Aircraft engine monitoring device and method for switching operating modes thereof

Abstract

The application provides an aero-engine monitoring device and a switching method of working modes thereof. The working modes of the aero-engine monitoring device include a normal mode, an OHMS maintenance mode and a GSE maintenance mode. The switching method comprises the following steps: after power-on or reset, a first mode selection switch signal and a second mode selection switch signal are acquired, and the state of a GSE maintenance flag is judged. The state of an OHMS maintenance flag is acquired, and the working mode of the aero-engine monitoring device is determined in combination with the state of the GSE maintenance flag. The switching method can improve the software running safety.

Description

Technical Field

[0001] This invention relates to aircraft engine health monitoring, and more particularly to an aircraft engine monitoring device and a method for switching its operating modes. Background Technology

[0002] The aircraft engine health management system monitors the real-time operating status of the engine and provides data and suggestions for engine fault diagnosis and maintenance. It consists of an airborne subsystem and a ground subsystem. The airborne subsystem includes monitoring sensors and an aircraft engine monitoring unit (EMU); the ground subsystem includes portable maintenance terminals and ground stations.

[0003] The main function of the airborne subsystem is to use monitoring sensors, control systems and engine operating data acquired by the aircraft to diagnose engine faults and assess the health status of engine components and systems with the help of airborne or ground-based models and algorithms. It also performs fault prediction before engine faults occur and transmits the necessary indications, alarm information and engine health status to the Electronic Engine Control (EEC) and the aircraft.

[0004] The ground subsystem receives raw flight data and fault reports recorded by the airborne subsystem and integrates a large amount of historical data to achieve fault diagnosis, trend analysis, and lifespan management. Simultaneously, the ground data center receives a large amount of maintenance data and uses data mining and machine learning algorithms to update fault diagnosis and prediction models.

[0005] With the increase in health monitoring data and the development of technology, the demand for engine health management will continue to grow. Therefore, the engine monitoring unit (EMU) software must be continuously iterated and updated.

[0006] However, since the EMU software is loaded into the aircraft engine monitoring unit, if the aircraft engine monitoring unit is constantly returned to the factory for software loading, it will reduce the service life and availability of the engine and aircraft. Summary of the Invention

[0007] The purpose of this invention is to provide an aircraft engine monitoring device and a method for switching its operating modes, which can improve the security of software operation.

[0008] One aspect of the present invention provides a method for switching the operating mode of an aircraft engine monitoring device, wherein the operating modes of the aircraft engine monitoring device include a normal mode, an OHMS maintenance mode, and a GSE maintenance mode; the switching method includes: after power-on or reset, acquiring a first mode selection switch signal and a second mode selection switch signal, and determining the status of the GSE maintenance flag; acquiring the status of the OHMS maintenance flag, and determining the operating mode of the aircraft engine monitoring device in combination with the status of the GSE maintenance flag.

[0009] In one embodiment, the step of acquiring the first mode selection switch signal and the second mode selection switch signal after power-on or reset, and determining the state of the GSE maintenance flag, includes: acquiring the first mode selection switch signal and the second mode selection switch signal after power-on or reset; if the first mode selection switch signal or the second mode selection switch signal is an open switch signal, then the GSE maintenance flag is determined to be in an invalid state; if both the first mode selection switch signal and the second mode selection switch signal are closed switch signals, then the GSE maintenance flag is determined to be in an valid state.

[0010] In one embodiment, the step of obtaining the status of the OHMS maintenance flag and determining the operating mode of the aircraft engine monitoring device in conjunction with the status of the GSE maintenance flag includes: obtaining the status of the OHMS maintenance flag; verifying software integrity compatibility to obtain a software integrity compatibility verification result; and determining the operating mode of the aircraft engine monitoring device by combining the software integrity compatibility verification result, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag.

[0011] In one embodiment, obtaining the status of the OHMS maintenance flag includes: obtaining an OHMS maintenance request; determining the validity of the OHMS maintenance request in conjunction with the aircraft engine status, and obtaining the status of the OHMS maintenance flag.

[0012] In one embodiment, determining the operating mode of the aircraft engine monitoring device by combining the software integrity compatibility verification result, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag includes: if both the OHMS maintenance flag and the GSE maintenance flag are invalid, and the software integrity compatibility verification result passes, then the operating mode of the aircraft engine monitoring device is determined to be the normal mode; if the GSE maintenance flag is invalid, and the OHMS maintenance flag is valid or the software integrity compatibility verification result fails, then the operating mode of the aircraft engine monitoring device is determined to be the OHMS maintenance mode; if the GSE maintenance flag is valid, then the operating mode of the aircraft engine monitoring device is determined to be the GSE maintenance mode.

[0013] In one embodiment, determining the operating mode of the aircraft engine monitoring device by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag further includes: when the aircraft engine monitoring device is in normal mode, re-acquiring the status of the GSE maintenance flag and the status of the OHMS maintenance flag; and determining whether to switch the operating mode of the aircraft engine monitoring device based on the status of the GSE maintenance flag and the status of the OHMS maintenance flag.

[0014] In one embodiment, determining whether to switch the operating mode of the aircraft engine monitoring device based on the status of the GSE maintenance flag and the OHMS maintenance flag includes: if the GSE maintenance flag is in a valid state, resetting it and exiting the normal mode to enter the GSE maintenance mode; if the GSE maintenance flag is in an invalid state and the OHMS maintenance flag is in a valid state, resetting it and exiting the normal state to enter the OHMS maintenance mode.

[0015] In one embodiment, the step of reacquiring the status of the GSE maintenance flag and the OHMS maintenance flag when the aircraft engine monitoring device is in normal mode includes: reacquiring the first mode selection switch signal and the second mode selection switch signal when the aircraft engine monitoring device is in normal mode; if the first mode selection switch signal or the second mode selection switch signal is an open switch signal, then the GSE maintenance flag is determined to be invalid; if both the first mode selection switch signal and the second mode selection switch signal are closed switch signals, then the GSE maintenance flag is determined to be valid.

[0016] In one embodiment, the step of reacquiring the status of the GSE maintenance flag and the OHMS maintenance flag when the aircraft engine monitoring device is in normal mode includes: reacquiring the OHMS maintenance request when the aircraft engine monitoring device is in normal mode; determining the validity of the OHMS maintenance request in conjunction with the aircraft engine status, and obtaining the status of the OHMS maintenance flag.

[0017] In one embodiment, determining the operating mode of the aircraft engine monitoring device by combining the software integrity compatibility verification result, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag further includes: when the aircraft engine monitoring device is in OHMS maintenance mode, re-acquiring the software integrity compatibility verification result; if the software integrity compatibility verification result passes, then determining that the OHMS maintenance flag is invalid, resetting it, and exiting the OHMS maintenance mode.

[0018] In one embodiment, determining the operating mode of the aircraft engine monitoring device by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag further includes: resetting and exiting the GSE maintenance mode when the aircraft engine monitoring device is in the GSE maintenance mode.

[0019] In one embodiment, in normal mode, the aircraft engine monitoring device performs health monitoring on the aircraft engine.

[0020] In one embodiment, under OHMS maintenance mode, the application software of the aircraft engine monitoring device is subjected to field loading, NVM data download, or NVM initialization.

[0021] In one embodiment, under GSE maintenance mode, the application software and / or operating software and / or parameters of the aircraft engine monitoring device are field-loaded or factory-loaded or NVM data downloaded or NVM initialized.

[0022] Another aspect of the present invention provides an aircraft engine monitoring device, comprising: a memory; and a processor connected to the memory, the processor being configured to implement a method for switching the operating mode of the aircraft engine monitoring device as described in any of the above embodiments.

[0023] The aircraft engine monitoring device of this invention, based on considerations of transmission security, loading security, storage security, and usage needs, provides different functions through different operating modes to adapt to different loading needs of developers and users. It restricts the EMU software configuration items that can be loaded, thereby eliminating the need for maintenance personnel to remove the engine monitoring device from the aircraft, reducing the maintenance burden on workers, and improving maintenance efficiency and aircraft uptime. This invention combines a two-way mode selection switch and OHMS maintenance flag status to select different operating modes, preventing accidental switch operation from entering unexpected modes and improving software operation security. Attached Figure Description

[0024] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0025] Figure 1 This is a schematic diagram of the architecture of an aircraft engine health management system;

[0026] Figure 2 This is a flowchart illustrating an embodiment of a method for switching the operating mode of an aircraft engine monitoring device according to the present invention.

[0027] Figure 3 This is a diagram showing the operational status transitions of an aircraft engine monitoring device;

[0028] Figure 4This is a timing diagram of the data interaction during the maintenance loading of the OHMS (Aircraft Engine Monitoring System). Detailed Implementation

[0029] The aircraft engine health management system is used to monitor the real-time operating status of the engine and provide data and suggestions for engine fault diagnosis and maintenance. Figure 1 The architecture of the aircraft engine health management system is shown, such as... Figure 1 As shown, the aircraft engine health management system consists of an airborne subsystem and a ground subsystem. The airborne subsystem includes monitoring sensors and an engine monitoring unit (EMU); the ground subsystem includes a portable maintenance terminal and a ground station.

[0030] The main function of the airborne subsystem is to use monitoring sensors, control systems and engine operating data acquired by the aircraft to diagnose engine faults and assess the health status of engine components and systems with the help of airborne or ground-based models and algorithms. It also performs fault prediction before engine faults occur and transmits the necessary indications, alarm information and engine health status to the Electronic Engine Control (EEC) and the aircraft.

[0031] The ground subsystem includes portable maintenance terminals and ground stations that receive raw flight data and fault reports recorded by the airborne subsystems. It also integrates a large amount of historical data to achieve fault diagnosis, trend analysis, and lifespan management. Simultaneously, the ground data center receives a large amount of maintenance data and utilizes data mining and machine learning algorithms to update fault diagnosis and prediction models.

[0032] With the increase in health monitoring data and the development of technology, the demand for engine health management from aircraft manufacturers will continue to grow. Therefore, engine monitoring unit (EMU) software must be continuously iterated and updated.

[0033] However, since the EMU software is loaded into the aircraft engine monitoring unit, if the aircraft engine monitoring unit is constantly returned to the factory for software loading, it will reduce the service life and availability of the engine and aircraft.

[0034] After the EMU software is upgraded, the engine monitoring unit will need to be returned to the factory for EMU software loading, which will reduce the engine and aircraft's service life and availability. Furthermore, for safety reasons, some functions of the software are not suitable for loading by the aircraft manufacturer.

[0035] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided to explain the invention and not to limit it. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made to the invention without departing from the scope or spirit thereof. For example, a feature shown or described as part of one embodiment may be used with another embodiment to produce yet another embodiment. Therefore, the invention is intended to cover these modifications and variations that fall within the scope of the appended claims and their equivalents.

[0036] The engine monitoring device software is real-time embedded software that runs on the monitoring device platform. The EMU software includes EMU operating software and EMU application software, and consists of several configuration items. The EMU operating software constructs the application software runtime environment, and the EMU application software runs on top of the operating software to complete the health monitoring business logic.

[0037] The operating modes of the aircraft engine monitoring device of the present invention include normal mode, OHMS maintenance mode, and GSE maintenance mode. Here, "OHMS" (Onboard Health Management System) refers to the airborne health maintenance system, i.e., user mode; and "GSE" (Ground Support Equipment) refers to ground support equipment, i.e., developer mode.

[0038] In normal mode, the aircraft engine monitoring system (AEMS) performs health monitoring of the aircraft engine, i.e., it runs the normal engine health monitoring logic. In OHMS maintenance mode, the AEMS application software undergoes field loading, NVM (Non-Volatile Memory) data download, or NVM initialization. In GSE maintenance mode, the AEMS application software and / or operating software and / or parameters undergo field loading, factory loading, NVM data download, or NVM initialization. Field loading refers to loading at the airline, airport, etc., while factory loading refers to loading at the engine manufacturer's workshop.

[0039] Figure 2 The method for switching the operating mode of the aircraft engine monitoring device of the present invention is shown. For example... Figure 2 As shown, the method for switching the operating mode of the aircraft engine monitoring device of the present invention includes steps S110 to S200:

[0040] In step S100, after power-on or reset, the first mode selection switch signal and the second mode selection switch signal are acquired, and the status of the GSE maintenance flag is determined.

[0041] In step S200, the status of the OHMS maintenance indicator is obtained, and the operating mode of the aircraft engine monitoring device is selected based on the status of the GSE maintenance indicator. Here, the maintenance indicator refers to a physical identifier, status indication, or software prompt used to identify that the device is in a maintenance state. The OHMS maintenance indicator is a signal sent by the aircraft.

[0042] The aircraft engine monitoring device of this invention, based on considerations of transmission security, loading security, storage security, and usage needs, provides different functions through different operating modes to adapt to different loading needs of developers and users. It restricts the EMU software configuration items that can be loaded and utilizes the software loading tools provided by the engine manufacturer to the aircraft, enabling on-board software loading. This eliminates the need for maintenance personnel to remove the engine monitoring device from the aircraft and return it to the factory for loading, reducing the maintenance burden on workers and improving maintenance efficiency and aircraft uptime. Furthermore, this invention combines a two-way mode selection switch with OHMS maintenance flag status to select different operating modes, preventing accidental switch operation from entering unexpected modes. This dual-layer protection avoids accidental triggering of unexpected modes and improves software operation security.

[0043] In one embodiment, step S100 further includes steps S110 to S130 to determine whether the GSE maintenance flag is valid or invalid:

[0044] In step S110, after power-on or reset, the first mode selection switch signal and the second mode selection switch signal are acquired. The first and second mode selection switches are two hardwired switches, both located within the EMU's cable, and their switching permissions are not provided to the aircraft. The EMU operating software determines the status of the GSE maintenance flag based on the first and second mode selection switches.

[0045] In step S120, if the first mode selection switch signal or the second mode selection switch signal is a disconnect switch signal, then the GSE maintenance flag is determined to be in an invalid state.

[0046] In step S130, if both the first mode selection switch signal and the second mode selection switch signal are closed switch signals, then the GSE maintenance flag is determined to be in an active state.

[0047] The logic for determining the state of the GSE maintenance flag, combining steps S110 to S130, is shown in Table 1:

[0048] Serial Number First mode selection switch Second mode selection switch GSE maintenance sign 1 0 0 invalid 2 1 0 invalid 3 0 1 invalid 4 1 1 efficient

[0049] Table 1 GSE Maintenance Sign Judgment Logic

[0050] In Table 1, "0" and "1" for digital inputs refer to open / close switch signals, respectively. High impedance indicates "OPEN" state, and low impedance indicates "CLOSED" state.

[0051] In one embodiment, step S200 further includes steps S210 to S230:

[0052] In step S210, the status of the OHMS maintenance flag is obtained. Step S210 includes steps S211 to S212:

[0053] In step S211, an OHMS maintenance request is obtained. The OHMS maintenance request is initiated by the aircraft to the EMU.

[0054] In step S212, the validity of the OHMS maintenance request is determined in conjunction with the aircraft engine status, the status of the OHMS maintenance flag is obtained, and stored in NVRAM (Non-Volatile Random Access Memory).

[0055] In step S220, the software integrity compatibility is verified to obtain the software integrity compatibility verification result.

[0056] In step S230, the operating mode of the aircraft engine monitoring device is selected by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag.

[0057] The EMU operating software writes the OHMS maintenance flag, the first mode selection switch, and the second mode selection switch's status into the NVRAM during EMU power-on / reset. After power-on again, as... Figure 3 and Figure 4 As shown, enter the corresponding operating mode. If the OHMS maintenance flag and the two-way mode switch status meet the requirements... Figure 3 As shown, but without powering the EMU back on, the EMU enters normal mode, that is, in Figure 3 The startup state shown requires a power cycle to select the operating mode. This is to prevent accidental operation (such as accidentally flipping a switch, accidentally loading software, or loading the wrong software) from triggering unexpected modes. The power cycle operation can be understood as a protective measure to improve the safety of software operation.

[0058] For safety reasons, some software functions are not suitable for the aircraft to load. (Continue to refer to...) Figure 3The validity of the GSE maintenance flag can be determined by using the first and second mode selection switches. Since the aircraft operator does not have the authority to toggle either mode selection switch (i.e., there are no first or second mode selection switches), they cannot enter GSE maintenance mode. Furthermore, because the software flashing tool is provided by the engine manufacturer, the tool provided to the aircraft operator does not contain the loading addresses for this software, therefore the aircraft operator cannot load this software.

[0059] Further, step S230 includes steps S231 to S233 to select the operating mode that the aircraft engine monitoring device enters:

[0060] In step S231, if both the OHMS maintenance flag and the GSE maintenance flag are invalid, and the software integrity and compatibility verification result is passed, then the operating mode of the aircraft engine monitoring device is determined to be normal mode.

[0061] In step S232, if the GSE maintenance flag is invalid and the OHMS maintenance flag is valid or the software integrity compatibility verification result is unsuccessful, then the operating mode of the aircraft engine monitoring device is determined to be OHMS maintenance mode.

[0062] In step S233, if the GSE maintenance flag is in an active state, the operating mode of the aircraft engine monitoring device is determined to be GSE maintenance mode.

[0063] In conjunction with steps S231 to S233, the operating mode selection of the aircraft engine monitoring device of the present invention is as follows:

[0064] As shown in Table 2:

[0065]

[0066] Table 2 Working Mode Selection Logic

[0067] By following the operating mode selection steps S231 to S233, the operating mode that the EMU enters after power-on / reset can be determined. It is important to note that the above operating mode selection steps are only performed during the initialization process. This provides double-layer protection, reducing the risk of accidental triggering of the operating mode and ensuring the safe operation of the EMU.

[0068] In one embodiment, after executing step S231, the aircraft engine monitoring device switches its operating mode in normal mode. Specifically, in step S231a, during the operational cycle, the status of the GSE maintenance flag and the OHMS maintenance flag are reacquired. The status of the GSE maintenance flag can be determined with reference to steps S110 to S130 and Table 1, specifically: when the aircraft engine monitoring device is in normal mode, the first mode selection switch signal and the second mode selection switch signal are reacquired; if either the first or second mode selection switch signal is an open switch signal, the GSE maintenance flag is determined to be invalid; if both the first and second mode selection switch signals are closed switch signals, the GSE maintenance flag is determined to be valid. The status of the OHMS maintenance flag can be determined with reference to steps S211 to S212, specifically: when the aircraft engine monitoring device is in normal mode, OHMS maintenance requests initiated by the aircraft OHMS system are periodically received; combined with the aircraft engine status, the validity of the OHMS maintenance request is determined, and the status of the OHMS maintenance flag is obtained.

[0069] In step S231b, based on the status of the GSE maintenance flag and the OHMS maintenance flag, it is determined whether to switch the operating mode of the aircraft engine monitoring device. Specifically, in this step, if the GSE maintenance flag is valid, it is reset and exits the normal mode, entering the GSE maintenance mode. If the GSE maintenance flag is invalid, but the OHMS maintenance flag is valid (i.e., OHMS communication is normal and the maintenance request sent by OHMS is valid, and the engine is stationary), then the "OHMS maintenance flag" is set to "valid" and written to NVRAM, and after reset, it exits the normal mode and enters the OHMS maintenance mode. If the conditions for entering the maintenance mode are not met, the aircraft engine monitoring device continues to perform the periodic tasks in the normal mode.

[0070] In one embodiment, after executing step S232, the aircraft engine monitoring device switches its operating mode while in OHMS maintenance mode. In OHMS maintenance mode, to prevent the loss of the ability to re-enter OHMS maintenance mode after partial software loading, the "OHMS maintenance flag" must be set to "invalid" only after ensuring the integrity of the software loading. In this scenario, if entering OHMS maintenance mode, a complete software loading must be performed before exiting OHMS maintenance mode.

[0071] Specifically, in step S232a, the software integrity compatibility verification result is reacquired. In step S232b, if the software integrity compatibility verification result passes, the OHMS maintenance flag is determined to be invalid, and the system exits the OHMS maintenance mode after a reset. In other words, when the EMU software enters OHMS maintenance mode, after the software is fully loaded, the "OHMS maintenance flag" is set to "invalid," the OHMS maintenance flag is written to NVRAM, and the system exits the OHMS maintenance mode after a reset.

[0072] In one embodiment, after executing step S233, the aircraft engine monitoring device switches its operating mode while in OHMS maintenance mode. Specifically, in step S233a, it exits GSE maintenance mode after resetting.

[0073] The aircraft engine monitoring device of this invention includes multiple operating modes, selected by a dual-mode switch and confirmed by aircraft signals, preventing accidental switch operation from entering unexpected modes. Furthermore, mode selection occurs only during initialization, providing double-layer protection to reduce the risk of false mode triggering and ensure the safe operation of the monitoring device.

[0074] The aircraft engine monitoring device of the present invention includes a memory and a processor, wherein the processor and the memory are connected, and the processor is configured to implement a method for switching the operating mode of the aircraft engine monitoring device as described in any of the above embodiments.

[0075] The storage medium of the present invention is used to store non-transitory computer instructions, which, when executed, perform a switching method as described in any of the above embodiments.

[0076] The computer program product of the present invention includes a computer program. When executed by a processor, the computer program implements the switching method as described in any of the above embodiments.

[0077] Embodiments of the subject matter described in this specification can be implemented as one or more computer programs, i.e., one or more modules of computer program instructions encoded on a tangible, non-transitory program carrier for execution by a data processing apparatus or for controlling the operation of a data processing apparatus. Alternatively or additionally, the program instructions may be encoded on artificially generated propagation signals, such as machine-generated electrical, optical, or electromagnetic signals, which are generated to encode information and transmit it to a suitable receiving device for execution by the data processing apparatus.

[0078] Computer storage media can be machine-readable storage devices, machine-readable storage substrates, random or serial access memory devices, or combinations thereof.

[0079] Suitable computers for executing computer programs include, for example, general-purpose and / or special-purpose microprocessors, or any other type of central processing unit. Typically, the central processing unit receives instructions and data from read-only memory and / or random access memory. The basic components of a computer include a central processing unit for implementing or executing instructions and one or more memory devices for storing instructions and data. Typically, a computer will also include one or more mass storage devices for storing data, such as disks, magneto-optical disks, or optical disks, or the computer will be operatively coupled to such mass storage devices to receive data from or transfer data to them, or both. However, a computer is not required to have such devices. Furthermore, a computer can be embedded in another device, such as a mobile phone, a personal digital assistant (PDA), a mobile audio or video player, a game console, a global positioning system (GPS) receiver, or a portable storage device such as a universal serial bus (USB) flash drive, to name a few.

[0080] Computer-readable media suitable for storing computer program instructions and data include all forms of non-volatile memory, media, and memory devices, such as semiconductor memory devices (e.g., EPROM, EEPROM, and flash memory devices), magnetic disks (e.g., internal hard disks or removable disks), magneto-optical disks, and CD-ROM and DVD-ROM disks. Processors and memory may be supplemented by or incorporated into dedicated logic circuitry.

[0081] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A method for switching the operating mode of an aircraft engine monitoring device, characterized in that, The operating modes of the aircraft engine monitoring device include normal mode, OHMS maintenance mode, and GSE maintenance mode. The switching method includes: After power-on or reset, acquire the first mode selection switch signal and the second mode selection switch signal, and determine the status of the GSE maintenance flag; Obtain the status of the OHMS maintenance indicator and, in conjunction with the status of the GSE maintenance indicator, determine the operating mode of the aircraft engine monitoring system.

2. The switching method as described in claim 1, characterized in that, After power-on or reset, acquiring the first mode selection switch signal and the second mode selection switch signal, and determining the status of the GSE maintenance flag, includes: After power-on or reset, acquire the first mode selection switch signal and the second mode selection switch signal; If the first mode selection switch signal or the second mode selection switch signal is an open switch signal, then the GSE maintenance flag is determined to be invalid. If both the first mode selection switch signal and the second mode selection switch signal are closed, then the GSE maintenance flag is determined to be in an active state.

3. The switching method as described in claim 1, characterized in that, The process of obtaining the status of the OHMS maintenance indicator and combining it with the status of the GSE maintenance indicator to determine the operating mode of the aircraft engine monitoring device includes: Obtain the status of the OHMS maintenance flag; The software integrity and compatibility are verified, and the software integrity and compatibility verification results are obtained. By combining the results of software integrity and compatibility verification, the status of GSE maintenance flags, and the status of OHMS maintenance flags, the operating mode of the aircraft engine monitoring device is determined.

4. The switching method as described in claim 3, characterized in that, The process of obtaining the status of the OHMS maintenance flag includes: Obtain OHMS maintenance request; By combining the status of the aircraft engine, the validity of the OHMS maintenance request is determined, and the status of the OHMS maintenance flag is obtained.

5. The switching method as described in claim 3, characterized in that, The method of determining the operating mode of the aircraft engine monitoring device by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag includes: If both the OHMS maintenance flag and the GSE maintenance flag are invalid, and the software integrity and compatibility verification result is passed, then the operating mode of the aircraft engine monitoring device is determined to be normal mode. If the GSE maintenance flag is invalid, and the OHMS maintenance flag is valid or the software integrity compatibility verification result is failed, then the operating mode of the aircraft engine monitoring device is determined to be OHMS maintenance mode. If the GSE maintenance flag is active, then the operating mode of the aircraft engine monitoring device is determined to be GSE maintenance mode.

6. The switching method as described in claim 5, characterized in that, The method of determining the operating mode of the aircraft engine monitoring device by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag also includes: With the aircraft engine monitoring system in normal mode, reacquire the status of the GSE maintenance flag and the OHMS maintenance flag; Based on the status of the GSE maintenance indicator and the OHMS maintenance indicator, determine whether to switch the operating mode of the aircraft engine monitoring system.

7. The switching method as described in claim 6, characterized in that, The step of determining whether to switch the operating mode of the aircraft engine monitoring device based on the status of the GSE maintenance indicator and the OHMS maintenance indicator includes: If the GSE maintenance flag is active, after resetting, exit normal mode and enter GSE maintenance mode; If the GSE maintenance flag is invalid and the OHMS maintenance flag is valid, the system will exit normal mode and enter OHMS maintenance mode after resetting.

8. The switching method as described in claim 6, characterized in that, The process of re-acquiring the status of the GSE maintenance flag and the OHMS maintenance flag when the aircraft engine monitoring device is in normal mode includes: When the aircraft engine monitoring device is in normal mode, reacquire the first mode selection switch signal and the second mode selection switch signal; If the first mode selection switch signal or the second mode selection switch signal is an open switch signal, then the GSE maintenance flag is determined to be invalid. If both the first mode selection switch signal and the second mode selection switch signal are closed, then the GSE maintenance flag is determined to be in an active state.

9. The switching method as described in claim 6, characterized in that, The process of re-acquiring the status of the GSE maintenance flag and the OHMS maintenance flag when the aircraft engine monitoring device is in normal mode includes: With the aircraft engine monitoring system in normal mode, reacquire the OHMS maintenance request; By combining the status of the aircraft engine, the validity of the OHMS maintenance request is determined, and the status of the OHMS maintenance flag is obtained.

10. The switching method as described in claim 5, characterized in that, The method of determining the operating mode of the aircraft engine monitoring device by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag also includes: When the aircraft engine monitoring device is in OHMS maintenance mode, reacquire the software integrity and compatibility verification results; If the software integrity and compatibility verification result passes, the OHMS maintenance flag is determined to be in an invalid state, and the system exits the OHMS maintenance state after resetting.

11. The switching method as described in claim 5, characterized in that, The method of determining the operating mode of the aircraft engine monitoring device by combining the software integrity and compatibility verification results, the status of the GSE maintenance flag, and the status of the OHMS maintenance flag also includes: When the aircraft engine monitoring device is in GSE maintenance mode, it exits GSE maintenance mode after resetting.

12. The switching method according to any one of claims 1-11, characterized in that, In normal mode, the aircraft engine monitoring system performs health monitoring on the aircraft engine.

13. The switching method as described in any one of claims 1-11, characterized in that, In OHMS maintenance mode, the application software of the aircraft engine monitoring device is subjected to field loading, NVM data download, or NVM initialization.

14. The switching method according to any one of claims 1-11, characterized in that, In GSE maintenance mode, the application software and / or operating software and / or parameters of the aircraft engine monitoring device are field-loaded or factory-loaded or NVM data downloaded or NVM initialized.

15. An aircraft engine monitoring device, characterized in that, include: Memory; as well as A processor, connected to the memory, the processor being configured to implement a method for switching the operating mode of an aircraft engine monitoring device as described in any one of claims 1-14.

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