• 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:
    - System and method for managing the transmission of data on an aircraft. - The data transmission management system (1) comprises a data transmission link (4) which is configured to allow data transmission between a portable electronic device (3) and a flight management system (2). the aircraft, and a data securing module (5) which is configured to automatically perform a data monitoring to be transmitted and to automatically manage a data transmission authorization between the flight management system (2) and the electronic device portable (3), according to said monitoring.
    公开号:FR3013929A1
    申请号:FR1456177
    申请日:2014-06-30
    公开日:2015-05-29
    发明作者:Jean-Claude Mere；Pierre Neri；Julien Bernat；Marc Vie
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a system and method for transmitting data on an aircraft, in particular on a transport aircraft. More specifically, the invention is intended for a transmission (or exchange) of data between a flight management system FMS (for "Flight Management System" in English), of avionic type (that is to say which is secure so as to obey particular constraints of integrity and availability), and a portable electronic device, open world type (that is to say, not sufficiently secure to be integrated as is in the aircraft).
    [0002] More particularly, although not exclusively, this portable electronic device can be an electronic flight device type EFB ("Electronic Flight Bag" in English), or any other laptop or tablet computer, allowing in particular to prepare a flight of the aircraft. It is known that an EFB device contains applications from the airline and / or data computed by the airline which make it possible, during the preparation of a flight or during a flight, to enter adequate data into the aircraft. the FMS system of the aircraft. Security constraints arise during the transmission of data to the FMS system, due to security requirements on the FMS system, which is an electronic sensitive system of the aircraft. In particular, it must be avoided that an attacker in the aircraft can enter data with corrupted codes in the FMS system, or that failed applications can send data that could cause a malfunction of the FMS system to the latter. Therefore, a conventional EFB device is not designed to transmit data to the FMS system. Also, to prepare a flight, the crew of the aircraft copies the data displayed on the screen of the EFB device in the FMS system, via a human / machine interface of the aircraft. Such loading of data presents a significant workload for the crew, further generating a waste of time and a risk of error. The present invention aims to overcome this disadvantage. It relates to a data transmission management system for an aircraft, which comprises: a flight management system, of avionic type; and at least one portable electronic device of the open world type. According to the invention, said data transmission management system further comprises: - a data transmission link which is configured to allow data transmission between the portable electronic device and the flight management system; and a data securing module, which is configured to automatically perform data monitoring to be transmitted and to automatically manage a data transmission authorization between the flight management system and the portable electronic device, according to said monitoring. . Thus, the system according to the invention is able to transmit (or transfer) automatically and securely (thanks to the security module, as specified below) data from the portable electronic device, in particular an EFB device such as above, to the flight management system of the aircraft. This reduces the workload of the crew, thus enabling the crew to save time during the preparation of the aircraft, while being more efficient (in particular avoiding input errors, ....). Preferably, said data securing module comprises: a switching element capable of being controlled, said switching element being configured to be able to be brought alternately into one or the other of two different positions, a first position in which prevents the transmission of data between the portable electronic device and the flight management system via said data transmission link and a second position in which it allows the transmission of data between the portable electronic device and the data management system. flight via said data transmission link; and a monitoring unit comprising at least one security application, the security application being configured to monitor data so as to detect incorrect data, said switching element being controlled to be brought to said first position at least in case of detection of incorrect data by said security application.
    [0003] In the context of the present invention, the term "incorrect data" means an incorrect data flow, data that is not expected (for example on certain flight phases) and / or data to be transmitted after a too long time interval. long following a corresponding request.
    [0004] In a preferred embodiment, the flight management system comprises a core module and an additional module, the monitoring unit being located on the same equipment as one of said two core modules and additional. In addition, advantageously, the system comprises a security software entity, the security software entity comprising at least said security application of said monitoring unit and at least one additional security application, and said security software entity being located on the same equipment as one of said two core and additional modules. Preferably, the monitoring unit comprises: - a data acquisition unit; and - a surveillance partition. Furthermore, in a particular embodiment, the security software entity comprises at least one of the following security applications: an incorrect data flow detection application; - a consistency check and data format application; - an input verification application; and - a data decryption application. In addition, advantageously, the additional module comprises a first software entity in which main additional applications and a second software entity in which at least one additional auxiliary application is implemented, and said system includes a data exchange interface between the main application and a second software entity. security software entity and one of said first and second software entities. Furthermore, advantageously, said switching element is of one of the following types: of the hardware type; - software type.
    [0005] The present invention also relates to a method for managing data transmission on an aircraft between an avionic-type flight management system and an open-world portable electronic device. According to the invention, this method comprises a first step of automatically performing a data monitoring to be transmitted and a second step of automatically managing, according to said monitoring, an authorization for data transmission via a data transmission link between the flight management system and the portable electronic device. In addition, advantageously, the monitoring of the first step consists of checking whether one of the following first conditions is fulfilled: a data stream to be transmitted is incorrect; the aircraft is in a flight phase, for which the data considered are not expected; and - a time greater than a predetermined time value has elapsed since the issuance of a request, and if at least one of these conditions is fulfilled, the second step is to prevent the transmission of data between the system flight management and portable electronic device. Advantageously, the monitoring of the first step also consists of checking whether at least one second condition is fulfilled and, if this second condition is fulfilled, the second step is to issue an alert. Furthermore, advantageously, the method comprises a step of presenting values to a crew member and a validation request, a data transmission being performed only in the event of validation by a crew member. The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements. Fig. 1 is a block diagram of a data transmission management system, which illustrates an embodiment of the invention. FIG. 2 is the block diagram of a particular embodiment of a data transmission management system comprising a flight management system which is provided with a core module and an additional dual entity module. Figures 3 and 4 show schematically means of the system of Figure 1, used for the implementation, respectively, of two different examples, with an indication of the different actions performed. The system 1 shown diagrammatically in FIG. 1 and making it possible to illustrate the invention, is especially intended for the management of a data transmission on an aircraft (not represented), in particular a transport aircraft, between a management system flight 2, avionics type, and a portable electronic device 3, open world type. This portable electronic device (referred to as a "portable device" hereafter) may notably be an Electronic Flight Bag (EFB) type electronic flight device, or any other portable computer or tablet computer, making it possible in particular to prepare a flight of the aircraft.
    [0006] According to the invention, the system 1 comprises, in addition to the flight management system 2 and the electronic device 3: - a data transmission link 4 which is configured to allow data transmission between the electronic device 3 and the system flight management 2; and a data security module 5, which is configured to automatically perform data monitoring to be transmitted and to automatically manage a data transmission authorization between the flight management system 2 and the electronic device 3, according to said monitoring. The data security module 5 comprises: a switching element 6 that can be controlled. This switching element 6 is configured to be brought alternately into one or the other of two different positions, a first position in which it prevents the electronic data transmission between the electronic device 3 and the flight management system 2 via said data transmission link 4 and a second position in which it authorizes the transmission of data via said data transmission link 4; and a monitoring unit (or module) 7 comprising at least one security application A1. This security application A1 is configured to monitor data so as to detect an incorrect data stream. More generally, the monitoring unit 7 is able to detect incorrect data, namely an incorrect data flow, data that is not expected (for example on certain flight phases of the aircraft) and / or data to transmit after an interval of time too long following a corresponding request. In addition, the switching element 6 is controlled to be brought into the first position preventing the transmission of data between the electronic device 3 and the flight management system 2 at least in case of detection of incorrect data. In a preferred embodiment, the system 1 comprises a security software entity 8. This security software entity 8 comprises at least the application Al of the monitoring unit 7, as well as at least one additional security application. , as specified below. Thus, the system 1 is able to transmit (or transfer) automatically and securely (through the data security module 5, as specified below) data between the electronic device 3, in particular an EFB device such as above, and the flight management system 2 of the aircraft, which belong to two worlds well segregated on the aircraft. This reduces the workload of the crew, and thus allows the crew to save time during the preparation of the aircraft, while being more efficient (avoiding in particular input errors, ....) . In a preferred embodiment, the present invention applies to a flight management system 2 comprising, as shown in FIG. 2, a core (or standard) module 10 and an additional (or specific) module 20. The core module 10 and the additional module 20 are hosted on the same IMA equipment or on two separate IMA equipment. The additional module 20 comprises two software entities, a first entity I comprising the main supplementary applications and a second entity II comprising the additional auxiliary applications, as specified below, the two software entities I and II being located on the same IMA equipment. . In addition, the security software entity 8 is located on the same equipment as one of said two core and additional modules. In a first preferred embodiment, the system 1 comprises: a switching element 6 (hardware or software) preferably located outside the flight management system 2 in separate equipment (different hardware element), which makes it possible to block the data before they arrive at the flight management system 2 in the core module 10 or in the additional module 20; and - the surveillance unit (or module) 7.
    [0007] In a less preferred embodiment, it is possible to provide a software switching element implemented in the additional module 20. It is also conceivable to implement the software-type switching element in the heart module 10 of the flight management system 2. In addition, the monitoring unit 7 comprises: a data acquisition function; and a monitoring partition 32. The monitoring partition 32 monitors the CPU utilization of the partition on which the security software entity 8 is hosted (and detects a CPU overhead in the event of a malicious attack).
    [0008] There is a feature that is hosted on a partition that is separate from the two partitions of the additional module 20, and located on the same IMA device as the two software entities of the additional module 20 or on a different IMA device. In the latter case, AFDX communication is provided with the other IMA equipment. The monitoring partition 32 has limited memory and CPU resources to reduce its impact on the specific module. In a preferred variant of this first embodiment, the system 1 comprises the security software entity 8 located on the same IMA device as the two software entities I and II of the additional module 20. It is also conceivable that the software entity 8 is located on the same IMA equipment as the core module 10. This security software entity 8 comprises a plurality of security applications.
    [0009] The connection between the electronic device 3 and the flight management system 2 passes through the security software entity 8, via a bus type A429 or Ethernet. In the particular embodiment shown in FIG. 2, the system 1 comprises a data exchange interface 33 between the security software entity 8 and the software entity I comprising the main additional applications. This data exchange interface 33 manages the communication between the two software entities 8 and I. Furthermore, the switching element 6 is: - either a hardware type switching element. Such a switching element is, for example, a switch (transistor) controlled by the monitoring unit 7 and one or more security applications that isolates the two devices; or a software-type switching element. Such a switching element is a program that automatically cuts the link when a particular condition is detected, for example an incorrect data stream, an erroneous format, etc.
    [0010] The switching element 6 (software or hardware) makes it possible to physically cut the exchange of information between the electronic device 3 and the flight management system 2. The switching element 6 is activated following the detection of the data flow. incorrect data, or on certain phases of flight where the data are not expected, or after a time interval too long following a data request, as specified below. The switching element 6 is controlled by the monitoring unit 7. As indicated above, in a preferred embodiment, the flight management system 2, of the FMS type ("Flight Management System" in English), presents, as represented in FIG. 2, an architecture comprising: the core module 10 (or standard module (or part)) for implementing generic functions relating to the management of the flight of the aircraft; and - the additional module 20 (or module (or part) specific) to implement specific additional functions. The core module 10 and the additional module 20 are linked together by a data exchange interface 30. The core module 10 comprises a set 11 of applications, called generic applications. The execution of each of the generic applications implements a generic function relating to the management of the flight of the aircraft (for example the management of the flight plan, the management of the fuel, etc.). The generic functionalities are either generic basic functions of a flight management system or generic functional services of a flight management system.
    [0011] Furthermore, the additional module 20 comprises a set 21 of additional main software applications, and a set of additional auxiliary software applications 22 each of which is accessible by one or more additional main applications. Each of the additional applications, main or auxiliary, is specific to an entity to which the aircraft belongs, such as a specific aircraft model, a family of aircraft, a company, an alliance, or all or part of a fleet. An auxiliary supplemental application includes one or more computational algorithms and its execution is only intended to provide computational results to one or more major supplementary applications.
    [0012] The execution of each of the main additional applications implements an additional functionality of the additional module 20. The additional functionalities are either new functions with respect to the functions of the core module 10, or functions that are alternatives to the functions of the core module 10 to which they provide behavioral modifications, that is, additional services over services of the heart module 10 that use one or more of these additional functions. The set 21 of additional main applications is implemented in the first software entity I and the set 22 of additional auxiliary applications is implemented in the second software entity II distinct from the first. A software entity is a software partition or software component of a software partition. A software component is a set of lines of code that is functionally or logically consistent and can share common resources with several other components of the same partition. A software partition can host multiple software components. Preferably, the main additional applications and additional auxiliary applications of the additional module 20 are implemented in two software partitions I, II (in accordance with ARINC653) hosted on the same IMA equipment. These two partitions are distinct from each other and are distinct from the software partition carrying the generic functionalities relating to the set 11. The additional module 20 further comprises a data exchange interface 60, provided between the two partitions I and II. The core module 10 also has a generic interface application 16, which, when it is executed, implements an interfacing functionality enabling the core module 10 to interface with the aircraft's onboard systems 40. comprising at least one human / machine interface 41, called generic. Embedded systems 40 may also include embedded devices 42 such as those currently installed in aircraft, for example flight instruments, sensors, etc. The main additional applications may, via the data exchange interface 30 generic and via the generic interface application 16, interface with the generic man / machine interface 41. The additional module 20 also has an interfacing function 26 provided for accessing, via the data exchange interface 30, the interfacing functionality of the core module 10 in order to interface with the human / machine interface. 41 generic. This interfacing functionality 26 of the additional module 20 can also allow direct interfacing with the generic human / machine interface 41, as well as interfacing with a human / machine interface 50 specific to the additional module 20. The or each human interface machine 41, 50 may consist of screens (large, tactile, ...), keyboards, mice, control balls, head-up vision systems, augmented reality systems, ..., and allows especially to the crew to enter data. The core module 10 may further comprise a set of elements, such as a database or a maintenance facility. Thanks to this structure with two distinct modules, the additional functionalities of the additional module 20 are integrated into the flight management system 2 without the need for modifying the software elements of the core module 10 and therefore using the latter, that the functional functions and services it offers (in this case the generic features of a flight management system). Also, these additional functionalities can be developed independently of the core module 10. In addition, the architecture of the additional module 20 on two software entities I and II makes it possible to update these two software entities independently and at different software levels. Thus, additional features of the additional module can be modified only by modifying the algorithms of the additional auxiliary applications. This provides greater industrial flexibility to the additional module 20. Furthermore, in a particular embodiment, the security software entity 8 comprises at least the following security applications as shown in FIG. 1: A / the application Al of data flow detection incorrect. In the first embodiment of the system 1, a dedicated partition is used, and all the data are acquired as they come, by memorizing them, and they are processed in the order of arrival, so that if the transmitter does not respect a time limit between two shipments, the second data is not taken into account. Thus, in case of "flooding", all the CPU time will be used for these acquisitions, thus causing a CPU overload that will be able to be detected by the monitoring partition; B / A2 application for consistency checking and data format. This application A2 compares an expected format to a measured format, according to the category of data considered. Even flight plan data and wind / temperature data with variable content and size have a known and detectable format and dimension. The expected format of the data is encoded in the application software, to prevent an attacker from bypassing the protection. The application A2 behaves like a filter by rejecting data that is not in the correct format or size before it is inserted into the flight management system 2; C / an application A3 for checking the consistency of the input data between the beginning and the end of the transmission; and D / an A4 application for decrypting data. It implements a usual method of calculating a value (CRC) depending on the data considered. The transmitter and the receiver apply the same algorithm to calculate this value, and if the data is sent with its CRC code, the receiver is able to decode the data, recalculate the CRC code and compare the calculated value with that received from the transmitter. Decryption ensures that the data has not been corrupted during the transfer of information, but it does not verify that the data was valid at the origin.
    [0013] The general operation of the system 1 is described below in particular examples relating to two examples of implementation (an "implementation example" is understood to mean a particular application): a first example of implementation ( or first application) concerning the transmission of results of low-speed performance calculations, with reference to FIG. 3; and a second example of implementation (or second application) relating to the transmission of a flight plan, with reference to FIG. 4. These examples are presented on the basis of the first embodiment of the invention 1 specified. above with reference to Figure 1.
    [0014] The switching element 6 is a hardware type switching element, and it is located outside the flight management system 2. Although this is not the case in the example of FIGS. 3 and 4, in FIG. a preferred embodiment, the entity 8 is in a separate partition with the applications A2 (for the example of FIGS. 3 and 4), A3 and A5 (for the example of FIG. 3), in connection with the module 20 through the interface 33 as in Figure 2. Figure 1 shows the detailed architecture for these two examples of implementation, showing in particular the security applications used. These are the following applications: - the application Al of incorrect data flow detection; the A2 consistency check and format application; the application A3 for verifying the coherence of the input data between the beginning and the end of the transmission; and - the A4 application for decrypting data. The applications A1 and A2 are generic, while the application A3 is dedicated to the first implementation example. In addition, the A4 application for decrypting data can be applied to both or none of the exemplary embodiments.
    [0015] The first example of implementation concerns low speed performance calculations (take-off, landing), which are currently not taken into account by the flight management system. These calculations are carried out by an application of the airline and / or the ground crew, which is housed in the electronic device 3. These calculations are made during the preparation of the flight, according to parameters such as wind and the mass of the aircraft, which entered the electronic device 3 by the pilot. In the usual situation, unlike the invention, the results of these calculations are then entered by the pilots in the flight management system, via a man / machine interface during the preparation of the flight. In this first example of implementation, the electronic device 3 comprises a calculation module M1 (for performing the performance calculations at low speed). The application A3 serves to compare the data sent to said calculation module M1 of the electronic device 3 with the same data returned by the calculation module M1 after calculation, to ensure that the data have not been corrupted between the flight management system 2 and the electronic device 3 and that the calculation has been done with the right data. The additional module 20 further comprises an application A5 calculation, specified below which is an additional auxiliary application. A request (message on RAM port or memory sharing) launched by a main application A6 relating to the man / machine interface is addressed to both the application A5 and the module M1. The man / machine interface on which the validation is carried out is either the specific man / machine interface 50 or the generic human / machine interface 41 (shown as a page P for illustration in FIG. 1) . In this first example of implementation, the calculations are carried out in the additional module 20 and in the electronic device 3 (which is considered as an external computer). The data to be transmitted are the results of the calculations of the module M1 of the electronic device 3. These data comprise takeoff data and landing data. More specifically, the takeoff data comprise: data to be loaded into the flight management system 2 (take-off speed, engine configuration, aerodynamic configuration, acceleration, altitude); - Secondary results of crew information, namely additional data provided by the module M1 and not used by the flight management system 2. This data can be displayed in particular on the specific man / machine interface 50; and - calculation inputs for a check. In addition, the landing data includes: - results to be loaded into the flight management system 2 (approach speed, aerodynamic configuration); - secondary results of crew information; and - calculation inputs for a check. Generally, these data are transmitted: - two to four times during the preparation of the flight (takeoff data, and possibly landing data); and - one to two times during the flight (landing data). The monitoring unit (or module) 7 activates the switching element 6 (to authorize the transmission of data) on receipt of a crew calculation request, via the specific man / machine interface 50, and transmits the request to the module M1 in the electronic device 3. The switching element 7 remains activated for a given duration, or until the response to the request has been received and the aircraft is not in operation. flight (except for landing data). Likewise, the monitoring unit 7 can block the transmission by controlling the switching element 6, if it detects an incorrect data format or an abnormal data flow with respect to what is expected. The application A5 implements a simplified calculation algorithm, making it possible to check the consistency of the calculation provided by the module M1. This calculation is less accurate than the calculation of the module Ml, but it is only used to generate an alert in case of significant difference.
    [0016] In addition: - the application A2 checks the volume and format of the data compared to what is expected (integer, character, ...); and the application Al monitors the rate (utilization rate of the CPU).
    [0017] The first example of implementation (or first application) may present, in a particular embodiment, the following successive steps E1 to E10, as shown in FIG. 3: El / the crew uses the human interface / standard machine 41 (associated with an application A7), as illustrated by a finger 34 acting on an interface element 35, to request the application A6 of the specific module 20 to display the corresponding specific page P1; E2 / page P1 is displayed on the specific man / machine interface 50; E3 / the crew checks and adjusts if necessary the data that will be used for the calculation, and it triggers the calculation on the specific man / machine interface 50; E4 / the application A6 sends a request to the calculation module M1 hosted in the electronic device 3 and closes the switching element (or asks the monitoring unit 7 to close it). This request contains all the data, reviewed and possibly adjusted by the crew, which are necessary for the calculation. The calculation module M1 in the electronic device 3 receives these data and performs (in the usual way) the corresponding calculations of low speed performance; E5 / the calculation results, as well as the input data, are sent to the application A6 via the switching element and the monitoring unit 7.
    [0018] In this case, if one of the following conditions is fulfilled, the monitoring unit 7 rejects the data or controls the switching element to block the transmission. A message may be provided back to the electronic device 3 to request a sending again. These conditions are: - no answer is received in a given time; or - the aircraft takes off (for take-off data only); or - the format / size or data flow is not what is expected. In addition: - if the format / volume or stream is correct, but the input data returned by the module M1 do not match those that were sent with the request, an alert is issued to indicate to the crew that the results do not necessarily correspond to what is expected, because of a transmission error; and - if the results are not consistent with calculations made by the A5 application, an alert is also issued to warn the crew; E6 / the results are displayed on a P2 page on the specific man / machine interface 50 for validation by the pilot; E7 / the pilot uses the specific man / machine interface 50 to request to send the values once they are validated to the flight management system 2; E8 / the values are taken into account by an application A8 flight plan; E9 / the new data is displayed on a page P3 on the standard human / machine interface 41; and E10 / the driver confirms the new data using the standard man / machine interface 41. This step El 0 is optional. Moreover, the second implementation example (or second application) concerns the transmission of a flight plan. It is relative to a calculated flight plan CFP 15 (for "Computerized Flight Plan"). In this second example of implementation, the electronic device 3 is considered as a database. Usually, the airline provides the flight plan to the pilot and / or ground crew preparing the aircraft prior to the flight. The flight plan is loaded into the electronic device 3 (via a floppy disk, a USB key or via wifi for example) before the flight, then it is entered during the preparation of the flight in the flight management system via an interface. man / machine (contrary to the present invention). No calculation is made because all the data is stored in a memory M2 of the electronic device 3. In this second embodiment, the data to be transmitted are in particular the following data contained in the electronic device 3: - the initial data of the flight (departure airport, flight number, date, estimated time of departure); - the planning of the fuel and the mass of the aircraft; The flight plan (including a sequence of procedures, corridors, crossing points, ...); and - wind and temperature along the flight plan.
    [0019] Generally, these data are entered once or twice during the preparation of the flight. This second example of implementation can present, in a particular embodiment, the following successive steps F1 to F9, as shown in FIG. 4: F1 / an operator of the airline or a member of the flight crew. the aircraft enters at least some of the aforementioned data in the electronic device 3 during the preparation of the flight; F2 / a crew member uses the standard man / machine interface 41 (page P4) 10 to request an A9 application (CFP calculated flight plan loading) from the additional module 20 of the flight management system 2. send a request to the electronic device 3; F3 / the application A9 sends a simple request to the electronic device 3 and closes the switching element to authorize the transmission (or asks the monitoring unit 7 to close it); F4 / the electronic device 3 sends the data from the memory M2 to the application A9, via the switching element and the monitoring unit 7. In this case, if one of the following conditions is fulfilled, the unit The monitoring station 7 rejects the data or controls the switching element to block the transmission. A message may be provided back to the electronic device 3 to request a sending again. These conditions are: - no answer is received in a given time; or - the airplane takes off; or 25 - format / size or data flow is not what is expected. F5 / the results are displayed on the specific man / machine interface 50 (page P5) for pilot validation; F6 / the pilot decides to send the values once validated to the flight management system 2 for their consideration and their display in the standard part; F7 / the values are transmitted to the flight plan application A8 for their integration in a secondary flight plan for example; F8 / secondary flight plan data is displayed on the standard man / machine interface 41 (page P6); and F9 / the pilot confirms the new data using this standard man-machine interface 41 so as to activate the secondary flight plan. Furthermore, in an alternative embodiment, the applications A2, A3 and A4 in particular can make the additional module 20 or the core module 10, in place of the entity 8. In addition, in a particular embodiment, a switch manual is implemented on the link between the flight management system 2 and the electronic device 3, so that the pilot (s) can (s) cut the link manually on detection of a particular condition.
    [0020] Furthermore, in a second embodiment of the invention, the system 1 comprises: a switching element preferably located outside the flight management system in a separate device, which makes it possible to block the data before they arrive at the specific module, or, in a less preferred variant, a software switching element implemented in the specific part; and a monitoring unit (or module), comprising at least the incorrect data flow detection application (ie a primary supplementary application). This application is hosted in the security software entity, if the system includes such a security software entity, and its function is to limit the data acquisition depth and control the flow so as to ignore data. that do not match the expected flow. In a particular variant of this second embodiment, the system 1 further comprises a security software entity. This security software entity comprises a plurality of security applications as mentioned above, which are additional principal applications of the software entity I. Moreover, in this second embodiment of the system 1, concerning the application of detection of incorrect data flow, located on the same partition as the other functionalities of the flight management system 2, it is limited, at the level of the application, the depth of the receiving ports to 1 and we control the period of data acquisition . This has the effect of ignoring too frequent data, by spending only a limited time on acquisitions.
    [0021] The system 1, as described above, has in particular the advantages indicated below. The security software entity 8 is implemented in a software entity different from the other two software entities I and II of the additional module 20, with CPU / memory resources restricted and monitored, so as not to affect their functions. Thus, the segregation of the security applications of the other applications of the flight management system 2 effectively protects the flight management system 2 against the introduction of malicious code in said flight management system 2 or the introduction of data. incorrect.
    [0022] A data flow transmission may be blocked upstream of the flight management system 2 (by the switching element 6), if the incorrect data flow detection application Al detects a problem or the Monitoring 7 detects over-activity of partitions. In the security software entity 8, the other security applications make it possible to block the transmission to the specific module 20 of incorrect data, that is to say invalid or non-coherent (functionally) data. This concerns only a part of this data, the other part being detected during the validation by the pilot. The system 1 makes it possible to avoid a "flooding" or to cut the link, when no data transmission is provided, which makes it possible to protect the flight management system 2 from any unwanted attack or data transfer. Indeed, the link for the transmission of data between the electronic device 3 and the flight management system 2 is available only when necessary, and it is unavailable for the rest of the time, in order to avoid unwanted data transmissions. to the flight management system 2 during the flight. On the other hand, the switching element 6 makes it possible to authorize the transmission of data for a short period of time. It allows: - to block the transmission of data after this short period of time or when the expected response of the electronic device 3 has been received (the data can no longer be transmitted, and are not yet in the buffer); and - to block the transmission in the event of reception of an incorrect frame from the electronic device 3 or when the monitoring unit detects an abnormal CPU usage (which may correspond to the reception of a large unexpected amount of data). The connection between the electronic device 3 and the flight management system 2 is performed via the security software entity 8 which acts as a buffer zone.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. A data transmission management system for an aircraft, said system (1) comprising: - a flight management system (2), of avionic type; and at least one portable electronic device (3), of open-world type, characterized in that it furthermore comprises: a data transmission link (4) which is configured to allow data transmission between the electronic device portable (3) and the flight management system (2); and a data securing module (5), which is configured to automatically perform a data monitoring to be transmitted and to automatically manage a data transmission authorization between the flight management system (2) and the portable electronic device ( 3), according to said monitoring.
    [0002]
    2. System according to claim 1, characterized in that said data securing module (5) comprises: a switching element (6) able to be controlled, said switching element (6) being configured so that it can be brought alternately in one or the other of two different positions, a first position in which it prevents the transmission of data between the portable electronic device (3) and the flight management system (2) via said data transmission link ( 4) and a second position in which it allows the transmission of data between the portable electronic device (3) and the flight management system (2) via said data transmission link (4); and - a monitoring unit (7) comprising at least one security application (A1), the security application (A1) being configured to monitor data so as to detect incorrect data, said switching element (6) being controlled to be brought into said first position at least in case of detection of incorrect data by said security application (A1).
    [0003]
    3. System according to claim 2, characterized in that the flight management system (2) comprises a core module (10) and an additional module (20), the monitoring unit (7) being located on the same equipment than one of said two core and additional modules (10, 20).
    [0004]
    4. System according to claim 3, characterized in that it comprises a security software entity (8), the security software entity (8) comprising at least said security application (A1) of said monitoring unit (7). ) and at least one additional security application (A2 to A4), and said security software entity (8) being located on the same equipment as one of said two core and additional modules (10, 20).
    [0005]
    5. System according to claim 4, characterized in that the security software entity (8) comprises at least one of the following security applications: - an application (A1) for incorrect data flow detection; an application (A2) for consistency checking and data format; an application (A3) for verifying entries; and an application (A4) for decrypting data.
    [0006]
    6. System according to one of claims 4 and 5, characterized in that the additional module (20) comprises a first software entity (I) in which are implemented additional main applications and a second software entity (II) in which is implemented at least one additional auxiliary application, and in that said system (1) comprises a data exchange interface (33) between the security software entity (8) and one of said first and second software entities (I , II).
    [0007]
    7. System according to any one of claims 2 to 6, characterized in that the monitoring unit (7) comprises: - a data acquisition unit; and - a surveillance partition (32).
    [0008]
    8. System according to any one of the preceding claims, characterized in that said switching element (6) is of one of the following types: - of hardware type; - software type.
    [0009]
    9. A method for managing data transmission on an aircraft between an avionics-type flight management system (2) and an open-world portable electronic device (3), characterized in that it comprises a first step of automatically performing data monitoring to be transmitted and a second step of automatically managing, according to said monitoring, a data transmission authorization via a data transmission link (4) between the flight management system (2). ) and the portable electronic device (3).
    [0010]
    10. Method according to claim 9, characterized in that the monitoring of the first step consists in checking whether one of the following first conditions is fulfilled: a data stream to be transmitted is incorrect; the aircraft is in a flight phase, for which the data considered are not expected; and - a time greater than a predetermined time value has elapsed since the issuance of a request, and if at least one of these conditions is fulfilled, the second step is to prevent the transmission of data between the system flight management system (2) and the portable electronic device (3).
    [0011]
    11. Method according to one of claims 9 and 10, characterized in that the monitoring of the first step is also to check if at least a second condition is met and, if this second condition is met, the second step is to issue an alert.
    [0012]
    12. Method according to any one of claims 9 to 11, characterized in that it comprises a step of presenting values to a crew member and validation request, a data transmission being performed only in case of validation. by a crew member.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20150150095A1|2015-05-28|
    US9529356B2|2016-12-27|
    US9709982B2|2017-07-18|
    CN104670509B|2016-10-05|
    FR3013880B1|2017-03-31|
    FR3013881B1|2021-01-29|
    US9323248B2|2016-04-26|
    CN104680852A|2015-06-03|
    CN104670509A|2015-06-03|
    FR3013881A1|2015-05-29|
    US10216180B2|2019-02-26|
    US20150148996A1|2015-05-28|
    US20150148998A1|2015-05-28|
    CN104670508A|2015-06-03|
    FR3013929B1|2017-11-24|
    CN104683142A|2015-06-03|
    CN104680852B|2017-01-18|
    CN104683142B|2018-02-06|
    US9606534B2|2017-03-28|
    FR3013831A1|2015-05-29|
    FR3013880A1|2015-05-29|
    US20170147008A1|2017-05-25|
    US20150148999A1|2015-05-28|
    CN104670508B|2017-01-11|
    FR3013831B1|2018-03-02|
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    法律状态:
    2015-06-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-27| PLFP| Fee payment|Year of fee payment: 3 |
    2017-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-06-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1361660A|FR3013880B1|2013-11-26|2013-11-26|AVIONIC SYSTEM, IN PARTICULAR AN AIRCRAFT FLIGHT MANAGEMENT SYSTEM|
    FR1453296A|FR3013831B1|2013-11-26|2014-04-14|AVIONIC SYSTEM OF AN AIRCRAFT|
    FR1456177A|FR3013929B1|2013-11-26|2014-06-30|SYSTEM AND METHOD FOR MANAGING DATA TRANSMISSION ON AN AIRCRAFT.|FR1456177A| FR3013929B1|2013-11-26|2014-06-30|SYSTEM AND METHOD FOR MANAGING DATA TRANSMISSION ON AN AIRCRAFT.|
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    US14/553,345| US9529356B2|2013-11-26|2014-11-25|Data management system of an aircraft|
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