Aircraft structural health monitoring data processing method, airborne unit and storage medium

Abstract

The present application provides an aircraft structure health monitoring data processing method, an airborne unit and a storage medium, which relate to the field of aviation testing technology. The method is applied to an airborne unit of an aircraft structure health monitoring system; the method comprises: determining a target time source from a plurality of candidate time sources; obtaining aircraft structure health monitoring data and time information of the target time source; and inserting the time information of the target time source as a timestamp into the aircraft structure health monitoring data to obtain the target monitoring data. The method is applicable to the aircraft structure health status monitoring process, and is used to solve the problem of poor effectiveness of the current aircraft structure health monitoring data.

Description

Technical Field

[0001] The present application relates to the field of aviation testing technology, and in particular to an aircraft structure health monitoring data processing method, an airborne unit and a storage medium. Background Art

[0002] After an aircraft is put into operation, it is subjected to long-term loads such as fatigue and impact, as well as structural aging caused by changes in temperature, humidity, pressure and other conditions. These factors can lead to a decline in aircraft structural performance or even component damage, causing catastrophic accidents.

[0003] In order to avoid accidents, the relevant technology can add an aircraft structural health monitoring system to the aircraft to monitor the aircraft body structural strength in real time. For example, the aircraft structural health monitoring system can include multiple sensors, and the aircraft structural health monitoring system can collect aircraft structural health monitoring data through multiple sensors, and monitor the aircraft body structural strength in real time based on the aircraft structural health monitoring data.

[0004] However, the aircraft structural health monitoring data collected by the aircraft structural health monitoring system of the related art has poor validity, and the aircraft structural health monitoring data is prone to failure. Summary of the invention

[0005] The present application provides an aircraft structure health monitoring data processing method, an airborne unit and a storage medium, which are used to solve the problem of poor validity of aircraft structure health monitoring data and easy failure of aircraft structure health monitoring data in related technologies.

[0006] In a first aspect, the present application provides an aircraft structural health monitoring data processing method, which is applied to an onboard unit of an aircraft structural health monitoring system; the method comprises: determining a target time source from a plurality of candidate time sources; acquiring aircraft structural health monitoring data and time information of the target time source; and entering the time information of the target time source as a timestamp into the aircraft structural health monitoring data to obtain the target monitoring data.

[0007] It should be understood that the aircraft structural health monitoring system of the related art usually uses a single time source to provide a time reference for the aircraft structural health monitoring data. However, since different aircraft models can provide different time sources, if a certain flight model cannot provide the time source required by the aircraft structural health monitoring system, it cannot provide an accurate time reference for the aircraft structural health monitoring system, and the aircraft structural health monitoring data recorded by it will also be invalid, resulting in poor validity of the aircraft structural health monitoring data, and the aircraft structural health monitoring data is prone to invalidation.

[0008] In the aircraft structural health monitoring data processing method provided by the present application, the onboard unit can determine the target time source from multiple candidate time sources, obtain the time information of the target time source, and use the time information of the target time source as a timestamp to enter the aircraft structural health monitoring data to obtain the target monitoring data. The onboard unit can support and be compatible with multiple candidate time sources, thereby avoiding the situation where the aircraft cannot provide a single type of time source supported by a certain aircraft structural health monitoring system, and avoiding the aircraft structural health monitoring data from being invalid due to the lack of a time reference provided by the time source.

[0009] Optionally, the onboard unit has a communication connection with the configuration management unit; determining the target time source from multiple candidate time sources includes: receiving a configuration message from the configuration management unit; and determining the target time source from multiple candidate time sources according to the configuration message.

[0010] Optionally, the configuration message is generated after the configuration management unit receives a user's selection operation on at least one candidate time source among a plurality of candidate time sources.

[0011] Optionally, the multiple candidate time sources include: RS422 bus time source, GNNS time source, and ARINC429 bus time source.

[0012] Optionally, determining a target time source from a plurality of candidate time sources includes: obtaining a target aircraft model of the aircraft where the airborne unit is located; determining a target time source according to the target aircraft model and a preset corresponding relationship; the preset corresponding relationship is used to characterize the corresponding relationship between the plurality of candidate time sources and the aircraft model.

[0013] Optionally, the onboard unit has a communication connection with the data processing unit; the method also includes: sending target monitoring data to the data processing unit, so that the data processing unit determines the current aircraft structure health status according to the target monitoring data, and the life cycle management unit predicts the future aircraft structure health status according to the current aircraft structure health status and the historical aircraft structure health status.

[0014] In a second aspect, the present application provides an aircraft structural health monitoring data processing device, which is applied to an onboard unit in an aircraft structural health monitoring system, and includes a processing module and an acquisition module.

[0015] A processing module, used for determining a target time source from a plurality of candidate time sources;

[0016] An acquisition module, used to acquire aircraft structural health monitoring data and time information of a target time source;

[0017] The processing module is also used to input the time information of the target time source as a timestamp into the aircraft structure health monitoring data to obtain the target monitoring data.

[0018] Optionally, the onboard unit is in communication with the configuration management unit; the processing module is specifically configured to receive a configuration message from the configuration management unit; and determine a target time source from a plurality of candidate time sources according to the configuration message.

[0019] Optionally, the configuration message is generated after the configuration management unit receives a user's selection operation on at least one candidate time source among a plurality of candidate time sources.

[0020] Optionally, the multiple candidate time sources include: RS422 bus time source, GNNS time source, and ARINC429 bus time source.

[0021] Optionally, the processing module is specifically used to obtain the target aircraft model of the aircraft where the airborne unit is located; determine the target time source according to the target aircraft model and a preset corresponding relationship; the preset corresponding relationship is used to characterize the corresponding relationship between multiple candidate time sources and aircraft models.

[0022] Optionally, the onboard unit has a communication connection with the data processing unit; the processing module is also used to send target monitoring data to the data processing unit, so that the data processing unit determines the current aircraft structure health status according to the target monitoring data, and the life cycle management unit predicts the future aircraft structure health status according to the current aircraft structure health status and the historical aircraft structure health status.

[0023] In a third aspect, the present application provides an aircraft structural health monitoring data processing method, which is applied to an aircraft structural health monitoring system, the aircraft structural health monitoring system including a configuration management unit and an airborne unit; the method includes:

[0024] The configuration management unit receives a user's selection operation of at least one candidate time source from a plurality of candidate time sources;

[0025] The configuration management unit generates a configuration message in response to the selection operation and sends it to the onboard unit;

[0026] The onboard unit determines a target time source from a plurality of candidate time sources according to the configuration message;

[0027] The onboard unit obtains aircraft structural health monitoring data and time information of a target time source;

[0028] The airborne unit uses the time information of the target time source as a timestamp into the aircraft structure health monitoring data to obtain the target monitoring data.

[0029] Optionally, the aircraft structure health monitoring system further includes a data processing unit and a life cycle management unit; the method further includes:

[0030] The data processing unit determines the current aircraft structural health status based on the target monitoring data;

[0031] The life cycle management unit predicts the future aircraft structural health status based on the current aircraft structural health status and historical aircraft structural health status.

[0032] In a fourth aspect, the present application provides an aircraft structure health monitoring system, the system comprising:

[0033] A configuration management unit, configured to receive a user's selection operation of at least one candidate time source from a plurality of candidate time sources; in response to the selection operation, generate a configuration message and send it to the onboard unit;

[0034] The airborne unit is used to determine a target time source from a plurality of candidate time sources according to a configuration message; obtain aircraft structural health monitoring data and time information of the target time source; and enter the time information of the target time source as a timestamp into the aircraft structural health monitoring data to obtain the target monitoring data.

[0035] Optionally, the aircraft structural health monitoring system further includes a data processing unit and a life cycle management unit;

[0036] A data processing unit, used to determine the current aircraft structural health status based on the target monitoring data;

[0037] The full life cycle management unit is used to predict the future aircraft structural health status based on the current aircraft structural health status and historical aircraft structural health status.

[0038] In a fifth aspect, the present application provides an airborne unit, which includes: a processor and a memory; the memory stores instructions executable by the processor; when the processor is configured to execute the instructions, the airborne unit implements the method described in the first aspect above.

[0039] In a sixth aspect, the present application provides a readable storage medium, which includes: software instructions; when the software instructions are executed on an onboard unit, the onboard unit implements the method described in the first aspect above.

[0040] In a seventh aspect, the present application provides a computer program product, which includes computer instructions; when the computer instructions are executed in an onboard unit, the onboard unit implements the method described in the first aspect above.

[0041] The beneficial effects of the second to seventh aspects mentioned above can be referred to the first aspect and will not be elaborated on again. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0043] Figure 1 A schematic diagram of the composition of an aircraft structural health monitoring system provided in an embodiment of the present application;

[0044] Figure 2 A flowchart of the configuration management unit 100 provided in an embodiment of the present application;

[0045] Figure 3 A flowchart of the time information collection and processing unit 210 provided in an embodiment of the present application;

[0046] Figure 4 A flowchart of the onboard unit 200 provided in an embodiment of the present application;

[0047] Figure 5 A flowchart of a method for processing aircraft structural health monitoring data provided by an embodiment of the present application;

[0048] Figure 6 A schematic diagram of the configuration message format definition provided in an embodiment of the present application;

[0049] Figure 7 A flowchart of another aircraft structure health monitoring data processing method provided in an embodiment of the present application;

[0050] Figure 8 A schematic diagram of the composition of an aircraft structural health monitoring data processing device provided in an embodiment of the present application;

[0051] Fig. 9 A schematic diagram of the composition of the airborne unit provided in an embodiment of the present application. DETAILED DESCRIPTION

[0052] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0053] It should be noted that, in the embodiments of the present application, words such as "exemplarily" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplarily" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplarily" or "for example" is intended to present related concepts in a specific way.

[0054] In order to facilitate the clear description of the technical solutions of the embodiments of the present application, in the embodiments of the present application, the words "first", "second", etc. are used to distinguish the same items or similar items with basically the same functions and effects. Those skilled in the art can understand that the words "first", "second", etc. are not limiting the quantity and execution order.

[0055] After an aircraft is put into operation, it is subjected to long-term loads such as fatigue and impact, as well as structural aging caused by changes in temperature, humidity, pressure and other conditions. These factors can lead to a decline in aircraft structural performance or even component damage, causing catastrophic accidents.

[0056] In order to avoid accidents, the relevant technology can add an aircraft structural health monitoring system to the aircraft to monitor the aircraft body structural strength in real time. For example, the aircraft structural health monitoring system can include multiple sensors, and the aircraft structural health monitoring system can collect aircraft structural health monitoring data through multiple sensors, and monitor the aircraft body structural strength in real time based on the aircraft structural health monitoring data.

[0057] However, the aircraft structural health monitoring data collected by the aircraft structural health monitoring system of the related art has poor validity, and the aircraft structural health monitoring data is prone to failure.

[0058] Based on this, the embodiments of the present application provide an aircraft structural health monitoring data processing method and an airborne unit storage medium, which can be compatible with multiple time sources, avoid the aircraft being unable to provide a single type of time source supported by a certain aircraft structural health monitoring system, and avoid the aircraft structural health monitoring data being invalid due to the lack of time reference provided by the time source.

[0059] The following is an introduction with reference to the accompanying drawings.

[0060] Figure 1 This is a schematic diagram of the components of the aircraft structural health monitoring system provided in the embodiment of the present application. Figure 1 As shown, the system includes: a configuration management unit 100 and an onboard unit 200. The configuration management unit 100 and the onboard unit 200 are connected in communication.

[0061] The configuration management unit 100 may be an electronic device with computing and processing functions, such as a server or a computer.

[0062] Among them, the server can be a single server, or it can be a server cluster composed of multiple servers. In some implementations, the server cluster can also be a distributed cluster. Optionally, the server can also be implemented on a cloud platform. For example, the cloud platform can include a private cloud, a public cloud, a hybrid cloud, a community cloud, a distributed cloud, an inter-cloud, and a multi-cloud, etc., or any combination thereof. The embodiments of the present application are not limited to this.

[0063] The configuration management unit 100 may be configured to receive a user's selection operation of at least one candidate time source from a plurality of candidate time sources; in response to the selection operation, generate a configuration message and send it to the onboard unit 200 .

[0064] For example, the configuration management unit 100 may include an input / output interface, which is connected to a display, a keyboard, and a mouse. The configuration management unit 100 may send relevant data to the display through the input / output interface, and display a first human-computer interaction interface through the display, and the first human-computer interaction interface may include multiple candidate time sources. Then, the configuration management unit 100 may receive a user's selection operation of at least one of the multiple candidate time sources through a mouse or keyboard.

[0065] As an example, the multiple candidate time sources may include: Recommended Standard (RS) 422 bus time source, Global Navigation Satellite System (GNNS) time source, and Aeronautical Radio Inc (ARINC) 429 bus time source.

[0066] The airborne unit 200 can be used to determine a target time source from a plurality of candidate time sources according to a configuration message; obtain aircraft structural health monitoring data and time information of the target time source; and enter the time information of the target time source as a timestamp into the aircraft structural health monitoring data to obtain the target monitoring data.

[0067] In some embodiments, the onboard unit 200 may include a time information acquisition and processing unit 210 , a data acquisition unit 220 , and a time stamping unit 230 .

[0068] The time information collection and processing unit 210 may be configured to determine a target time source from a plurality of candidate time sources according to a configuration message, and obtain time information of the target time source.

[0069] The data acquisition unit 220 may be used to acquire aircraft structural health monitoring data.

[0070] For example, the data acquisition unit 220 may be a fiber Bragg grating data acquisition unit, and the aircraft structure health monitoring data may specifically be fiber Bragg grating data.

[0071] In some embodiments, the configuration management unit 100 can also configure the data acquisition unit 220. For example, taking the data acquisition unit 220 as a fiber Bragg grating data acquisition unit, the configuration management unit 100 can send relevant data to the display through the input and output interface, display the second human-computer interaction interface through the display, and the configuration management unit 100 can receive the configuration information input by the user in the second human-computer interaction interface and send the configuration information to the fiber Bragg grating data acquisition unit.

[0072] The time stamping unit 230 may stamp the time information of the target time source into the aircraft structure health monitoring data as a time stamp to obtain the target monitoring data.

[0073] In some embodiments, taking the above-mentioned multiple candidate time sources including RS422 bus time source, GNNS time source, and ARINC429 bus time source as an example, the time information acquisition and processing unit 210 can specifically include: RS422 bus configuration receiving and parsing unit 211, ARINC429 bus configuration receiving and parsing unit 212, RS422 bus data acquisition unit 213, ARINC429 bus data acquisition unit 214, GNSS unit 215, NMEA message parsing unit 216, and ARINC429 bus data parsing unit 217.

[0074] The RS422 bus configuration receiving and parsing unit 211 is used to receive the configuration message from the configuration management unit 100 , parse it according to the configuration protocol, obtain the configuration information, and send the configuration information to the RS422 bus data acquisition unit 213 .

[0075] The RS422 bus data acquisition unit 213 is used to receive the configuration information from the RS422 bus configuration receiving and parsing unit 211, and complete the collection of RS422 bus data (or the National Marine Electronics Association (NMEA) standard message (referred to as NMEA message)) according to the configuration information, and send the NMEA message to the NMEA message parsing unit 216.

[0076] The GNSS unit 215 is used to receive a radio frequency input signal through an antenna, process the received radio frequency input signal, generate a NMEA message, and send the NMEA message to the NMEA message parsing unit 216 .

[0077] The NMEA message parsing unit 216 is used to receive the NMEA message from the RS422 bus data acquisition unit 213 or the GNSS unit 215, and parse the NMEA message according to the NMEA protocol to obtain the time information of the RS422 bus time source or the time information of the GNSS time source (that is, the time information of the above-mentioned target time source), and send the parsed time information to the timestamping unit 230.

[0078] The ARINC429 bus configuration receiving and parsing unit 212 is used to receive the configuration message from the configuration management unit 100 , parse it according to the configuration protocol, obtain the configuration information, and send the configuration information to the ARINC429 bus data acquisition unit 214 .

[0079] The ARINC429 bus data acquisition unit 214 is used to receive the configuration information from the ARINC429 bus configuration receiving and parsing unit 212, complete the collection of ARINC429 bus data according to the configuration information, and send the ARINC429 bus data to the ARINC429 bus data parsing unit 217.

[0080] The ARINC429 bus data parsing unit 217 is used to receive the ARINC429 bus data from the ARINC429 bus data acquisition unit 214, and parse the ARINC429 bus data according to the ARINC429 bus protocol, extract the time information of the ARINC429 bus time source (that is, the time information of the above-mentioned target time source), and send the extracted time information to the timestamping unit 230.

[0081] In some embodiments, the airborne unit 200 may further include a data storage unit 240. After the time stamping unit 230 inserts the time information of the target time source as a time stamp into the aircraft structural health monitoring data to obtain the target monitoring data, it may also send the target monitoring data to the data storage unit 240. The data storage unit 240 may be used to receive and store the target monitoring data from the time stamping unit 230.

[0082] For example, the data storage unit 240 may store the target monitoring data in a file system format compatible with the computer Windows system.

[0083] In some embodiments, the onboard unit 200 may further include a data unloading unit 250. The aircraft structural health monitoring system may further include a data processing unit 300 (the specific form of the data processing unit 300 may refer to the configuration management unit 100 described above, and will not be repeated here). The data unloading unit 250 may be used to copy the target monitoring data stored in the data storage unit 240, and then send the target monitoring data (or a copy of the target monitoring data) to the data processing unit 300. The data processing unit 300 may determine the current aircraft structural health status based on the target monitoring data.

[0084] In some embodiments, the aircraft structure health monitoring system may further include a life cycle management unit 400 (the specific form of the life cycle management unit 400 may refer to the configuration management unit 100 described above, and will not be described in detail here). The data processing unit 300 may also send the current aircraft structure health status to the life cycle management unit 400. The life cycle management unit 400 may predict the future aircraft structure health status based on the current aircraft structure health status and the historical aircraft structure health status.

[0085] Based on the understanding of the above embodiments, Figure 2 The following is a flowchart of the configuration management unit 100 provided in the embodiment of the present application. Figure 2 As shown, the workflow of the configuration management unit 100 may include the following steps:

[0086] S101, reading a time source configuration from a first human-machine interface.

[0087] S102: Determine the type of the time source.

[0088] If the time source is an RS422 bus time source, execute S103 and then execute S105; if the time source is an ARINC429 bus time source, execute S104 and then execute S105; if the time source is a GNSS time source, execute S105 directly.

[0089] S103: Pack and output RS422 bus data acquisition configuration message according to the configuration protocol.

[0090] S104: Pack and output the ARINC429 bus data acquisition configuration message according to the configuration protocol.

[0091] S105 , reading the fiber Bragg grating acquisition configuration information from the second human-machine interface, and outputting it to the fiber Bragg grating acquisition unit.

[0092] Based on the understanding of the above embodiments, Figure 3 FIG. 2 is a flowchart of the time information collection and processing unit 210 provided in the embodiment of the present application. Figure 3As shown, the workflow of the time information collection and processing unit 210 may include the following steps:

[0093] S201. Receive a configuration message.

[0094] The configuration message may include the RS422 bus data acquisition configuration message or the ARINC429 bus data acquisition configuration message.

[0095] S202: Determine the type of the time source.

[0096] If the time source is an RS422 bus time source, execute S203 and S204 before executing S206; if the time source is an ARINC429 bus time source, execute S205 before executing S206; if the time source is a GNSS time source, execute S207 to S209.

[0097] S203, receiving RS422 bus collection configuration message and parsing the configuration message according to the configuration protocol.

[0098] S204, completing RS422 bus data, ie, NMEA message collection according to the parsed configuration information.

[0099] S205: Receive a radio frequency input signal through the antenna, and generate a NMEA message after signal processing.

[0100] S206: Parse the NMEA message according to the NMEA protocol, extract the time information and output it.

[0101] S207, receiving an ARINC429 bus acquisition configuration message and parsing the configuration message according to a configuration protocol.

[0102] S208. Complete ARINC429 bus data collection according to the parsed configuration information.

[0103] S209, parsing ARINC429 bus data according to the ARINC429 bus protocol, extracting time information and outputting it.

[0104] Based on the understanding of the above embodiments, Figure 4 This is a flowchart of the onboard unit 200 provided in the embodiment of the present application. Figure 4 As shown, the workflow of the onboard unit 200 may include the following steps:

[0105] S301: Receive a configuration message sent by the configuration management unit 100 and parse out configuration information.

[0106] The configuration information may include time configuration information and fiber grating acquisition configuration information.

[0107] S302: Complete the collection, processing and extraction of time information according to the time configuration information.

[0108] S303, completing fiber Bragg grating data acquisition according to the fiber Bragg grating configuration information.

[0109] S304: Use the time information as a timestamp to stamp the fiber Bragg grating data to form a new fiber Bragg grating data packet.

[0110] S305, storing the new fiber grating data packet in a file system format compatible with the computer Windows system.

[0111] S306: Copy the stored data packet to a subsequent unit for subsequent analysis.

[0112] It should be noted that the above description is based on the example that the configuration management unit 100, the airborne unit 200, the data processing unit 300, and the full life cycle management unit 400 are independent devices. Optionally, any two or more of the configuration management unit 100, the airborne unit 200, the data processing unit 300, and the full life cycle management unit 400 can be combined into one.

[0113] As an example, the configuration management unit 100 or its corresponding functions and the airborne unit 200 or its corresponding functions may be integrated into one device, for example, an airborne unit having a configuration management function and an aircraft structural health monitoring data processing function.

[0114] As another example, the onboard unit 200 or its corresponding function, the data processing unit 300 or its corresponding function, and the lifecycle management unit 400 or its corresponding function may be integrated into one device, for example, an onboard unit having the functions of processing aircraft structure health monitoring data, determining the current aircraft structure health status, and predicting the future aircraft structure health status.

[0115] As another example, the configuration management unit 100 or its corresponding function, the data processing unit 300 or its corresponding function, and the lifecycle management unit 400 or its corresponding function may be integrated into one device, for example, a ground computing device having a configuration management function, a function of determining the current aircraft structure health status, and a function of predicting the future aircraft structure health status.

[0116] As another example, the configuration management unit 100 or its corresponding function, the airborne unit 200 or its corresponding function, the data processing unit 300 or its corresponding function, and the lifecycle management unit 400 or its corresponding function may be integrated into one device, for example, an airborne unit having a configuration management function, an aircraft structure health monitoring data processing function, a function of determining the current aircraft structure health status, and a function of predicting the future aircraft structure health status.

[0117] The following is an introduction to the aircraft structure health monitoring data processing method provided in an embodiment of the present application.

[0118] In some possible embodiments, the embodiments of the present application provide a method for processing aircraft structural health monitoring data. The method can be applied to an onboard unit (such as the above-mentioned onboard unit 200) of an aircraft structural health monitoring system. Figure 5 The following is a flow chart of a method for processing aircraft structural health monitoring data provided by an embodiment of the present application. Figure 5 As shown, the method includes the following steps:

[0119] S401: Determine a target time source from multiple candidate time sources.

[0120] The target time source may be one of a plurality of candidate time sources, and the target time source may be understood as a candidate time source that can be provided by the aircraft where the current airborne unit is located.

[0121] For example, as described above, the multiple candidate time sources may include: RS422 bus time source, GNNS time source, and ARINC429 bus time source. The airborne unit may select one of the RS422 bus time source, GNNS time source, and ARINC429 bus time source as the target time source.

[0122] S402: Acquire aircraft structure health monitoring data and time information of a target time source.

[0123] For example, as mentioned above, the aircraft structural health monitoring data may specifically be fiber Bragg grating data.

[0124] S403: Enter the time information of the target time source as a timestamp into the aircraft structure health monitoring data to obtain target monitoring data.

[0125] It should be understood that the aircraft structural health monitoring system of the related art usually uses a single time source to provide a time reference for the aircraft structural health monitoring data. However, since different aircraft models can provide different time sources, if a certain flight model cannot provide the time source required by the aircraft structural health monitoring system, it cannot provide an accurate time reference for the aircraft structural health monitoring system, and the aircraft structural health monitoring data recorded by it will also be invalid, resulting in poor validity of the aircraft structural health monitoring data, and the aircraft structural health monitoring data is prone to invalidation.

[0126] In the aircraft structural health monitoring data processing method provided in the embodiment of the present application, the onboard unit can determine the target time source from multiple candidate time sources, obtain the time information of the target time source, and use the time information of the target time source as a timestamp to enter the aircraft structural health monitoring data to obtain the target monitoring data. The onboard unit can support and be compatible with multiple candidate time sources, thereby avoiding the situation where the aircraft cannot provide a single type of time source supported by a certain aircraft structural health monitoring system, and avoiding the aircraft structural health monitoring data from being invalid due to the lack of a time reference provided by the time source.

[0127] The specific process of the above S401 is introduced below.

[0128] In some embodiments, there is a communication connection between the onboard unit (onboard unit 200) and the configuration management unit (configuration management unit 100) as described above. In this case, the above S401 may include the following steps:

[0129] Step 1a: Receive a configuration message from a configuration management unit.

[0130] Among them, the configuration message may include a time source selection field.

[0131] For example, Figure 6 This is a schematic diagram of the configuration message format definition provided in the embodiment of the present application. Figure 6 As shown, the configuration message ( Figure 6 Taking IUTE_Message as an example) may specifically include a message header ( Figure 6 IUTE_Headr is used as an example), message command field ( Figure 6 IUTE_Cmd is used as an example), data length ( Figure 6 IUTE_DataLength is used as an example), configure the content field ( Figure 6 ), and the cyclic redundancy check field ( Figure 6 IUTE_CRC is used as an example in the figure).

[0132] Among them, IUTE_Headr occupies 32 bits and has a fixed value of 0xFE6B2840.

[0133] IUTE_Cmd occupies 8 bits and is the message command field. The specific content can be shown in the following Table 1:

[0134] Table 1

[0135]

[0136] For example, as shown in Table 1, when IUTE_Cmd is 0x00, to save the configuration, IUTE_Data=0x00, and the device restarts after saving the parameters. The value of the 16-bit field of IUTE_Data can be specifically shown in Table 2 below:

[0137] Table 2

[0138]

[0139] Exemplarily, as shown in Table 1, when IUTE_Cmd is 0x01, IUTE_Data is a (candidate) time source selection, and the (candidate) time source may include a GNSS time source, an RS422 bus time source, and an ARINC429 bus time source. The meaning of the 16-bits field of IUTE_Data may be specifically shown in the following Table 3:

[0140] Table 3

[0141]

[0142] As shown in Table 3, when IUTE_Cmd is 0x01, the first and the second bits in the 16-bit field of IUTE_Data can be used to indicate the selected time source.

[0143] For example, as shown in Table 1, when IUTE_Cmd is 0x02, IUTE_Data is the RS422 bus acquisition configuration, specifically including the channel number, baud rate, data bit, stop bit, and check bit. At this time, the meaning of the 16 bits field of IUTE_Data can be specifically shown in the following Table 4:

[0144] Table 4

[0145]

[0146] As shown in Table 4, bits 14 to 12 of IUTE_Data can be used to indicate message selection, bit 11 can be used to indicate the channel number, bits 10 and 9 can be used to indicate data bits, bits 8 and 7 can be used to indicate stop bits, bits 6 and 4 can be used to indicate check bits, and bits 3 to 0 can be used to indicate baud rate.

[0147] For example, as shown in Table 1, when IUTE_Cmd is 0x03, IUTE_Data is the ARINC429 bus acquisition configuration, including channel number, transmission rate, source / destination identifier, label (supporting up to 32 labels), data bit, and check bit. At this time, the meaning of the 16-bit field of IUTE_Data can be specifically shown in the following Tables 5 and 6:

[0148] Table 5

[0149]

[0150] As shown in Table 5, bit 15 of IUTE_Data can be used to indicate the data bit, bits 14 to 12 can be used to indicate the source / destination identifier, bits 11 to 10 can be used to indicate the check bit, bit 9 can be used to indicate the channel number, bit 8 can be used to indicate the transmission rate, and bits 7 to 0 can be used to indicate the label.

[0151] Table 6

[0152]

[0153] As shown in Table 6, bits 15 to 8 of IUTE_Data can be used to represent a label (label 1 is shown as an example in Table 6), and bits 7 to 0 can be used to represent another label (label 2 is shown as an example in Table 6).

[0154] For example, as shown in Table 1, when IUTE_Cmd is 0x04, IUTE_Data is GNSS configuration, specifically including message selection and baud rate. In this case, the meaning of the 16-bit field of IUTE_Data can be specifically shown in the following Table 7:

[0155] Table 7

[0156]

[0157] As shown in Table 7, bits 14 to 12 of IUTE_Data may be used to indicate message selection, and bits 3 to 0 may be used to indicate baud rate.

[0158] IUTE_CRC occupies 8 bits and uses XOR check.

[0159] Step 2a: According to the configuration message, determine the target time source from multiple candidate time sources.

[0160] In some other embodiments, the onboard unit may store the correspondence between the multiple candidate time sources and the aircraft models. In this case, the above S401 may specifically include the following steps:

[0161] Step 1b: Obtain the target aircraft model of the aircraft where the airborne unit is located.

[0162] Step 2b: Determine the target time source according to the target aircraft model and the preset corresponding relationship.

[0163] The preset corresponding relationship is used to characterize the corresponding relationship between multiple candidate time sources and aircraft models.

[0164] Optionally, the airborne unit may use the target aircraft model as an index to traverse and search for preset corresponding relationships, and use the candidate time source corresponding to the target aircraft model in the preset corresponding relationship as the target time source.

[0165] Exemplarily, the preset corresponding relationship may be specifically shown in the following Table 8:

[0166] Table 8

[0167]

[0168] As shown in Table 8, the monogram may include an aircraft model item and a candidate time source item. Among them, the aircraft model item may include: Model 1, Model 2, and Model 3. The candidate time source item may include: RS422 bus time source and GNNS time source, ARINC429 bus time source and GNNS time source, and GNNS time source. Model 1 has a corresponding relationship with the RS422 bus time source and the GNNS time source. Model 2 has a corresponding relationship with the ARINC429 bus time source and the GNNS time source. Model 3 has a corresponding relationship with the GNNS time source.

[0169] In some possible embodiments, as described above, the onboard unit (onboard unit 200) is also connected to the data processing unit (data processing unit 300) for communication. In this case, the onboard unit may also send target monitoring data to the data processing unit, so that the data processing unit determines the current aircraft structure health state according to the target monitoring data, and the life cycle management unit predicts the future aircraft structure health state according to the current aircraft structure health state and the historical aircraft structure health state.

[0170] The aircraft structure health monitoring data processing method provided in the embodiment of the present application can also adopt a full life cycle management unit, which can not only process and analyze the current aircraft structure health monitoring data, but also predict the future aircraft structure health status based on the healthy development trend of the aircraft structure throughout its life cycle.

[0171] In an exemplary embodiment, the present application also provides another aircraft structural health monitoring data processing method, which can be applied to an aircraft structural health monitoring system. For example, as described above, the aircraft structural health monitoring system may include a configuration management unit (configuration management unit 100) and an airborne unit (airborne unit 200). Figure 7 A flowchart of another aircraft structure health monitoring data processing method provided in an embodiment of the present application. Figure 7 As shown, the method includes the following steps:

[0172] S501: A configuration management unit receives a user's selection operation of at least one candidate time source from a plurality of candidate time sources.

[0173] S502: In response to the selection operation, the configuration management unit generates a configuration message and sends it to the onboard unit.

[0174] S503: The onboard unit determines a target time source from a plurality of candidate time sources according to the configuration message.

[0175] S504: The airborne unit obtains aircraft structural health monitoring data and time information of a target time source.

[0176] S505. The airborne unit uses the time information of the target time source as a timestamp and enters it into the aircraft structure health monitoring data to obtain target monitoring data.

[0177] The specific process from S501 to S505 can refer to the above Figure 1 The above-mentioned steps S401 to S403 are not described here in detail.

[0178] In some embodiments, the aircraft structural health monitoring system further includes a data processing unit and a full life cycle management unit. In this case, the method may further include the following steps:

[0179] Step 1c: The data processing unit determines the current aircraft structure health status based on the target monitoring data.

[0180] For example, the data processing unit may be preset with a correspondence between aircraft structure health monitoring data and aircraft structure health status, and the data processing unit may determine the current aircraft structure health status based on the target monitoring data and the correspondence.

[0181] Step 2c: The life cycle management unit predicts the future aircraft structure health state based on the current aircraft structure health state and the historical aircraft structure health state.

[0182] In a possible implementation, the full life management unit may use a deep learning model to predict the future aircraft structural health state based on the current aircraft structural health state and the historical aircraft structural health state. In this case, the above step 2c may specifically include:

[0183] Step 2.1c: The life cycle management unit predicts the future aircraft structural health status based on the current aircraft structural health status, the historical aircraft structural health status, and the structural health status prediction model.

[0184] Among them, the structural health status prediction model has the function of predicting the future aircraft structural health status based on the current aircraft structural health status and historical aircraft structural health status.

[0185] Optionally, before the above step 2.1c, the life cycle management unit may also obtain a trained structural health status prediction model.

[0186] In one possible implementation, the life cycle management unit can directly obtain the trained structural health status prediction model from other devices.

[0187] In another possible implementation, the life cycle management unit can be trained to obtain a structural health status prediction model. In this case, before the above step 2.1c, the method can also include the following steps:

[0188] Step 1d: The full life cycle management unit obtains a training sample set.

[0189] The training sample set includes multiple training samples. Each training sample is a time series of aircraft structural health status. The label of the training sample is the aircraft structural health status at a future moment in the time series.

[0190] Step 2d: The life cycle management unit trains the preset initial model based on the training sample set to obtain a structural health status prediction model.

[0191] Among them, the preset initial model can be a long short-term memory (LSTM) network model.

[0192] Optionally, as described above, the training sample set may include multiple training samples. In this case, the full life cycle management unit may input one or more training samples into the LSTM network model each time to obtain the predicted value of the LSTM network model, and calculate the loss function (loss) according to the predicted value and the label of the training sample, and adjust the parameters in the LSTM network model according to the loss function until the LSTM network model converges to obtain the structural health status prediction model.

[0193] Optionally, the conditions for the LSTM network model to converge may include: the number of times the training sample is input into the LSTM network model reaches a number threshold, and / or the error of the LSTM network model is less than an error threshold.

[0194] Among them, the number threshold can be preset in the full life cycle management unit. For example, the number threshold can be set to 500 times, 1000 times, or 10000 times. The embodiment of the present application does not limit the specific value of the number threshold. The error threshold can be preset in the full life cycle management unit. For example, the error threshold can be set to 5%, 8%, or 10%. The embodiment of the present application does not limit the specific value of the error threshold.

[0195] The above mainly introduces the solution provided by the embodiment of the present application from the perspective of the method. In order to achieve the above functions, it includes hardware structures and / or software modules corresponding to the execution of each function. It should be easy to realize that the technical goals in this field are combined with the units and algorithm steps of each example described in the embodiments disclosed in this article, and the present application can be implemented in the form of hardware or a combination of hardware and computer software. Whether a function is executed in the form of hardware or computer software driving hardware depends on the specific application and design constraints of the technical solution. Professional and technical goals can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0196] In an exemplary embodiment, the present application also provides an aircraft structural health monitoring data processing device, which can be applied to the above-mentioned airborne unit. Figure 8 This is a schematic diagram of the composition of the aircraft structure health monitoring data processing device provided in the embodiment of the present application. Figure 8 As shown, the device includes: a processing module 801 and an acquisition module 802.

[0197] Processing module 801, used to determine a target time source from multiple candidate time sources;

[0198] An acquisition module 802 is used to acquire aircraft structural health monitoring data and time information of a target time source;

[0199] The processing module 801 is further used to input the time information of the target time source as a timestamp into the aircraft structure health monitoring data to obtain the target monitoring data.

[0200] In some possible embodiments, the onboard unit is in communication with the configuration management unit; the processing module 801 is specifically configured to receive a configuration message from the configuration management unit; and determine a target time source from a plurality of candidate time sources according to the configuration message.

[0201] In some other possible embodiments, the configuration message is generated after the configuration management unit receives a user's selection operation on at least one candidate time source among a plurality of candidate time sources.

[0202] In some other possible embodiments, the multiple candidate time sources include: an RS422 bus time source, a GNNS time source, and an ARINC429 bus time source.

[0203] In some other possible embodiments, the processing module 801 is specifically used to obtain the target aircraft model of the aircraft where the airborne unit is located; determine the target time source according to the target aircraft model and a preset correspondence relationship; the preset correspondence relationship is used to characterize the correspondence between multiple candidate time sources and aircraft models.

[0204] In some other possible embodiments, the onboard unit has a communication connection with the data processing unit; the processing module 801 is also used to send target monitoring data to the data processing unit, so that the data processing unit determines the current aircraft structure health status according to the target monitoring data, and the life cycle management unit predicts the future aircraft structure health status according to the current aircraft structure health status and the historical aircraft structure health status.

[0205] It should be noted that the above description of the aircraft structural health monitoring data processing device is only an example. The device may include Figure 8 The structure shown has more or fewer components, which is not limited in the embodiments of the present application.

[0206] In an exemplary embodiment, the present application also provides an airborne unit. Fig. 9 The following is a schematic diagram of the composition of the airborne unit provided in the embodiment of the present application. Fig. 9 As shown, the airborne unit includes: a processor 901 and a memory 902; the memory 902 stores instructions executable by the processor 901; when the processor 901 is configured to execute the instructions, the airborne unit implements the method described in the aforementioned method embodiment.

[0207] In an exemplary embodiment, the embodiment of the present application further provides a computer program product, which includes computer instructions; when the computer instructions are executed in an onboard unit, the onboard unit implements the method described in the aforementioned method embodiment.

[0208] In an exemplary embodiment, the embodiment of the present application further provides a readable storage medium, which includes: software instructions. When the software instructions are executed in the onboard unit, the onboard unit implements the method described in the aforementioned method embodiment. The computer-readable storage medium may be a non-temporary computer-readable storage medium, for example, the non-temporary computer-readable storage medium may be a ROM, a random access memory (RAM), a CD-ROM, a magnetic tape, a floppy disk, an optical data storage device, etc.

[0209] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented using a software program, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer-executable instructions. When the computer-executable instructions are loaded and executed on a computer, the process or function according to the embodiment of the present application is generated in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer-executable instructions can be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium. For example, the computer-executable instructions can be transmitted from a website site, a computer, a server or a data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) mode to another website site, computer, server or data center.

[0210] Although the present application is described herein in conjunction with various embodiments, in the process of implementing the claimed application, those skilled in the art may understand and implement other changes to the disclosed embodiments by viewing the drawings, the disclosure, and the appended claims. In the claims, the word "comprising" does not exclude other components or steps, and "one" or "an" does not exclude multiple situations. A single processor or other unit may implement several functions listed in a claim. Certain measures are recorded in different dependent claims, but this does not mean that these measures cannot be combined to produce good results.

[0211] Although the present application has been described in conjunction with specific features and embodiments thereof, it is obvious that various modifications and combinations may be made thereto without departing from the spirit and scope of the present application. Accordingly, this specification and the drawings are merely exemplary illustrations of the present application as defined by the appended claims, and are deemed to have covered any and all modifications, variations, combinations or equivalents within the scope of the present application. Obviously, those skilled in the art may make various modifications and variations to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

[0212] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A method for processing aircraft structural health monitoring data, characterized in that: The method is applied to an onboard unit of an aircraft structural health monitoring system; The onboard unit is in communication with the configuration management unit; the method comprises: Receiving a configuration message from the configuration management unit; determining a target time source from a plurality of candidate time sources according to the configuration message; the configuration message is generated after the configuration management unit receives a user's selection operation of at least one candidate time source from the plurality of candidate time sources; or, Obtaining a target aircraft model of the aircraft where the airborne unit is located; determining a target time source according to the target aircraft model and a preset corresponding relationship; the preset corresponding relationship is used to characterize the corresponding relationship between multiple candidate time sources and aircraft models; Acquiring aircraft structural health monitoring data and time information of the target time source; Entering the time information of the target time source as a timestamp into the aircraft structure health monitoring data to obtain target monitoring data; The target monitoring data is sent to a data processing unit, so that the data processing unit determines the current aircraft structure health state according to the target monitoring data, and the life cycle management unit predicts the future aircraft structure health state according to the current aircraft structure health state and the historical aircraft structure health state.

2. The method according to claim 1, characterized in that The multiple candidate time sources include: an RS422 bus time source, a GNNS time source, and an ARINC429 bus time source.

3. An aircraft structural health monitoring system, characterized in that: The system comprises: A configuration management unit, configured to receive a user's selection operation of at least one candidate time source from a plurality of candidate time sources; in response to the selection operation, generate a configuration message and send it to the onboard unit; The airborne unit is configured to determine a target time source from the multiple candidate time sources according to the configuration message; or obtain a target aircraft model of the aircraft where the airborne unit is located; determine a target time source according to the target aircraft model and a preset corresponding relationship; the preset corresponding relationship is used to characterize the corresponding relationship between multiple candidate time sources and aircraft models; The onboard unit is further used to obtain aircraft structure health monitoring data and time information of the target time source; the time information of the target time source is used as a timestamp to enter the aircraft structure health monitoring data, obtain target monitoring data and send it to the data processing unit; a data processing unit, configured to determine a current aircraft structural health status based on the target monitoring data; The full life cycle management unit is used to predict the future aircraft structure health state based on the current aircraft structure health state and the historical aircraft structure health state.

4. An airborne unit, characterized in that: The onboard unit includes: a processor and a memory; The memory stores instructions executable by the processor; When the processor is configured to execute the instructions, the onboard unit implements the method as described in claim 1 or 2.

5. A readable storage medium, characterized in that: The readable storage medium includes: software instructions; When the software instructions are executed on the onboard unit, the onboard unit is enabled to implement the method according to claim 1 or 2.

6. A computer program product, characterized in that The computer program product comprises computer instructions; When the computer instructions are executed in an onboard unit, the onboard unit is caused to implement the method according to claim 1 or 2.

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