Aircraft important structure project judgment and analysis organization method

Abstract

The invention belongs to the technical field of aviation maintenance engineering, and relates to a method for judging, analyzing and organizing important structure projects of an aircraft. According to the method, a double-layer screening mechanism of'direct inclusion of main structural units and five-dimensional quantitative judgment of non-main structural units' is established, and MSG-3 analysis verification is combined, so that the problems of high subjectivity, fuzzy standard and the like in traditional judgment are solved. Five-dimensional judgment indexes (flight load, ground / water surface load, pressure load, control load and structural integrity influence) realize objective quantitative screening of non-main structural units, and MSG-3 analysis is further verified from the aspects of fault mode, influence and detection logic, so that the deviation rate of judgment results of important structural projects is reduced.

Description

Technical Field

[0001] This invention belongs to the field of aviation maintenance engineering technology and relates to a method for determining and analyzing important structural items of an aircraft. Background Technology

[0002] In the field of aircraft maintenance engineering, the identification and rational analysis of critical aircraft structural items are core aspects of ensuring the safe and reliable operation of aircraft. With the continuous development of aviation technology, aircraft structures are becoming increasingly complex, placing higher demands on the maintenance management of critical structural items. However, existing analysis techniques have the following shortcomings: From a judgment perspective, the assessment of critical structural items lacks a comprehensive, systematic, and clear guiding framework. Traditional assessment methods often rely on the personal experience and subjective judgment of maintenance personnel, leading to significant differences in judgment standards and conclusions among different individuals, resulting in substantial subjectivity and uncertainty in the assessment results.

[0003] From an organizational perspective, existing analytical processes lack scientific classification and integration strategies, resulting in cumbersome and complex workflows that significantly increase the number of tasks. This not only reduces work efficiency and extends maintenance cycles but may also introduce more analytical errors due to the multiple steps involved in the complex processes, affecting the accuracy and effectiveness of maintenance decisions.

[0004] Therefore, there is an urgent need for a scientific, systematic, and efficient method for identifying and analyzing critical aircraft structural components in order to address the problems existing in current technologies. Summary of the Invention

[0005] Purpose of the invention This invention addresses the shortcomings of existing technologies by providing a standardized and verifiable method for identifying and analyzing critical aircraft structural items. This method aims to improve the accuracy and efficiency of aircraft structural maintenance, ensure the safety and reliability of aircraft operation, reduce maintenance costs, and enhance the economic benefits of maintenance management.

[0006] This method systematically identifies and classifies important aircraft structural items through scientific judgment criteria and efficient analysis and organization processes, so as to achieve precise and efficient management of aircraft structural maintenance, thereby ensuring the safety and reliability of aircraft operation, while meeting the economic requirements of modern aviation maintenance.

[0007] Technical solution This invention provides a method for determining critical structural items of an aircraft, comprising: S1: Determine the list of aircraft structural items based on the aircraft model design documents.

[0008] S2: Based on the aircraft structural project list obtained in S1, all structural components selected as primary structural units are considered as candidates for important structural projects. For non-primary structural units, a five-dimensional assessment is conducted based on whether they bear flight loads, ground / water loads, pressure loads, control loads, and whether they affect the structural integrity required for aircraft safety. Structural projects that meet any one or more of these dimensions are identified as candidates for important structural projects.

[0009] S3: Based on the list of candidate important structural projects determined in S2, and after analysis and verification by MSG-3, the initial important structural projects are determined.

[0010] Furthermore, the main structural units are specifically the parts of the aircraft structure that play a key role in the overall structural strength and stability.

[0011] Furthermore, the five dimensions for determining whether a non-major structural unit is a candidate for an important structural project are: flight load bearing capacity, ground / water surface load bearing capacity, pressure load bearing capacity, maneuvering load bearing capacity, and structural integrity impact. Flight load bearing dimension: Determine whether the structural components can bear the various loads generated during flight.

[0012] Ground / water surface load bearing dimension: Consider whether the structural components bear ground support force and water buoyancy load during ground / water surface take-off, landing and sliding.

[0013] Pressure load bearing dimension: assess whether the structural components can withstand the pressure load generated by the pressure difference between the internal and external pressure of the aircraft.

[0014] Control load bearing dimension: Analyze whether structural components participate in the force transmission of the aircraft control system and bear the control loads generated by the deflection of control surfaces.

[0015] Dimensions of impact on structural integrity: Determining whether the failure of structural components will affect the structural integrity required for aircraft safety.

[0016] Furthermore, the list of candidates for important structural projects is verified by MSG-3 analysis to ensure the accuracy and rationality of the candidates, and finally the list of important structural projects is determined.

[0017] In another aspect, the present invention also provides a method for analyzing and organizing critical structural items of an aircraft, comprising: S1: Determine the list of aircraft structural items based on the aircraft model design documents.

[0018] S2: Based on the aircraft structural project list obtained in S1, all structural components selected as primary structural units are considered as candidates for important structural projects. For non-primary structural units, a five-dimensional assessment is conducted based on whether they bear flight loads, ground / water loads, pressure loads, control loads, and whether they affect the structural integrity required for aircraft safety. Structural projects that meet any one or more of these dimensions are identified as candidates for important structural projects.

[0019] S3: Based on the list of candidate important structural projects determined in S2, and after analysis and verification by MSG-3, the initial important structural projects are determined.

[0020] S4: Based on the structural components included in the important structural projects identified in S3, classify them according to region, accessibility, standard numbering system, material properties, etc., and determine the classified structural components.

[0021] S5: Based on the list of structural components classified in S4, reclassify and merge them according to maintenance needs, the correlation between structural components, and the principle of optimal allocation of maintenance resources to determine the optimized important structural items.

[0022] Furthermore, for the structural components included in the initial major structural projects, the dimensions include: area dimension, accessibility dimension, and material property dimension: Regional dimension: Based on the structural layout of the aircraft, the structural components are divided into different regions, such as the fuselage region, wing region, and tail region.

[0023] Accessibility dimension: Assess the accessibility of structural components during maintenance, whether they are approached from the same point of contact, and comprehensively consider the layout of maintenance access panels in the system equipment, cables, and their respective areas.

[0024] Material properties dimension: Based on the material type and properties of structural components, they are divided into metallic materials and composite materials.

[0025] Technical effect This invention provides a standardized and verifiable method for identifying and analyzing critical aircraft structural items. Its core advantages lie in achieving standardized processes, quantified analysis, and refined decision-making. This method establishes a two-tiered screening mechanism: direct inclusion of major structural units + five-dimensional quantitative judgment of non-major structural units. Combined with MSG-3 analysis verification, it solves the problems of strong subjectivity and vague standards in traditional judgment methods. The five-dimensional judgment indicators (flight load, ground / water surface load, pressure load, control load, and structural integrity impact) enable objective quantitative screening of non-major structural units, while MSG-3 analysis further verifies from the perspectives of failure modes, impacts, and detection logic, reducing the deviation rate of the judgment results for critical structural items.

[0026] This method further optimizes the efficiency of analysis organization and resource allocation. Through "multi-dimensional classification + functional correlation merging," dispersed structural components are systematically categorized according to dimensions such as region, accessibility, and material properties. These are then integrated into SSIs based on maintenance needs and resource optimization principles, reducing repetitive analysis tasks and simplifying the analysis process. Simultaneously, grouping by accessibility and material properties facilitates precise matching of maintenance resources (such as tools and personnel), avoiding resource waste and ensuring maintenance economics.

[0027] This method, through clearly defined steps (judgment-classification-merging) and quantifiable indicators, forms a replicable standardized process applicable to the analysis of critical structural items in various aircraft (such as UAVs and eVTOLs). Furthermore, SSI's modular design provides a foundation for subsequent extended applications such as rating and regional adjustments, and can seamlessly integrate with other processes in the aviation maintenance system (such as fault prediction and maintenance planning), meeting the systematic and digital development needs of modern aviation maintenance and providing technical support for improving the level of life-cycle maintenance management. Attached Figure Description

[0028] Figure 1 This is an analytical flowchart of the method for determining important structural items of an aircraft according to the present invention.

[0029] Figure 2 This is a flowchart of the method for analyzing and organizing important structural items of an aircraft according to the present invention. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the invention.

[0032] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the stated directions or positional relationships and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0033] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0034] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to and in conjunction with the embodiments.

[0035] The method for identifying and analyzing critical aircraft structural items is as follows: Step 1: Based on the aircraft model design documents, compile a complete list of all structural components for the aircraft. Step 2: The aircraft structure consists of all load-bearing components, categorized into primary structural elements (PSEs) and non-primary structural elements. Primary structural elements (PSEs) are any components that play a crucial role in bearing flight loads, ground / water loads, pressurization loads, and control loads, and whose failure would have catastrophic consequences. Primary structural elements (PSEs) are directly considered candidates for important structural items and proceed to subsequent analysis steps. For non-primary structural elements, they are assessed based on five dimensions: whether they bear flight loads, ground / water loads, pressure loads, control loads, and whether they affect the structural integrity required for aircraft safety. A "yes" or "no" answer is given for each question. If any one question is answered "yes," the non-primary structural element is considered a candidate for an important structural item and the analysis continues; if all are answered "no," it is classified as another structural item and the following analysis steps are not performed. (Refer to Appendix) Figure 1 .

[0036] Step 3: Using the MSG-3 analysis method, further analyze the candidate critical structural items. Starting from the function of the structural item, analyze its role and working principle within the aircraft system; identify potential failure modes, such as cracking, deformation, and corrosion of structural components; assess the impact of failures on aircraft safety, performance, and operation; and study suitable failure detection methods, including non-destructive testing techniques and periodic inspection procedures. Through comprehensive and systematic analysis and verification, items that pass the review and meet the requirements are identified as initial critical structural items.

[0037] Step 4: Classify the initial important structural items according to factors such as region, accessibility, standard numbering system, and material properties. Refer to the appendix. Figure 2 .

[0038] Step 5: Based on the above classification results, and considering maintenance needs, functional relationships between structural components, and the actual situation of maintenance resources, the structural components are re-divided and merged. During the merging process, convenience and efficiency of maintenance are fully considered, and structural components with similar maintenance needs and functional relationships are grouped together. For example, metal structural components located in the same area with the same maintenance cycle and similar maintenance processes are merged into one SSI; for difficult-to-access composite structural components, structural components with similar functions and repair methods are integrated into an independent maintenance unit. Through multiple optimizations and adjustments, a complete and reasonable SSI is finally determined, forming a systematic organizational result for the analysis of critical aircraft structural items, providing strong support for subsequent maintenance management work.

[0039] Furthermore, the main structural units are usually the parts of the aircraft structure that play a key role in the overall structural strength and stability. These structures undertake important load transfer and support functions in the design and operation of the aircraft, so it is reasonable and necessary to regard them as candidates for important structural projects.

[0040] Furthermore, the five dimensions for determining whether a non-primary structural unit is a candidate for an important structural project are as follows: Flight load bearing capacity: This determines whether structural components can withstand various loads generated during flight, such as aerodynamic forces and inertial forces. These loads continuously act on the structural components during flight; if the components cannot effectively bear them, it may lead to aircraft structural damage and affect flight safety.

[0041] Ground / water surface load bearing dimension: This considers whether structural components bear loads such as ground support forces and water buoyancy during takeoff, landing, and taxiing on ground / water surfaces. These ground / water surface loads have a significant impact on the integrity and stability of the aircraft structure.

[0042] Pressure load bearing dimension: assess whether the structural components can withstand the pressure load generated by the pressure difference between the internal and external pressure of the aircraft. For example, the structural components of the fuselage pressurization compartment are subjected to internal pressurization pressure during flight. If the structural components of this part fail, it may cause serious accidents such as cabin depressurization.

[0043] Control load bearing dimension: This analyzes whether structural components participate in the force transmission of the aircraft control system and bear the control loads generated by the deflection of control surfaces. Control loads are directly related to the aircraft's handling performance and flight safety, making the load-bearing capacity of structural components crucial.

[0044] Dimensions of impact on structural integrity: Determining whether the failure of structural components will affect the structural integrity required for aircraft safety. Even if some structural components do not directly bear the aforementioned loads, their failure can still compromise the overall structural integrity of the aircraft, leading to a decline in aircraft structural performance and potentially causing safety accidents.

[0045] Furthermore, the list of candidates for important structural projects is verified by MSG-3 analysis to ensure the accuracy and rationality of the candidates, and finally the list of important structural projects is determined.

[0046] In another aspect, the present invention also provides a method for analyzing and organizing critical structural items of an aircraft, comprising: S4: Based on the structural components included in the important structural projects identified in S3, classify them according to region, accessibility, standard numbering system, material properties, etc., and determine the classified structural components.

[0047] S5: Based on the list of structural components classified in S4, reclassify and merge them according to maintenance needs, the correlation between structural components, and the principle of optimal allocation of maintenance resources to determine the optimized important structural items (SSI, Structural Significance Item).

[0048] Furthermore, the structural components included in the initial major structural projects are classified according to the following dimensions: Regional Dimension: Based on the aircraft's structural layout, structural components are divided into different regions, such as the fuselage region, wing region, and tail region. The structural components in different regions differ in function and maintenance requirements; regional division facilitates targeted management and maintenance operations for these components.

[0049] Accessibility Dimension: Assess the accessibility of structural components during maintenance, including whether they are approached from the same point (e.g., on the floor / under the floor), taking into account the layout of system equipment, cables, and maintenance access panels within their areas. Accessibility assessment helps in the rational allocation of maintenance resources and the development of maintenance plans. Standard Numbering System Dimension: Use ATA (Air Transport Association) sections as a key basis for SSI boundary delineation, numbering and classifying structural components. ATA standards provide a unified coding and classification system for the aviation maintenance field, facilitating information exchange and sharing between different maintenance units, and also benefiting the management and analysis of maintenance data.

[0050] Material properties dimension: Based on the material type and properties of structural components, they are classified into metallic materials, composite materials, etc. Structural components made of different materials differ in performance, maintenance methods, and service life. Classification by material properties allows for the development of corresponding maintenance strategies and quality control standards for different materials.

[0051] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A method for determining critical structural items of an aircraft, characterized in that, Include: S1: Determine the list of aircraft structural items based on the aircraft model design documents; S2: Based on the list of aircraft structural items obtained in S1, all structural components selected as major structural units are considered as candidates for important structural projects. For non-major structural units, they are judged from five dimensions: whether they bear flight loads, whether they bear ground / water loads, whether they bear pressure loads, whether they bear control loads, and whether they affect the structural integrity required for aircraft safety. Structural projects that meet any one or more of these dimensions are determined as candidates for important structural projects. S3: Based on the list of candidate important structural projects determined in S2, and after analysis and verification by MSG-3, the initial important structural projects are determined.

2. The method as described in claim 1, characterized in that, The main structural units are the parts of the aircraft structure that play a key role in the overall structural strength and stability.

3. The method as described in claim 1, characterized in that, The five dimensions for determining whether a non-major structural unit is a candidate for an important structural project are: flight load bearing capacity, ground / water surface load bearing capacity, pressure load bearing capacity, maneuver load bearing capacity, and impact on structural integrity. Flight load bearing dimension: Determine whether the structural components can bear the various loads generated during flight; Ground / water surface load bearing dimension: Consider whether the structural components bear ground support force and water buoyancy load during ground / water surface take-off, landing and sliding processes; Pressure load bearing dimension: assess whether the structural components can withstand the pressure load generated by the pressure difference between the internal and external pressure of the aircraft. Control load bearing dimension: Analyze whether structural components participate in the force transmission of the aircraft control system and bear the control loads generated by the deflection of control surfaces. Dimensions of impact on structural integrity: Determining whether the failure of structural components will affect the structural integrity required for aircraft safety.

4. The method as described in claim 1, characterized in that, The list of candidates for important structural projects was verified using MSG-3 analysis to ensure the accuracy and rationality of the candidates, and the final list of important structural projects was determined.

5. A method for analyzing and organizing critical structural items of an aircraft, characterized in that, Include: S1: Determine the list of aircraft structural items based on the aircraft model design documents; S2: Based on the list of aircraft structural items obtained in S1, all structural components selected as major structural units are considered as candidates for important structural projects. For non-major structural units, they are judged from five dimensions: whether they bear flight loads, whether they bear ground / water loads, whether they bear pressure loads, whether they bear control loads, and whether they affect the structural integrity required for aircraft safety. Structural projects that meet any one or more of these dimensions are determined as candidates for important structural projects. S3: Based on the list of candidate important structural projects determined in S2, the initial important structural projects are determined through MSG-3 analysis and verification. S4: Based on the structural components included in the important structural items identified in S3, classify them according to region, accessibility, standard numbering system, and material properties, and determine the classified structural components; S5: Based on the list of structural components classified in S4, reclassify and merge them according to maintenance needs, the correlation between structural components, and the principle of optimal allocation of maintenance resources to determine the optimized important structural items.

6. The method as described in claim 5, characterized in that, The structural components included in the initial important structural project include the dimensions of region, accessibility, and material properties.

7. The method as described in claim 6, characterized in that, Regional dimension: Based on the structural layout of the aircraft, the structural components are divided into different regions, such as the fuselage region, wing region, and tail region.

8. The method as described in claim 7, characterized in that, Accessibility dimension: Assess the accessibility of structural components during maintenance, whether they are approached from the same point of contact, and comprehensively consider the layout of maintenance access panels in the system equipment, cables, and their respective areas.

9. The method as described in claim 8, characterized in that, Material properties dimension: Based on the material type and properties of structural components, they are divided into metallic materials and composite materials.

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