Aviation motor detection method, device, computer equipment and storage medium

Abstract

The present invention discloses an aviation motor detection method, device, computer equipment and storage medium, which relate to the field of aviation technology and are used to realize the detection of aviation motors. The main technical scheme of the present invention is: obtaining the body vibration information and system operation information of the aviation motor under test, as well as the environmental vibration information of the environment in which the aviation motor under test is located; determining the state indication information and execution information corresponding to the aviation motor under test according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the aviation motor under test, and the execution information is the control instruction corresponding to the state indication information; outputting the state indication information, and executing the control instruction corresponding to the execution information.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to an aviation motor detection method, device, computer equipment and storage medium. Background Art

[0002] Aircraft motors are an important part of aircraft power systems. As the power consumption of modern aircraft increases, the importance of health status testing of aircraft motors also increases.

[0003] Aviation motors are usually arranged in the engine nacelle or APU (Auxiliary Power Unit) compartment. Their operating environment is a high-vibration environment, and the vibration state of aviation motors during operation is a direct factor affecting their lifespan.

[0004] In ground testing, the vibration index of aircraft motors can reflect many problems such as the motor body state, the gearbox state of the drive system, the adapter shaft state, etc. When the aircraft motor is in an unsafe operating state, it may disintegrate, damage the onboard and ground test equipment, and other dangerous consequences. Therefore, modern aircraft have put forward new requirements for the vibration detection of aircraft motors. Summary of the invention

[0005] The present invention provides an aviation motor detection method, device, computer equipment and storage medium for realizing the detection of the aviation motor.

[0006] An embodiment of the present invention provides an aviation motor detection method, the method comprising:

[0007] Obtaining body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located;

[0008] Determine the state indication information and execution information corresponding to the tested aviation motor according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the tested aviation motor, and the execution information is a control instruction corresponding to the state indication information;

[0009] Output the status indication information, and execute the control instruction corresponding to the execution information.

[0010] An embodiment of the present invention provides an aircraft motor detection device, the device comprising:

[0011] An acquisition module, used to acquire body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located;

[0012] A determination module, used to determine the state indication information and execution information corresponding to the aircraft motor under test according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the aircraft motor under test, and the execution information is a control instruction corresponding to the state indication information;

[0013] The output execution module is used to output the status indication information and execute the control instruction corresponding to the execution information.

[0014] A computer device comprises a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the above-mentioned aviation motor detection method is implemented when the processor executes the computer program.

[0015] A computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the above-mentioned aviation motor detection method is implemented.

[0016] The present invention provides an aviation motor detection method, device, computer equipment and storage medium, which obtain the body vibration information and system operation information of the aviation motor under test, as well as the environmental vibration information of the environment in which the aviation motor under test is located; according to the body vibration information, the system operation information and / or the environmental vibration information, the state indication information and execution information corresponding to the aviation motor under test are determined; the state indication information is used to indicate the working state of the aviation motor under test, and the execution information is the control instruction corresponding to the state indication information; the state indication information is output, and the control instruction corresponding to the execution information is executed. Therefore, the present invention can realize the detection of aviation motors. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative labor.

[0018] Figure 1 is a structural diagram of an aviation motor detection method in one embodiment of the present invention;

[0019] Figure 2 is a schematic diagram of the state assessment of an aviation motor in one embodiment of the present invention;

[0020] Figure 3 is a flow chart of an aviation motor detection method in one embodiment of the present invention;

[0021] Figure 4It is a principle block diagram of an aviation motor detection device in one embodiment of the present invention;

[0022] Figure 5 is a schematic diagram of a computer device in one embodiment of the present invention. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] like Figure 1 , Figure 2 and Figure 3 As shown, an embodiment of the present invention provides an aviation motor detection method, comprising the following steps:

[0025] S101, obtaining body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located.

[0026] Among them, the main body vibration information includes but is not limited to the X-axis vibration information, Y-axis vibration information, and Z-axis vibration information of the tested aviation motor; the environmental vibration information includes but is not limited to the X-axis vibration information, Y-axis vibration information, and Z-axis vibration information of the gearbox of the drag system.

[0027] Specifically, this embodiment is as follows Figure 2 The vibration sensor set in obtains various vibration information.

[0028] S102: determining state indication information and execution information corresponding to the tested aviation motor according to the body vibration information, the system operation information and / or the environmental vibration information.

[0029] The state indication information is used to indicate the working state of the tested aviation motor, and the execution information is a control instruction corresponding to the state indication information. The state indication information at least includes normal state, warning state, and emergency stop state; the output execution, the execution information at least includes warning execution and output execution.

[0030] In an optional embodiment provided by the present invention, determining the state indication information and execution information corresponding to the tested aviation motor according to the body vibration information, the system operation information and / or the environmental vibration information includes:

[0031] S1021, obtaining the maximum vibration difference value of the X axis, the maximum vibration difference value of the Y axis, and the maximum vibration difference value of the Z axis respectively corresponding to the main body vibration information and the environmental vibration information.

[0032] S1022: Determine the electrical power, the drive system shaft power, and the motor efficiency of the tested aviation motor according to the system operation information.

[0033] Specifically, according to the system operation information, the electrical power of the tested aviation motor, the shaft power of the traction system, and the motor efficiency are determined, including: determining the electrical power through the voltage and current of the tested aviation motor; determining the shaft power of the traction system through the speed and torque of the tested aviation motor; determining the motor efficiency through the electrical power of the tested aviation motor and the shaft power of the traction system.

[0034] S1023, determining the status indication information and execution information corresponding to the tested aviation motor according to the corresponding X-axis maximum vibration difference, Y-axis maximum vibration difference, Z-axis maximum vibration difference, the electrical power, the traction system shaft power and / or the motor efficiency in the main body vibration information and the environmental vibration information respectively.

[0035] Specifically, this embodiment determines the state indication information and execution information corresponding to the tested aviation motor by comparing the corresponding X-axis maximum vibration difference, Y-axis maximum vibration difference, and Z-axis maximum vibration difference in the body vibration information and the environmental vibration information with the corresponding warning threshold and fault threshold, and / or compares the electrical power, the traction system shaft power, and the motor efficiency with the corresponding warning threshold and fault threshold, respectively, to determine the state indication information and execution information corresponding to the tested aviation motor. The specific values ​​of the warning threshold and the fault threshold are generally provided by the motor manufacturer or determined by experience, such as: the warning threshold is set to 10G, and the fault threshold is set to 14G.

[0036] In an embodiment provided by the present invention, the state indication information and execution information corresponding to the aircraft motor under test are determined according to the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency respectively corresponding to the body vibration information and the environmental vibration information, including: determining whether an abnormal point occurs in time in the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency; if the abnormal point occurs, determining the state indication information and execution information corresponding to the aircraft motor under test according to the absolute value of the difference corresponding to the abnormal point, the absolute value of the difference being the value at the current moment minus the value at the adjacent moment, or the average value of a certain period minus the average value of the adjacent period.

[0037] Specifically, in this embodiment, if the motor vibration suddenly increases or the absolute value of the difference in the drive system shaft power output or motor efficiency exceeds the set warning threshold within several consecutive test points, it means that the motor under test is abnormal. At this time, the test system should warn the tester through the status indication information. If the absolute value of the difference exceeds the set fault threshold, the test system should perform emergency stop and other operations to ensure safety.

[0038] In an optional embodiment provided by the present invention, the maximum difference between the inlet and outlet oil temperatures can also be obtained according to a set period; the maximum difference between the inlet and outlet oil temperatures is compared with the corresponding warning threshold and fault threshold to determine the state indication information and execution information corresponding to the tested aviation motor. The maximum value of the outlet oil temperature is filtered according to the set period; the maximum difference between the inlet and outlet oil temperatures is obtained by subtracting the inlet oil temperature from the maximum value of the outlet oil temperature.

[0039] The cycle setting is determined by the test requirements, such as the oil temperature test cycle can be set to 60s. The electric power cycle can be set to 10 modes, and the mechanical vibration cycle can be set to 100ms. The specific values ​​of the warning threshold and the fault threshold are generally provided by the motor manufacturer or determined by experience, such as the warning threshold is set to 30℃ and the fault threshold is set to 40℃.

[0040] S103, output the status indication information, and execute the control instruction corresponding to the execution information.

[0041] The output results include status indication information, including normal, warning, fault status indication and degradation assessment; execution information, including warning execution, i.e., the set signal to the motor controller to make shutdown suggestions; emergency stop execution, i.e., outputting emergency stop instructions to the traction system and motor controller, which requires the traction system and motor controller to have control interfaces for this instruction.

[0042] The present invention provides an aviation motor detection method, which obtains the body vibration information and system operation information of the aviation motor under test, as well as the environmental vibration information of the environment in which the aviation motor under test is located; determines the state indication information and execution information corresponding to the aviation motor under test according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the aviation motor under test, and the execution information is the control instruction corresponding to the state indication information; outputs the state indication information, and executes the control instruction corresponding to the execution information. Thus, the present invention can realize the detection of aviation motors.

[0043] It should be understood that the order of execution of the steps in the above embodiment does not necessarily mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiment of the present invention.

[0044] In one embodiment, an aircraft motor detection device is provided, and the aircraft motor detection device corresponds one-to-one to the aircraft motor detection method in the above embodiment. Figure 4 As shown, the aircraft motor detection device includes: an acquisition module 10, a determination module 20, and an output execution module 30. The functional modules are described in detail as follows:

[0045] An acquisition module 10 is used to acquire body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located;

[0046] The determination module 20 is used to determine the state indication information and execution information corresponding to the aircraft motor under test according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the aircraft motor under test, and the execution information is a control instruction corresponding to the state indication information;

[0047] The output execution module 30 is used to output the state indication information and execute the control instruction corresponding to the execution information.

[0048] In an optional embodiment provided by the present invention, the body vibration information includes but is not limited to the X-axis vibration information, Y-axis vibration information, and Z-axis vibration information of the tested aviation motor; the environmental vibration information includes but is not limited to the X-axis vibration information, Y-axis vibration information, and Z-axis vibration information of the gear box of the drag system; the status indication information at least includes normal status, warning status, and emergency stop status; the output execution, the execution information at least includes warning execution and output execution.

[0049] In an optional embodiment provided by the present invention, the determination module 20 is specifically configured to:

[0050] Obtaining the maximum vibration difference of the X axis, the maximum vibration difference of the Y axis, and the maximum vibration difference of the Z axis respectively corresponding to the body vibration information and the environmental vibration information;

[0051] Determine the electrical power, drive system shaft power, and motor efficiency of the tested aviation motor according to the system operation information;

[0052] According to the X-axis maximum vibration difference, Y-axis maximum vibration difference, Z-axis maximum vibration difference, the electrical power, the traction system shaft power and / or the motor efficiency respectively corresponding to the main body vibration information and the environmental vibration information, the state indication information and execution information corresponding to the tested aviation motor are determined.

[0053] In an optional embodiment provided by the present invention, the determination module 20 is specifically configured to:

[0054] Compare the X-axis maximum vibration difference, Y-axis maximum vibration difference, and Z-axis maximum vibration difference corresponding to the main body vibration information and the environmental vibration information with the corresponding warning threshold and fault threshold, respectively, to determine the state indication information and execution information corresponding to the tested aviation motor; and / or

[0055] The electrical power, the drive system shaft power and the motor efficiency are respectively compared with the corresponding warning threshold and fault threshold to determine the state indication information and execution information corresponding to the tested aviation motor.

[0056] In an optional embodiment provided by the present invention, the acquisition module 10 is further used to obtain the maximum difference between the inlet and outlet oil temperatures according to a set period;

[0057] The determination module 20 is further used to compare the maximum difference between the inlet and outlet oil temperatures with the corresponding warning threshold and fault threshold to determine the state indication information and execution information corresponding to the tested aviation motor.

[0058] In an optional embodiment provided by the present invention, the determination module 20 is specifically configured to:

[0059] Determine the electrical power by the voltage and current of the tested aviation motor;

[0060] Determine the shaft power of the traction system by the rotation speed and torque of the tested aviation motor;

[0061] The motor efficiency is determined by the electrical power of the tested aviation motor and the shaft power of the traction system.

[0062] In an optional embodiment provided by the present invention, the determination module 20 is specifically configured to:

[0063] Determine whether the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency have abnormal points in time;

[0064] If the abnormal point occurs, the state indication information and execution information corresponding to the tested aviation motor are determined according to the absolute value of the difference corresponding to the abnormal point, where the absolute value of the difference is the value at the current moment minus the value at the adjacent moment, or the cycle average value minus the average value of the adjacent cycle.

[0065] The specific definition of the aircraft motor detection device can be found in the definition of the aircraft motor detection method above, which will not be repeated here. Each module in the above-mentioned aircraft motor detection device can be implemented in whole or in part by software, hardware and a combination thereof. The above-mentioned modules can be embedded in or independent of the processor in the computer device in the form of hardware, or can be stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[0066] In one embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as follows: Figure 5 As shown. The computer device includes a processor, a memory, a network interface and a database connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, an aviation motor detection method is implemented.

[0067] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the following steps when executing the computer program:

[0068] Acquire body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located;

[0069] Determine the state indication information and execution information corresponding to the tested aviation motor according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the tested aviation motor, and the execution information is a control instruction corresponding to the state indication information;

[0070] Output the status indication information, and execute the control instruction corresponding to the execution information.

[0071] In one embodiment, a computer readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, the following steps are implemented:

[0072] Obtaining body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located;

[0073] Determine the state indication information and execution information corresponding to the tested aviation motor according to the body vibration information, the system operation information and / or the environmental vibration information; the state indication information is used to indicate the working state of the tested aviation motor, and the execution information is a control instruction corresponding to the state indication information;

[0074] Output the status indication information, and execute the control instruction corresponding to the execution information.

[0075] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0076] Those skilled in the art can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above.

[0077] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims

1. A method for detecting an aviation motor, characterized in that: The method comprises: Acquire body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located; Obtaining the maximum vibration difference of the X axis, the maximum vibration difference of the Y axis, and the maximum vibration difference of the Z axis respectively corresponding to the body vibration information and the environmental vibration information; Determine the electrical power, the drive system shaft power, and the motor efficiency of the tested aviation motor according to the system operation information; According to the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency respectively corresponding to the main body vibration information and the environmental vibration information, the state indication information and the execution information corresponding to the tested aviation motor are determined; the state indication information is used to indicate the working state of the tested aviation motor, and the execution information is a control instruction corresponding to the state indication information; Output the status indication information, and execute the control instruction corresponding to the execution information; The determining of the state indication information and execution information corresponding to the tested aviation motor according to the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency respectively corresponding to the body vibration information and the environmental vibration information includes: Determine whether the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency have abnormal points in time; If the abnormal point occurs, the state indication information and execution information corresponding to the tested aviation motor are determined according to the absolute value of the difference corresponding to the abnormal point, and the absolute value of the difference is the value at the current moment minus the value at the adjacent moment, or the cycle average value minus the average value of the adjacent cycle.

2. The method according to claim 1, characterized in that The body vibration information includes the X-axis vibration information, Y-axis vibration information, and Z-axis vibration information of the tested aviation motor; the environmental vibration information includes the X-axis vibration information, Y-axis vibration information, and Z-axis vibration information of the gearbox of the drag system; the status indication information at least includes normal status, warning status, and emergency stop status; the output execution, the execution information at least includes warning execution and output execution.

3. The method according to claim 1, characterized in that The determining of the state indication information and execution information corresponding to the tested aviation motor according to the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency respectively corresponding to the body vibration information and the environmental vibration information includes: Compare the X-axis maximum vibration difference, Y-axis maximum vibration difference, and Z-axis maximum vibration difference corresponding to the main body vibration information and the environmental vibration information with the corresponding warning threshold and fault threshold, respectively, to determine the state indication information and execution information corresponding to the tested aviation motor; and / or The electrical power, the drive system shaft power and the motor efficiency are respectively compared with the corresponding warning threshold and fault threshold to determine the state indication information and execution information corresponding to the tested aviation motor.

4. The method according to claim 1, characterized in that: The method further comprises: Obtain the maximum difference between inlet and outlet oil temperatures according to the set cycle; The maximum difference between the inlet and outlet oil temperatures is compared with the corresponding warning threshold and fault threshold to determine the state indication information and execution information corresponding to the tested aviation motor.

5. The method according to claim 1, characterized in that Determining the electrical power, the drive system shaft power, and the motor efficiency of the tested aviation motor according to the system operation information includes: Determine the electrical power by the voltage and current of the tested aviation motor; Determine the shaft power of the traction system by the rotation speed and torque of the tested aviation motor; The motor efficiency is determined by the electrical power of the tested aviation motor and the shaft power of the traction system.

6. An aviation motor detection device, characterized in that: The device comprises: An acquisition module, used to acquire body vibration information and system operation information of the aircraft motor under test, as well as environmental vibration information of the environment in which the aircraft motor under test is located; A determination module is used to obtain the maximum vibration difference of the X-axis, the maximum vibration difference of the Y-axis, and the maximum vibration difference of the Z-axis respectively corresponding to the main body vibration information and the environmental vibration information; determine the electrical power, the shaft power of the drag system, and the motor efficiency of the tested aviation motor according to the system operation information; determine the state indication information and execution information corresponding to the tested aviation motor according to the maximum vibration difference of the X-axis, the maximum vibration difference of the Y-axis, the maximum vibration difference of the Z-axis, the electrical power, the shaft power of the drag system and / or the motor efficiency respectively corresponding to the main body vibration information and the environmental vibration information; the state indication information is used to indicate the working state of the tested aviation motor, and the execution information is a control instruction corresponding to the state indication information; Output execution module, used to output the status indication information and execute the control instruction corresponding to the execution information The determination module is specifically used for: Determine whether the X-axis maximum vibration difference, the Y-axis maximum vibration difference, the Z-axis maximum vibration difference, the electrical power, the drive system shaft power and / or the motor efficiency have abnormal points in time; If the abnormal point occurs, the state indication information and execution information corresponding to the tested aviation motor are determined according to the absolute value of the difference corresponding to the abnormal point, and the absolute value of the difference is the value at the current moment minus the value at the adjacent moment, or the cycle average value minus the average value of the adjacent cycle.

7. 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, the aviation motor detection method according to any one of claims 1 to 5 is implemented.

8. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the aviation motor detection method according to any one of claims 1 to 5 is implemented.

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