• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
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    • 专利摘要:
    The present invention relates to the field of avionics. It relates in particular to a data transmission switch configured to be on board an aircraft, the switch comprising: at least one input configured to receive data from a flight management computer on a first transmission channel, said channel operating in a mode Way; at least one output configured to transmit said data to at least one avionics equipment on a second transmission channel, said switch characterized by further comprising a transducer configured to generate synchronization instructions of said second transmission channel.
    公开号:FR3027477A1
    申请号:FR1402344
    申请日:2014-10-17
    公开日:2016-04-22
    发明作者:Jean Philippe Chedas；Remy Touron
    申请人:Thales SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION [0001] The present invention relates to the avionics field.  More specifically, it relates to communications between avionic systems using heterogeneous communication protocols and synchronization means.  STATE OF THE PRIOR ART [0002] The so-called avionics systems are all the electronic, electrical and computer equipment that assist in piloting aircraft.  [0003] Historically, the avionic devices have constituted separate modules communicating with each other by means of unidirectional links and potentially synchronous communication protocols.  In this architecture, each of the different avionics equipment (for example, a flight management system 20, a flight guidance system, a terrain alert system or a visualization) communicates separately with the equipment with which it must interact according to a potentially synchronous point-to-point or point-to-multipoint communication.  In the context of unidirectional communication means, a device is either transmitter or data receiver.  In the case where the transmission of data between two pieces of equipment has to be done in both directions, a first transmission means is used to transmit the data from the first to the second piece of equipment, and a second means of transmission is used for the transmission in both directions. reverse.  [0004] Point-to-point communication between two remote devices can notably be carried out via an ARINC bus 429 (named after the company Aeronautical Radio, INCorporated, which publishes the standards defined by the AEEC (Airlines Electronic Engineering Committee). ) relating to aircraft internal networks and buses and protocols used in aeronautics. ).  The ARINC bus 429, which can also be named A429 in this application, is standardized.  It comprises a physical layer consisting of a pair of shielded twisted wires, as well as a transport layer.  The transport layer can be used according to different communication protocols between the avionics equipment.  The protocols used by these devices to communicate can be synchronous.  For example, as part of the Williamsburg file transfer protocol, defined by the ARINC 429 P3-18 standard, avionics equipment must require authorization to send data, via a "Request to send" message. English "Request to Send") to receiving equipment, which must allow sending of data via a "Clear fo send" message.  An ARINC 429 bus is a unidirectional communication bus, comprising a single transmitter and up to 20 receivers.  In some cases, the point-to-point communication between two avionics equipment can be performed by a shared memory.  This is for example the case in some avionics system architectures, for the communication between the flight management system and the flight control system, in order to allow a faster transmission of information.  The transmission of information is then also synchronous: in order to prevent concurrent access to the shared memory, a memory zone indicates whether the memory is being written, and can be read or not.  The communication between the flight management computer and the flight control computer is bidirectional, the two devices exchanging information within the shared memory.  In particular, the flight management computer can send guidance commands to the flight guidance computer.  Conversely, the flight guide computer can send information to the flight management computer indicating its status and what are the expected guidance orders.  The avionics system architectures based on unidirectional links have certain limitations.  In particular, the number of links increases very rapidly with the number of avionics equipment.  This makes the addition of new equipment to the avionics system more complex.  In addition, in the case of links on the ARINC 429 bus, the installation of a large number of cables increases the weight of the aircraft.  In order to overcome these disadvantages, modular avionics system architectures have been designed.  For example, the AFDX bus (English Avionics FullDupleX Ethernet switching, full duplex avionics Ethernet in simultaneous multidirectional transmission), standardized by the standard ARINC 664, part 7, proposes an Ethernet type bus complying with specific security constraints.  While retaining the flexibility and overall operation of an Ethernet bus, it has redundancy for sending packets, and a packet switching system that manages queues to circulate only one packet. packet on both the network.  This system makes it possible to avoid collisions of data packets, and to ensure a deterministic data transmission essential for an aeronautical system.  [0008] An avionics system whose architecture is based on an AFDX bus is much more flexible than a system based on unidirectional links.  Indeed, it is sufficient to add a device to connect it to the AFDX bus and assign a network address to it, rather than creating and testing new unidirectional connections separately.  In addition, once the equipment is installed, it is possible to provide additional functionality by a simple software update.  Communications on an AFDX bus are not synchronous: each device sends data packets to a target device, and packets can be sent simultaneously within the network, their traffic being adjusted to avoid collisions. .  In addition, communications within an AFDX bus are multidirectional simultaneous: two devices can transmit data to each other simultaneously through the same data bus AFDX [0009] The AFDX bus facility has facilitated adoption of new equipment in aircraft.  In addition many recent features have been developed for flight management computers communicating through an AFDX network.  Among recent features, the approach procedures CDA (Continuous Descent Approach Approach) can save fuel during the descent of aircraft.  These features would be complex to redevelop for a flight management computer operating on synchronized links.  Similarly, it is relatively easy to deploy new elements, for example more efficient tactile interfaces within an avionics system in which the communications between equipment are based on an AFDX bus.  It is much more complex to provide new features as they are designed to an aircraft whose communications between elements were initially designed in a point-to-point synchronous mode.  This problem is particularly important with regard to the flight management system, for which new features, including fuel savings, are regularly made.  A naive solution to this problem is to replace all the avionics equipment of an aircraft by communicating equipment by means of an AFDX bus.  This solution is in practice ineffective.  It is indeed extremely expensive, and forces the immobilization of the aircraft for an unacceptable length by an airline.  US20070127521 discloses a method for converting messages expressed according to heterogeneous buses or protocols, for example an AFDX bus and ARINC 429.  However, it only offers a direct conversion of packets between two buses, and therefore does not address the problem of the synchronization of the communication channels.  Thus, an avionics equipment whose communications are based on the AFDX bus will emulate a synchronous communication as defined in a protocol complying with the ARINC 429 standard, for example by sending messages respecting the Williamsburg protocol within an AFDX bus.  In addition, it does not address other types of communications between avionics equipment, such as shared memory communications.  In order to solve the aforementioned problem, an object of the present invention is to provide an avionics system for inserting a flight management computer whose communications are based on a multidirectional channel, for example an AFDX bus at within a set of avionics equipment using synchronous communications.  SUMMARY OF THE INVENTION [0014] For this purpose, the subject of the invention is a data transmission switch configured to be on board an aircraft, the switch comprising at least one input configured to receive data from a management computer. flight on a first transmission channel, said channel operating in multidirectional mode; at least one output configured to transmit said data to at least one avionics equipment on a second transmission channel; said switch being characterized in that it further comprises a transducer configured to generate synchronization instructions of said second transmission channel.  [0015] Advantageously, the synchronization instructions of the second transmission channel comprise at least one verification of a possibility of data transmission; an indication of the beginning of data transmission; the indication of the end of the data transmission.  In one embodiment of the invention, said at least one output is connected to a shared memory between the switch and said at least one avionic equipment.  Advantageously, the transducer is configured to check the state of a semaphore to check the possibility of a data transmission; to take said semaphore prior to the transmission of data; releasing said semaphore at the end of the data transmission.  In another embodiment of the invention, said at least one output is connected to an ARINC 429 data bus.  Advantageously, the output data are sent according to the Williamsburg protocol, and the transducer is configured to send an "RTS" message to verify the possibility of data transmission; send a "SOT" message prior to the transmission of data; send an "EOT" message at the end of the data transmission.  [0020] Advantageously, the first transmission channel is an AFDX data bus.  In one embodiment of the invention, the switch comprises at least one output connected to an ARINC bus 429 for transmitting the data to at least one additional avionics equipment.  In one embodiment of the invention, the switch is configured to transmit data on at least a second output according to a periodic cycle.  The invention also relates to a data transmission method intended to be executed by an on-board equipment on an aircraft, the method comprising at least one step of receiving, on at least one input, data from a management computer. flight on a first transmission channel, said channel operating in multidirectional mode; a step of transmitting, on at least one output, said data to at least one avionic equipment on a second transmission channel; said method being characterized in that it further comprises a step of generating synchronization instructions of said second transmission channel.  The invention also relates to an avionic system comprising at least one switch according to the invention, and at least one touch-sensitive human-machine interface 25 that can communicate both according to an ARINC 661 protocol and an ARINC 739 protocol.  LIST OF FIGURES [0025] Other characteristics will become apparent on reading the detailed description given by way of nonlimiting example which follows, with reference to appended drawings which represent: FIG. 1, an example of an avionics system within which a flight management computer communicates with avionic equipment by unidirectional links according to the state of the art; FIG. 2, an example of an avionics system in which a flight management computer communicates with avionic equipment via an AFDX bus according to the state of the art; FIGS. 3a and 3b, two examples of synchronous communication protocols between a FMC and an avionics equipment according to the state of the art, respectively in the case of a synchronous communication protocol on an ARINC bus 429 and by a shared memory ; FIG. 4, an example of an avionics system according to the invention; FIG. 5, an example of an avionic system according to the invention comprising tactile interfaces; FIGS. 6a, 6b and 6c show three examples of data switching device according to the invention; FIG. 7, an exemplary data transmission method according to one embodiment of the invention; [0026] Certain English acronyms commonly used in the technical field of the present application may be used during the description.  These acronyms are listed in the table below, including their Anglo-Saxon expression and their meaning.  Acronym Expression Meaning ACK Acknowledgment Acknowledgment.  Computer signal sent by a receiver to indicate to the sender that the connection is well established or that the transmitted message has been well received.  AFDX Avionics Full DupleX Ethernet avionics switches bidirectional.  Redundant and reliable Ethernet network, developed and standardized by the European avionics industry.  ARINC Aeronautical Radio Aeronautical Radio Company.  Company owned by major US aerospace players known for defining the main communication standards inside aircraft and between aircraft and ground.  Refers to both the company and the product standards, for example the ARINC 429 or ARINC 661 standards.  INCorporated CDU Control Display Unit Display Control Unit.  Control and display panel embedded in an aircraft for displaying information on the state of the aircraft and entering instructions.  COM COMmand.  In an onboard card architecture called COM MON, the COM card is responsible for performing the calculations and commands.  CTS Clear To Send Clear For Sending.  Williamsburg protocol message from a receiver to a sender indicating that sending data is possible.  DMC Display Display Management Computer.  Computer receiving data from different avionics systems and manipulating them to display data on external monitors.  Computer Management EIS Electronic Instrument System Electronic Instrument System.  Instrument display system for aircraft cockpit, in which the instruments are electronic.  EOT End Of Transmission End.  Williamsburg protocol message from a transmitter to a receiver indicating the end of the data transmission.  Transmission FGC Flight Guidance Computer Flight Steering Computer.  Computer whose purpose is to provide indications of aeronautical equipment (engine thrust, extension spouts and flaps. . . ) to follow a predefined path.  FGCP Flight Guidance Control Panel Flight Guidance Panel.  Panel indicating the state of the flight guidance computer and allowing to control certain functions.  FM Flight Flight Management.  Set of techniques and systems for controlling the trajectory of an aircraft.  Management FMC Flight Flight Management Computer.  Computer for calculating aircraft flight paths and flight plans, and providing guidance instructions adapted to the pilot or autopilot to follow the calculated Computer Management trajectory.  FMS Flight Flight Management System.  Computerized system for calculating aircraft flight paths and flight plans, and providing guidance instructions adapted to the pilot or autopilot to follow the calculated trajectory.  Global GPS System Management Global Positioning System.  Satellite positioning system.  Positionning System IMDU Interactive Multi Display Unit Interactive Multiple Display Unit.  Human-Machine Interface embedded in an aircraft capable of communicating both according to an ARINC 661 protocol and an ARINC 739 protocol.  LDU Link Data Unit Data Link Unit.  Williamsburg protocol data transmission unit comprising from 3 to 255 words.  MCDU Multi Control Display Unit Multifunction Display Unit.  Man-machine interface that can be integrated into a cockpit allowing the display and the entry of many information related to the FMS.  MON MONitor MONITOR.  Within a COM MON architecture, the MON card is responsible for checking calculations.  ND Navigation Display Navigation Screen.  Cockpit display element showing the lateral flight path.  PFD Primary Flight Display Primary Flight Display.  Display element that can be integrated into a cockpit.  RTS Request To Send Shipping Request.  Message from a sender to a receiver in the Williamsburg protocol requesting to open a channel for sending data.  DETAILED DESCRIPTION In the remainder of the description, the method according to the invention is illustrated by examples relating to the transmission of flight commands between a flight management computer sending commands on a multidirectional network of aircraft. AFDX type and a flight control computer receiving its instructions through an input whose management includes a synchronization protocol.  It should be noted, however, that the invention can also be applied to communications between a flight management computer and other avionics equipment, as well as communications between a touch interface and avionics equipment.  FIG. 1 represents an example of an avionics system in which a flight management computer communicates with avionic equipment via point-to-point unidirectional links according to the state of the art.  This avionics system 1000 comprises a FMC 1100, the role of which is to predict an aircraft trajectory and to provide flight instructions to the FGC 1210 in order to fly the predicted trajectory, as well as to provide data for the display of the flight. trajectory to visualization equipment.  To do this, the FMC is connected in particular to a PFD 1201, a FGCP 1202, aerial data 1203, a radio navigation device 1204, positioning tools (GPS and inertial data) 1205, a printer 1206, a link computer 1207, CDU 1208, ND 1209 and FGC 1210.  In some data links, the FMC is transmitter, and the second avionics equipment is data receiver.  This is for example the case of the link between the FMC 1100 and the ND 1209, in which the FMC 1100 provides a graphical representation of the trajectory at ND 1209.  In other connections, the FMC 1100 is instead a data receiver, and the second transmitter equipment.  This is for example the case of the link 1303, in which the sensors 1203 provide position and speed information to the FMC 1100.  In other links, the FMC 1100 is both a receiver and a data transmitter.  This is for example the case of the link between the FMC 1100 and the FGC 1210, in which the FMC 1100 provides instructions on the path to follow at the FGC 1210, and the FGC 1210 provides information on the guidance mode. selected at FMC 1100.  The FMC 1100 is linked to these different equipment by data buses ARINC 429, respectively 1301, 1302, 1303, 1304, 1305, 1306, 1307, 1308, 1309, 1310.  The ARINC 429 standard defines a unidirectional data bus with a single transmitter and up to 20 receivers.  This architecture is therefore complex to implement.  Some communication protocols within ARINC links 429, for example the Williamsburg protocol, use synchronous communications.  Others, for example the ARINC 702 protocol for the link to the ND, do not include synchronization elements.  The FGC 1210 receives instructions from the FMC 1100 on the path to follow.  It converts these instructions into a set of commands to hold the desired trajectory.  These controls integrate together the output or the return of beaks and flaps, or the modulation of the thrust of each of the engines.  The FMC 1100 can provide instructions to the FGC 1210 via ARINC Link 429 1310.  It can also provide through a 1400 shared memory.  This shared memory makes it possible to provide instructions much faster.  When this solution is adopted, the FMC 1100 and FGC 1210 must be disposed contiguously in the cockpit of the aircraft, and have read / write access to the same memory zone 1400.  FIG. 2 represents an example of an avionics system 2000 in which a flight management computer communicates with avionic equipment via an AFDX bus according to the state of the art.  Within this system, the FMC 2100, PFD 2201, FGCP 2202, aerial data 2203, radio navigation device 2204, positioning tools (GPS and inertial data) 2205, printer 2206, data link computer 2207, CDU 2208, ND 2309 and FGC 2210 have the same functionalities as the FMC 1100, PFD 1201, FGCP 1202, overhead data 1203, radio navigation device 1204, positioning tools (GPS and inertial data) 1205, printer 1206, computer data link 1207, CDU 1208, ND 1209 and FGC 1210 present in the system 1000.  Most of the equipment of the system 2000 are connected to each other by a data network of the aircraft 1400.  This network is based on a multidirectional data bus, for example an AFDX bus.  This system makes it possible to install new equipment, and to update the existing equipment in a much easier way than the ARINC 429 links or the 1000 system shared memory.  The avionics systems of recent aircraft, for example the Airbus A380, are generally organized on the model of the 2000 system.  In the system 2000, some equipment, for example the FGCP 2202, the aerial data 2203, the radionavigation tools 2204 and the positioning tools 2205 can communicate by links ARINC 429, for example the links 2302, 2303, 2304 and 2305.  In this case, an I / O manager 1401 can perform the conversions between the ARINC link data 429 2302, 2303, 2304 and 2305 and the AFDX network 1400.  This conversion consists only in extracting the data contained in the ARINC 429 packets and encapsulating them in AFDX packets, and vice versa.  FIGS. 3a and 3b show two examples of synchronous communication protocols between a FMC and an avionic equipment according to the state of the art, respectively in the case of a synchronous communication protocol on an ARINC bus 429 and by a shared memory.  FIG. 3a shows an exemplary synchronous communication protocol 300a between a FMC and an avionics equipment according to the state of the art, in the case of a communication by an ARINC data bus 429.  This protocol may be the Williamsburg protocol for links to the ground-edge data link equipment.  In the context of a synchronous communication protocol, the sending equipment must ensure that the transmission is possible, and indicate the beginning and the end of the data transmission.  For this purpose, in a first step, a first device, for example the FMC 1100, sends a transmission request 310a to a second avionics equipment 302a.  In the case of the Williamsburg protocol, it is an RTS message.  The equipment 302a responds with an acknowledgment 314a, indicating that the transmission is possible.  In the Williamsburg protocol, this acknowledgment may be a CTS message.  The equipment 301a then sends a transmission start message 311a (SOT message in the Williamsburg protocol), and then transmits the data using at least one message 312a.  As part of the Williamsburg protocol, these are LDU blocks of 3 to 255 words.  The number of messages sent depends on the amount of data to be transferred.  When the data transmission is complete, the equipment 301a sends an end-of-transmission message 313a (EOT message in the Williamsburg protocol), to which the equipment 302a responds with an acknowledgment 315a (ACK keyword in the Williamsburg protocol).  This set of queries and synchronization messages makes it possible to ensure that the data is sent when the receiver is ready to receive them, that there is no interference between different data transmissions and that the data has been well received. received by equipment 302a.  FIG. 3b shows an exemplary synchronous communication protocol 300b between a FMC and an avionics equipment according to the state of the art, in the case of communication by shared memory.  In this example, a first device 301b writes data to a memory 303b, which is read by a second device 302b.  It may be, for example, in architecture 1000, the FMC 1100 which writes the path instructions to be followed in memory 1400, which is read by the FGC 1210.  The memory 303b has a semaphore.  This semaphore makes sure that the memory is not read and written at the same time.  When the equipment 301b plans to send commands to the equipment 302b, it first checks that the semaphore is available 310b.  It then seizes semaphore 311b, then writes data 312b before releasing semaphore 313b.  At the same time, the equipment 302b, configured in this example to receive instructions from the equipment 301b, periodically checks whether the semaphore is available 314b, 315b, 316b.  During checks 314b and 315b, the semaphore is not available because the equipment 301b is writing the data 312b and has not yet released 313b.  The equipment 302b therefore continues to check the availability of the semaphore without accessing the memory.  At check 316b, the equipment 301b has finished writing and the semaphore is free.  The equipment 302b then seizes the semaphore 317b, then reads the memory data transmitted to it by the equipment 301b.  This protocol makes it possible to exchange data between a device 301b and 302b by means of a shared memory, which makes it possible to exchange the data in a very fast manner.  The verification system, taken and released the semaphore makes sure that the data is not read and written at the same time.  The above example gives an example of a protocol in which the equipment 301b provides data or instructions to the equipment 302b.  More complex examples in which both devices read and write data successively are also possible.  FIG. 4 represents an example of an avionics system according to the invention.  This system comprises many avionics equipment connected to inputs / outputs according to ARINC data buses 429.  This equipment may for example be from a 1000 avionics system.  These equipments include two FGC 420, 430; two DMCs 421, 431, two MCDUs 422, 432; legacy systems 423, 433; a FGCP 424.  Legacy systems 423, 433 may include, for example, PFD 1201, FGCP 1202 aerial data 1203 or radionavigation equipment 1204.  This equipment communicates in particular by means of data buses ARINC 429 440, 441, 442, 443, 444, 445, 446, 450, 451, 452, 453, 454, 455, 456.  In this avionics system, most equipment is present in duplicate, to guard against a failure of one of the equipment.  This system according to the invention comprises at least one switch 413, 414 configured to be embedded on the aircraft in which is embedded the avionics system 400.  This switch comprises at least one input configured to receive flight commands from a flight management computer 411, 412 on a first transmission channel 410, said channel operating in multidirectional mode.  It also includes at least one output configured to transmit said flight commands to a flight control computer over a second transmission channel, said computer being characterized by further comprising a transducer configured to generate synchronization instructions. said transmission channel.  In one embodiment of the invention, the output of the switch is connected to a shared memory 460, 461 between the switch and the flight control computer.  In another embodiment of the invention, the output of the switch is connected to an ARINC data bus 429, by which the trajectory information is sent to the flight control computer.  Advantageously, the switch comprises at least a second output, connected to an ARINC data bus 429, for transmitting data from the flight management computer to an avionic equipment, and that said transducer is configured to generate the synchronization messages of said ARINC data bus 429.  [0051] The multidirectional operation of the transmission channel 410 allows greater flexibility in the transmission of messages between a flight management computer 411, 412 and a flight control computer 420, 430, and possibly at least one other equipment. avionics.  The switch 413, 414 makes it possible to manage the synchronization of the links with the other avionics equipment, whether they are shared memory links 460, 461 or ARINC links 429.  [0052] Advantageously, the first data transmission channel is connected to an AFDX bus.  This system makes it possible to integrate a flight management computer 411, 412 communicating via a multidirectional transmission channel, for example an AFDX bus, to an avionic system whose most equipment communicates via ARINC links 429 or memory. shared.  It is extremely interesting because the synchronization of data between the flight management computer and other avionics equipment, including the flight control computer, is managed by the switch 413, 414.  The flight management computer can therefore send or receive data as it would within an avionics system whose communications are based on an AFDX bus, such as the 2000 system.  This allows a lot more flexibility in bringing new features to the flight management computer.  Some ARINC links 429 are governed by a communication protocol including synchronization instructions, for example the Williamsburg protocol.  Other links are not governed by a communication protocol including synchronization instructions, but may be subject to other constraints.  This is for example the case of the link to the ND.  It is governed by the ARINC 702 protocol which does not include synchronization instructions, but the ND must receive data at regular intervals in order to refresh the display without error.  In addition, the amounts of data sent must be small enough so as not to saturate the memory capacity of the ND equipment.  Advantageously, the switch is configured to transmit data on at least a second output according to a periodic cycle.  In addition, this system according to the invention has the advantage of being easily deployed in an older generation avionics system whose main communications are based on ARINC buses 429, such as the 1000 system.  Indeed, a complete replacement of an avionics system 1000 essentially based on ARINC communications 429 by an avionics system 2000 essentially based on AFDX communications is extremely long and expensive, and therefore difficult to apply by an airline.  On the other hand, the transformation of an avionics system based on ARINC communications 429 such as the system 1000 into a system according to the invention is relatively easy: it suffices to replace the existing flight management computer with the switch according to FIG. The invention is intended to deploy a multidirectional data channel, for example an AFDX bus, and then connect at least one flight management computer to the multidirectional data channel.  This retrofit operation can be carried out in a very short time, for example during a night during which the aircraft is on call, which generates no operating loss for the airline.  Once the system according to the invention has been deployed, the addition of new equipment on the AFDX bus, as well as the update of the flight management computer, are as easy as in an avionics system 2000 of which communications are essentially based on an AFDX bus.  During the transformation of an avionics system according to the state of the art into an avionics system according to the invention, the communication channel between a switch 413, 414 and a flight control computer 420, 430 may depend on the communication channel initially in place in the avionics system according to the state of the art.
    [0002] For example, if the communication channel initially in place is a shared memory 1400, a switch 413 can write directly to that memory, which then becomes the memory 460 of the system 400. Thus, the flight control computer reads its instructions in shared memory as it did previously, and it does not require any updates. In another embodiment of the invention, if the communication channel initially in place between the flight management computer and the flight control computer is an ARINC link 429 1310, the switch may send the instructions from the flight management computer in the same ARINC 429 link, and the flight control computer receives its instructions on the same input channel. In this case too, no update is necessary. FIG. 5 represents an example of an avionic system according to the invention comprising tactile interfaces. This avionic system 500 is similar to the avionics system 400 according to the invention, in which the MCDU interfaces 422 and 432 have been replaced by touch-sensitive human-machine interfaces 522 and 532 connected to the AFDX 410 data bus. embodiment of the invention, these tactile human-machine interfaces are capable of communicating both according to an ARINC protocol 739 and an ARINC protocol 661. They can then communicate with legacy equipment 423, 443 by data buses ARINC 429 442 , 452 thanks to an ARINC 739 protocol, and to communicate with a flight management computer 411, 412 via an AFDX 410 data bus thanks to an ARINC 661 protocol. These touch interfaces are particularly advantageous, since they allow at the same time interface with legacy avionic equipment communicating according to an ARINC 739 protocol, and more modern avionics equipment communicating via an ARINC 661 protocol. Figure 6a shows an example of a data transmission switch according to an embodiment of the invention. This data transmission switch is configured to be on board an aircraft, for example within an avionics system 400 or 500. It comprises at least one input 610a configured to receive flight commands from a computer of flight management, for example the computer 411 or 412 on a first channel 620a operating in multidirectional mode. It also includes at least one output 611a configured to transmit said flight commands to a flight control computer, for example the computer 420 or 430 on a second transmission channel 612a. The second transmission channel requiring synchronization with the receiver equipment, this switch is characterized in that it comprises a transducer 630a for generating the synchronization instructions of said transmission channel. In one embodiment of the invention, the synchronization instructions of the second transmission channel may in particular comprise at least: a verification of a possibility of data transmission; - an indication of the beginning of data transmission; - The indication of the end of the data transmission. In one embodiment of the invention, the switch comprises a second output 612a, connected to an ARINC data bus 429 622a. This allows the switch 600a, by analyzing the destination equipment, to send the messages either to the flight control computer via the channel 621a or to an avionics equipment via the ARINC line 429 622a. Figure 6b shows an example of a data transmission switch according to a second embodiment of the invention. In this embodiment of the invention, at least one output 611b is connected to an ARINC data bus 429, on which the flight control computer receives its instructions. In this embodiment of the invention, the first transmission channel is an AFDX data bus 620b, and at least one output 611b also allows to transmit instructions to other avionics equipment. In this embodiment of the invention, the transducer 630b is a programmable logic circuit configured to generate all the synchronization messages of the communication protocols to the flight control computer and the other avionics equipment. FIG. 6c represents an example of a data transmission switch according to a third mode of implementation of the invention. In this embodiment of the invention, the at least one output is connected to a shared memory 611c between the switch and the flight control computer. In this embodiment of the invention the switch is placed contiguously to the flight control computer, consisting of a COM card 640c and a MON 641c card, and the switch 600c and the Flight control computer 640c, 641c are interconnected by a gateway card 650c. In the COM MON architecture thus defined, the COM card performs a first data calculation, and the MON card checks the result of the calculation. The shared memory 611c is located on the switch, and is accessed by the COM card of the flight control computer 640c. In this embodiment of the invention, the switch comprises at least a second output 612c connected to an ARINC bus 429 622c to communicate with at least one avionic equipment. This communication can be carried out according to several communication protocols, for example the Williamsburg protocol or the ARINC 702 protocol. In the context of a link to an ND, the ND may require the reception of a limited amount of data. cyclically. These conditions are not met if the switch sends data to the ND directly after reception. Advantageously, the switch is in this case configured to transmit data on at least a second output according to a periodic cycle. In this embodiment of the invention, the first transmission channel is an AFDX data bus 620c. The switch 600c may comprise a processor configured to generate the synchronization messages of the shared memory 611c, and communication protocols for the second output 612c. In one embodiment of the invention, an operating system is installed on the switch. The drivers required for the different physical communications are then installed on the operating system, for example an AFDX driver to drive the data bus AFDX 620c, a shared memory driver to drive the shared memory 611c, an ARINC bus driver 429 for control the output 612c to the bus 622c, etc. The transducer can then be a software module for synchronizing communications on the different outputs from the data received from the flight management computer. FIG. 7 represents an example of a data transmission method 700 according to one embodiment of the invention. This method can in particular be executed by a switch 600 for transmitting data transmitted by the flight management computer via a multidirectional input channel to a flight control computer or other avionic equipment. The method comprises a first step 710 for receiving, on at least one input, flight commands from a flight management computer on a first transmission channel, said channel operating in multidirectional mode. This first transmission channel may for example be connected to an AFDX network on which the flight management computer sends the flight controls. Step 710 then comprises receiving packets sent over the network and analyzing their contents. The method comprises a second step 720 of identifying the type of data. It includes the verification that the data have been issued by the flight computer. Depending on the type of data, these will be sent to different avionics equipment. If it is a trajectory instruction, the data will be sent to the flight control computer. Otherwise, for example if it is a path to be viewed, the data will be sent to the appropriate equipment. In one embodiment of the invention, the method may then comprise, for certain types of data, a step 730 of verifying a sending condition. It can for example be a temporal condition. For example, if the flight control computer is configured to read instructions every 60 ms, step 730 may include waiting for a send condition to respect this interval. For example, it may include waiting for the expiration of a clock or a cyclic event with one occurrence every 60 ms. When sending data according to an ARINC 702 protocol to an ND, the verification of the sending condition can be a purely time-dependent condition, in order to send the data in a regular cycle for the refresh of the display. . It can also be a more complex condition, for example a condition for sending both data cyclically, but in packets of limited size depending on the capacity of the memory of the destination equipment. The method 700 then comprises a step 740 for selecting the necessary protocol. This protocol depends on the target equipment. For example, in the case of a shared memory data transmission, it may be a synchronization protocol and memory writing such as protocol 3b. In the case of sending data by an ARINC 429 protocol, it may be a Williamsburg type protocol such as protocol 3a. In one embodiment of the invention, the method 700 may, in addition to the protocols comprising synchronization information, transmit data according to protocols without synchronization. This is for example the case when the target equipment is an ND, for which the communication protocol is the ARINC 702 protocol, which does not include synchronization messages. Messages not requiring synchronization of their communication channel may pass through a switch according to the invention as well as messages to be transmitted on a synchronous communication channel. The method 700 comprises, in the case of a protocol requiring synchronization, a step 750 of synchronization of the connection with the recipient. This step is to ensure that the receiving device is ready to receive the data, and that the communication channel is available. In an embodiment based on shared memory, this step may include checking the availability of a 310b semaphore. In an embodiment based on a Williamsburg-type protocol, this step may comprise sending a transmission request message 310a (for example the RTS message) and receiving an acknowledgment 314a (for example the message CTS). Once the synchronization has been completed, or directly after the selection of the protocol, the method 700 comprises a step 760 of beginning of transmission. In the case of a communication protocol based on a shared memory, it may be the taking of a semaphore 311b. In the case of a Williamsburg type protocol, it may be the sending of a transmission start message 311a, for example a SOT message. The method then comprises a step of transmitting the data 770 and checking the end of transmission 780. The method sends data 770 to the target device until the data transmission is complete 780. In An embodiment of the invention based on a shared memory, the data transmission includes writing data 312b as long as there is data to write. In an embodiment of the invention based on a Williamsburg type protocol, step 770 may include packet forwarding 312a for all data. When the data transmission is complete, the method comprises a step 790 of notifying the end of the transmission. In an embodiment based on shared memory, it may include loosening a semaphore 313b. In one embodiment of the invention based on a Williamsburg protocol, it may include sending an end-of-transmission message 313a, for example an "EOT" message in the Williamsburg protocol. The above examples demonstrate the ability of a data transmission switch according to the invention to establish communications between a flight computer sending commands over a multidirectional transmission channel, for example an AFDX bus, and equipment receiving their communications on a channel operating according to a synchronous communication. However, they are only given by way of example and in no way limit the scope of the invention, defined in the claims below.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A data transmission switch configured to be embedded on an aircraft, the switch comprising: - at least one input (610a, 610b, 610c) configured to receive data from a flight management computer (411, 412) on a first transmission channel (620a, 620b, 620c), said channel operating in multidirectional mode; at least one output (611a, 611b, 611c) configured to transmit said data to at least one avionics equipment (420, 430) on a second transmission channel (621a, 621b, 621c); said switch being characterized in that it further comprises a transducer configured to generate synchronization instructions of said second transmission channel. 15
    [0002]
    2. Switch according to claim 1, characterized in that the synchronization instructions of the second transmission channel comprise at least: a verification of a possibility of data transmission (750); An indication of the beginning of data transmission (760); - The indication of the end of the data transmission (780).
    [0003]
    3. Switch according to one of claims 1 to 2, characterized in that said at least one output is connected to a shared memory (621c) between the switch and said at least one avionics equipment.
    [0004]
    4. Switch according to claim 3, characterized in that the transducer is configured to check the state of a semaphore to check the possibility of a data transmission (750, 310b); taking said semaphore 30 prior to data transmission (760, 311b); releasing said semaphore at the end of the data transmission (790, 313b).
    [0005]
    5. Switch according to one of claims 1 to 2, characterized in that said at least one output (611b) is connected to an ARINC data bus 429 (621b).
    [0006]
    Switch according to claim 5, characterized in that the output data is sent according to the Williamsburg protocol, and in that the transducer is configured to send an "RTS" message to check the possibility of a data transmission (750, 310b); send a "SOT" message prior to data transmission (760, 311b); send an "EOT" message at the end of the data transmission (790, 313b).
    [0007]
    Switch according to one of Claims 1 to 6, characterized in that the first transmission channel is an AFDX data bus (410, 620b, 620c).
    [0008]
    8. Switch according to one of claims 1 to 7, characterized in that it comprises at least a second output (612a, 612c) connected to an ARINC bus 429 for transmitting data to at least one additional avionics equipment.
    [0009]
    9. Switch according to claim 8, characterized in that it is configured to transmit data on at least a second output according to a periodic cycle.
    [0010]
    A method for transmitting data for execution by an on-board equipment on an aircraft, the method comprising: at least one step of receiving, on at least one input, data from a flight management computer on a first transmission channel, said channel operating in multidirectional mode (710); at least one step of transmitting, on at least one output, said data to at least one avionic equipment on a second transmission channel (770); said method being characterized in that it further comprises a step of generating synchronization instructions of said second transmission channel (750, 760, 790).
    [0011]
    11.Avanced system comprising at least one switch according to claim 1, characterized in that it comprises at least one touch-sensitive human-machine interface capable of communicating both according to an ARINC 661 protocol and an ARINC 739 protocol (522, 532). 35
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1402344A|FR3027477B1|2014-10-17|2014-10-17|SWITCHING DATA TRANSMISSION BETWEEN HETEROGENEOUS NETWORKS FOR AIRCRAFT|FR1402344A| FR3027477B1|2014-10-17|2014-10-17|SWITCHING DATA TRANSMISSION BETWEEN HETEROGENEOUS NETWORKS FOR AIRCRAFT|
    US14/884,537| US9876598B2|2014-10-17|2015-10-15|Switch for transmission of data between heterogeneous networks for aircraft|
    CA2909269A| CA2909269A1|2014-10-17|2015-10-16|Switch for transmission of data between heterogeneous networks for aircraft|
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