CN112506459A - Data synchronization method and system for avionics system comprehensive display control unit - Google Patents
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Abstract
The invention relates to the technical field of avionic equipment, in particular to a data synchronization method and a data synchronization system for an avionic system comprehensive display control unit. The system comprises a user interface synchronization management unit, a data center unit, a synchronous data logic processing unit and a synchronous channel, wherein the user interface synchronization management unit is used for setting a synchronization identifier, detecting the data state in the data center unit in real time and informing a user interface of updating and displaying the latest data when the data state in the data center unit changes; the data center unit is used for storing the synchronous key data; the synchronous data logic processing unit is used for data logic processing in the data synchronization system; the synchronous channel is used for exchanging data with the comprehensive display control unit with other redundancy. The data synchronization of the multi-cabin redundancy comprehensive display control unit is realized, and the consistency of key data display in the flight process is ensured.
Description
Technical Field
The invention relates to the technical field of avionic equipment, in particular to a data synchronization method and a data synchronization system for an avionic system comprehensive display control unit.
Background
Modern aircraft usually use a unified processor to process information of various avionics devices on the aircraft uniformly, combine the devices with the same or similar functions in one assembly, display related parameters comprehensively on a display, and transmit related information among the avionics devices through an onboard data bus, so that the performance of all the avionics devices on the whole aircraft reaches a higher level, and such a system is called a comprehensive avionics system.
The integrated avionics system comprises a plurality of functional devices, such as a data interface Unit, a dual-redundancy atmospheric data system, an INS/GNSS integrated navigation system, an integrated radio system, a head-up Display Unit, a cockpit monitoring system and the like, and the devices transmit data to an integrated Display control Unit (DU) through various communication interfaces for Display, and simultaneously a pilot transmits control commands through the DU to control the operation state of the devices, and the DU becomes a key terminal for man-machine interaction between the pilot and airborne devices. In the prior art, in order to ensure the reliability and stability of the system, the DU generally adopts a dual-redundancy active/standby mode, and ensures that the backup redundancy is switched to the main redundancy to work when the main redundancy is hung up. In an aircraft with multiple bays, a DU is usually provided for each bay, for example, in a general-purpose aircraft distributed in the tandem cockpit, one DU is provided in each of the tandem bays, and the pilot controls the onboard equipment via the respective DU, wherein one DU is the primary redundancy and the other DU is the backup redundancy.
Due to the multi-cabin aircraft structure, the DUs are respectively installed in different cabins of the aircraft, and pilots in each cabin operate the respective DUs, so that the DUs on the aircraft are displayed asynchronously, and pictures presented by the DUs for the pilots are inconsistent, thereby influencing flight decisions and flight safety of the pilots. Therefore, the problem of inconsistency of multi-cabin DU data needs to be solved.
Disclosure of Invention
The invention aims to keep the consistency of the display data content of the comprehensive display control unit, ensure that the whole avionics system can normally run when any redundancy or comprehensive display control unit stops working, simultaneously keep the latest display data content when any redundancy or comprehensive display control unit restarts, improve the reliability and stability of the whole avionics system and provide a processing method of man-machine interaction events of a synthetic vision system.
In order to achieve the above object, the present invention adopts the following aspects.
A data synchronization system for an avionics system integrated display control unit comprises a user interface synchronization management unit, a data center unit, a synchronous data logic processing unit and a synchronization channel,
the user interface synchronization management unit is used for setting a synchronization identifier, detecting the data state in the data center unit in real time and informing a user interface to update and display the latest data when the data state in the data center unit changes;
the data center unit is used for storing synchronous key data generated after the redundancy user operates the data center unit and synchronous key data synchronously transmitted after other redundancy user operates the data center unit;
the synchronous data logic processing unit is used for data logic processing in the data synchronization system, and comprises synchronous channel initialization, data transceiving task management and synchronous data request sending;
the synchronous channel is used for exchanging data with the comprehensive display control unit with other redundancy.
As a preferred embodiment of the present invention, the synchronization channel initialization refers to testing initialization parameters of a synchronization channel and creating the synchronization channel.
As a preferred scheme of the invention, the data transceiving task management means that the data receiving and sending are realized by adopting a multi-thread task mode,
the transmission of data refers to: the sending thread sequentially takes out key data to be synchronized from the data center unit of the sending thread, packages the key data to be synchronized to generate a synchronous data packet, selects a synchronous channel and sends the synchronous data packet to the comprehensive display control unit with other redundancies;
the reception of data means: and the receiving thread receives the synchronous data packets sent from other redundancy comprehensive display control units, checks the synchronous data packets after receiving, analyzes the synchronous data packets after successful checking to obtain synchronous updating key data, and updates the data in the data center unit by using the synchronous updating key data.
As a preferred embodiment of the present invention, the sending of the synchronous data request refers to that when the current redundancy integrated display control unit encounters a failure and restarts, the synchronous data logic processing unit packages and generates a request data packet, and periodically sends the request data packet to other redundancy integrated display control units.
Based on the same conception, the invention also provides a data synchronization method for the avionics system comprehensive display control unit, which comprises a synchronous key data sending step and a synchronous key data receiving step, wherein the synchronous key data sending step specifically comprises the following steps:
s1, when the synchronous key data of the redundancy comprehensive display control unit changes, the user interface synchronous management unit acquires the changed synchronous key data and the ID number corresponding to the changed data;
s2, the user interface synchronous management unit updates the data corresponding to the ID number in the data center unit to the latest data, and informs the user interface to update and display the latest data; setting a corresponding synchronization identifier of the key synchronization data according to a preset synchronization channel;
s3, the synchronous data logic processing unit packages the latest synchronous key data and the corresponding ID number into a synchronous data packet according to the preset synchronous channel and the synchronous identification, and sends the synchronous data packet to other redundancy comprehensive display control units through the synchronous channel;
the step of receiving the synchronization critical data specifically comprises the following steps:
a1, when the self redundancy comprehensive display control unit receives the synchronous data packet sent by other redundancy comprehensive display control units, the synchronous data logic processing unit analyzes the synchronous data packet to obtain the synchronous key data, ID number and synchronous identification in the synchronous data packet;
a2, the user interface synchronization management unit controls the data center unit to acquire corresponding synchronization key data from the synchronization data logic processing unit, stores the acquired synchronization key data according to the ID number, and reduces the synchronization identification corresponding to the stored synchronization key data by one, and the user interface synchronization management unit also updates the user interface and displays the latest data according to the received synchronization key data;
a3, the synchronous data logic processing unit determines whether the corresponding synchronous key data needs to be forwarded according to the latest state of the synchronous identifier.
As a preferred scheme of the present invention, if the synchronization identifier is 0 after the synchronization identifier is reduced by one, the key synchronization data corresponding to the synchronization identifier is not sent to the outside; if the synchronous mark is not 0 after the synchronous mark is subtracted by one, the synchronous data logic processing unit encapsulates the received synchronous key data into a synchronous data packet according to a preset synchronous channel and the synchronous mark and sends the synchronous data packet to other redundancy comprehensive display control units.
As a preferred scheme of the invention, when any redundancy comprehensive display control unit is restarted due to a fault, the data synchronization comprises the following steps:
a synchronous data logic processing unit in the redundancy comprehensive display control unit which is restarted in case of a fault packages and generates a request data packet, and the request data packet is periodically sent to other redundancy comprehensive display control units;
after receiving the request data packet, the other redundancy integrated display control units set the synchronization identifier of the packed data to 1 through the user interface synchronization management unit, and pack the data corresponding to the synchronization identifier, the ID number and the ID number into a feedback synchronization data packet, and the synchronization data logic processing unit also sends the feedback synchronization data packet to the redundancy integrated display control unit which is restarted in case of a fault through a channel for receiving the request data packet.
In summary, due to the adoption of the technical scheme, the invention at least has the following beneficial effects:
the key data synchronization system and method for the comprehensive display control unit of the avionic system, provided by the invention, adopt the key technology of synchronous identification and distributed data center design, realize data synchronization of the multi-bay redundancy comprehensive display control unit, ensure the consistency of key data display in the flight process, and enable the rest comprehensive display control units or redundancies to work normally and display key data of other units or redundancies when a certain redundancy or comprehensive display control unit fails, thereby improving the stability and reliability of the whole avionic system.
Drawings
FIG. 1 is a schematic view showing connection of front and rear cabin DU in embodiment 1;
FIG. 2 is a schematic structural diagram of a key data synchronization system for an avionics system integrated display control unit in embodiment 1;
FIG. 3 is a flow chart for synchronization of changes in key data in embodiment 2;
FIG. 4 is a detailed synchronization flowchart of the change of key data in embodiment 2;
fig. 5 is a flowchart of the redundancy restart data synchronization in embodiment 2.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and embodiments, so that the objects, technical solutions and advantages of the present invention will be more clearly understood. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example 1
An aircraft with multiple bays is usually provided with one DU for each bay, for example, a general-purpose aircraft with front and rear cabins is provided with one DU in each of the front and rear cabins, the front cabin DU is referred to as DU1, and the rear cabin DU is referred to as DU2, wherein DU1 further includes a main redundancy and a backup redundancy, respectively referred to as DU1-M, DU1-S, and DU2 also includes a main redundancy and a backup redundancy, respectively referred to as DU2-M, DU 2-S. In general, the main redundancy on each DU device is preferentially displayed, the backup redundancy is run in the background, and when the main redundancy fails, the backup redundancy is automatically switched to.
DU1-M and DU1-S run on front cabin DU equipment at the same time, DU2-M, DU2-S run on rear cabin DU equipment at the same time, DU1-M and DU2-S, DU2-M and DU2-S are connected by Ethernet (without limitation), and the connection between them is called as a main channel and a backup channel. DU1-M and DU2-M, DU1-S and DU2-S are connected using Ethernet (not limited), and the connection between them is called front and back channels. Thus DU1-M, DU1-S, DU2-M, DU2-S forms a ring structure, and the connection of front and rear cabin DU is schematically shown in figure 1.
Data synchronization of individual devices and redundancy is required in two cases, including: 1. when the flight crew operates the DU and certain key data changes; 2. when a certain redundancy encounters a failed restart.
In order to solve the problem that the data of the integrated display control unit of the whole avionic system are inconsistent when the two situations occur based on the front and rear cabin DU connection mode, a key data synchronization system for the integrated display control unit of the avionic system is provided, and the system composition structure schematic diagram is shown in figure 2 and comprises a user interface synchronization management unit, a data center unit, a synchronous data logic processing unit and a synchronization channel.
The user interface synchronization management unit: the unit is used for sending user interface synchronous data, detecting the data state in the data center unit in real time, and informing the user interface to update and display the latest data when the data state in the data center unit changes.
A data center unit: the unit is used for storing all key data needing to be synchronized in the key data synchronization system, including the latest key synchronization data generated after the redundancy user operates the unit and other data synchronized after the redundancy user operates the unit. And providing up-to-date data support for the whole key data synchronization system.
The synchronous data logic processing unit: the unit is used for all data logic processing of a key data synchronization system, including synchronization channel initialization, data transceiving task management and synchronous data request sending.
The synchronous channel is initialized to test various initialized parameters of the synchronous channel and establish the synchronous channel.
In order to improve the system operation efficiency and the data processing capacity, the key data synchronization system for the avionics system comprehensive display control unit realizes data receiving and sending by adopting a multi-thread task mode. The data receiving and sending task management is used for managing task threads in the system, including starting and stopping. The sending thread is responsible for sequentially taking out data to be synchronized from the data center unit, packaging the data to generate a synchronous data packet and sending the data out by using a proper synchronous channel. The receiving thread is responsible for receiving synchronous data packets sent from other redundancies and processing the data, verifying the data after receiving the data, analyzing the data after the verification is successful, and updating the data in the data center unit by using the synchronized data.
And the synchronous data request sending is used for generating a request data packet by packaging the synchronous data logic processing unit when the current redundancy is restarted due to a fault, and periodically sending the data packet to other redundancies until other data respond or the request times are exceeded.
A synchronous channel: the mode for data communication with other redundancies is called a channel herein, and provides support for data exchange for other units of the system, including initialization, opening, closing, sending data, and receiving data.
Example 2
Based on the same conception, the invention also provides a key data synchronization method for the avionics system comprehensive display control unit, which is used for synchronizing the key data in the two situations (1, when a pilot operates the DU and certain key data changes; and 2, when certain redundancy is restarted due to a fault). A detailed description of the implementation of the method when both of these cases occur is provided below.
In the first case, when the pilot operates on the DU, some critical data changes.
When the flight crew operates the DUs and certain key data changes, the current redundancy data is synchronized to other redundancies, for example, the data of DU1-M changes, and then the synchronization data are simultaneously sent to DU1-S and DU2-M respectively. When the master and slave channels are used by the DU1-M to send a synchronization packet to the DU1-S, the synchronization flag is set to 2, after the DU1-S receives the synchronization packet, the master and slave channels are used to reply to the DU1-M with the response packet, and the data synchronization flag is reduced by 1, at this time, the synchronization flag is not 0, the DU1-S continues to send the synchronization packet to the DU2-S using the front and back channels, after the DU2-S receives the synchronization packet, the front and back channels are used to reply to the DU1-S with the data synchronization flag reduced by 1, at this time, the synchronization flag is 0, and the DU2-S does not send synchronization data outwards any more, that is, the data synchronization work of the data link from the DU1-M to the DU1-S is completed.
The principle that DU1-M transfers data to DU2-M is consistent with that DU1-M transfers data to DU 1-S.
The scheme solves the problem that when any redundancy fails, the rest redundancies can synchronize data normally, and the consistency of various key data is kept. The key data change synchronization flow chart is shown in fig. 3.
To further illustrate this scenario, a detailed synchronization flow chart for critical data changes is shown in fig. 4, which illustrates the entire detailed synchronization process for critical data when the pilot is operating with DUs.
step 3, the DU1-M synchronized data logic processing unit periodically detects whether the data synchronization identifier in the data center unit is 0, and if some synchronization identifiers are 0, if the data with ID 1 therein changes, the synchronized data processing unit takes out the data from the data center and encapsulates the data into a synchronized data packet, and periodically sends the synchronized data to DU1-S by using corresponding channels, such as the primary and secondary channels, until receiving the response data fed back by DU1-S or exceeding the set sending times;
step 4, DU1-S also obtains the synchronization data through its own active/standby channel, and after receiving the synchronization data, first sends a response data packet to DU1-M using the active/standby channel, and then analyzes the synchronization data to obtain ID, synchronization identifier and data. And searching data corresponding to the ID stored in the DU1-S data center unit according to the ID, updating by using the received data, setting the updating identifier of the data to be in an updating state, and subtracting 1 from the synchronous identifier of the data. If the synchronous identification is not 0 after subtracting 1, the synchronous data logic processing unit of the current redundancy processes the data according to the step 3, and only needs to switch channels when sending the data;
step 5, the DU1-S user interface synchronization management unit periodically detects the data in the data center unit that are identified as updated and sends these data to the UI for processing and display.
In the second case, when any redundancy is restarted with a failure.
When any redundancy is restarted with a failure, other redundancies should synchronize all changed critical data to that redundancy.
When task redundancy encounters a failed restart, such as a failed restart in DU1-M, the software is in an initialization state, at which time DU1-M periodically sends request packets to DU1-S and DU2-M to request the latest critical data, respectively, until DU1-S or DU2-M responds. And after the DU1-S and the DU2-M receive the request data packet, sequentially packaging the key data stored in the own data center into a synchronous data packet, setting the synchronous identifier as 1, and sending the synchronous data packet to the DU 1-M. DU1-M receives the synchronization packets and replies with response data to other redundancies or devices using the corresponding lanes. The redundancy restart data synchronization flow chart is shown in fig. 5.
The data synchronization flow in this case is further explained. After the DU1-M redundancy is restarted due to a failure, the DU1-M synchronization logic processing unit starts to periodically send request data packets to the DU1-S and the DU2-M respectively until the DU1-S and the DU2-M respond or exceed the set request times. And after the DU1-S and DU2-M receive the request data packet, the data in the own data center are checked, if the own data center has updated data, the synchronization logic processing unit sets the data synchronization identifier of the data center to be 1, and the data are packaged into a synchronization data packet by using a channel for receiving the request data packet and sent to the DU 1-M. And after receiving the synchronous data packet, the DU1-M processes the data, and the subsequent processing flow is consistent with the processing that other redundancies receive the synchronous data packet sent by the current redundancy when the key data is sent and changed.
The units and modules described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units; can be located in one place or distributed on a plurality of network units; some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, all units (for example, each functional unit, processor, memory, and the like) in each embodiment of the present invention may be integrated into one unit, each unit may be separately regarded as one unit, or two or more units may be integrated into one unit; the integrated unit can be realized in a form of hardware, or in a form of hardware plus a software functional unit.
Those skilled in the art will understand that: all or part of the steps for realizing the method embodiments can be completed by hardware related to program instructions, the program can be stored in a computer readable storage medium, and the program executes the steps comprising the method embodiments when executed; and the aforementioned storage medium includes: various media that can store program codes, such as a removable Memory device, a Read Only Memory (ROM), a magnetic disk, or an optical disk.
When the integrated unit of the present invention is implemented in the form of a software functional unit and sold or used as a separate product, it may also be stored in a computer-readable storage medium. Based on such understanding, the technical solutions of the embodiments of the present invention may be essentially implemented or a part contributing to the prior art may be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the methods described in the embodiments of the present invention. And the aforementioned storage medium includes: a removable storage device, a ROM, a magnetic or optical disk, or other various media that can store program code.
The foregoing is merely a detailed description of specific embodiments of the invention and is not intended to limit the invention. Various alterations, modifications and improvements will occur to those skilled in the art without departing from the spirit and scope of the invention.
Claims (7)
1. A data synchronization system for an avionics system integrated display control unit is characterized by comprising a user interface synchronization management unit, a data center unit, a synchronous data logic processing unit and a synchronization channel,
the user interface synchronization management unit is used for setting a synchronization identifier, detecting the data state in the data center unit in real time and informing a user interface to update and display the latest data when the data state in the data center unit changes;
the data center unit is used for storing synchronous key data generated after the redundancy user operates the data center unit and synchronous key data synchronously transmitted after other redundancy user operates the data center unit;
the synchronous data logic processing unit is used for data logic processing in the data synchronization system, and comprises synchronous channel initialization, data transceiving task management and synchronous data request sending;
and the synchronous channel is used for exchanging data with the comprehensive display control unit with other redundancy.
2. The data synchronization system of claim 1, wherein the synchronization channel initialization means testing initialization parameters of the synchronization channel and creating a synchronization channel.
3. The data synchronization system for the avionics system integrated display control unit according to claim 1, wherein the data transceiving task management means receiving and sending data by adopting a multi-thread task mode,
the transmission of data refers to: the sending thread sequentially takes out key data to be synchronized from the data center unit of the sending thread, packages the key data to be synchronized to generate a synchronous data packet, selects a synchronous channel and sends the synchronous data packet to the comprehensive display control unit with other redundancies;
the reception of data means: and the receiving thread receives the synchronous data packets sent from other redundancy comprehensive display control units, checks the synchronous data packets after receiving, analyzes the synchronous data packets after successful checking to obtain synchronous updating key data, and updates the data in the data center unit by using the synchronous updating key data.
4. The data synchronization system of claim 1, wherein the synchronous data request transmission means that when the current redundancy integrated display control unit is restarted due to a fault, the synchronous data logic processing unit generates the request data packet in a packaging manner, and periodically transmits the request data packet to other redundancy integrated display control units.
5. A data synchronization method for an avionics system comprehensive display control unit is characterized by comprising a synchronous key data sending step and a synchronous key data receiving step, wherein the synchronous key data sending step specifically comprises the following steps:
s1, when the synchronous key data of the redundancy comprehensive display control unit changes, the user interface synchronous management unit acquires the changed synchronous key data and the ID number corresponding to the changed data;
s2, the user interface synchronous management unit updates the data corresponding to the ID number in the data center unit to the latest data, and informs the user interface to update and display the latest data; setting a corresponding synchronization identifier of the key synchronization data according to a preset synchronization channel;
s3, the synchronous data logic processing unit packages the latest synchronous key data and the corresponding ID number into a synchronous data packet according to the preset synchronous channel and the synchronous identification, and sends the synchronous data packet to other redundancy comprehensive display control units through the synchronous channel;
the step of receiving the synchronization critical data specifically comprises the following steps:
a1, when the self redundancy comprehensive display control unit receives the synchronous data packet sent by other redundancy comprehensive display control units, the synchronous data logic processing unit analyzes the synchronous data packet to obtain the synchronous key data, ID number and synchronous identification in the synchronous data packet;
a2, the user interface synchronization management unit controls the data center unit to acquire corresponding synchronization key data from the synchronization data logic processing unit, stores the acquired synchronization key data according to the ID number, and reduces the synchronization identification corresponding to the stored synchronization key data by one, and the user interface synchronization management unit also updates the user interface and displays the latest data according to the received synchronization key data;
a3, the synchronous data logic processing unit determines whether the corresponding synchronous key data needs to be forwarded according to the latest state of the synchronous identifier.
6. The data synchronization method for the avionics system integrated display control unit according to claim 5, characterized in that if the synchronization identifier is 0 after the synchronization identifier is subtracted by one, the corresponding synchronization key data of the synchronization identifier is not sent to the outside; and if the synchronous identifier is not 0 after the synchronous identifier is subtracted by one, the synchronous data logic processing unit encapsulates the received synchronous key data into a synchronous data packet according to a preset synchronous channel and the synchronous identifier and sends the synchronous data packet to other redundancy comprehensive display control units.
7. The data synchronization method for the avionics system integrated display control unit according to claim 5 or 6, characterized in that when any redundancy integrated display control unit is restarted due to a fault, the data synchronization comprises the following steps:
a synchronous data logic processing unit in the redundancy comprehensive display control unit which is restarted in case of a fault packages and generates a request data packet, and the request data packet is periodically sent to other redundancy comprehensive display control units;
after receiving the request data packet, the other redundancy integrated display control units set the synchronization identifier of the packed data to 1 through the user interface synchronization management unit, and pack the data corresponding to the synchronization identifier, the ID number and the ID number into a feedback synchronization data packet, and the synchronization data logic processing unit also sends the feedback synchronization data packet to the redundancy integrated display control unit which is restarted in case of a fault through a channel for receiving the request data packet.
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