A digital assembly process for civil aircraft framed door structural components

Abstract

The present invention relates to a digital assembly process method for a cabin door structure component for a civil aircraft, which belongs to the field of aircraft assembly technology and includes the following steps: 1) constructing an assembly process digital model; 2) designing an integrated skeleton assembly streamlined tooling; 3) designing a parts manufacturing process digital model for the cabin door structure component digital assembly method for the assembly delivery requirements; 4) designing a tolerance determination method based on digital assembly and parameter-driven tolerance zone geometric elements constrained by the delivery requirements. In the technical background of digital machining and high-precision measurement of parts, the digital assembly process method for a cabin door structure component for a civil aircraft proposed by the present invention completely changes the assembly process in which the parts in the "skin" and "skeleton" are simultaneously positioned by complex tooling.

Description

Technical Field

[0001] The invention relates to a digital assembly process method for a framed cabin door structural component of a civil aircraft, belonging to the technical field of aircraft assembly. Background Art

[0002] With the continuous expansion of the demand for the civil aviation market, the demand for rapid manufacturing and delivery of civil aircraft is increasing day by day, which puts higher requirements on the assembly efficiency and quality of civil aircraft. With the development of automation technologies such as automatic drilling and riveting, as well as high-precision digital measurement technologies such as laser trackers, the assembly of civil aircraft has gotten rid of the analog quantity transmission assembly method of mold line templates and fully entered the era of digital assembly. At the same time, the machining of civil aircraft parts is undergoing a profound digital manufacturing transformation with the rapid development of new generation information technology, precision CNC processing technology, and high-precision measurement technology. The design, process, manufacturing, and inspection and delivery of civil aircraft parts have achieved full process digitization, which can realize the continuous completion of CNC machining and high-precision measurement of different parts on a fully automated unmanned production line. The in-depth development of digital manufacturing of civil aircraft parts provides a basic premise for the further transformation of digital assembly of civil aircraft.

[0003] The structural dimensions of the framed cabin door structural assembly of a civil aircraft are relatively small, and the frames, beams, bulkheads and other parts involved are all CNC machined parts, which have better rigidity than sheet metal frames and sheet metal beam parts. Under the above technical background, the present invention proposes a digital assembly process method for the framed cabin door structural assembly of a civil aircraft, and designs a new digital assembly process for the framed cabin door structural assembly of a civil aircraft to improve assembly efficiency and quality. Summary of the invention

[0004] The technical problem to be solved by the present invention is how to further improve the assembly efficiency and quality by conducting a new digital design of the assembly process of the machined frame door structure components under the technical background of digital machining and high-precision measurement of parts.

[0005] In order to solve the above problems, the present invention deeply studies the assembly characteristics and delivery requirements of the machine-added frame cabin door structure assembly, and invents a digital assembly process method for the machine-added frame cabin door structure assembly of a civil aircraft by performing a new digital design on the assembly process of the machine-added frame cabin door structure assembly, including the following complete set of technical solutions:

[0006] A digital assembly process method for a framed cabin door structural component of a civil aircraft includes the following complete process methods:

[0007] 1) Design a 3D digital model of the assembly process for the digital assembly of the hatch structure components based on “assembly characteristics” and “delivery requirements”:

[0008] The "machine-added frame cabin door" is relative to the "sheet metal frame cabin door", which is characterized by the "frame and beam parts" that constitute the cabin door being processed and formed by metal cutting machine tools, and having good rigidity;

[0009] The "door structure assembly" mentioned above refers to the rigid door body part of the civil aircraft door except for the "door movement mechanism assembly", "door insulation pad" and "door interior" parts; the "door structure assembly" includes the "skin" which is a thin-walled part formed by sheet metal technology that conforms to the aerodynamic shape of the aircraft, and the "skeleton" part that is closely attached to the "skin" and is used to ensure the aerodynamic shape of the "skin" and the rigidity of the door;

[0010] The door "skeleton" is a rigid frame structure composed of "beam parts" arranged along the axis of the aircraft body and "frame parts" arranged perpendicular to the axis of the aircraft body, connected by rivets, bolts, etc.

[0011] The assembly process three-dimensional digital model is formed by reconstructing the three-dimensional digital model of the hatch structure component engineering design according to the assembly process requirements of the new design; it includes two parts, the "skeleton" and the "skin", and the "assembly process benchmark" of the parts is newly designed and defined;

[0012] The "assembly process datum" mentioned above includes "assembly process hole datum" and "assembly process surface datum";

[0013] The "assembly process hole datum" is designed and defined in the "skeleton" assembly process as follows: based on the "assembly characteristic" of direct mutual positioning between parts and the convenience of assembly operation, a specific hole is selected and defined from the "fastener point line hole" set of the engineering design three-dimensional digital model;

[0014] The "assembly process hole benchmark" is designed and defined in the "skin and frame assembly" process as follows: based on the "delivery requirements", the specific holes distributed on the "skin" related to the "assembly characteristics" are selected and defined from the "fastener point line hole" set of the engineering design three-dimensional digital model;

[0015] The “fastener point-line hole” mentioned above refers to a set of graphics used to represent the positions and axes of fasteners such as rivets and bolts in the three-dimensional digital model of the door structure component engineering design;

[0016] The “delivery requirements” mentioned above include the requirements for the fit between the “skin” and the “frame”, the requirements for the skin contour, the requirements for the shape and position of the bearing holes, and the requirements for the shape and position of the stop joints;

[0017] The "assembly process surface reference" is designed and defined as the assembly contact surface between parts in the "skeleton assembly" process, and is designed and defined as the assembly contact surface between the "skeleton" and the "skin" in the "skin and skeleton assembly" process;

[0018] The "assembly process benchmark" is marked in the assembly process digital model in the form of 3D annotations and is included in the graphic set of "assembly process benchmark";

[0019] 2) Design an integrated “skeleton assembly streamlined tooling” based on the digital assembly process of the hatch structure components oriented to “assembly characteristics” and “delivery requirements”:

[0020] The positioning surface of the "skeleton assembly simplified tooling" is only the fitting surface of the "skeleton" and the "skin", and the positioning surface is a CNC machined surface made of an integrated component after one-time clamping; the "assembly process hole reference" in the "skin and skeleton assembly" process is arranged on the positioning surface; a clamp is arranged around the "skeleton assembly simplified tooling" to fix the "frame" and "beam" of the "skeleton" assembly; the "skeleton assembly simplified tooling" is equipped with a clamping clamp to facilitate the clamping and fixing of the internal "beam" during the "skeleton" assembly;

[0021] The tolerance zone geometric elements of the positioning surface are constructed in the digital model of the "simplified tooling for skeleton assembly" and marked in the form of 3D annotations, and are collected in a graphic set called "simplified tooling tolerance zone"; the high-precision measurement point cloud of the positioning surface of the delivered tooling should be within the "simplified tooling tolerance zone";

[0022] 3) Design the digital model of the parts manufacturing process based on the "assembly process benchmark" and oriented to the "delivery requirements":

[0023] The described part manufacturing process digital model is characterized by: defining the "key feature geometric elements of part delivery" based on the assembly "delivery requirements", and completely defining the tolerance requirements of the "key feature geometric elements of part delivery" based on the "assembly process benchmark" to replace the corresponding engineering design three-dimensional digital model part tolerance requirements, and constructing tolerance zone geometric elements in the part manufacturing process digital model, marking them in the form of 3D annotations, and at the same time collecting them in a graphic set named "part manufacturing tolerance zone" to construct the part manufacturing process digital model; the high-precision measurement point cloud of the delivered part should be within the "part manufacturing tolerance zone";

[0024] 4) Design a tolerance determination method based on digital assembly and parametrically driven tolerance zone geometric elements with "delivery requirements" as constraints:

[0025] In the three-dimensional digital model of the "skeleton assembly streamlined tooling" and the three-dimensional digital model of the parts manufacturing process, the limit deviations of the "streamlined tooling tolerance zone" and the "parts manufacturing tolerance zone" are parameterized and assigned initial values, and then the limit deviation geometric elements driven by the above limit deviation parameters are constructed in the three-dimensional digital model; the above limit deviation geometric elements are used for assembly and coordination, and the "limit deviation assembly digital model" is constructed according to the limit deviations of the "delivery requirements" of the hatch structure components; finally, the acceptable "skeleton assembly streamlined tooling" manufacturing tolerance and part manufacturing tolerance values ​​are determined according to the "delivery requirements" of the hatch structure components;

[0026] 5) Design digital assembly process methods for hatch structure components based on “assembly characteristics” and “delivery requirements”:

[0027] The process method includes two major process steps, namely "frame assembly" and "skin and frame assembly", which completely changes the assembly process method in which all parts of the "skin" and "frame" are on the same complex tooling, and each part is positioned by a tooling locator;

[0028] The "skeleton assembly" process is an assembly positioning method that combines positioning of "skeleton" parts in "skeleton assembly streamlined tooling" and direct positioning of "skeleton" parts with each other:

[0029] The "frame" and "beam" of the hatch are positioned in the "skeleton assembly streamlined tooling" according to the "assembly process surface datum" and "assembly process hole datum" to ensure that the shape and position tolerances of the mating surface of the "skeleton" assembly and the "skin" meet the assembly requirements; at the same time, the "frame" and "beam" parts are also positioned relative to each other through the "assembly process surface datum" and "assembly process hole datum"; the coordination of the positioning of the parts in the "skeleton assembly streamlined tooling" and the mutual positioning of the parts is ensured by the tolerance of the newly designed "skeleton assembly streamlined tooling" and the tolerance of the parts manufacturing process digital model, as well as the gaskets allowed to be added to the three-dimensional digital model of the hatch structure component engineering design;

[0030] The above assembly process uses a spring pin specially used for aircraft assembly, which passes through the "assembly process hole datum" of the matching parts and the tooling to complete the centering of the "assembly process hole datum" and the tensioning of the "assembly process surface datum"; then the clamp and clamp configured by the tooling are used to fix the positioned parts;

[0031] After the "skeleton" parts are completely positioned and fixed in the "skeleton assembly streamlined tooling", the remaining "point and line holes" of the "skeleton" are drilled, and the "skeleton" parts are disassembled and the drilling burrs are removed; then the "skeleton" is reassembled on the "skeleton assembly streamlined tooling" according to the above process method, and the "skeleton" fasteners are installed to complete the "skeleton" assembly;

[0032] The "skin and frame assembly" process is an assembly process method that uses the "skin" and the "frame" to directly position each other:

[0033] Place the assembled "skeleton" and "skin" with the mating side facing upwards and stably on the assembly operating table, and position the "skin" on the "skeleton" according to the "assembly process surface datum" and "assembly process hole datum"; the above-mentioned assembly process uses a spring pin specially used for aircraft assembly, which passes through the "assembly process hole datum" of the matching "skin" and "skeleton" to complete the centering of the "assembly process hole datum" and the tightening of the "assembly process surface datum"; then complete the drilling of the remaining "dot-line holes" of the assembly of the "skin" and the "skeleton", and disassemble the "skin" and the "skeleton" to remove the drilling burrs, and then reassemble the "skin" and the "skeleton" according to the above-mentioned process method, and install the fasteners to complete the assembly of the cabin door structure components.

[0034] The beneficial effects brought by the present invention are as follows: Under the technical background of digital machining and high-precision measurement of parts, the digital assembly process method for machine-mounted frame door structural components of civil aircraft proposed by the present invention completely changes the assembly process in which the parts in the "skin" and "skeleton" are simultaneously positioned by complex tooling. The present invention effectively simplifies the assembly process flow of machine-mounted frame door structural components, reduces the complexity of assembly operations, saves assembly operation time, and improves assembly production efficiency; it greatly reduces the complexity of the relevant assembly tooling structure, improves tooling reliability, saves tooling design, manufacturing, regular inspection and other costs, and has good practicality. At present, except for the sheet metal frame doors of a few small and medium-sized regional civil aircraft, the present invention is suitable for the assembly of most regional and trunk civil aircraft door structural components, and has a wide range of applicability. DETAILED DESCRIPTION

[0035] A digital assembly process method for a framed cabin door structural component of a civil aircraft includes the following complete process methods:

[0036] 1) Design a 3D digital model of the assembly process for the digital assembly of the hatch structure components based on “assembly characteristics” and “delivery requirements”:

[0037] The "machine-added frame cabin door" is relative to the "sheet metal frame cabin door", which is characterized by the "frame and beam parts" that constitute the cabin door being processed and formed by metal cutting machine tools, and having good rigidity;

[0038] The "door structure assembly" mentioned above refers to the rigid door body part of the civil aircraft door except for the "door movement mechanism assembly", "door insulation pad" and "door interior" parts; the "door structure assembly" includes the "skin" which is a thin-walled part formed by sheet metal technology that conforms to the aerodynamic shape of the aircraft, and the "skeleton" part that is closely attached to the "skin" and is used to ensure the aerodynamic shape of the "skin" and the rigidity of the door;

[0039] The door "skeleton" is a rigid frame structure composed of "beam parts" arranged along the axis of the aircraft body and "frame parts" arranged perpendicular to the axis of the aircraft body, connected by rivets, bolts, etc.

[0040] The assembly process three-dimensional digital model is formed by reconstructing the three-dimensional digital model of the hatch structure component engineering design according to the assembly process requirements of the new design; it includes two parts, the "skeleton" and the "skin", and the "assembly process benchmark" of the parts is newly designed and defined;

[0041] The "assembly process datum" mentioned above includes "assembly process hole datum" and "assembly process surface datum";

[0042] The "assembly process hole datum" is designed and defined in the "skeleton" assembly process as follows: based on the "assembly characteristic" of direct mutual positioning between parts and the convenience of assembly operation, a specific hole is selected and defined from the "fastener point line hole" set of the engineering design three-dimensional digital model;

[0043] The "assembly process hole benchmark" is designed and defined in the "skin and frame assembly" process as follows: based on the "delivery requirements", the specific holes distributed on the "skin" related to the "assembly characteristics" are selected and defined from the "fastener point line hole" set of the engineering design three-dimensional digital model;

[0044] The “fastener point-line hole” mentioned above refers to a set of graphics used to represent the positions and axes of fasteners such as rivets and bolts in the three-dimensional digital model of the door structure component engineering design;

[0045] The “delivery requirements” mentioned above include the requirements for the fit between the “skin” and the “frame”, the requirements for the skin contour, the requirements for the shape and position of the bearing holes, and the requirements for the shape and position of the stop joints;

[0046] The "assembly process surface reference" is designed and defined as the assembly contact surface between parts in the "skeleton assembly" process, and is designed and defined as the assembly contact surface between the "skeleton" and the "skin" in the "skin and skeleton assembly" process;

[0047] The "assembly process benchmark" is marked in the assembly process digital model in the form of 3D annotations and is included in the graphic set of "assembly process benchmark";

[0048] 2) Design an integrated “skeleton assembly streamlined tooling” based on the digital assembly process of the hatch structure components oriented to “assembly characteristics” and “delivery requirements”:

[0049] The positioning surface of the "skeleton assembly simplified tooling" is only the fitting surface of the "skeleton" and the "skin", and the positioning surface is a CNC machined surface made of an integrated component after one-time clamping; the "assembly process hole reference" in the "skin and skeleton assembly" process is arranged on the positioning surface; a clamp is arranged around the "skeleton assembly simplified tooling" to fix the "frame" and "beam" of the "skeleton" assembly; the "skeleton assembly simplified tooling" is equipped with a clamping clamp to facilitate the clamping and fixing of the internal "beam" during the "skeleton" assembly;

[0050] The tolerance zone geometric elements of the positioning surface are constructed in the digital model of the "simplified tooling for skeleton assembly" and marked in the form of 3D annotations, and are collected in a graphic set called "simplified tooling tolerance zone"; the high-precision measurement point cloud of the positioning surface of the delivered tooling should be within the "simplified tooling tolerance zone";

[0051] 3) Design the digital model of the parts manufacturing process based on the "assembly process benchmark" and oriented to the "delivery requirements":

[0052] The described part manufacturing process digital model is characterized by: defining the "key feature geometric elements of part delivery" based on the assembly "delivery requirements", and completely defining the tolerance requirements of the "key feature geometric elements of part delivery" based on the "assembly process benchmark" to replace the corresponding engineering design three-dimensional digital model part tolerance requirements, and constructing tolerance zone geometric elements in the part manufacturing process digital model, marking them in the form of 3D annotations, and at the same time collecting them in a graphic set named "part manufacturing tolerance zone" to construct the part manufacturing process digital model; the high-precision measurement point cloud of the delivered part should be within the "part manufacturing tolerance zone";

[0053] 4) Design a tolerance determination method based on digital assembly and parametrically driven tolerance zone geometric elements with "delivery requirements" as constraints:

[0054] In the three-dimensional digital model of the "skeleton assembly streamlined tooling" and the three-dimensional digital model of the parts manufacturing process, the limit deviations of the "streamlined tooling tolerance zone" and the "parts manufacturing tolerance zone" are parameterized and assigned initial values, and then the limit deviation geometric elements driven by the above limit deviation parameters are constructed in the three-dimensional digital model; the above limit deviation geometric elements are used for assembly and coordination, and the "limit deviation assembly digital model" is constructed according to the limit deviations of the "delivery requirements" of the hatch structure components; finally, the acceptable "skeleton assembly streamlined tooling" manufacturing tolerance and part manufacturing tolerance values ​​are determined according to the "delivery requirements" of the hatch structure components;

[0055] 5) Design digital assembly process methods for hatch structure components based on “assembly characteristics” and “delivery requirements”:

[0056] The process method includes two major process steps, namely "frame assembly" and "skin and frame assembly", which completely changes the assembly process method in which all parts of the "skin" and "frame" are on the same complex tooling, and each part is positioned by a tooling locator;

[0057] The "skeleton assembly" process is an assembly positioning method that combines positioning of "skeleton" parts in "skeleton assembly streamlined tooling" and direct positioning of "skeleton" parts with each other:

[0058] The "frame" and "beam" of the hatch are positioned in the "skeleton assembly streamlined tooling" according to the "assembly process surface datum" and "assembly process hole datum" to ensure that the shape and position tolerances of the mating surface of the "skeleton" assembly and the "skin" meet the assembly requirements; at the same time, the "frame" and "beam" parts are also positioned relative to each other through the "assembly process surface datum" and "assembly process hole datum"; the coordination of the positioning of the parts in the "skeleton assembly streamlined tooling" and the mutual positioning of the parts is ensured by the tolerance of the newly designed "skeleton assembly streamlined tooling" and the tolerance of the parts manufacturing process digital model, as well as the gaskets allowed to be added to the three-dimensional digital model of the hatch structure component engineering design;

[0059] The above assembly process uses a spring pin specially used for aircraft assembly, which passes through the "assembly process hole datum" of the matching parts and the tooling to complete the centering of the "assembly process hole datum" and the tensioning of the "assembly process surface datum"; then the clamp and clamp configured by the tooling are used to fix the positioned parts;

[0060] After the "skeleton" parts are completely positioned and fixed in the "skeleton assembly streamlined tooling", the remaining "point and line holes" of the "skeleton" are drilled, and the "skeleton" parts are disassembled and the drilling burrs are removed; then the "skeleton" is reassembled on the "skeleton assembly streamlined tooling" according to the above process method, and the "skeleton" fasteners are installed to complete the "skeleton" assembly;

[0061] The "skin and frame assembly" process is an assembly process method that uses the "skin" and the "frame" to directly position each other:

[0062] Place the assembled "skeleton" and "skin" with the mating side facing upwards and stably on the assembly operating table, and position the "skin" on the "skeleton" according to the "assembly process surface datum" and "assembly process hole datum"; the above-mentioned assembly process uses a spring pin specially used for aircraft assembly, which passes through the "assembly process hole datum" of the matching "skin" and "skeleton" to complete the centering of the "assembly process hole datum" and the tightening of the "assembly process surface datum"; then complete the drilling of the remaining "dot-line holes" of the assembly of the "skin" and the "skeleton", and disassemble the "skin" and the "skeleton" to remove the drilling burrs, and then reassemble the "skin" and the "skeleton" according to the above-mentioned process method, and install the fasteners to complete the assembly of the cabin door structure components.

Claims

1. A digital assembly process for a framed cabin door structural component of a civil aircraft, characterized in that: Including the following set of process methods: 1) Design a 3D digital model of the assembly process for the digital assembly of hatch structure components based on "assembly characteristics" and "delivery requirements": The "machine-attached frame door" is relative to the "sheet metal frame door". The "frame and beam parts" that constitute the door are processed and formed by metal cutting machine tools, and have good rigidity. The "door structure assembly" mentioned above refers to the rigid door body part of the door of a civil aircraft except for the "door movement mechanism assembly", "door insulation pad" and "door interior" parts; the "door structure assembly" includes the "skin" which is a thin-walled part formed by sheet metal technology that conforms to the aerodynamic shape of the aircraft, and the "frame" part that is closely attached to the "skin" and is used to ensure the aerodynamic shape of the "skin" and the rigidity of the door; The "skeleton" is a rigid frame structure composed of "beam parts" arranged along the axis of the aircraft body and "frame parts" arranged perpendicular to the axis of the aircraft body, connected by rivets and bolts; The assembly process three-dimensional digital model is formed by reconstructing the three-dimensional digital model of the hatch structure component engineering design according to the assembly process requirements of the new design; it includes two parts, the "skeleton" and the "skin", and the "assembly process benchmark" of the parts is newly designed and defined; The "assembly process datum" includes "assembly process hole datum" and "assembly process surface datum"; The "assembly process hole datum" is designed and defined in the "skeleton" assembly process as follows: based on the "assembly characteristic" of direct mutual positioning between parts and the convenience of assembly operation, a specific hole is selected and defined from the "fastener point line hole" set of the engineering design three-dimensional digital model; The "assembly process hole benchmark" is designed and defined in the "skin and frame assembly" process as follows: based on the "delivery requirements", the specific holes distributed on the "skin" related to the "assembly characteristics" are selected and defined from the "fastener point line hole" set of the engineering design three-dimensional digital model; The "fastener point line hole" mentioned above refers to a set of graphics used to represent the position and axis of fasteners such as rivets and bolts in the three-dimensional digital model of the door structure component engineering design; The "delivery requirements" include the "skin" and "frame" fit requirements, skin contour requirements, bearing hole shape and position requirements, stop joint shape and position requirements; The "assembly process surface reference" is defined as the assembly contact surface between parts in the "skeleton assembly" process, and is defined as the assembly contact surface between the "skeleton" and the "skin" in the "skin and skeleton assembly" process; The "assembly process benchmark" is marked in the assembly process digital model in the form of 3D annotations and is included in the graphic set of "assembly process benchmark"; 2) Design an integrated "skeleton assembly streamlined tooling" based on the digital assembly process of the hatch structure components oriented to "assembly characteristics" and "delivery requirements": The positioning surface of the "simplified tooling for skeleton assembly" is only the fitting surface between the "skeleton" and the "skin", and the positioning surface is a CNC machined surface made of an integrated component after one-time clamping; the "assembly process hole reference" in the "skin and skeleton assembly" process is arranged on the positioning surface; a clamp is arranged around the "simplified tooling for skeleton assembly" to fix the "frame" and "beam" of the "skeleton" assembly; the "simplified tooling for skeleton assembly" is equipped with a clamping clamp to facilitate the clamping and fixing of the internal "beam" during the assembly of the "skeleton"; The geometric elements of the tolerance zone of the positioning surface are constructed in the digital model of the "simplified tooling for skeleton assembly" and marked in the form of 3D annotations. At the same time, they are grouped in a graphic set called "simplified tooling tolerance zone". The high-precision measurement point cloud of the positioning surface of the delivered tooling should be within the "simplified tooling tolerance zone". 3) Design the digital model of the parts manufacturing process based on the "assembly process benchmark" and oriented to the "delivery requirements": The part manufacturing process digital model defines the "key feature geometric elements of part delivery" based on the assembly "delivery requirements", and newly defines the tolerance requirements of the "key feature geometric elements of part delivery" based on the "assembly process benchmark" to replace the corresponding engineering design three-dimensional digital model part tolerance requirements, and constructs the tolerance zone geometric elements in the part manufacturing process digital model, identifies them in the form of 3D annotations, and collects them in a graphic set called "part manufacturing tolerance zone" to construct the part manufacturing process digital model; the high-precision measurement point cloud of the delivered part should be within the "part manufacturing tolerance zone"; 4) Design a tolerance determination method for geometric elements of tolerance zones based on digital assembly and parametrically driven tolerance zones with "delivery requirements" as constraints: In the three-dimensional digital model of "skeleton assembly streamlined tooling" and the three-dimensional digital model of the parts manufacturing process, the limit deviations of the "streamlined tooling tolerance zone" and the "parts manufacturing tolerance zone" are parameterized and assigned initial values, and then the limit deviation geometric elements driven by the above limit deviation parameters are constructed in the three-dimensional digital model; the above limit deviation geometric elements are used for assembly and coordination, and the "limit deviation assembly digital model" is constructed according to the limit deviation of the "delivery requirements" of the hatch structure components; finally, the acceptable "skeleton assembly streamlined tooling" manufacturing tolerance and part manufacturing tolerance values ​​are determined according to the "delivery requirements" of the hatch structure components; 5) Design digital assembly process methods for hatch structure components based on "assembly characteristics" and "delivery requirements": The process method includes two major process steps, namely "frame assembly" and "skin and frame assembly", which completely changes the assembly process method in which all parts of the "skin" and "frame" are on the same complex tooling, and each part is positioned by a tooling locator; The "skeleton assembly" process is an assembly positioning method that combines positioning of "skeleton" parts in "skeleton assembly streamlined tooling" and direct positioning of "skeleton" parts with each other: The "frame" and "beam" of the hatch are positioned in the "skeleton assembly simplified tooling" according to the "assembly process surface datum" and "assembly process hole datum" to ensure that the shape and position tolerances of the mating surface of the "skeleton" assembly and the "skin" meet the assembly requirements; at the same time, the "frame" and "beam" parts are also positioned relative to each other through the "assembly process base surface datum" and "assembly process hole datum"; the coordination of the positioning of the parts in the "skeleton assembly simplified tooling" and the mutual positioning of the parts is ensured by the tolerance of the newly designed "skeleton assembly simplified tooling" and the tolerance of the parts manufacturing process digital model, as well as the gaskets allowed to be added to the three-dimensional digital model of the hatch structure component engineering design; The above assembly process uses a special spring pin for aircraft assembly, which passes through the matching parts and the "assembly process hole reference" of the tooling to complete the centering of the "assembly process hole reference" and the tensioning of the "assembly process surface reference"; then the clamp and clamp configured by the tooling are used to fix the positioned parts; After the "skeleton" parts are completely positioned and fixed on the "skeleton assembly streamlined tooling", complete the drilling of the remaining "point and line holes" of the "skeleton", decompose the "skeleton" parts and remove the drilling burrs; then reassemble the "skeleton" on the "skeleton assembly streamlined tooling" according to the above process method, and install the "skeleton" fasteners to complete the "skeleton" assembly; The "skin and frame assembly" process is an assembly process method that uses the "skin" and "frame" to directly position each other: The assembled "skeleton" and "skin" are placed stably on the assembly operating table with the mating side facing upwards, and the "skin" is positioned on the "skeleton" according to the "assembly process surface datum" and "assembly process hole datum"; the above-mentioned assembly process uses a spring pin specially used for aircraft assembly, which passes through the "assembly process hole datum" matched by the "skin" and the "skeleton" to complete the centering of the "assembly process hole datum" and the tightening of the "assembly process surface datum"; then the drilling of the remaining "point and line holes" of the assembly of the "skin" and the "skeleton" is completed, and the "skin" and the "skeleton" are disassembled to remove the drilling burrs, and then the "skin" and the "skeleton" are reassembled according to the above-mentioned process method, and the fasteners are installed to complete the assembly of the cabin door structure components.