illustrated in FIG.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Electrical distribution system for an aircraft comprising at least one power supply channel comprising at least one power unit capable of opening or closing the connection between at least one source of electrical energy and at least one member of the aircraft, characterized in that it comprises protection cards (2b, 2n) each comprising at least two microcontrollers each capable of transmitting a command intended for each power unit of the power supply channels protected by each protection card, and among all the microcontrollers of the protection cards, at least two microcontrollers are provided with a communication function and calculation with all the microcontrollers of the protection cards (2b, 2n).
    [0002]
    2. System according to claim 1, in which the microcontrollers provided with a communication and calculation function are arranged on the same protection card (8), the microcontrollers provided with a communication and calculation function each having an interface with an airplane bus (3a, 3b.
    [0003]
    3. System according to claim 1, wherein the microcontrollers provided with a communication function and calculation are arranged on different protection cards (8a, 8b), the microcontrollers provided with a communication and calculation function each having an interface with an airplane bus (3a, 3b.
    [0004]
    4. System according to claim 1, wherein the microcontrollers provided with a communication function and calculation are arranged on at least one protection card each connected to a daughter card comprising the interfaces with the aircraft bus.
    [0005]
    5. System according to claim 4, comprising at least two locations adapted to receive a protection card, each location comprising power supplies and data connections allowing the operation of the inserted protection card, the daughter card being connected and arranged in solidarity with a protection card slot.
    [0006]
    6. System according to claim 4, wherein the daughter card is connected and arranged in solidarity with a protection card.
    [0007]
    7. System according to any one of claims 1 to 4, comprising at least two locations adapted to receive a protection card, each location comprising power supplies and data connections allowing the operation of the card, the protection cards. comprising microprocessors provided with a communication and calculation function are protection cards configured to dispose of the communication and calculation function when they are arranged in a predetermined protection card slot.
    [0008]
    8. System according to any one of claims 2 and 4 to 7, wherein the microcontrollers provided with a communication function and calculation are arranged on the same protection card concentrating all the information from the airplane bus 20 and discrete inputs of all the protection cards of the system, the microcontrollers being able to calculate all the controls of the power organs of the protection cards (2b, 2n) via the internal bus.
    [0009]
    9. System according to claim 1, in which the microcontrollers of each protection card receive information coming from the discrete inputs directly connected to each protection card, the microcontrollers being able to determine and transmit the commands of the power devices according to the information from the discrete inputs read. 30
    [0010]
    10. System according to any one of claims 1, 2 and 4 to 7, wherein the microcontrollers of each protection card receives information from the discrete inputs directly connected to each protection card, the microcontrollers being able either to determine and issuing the controls of the power devices according to the information from the discrete inputs read, or to receive commands calculated by at least one protection card comprising microcontrollers provided with a communication function. 5
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    同族专利:
    公开号 | 公开日
    GB2530887A|2016-04-06|
    DE102015113386A1|2016-02-18|
    FR3024927B1|2016-08-26|
    CN105375622B|2019-06-25|
    CN105375622A|2016-03-02|
    CA2900060A1|2016-02-14|
    US9804653B2|2017-10-31|
    US20160048186A1|2016-02-18|
    BR102015019451A2|2016-02-16|
    GB201514131D0|2015-09-23|
    GB2530887B|2021-05-05|
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    法律状态:
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    2016-02-19| PLSC| Search report ready|Effective date: 20160219 |
    2016-05-25| PLFP| Fee payment|Year of fee payment: 3 |
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    2021-04-30| TP| Transmission of property|Owner name: SAFRAN ELECTRICAL & POWER, FR Effective date: 20210326 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1457844A|FR3024927B1|2014-08-14|2014-08-14|ELECTRICAL DISTRIBUTION SYSTEM FOR AN AIRCRAFT|FR1457844A| FR3024927B1|2014-08-14|2014-08-14|ELECTRICAL DISTRIBUTION SYSTEM FOR AN AIRCRAFT|
    CA2900060A| CA2900060A1|2014-08-14|2015-08-07|Electrical distribution system for an aircraft|
    GB1514131.0A| GB2530887B|2014-08-14|2015-08-11|Electrical distribution system for an aircraft|
    BR102015019451A| BR102015019451A2|2014-08-14|2015-08-13|electrical distribution system for an aircraft|
    DE102015113386.5A| DE102015113386A1|2014-08-14|2015-08-13|Electrical distribution system for an aircraft|
    CN201510502972.5A| CN105375622B|2014-08-14|2015-08-14|The distribution system of aircraft|
    US14/826,741| US9804653B2|2014-08-14|2015-08-14|Electrical distribution system for an aircraft|
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