A method, apparatus, computer device and medium for monitoring communication

Abstract

This invention provides a method and apparatus for monitoring communication. The method includes the following steps: a flight control computer sends a heartbeat synchronization signal to an actuator control electronics device via a data bus; upon receiving the heartbeat synchronization signal, the actuator control electronics device generates a random heartbeat number and sends it to the flight control computer via the data bus; the flight control computer wraps the received random heartbeat number back to the actuator control electronics device; the actuator control electronics device receives the wrapped random number from the flight control computer and determines the communication status between the flight control computer and the actuator control electronics device based on the consistency between the random heartbeat number and the wrapped random number. This method enables timely response and isolation of communication failures between the actuator control electronics device and the flight control computer, ensuring flight safety after a failure and ultimately improving the safety of the flight control system.

Description

Technical Field

[0001] This invention relates to the field of communication monitoring technology, and in particular to a method, apparatus, computer equipment, and medium for monitoring communications. Background Technology

[0002] In current fixed-wing aircraft main flight control systems, the monitoring of communication between the flight control computer and the actuator control electronics is achieved through hardware circuits. Traditional hardware circuits can only generate pseudo-random numbers with only two values: high or low. In some cases, after a fault occurs, the comparison result may still appear normal for a certain period of time, making it impossible to detect the fault and respond promptly. Furthermore, once the hardware circuit design is completed, parameters such as the monitoring time threshold cannot be changed, resulting in high modification cycles and costs. Summary of the Invention

[0003] In view of this, embodiments of the present invention provide a method for monitoring system communication to solve the technical problems of existing hardware circuits being unable to detect faults and respond in a timely manner, being unable to change monitoring time thresholds and other parameters after completion, and having high modification cycles and costs. The method includes:

[0004] The flight control computer sends heartbeat synchronization signals to the actuator control electronics via a data bus.

[0005] When the actuator control electronics receives the heartbeat synchronization signal within a preset number of bus communication cycles, the actuator control electronics generates a random heartbeat number through software at the rising edge of each heartbeat synchronization signal and sends the random heartbeat number to the flight control computer through the data bus. The heartbeat synchronization signal is a square wave signal that flips according to a preset cycle.

[0006] The flight control computer feeds the received random heartbeat number back to the actuator control electronics.

[0007] The actuator control electronics receive the random number looped from the flight control computer and determine the communication status between the flight control computer and the actuator control electronics based on the consistency between the heartbeat random number and the looped random number.

[0008] This invention also provides a communication device for a monitoring system to solve the technical problems of existing hardware circuits being unable to detect faults and respond in a timely manner, being unable to change monitoring parameters such as time thresholds after completion, and having high modification cycles and costs. The device includes:

[0009] The heartbeat synchronization signal transmission and reception module is used by the flight control computer to send heartbeat synchronization signals to the actuator control electronics via the data bus.

[0010] The heartbeat random number generation and transmission module is used to generate a heartbeat random number through software at the rising edge of each heartbeat synchronization signal when the actuator control electronics receives the heartbeat synchronization signal within a preset number of bus communication cycles, and send the heartbeat random number to the flight control computer through the data bus. The heartbeat synchronization signal is a square wave signal that flips according to a preset period.

[0011] The random number generation and transmission module is used by the flight control computer to rewind the received heartbeat random numbers to the actuator control electronics.

[0012] The communication status confirmation module is used for the actuator control electronics to receive the random number looped by the flight control computer and determine the communication status between the flight control computer and the actuator control electronics based on the consistency between the heartbeat random number and the looped random number.

[0013] This invention also provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements any of the above-mentioned monitoring system communication methods, thereby solving the technical problems in the prior art.

[0014] This invention also provides a computer-readable storage medium storing a computer program that executes any of the above-described monitoring system communication methods, thereby solving the technical problems in the prior art.

[0015] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0016] This paper proposes a method for monitoring the communication between the actuator control electronics system and the flight control computer using software. This method avoids the shortcomings of previously used hardware circuit techniques. While monitoring the effectiveness of communication between the actuator control electronics and the flight control computer, it reduces circuit design complexity, lowers circuit costs, improves fault response speed, enhances flight safety, and allows for adjustment of monitoring parameters to adapt to different application scenarios. The communication monitoring method in this embodiment enables timely response and isolation of faults in the communication between the actuator control electronics and the flight control computer, ensuring flight safety after a fault occurs. Ultimately, this improves the safety of the flight control system and ensures the scalability and robustness of the flight control computer program and the actuator control electronics program. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a flowchart of a monitoring system communication method provided in an embodiment of the present invention;

[0019] Figure 2 It is a hardware circuit diagram for monitoring the communication between the flight control computer and the actuator control electronics.

[0020] Figure 3 This is a flowchart illustrating the communication between the flight control computer and the actuator control electronic device according to an embodiment of the present invention.

[0021] Figure 4 This is a flowchart illustrating the monitoring of flight control computer communication via actuator-controlled electronic devices according to an embodiment of the present invention;

[0022] Figure 5 This is a structural block diagram of a computer device provided in an embodiment of the present invention;

[0023] Figure 6 This is a structural block diagram of a monitoring system communication construction device provided in an embodiment of the present invention. Detailed Implementation

[0024] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0025] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] In the main flight control system of a fixed-wing aircraft, digital communication is required between the Flight Control Computer (FCC) and the Actuator Control Electronics (ACE). Typically, monitoring of this communication is achieved through hardware circuitry. The monitoring principle is as follows:

[0027] like Figure 4 As shown, the flight control computer software sends a heartbeat synchronization signal to the actuator control electronics via the data bus. The actuator control electronics software parses this signal according to the communication protocol and sends it to the hardware monitor. If the watchdog timer does not receive the signal within a certain time, it latches a heartbeat monitoring fault and sends a valid monitoring signal (HB-VALID) to the flight control computer. After receiving the fault signal, the flight control computer pauses sending the heartbeat synchronization signal for a certain period of time, and then resynchronizes to allow the actuator control electronics to resume communication with the flight control computer. After the actuator control electronics monitor receives the rising edge of the heartbeat synchronization signal, it generates a random heartbeat number (HB-DATA) through a hardware circuit pseudo-random number generator and sends it to the flight control computer. The flight control computer wraps the received random number back to the actuator control electronics (HB-ECO) and compares the previous HB-DATA with HB-ECO through a comparator. If the two values ​​are equal, the comparator outputs a high level, indicating that the actuator control electronics and the flight control computer are communicating normally. Otherwise, it outputs a low level, indicating that the actuator control electronics and the flight control computer are communicating malfunctioning.

[0028] However, the hardware circuit can only generate pseudo-random numbers with either a high or low level. In some cases, after a fault occurs, the comparison result may still appear normal for a certain period of time, making it impossible to detect the fault and respond promptly. Furthermore, once the hardware circuit design is complete, parameters such as the monitoring time threshold cannot be changed, and modifications are time-consuming and costly.

[0029] Therefore, in this embodiment of the invention, a method for monitoring system communication is provided, such as... Figure 2 and Figure 3 As shown, the technical solution of this method is as follows:

[0030] 1. The flight control computer sends a heartbeat synchronization signal to the actuator control electronics via the data bus. If the actuator control electronics does not receive the heartbeat synchronization signal within a preset number of bus communication cycles, it actively sends a monitoring failure result to the flight control computer. If the flight control computer still receives a monitoring failure result or does not receive the heartbeat random number reported by the actuator control electronics after sending multiple heartbeat synchronization signals consecutively, then there is a communication failure between the flight control computer and the actuator control electronics.

[0031] 2. After receiving the heartbeat synchronization signal, the actuator control electronics generates a random number through software and sends it to the flight control computer. The flight control computer then wraps the received random number back to the actuator control electronics. The actuator control electronics compares the random number with the wrapped number. If they match, the communication between the flight control computer and the actuator control electronics is normal; otherwise, the communication is faulty.

[0032] In this embodiment of the invention, the communication principle of the flight control computer monitoring system is as follows:

[0033] After establishing a communication connection with the actuator control electronics via the data bus, the flight control computer sends a heartbeat synchronization signal that flips at a specific cycle to the actuator control electronics. If the actuator control electronics does not receive this signal within a preset number of bus communication cycles, it actively sends a monitoring failure result to the flight control computer. After receiving the monitoring failure result, the flight control computer delays for 500ms and then continues to send the heartbeat synchronization signal, resetting the actuator control electronics and allowing it to return to normal operation. If the flight control computer continuously sends multiple heartbeat synchronization signals (square wave signals that flip according to a preset cycle) and still receives a monitoring failure result, or fails to receive the heartbeat random number reported by the actuator control electronics, it considers the communication between the flight control computer and the actuator control electronics to be faulty. If the flight control computer can receive the random number signal and the monitoring normal result sent by the actuator control electronics, it considers the communication to be normal.

[0034] In some implementations, the preset number of bus communication cycles is 10 bus communication cycles.

[0035] Depend on Figure 2 As shown in the flowchart, the specific communication of the flight control computer monitoring system includes the following steps:

[0036] The flight control computer sends heartbeat synchronization signals to the actuator control electronics via a data bus.

[0037] If the flight control computer sends multiple heartbeat synchronization signals to the actuator control electronics in succession, but does not receive a signal indicating normal communication from the actuator control electronics, or does not receive a random heartbeat number from the actuator control electronics, then the flight control computer determines that there is a communication failure between the flight control computer and the actuator control electronics.

[0038] The flight control computer feeds the received random heartbeat number back to the actuator control electronics.

[0039] In this embodiment of the invention, the communication principle of the actuator control electronic device monitoring system is as follows:

[0040] After receiving a heartbeat synchronization signal with a specific cycle from the flight control computer, the actuator control electronics (ECU) generates a random heartbeat number through its internal software and sends it to the flight control computer via the data bus. The flight control computer then wraps the received random number back to the ECU. The ECU compares its sent random heartbeat number with the wrapped random heartbeat number. If they match, communication between the ECU and the flight control computer is normal. If they do not match, a communication failure occurs. The ECU suspends receiving commands from the flight control computer for 100 bus communication cycles (one heartbeat cycle is two bus communication cycles), and then re-attempts to communicate with the flight control computer. If it receives the flight control computer's heartbeat synchronization signal and the heartbeat monitoring is normal, the ECU can resume communication and receive commands. If it still cannot receive the flight control computer's heartbeat synchronization signal, the ECU will disconnect from the flight control computer's commands and directly receive cockpit control commands.

[0041] Depend on Figure 3 As shown in the flowchart, the communication between the actuator control electronics monitoring system and the system specifically includes the following steps:

[0042] When the actuator control electronics receives the heartbeat synchronization signal within a preset number of bus communication cycles, the actuator control electronics generates a random heartbeat number through software at the rising edge of each heartbeat synchronization signal and sends the random heartbeat number to the flight control computer through the data bus. The heartbeat synchronization signal is a square wave signal that flips according to a preset cycle.

[0043] If the actuator control electronics fails to receive a heartbeat synchronization signal within a preset number of bus communication cycles, the actuator control electronics will determine that there is a communication failure between the flight control computer and the actuator control electronics, and will send a signal indicating the communication failure to the flight control computer.

[0044] The actuator control electronics receive the random number looped from the flight control computer and determine the communication status between the flight control computer and the actuator control electronics based on the consistency between the heartbeat random number and the looped random number.

[0045] If the heartbeat random number and the looping random number are inconsistent for three consecutive times, the actuator control electronics will determine that there is a communication failure between the flight control computer and the actuator control electronics, and will send a signal indicating the communication failure to the flight control computer.

[0046] In this embodiment of the invention, when a communication failure occurs, the following process is adopted:

[0047] After the actuator control electronics determines that there is a communication failure between the flight control computer and the actuator control electronics, the actuator control electronics suspends receiving flight control commands from the flight control computer.

[0048] After the actuator control electronics pauses receiving flight control commands from the flight control computer for 100 bus communication cycles, it resumes receiving the heartbeat synchronization signal from the flight control computer.

[0049] If a heartbeat synchronization signal is received, the actuator control electronics determine that communication between the flight control computer and the actuator control electronics has been restored, and receive flight control commands issued by the flight control computer.

[0050] If a heartbeat synchronization signal is not received, the actuator control electronics will cut off the flight control commands issued by the flight control computer and directly receive the flight control commands issued by the cockpit.

[0051] In this embodiment, a computer device is provided, such as... Figure 5 As shown, it includes a memory 501, a processor 502, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the communication method of any of the monitoring systems described above.

[0052] Specifically, the computer device can be a computer terminal, a server, or a similar computing device.

[0053] In this embodiment, a computer-readable storage medium is provided, which stores a computer program that executes any of the above-described monitoring system communication methods.

[0054] Specifically, computer-readable storage media include both permanent and non-permanent, removable and non-removable media that can store information using any method or technology. Information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer-readable storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic magnetic disk storage or other magnetic storage devices, or any other non-transferable medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media does not include transient media, such as modulated data signals and carrier waves.

[0055] Based on the same inventive concept, this invention also provides a monitoring system communication device, as described in the following embodiments. Since the principle by which the monitoring system communication device solves the problem is similar to that of the monitoring system communication method, the implementation of the monitoring system communication device can refer to the implementation of the monitoring system communication method, and repeated details will not be elaborated further. As used below, the terms "unit" or "module" can refer to a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0056] Figure 6 This is a structural block diagram of a monitoring system communication device according to an embodiment of the present invention, such as... Figure 6 As shown, it includes:

[0057] Heartbeat synchronization signal transmission and reception module 01 is used by the flight control computer to send heartbeat synchronization signals to the actuator control electronics via the data bus;

[0058] The heartbeat random number generation and transmission module 02 is used to generate a heartbeat random number through software at the rising edge of each heartbeat synchronization signal when the actuator control electronic device receives the heartbeat synchronization signal within a preset number of bus communication cycles, and send the heartbeat random number to the flight control computer through the data bus. The heartbeat synchronization signal is a square wave signal that flips according to a preset period.

[0059] The random number generation and transmission module 03 is used by the flight control computer to rewind the received heartbeat random number to the actuator control electronics.

[0060] The communication status confirmation module 04 is used for the actuator control electronics to receive the random number cyclically generated by the flight control computer, and to determine the communication status between the flight control computer and the actuator control electronics based on the consistency between the heartbeat random number and the cyclically generated random number.

[0061] In one embodiment, the heartbeat synchronization signal transmitting and receiving module 01 includes:

[0062] The first communication fault judgment unit is used to determine that there is a communication fault between the flight control computer and the actuator control electronics if the actuator control electronics does not receive a heartbeat synchronization signal within a preset number of bus communication cycles, and then sends a signal indicating the communication fault to the flight control computer.

[0063] In one embodiment, the heartbeat random number generation and sending module 02 includes:

[0064] The second communication fault judgment unit is used to determine that there is a communication fault between the flight control computer and the actuator control electronics if the flight control computer fails to receive a signal indicating normal communication from the actuator control electronics after continuously sending multiple heartbeat synchronization signals to the actuator control electronics, or fails to receive a random heartbeat number from the actuator control electronics.

[0065] In one embodiment, the communication status confirmation module 04 includes:

[0066] The communication status judgment unit is used to determine that if the heartbeat random number and the looping random number are inconsistent for three consecutive times, the actuator control electronics device will determine that there is a communication failure between the flight control computer and the actuator control electronics device, and send a signal indicating the communication failure to the flight control computer.

[0067] The waiting-to-re-communication unit is used to, when the communication between the flight control computer and the actuator control electronics fails, suspend the receiving of flight control commands from the flight control computer for 100 bus communication cycles, and then resume receiving the heartbeat synchronization signal from the flight control computer.

[0068] The communication recovery execution unit is used to determine that communication between the flight control computer and the actuator control electronics has been restored if a heartbeat synchronization signal is received, and to receive flight control commands issued by the flight control computer.

[0069] The communication cut-off execution unit is used to cut off the flight control commands issued by the flight control computer and directly receive the flight control commands issued by the cockpit if a heartbeat synchronization signal is not received.

[0070] In another embodiment, software is also provided for executing the technical solutions described in the above embodiments and preferred embodiments.

[0071] In another embodiment, a storage medium is also provided, which stores the above-mentioned software. The storage medium includes, but is not limited to, optical discs, floppy disks, hard disks, and rewritable memory.

[0072] The embodiments of the present invention achieve the following technical effects:

[0073] This paper proposes a method for monitoring the communication between the actuator control electronics system and the flight control computer using software. This method avoids the shortcomings of previously used hardware circuit techniques. While monitoring the effectiveness of communication between the actuator control electronics and the flight control computer, it reduces circuit design complexity, lowers circuit costs, improves fault response speed, enhances flight safety, and allows for adjustment of monitoring parameters to adapt to different application scenarios. This communication monitoring method enables timely response and isolation of faults in the communication between the actuator control electronics and the flight control computer, ensuring flight safety after a fault occurs. Ultimately, it improves the safety of the flight control system and ensures the scalability and robustness of the flight control computer program and the actuator control electronics program.

[0074] Obviously, those skilled in the art should understand that the modules or steps of the above-described embodiments of the present invention can be implemented using general-purpose computing devices. They can be centralized on a single computing device or distributed among various computing devices.

[0075] Distributed across a network of multiple computing devices, these devices may optionally be implemented using computer-executable program code, thereby allowing them to be stored in a storage device for execution by the computing device. Furthermore, in some cases, the steps shown or described may be performed in a different order than those described herein, or they may be implemented as separate integrated circuit modules, or multiple modules or steps may be implemented as a single integrated circuit module. Thus, embodiments of the present invention are not limited to any particular hardware and software combination.

[0076] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for communication in a monitoring system, characterized in that, include: The flight control computer sends a heartbeat synchronization signal to the actuator control electronics via a data bus. When the actuator control electronics receives the heartbeat synchronization signal within a preset number of bus communication cycles, the actuator control electronics generates a random heartbeat number through software at the rising edge of each heartbeat synchronization signal and sends the random heartbeat number to the flight control computer through the data bus. The heartbeat synchronization signal is a square wave signal that flips according to a preset period. The flight control computer will receive the random heartbeat number and then feed it back to the actuator control electronics. The actuator control electronics receive the random number cyclically generated by the flight control computer and determine the communication status between the flight control computer and the actuator control electronics based on the consistency between the heartbeat random number and the cyclically generated random number.

2. The method for communication in a monitoring system as described in claim 1, characterized in that, Also includes: If the actuator control electronics fails to receive the heartbeat synchronization signal within a preset number of bus communication cycles, the actuator control electronics determines that there is a communication failure between the flight control computer and the actuator control electronics, and sends a signal indicating the communication failure to the flight control computer.

3. The method for communication in a monitoring system as described in claim 1, characterized in that, Also includes: If the flight control computer sends multiple heartbeat synchronization signals to the actuator control electronics and does not receive a signal indicating normal communication from the actuator control electronics, or does not receive the random heartbeat number from the actuator control electronics, then the flight control computer determines that there is a communication failure between the flight control computer and the actuator control electronics.

4. The method for communication in a monitoring system as described in claim 1, characterized in that, Based on the consistency between the heartbeat random number and the looping random number, the communication status between the flight control computer and the actuator control electronics is determined, including: If the heartbeat random number and the looping random number are inconsistent for three consecutive times, the actuator control electronics determine that there is a communication failure between the flight control computer and the actuator control electronics, and sends a signal indicating a communication failure to the flight control computer.

5. The method for communication of a monitoring system as described in any one of claims 1 to 4, characterized in that, Also includes: After the actuator control electronics determines that there is a communication failure between the flight control computer and the actuator control electronics, the actuator control electronics suspends receiving flight control commands issued by the flight control computer.

6. The method for communication in a monitoring system as described in claim 5, characterized in that, Also includes: When the flight control computer fails to communicate with the actuator control electronics, the actuator control electronics will suspend receiving the flight control commands issued by the flight control computer for 100 bus communication cycles, and then resume receiving the heartbeat synchronization signal issued by the flight control computer. If the heartbeat synchronization signal is received, the actuator control electronics determine that communication between the flight control computer and the actuator control electronics has been restored, and receive flight control commands issued by the flight control computer; If the heartbeat synchronization signal is not received, the actuator control electronics will cut off the flight control commands issued by the flight control computer and directly receive the flight control commands issued by the cockpit.

7. The method for communication in a monitoring system as described in claim 5, characterized in that, Also includes: When a communication failure occurs between the flight control computer and the actuator control electronics, after receiving a signal indicating a communication failure from the actuator control electronics, the flight control computer waits for a preset time and then resends the heartbeat synchronization signal to the actuator control electronics.

8. A communication device for a monitoring system, characterized in that, include: The heartbeat synchronization signal transmission and reception module is used by the flight control computer to send heartbeat synchronization signals to the actuator control electronics via the data bus. A heartbeat random number generation and transmission module is used to generate a heartbeat random number through software at the rising edge of each heartbeat synchronization signal when the actuator control electronic device receives the heartbeat synchronization signal within a preset number of bus communication cycles, and send the heartbeat random number to the flight control computer through the data bus. The heartbeat synchronization signal is a square wave signal that flips according to a preset period. A random number generation and transmission module is used by the flight control computer to rewind the received heartbeat random number to the actuator control electronics. The communication status confirmation module is used for the actuator control electronics to receive the random number circling back from the flight control computer, and to determine the communication status between the flight control computer and the actuator control electronics based on the consistency between the heartbeat random number and the circling random number.

9. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the method of monitoring system communication as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that performs the method of monitoring system communication as described in any one of claims 1 to 7.

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