Aircraft structure integrity monitoring method, system, equipment and medium

Abstract

The invention discloses an aircraft structure integrity monitoring method, system and device and a medium, and the method comprises the steps: collecting the identification information of aircraft structure maintenance / modification, recognizing the identification information according to a preset condition, obtaining a recognition result, and sending an aircraft structure integrity evaluation task according to the recognition result; wherein the evaluation task is used for instructing a user to perform aircraft structure integrity evaluation to obtain an evaluation result, and an aircraft structure integrity analysis report is generated based on the evaluation result. According to the embodiment of the invention, the monitoring of the structural integrity of the aircraft can be efficiently, accurately and traceably realized, and the monitoring level of the structural integrity of the aircraft can be effectively improved, so that the safe operation of the aircraft is ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft structure identification, and in particular to an aircraft structure integrity monitoring method, system, equipment and medium. Background Art

[0002] The structural integrity of an aircraft is a key factor in aircraft safety. After the structure of the aircraft is designed, various deviations and damages may occur during the production and maintenance process. Monitoring and tracking of repairs / modifications involving important structures is essential. Many air crashes in history were caused by irregular modifications and repairs that failed to ensure the structural integrity of the aircraft. In order to ensure the structural integrity of the aircraft, regular inspections are required to ensure the records of modifications and repairs, and to ensure that the modifications and repairs are correct and in good condition.

[0003] The existing method of inspecting structural repairs and modifications usually involves engineers reviewing the aircraft's historical execution records, identifying the structural repair and modification documents, and then sorting out the repairs and modifications that need to be inspected on site. The repair and modification information that needs to be inspected on site is then compiled into a list for frontline workers to inspect. Finally, based on the execution documents inspected by the frontline workers, engineers evaluate the aircraft's repair and modification status and determine follow-up work. This process repeats itself in the next inspection cycle.

[0004] However, as the aircraft ages, the number of structural repairs and modifications will increase, and the search and organization of relevant aviation material information, manual information, and maintenance records is very time-consuming; at the same time, the aircraft's structural repair and modification data are scattered across various units and departments, relying on manual monitoring methods, which are cumbersome and not only inefficient but also prone to omissions and loss of control. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a method, system, equipment and medium for monitoring aircraft structural integrity, which can effectively improve the monitoring efficiency and accuracy of aircraft structural integrity and ensure the safe operation of aircraft.

[0006] In order to solve the above technical problems, an embodiment of the present invention provides an aircraft structure integrity monitoring method, comprising:

[0007] Collect identification information of aircraft structural maintenance / modification;

[0008] Identify the identification information according to preset conditions to obtain an identification result;

[0009] Sending an aircraft structural integrity assessment task according to the identification result; wherein the assessment task is used to instruct a user to perform an aircraft structural integrity assessment and obtain an assessment result;

[0010] An aircraft structural integrity analysis report is generated based on the evaluation results.

[0011] As an improvement of the above solution, after identifying the identification information according to the preset conditions and obtaining the identification result, the method further includes:

[0012] According to the recognition result, identification information of aircraft structure maintenance / modification that meets preset conditions is stored in a pre-built database.

[0013] As an improvement of the above solution, the acquisition of identification information of aircraft structure maintenance / modification includes:

[0014] The identification information of the aircraft structure maintenance / modification is collected from the pre-built database according to the preset time.

[0015] Specifically, the identification information includes at least one of an important structure identification, a fatigue critical structure identification and a structure modification identification.

[0016] As an improvement of the above solution, the identification information is identified according to a preset condition to obtain an identification result, including:

[0017] When it is identified that the identification information includes at least one of an important structure identification, a fatigue critical structure identification, and a structure modification identification, obtaining an identification result;

[0018] The recognition result includes key data for aircraft structure maintenance / modification corresponding to the identification information that needs to be evaluated.

[0019] As an improvement of the above scheme, the aircraft structural integrity assessment task includes a textual assessment task and a textual assessment task;

[0020] Wherein, the document evaluation task is to check the correctness of the aircraft structure maintenance / modification according to the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the designated document;

[0021] The documented factual assessment task is to conduct on-site verification of the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the on-site conditions of the aircraft.

[0022] In order to solve the above technical problems, an embodiment of the present invention further provides an aircraft structure integrity monitoring system, comprising:

[0023] An identification information acquisition module is used to obtain identification information of aircraft structure maintenance / modification from a pre-built database according to a preset time;

[0024] An identification recognition module, used to recognize the identification information according to preset conditions and obtain a recognition result;

[0025] An assessment task issuing module, used to send an aircraft structural integrity assessment task according to the identification result; wherein the assessment task is used to instruct a user to perform an aircraft structural integrity assessment and obtain an assessment result;

[0026] The analysis report generating module is used to generate an aircraft structural integrity analysis report based on the evaluation result.

[0027] As an improvement of the above solution, the aircraft structural integrity monitoring system further includes an identification information storage module, which is used to:

[0028] According to the recognition result, identification information of aircraft structure maintenance / modification that meets preset conditions is stored in a pre-built database.

[0029] To solve the above technical problems, an embodiment of the present invention further provides a terminal device, comprising a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein the processor implements the aircraft structural integrity monitoring method as described in any one of the above when executing the computer program.

[0030] In order to solve the above technical problems, an embodiment of the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute any one of the aircraft structural integrity monitoring methods described above.

[0031] Compared with the prior art, the embodiment of the present invention provides an aircraft structural integrity monitoring method, system, device and medium, wherein the method includes collecting identification information of aircraft structure maintenance / modification, identifying the identification information according to preset conditions, obtaining identification results, and sending an aircraft structural integrity assessment task according to the identification results; wherein the assessment task is used to instruct the user to perform an aircraft structural integrity assessment, obtain an assessment result, and generate an aircraft structural integrity analysis report based on the assessment result. The embodiment of the present invention identifies the identification information by preset conditions, and can automatically screen out the items that need to be evaluated, reduce the workload of manual screening, and improve efficiency; automatically generate an assessment task according to the identification result, which can save time for manually writing assessment tasks and improve assessment efficiency; identify and evaluate by preset conditions, which can ensure the standardization of the assessment process and reduce human errors; through data analysis, the integrity of the aircraft structure can be more effectively monitored and potential safety hazards can be discovered in a timely manner. In addition, by collecting and analyzing the maintenance / modification identification information, a large amount of structural integrity data can be accumulated to provide data support for subsequent structural integrity management, and a more systematic aircraft structural integrity monitoring system can be established to improve management efficiency. Therefore, the embodiments of the present invention provide an efficient, accurate and traceable aircraft structural integrity monitoring method, which can effectively improve the monitoring level of aircraft structural integrity and ensure the safe operation of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the technical solution of the present invention, the drawings used in the implementation mode will be briefly introduced below. Obviously, the drawings described below are only some implementation modes of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0033] Figure 1 is a flow chart of a method for monitoring aircraft structure integrity provided by an embodiment of the present invention;

[0034] Figure 2 is a structural block diagram of an aircraft structural integrity monitoring system provided by an embodiment of the present invention;

[0035] Figure 3 It is a structural block diagram of a terminal device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0036] 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 only 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.

[0037] See also Figure 1 , Figure 1 : is a flow chart of a method for monitoring aircraft structure integrity provided by an embodiment of the present invention, wherein the method for monitoring aircraft structure integrity comprises steps S1 to S4:

[0038] S1. Collect identification information of aircraft structure maintenance / modification;

[0039] It is understandable that a database may be pre-built to store key data of aircraft structure maintenance / modification, wherein the key data includes basic information and identification information of aircraft structure maintenance / modification. When maintenance / modification occurs to the aircraft structure, the front-line operators may be required to fill in the maintenance / modification records into pre-set tables or fields according to the requirements and store them in the pre-built database.

[0040] Specifically, the identification information includes at least one of an important structure identification, a fatigue critical structure identification and a structure modification identification.

[0041] It should be noted that the identification information includes but is not limited to: important structure identification, such as PSE (Principal Structural Elements) identification; fatigue critical structure identification, such as STR (Structure) identification, FCS (Fatigue Critical Structure) identification; structural modification identification, such as STR MOD (Structural Modification) identification, etc.

[0042] Among them, FCS refers to the fatigue critical structure that may have fatigue cracks and cause aviation disasters; PSE refers to the important structural elements that make important contributions to carrying flight, ground parking and pressurization loads, and the failure of these important structural elements can also cause aviation disasters.

[0043] In specific implementation, basic information and identification information of aircraft structure maintenance / modification can be collected through the database, and the structural maintenance / modification information in the database can be periodically analyzed to provide a data basis for subsequent inspections of the integrity of the aircraft structure.

[0044] S2. Identify the identification information according to preset conditions to obtain an identification result;

[0045] Specifically, the identifying information is identified according to a preset condition to obtain an identification result, including:

[0046] When it is identified that the identification information includes at least one of an important structure identification, a fatigue critical structure identification, and a structure modification identification, obtaining an identification result;

[0047] The recognition result includes key data for aircraft structure maintenance / modification corresponding to the identification information that needs to be evaluated.

[0048] Exemplarily, conditional judgment is performed on the identification information of the repair / modification newly entered into the database. If the identification information is an STR identification, an FCS identification or a PSE identification, or an STR MOD identification, the recognition result is that the key data of the repair / modification needs to be evaluated and reviewed.

[0049] S3, sending an aircraft structural integrity assessment task according to the identification result; wherein the assessment task is used to instruct to perform an aircraft structural integrity assessment and obtain an assessment result;

[0050] In a preferred embodiment, the aircraft structural integrity assessment task includes a textual assessment task and a factual assessment task;

[0051] Wherein, the document evaluation task is to check the correctness of the aircraft structure maintenance / modification according to the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the designated document;

[0052] The documented factual assessment task is to conduct on-site verification of the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the on-site conditions of the aircraft.

[0053] It should be noted that a documented assessment refers to looking at the modification or repair process from the maintenance records, including the correctness of the document steps, the correctness of the signatures, the legality and correctness of the aviation materials used, and whether they comply with the manual and airworthiness requirements. A factual assessment refers to an on-site assessment of specific repairs and modifications (such as enhanced repairs involving PSE and FCS), including whether the current status of the repairs is good, whether the arrangement of fasteners is correct, etc., and in the process of documented assessment, some repairs and modifications that are questionable and do not meet the requirements also require on-site verification. Among them, aircraft structural repairs / modifications saved in the database require documented assessments, and only repairs and modifications that meet the requirements require factual assessments.

[0054] Exemplarily, a written assessment task is issued, and eligible aircraft structure maintenance / modifications in the database are pushed to the corresponding assessment base. After receiving the assessment task, the engineers at the written assessment base conduct a written assessment on each aircraft structure maintenance / modification record in the database. Then, based on the judgment of "whether a written assessment is required" and "whether an on-site verification is required in the written assessment", the written assessment task is sent to conduct an on-site inspection of the structural integrity of the aircraft.

[0055] For example, the document assessment can verify the compliance of the structural repair / modification of the aircraft according to the following principles:

[0056] a. Confirm whether DTI (damage tolerance inspection requirement) is required;

[0057] b. Confirm the legality of the modification plan and its correct basis and source;

[0058] c. Check the consistency between the work sheet and the reference document. If there is any deviation in the modification, the approval of the manufacturer and the authority shall be obtained;

[0059] d. Whether the modification record is signed completely without missing items, and whether the work logic relationship between the signature and NA (not applicable) items is correct;

[0060] e. If there is test data, the actual measured data should be filled in;

[0061] f. For modifications that require subsequent inspection, there should be instructions for the subsequent inspection and control methods;

[0062] g. For replaceable structural components that need to be disassembled and replaced, the components must be traced back to the factory and the disassembly and assembly records of the components must be explained.

[0063] For example, the documented assessment verifies the compliance of the aircraft structural repair / modification according to the following principles:

[0064] a. Compare the actual repair position with the drawing to see if it is consistent;

[0065] b. Check the area around the modification to see if there are other repairs or modifications that may interfere with this modification;

[0066] c. Measure the radius of the damage removal corner and the radius of the repair patch corner to confirm that the solutions are consistent;

[0067] d. Check and confirm the outline size and thickness of the patch to confirm whether it is consistent with the plan;

[0068] e. Visually inspect the fastener type, installation condition, and nail arrangement condition to confirm that they are consistent with the plan drawings or manuals (fastener length and nail arrangement margin / spacing should be measured and confirmed);

[0069] f. If any suspicious signs of damage are found, further approach should be made, or NDT (non-destructive testing) should be performed to confirm the structural condition: if any abnormalities are found, non-routine cards should be activated to make corrections.

[0070] S4. Generate an aircraft structural integrity analysis report based on the evaluation results.

[0071] Exemplarily, when a plan for aircraft structural maintenance / modification is written, engineers determine the identification information of the structural maintenance / modification. When the plan is executed, that is, after the aircraft structure is repaired / modified, the corresponding maintenance / modification of the aircraft is identified, and the filled-in structured data is stored in a database. When production needs to inspect and evaluate the aircraft structural integrity, an evaluation task is issued, and finally an aircraft structural integrity analysis report is generated based on the evaluation results.

[0072] In a preferred embodiment, after identifying the identification information according to the preset conditions and obtaining the identification result, the method further includes:

[0073] According to the recognition result, identification information of aircraft structure maintenance / modification that meets preset conditions is stored in a pre-built database.

[0074] The collection of identification information of aircraft structure maintenance / modification includes:

[0075] The identification information of the aircraft structure maintenance / modification is collected from the pre-built database according to the preset time.

[0076] It should be noted that, in addition to identifying the identification information of the aircraft structure maintenance / modification newly entered for the first time, the identification information that has been saved in the database will be analyzed regularly, and the identification information will also be identified according to preset conditions to obtain an identification result; an aircraft structure integrity assessment task will be sent according to the identification result; wherein the assessment task is used to instruct the user to perform an aircraft structure integrity assessment and obtain an assessment result; and an aircraft structure integrity analysis report will be generated based on the assessment result.

[0077] For example, for aircraft structural maintenance / modification of different aircraft models or numbers, the preset time may be different and can be set based on engineering assessment experience. Generally, the aircraft structural maintenance / modification of general aircraft models or numbers can be set to 7 years, and the aircraft structural maintenance / modification of special aircraft models or numbers can be manually modified according to actual conditions.

[0078] In summary, an aircraft structural integrity monitoring method provided by an embodiment of the present invention includes collecting identification information of aircraft structural maintenance / modification, identifying the identification information according to preset conditions, obtaining identification results, and sending an aircraft structural integrity assessment task according to the identification results; wherein the assessment task is used to instruct the user to conduct an aircraft structural integrity assessment, obtain an assessment result, and generate an aircraft structural integrity analysis report based on the assessment result. The embodiment of the present invention identifies the identification information by preset conditions, and can automatically screen out the items that need to be evaluated, reduce the workload of manual screening, and improve efficiency; automatically generate an assessment task according to the identification result, which can save time for manually writing assessment tasks and improve assessment efficiency; identify and evaluate by preset conditions, which can ensure the standardization of the assessment process and reduce human errors; through data analysis, the integrity of the aircraft structure can be more effectively monitored, and potential safety hazards can be discovered in time. In addition, by collecting and analyzing the maintenance / modification identification information, a large amount of structural integrity data can be accumulated to provide data support for subsequent structural integrity management, and a more systematic aircraft structural integrity monitoring system can be established to improve management efficiency. Therefore, an embodiment of the present invention provides an efficient, accurate, and traceable aircraft structural integrity monitoring method, which can effectively improve the monitoring level of aircraft structural integrity and ensure the safe operation of aircraft.

[0079] On the basis of the above-mentioned method items, the present invention provides corresponding embodiments of the system items.

[0080] See also Figure 2 , Figure 2 1 is a structural block diagram of an aircraft structural integrity monitoring system provided by an embodiment of the present invention. The aircraft structural integrity monitoring system comprises:

[0081] The identification information acquisition module 21 is used to obtain identification information of aircraft structure maintenance / modification from a pre-built database according to a preset time;

[0082] The identification recognition module 22 is used to recognize the identification information according to preset conditions and obtain a recognition result;

[0083] An assessment task issuing module 23 is used to send an aircraft structural integrity assessment task according to the identification result; wherein the assessment task is used to instruct a user to perform an aircraft structural integrity assessment and obtain an assessment result;

[0084] The analysis report generating module 24 is used to generate an aircraft structural integrity analysis report based on the evaluation results.

[0085] In an optional embodiment, the system further includes an identification information storage module, which is used to:

[0086] According to the recognition result, identification information of aircraft structure maintenance / modification that meets preset conditions is stored in a pre-built database.

[0087] In an optional embodiment, the identification information collection module 21 is further used to:

[0088] The identification information of the aircraft structure maintenance / modification is collected from the pre-built database according to the preset time.

[0089] Specifically, the identification information includes at least one of an important structure identification, a fatigue critical structure identification and a structure modification identification.

[0090] In an optional embodiment, the identification recognition module 22 is further used to:

[0091] When it is identified that the identification information includes at least one of an important structure identification, a fatigue critical structure identification, and a structure modification identification, obtaining an identification result;

[0092] The recognition result includes key data for aircraft structure maintenance / modification corresponding to the identification information that needs to be evaluated.

[0093] Specifically, the aircraft structural integrity assessment task includes a textual assessment task and a factual assessment task;

[0094] Wherein, the document evaluation task is to check the correctness of the aircraft structure maintenance / modification according to the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the designated document;

[0095] The documented factual assessment task is to conduct on-site verification of the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the on-site conditions of the aircraft.

[0096] It should be noted that an aircraft structural integrity monitoring system provided in an embodiment of the present invention is used to execute all process steps of an aircraft structural integrity monitoring system method in the above embodiment, and the working principles and beneficial effects of the two correspond one to one, so they will not be repeated here.

[0097] The embodiment of the present invention also provides a terminal device, such as Figure 3 , which is a structural block diagram of a preferred embodiment of a terminal device provided by the present invention. The terminal device includes a processor 31, a memory 32, and a computer program stored in the memory 32 and configured to be executed by the processor 31. When the processor 31 executes the computer program, the aircraft structural integrity monitoring method described in any of the above embodiments is implemented.

[0098] In addition, an embodiment of the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute the aircraft structural integrity monitoring method as described in any of the above embodiments.

[0099] When the processor 31 executes the computer program, the steps in the above-mentioned aircraft structural integrity monitoring method embodiment are implemented, for example: Figure 1 Alternatively, when the processor 31 executes the computer program, the functions of each module in the above-mentioned aircraft structure integrity monitoring system embodiment are realized, for example Figure 3 The functions of each module of the aircraft structural integrity monitoring system are shown.

[0100] Preferably, the computer program can be divided into one or more modules / units, which are stored in the memory 32 and executed by the processor 31 to implement the present invention. The one or more modules / units can be a series of computer program instruction segments that can implement specific functions, and the instruction segments are used to describe the execution process of the computer program in the terminal device.

[0101] The processor 31 can be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor can be a microprocessor, or the processor 31 can be any conventional processor. The processor 31 is the control center of the terminal device, and various parts of the terminal device are connected using various interfaces and lines.

[0102] The memory 32 mainly includes a program storage area and a data storage area, wherein the program storage area can store an operating system, an application required for at least one function, etc., and the data storage area can store related data, etc. In addition, the memory 32 can be a high-speed random access memory, or a non-volatile memory, such as a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, and a flash card (Flash Card), etc., or the memory 32 can also be other volatile solid-state storage devices.

[0103] It should be noted that the above terminal device may include, but is not limited to, a processor and a memory. Those skilled in the art will understand that Figure 3 The structural block diagram shown is only a structural example of the above-mentioned terminal device and does not constitute a structural limitation of the above-mentioned terminal device. The above-mentioned terminal device may include more or fewer components than shown in the figure, or combine certain components, or different components.

[0104] The above is a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements and modifications without departing from the principle of the present invention. These improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A method for monitoring aircraft structural integrity, characterized in that: include: Collect identification information of aircraft structural maintenance / modification; Identify the identification information according to preset conditions to obtain an identification result; Sending an aircraft structural integrity assessment task according to the identification result; wherein the assessment task is used to instruct a user to perform an aircraft structural integrity assessment and obtain an assessment result; An aircraft structural integrity analysis report is generated based on the evaluation results.

2. The aircraft structural integrity monitoring method according to claim 1, characterized in that: After identifying the identification information according to the preset conditions and obtaining the identification result, the method further includes: According to the recognition result, identification information of aircraft structure maintenance / modification that meets preset conditions is stored in a pre-built database.

3. The aircraft structural integrity monitoring method according to claim 2, characterized in that: The collection of identification information of aircraft structure maintenance / modification includes: The identification information of the aircraft structure maintenance / modification is collected from the pre-built database according to the preset time.

4. The aircraft structural integrity monitoring method according to any one of claims 1 to 3, characterized in that: The identification information includes at least one of an important structure identification, a fatigue critical structure identification and a structure modification identification.

5. The aircraft structural integrity monitoring method according to claim 4, characterized in that: The identifying information is identified according to the preset conditions to obtain an identification result, including: When it is identified that the identification information includes at least one of an important structure identification, a fatigue critical structure identification, and a structure modification identification, obtaining an identification result; The recognition result includes key data for aircraft structure maintenance / modification corresponding to the identification information that needs to be evaluated.

6. The aircraft structural integrity monitoring method according to claim 5, characterized in that: The aircraft structural integrity assessment task includes a textual assessment task and a factual assessment task; Wherein, the document evaluation task is to check the correctness of the aircraft structure maintenance / modification according to the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the designated document; The documented factual assessment task is to conduct on-site verification of the key data of the aircraft structure maintenance / modification corresponding to the identification information according to the on-site conditions of the aircraft.

7. An aircraft structural integrity monitoring system, characterized in that: include: An identification information acquisition module is used to obtain identification information of aircraft structure maintenance / modification from a pre-built database according to a preset time; An identification recognition module, used to recognize the identification information according to preset conditions and obtain a recognition result; An assessment task issuing module, used to send an aircraft structural integrity assessment task according to the identification result; wherein the assessment task is used to instruct a user to perform an aircraft structural integrity assessment and obtain an assessment result; The analysis report generating module is used to generate an aircraft structural integrity analysis report based on the evaluation result.

8. The aircraft structural integrity monitoring system according to claim 7, characterized in that: The system also includes an identification information storage module, which is used to: According to the recognition result, identification information of aircraft structure maintenance / modification that meets preset conditions is stored in a pre-built database.

9. A terminal device, characterized in that: The invention comprises a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein when the processor executes the computer program, the aircraft structure integrity monitoring method according to any one of claims 1 to 6 is implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium includes a stored computer program, wherein when the computer program is executed, the device where the computer-readable storage medium is located is controlled to execute the aircraft structural integrity monitoring method according to any one of claims 1 to 6.

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