Aircraft structure maintenance auxiliary system and method based on labview
The LabVIEW-based aircraft structural maintenance assistance system enables rapid visualization and location of aircraft damage and intelligent maintenance decision-making. It solves the problems of long maintenance time, high cost, and risk of misjudgment in traditional maintenance, improves maintenance efficiency and accuracy, and ensures aircraft safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-28
- Publication Date
- 2026-03-27
AI Technical Summary
Existing aircraft structural maintenance relies on traditional manual processes, resulting in high maintenance costs, long maintenance times, and susceptibility to subjective factors, posing risks of missed inspections and misjudgments, which affect flight safety.
An aircraft structural maintenance assistance system based on LabVIEW is adopted. The system receives damage information through an interactive module, performs intelligent evaluation through a decision-making module, and provides maintenance solutions through a generation module. It integrates an expert knowledge base and a rule engine to achieve rapid visual location and automated evaluation of damaged areas.
It significantly improves maintenance efficiency and accuracy, reduces unplanned downtime, minimizes human error, ensures maintenance quality and aircraft safety, and provides traceable electronic work order support.
Smart Images
Figure CN121745894A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of aircraft structural maintenance technology, and in particular to an aircraft structural maintenance auxiliary system and method based on LabVIEW. Background Technology
[0002] As aircraft and their systems and equipment become increasingly complex, maintenance and training costs have risen significantly. Maintenance plays a crucial role in maintaining the integrity and availability of aircraft. Therefore, aircraft maintenance has become a major concern for the industry.
[0003] Currently, aircraft structural maintenance primarily relies on traditional, manually-driven processes. This technical system centers on the individual experience of maintenance personnel, combined with paper or electronic technical manuals (such as the Structural Repair Manual, SRM), and uses visual inspection, manual measurement, and item-by-item comparison to complete damage assessment and maintenance decisions. While this approach has been used in the aviation maintenance industry for decades and possesses a certain degree of reliability, it is costly, and manual assessment is susceptible to subjective factors such as fatigue and lack of experience, potentially leading to missed inspections or misjudgments, thus posing a threat to flight safety. Summary of the Invention
[0004] This application provides a LabVIEW-based aircraft structural maintenance auxiliary system and method, which can improve the efficiency and accuracy of aircraft maintenance while reducing maintenance costs.
[0005] To achieve the above objectives, this application adopts the following technical solution: In a first aspect, this application provides a LabVIEW-based aircraft structure maintenance auxiliary system, the system comprising: The interaction module includes an interactive interface for receiving damage information of the aircraft input by the user and transmitting the damage information to the decision module. The damage information includes damage location, damage type and damage parameters. The decision module is used to, after receiving the damage information, match the target judgment rule corresponding to the damage location and the damage type from the pre-stored expert knowledge base according to the damage location and the damage type, input the damage parameters into the target judgment rule for evaluation and generate an evaluation result, and if the evaluation result indicates that repair is required, then transmit the damage information to the generation module; The generation module is used to match a corresponding repair plan from the expert knowledge base after receiving the damage information, and transmit the repair plan to the interactive interface.
[0006] As one possible implementation, the interaction module is also used for: Load a three-dimensional simulation model of the aircraft, the simulation model including the load-bearing structure inside the aircraft; The three-dimensional simulation model is divided into regions, and each region is assigned a corresponding identifier; The interaction module is specifically used to: receive the region location of the simulation model clicked by the user, and determine the damage location based on the identifier of the region location of the clicked simulation model.
[0007] As one possible implementation, the expert knowledge base includes: a standard database and a non-standard database; the system also includes a configuration module, which is used for: Obtain aircraft maintenance information by acquiring maintenance manuals, standards, material parameters, and historical maintenance records for different aircraft models. The aircraft maintenance information is encoded and stored according to multiple dimensions such as aircraft type, region, component type, and damage mode, including tolerance data, evaluation criteria, and maintenance plans, to obtain the standard database.
[0008] As one possible implementation, the configuration module is also used for: Obtain historical out-of-specification data from aircraft historical maintenance information; After cleaning and classifying the historical out-of-standard data, the non-standard data is obtained.
[0009] As one possible implementation, the decision module is specifically used for: Based on the damage location and the damage type, the target evaluation rules corresponding to the damage location and the damage type are matched from the pre-stored expert knowledge base. If the damage location or the damage type is not matched from the standard database, the target evaluation rules corresponding to the damage location and the damage type are matched from the non-standard database.
[0010] As one possible implementation, the decision module integrates a processing engine, and the decision module is further used for: Upon receiving the damage information, the processing engine is invoked to perform the evaluation process, which includes: matching the target judgment rule corresponding to the damage location and the damage type from a pre-stored expert knowledge base based on the damage location and the damage type, inputting the damage parameters into the target judgment rule for evaluation, and generating an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module.
[0011] As one possible implementation, the interactive interface is a graphical user interface developed using LabVIEW.
[0012] A second aspect of this application provides a LabVIEW-based aircraft structure maintenance method, applied to the LabVIEW-based aircraft structure maintenance auxiliary system described in the first aspect of this application. The method includes: The interaction module receives damage information of the aircraft input by the user and transmits the damage information to the decision module. The damage information includes damage location, damage type and damage parameters. After receiving the damage information, the decision-making module matches the target judgment rule corresponding to the damage location and the damage type from the pre-stored expert knowledge base, and inputs the damage parameters into the target judgment rule for evaluation to generate an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module. After receiving the damage information, the generation module matches the corresponding repair plan from the expert knowledge base and transmits the repair plan to the interactive interface.
[0013] As one possible implementation, the interaction module receives damage information about the aircraft input by the user, including: Load a three-dimensional simulation model of the aircraft, the simulation model including the load-bearing structure inside the aircraft; The three-dimensional simulation model is divided into regions, and each region is assigned a corresponding identifier; The system receives the region location of the simulation model clicked by the user, and determines the damage location based on the identifier of the region location of the clicked simulation model.
[0014] As one possible implementation, the expert knowledge base includes: a standard database and a non-standard database; the system also includes a configuration module, which is used for: Obtain aircraft maintenance information by acquiring maintenance manuals, standards, material parameters, and historical maintenance records for different aircraft models. The aircraft maintenance information is encoded and stored according to multiple dimensions such as aircraft type, region, component type, and damage mode, including tolerance data, evaluation criteria, and maintenance plans, to obtain the standard database.
[0015] A third aspect of this application provides an electronic device, including a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, it implements the LabVIEW-based aircraft structure maintenance method of the second aspect of this application.
[0016] In a fourth aspect of this application, a computer-readable storage medium is provided, on which a computer program is stored, wherein when the computer program is executed by a processor, it implements the LabVIEW-based aircraft structure maintenance method described in the second aspect of this application.
[0017] The beneficial effects of the technical solutions provided in this application include at least the following: This application provides a LabVIEW-based aircraft structural maintenance assistance system. The system includes: an interaction module with an interface for receiving user-inputted aircraft damage information and transmitting it to a decision module. The damage information includes damage location, damage type, and damage parameters. The decision module, upon receiving the damage information, matches target evaluation rules corresponding to the damage location and damage type from a pre-stored expert knowledge base. It then inputs the damage parameters into the target evaluation rules for evaluation and generates an evaluation result. If the evaluation result indicates that maintenance is required, the damage information is transmitted to a generation module. The generation module, upon receiving the damage information, matches a corresponding maintenance plan from the expert knowledge base and transmits the maintenance plan to the interaction interface. This maintenance assistance system enables rapid visual location and parameter input of damaged areas. The system can complete the assessment and judgment of whether maintenance is required within minutes, minimizing unplanned downtime caused by aircraft waiting for evaluation and significantly improving the continuity and economy of route operations.
[0018] Furthermore, regarding the accuracy and consistency of decision-making, traditional methods are limited by the technical level, experience differences, and subjective judgment of maintenance personnel, easily leading to misjudgments, omissions, or inconsistent standard implementation. This application, by procedurally embedding maintenance standards into the system, constructs a rule-engine-based decision-making module, completely eliminating interference from subjective human factors. This ensures that every damage assessment is strictly performed according to the latest manual standards, effectively avoiding secondary or over-maintenance due to human error, and improving maintenance quality and aircraft safety. In addition, this application achieves seamless integration of damage assessment, decision generation, and maintenance guidance, forming a complete closed-loop processing flow. All operational steps and judgment criteria are automatically recorded by the system, forming traceable electronic work orders. This not only greatly improves the efficiency and accuracy of maintenance work but also provides reliable data support for statistical analysis and management decisions based on maintenance data. Attached Figure Description
[0019] Figure 1 The structure of an aircraft structure maintenance auxiliary system based on LabVIEW provided in this application embodiment Figure 1 ; Figure 2The structure of an aircraft structure maintenance auxiliary system based on LabVIEW provided in this application embodiment Figure 2 ; Figure 3 A flowchart illustrating an aircraft structure maintenance auxiliary method based on LabVIEW, provided as an embodiment of this application; Figure 4 This is a schematic diagram of the internal structure of an electronic device provided in an embodiment of this application. Detailed Implementation
[0020] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.
[0021] Hereinafter, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of embodiments of this disclosure, unless otherwise stated, "a plurality of" means two or more.
[0022] In addition, the use of “based on” or “according to” implies openness and inclusivity, because processes, steps, calculations or other actions “based on” or “according to” one or more conditions or values can in practice be based on additional conditions or values beyond those conditions.
[0023] As aircraft and their systems and equipment become increasingly complex, maintenance and training costs have risen significantly. Maintenance plays a crucial role in maintaining the integrity and availability of aircraft. Therefore, aircraft maintenance has become a major concern for the industry.
[0024] Currently, aircraft structural maintenance primarily relies on traditional, manually-driven processes. This system centers on the personal experience of maintenance personnel, combined with paper or electronic technical manuals (such as the Structural Maintenance Manual, SRM), and uses visual inspection, manual measurement, and item-by-item comparison to complete damage assessments and maintenance decisions. While this approach has been used in the aviation maintenance industry for decades and possesses a degree of reliability, it suffers from several drawbacks: First, it is extremely time-consuming. Due to its complete reliance on manual manual review and item-by-item comparison, even a simple damage assessment can take several hours, severely impacting aircraft turnaround efficiency. As shown in the figure, the time consumption in traditional maintenance processes is significantly higher than that of automated systems, increasing the risk of flight delays and directly leading to operational losses. Second, monetary costs are difficult to control. This stems from both the direct economic losses caused by extended aircraft downtime and the potential for secondary repairs or unnecessary component replacements due to human error, further increasing maintenance expenses. Data in the figure shows that the overall cost of traditional methods far exceeds that of automated solutions. Third, the cost of errors remains high. Human assessments are susceptible to subjective factors such as fatigue and lack of experience, potentially leading to missed inspections or misjudgments, posing a threat to flight safety. The examples in the diagram clearly illustrate the serious consequences that human error can lead to. These shortcomings collectively expose the fundamental problem that existing technologies are ill-suited to the high-efficiency, high-precision demands of modern aircraft maintenance.
[0025] To address the aforementioned problems, embodiments of this application provide an aircraft structure maintenance auxiliary system based on LabVIEW, such as... Figure 1 As shown, the system includes: The interaction module includes an interactive interface for receiving damage information of the aircraft input by the user and transmitting the damage information to the decision module. The damage information includes damage location, damage type and damage parameters. The decision module is used to, after receiving the damage information, match the target judgment rule corresponding to the damage location and the damage type from the pre-stored expert knowledge base according to the damage location and the damage type, input the damage parameters into the target judgment rule for evaluation and generate an evaluation result, and if the evaluation result indicates that repair is required, then transmit the damage information to the generation module; The generation module is used to match a corresponding repair plan from the expert knowledge base after receiving the damage information, and transmit the repair plan to the interactive interface.
[0026] The location of damage refers to the specific physical part of the aircraft where the damage occurred. It is usually categorized according to the aircraft's structure and systems. This can include: fuselage, wings, tail, power plant, landing gear, systems, and components. Specifically, the fuselage can be divided into: skin, frame / struts, doors / canopies, and fuselage spars; the wings can be divided into: leading / trailing edges, wingtips, main wing box, and skin; the tail can be divided into: horizontal stabilizer, elevator, vertical stabilizer, and rudder; and the power plant can be divided into: engine nacelle, engine blades, engine core, and thrust reversers.
[0027] Damage type refers to the nature or mechanism of damage, that is, how the damage is caused and its manifestation. The main types include: cracks (metal fatigue, stress corrosion cracks); buckling / deformation (structural instability under pressure; corrosion: uniform corrosion, pitting, intergranular corrosion); delamination / delamination (interlaminar separation in composite materials); bird strikes (causing skin dents, radome ruptures, engine damage); hail (causing large-area dents in the skin); runway debris (damaging landing gear, tires, lower fuselage); collisions with ground equipment (collisions with jet bridges, refueling trucks, baggage carts, etc.); and lightning strikes (generating…). Ablation points, structural melting; electrostatic discharge: producing small ablation points); overheating / overcooling (leading to material performance degradation and seal failure); heavy rain / floods (leading to water ingress into equipment and electrical short circuits); wear (normal wear of moving parts); metal fatigue (cracks generated under alternating loads); aging (hardening and cracking of rubber parts, seals, and cable insulation over time); improper operation (hard landing, tail scraping during takeoff / landing); maintenance errors (tools falling and causing dents, improper tightening torque of fasteners); emergency landing / runway overrun (leading to landing gear collapse and fuselage scraping the ground).
[0028] Loss parameters are specific indicators used to quantify the degree of damage and are key bases for assessment, repair, and damage determination. Loss parameters can include: geometric parameters, material and performance parameters, and functional and condition parameters.
[0029] Among them, geometric dimensional parameters can be divided into: length / depth / width: such as crack length, pit depth; area / volume: such as corrosion area, delamination area; location coordinates: the distance of the damage from a reference line; quantity: such as the number of pits, the number of lightning strikes; fire: leading to loss of structural strength and material properties; explosion / shock wave damage.
[0030] Material and performance parameters can be categorized as follows: Material removal: the thickness of material lost after grinding and repair; Residual strength: the current load-bearing capacity of the damaged part; Hardness change: the change in hardness of the heat-affected area; Electrical conductivity / magnetic permeability change: used to assess damage from lightning strikes or overheating.
[0031] Functional and status parameters can be categorized as follows: System pressure / flow rate: pressure drop caused by leakage in the hydraulic system; Resistance / insulation resistance: electrical performance of circuits or components; Sealing: leakage rate of the tank or hatch; Clearance / tolerance: whether the clearance between moving parts is within tolerance.
[0032] For example, for a damage location on an aircraft wing and a damage type of lightning strike, the process of inputting the damage parameters into the target evaluation rules to generate an evaluation result can be as follows: sequentially verifying whether the damage diameter exceeds the allowable value, whether it penetrates the structural layer, and whether it is in a critical stress path to determine the evaluation result.
[0033] Optionally, the interaction module is further used for: Load a three-dimensional simulation model of the aircraft, the simulation model including the load-bearing structure inside the aircraft; The three-dimensional simulation model is divided into regions, and each region is assigned a corresponding identifier; The interaction module is specifically used to: receive the region location of the simulation model clicked by the user, and determine the damage location based on the identifier of the region location of the clicked simulation model.
[0034] In other words, when receiving the location of damage to an aircraft, the system can receive the damage location directly input by the user, or it can receive the identifier of the area clicked by the user on the 3D simulation model to determine the damage location.
[0035] Optionally, the interactive interface is a graphical user interface developed using LabVIEW.
[0036] Optionally, 3D simulation modeling software such as CATIA can be used to construct a high-precision 3D model of the entire aircraft, covering major structures such as the fuselage, wings, and tail, based on the aircraft's original design data. This model not only faithfully reproduces the aircraft's external aerodynamic shape but also shows in detail key load-bearing structures such as the internal skeleton, stringers, and bulkheads, allowing for the identification of damage locations based on the aircraft's 3D simulation model.
[0037] Referring to the division standards in aircraft structural maintenance manuals, we logically divided the 3D model into multiple independently manageable areas. For example, the fuselage was divided into grid-based partitions according to station positions, waterlines, and longitudinal lines, and each area was assigned a unique identifier. This step allows the abstract description of "damage location" (such as "STA905, upper S14R") to be precisely associated with specific 3D spatial coordinates in the model, greatly facilitating the intuitive understanding and location by maintenance personnel.
[0038] Optionally, the expert knowledge base includes: standard databases and non-standard databases; such as... Figure 2 As shown, the system also includes a configuration module, which is used for: Obtain aircraft maintenance information by acquiring maintenance manuals, standards, material parameters, and historical maintenance records for different aircraft models. The aircraft maintenance information is encoded and stored according to multiple dimensions such as aircraft type, region, component type, and damage mode, including tolerance data, evaluation criteria, and maintenance plans, to obtain the standard database.
[0039] The standard database is organized using a hierarchical architecture. It encodes and stores tolerance data, evaluation criteria, and maintenance plans based on multiple dimensions such as model, region, component type, and damage mode. This transforms the engineering logic hidden in the text into a data model that can be recognized and processed by computers, providing an accurate data foundation for subsequent automated assessments.
[0040] Optionally, the configuration module is further configured to: acquire historical out-of-standard data from aircraft historical maintenance information; clean the historical out-of-standard data and classify and store it accordingly to obtain the non-standard data.
[0041] Among them, non-standard data refers to historical maintenance data that does not conform to maintenance specifications. After cleaning and classifying these historical non-standard data, the non-standard data is obtained.
[0042] Optionally, the decision module is specifically used to: match the target evaluation rules corresponding to the damage location and the damage type from a pre-stored expert knowledge base based on the damage location and the damage type; if the damage location or the damage type is not matched from the standard database, then match the target evaluation rules corresponding to the damage location and the damage type from the non-standard database.
[0043] Optionally, the decision module integrates a processing engine, and the decision module is further used for: Upon receiving the damage information, the processing engine is invoked to perform the evaluation process, which includes: matching the target judgment rule corresponding to the damage location and the damage type from a pre-stored expert knowledge base based on the damage location and the damage type, inputting the damage parameters into the target judgment rule for evaluation, and generating an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module.
[0044] The aircraft structural maintenance system based on LabVIEW provided in this application relies on the programmatic embedding and system integration of the decision-making module as a core technological step in transforming traditional manual experience-based judgment into automated intelligent decision-making. This process begins with in-depth analysis and digital reconstruction of unstructured textual knowledge such as aircraft structural maintenance manuals, material standards, and maintenance procedures, forming a structured expert knowledge base. Based on this comprehensive expert knowledge base, the system achieves intelligent evaluation by embedding a rule-based engine-based decision algorithm. The core of this algorithm lies in transforming complex maintenance standards into a series of executable logical judgment rules.
[0045] After a user submits the location, type, and size parameters of the damage through the interactive interface, the system first precisely locates the damaged area and then automatically retrieves the corresponding set of evaluation rules from the knowledge base. The decision engine sequentially executes conditional judgments according to a preset logical chain. The entire reasoning process is fully procedural, ensuring the consistency and objectivity of the evaluation results. The decision module is highly integrated with other modules of the system, and after the evaluation conclusion is generated, the system automatically triggers subsequent processes.
[0046] For damage that does not require repair, a release report is generated and recorded for filing; for cases that require repair, specific repair plan guidelines are further linked from the knowledge base and pushed, such as the layup design of composite material reinforcement sheets, grinding process parameters, or fastener replacement standards.
[0047] This integrated system effectively achieves seamless integration of damage assessment, decision generation, and maintenance guidance, forming a complete closed-loop processing flow. All operational steps and judgment criteria are automatically recorded by the system, generating traceable electronic work orders. This not only greatly improves the efficiency and accuracy of maintenance work but also provides reliable data support for statistical analysis and management decisions based on maintenance data.
[0048] In addition, this application selects LabVIEW as the front-end development environment because its powerful engineering data acquisition, instrument control capabilities and efficient graphical programming features are very suitable for developing such industrial applications.
[0049] The system interface of this application is designed to be simple and intuitive, guiding users step by step through the operation. Initial Interface: After system startup, the main interface displays a panoramic view of the aircraft's 3D model and provides a main menu navigation. Users can choose to enter the "Damage Assessment" module. Through the interactive interface, users first click on the 3D model or select the approximate area of the damage via a drop-down menu. Then, they further select or enter a precise location code. Users select the damage type (such as lightning strike, dent) from a predefined list and fill in damage parameters in the input box, such as the measured damage size. After clicking the "Assess" button, the system's background program quickly invokes the decision-making logic and generates an assessment report within seconds. The results interface clearly displays the conclusion: "Repair Required," "Repair Not Required," or "Further Inspection Required." For repairable damage, the system will provide further detailed auxiliary repair guidance.
[0050] This application provides a LabVIEW-based aircraft structural maintenance system that addresses a series of technical bottlenecks in the current aircraft maintenance field, such as lengthy maintenance processes, high economic costs, and frequent human error. This application aims to systematically solve several core problems and promote the maintenance process towards intelligence, precision, and standardization. Specifically, this application focuses on solving the following technical problems: Firstly, regarding improving maintenance efficiency, traditional damage assessment typically relies on on-site inspections by engineers, manual recording, and repeated verification. This process often lasts for hours or even longer, resulting in significant operational losses due to prolonged aircraft downtime. This application introduces an automated assessment system. Engineers only need to input the dimensions of the aircraft structural damage and the type of damage into the system to determine whether the damage meets release criteria. This drastically reduces assessment time from hours to minutes, significantly decreasing aircraft non-operational time and improving the continuity of flight operations.
[0051] Secondly, regarding economic cost control, manual judgment is prone to misjudgment due to factors such as differences in experience, visual fatigue, or inconsistent standards, leading to problems such as secondary repairs, over-repairs, or under-repairs. This not only increases material and labor costs but may also pose potential risks to the structural integrity of the aircraft. This system, by establishing a standardized damage assessment logic and maintenance decision knowledge base, effectively avoids subjective bias, reduces unnecessary maintenance operations, thereby lowering overall maintenance costs and ensuring the economic efficiency and rationality of maintenance plans.
[0052] Regarding the accuracy of assessments, this invention focuses on promoting the standardization of maintenance processes to achieve repeatability and traceability. By incorporating damage identification, assessment, decision-making, and recording into a unified digital management platform, uncertainties caused by human subjectivity are eliminated, ensuring consistent and verifiable results for similar damage at different times and in different maintenance settings. This not only facilitates stable control of maintenance quality but also provides airlines, manufacturers, and regulatory agencies with comprehensive maintenance data support, meeting their high requirements for transparency and standardization in the maintenance process.
[0053] In summary, this application focuses on the key challenges in aircraft structural maintenance, especially in the context of the widespread application of new-generation aircraft such as the C919. It strives to solve core challenges such as rapid damage location and intelligent maintenance decision-making, with the aim of forming an efficient, economical, accurate and standardized maintenance solution, providing important support for the technological upgrading and model innovation of the civil aviation maintenance industry.
[0054] This application also provides a LabVIEW-based aircraft structure repair method, applied to the LabVIEW-based aircraft structure repair auxiliary system described in the first aspect of the embodiments of this application, such as... Figure 3 As shown, the method includes the following steps: Step 101: The interaction module receives the damage information of the aircraft input by the user and transmits the damage information to the decision module. The damage information includes the damage location, damage type and damage parameters. Step 102: After receiving the damage information, the decision module matches the target judgment rule corresponding to the damage location and the damage type from the pre-stored expert knowledge base according to the damage location and the damage type, and inputs the damage parameters into the target judgment rule for evaluation to generate an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module. Step 103: After receiving the damage information, the generation module matches the corresponding repair plan from the expert knowledge base and transmits the repair plan to the interactive interface.
[0055] In one embodiment, the interaction module receives damage information about the aircraft input by the user, including: Load a three-dimensional simulation model of the aircraft, the simulation model including the load-bearing structure inside the aircraft; The three-dimensional simulation model is divided into regions, and each region is assigned a corresponding identifier; The system receives the region location of the simulation model clicked by the user, and determines the damage location based on the identifier of the region location of the clicked simulation model.
[0056] In one embodiment, the expert knowledge base includes: a standard database and a non-standard database; the method further includes: Obtain aircraft maintenance information by acquiring maintenance manuals, standards, material parameters, and historical maintenance records for different aircraft models. The aircraft maintenance information is encoded and stored according to multiple dimensions such as aircraft type, region, component type, and damage mode, including tolerance data, evaluation criteria, and maintenance plans, to obtain the standard database.
[0057] In one embodiment, the method further includes: acquiring historical out-of-standard data from aircraft historical maintenance information; cleaning the historical out-of-standard data and classifying and storing it accordingly to obtain the non-standard data.
[0058] In one embodiment, after matching the target evaluation rules corresponding to the damage location and the damage type from a pre-stored expert knowledge base, the method further includes: Based on the damage location and the damage type, the target evaluation rules corresponding to the damage location and the damage type are matched from the pre-stored expert knowledge base. If the damage location or the damage type is not matched from the standard database, the target evaluation rules corresponding to the damage location and the damage type are matched from the non-standard database.
[0059] In one embodiment, the method further includes: Upon receiving the damage information, the processing engine is invoked to perform the evaluation process, which includes: matching the target judgment rule corresponding to the damage location and the damage type from a pre-stored expert knowledge base based on the damage location and the damage type, inputting the damage parameters into the target judgment rule for evaluation, and generating an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module.
[0060] In one embodiment, the interactive interface is a graphical user interface developed using LabVIEW.
[0061] Specific limitations regarding the LabVIEW-based aircraft structure maintenance assistance method can be found in the limitations of the LabVIEW-based aircraft structure maintenance assistance system described above, and will not be repeated here. Each module in the aforementioned LabVIEW-based aircraft structure maintenance assistance system can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor of the electronic device in hardware form, or stored in the memory of the electronic device in software form, so that the processor can call and execute the corresponding operations of each module.
[0062] The execution subject of the aircraft structure maintenance auxiliary method based on LabVIEW provided in this application embodiment can be an electronic device, which can be a processor, processing chip, computer equipment, terminal equipment, server or server cluster. This application embodiment does not specifically limit this.
[0063] Figure 4 This is a schematic diagram of the internal structure of an electronic device provided in an embodiment of this application. Figure 4 As shown, the electronic device includes a processor and a memory connected via a system bus. The processor provides computational and control capabilities. The memory may include a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system and computer programs. These computer programs can be executed by the processor to implement the steps of the LabVIEW-based aircraft structure maintenance assistance method provided in the various embodiments above. The internal memory provides a cached runtime environment for the operating system and computer programs in the non-volatile storage medium.
[0064] Those skilled in the art will understand that Figure 4 The diagram shown is an internal structure diagram of an electronic device, which is only a block diagram of a part of the structure related to the present application and does not constitute a limitation on the electronic device to which the present application is applied. A specific electronic device may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.
[0065] In another embodiment of this application, a computer-readable storage medium is also provided, on which a computer program is stored, wherein when the computer program is executed by a processor, the steps of the LabVIEW-based aircraft structure maintenance auxiliary method as described in the embodiments of this application are implemented.
[0066] In the above embodiments, implementation can be achieved, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented using software programs, implementation can be, in whole or in part, in the form of a computer program product. This computer program product includes one or more computer instructions. When these computer instructions are loaded and executed on a computer, all or part of the flow or function according to the embodiments of this application is generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, computer instructions can be transmitted from one website, computer, server, or data center to another via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) means. The computer-readable storage medium can be any available medium accessible to a computer or a data storage device containing one or more servers, data centers, etc., that can be integrated with the medium. The available media can be magnetic media (e.g., floppy disks, hard disks, magnetic tapes), optical media (e.g., DVDs), or semiconductor media (e.g., solid-state disks, SSDs).
[0067] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0068] The above embodiments merely illustrate several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.
Claims
1. A LabVIEW-based aircraft structural maintenance auxiliary system, characterized in that, The system includes: The interaction module includes an interactive interface for receiving damage information of the aircraft input by the user and transmitting the damage information to the decision module. The damage information includes damage location, damage type and damage parameters. The decision module is used to, after receiving the damage information, match the target judgment rule corresponding to the damage location and the damage type from the pre-stored expert knowledge base according to the damage location and the damage type, input the damage parameters into the target judgment rule for evaluation and generate an evaluation result, and if the evaluation result indicates that repair is required, then transmit the damage information to the generation module; The generation module is used to match a corresponding repair plan from the expert knowledge base after receiving the damage information, and transmit the repair plan to the interactive interface.
2. The system according to claim 1, characterized in that, The interaction module is also used for: Load a three-dimensional simulation model of the aircraft, the simulation model including the load-bearing structure inside the aircraft; The three-dimensional simulation model is divided into regions, and each region is assigned a corresponding identifier; The interaction module is specifically used to: receive the region location of the simulation model clicked by the user, and determine the damage location based on the identifier of the region location of the clicked simulation model.
3. The system according to claim 1, characterized in that, The expert knowledge base includes: a standard database and a non-standard database; the system also includes a configuration module, which is used for: Obtain aircraft maintenance information by acquiring maintenance manuals, standards, material parameters, and historical maintenance records for different aircraft models. The aircraft maintenance information is encoded and stored according to multiple dimensions such as aircraft type, region, component type, and damage mode, including tolerance data, evaluation criteria, and maintenance plans, to obtain the standard database.
4. The system according to claim 3, characterized in that, The configuration module is also used for: Obtain historical out-of-specification data from aircraft historical maintenance information; After cleaning and classifying the historical out-of-standard data, the non-standard data is obtained.
5. The system according to claim 4, characterized in that, The decision-making module is specifically used for: Based on the damage location and the damage type, the target evaluation rules corresponding to the damage location and the damage type are matched from the pre-stored expert knowledge base. If the damage location or the damage type is not matched from the standard database, the target evaluation rules corresponding to the damage location and the damage type are matched from the non-standard database.
6. The system according to claim 1, characterized in that, The decision module integrates a processing engine, and the decision module is also used for: Upon receiving the damage information, the processing engine is invoked to perform the evaluation process, which includes: matching the target judgment rule corresponding to the damage location and the damage type from a pre-stored expert knowledge base based on the damage location and the damage type, inputting the damage parameters into the target judgment rule for evaluation, and generating an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module.
7. The system according to claim 1, characterized in that, The interactive interface is a graphical user interface developed using LabVIEW.
8. A LabVIEW-based aircraft structure maintenance method, applied to the LabVIEW-based aircraft structure maintenance auxiliary system according to any one of claims 1-7, the method comprising: The interaction module receives damage information of the aircraft input by the user and transmits the damage information to the decision module. The damage information includes damage location, damage type and damage parameters. After receiving the damage information, the decision-making module matches the target judgment rule corresponding to the damage location and the damage type from the pre-stored expert knowledge base, and inputs the damage parameters into the target judgment rule for evaluation to generate an evaluation result. If the evaluation result indicates that repair is required, the damage information is transmitted to the generation module. After receiving the damage information, the generation module matches the corresponding repair plan from the expert knowledge base and transmits the repair plan to the interactive interface.
9. The method according to claim 8, characterized in that, The interaction module receives damage information about the aircraft input by the user, including: Load a three-dimensional simulation model of the aircraft, the simulation model including the load-bearing structure inside the aircraft; The three-dimensional simulation model is divided into regions, and each region is assigned a corresponding identifier; The system receives the region location of the simulation model clicked by the user, and determines the damage location based on the identifier of the region location of the clicked simulation model.
10. The method according to claim 8, characterized in that, The expert knowledge base includes: a standard database and a non-standard database; the system also includes a configuration module, which is used for: Obtain aircraft maintenance information by acquiring maintenance manuals, standards, material parameters, and historical maintenance records for different aircraft models. The aircraft maintenance information is encoded and stored according to multiple dimensions such as aircraft type, region, component type, and damage mode, including tolerance data, evaluation criteria, and maintenance plans, to obtain the standard database.