A method and system for aircraft rvsm airworthiness certification manufacturing compliance demonstration

Abstract

This application belongs to the field of aircraft design technology, and specifically relates to a method and system for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification. Based on a minimally independent list of manufacturing conformity inspection scopes, and combined with the manufacturing conformity inspection process, the resource and data dependencies within the inspection scopes are obtained. Then, the critical path method is used to determine at least two parallel inspection links, and a manufacturing conformity checklist is further generated. Manufacturing conformity inspections are performed on the four major functional systems, and structural inspections of the four major functional systems are conducted in conjunction with the manufacturing conformity checklist to obtain structural inspection data. The manufacturing conformity checklist and structural inspection data are compared and summarized to obtain a manufacturing conformity evidence package. This achieves independent, process-oriented, and standardized demonstration of RVSM manufacturing conformity, shortening the overall airworthiness review cycle, reducing the cost of repetitive inspections, and ensuring the integrity and rigor of aircraft RVSM airworthiness conformity determination.

Description

Technical Field

[0001] This application belongs to the field of aircraft design technology, and specifically relates to a method and system for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification. Background Technology

[0002] RVSM is an important standard promoted by the International Civil Aviation Organization (ICAO) to improve airspace utilization. By reducing the vertical separation between flight levels, air traffic efficiency can be significantly improved. When an aircraft operates in RVSM airspace, its altitude measurement system error must meet the requirements specified in Advisory Circular AC-21-13 (Airworthiness Approval of Aircraft Operating with a 300-meter (1000-foot) Vertical Separation Standard in RVSM Airspace).

[0003] Currently, the airworthiness certification of RVSMs for civil transport aircraft is carried out along with the airworthiness review and certification of the entire aircraft. How to conduct independent airworthiness certification and review of RVSM-related equipment and functional performance is a problem that urgently needs to be solved to meet the operational requirements of aircraft RVSMs. This invention, combining the requirements of aircraft RVSM airworthiness certification, constructs a method and system for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification, specifically addressing the production, manufacturing, certification, and flight testing verification of equipment and functional performance directly related to RVSMs. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a method and system for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification, thereby resolving the problem in the prior art of accurately determining the conformity of aircraft RVSM airworthiness certification.

[0005] The technical solution of this application is: a method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification, comprising:

[0006] Data from different levels within the four functional systems required for RVSM operation is collected, and mapping relationships between different levels are established. Based on these mapping relationships, key equipment, hardware, software, and critical areas of the machine body are screened to obtain a list of minimally independent manufacturing conformity inspection scopes. The four functional systems include a height measurement system, a height display and reporting system, a height alarm system, and a height holding system.

[0007] Error analysis and evaluation were conducted on the four major functional systems to obtain the error allocation evaluation results, determine the surface quality technical requirements of each RVSM key area, and construct the manufacturing conformity inspection process.

[0008] Based on the list of minimal independent manufacturing conformity inspection scopes, the resource dependencies and data dependencies within the inspection scopes are obtained in conjunction with the manufacturing conformity inspection process; then, at least two parallel inspection links are determined using the critical path method, and a manufacturing conformity inspection checklist is further generated.

[0009] Manufacturing conformity checks were performed on the four major functional systems. In conjunction with the manufacturing conformity checklist, structural, configuration, surface quality checks of critical areas of the RVSM, and functional checks of the hydrostatic system were conducted on the four major functional systems to obtain structural inspection data.

[0010] The manufacturing conformity checklist and structural inspection data are compared and summarized to obtain the manufacturing conformity evidence package.

[0011] Preferably, the mapping relationship between different levels includes a three-level mapping relationship of function-airborne equipment-physical area. Based on the mapping relationship of different levels, key equipment, hardware and software, and key areas of the airframe are screened. The specific design is as follows:

[0012] Taking the static pressure source error allocation of RVSM operation as the main line, the altitude error budget item is back-linked to the corresponding LRU equipment, software configuration item and fuselage skin area to form a two-way traceability matrix of function-airborne equipment-physical area;

[0013] The Boolean logic matrix is ​​used for correlation analysis, and the necessity score for the inspection is calculated using the following formula:

[0014] Necessity of inspection = aerodynamic impact weight × 0.4 + functional impact weight × 0.3 + safety level coefficient × 0.3;

[0015] When the necessity score for inspection is less than or equal to 0.7, the corresponding equipment, hardware, software, or body area will be included in the list of minimally independent manufacturing compliance inspection areas.

[0016] Preferably, a manufacturing conformity inspection process is established, specifically as follows:

[0017] Based on the RVSM height error allocation evaluation results, the 15cm area around the nose static pressure sensor and the ±5° pitch angle projected skin area are defined as the RVSM key control areas.

[0018] Obtain the surface quality technical requirements for the critical control areas of the RVSM, including: skin surface waviness, skin seam gap and step difference, step difference of the sensor mounting base relative to the surrounding skin, step difference of the sensor head relative to the mounting base, and rivet head protrusion / concavity in the critical area.

[0019] The manufacturing conformity inspection process is categorized into structural geometry inspection, airtightness testing, equipment installation verification, software and hardware version verification, and signal transmission verification to meet surface quality requirements.

[0020] Preferably, a manufacturing conformity checklist is further generated, specifically as follows:

[0021] Based on a minimal manufacturing conformity checklist, this study uses an enhanced comparison method that ensures document-to-fact consistency to identify the dependencies between various checks on personnel, tools, support resources, and input / output data.

[0022] The critical path method is used to organize the originally sequential configuration checks, critical area surface condition checks, and drag cone system function checks into at least two parallel check chains:

[0023] First link: RVSM functional system equipment configuration check, using the real-time configuration data management platform to compare and check with the actual installed software, and at the same time verify the history book or certificate of conformity to ensure that the actual installation status of the relevant software and hardware, history book / certificate of conformity are consistent with the approved configuration documents;

[0024] The second link: Inspection of the surface quality and drag cone installation structure of the key areas of the fuselage RVSM, using a laser tracker or digital scanning equipment to record the geometric state of the key areas;

[0025] After the two links are completed in parallel, they are merged into a unified data fusion node for cross-validation to obtain the cross-validation results;

[0026] Based on the cross-validation results, the inspection items, acceptance criteria, tools and equipment, personnel qualifications, support conditions, and on-site record items are broken down to form a manufacturing conformity checklist.

[0027] Preferably, before performing manufacturing conformity checks on the four major functional systems, the following steps are also included:

[0028] A digital comparison instruction set is generated based on the minimized manufacturing conformity checklist, the surface quality technical requirements of RVSM key areas, and the parallel inspection chain.

[0029] The digital comparison instruction set specifically includes:

[0030] 1) Automatically generate a list of equipment to be inspected and its corresponding airworthiness approval document number based on the minimum inspection scope;

[0031] 2) Generate an executable inspection task sequence based on surface quality technical requirements, including inspection point coordinates, allowable tolerances, measuring tool numbers, and measurement paths;

[0032] 3) Generate a triplet verification table of equipment part number, software version number, and hardware serial number based on the approved configuration for automatic on-site configuration comparison.

[0033] Preferably, the structural inspection of the four major functional systems is carried out in conjunction with the manufacturing conformity checklist, specifically as follows:

[0034] 1) Configuration consistency check: Scan the electronic tags of airborne equipment, automatically read the part number, serial number, and software version information, compare them with the approved configuration database in real time, and complete the verification of document-to-fact consistency and document-to-document consistency.

[0035] 2) Surface structure inspection of key areas: Surface quality inspection is carried out on the machine head skin, the area around the static pressure hole, and the sensor installation area to obtain structural data such as skin waviness, seam gap and step difference, mounting base step difference, sensor head step difference, and rivet protrusion and concavity.

[0036] 3) Inspection of the structure and function of the tow cone system: Conduct verification of the tow cone installation structure, airtightness test, retraction and remote control function test, and cable laying inspection to obtain structural installation and airtightness performance data;

[0037] The configuration inspection data, surface structure data, and drag cone system inspection data are summarized to form the structural inspection data of the four major functional systems.

[0038] Preferably, a text-fact consistency enhancement comparison method is used for configurational consistency checking, specifically:

[0039] By scanning the electronic tags of airborne equipment and airframe components, the device automatically obtains information such as part number, hardware serial number, and software version number.

[0040] The physical information read is compared with the approved configuration database in real time online. If there is a complete match, an electronic signature of "configuration approved" is automatically generated.

[0041] If discrepancies exist, the configuration management database is automatically connected to match historical change records. The discrepancies are classified into three levels according to their relevance to RVSM functions: permissible deviations, deviations requiring engineering evaluation, and unacceptable deviations. The corresponding deviation handling workflow is then triggered for each level.

[0042] Preferably, a visually guided automatic measurement and real-time judgment method is used to inspect the surface structure of key areas, specifically as follows:

[0043] Using an airworthiness-approved laser scanner or augmented reality equipment, the preset coordinates of the inspection points and the measurement path are projected onto the surface of the aircraft to guide the inspectors to accurately locate and measure.

[0044] The measuring instrument automatically transmits the collected surface geometric data to the mobile terminal, fills in the corresponding fields of the manufacturing conformity checklist in real time, and automatically compares and judges it with the preset surface quality technical standards.

[0045] After the measurement is completed, the mobile terminal automatically generates a surface quality inspection report for key areas, including skin waviness, seam gap and step difference, sensor mounting base step difference, sensor head and base step difference, and rivet head concavity and convexity, according to the preset template, forming structural inspection data.

[0046] Preferably, the structural and functional check of the towing cone system specifically includes:

[0047] Mechanical structure and installation accuracy checks were performed on the towing cone installation section, the retraction mechanism, and the installation base to verify the structural assembly conformity and obtain structural installation data.

[0048] Based on the static pressure transmission sealing RVSM height measurement requirements, the airtightness performance of the towing cone system pipeline and cabin was tested, and airtightness test data was obtained.

[0049] Execute remote control commands in the cockpit to complete the verification codes for the automatic towing cone retraction function, remote control function, and status feedback function, and obtain function verification data.

[0050] The continuity and laying of the cables and signal transmission paths related to the tow cone were checked to obtain signal stability data.

[0051] Structural installation data, airtightness test data, functional verification data, and signal stability data are compiled to form the structural inspection data of the tow cone system.

[0052] Another technical solution of this application is: an aircraft RVSM airworthiness certification manufacturing conformity indication system, comprising:

[0053] The scope list design module is used to collect data from different levels within the four major functional systems required for RVSM operation, establish mapping relationships between different levels, and screen key equipment, hardware and software and key areas of the machine body based on the mapping relationships between different levels to obtain a minimal independent manufacturing conformity inspection scope list.

[0054] The inspection process design module is used to perform error analysis and evaluation on the four major functional systems, obtain error allocation evaluation results, determine the surface quality technical requirements of each RVSM key area, and construct the manufacturing conformity inspection process.

[0055] The link inspection design module is used to obtain the resource dependencies and data dependencies in the inspection scope based on the minimum independent list of manufacturing conformity inspection scopes and the manufacturing conformity inspection process; then, it uses the critical path method to determine at least two inspection links that are executed in parallel, and further generates a manufacturing conformity inspection checklist.

[0056] The structural inspection design module is used to perform manufacturing conformity checks on the four major functional systems, and, in conjunction with the manufacturing conformity checklist, to perform structural, configuration, RVSM critical area surface quality checks, and hydrostatic system functional checks on the four major functional systems.

[0057] The evidence package acquisition module is used to compare and summarize the manufacturing conformity checklist and structural inspection data to obtain the manufacturing conformity evidence package.

[0058] The aircraft RVSM airworthiness certification manufacturing conformity demonstration method and system of this application have the following advantages:

[0059] By narrowing the inspection scope through hierarchical mapping, clarifying surface technical requirements through error assessment, achieving multi-link parallel inspection through the critical path method, and solidifying the results through structured on-site inspection and evidence packages, we can break away from the traditional serial inspection mode that relies on whole-aircraft certification. This enables the independent, process-oriented, and standardized demonstration of RVSM manufacturing compliance, thereby shortening the airworthiness review cycle, reducing the cost of repetitive inspections, and ensuring the integrity and rigor of aircraft RVSM airworthiness compliance determination.

[0060] Breaking away from the traditional RVSM airworthiness review model that must rely on whole-aircraft certification, this approach establishes a three-layer mapping and quantitative screening rule for functions, airborne equipment, and physical areas. This creates a quantifiable, traceable, and reusable minimum inspection scope, eliminating the arbitrariness of manually defined scopes. It avoids omissions and over- or redundant inspections, supporting applications in scenarios such as aircraft RVSM-specific independent airworthiness certification, modification certification, and component localization review. Attached Figure Description

[0061] Figure 1 This is a schematic diagram of the overall process of this application. Detailed Implementation

[0062] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0063] The first aspect of this application provides a method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification, such as... Figure 1 As shown, it includes the following steps:

[0064] Step S100: Collect data from different levels within the four functional systems required for RVSM operation, establish mapping relationships between different levels, and screen key equipment, hardware and software, and key areas of the machine body based on the mapping relationships between different levels to obtain a list of minimal independent manufacturing conformity inspection scopes.

[0065] The four main functional systems include a height measurement system, a height display and reporting system, a height alarm system, and a height holding system.

[0066] Preferably, the mapping relationship between different levels includes a three-level mapping relationship of function-airborne equipment-physical area. Based on the mapping relationship of different levels, key equipment, hardware and software, and key areas of the airframe are screened. The specific design is as follows:

[0067] Taking the static pressure source error allocation of RVSM operation as the main line, the altitude error budget item is back-linked to the corresponding LRU equipment, software configuration item and fuselage skin area to form a two-way traceability matrix of function-airborne equipment-physical area;

[0068] The Boolean logic matrix is ​​used for correlation analysis, and the necessity score for the inspection is calculated using the following formula:

[0069] Necessity of inspection = aerodynamic impact weight × 0.4 + functional impact weight × 0.3 + safety level coefficient × 0.3;

[0070] When the necessity score for inspection is less than or equal to 0.7, the corresponding equipment, hardware, software, or body area will be included in the list of minimally independent manufacturing compliance inspection areas.

[0071] It solves the problems of traditional RVSM inspection scope relying on manual experience, vague boundaries, and easy omissions or over-inspections; by quantifying the correlation degree with a fixed weight formula and setting an admission threshold, it achieves accurate screening of key equipment, software and hardware, and airframe areas, and two-way traceability, forming a minimized inspection scope, which greatly reduces the inspection workload while ensuring full coverage of airworthiness inspection.

[0072] Step S200: Perform error analysis and evaluation on the four major functional systems, obtain the error allocation evaluation results, determine the surface quality technical requirements of each RVSM key area, and construct the manufacturing conformity inspection process.

[0073] Preferably, a manufacturing conformity inspection process is established, specifically as follows:

[0074] Based on the RVSM height error allocation evaluation results, the 15cm area around the nose static pressure sensor and the ±5° pitch angle projected skin area are defined as the RVSM key control areas.

[0075] Obtain the surface quality technical requirements for the critical control areas of the RVSM, including: skin surface waviness, skin seam gap and step difference, step difference of the sensor mounting base relative to the surrounding skin, step difference of the sensor head relative to the mounting base, and rivet head protrusion / concavity in the critical area.

[0076] The manufacturing conformity inspection process is categorized into structural geometry inspection, airtightness testing, equipment installation verification, software and hardware version verification, and signal transmission verification to meet surface quality requirements.

[0077] The manufacturing and acceptance standards for core areas such as the nose cone skin and sensor periphery have been standardized to avoid problems such as inconsistent on-site inspection standards and omissions in key geometric parameters.

[0078] Step S300: Based on the list of minimized independent manufacturing compliance inspection scopes, the resource dependencies and data dependencies in the inspection scope are obtained in conjunction with the manufacturing compliance inspection process; then, at least two parallel inspection links are determined by the critical path method, and a manufacturing compliance inspection checklist is further generated.

[0079] Preferably, a manufacturing conformity checklist is further generated, specifically as follows:

[0080] Based on a minimal manufacturing conformity checklist, this study uses an enhanced comparison method that ensures document-to-fact consistency to identify the dependencies between various checks on personnel, tools, support resources, and input / output data.

[0081] The critical path method is used to organize the originally sequential configuration checks, critical area surface condition checks, and drag cone system function checks into at least two parallel check chains:

[0082] First link: RVSM functional system equipment configuration check, using the real-time configuration data management platform to compare and check with the actual installed software, and at the same time verify the history book or certificate of conformity to ensure that the actual installation status of the relevant software and hardware, history book / certificate of conformity are consistent with the approved configuration documents;

[0083] The second link: Inspection of the surface quality and drag cone installation structure of the key areas of the fuselage RVSM, using a laser tracker or digital scanning equipment to record the geometric state of the key areas;

[0084] After the two links are completed in parallel, they are merged into a unified data fusion node for cross-validation to obtain the cross-validation results;

[0085] Based on the cross-validation results, the inspection items, acceptance criteria, tools and equipment, personnel qualifications, support conditions, and on-site record items are broken down to form a manufacturing conformity checklist.

[0086] By identifying resource and data dependencies and reconstructing the inspection logic using the critical path method, the traditional serial inspection is transformed into a dual-link parallel operation, combined with offline, non-disassembly software comparison, laser digital scanning, and data cross-verification; the inspection period is significantly reduced, while configuration and surface quality are carried out simultaneously and results are cross-verified, improving inspection efficiency and data reliability.

[0087] Step S400: Perform manufacturing conformity checks on the four major functional systems, and combine the manufacturing conformity check sheet to perform structural, configuration, surface quality checks of critical areas of the RVSM and static pressure system of the four major functional systems, and obtain structural inspection data.

[0088] Before conducting manufacturing conformity checks on the four major functional systems, the following also applies:

[0089] A digital comparison instruction set is generated based on the minimized manufacturing conformity checklist, the surface quality technical requirements of RVSM key areas, and the parallel inspection chain.

[0090] The digital comparison instruction set specifically includes:

[0091] 1) Automatically generate a list of equipment to be inspected and its corresponding airworthiness approval document number based on the minimum inspection scope;

[0092] 2) Generate an executable inspection task sequence based on surface quality technical requirements, including inspection point coordinates, allowable tolerances, measuring tool numbers, and measurement paths;

[0093] 3) Generate a triplet verification table of equipment part number, software version number, and hardware serial number based on the approved configuration for automatic on-site configuration comparison.

[0094] A digital comparison instruction set is constructed to transform the inspection scope, technical tolerances, and configuration verification rules into directly executable digital tasks; this enables the automatic distribution and standardized execution of equipment lists, inspection points, and part number version verifications, reducing errors caused by manual transcription.

[0095] Preferably, the structural inspection of the four major functional systems is carried out in conjunction with the manufacturing conformity checklist, specifically as follows:

[0096] 1) Configuration consistency check: Scan the electronic tags of airborne equipment, automatically read the part number, serial number, and software version information, compare them with the approved configuration database in real time, and complete the verification of document-to-fact consistency and document-to-document consistency.

[0097] 2) Surface structure inspection of key areas: Surface quality inspection is carried out on the machine head skin, the area around the static pressure hole, and the sensor installation area to obtain structural data such as skin waviness, seam gap and step difference, mounting base step difference, sensor head step difference, and rivet protrusion and concavity.

[0098] 3) Inspection of the structure and function of the tow cone system: Conduct verification of the tow cone installation structure, airtightness test, retraction and remote control function test, and cable laying inspection to obtain structural installation and airtightness performance data;

[0099] The configuration inspection data, surface structure data, and drag cone system inspection data are summarized to form the structural inspection data for the four major functional systems. This achieves full coverage of RVSM-related manufacturing compliance, systematic inspection by modules, and standardization of various measured data.

[0100] Among them, the text-fact consistency enhancement comparison method is used to check configurational consistency, specifically as follows:

[0101] By scanning the electronic tags of airborne equipment and airframe components, the device automatically obtains information such as part number, hardware serial number, and software version number.

[0102] The physical information read is compared with the approved configuration database in real time online. If there is a complete match, an electronic signature of "configuration approved" is automatically generated.

[0103] If discrepancies exist, the configuration management database is automatically connected to match historical change records. The discrepancies are classified into three levels according to their relevance to RVSM functions: permissible deviations, deviations requiring engineering evaluation, and unacceptable deviations. The corresponding deviation handling workflow is then triggered for each level.

[0104] A visually guided automatic measurement and real-time judgment method is used to inspect the surface structure of key areas, specifically as follows:

[0105] Using an airworthiness-approved laser scanner or augmented reality equipment, the preset coordinates of the inspection points and the measurement path are projected onto the surface of the aircraft to guide the inspectors to accurately locate and measure.

[0106] The measuring instrument automatically transmits the collected surface geometric data to the mobile terminal, fills in the corresponding fields of the manufacturing conformity checklist in real time, and automatically compares and judges it with the preset surface quality technical standards.

[0107] After the measurement is completed, the mobile terminal automatically generates a surface quality inspection report for key areas, including skin waviness, seam gap and step difference, sensor mounting base step difference, sensor head and base step difference, and rivet head concavity and convexity, according to the preset template, forming structural inspection data.

[0108] The structural and functional checks of the towing cone system specifically include:

[0109] Mechanical structure and installation accuracy checks were performed on the towing cone installation section, the retraction mechanism, and the installation base to verify the structural assembly conformity and obtain structural installation data.

[0110] Based on the static pressure transmission sealing RVSM height measurement requirements, the airtightness performance of the towing cone system pipeline and cabin was tested, and airtightness test data was obtained.

[0111] Execute remote control commands in the cockpit to complete the verification codes for the automatic towing cone retraction function, remote control function, and status feedback function, and obtain function verification data.

[0112] The continuity and laying of the cables and signal transmission paths related to the tow cone were checked to obtain signal stability data.

[0113] Structural installation data, airtightness test data, functional verification data, and signal stability data are compiled to form the structural inspection data of the tow cone system.

[0114] Step S500: Compare and summarize the manufacturing conformity checklist and structural inspection data to obtain the manufacturing conformity evidence package.

[0115] All original inspection records, deviation handling forms, evidence citation lists, and parallel inspection sequence diagrams generated from the conformity checklist are compiled and organized into a manufacturing conformity evidence package according to the data structure (such as a conformity matrix table) approved by the review team. This evidence package includes a deviation impact analysis table, which is used to classify the non-conformities found in the inspection into RVSM functional impact levels (fatal / major / minor / negligible), and provides different rectification and re-inspection strategies accordingly.

[0116] The output format of the manufacturing conformity evidence package is as follows: it includes a conformity declaration summary table, which lists each item in a minimal, independent manufacturing conformity inspection scope checklist: inspection conclusion (compliant / non-compliant / not applicable), evidence index, evidence generation date, and inspector qualification number; and a deviation impact classification table, which indicates the impact level on RVSM functionality, recommended re-inspection method, and expected closure time for each non-compliance.

[0117] In summary, this application has the following advantages:

[0118] By narrowing the inspection scope through hierarchical mapping, clarifying surface technical requirements through error assessment, achieving multi-link parallel inspection through the critical path method, and solidifying the results through structured on-site inspection and evidence packages, we can break away from the traditional serial inspection mode that relies on whole-aircraft certification. This enables the independent, process-oriented, and standardized demonstration of RVSM manufacturing compliance, thereby shortening the airworthiness review cycle, reducing the cost of repetitive inspections, and ensuring the integrity and rigor of aircraft RVSM airworthiness compliance determination.

[0119] Breaking away from the traditional RVSM airworthiness review model that must rely on whole-aircraft certification, this approach establishes a three-layer mapping and quantitative screening rule for functions, airborne equipment, and physical areas. This creates a quantifiable, traceable, and reusable minimum inspection scope, eliminating the arbitrariness of manually defined scopes. It avoids omissions and over- or redundant inspections, supporting applications in scenarios such as aircraft RVSM-specific independent airworthiness certification, modification certification, and component localization review.

[0120] As another specific implementation, an aircraft RVSM airworthiness certification manufacturing conformity indication system includes:

[0121] The scope list design module is used to collect data from different levels within the four major functional systems required for RVSM operation, establish mapping relationships between different levels, and screen key equipment, hardware and software, and key areas of the machine body based on the mapping relationships between different levels to obtain a minimal independent manufacturing conformity inspection scope list.

[0122] The inspection process design module is used to perform error analysis and evaluation on the four major functional systems, obtain error allocation evaluation results, determine the surface quality technical requirements of each RVSM key area, and construct the manufacturing conformity inspection process.

[0123] The link inspection design module is used to obtain the resource dependencies and data dependencies in the inspection scope based on the minimum independent list of manufacturing conformity inspection scopes and the manufacturing conformity inspection process; then, it uses the critical path method to determine at least two inspection links that are executed in parallel, and further generates a manufacturing conformity inspection checklist.

[0124] The structural inspection design module is used to perform manufacturing conformity checks on the four major functional systems, and, in conjunction with the manufacturing conformity checklist, to perform structural, configuration, RVSM critical area surface quality checks, and hydrostatic system functional checks on the four major functional systems.

[0125] The evidence package acquisition module is used to compare and summarize the manufacturing conformity checklist and structural inspection data to obtain the manufacturing conformity evidence package.

[0126] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification, characterized in that, include: Data from different levels within the four functional systems required for RVSM operation is collected, and mapping relationships between different levels are established. Based on these mapping relationships, key equipment, hardware, software, and critical areas of the machine body are screened to obtain a list of minimally independent manufacturing conformity inspection scopes. The four functional systems include a height measurement system, a height display and reporting system, a height alarm system, and a height holding system. Error analysis and evaluation were conducted on the four major functional systems to obtain the error allocation evaluation results, determine the surface quality technical requirements of each RVSM key area, and construct the manufacturing conformity inspection process. Based on the list of minimal independent manufacturing compliance checks, and in conjunction with the manufacturing compliance check process, obtain the resource dependencies and data dependencies within the check scope; Then, the critical path method is used to determine at least two parallel inspection links, and a manufacturing compliance checklist is generated. Manufacturing conformity checks were performed on the four major functional systems. In conjunction with the manufacturing conformity checklist, structural, configuration, surface quality checks of critical areas of the RVSM, and functional checks of the hydrostatic system were conducted on the four major functional systems to obtain structural inspection data. The manufacturing conformity checklist and structural inspection data are compared and summarized to obtain the manufacturing conformity evidence package.

2. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 1, characterized in that, The mapping relationship between different levels includes a three-layer mapping relationship of function-airborne equipment-physical area. Based on the mapping relationship of different levels, key equipment, hardware and software, and key areas of the airframe are screened. The specific design is as follows: Taking the static pressure source error allocation of RVSM operation as the main line, the altitude error budget item is back-linked to the corresponding LRU equipment, software configuration item and fuselage skin area to form a two-way traceability matrix of function-airborne equipment-physical area; The Boolean logic matrix is ​​used for correlation analysis, and the necessity score for the inspection is calculated using the following formula: Necessity of inspection = aerodynamic impact weight × 0.4 + functional impact weight × 0.3 + safety level coefficient × 0.3; When the necessity score for inspection is less than or equal to 0.7, the corresponding equipment, hardware, software, or body area will be included in the list of minimally independent manufacturing compliance inspection areas.

3. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 1, characterized in that, The manufacturing conformity inspection process is established as follows: Based on the RVSM height error allocation evaluation results, the 15cm area around the nose static pressure sensor and the ±5° pitch angle projected skin area are defined as the RVSM key control areas. Obtain the surface quality technical requirements for the critical control areas of the RVSM, including: skin surface waviness, skin seam gap and step difference, step difference of the sensor mounting base relative to the surrounding skin, step difference of the sensor head relative to the mounting base, and rivet head protrusion / concavity in the critical area. The manufacturing conformity inspection process is categorized into structural geometry inspection, airtightness testing, equipment installation verification, software and hardware version verification, and signal transmission verification to meet surface quality requirements.

4. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 1, characterized in that, Further, a manufacturing conformity checklist is generated, specifically as follows: Based on a minimal manufacturing conformity checklist, this study uses an enhanced comparison method that ensures document-to-fact consistency to identify the dependencies between various checks on personnel, tools, support resources, and input / output data. The critical path method is used to organize the originally sequential configuration checks, critical area surface condition checks, and drag cone system function checks into at least two parallel check chains: First link: RVSM functional system equipment configuration check, using the real-time configuration data management platform to compare and check with the actual installed software, and at the same time verify the history book or certificate of conformity to ensure that the actual installation status of the relevant software and hardware, history book / certificate of conformity are consistent with the approved configuration documents; The second link: Inspection of the surface quality and drag cone installation structure of the key areas of the fuselage RVSM, using a laser tracker or digital scanning equipment to record the geometric state of the key areas; After the two links are completed in parallel, they are merged into a unified data fusion node for cross-validation to obtain the cross-validation results; Based on the cross-validation results, the inspection items, acceptance criteria, tools and equipment, personnel qualifications, support conditions, and on-site record items are broken down to form a manufacturing conformity checklist.

5. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 4, characterized in that, Before conducting manufacturing conformity checks on the four major functional systems, the following also applies: A digital comparison instruction set is generated based on the minimized manufacturing conformity checklist, the surface quality technical requirements of RVSM key areas, and the parallel inspection chain. The digital comparison instruction set specifically includes: 1) Automatically generate a list of equipment to be inspected and its corresponding airworthiness approval document number based on the minimum inspection scope; 2) Generate an executable inspection task sequence based on surface quality technical requirements, including inspection point coordinates, allowable tolerances, measuring tool numbers, and measurement paths; 3) Generate a triplet verification table of equipment part number, software version number, and hardware serial number based on the approved configuration for automatic on-site configuration comparison.

6. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 1, characterized in that, Structural checks of the four major functional systems were conducted in conjunction with the manufacturing conformity checklist, specifically as follows: 1) Configuration consistency check: Scan the electronic tags of airborne equipment, automatically read the part number, serial number, and software version information, compare them with the approved configuration database in real time, and complete the verification of document-to-fact consistency and document-to-document consistency. 2) Surface structure inspection of key areas: Surface quality inspection is carried out on the machine head skin, the area around the static pressure hole, and the sensor installation area to obtain structural data such as skin waviness, seam gap and step difference, mounting base step difference, sensor head step difference, and rivet protrusion and concavity. 3) Inspection of the structure and function of the tow cone system: Conduct verification of the tow cone installation structure, airtightness test, retraction and remote control function test, and cable laying inspection to obtain structural installation and airtightness performance data; The configuration inspection data, surface structure data, and drag cone system inspection data are summarized to form the structural inspection data of the four major functional systems.

7. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 6, characterized in that, A text-fact consistency enhancement comparison method is used to check configurational consistency, specifically as follows: By scanning the electronic tags of airborne equipment and airframe components, the device automatically obtains information such as part number, hardware serial number, and software version number. The physical information read is compared with the approved configuration database in real time online. If there is a complete match, an electronic signature of "configuration approved" is automatically generated. If discrepancies exist, the configuration management database is automatically connected to match historical change records. The discrepancies are classified into three levels according to their relevance to RVSM functions: permissible deviations, deviations requiring engineering evaluation, and unacceptable deviations. The corresponding deviation handling workflow is then triggered for each level.

8. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 6, characterized in that, A visually guided automatic measurement and real-time judgment method is used to inspect the surface structure of key areas, specifically as follows: Using an airworthiness-approved laser scanner or augmented reality equipment, the preset coordinates of the inspection points and the measurement path are projected onto the surface of the aircraft to guide the inspectors to accurately locate and measure. The measuring instrument automatically transmits the collected surface geometric data to the mobile terminal, fills in the corresponding fields of the manufacturing conformity checklist in real time, and automatically compares and judges it with the preset surface quality technical standards. After the measurement is completed, the mobile terminal automatically generates a surface quality inspection report for key areas, including skin waviness, seam gap and step difference, sensor mounting base step difference, sensor head and base step difference, and rivet head concavity and convexity, according to the preset template, forming structural inspection data.

9. The method for demonstrating manufacturing conformity for aircraft RVSM airworthiness certification as described in claim 6, characterized in that, The structural and functional inspection of the towing cone system specifically includes: Mechanical structure and installation accuracy checks were performed on the towing cone installation section, the retraction mechanism, and the installation base to verify the structural assembly conformity and obtain structural installation data. Based on the static pressure transmission sealing RVSM height measurement requirements, the airtightness performance of the towing cone system pipeline and cabin was tested, and airtightness test data was obtained. Execute remote control commands in the cockpit to complete the verification codes for the automatic towing cone retraction function, remote control function, and status feedback function, and obtain function verification data. The continuity and laying of the cables and signal transmission paths related to the tow cone were checked to obtain signal stability data. Structural installation data, airtightness test data, functional verification data, and signal stability data are compiled to form the structural inspection data of the tow cone system.

10. A manufacturing conformity indication system for aircraft RVSM airworthiness certification, employing the method described in any one of claims 1-9, characterized in that, include: The scope list design module is used to collect data from different levels within the four major functional systems required for RVSM operation, establish mapping relationships between different levels, and screen key equipment, hardware and software and key areas of the machine body based on the mapping relationships between different levels to obtain a minimal independent manufacturing conformity inspection scope list. The inspection process design module is used to perform error analysis and evaluation on the four major functional systems, obtain error allocation evaluation results, determine the surface quality technical requirements of each RVSM key area, and construct the manufacturing conformity inspection process. The link inspection design module is used to obtain the resource dependencies and data dependencies in the inspection scope based on a list of minimally independent manufacturing compliance inspection scopes and the manufacturing compliance inspection process. Then, the critical path method is used to determine at least two parallel inspection links, and a manufacturing compliance checklist is generated. The structural inspection design module is used to perform manufacturing conformity checks on the four major functional systems, and, in conjunction with the manufacturing conformity checklist, to perform structural, configuration, RVSM critical area surface quality checks, and hydrostatic system functional checks on the four major functional systems. The evidence package acquisition module is used to compare and summarize the manufacturing conformity checklist and structural inspection data to obtain the manufacturing conformity evidence package.

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