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CN-122020852-A - System and method for aircraft structural repair scheme design

CN122020852ACN 122020852 ACN122020852 ACN 122020852ACN-122020852-A

Abstract

The present invention relates to a system and method for aircraft structural repair scheme design. In the technical scheme of the invention, the damage of the aircraft structure can be automatically identified to determine damage information, including geometric parameters, positions and types of the damage. Based on the damage information, a repair plan is generated with reference to the digitally processed structure repair manual and structure repair rule base, and projected onto the skin surface.

Inventors

  • WEI JIAWEI
  • Cui Zifan
  • SHI ZHIJUN

Assignees

  • 中国商用飞机有限责任公司
  • 中国商用飞机有限责任公司上海飞机设计研究院

Dates

Publication Date
20260512
Application Date
20260128

Claims (15)

  1. 1. A system for aircraft structural repair scheme design, the system comprising: A lesion recognition module configured to automatically recognize a structural lesion to determine lesion information including geometric parameters, location, and type of the structural lesion; A repair expert module configured to: performing a digitizing process on the structure repair manual SRM; constructing a repair rule base based on the digitally processed SRM; generating a repair scheme using the repair rule base according to the damage information; a dynamic projection module configured to: generating a repair plan digital map according to the repair plan; projecting the repair plan digitized map onto a skin surface at the location of the structural damage.
  2. 2. The system of claim 1, wherein the geometric parameters of the structural damage include a maximum length, a pit depth, and a depth-to-length ratio, the damage identification module being further configured to determine the type from the geometric parameters and to determine the location of the structural damage by: Measuring the relative positions of the structural damage and a plurality of aircraft feature points; establishing a coordinate system taking the aircraft as a reference according to the relative position; And determining the station information of the structural damage in the coordinate system.
  3. 3. The system of claim 1, wherein the repair expert module is further configured to perform the digitizing by: performing vectorization processing on the schematic diagram in the SRM, wherein the vectorization processing comprises the steps of disassembling graphic elements in the schematic diagram into basic geometric units; Assigning a unique identifier to each basic geometric unit and recording the size, the position and the connection relation of the unique identifier; the parameter specifications in the SRM, including material performance parameters, process parameters, dimensional tolerances, are stored in the form of structured data.
  4. 4. The system of claim 1, wherein the repair expert module is further configured to construct the repair rules library by: classifying rule terms in the digitally processed SRM according to standardized concepts including repair objects, damage types, and repair processes and establishing a hierarchical structure; determining association relationships and dependency relationships between rule terms based on the classification and the hierarchy to form a structured rule network; semantic analysis of the rule terms using natural language processing techniques; Converting the structured rule network into the machine-understandable repair rule base according to the semantic analysis.
  5. 5. The system of claim 1, wherein the repair plan further comprises fastener arrangement optimization, wherein: the damage identification module is further configured to automatically identify potential interferents within a predetermined range outside an edge of the structural damage, and The repair expert module is further configured to set a minimum spacing of fasteners from the potential interfering object within the predetermined range, the minimum spacing being greater than a minimum spacing required in the SRM.
  6. 6. The system of claim 1, wherein the repair plan digitized map includes a repair area, aperture coordinates, fastener locations, and repair parameters, and the dynamic projection module is further configured to perform the projection onto the skin surface by: generating a theoretical projection path based on the computer-aided three-dimensional interactive application CATIA model; the theoretical projection path is adapted to the skin surface by compensating for projection distortions due to surface deformations of the skin surface using an interpolation algorithm to obtain an actual projection path.
  7. 7. The system of claim 1, wherein the repair expert module is further configured to digitize the hyper-manual repair scheme and build the repair rules library based on the digitized SRM and hyper-manual repair scheme, and wherein the repair expert module is further configured to: comparing and judging the damage information with the allowable damage limiting standard in the SRM; Generating a base repair plan and giving clearance requirements in the event that the structural damage does not exceed the allowable damage limit criteria; Retrieving and matching in the digitally processed SRM based on the damage information if the structural damage exceeds the allowable damage limit criteria; Extracting the repair plan from the SRM if the matching is successful; And in case of unsuccessful matching, generating the repair scheme according to the damage information by using the repair rule base.
  8. 8. A method for aircraft structural repair scheme design, the method comprising: Automatically identifying structural damage to determine damage information including geometric parameters, location and type of the structural damage; performing a digitizing process on the structure repair manual SRM; constructing a repair rule base based on the digitally processed SRM; generating a repair scheme using the repair rule base according to the damage information; Generating a repair plan digitized map from the repair plan, and Projecting the repair plan digitized map onto a skin surface at the location of the structural damage.
  9. 9. The method of claim 8, wherein the geometric parameters of the structural damage include a maximum length, a pit depth, and a depth-to-length ratio, the type being determined from the geometric parameters, determining the location of the structural damage further comprising: Measuring the relative positions of the structural damage and a plurality of aircraft feature points; establishing a coordinate system taking the aircraft as a reference according to the relative position; And determining the station information of the structural damage in the coordinate system.
  10. 10. The method of claim 8, wherein the digitizing process further comprises: performing vectorization processing on the schematic diagram in the SRM, wherein the vectorization processing comprises the steps of disassembling graphic elements in the schematic diagram into basic geometric units; Assigning a unique identifier to each basic geometric unit and recording the size, the position and the connection relation of the unique identifier; the parameter specifications in the SRM, including material performance parameters, process parameters, dimensional tolerances, are stored in the form of structured data.
  11. 11. The method of claim 8, wherein constructing the repair rules library further comprises: classifying rule terms in the digitally processed SRM according to standardized concepts including repair objects, damage types, and repair processes and establishing a hierarchical structure; determining association relationships and dependency relationships between rule terms based on the classification and the hierarchy to form a structured rule network; semantic analysis of the rule terms using natural language processing techniques; Converting the structured rule network into the machine-understandable repair rule base according to the semantic analysis.
  12. 12. The method of claim 8, wherein the repair plan further comprises a fastener arrangement optimization, wherein the method further comprises performing the fastener arrangement optimization by: automatically identifying potential interferents within a predetermined range outside the edge of the structural damage; setting a minimum spacing of fasteners from the potential interfering object within the predetermined range, the minimum spacing being greater than a minimum spacing required in the SRM.
  13. 13. The method of claim 8, wherein the repair plan digital map includes a repair area, aperture coordinates, fastener locations, and repair parameters, and projecting to the skin surface further comprises: generating a theoretical projection path based on the computer-aided three-dimensional interactive application CATIA model; the theoretical projection path is adapted to the skin surface by compensating for projection distortions due to surface deformations of the skin surface using an interpolation algorithm to obtain an actual projection path.
  14. 14. The method of claim 8, wherein constructing the repair rules library further comprises digitizing a hyper-manual repair scheme and constructing the repair rules library based on the digitized SRM and hyper-manual repair scheme, and wherein the method further comprises: comparing and judging the damage information with the allowable damage limiting standard in the SRM; Generating a base repair plan and giving clearance requirements in the event that the structural damage does not exceed the allowable damage limit criteria; Retrieving and matching in the digitally processed SRM based on the damage information if the structural damage exceeds the allowable damage limit criteria; Extracting the repair plan from the SRM if the matching is successful; And in case of unsuccessful matching, generating the repair scheme according to the damage information by using the repair rule base.
  15. 15. A computer-readable storage medium, wherein the computer-readable storage medium stores instructions that, the instructions, when executed, implement the method of any of claims 8-14.

Description

System and method for aircraft structural repair scheme design Technical Field The invention relates to the field of aviation maintenance, in particular to a system and a method for aircraft structural repair scheme design. Background In aircraft maintenance operations, maintenance personnel need to instruct to complete the design of a machine body structure repair scheme according to the latest version of a structure repair manual (Structural Repair Manual, SRM), currently, electronic manuals are generally queried through special software, and required contents are transmitted to mobile equipment or printed paper version belts to the site. However, in actual operation, the following problems often occur that 1) a typical repair scheme in a structure repair manual only gives a repair schematic diagram, such as standard layout of a single row of 3 rivets, in actual operation, the design is required to be purposefully designed according to the damage size, but no design auxiliary tool is provided at present to ensure that the manual meets the manual requirement, and the avoidance and the purposeful design of obstacles such as EWIS wire harnesses and the like close to the skin in a fuselage still depend on personnel experience, and a verification confirmation mechanism is lacking, 2) the traditional manual has low consulting efficiency, when operations such as cutting parameters and drilling coordinates are involved, a maintainer needs to interrupt operation for 3-5 times on average to repeatedly check, so that the maintenance period is prolonged, the risk of manual operation errors is increased, and 3) the whole maintenance process has not established a real-time data acquisition and recording mechanism, and the retrospective review of the maintenance process cannot be realized. These problems not only affect maintenance efficiency, but also bring hidden trouble to aircraft maintenance quality control and safety management. Accordingly, there is a need for a solution that further improves upon the prior art. Disclosure of Invention This summary is provided to introduce a selection of concepts in a simplified form that are further described below in the detailed description. This summary is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter. In response to the problems in the prior art, the present invention is directed to a system and method for aircraft structural repair scheme design. In the technical scheme of the invention, the system consists of the damage identification module, the maintenance expert module and the dynamic projection module, so that the functions of automatic identification of the damage of the aircraft structure, intelligent design of a customized repair scheme, projection auxiliary repair and the like are realized, the rationality and the accuracy of the repair scheme design and the maintenance operation process are improved, and the problems of frequent interruption caused by manual review, long time consumption of the repair scheme generated in the traditional mode, easiness in reworking, difficult traceability of the maintenance history and the like are reduced. In one embodiment of the invention, a system for aircraft structural repair scheme design is disclosed, the system comprising: a lesion recognition module configured to automatically recognize a structural lesion to determine lesion information including geometric parameters, location, and type of the structural lesion; A repair expert module configured to: performing a digitizing process on the structure repair manual SRM; constructing a repair rule base based on the digitally processed SRM; generating a repair plan using the repair rule base according to the damage information; a dynamic projection module configured to: Generating a repair plan digital map from the repair plan; the repair plan digitized map is projected onto the skin surface where the structural damage is located. In an alternative embodiment, the geometric parameters of the structural damage include a maximum length, a pit depth, and a depth-to-length ratio, and the damage identification module is further configured to determine the type based on the geometric parameters and to determine the location of the structural damage by: Measuring the relative positions of the structural damage and a plurality of aircraft feature points; Establishing a coordinate system taking the aircraft as a reference according to the relative position; and determining the station information of the structural damage in the coordinate system. In an alternative embodiment, the damage-recognition module is further configured to fully record audio and video data based on the repair operation of the repair plan and generate a digitized repair record. In an alternative embodiment, the repair expert module is further configured to perform the digitiz