A mating integrated tooling for a large aircraft window frame assembly

Abstract

The application discloses a kind of big aircraft skylight framework assembly's folding integrated tool, including assembly base, windshield assembly component, cabin roof panel assembly component;Wherein, windshield assembly component, cabin roof panel assembly component are installed on the same assembly base, windshield assembly component is used to assemble aircraft windshield, including windshield assembly framework and several windshield assembly positioning members;Cabin roof panel assembly component is used to assemble aircraft cockpit roof panel, including cabin roof panel assembly framework and several panel assembly positioning members;Windshield assembly component, cabin roof panel assembly component are respectively supported and fixed by corresponding framework and assembly positioning member to the frame and skin required to the component assembled, so that the assembly of aircraft windshield and cockpit roof panel can be integrated on a tool, avoid the problem that multiple sets of tool are needed for independent assembly and occupy large space, and parallel assembly production of different aircraft and different components can be realized, which is beneficial to the improvement of production efficiency.

Description

Technical Field

[0001] This application relates to the field of aircraft manufacturing technology, and in particular to a tooling for the assembly and integration of a large aircraft sunroof frame component. Background Technology

[0002] Aircraft component assembly refers to the process of positioning various aircraft components using locators on tooling, such as threaded pins, limit pins, conformal surface clamps, stops, and inspection blocks, and then rigidly connecting these components to form a complete large component or part. Cockpit component assembly typically involves planning different process flows for the components to be assembled, based on factors such as component size, assembly rationality, openness, safety, and mating relationships. This ensures the assembly of various aircraft components is completed while meeting assembly precision and technical requirements. The sunroof frame assembly mainly includes the windshield assembly and the cockpit roof panel assembly; its assembly process is a crucial step in cockpit structural assembly, and the accuracy and efficiency of the assembly directly affect the overall assembly quality and timeline.

[0003] In existing technologies, the assembly of sunroof frame components (including windshield components and cockpit roof panel components) is mainly completed in stages using multiple sets of specialized tooling. Specifically, typically, one set of tooling is first used to position and assemble the windshield component, and then the semi-finished product is transferred to another set of tooling by hoisting to continue assembling the cockpit roof panel component. In this process, the assembly work not only relies on multiple sets of independent tooling, resulting in high costs, but the layout of multiple tooling occupies a large amount of production space, limiting the effective utilization of workshop space. At the same time, the staged assembly requires strict adherence to the sequential operation, and the windshield component and roof panel component cannot be operated in parallel, resulting in a lengthy assembly cycle. In addition, frequent hoisting of large components not only increases operational risks but may also introduce positioning reference errors when switching tooling, affecting cumulative accuracy. In terms of assembly openness, the complex tooling structure, numerous fixed locators, and limited assembly space make it difficult for operators to flexibly adjust or avoid obstacles, affecting the convenience and safety of assembly. Summary of the Invention

[0004] The main objective of this application is to provide an assembly and integration tooling for a large aircraft sunroof frame assembly, in order to solve the problem of poor efficiency caused by the independent operation of each part in the assembly process of the aircraft sunroof frame assembly in the prior art.

[0005] To achieve the above objectives, this application provides the following technical solution: a tooling for assembling and integrating a large aircraft sunroof frame assembly, characterized in that it comprises:

[0006] Assemble the base;

[0007] A windshield assembly assembly, used for assembling aircraft windshields, is disposed on one side of the assembly base and includes a windshield assembly frame and several windshield assembly positioning components; wherein...

[0008] The windshield assembly frame is constructed with the streamlined outline of an aircraft windshield and is vertically configured to support the frame and skin required for assembling the aircraft windshield.

[0009] Several windshield assembly positioning components are installed on the windshield assembly frame and correspond to various structural positions of the aircraft windshield, used to fix the frame and skin required for assembling the aircraft windshield.

[0010] The cockpit roof panel assembly assembly, used for assembling the aircraft cockpit roof panels, is symmetrically positioned on the other side of the assembly base and includes a cockpit roof panel assembly frame and several panel assembly positioning components; wherein...

[0011] The roof panel assembly frame is erected with the arched profile of the roof panel and is used to support the frame and skin required for assembling the roof panel.

[0012] Several wall panel assembly positioning components are installed on the cabin roof wall panel assembly frame and correspond to the various structural positions of the cabin roof wall panel, used to fix the frame and skin required for assembling the cabin roof wall panel.

[0013] For example, in the mating and integration tooling provided in at least one embodiment of this application, the windshield assembly frame includes a first main support frame and a first configuration frame. The first configuration frame is divided into multiple windshield longitudinal frames and at least one windshield transverse frame. The multiple windshield longitudinal frames are connected between the first main support frame and the assembly base. The windshield transverse frame is connected between the multiple windshield longitudinal frames, and both ends are respectively installed on the first main support frame to form a streamlined profile structure of the aircraft windshield.

[0014] Several windshield assembly positioning components are respectively installed on the first main support frame, multiple windshield longitudinal frames, the windshield transverse frame, and the assembly base, for fixing the frame and skin of the aircraft windshield respectively.

[0015] For example, in the assembly tooling provided in at least one embodiment of this application, the cabin roof panel assembly frame includes a second main support frame and a second configuration frame. The second configuration frame is divided into multiple cabin roof transverse frames and at least one cabin roof longitudinal frame. The cabin roof longitudinal frame is connected between the second main support frame and the assembly base. The multiple cabin roof transverse frames are installed in parallel on the cabin roof longitudinal frame, and their two ends are respectively installed on the second main support frame to form an arched profile structure of the aircraft cabin roof.

[0016] Several wall panel assembly positioning components are respectively installed on the second main support frame, the longitudinal frame of the cabin roof, multiple transverse frames of the cabin roof, and the assembly base, for fixing the frame and skin of the assembled cabin roof wall panel respectively.

[0017] For example, in the mating and integration tooling provided in at least one embodiment of this application, a plurality of windshield assembly positioning components include a telescopic frame positioner, a fixed frame positioner, and a skin lug hole positioner.

[0018] Multiple telescopic frame positioners are configured and are respectively installed on the first main support frame and each windshield longitudinal frame;

[0019] Multiple fixed frame positioners are configured and installed on each windshield longitudinal frame and the windshield transverse frame, respectively.

[0020] At least two skin lug hole positioners are symmetrically arranged and installed on the assembly base.

[0021] For example, in at least one embodiment of this application, the mating and integration tooling includes a number of panel assembly positioning components, such as a fixed frame positioning device and a skin lug hole positioning device.

[0022] Multiple fixed frame positioners are configured and are respectively installed on each transverse frame on the top of the compartment and on the assembly base;

[0023] At least two skin lug hole positioners are symmetrically arranged and installed on the assembly base.

[0024] For example, in at least one embodiment of the assembly tooling provided in this application, the cabin top wall panel assembly frame further includes a windshield fixing bracket and a telescopic frame positioner; wherein...

[0025] Multiple telescopic frame positioners are configured and installed on the second main support frame;

[0026] The windshield fixing bracket is connected to the longitudinal frame on the top of the cabin and is equipped with a windshield frame locator;

[0027] The telescopic frame positioner and the windshield frame positioner are used to secure the assembled aircraft windshield.

[0028] For example, in at least one embodiment of the mating and integration tooling provided in this application, the plurality of wall panel assembly positioning components further include a stringer positioner and a stringer end face stop, wherein,

[0029] The stringer positioner is configured as a plurality of them, and is installed on each of the transverse frames on the top of the compartment;

[0030] The stringer end face is configured as multiple, and is respectively installed on the assembly base.

[0031] For example, in at least one embodiment of the present application, the bottom of the assembly base is provided with several leveling supports.

[0032] For example, in at least one embodiment of the present application, the assembly of the cabin top wall panel further includes a skin tensioning strap, the two ends of which are installed on the cabin top wall panel assembly frame and are tightened and fixed by fitting the skin.

[0033] For example, in at least one embodiment of the present application, the windshield assembly assembly further includes a skin marking template, which is mounted on the assembly base and close to the windshield transverse frame for marking and trimming the skin edge.

[0034] Compared with existing aircraft sunroof frame assembly tooling and related methods and processes, the mating and integration tooling of this application has at least the following beneficial effects: the windshield assembly assembly and the cockpit roof panel assembly assembly respectively support and fix the frame and skin required for assembly through corresponding skeletons and assembly positioning parts, so that the assembly of the aircraft windshield and cockpit roof panel can be integrated on a common tooling (assembly base), avoiding the problem of needing to use multiple sets of tooling and occupying a lot of space for separate independent assembly, and enabling different components of the aircraft to be assembled and produced in parallel; in addition, through the position association design of the assembly structure on the same tooling, the windshield assembly assembly and the cockpit roof panel assembly assembly are located on both sides of the assembly base. After the aircraft windshield and cockpit roof panel are assembled, they can be quickly mated after the fixation is released, which can significantly improve the mating work efficiency. Attached Figure Description

[0035] Figure 1 This is a side view of an embodiment of the integrated tooling of this application;

[0036] Figure 2 for Figure 1 A schematic diagram of the side view structure from a mid-facing perspective;

[0037] Figure 3 A diagram illustrating the assembly of an aircraft windshield on a mating and integrated tooling embodiment.

[0038] Figure 4 A front view of the assembly positioning component installed on an embodiment of the mating and integrating tooling;

[0039] Figure 5 A top view of the assembly positioning component installed on an example of a mating integrated tooling;

[0040] Figure 6 Another top view of the assembly positioning component installed on the mating integrated tooling embodiment;

[0041] Figure 7 This is a diagram demonstrating the alignment of the aircraft windshield and cabin roof panel in an embodiment of the assembly tooling.

[0042] Numbering Explanation: 100, Circular Assembly Base; 200, Windshield Assembly Component; 210, Windshield Assembly Frame; 211, First Main Support Frame; 212, First Configuration Frame; 212-a, Windshield Longitudinal Frame; 212-b, Windshield Transverse Frame; 213, Skin Marking Template; 220, Aircraft Windshield; 221, Porthole; 222, Windshield Top; 300, Cabin Top Wall Panel Assembly Component; 310, Cabin Top Wall Panel Assembly Frame; 311, ... Second main support frame; 312, Second configuration frame; 312-a, Cabin roof transverse frame; 312-b, Cabin roof longitudinal frame; 313, Windshield fixing bracket; 320, Cabin roof wall panel; 410, Telescopic frame positioner; 420, Fixed frame positioner; 430, Skin lug hole positioner; 440, Long stringer positioner; 450, Long stringer end face stop; 460, Windshield frame positioner; 470, Skin tensioning strap; 500, Leveling support;

[0043] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0044] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0045] The terms "first," "second," and "third" in this application are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first," "second," or "third" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified. All directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationships and movements between components in a specific orientation (as shown in the figures). If the specific orientation changes, the directional indications also change accordingly. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or devices.

[0046] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a mutually exclusive, independent, or alternative embodiment. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0047] This application provides a mating and integration fixture for a large aircraft sunroof frame assembly. The fixture includes an assembly base, a windshield assembly assembly, and a cabin roof panel assembly assembly. The windshield assembly assembly, used for assembling the aircraft windshield, is located on one side of the assembly base and includes a windshield assembly frame and several windshield assembly positioning components. The windshield assembly frame is vertically configured with a streamlined outline of the aircraft windshield to support the frame and skin required for assembling the windshield. The windshield assembly positioning components are mounted on the windshield assembly frame and align with various structural positions of the aircraft windshield. The system comprises a frame and skin for securing the aircraft windshield; a cockpit roof panel assembly assembly for assembling the aircraft cockpit roof panel, symmetrically positioned on the other side of the assembly base, including a roof panel assembly frame and several panel assembly positioning components; the roof panel assembly frame is erected with the arched profile of the roof panel to support the frame and skin required for assembling the roof panel; and the panel assembly positioning components are installed on the roof panel assembly frame and correspond to various structural positions of the roof panel to secure the frame and skin required for assembling the roof panel.

[0048] Specifically, see Figure 1 and Figure 2 This is one embodiment of the assembly tooling of this application. The assembly tooling is supported by an annular assembly base 100. The annular assembly base 100 has two arc / bend sections as two sides, on which a windshield assembly assembly 200 and a cabin roof panel assembly 300 are respectively provided. The windshield assembly assembly 200 and the cabin roof panel assembly 300 are symmetrical in position, so that after the aircraft windshield 220 and the cabin roof panel 320 are assembled on both sides respectively, it is convenient to assemble them, for example, by hoisting or other means to install the aircraft windshield 220 onto the cabin roof panel 320.

[0049] The windshield assembly frame 210 of the windshield assembly assembly 200 is structured to match the streamlined profile of the aircraft windshield 220, that is, it gradually expands from the nose tip towards the cabin. In the tooling of this embodiment, this is achieved through the following structure: the windshield assembly frame 210 includes a first main support frame 211 and a first configuration frame 212. The first main support frame 211 is located in the middle position of the annular assembly base 100 (relative to the two sides) and is in the shape of a "door" or an arch. The first configuration frame 212 is divided into three windshield longitudinal frames. The windshield consists of a 212-a and a windshield transverse frame 212-b. Three windshield longitudinal frames 212-a are connected between the first main support frame 211 and the annular mounting base 100, and are inclined at a certain angle to form a streamlined shape. The windshield transverse frame 212-b is connected between multiple windshield longitudinal frames 212-a, and its two ends are respectively installed on the first main support frame 211. The streamlined profile of the aircraft windshield 220 is formed by the structural combination of the windshield longitudinal frames 212-a and the windshield transverse frame 212-b.

[0050] It should be noted that the aircraft windshield 220 to be assembled in this application can be broadly divided into two parts: the window 221 and the windshield top 222. Figure 1 In the windshield assembly frame 210 shown, the aircraft windshield 220 is assembled in a vertical installation posture with the porthole 221 on top and the top of the windshield 222 on the bottom. The assembled product is as follows: Figure 3 As shown, the upper half of the windshield longitudinal frame 212-a mainly constitutes the tilt angle of the porthole 221, while the lower half and the windshield transverse frame 212-b are used to support the curved structure forming the windshield top 222. It can be understood that the key to the combined use of the windshield longitudinal frame 212-a and the windshield transverse frame 212-b is to form a streamlined profile and provide fixed support. The assembly posture and orientation of the windshield are determined by the combination of the windshield longitudinal frame 212-a and the windshield transverse frame 212-b. Without substantially deviating from the basic structure of the windshield assembly frame 210 of this application, any changes in form, such as adjusting the assembly direction or orientation, should be considered substantially the same as this application. Furthermore, the quantities of each structure used in this embodiment are similar and will not be repeated.

[0051] Several windshield assembly positioning components are installed on various parts of the windshield assembly frame 210. In this embodiment, the main function of these positioning components is to position and fix the frame and skin used for assembling the aircraft windshield 220. They are comprehensively distributed, being installed on the first main support frame 211, the windshield longitudinal frame 212-a, the windshield transverse frame 212-b, and the assembly base. Figure 4 , Figure 5 , Figure 6 Below is a basic introduction.

[0052] In the windshield assembly assembly 200, the types of windshield assembly positioning components include telescopic frame positioning device 410, fixed frame positioning device 420, and skin lug hole positioning device 430.

[0053] Multiple telescopic frame positioners 410 are configured in the form of telescopic connecting rods, which are respectively fixed on the first main support frame 211, each windshield longitudinal frame 212-a and windshield transverse frame 212-b, and are connected and fixed to the windshield frame structure, for example by pin connection. The telescopic frame positioners 410 adapt to windshield products of different specifications or assembly standards through telescopic function.

[0054] Furthermore, in a possible implementation, the telescopic frame positioner 410 is fixedly installed on each part by a rotating structure, thereby achieving a certain angle adjustment to meet the actual needs of windshield assembly.

[0055] Multiple fixed frame positioners 420 are configured with common traditional connection and fixing methods such as coordination holes and fixed positions, and are respectively installed on each windshield longitudinal frame 212-a and windshield transverse frame 212-b. They are mainly used to position and fix the internal frame and other structural components of the windshield; similarly, pin connection can also be used.

[0056] The skin ear hole positioner 430 is used to position the skin. Two are set and symmetrically installed on the annular assembly base 100. The positioning and fixing are achieved by connecting with the ear holes on the skin, and the basic assembly of the skin and frame is basically finalized.

[0057] It should be understood that the installation of each of the above-mentioned positioners needs to correspond to the structural position of the windshield, for example, in combination with Figure 5 The single-sided window section of the windshield is positioned using telescopic frame locators 410 and fixed frame locators 420 (a total of 8), and then the skin is positioned using skin lug hole locators 430. The basic structure positioning and fixation of the aircraft windshield are then completed, and assembly can begin.

[0058] Specifically, the windshield assembly assembly 200 also includes a skin marking template 213, which is mounted on the annular assembly base 100 near the windshield transverse frame 212-b. The template is similar in shape to the transverse frame 212-b, but with a longer arc length. It is mainly used for marking and trimming the skin edge. That is, when the skin length is greater than the assembly parameters, the template is used as a reference for marking, and then the excess skin is cut off.

[0059] See Figure 1 , Figure 2On the other side of the annular assembly base 100, a cabin roof panel assembly assembly 300 is provided. This assembly includes a cabin roof panel assembly frame 310 and panel assembly positioning components. The cabin roof panel assembly frame 310 is similar to the curved structure of the cockpit cabin roof panel, that is, it is arched and can be connected to the end edge of the aircraft windshield. In the tooling of this embodiment, it is achieved by the following structure: the cabin roof panel assembly frame 310 includes a second main support frame 311 and a second configuration frame 312. The second main support frame 311 is "door" shaped. The second configuration frame 312 is divided into three cabin roof transverse frames 312-a and one cabin roof longitudinal frame 312-b. The cabin roof longitudinal frame 312-b is connected between the second main support frame 311 and the assembly base. Multiple cabin roof transverse frames 312-a are installed in parallel on the cabin roof longitudinal frame 312-b, and both ends are installed on the second main support frame 311 respectively. The combined structure of the cabin roof transverse frames 312-a forms the arched profile structure of the aircraft cabin roof.

[0060] In the wall panel assembly frame structure of the above embodiment, the second column support frame and the longitudinal frame 312-b of the cabin roof are both set up as the main support. The arched profile of the cabin roof is mainly formed by the arc shape and installation method of multiple transverse frames 312-a of the cabin roof. Therefore, it can be understood that whether it is the second main support frame 311 or the longitudinal frame 312-b of the cabin roof, as long as it can provide support and fixation for the transverse frame 312-a of the cabin roof to form an arched structure, it is not limited to the specific structure in this embodiment.

[0061] Taking the wall panel assembly structure of this embodiment as an example, several wall panel assembly positioning components include a fixed frame positioner 420 and a skin lug hole positioner 430, each in multiple quantities. The fixed frame positioner 420 and the skin lug hole positioner 430 have the same function as those in the aforementioned windshield assembly 200; see Figure 4 , Figure 5 , Figure 6 The fixed frame positioners 420 are installed on each of the transverse frames 312-a on the top of the cabin and on the assembly base, and are distributed at intervals; the skin lug hole positioners 430 are also symmetrically installed on the annular assembly base 100 at the same positions.

[0062] More specifically, the wall panel assembly positioning components also include stringer positioners 440 and stringer end face blocks 450. Multiple stringer positioners 440 are configured and installed on each transverse frame 312-a on the top of the cabin, respectively, to position and fix the stringer by clamping. The stringer end face blocks 450 are installed on the assembly base to limit and fix the ends of the stringer. In addition, there are multiple stringers in the structure of the top wall panel, and the number of stringer end face blocks 450 corresponds to the number of stringers. Therefore, all stringers can be positioned and assembled by the positioning combination of the stringer positioners 440 and the stringer end face blocks 450.

[0063] The structure of the wall panel assembly is relatively regular, mainly depending on the arched curved surface structure of the roof wall panel. Similar to the windshield assembly 200, it also adopts a vertical assembly posture, which can effectively reduce the space occupied during assembly and avoid damage to the frame and skin during operation.

[0064] Furthermore, the roof bulkhead assembly 300 also includes a skin tensioning strap 470, the two ends of which are mounted on the roof bulkhead assembly frame 310 and fitted to the skin to tighten and secure it. See Figure 7 On the side wall of the second main support frame 311, there are buckles for fastening the end of the skin tensioning strap 470. When the skin is covered onto the frame structure, the end of the skin tensioning strap 470 is fixed by the buckles and stretched laterally to fasten to the second main support frame 311. The skin is kept in a tight state to prevent it from falling off.

[0065] The skin tensioning straps 470 can be arranged in the same manner as the transverse frame 312-a on the top of the cabin, with three or more straps arranged in parallel.

[0066] The windshield assembly component 200 and the wall panel assembly component of this application can be used in parallel during the assembly process, shortening the assembly cycle of the sunroof frame component. After the components on both sides are assembled, the positioning devices on the windshield assembly are released, and the assembled windshield is lifted and aligned with the tooling on the other side. Figure 1 Taking the assembly posture as an example, rotate 180° along the vertical axis, adjust the angle and position, and then use a locator to fix it in place. Figure 7 The assembly posture in the process.

[0067] In the above assembly process, the aircraft windshield 220 is aligned with the cabin roof panel 320 by the windshield assembly assembly 200 and the cabin roof panel assembly assembly 300. Since the cabin roof panel assembly assembly 300 is mainly used for assembling the cabin roof panel 320, it lacks the positioning and fixing parts required for the alignment process, which is not conducive to the completion of the alignment operation. Therefore, in some embodiments of this application, the cabin roof panel assembly frame 310 also includes a windshield fixing bracket 313 and a telescopic frame locator 410. Among them, multiple telescopic frame locators 410 are provided and installed on the second main support frame 311. The windshield fixing bracket 313 is connected to the cabin roof longitudinal frame 312-b and is provided with a windshield frame locator 460. The telescopic frame locator 410 and the windshield frame locator 460 are used to fix the assembled aircraft windshield.

[0068] like Figure 1 , Figure 2As shown, the longitudinal frame 312-b on the cabin roof is equipped with an upwardly extending windshield fixing bracket 313, the position of which corresponds to the windshield mating position. The windshield fixing bracket 313 and the second main support frame 311 are respectively equipped with a windshield frame locator 460 and a telescopic frame locator 410, which can fix the assembled windshield frame part, so that the aircraft windshield 220 and the cabin roof wall panel 320 can be mated in a relatively stable state.

[0069] It should be noted that the positioning components involved in the foregoing embodiments, such as the telescopic frame positioner 410, the fixed frame positioner 420, the skin lug hole positioner 430, and the windshield frame positioner 460, can all be understood as prior art. Therefore, this application will not provide a detailed description of the structure of each positioner, and positioners with the same name on various components (such as the skin lug hole positioner 430 on two assembly components) can be understood in the same way. This application aims to protect the technical solution of arranging each positioner accordingly based on the main structure of the tooling to achieve the positioning and fixing effect of specific assembly components.

[0070] In some embodiments of this application, the bottom of the mounting base is further equipped with several leveling supports 500, for example... Figure 1 , Figure 2 The ring-shaped assembly base 100 shown in the figure has multiple settings at its bottom, which can achieve horizontal adjustment of the entire tooling and avoid tilting.

[0071] The specific embodiments of the invention have been described in detail above, but these are merely examples, and the invention is not limited to the specific embodiments described above. For those skilled in the art, any equivalent modifications or substitutions to the invention are also within the scope of this invention. Therefore, all equivalent transformations, modifications, and improvements made without departing from the spirit and principles of this invention should be included within the scope of this invention.

Claims

1. A tooling for assembling and integrating a large aircraft sunroof frame assembly, characterized in that, include: Assemble the base; A windshield assembly assembly, used for assembling aircraft windshields, is disposed on one side of the assembly base and includes a windshield assembly frame and several windshield assembly positioning components; wherein... The windshield assembly frame is vertically configured with a streamlined outline of an aircraft windshield, including a first main support frame and a first configuration frame. The first configuration frame is divided into multiple windshield longitudinal frames and at least one windshield transverse frame. The multiple windshield longitudinal frames are connected between the first main support frame and the assembly base. The windshield transverse frame is connected between the multiple windshield longitudinal frames, and its two ends are respectively mounted on the first main support frame to form a streamlined outline of the aircraft windshield; used to support the frame and skin required for assembling the aircraft windshield; Several windshield assembly positioning components are installed on the windshield assembly frame and correspond to various structural positions of the aircraft windshield, used to fix the frame and skin required for assembling the aircraft windshield. The cockpit roof panel assembly assembly, used for assembling the aircraft cockpit roof panels, is symmetrically positioned on the other side of the assembly base and includes a cockpit roof panel assembly frame and several panel assembly positioning components; wherein... The cabin roof panel assembly frame is vertically configured with the arched profile of the cabin roof panel, including a second main support frame and a second configuration frame. The second configuration frame is divided into multiple cabin roof transverse frames and at least one cabin roof longitudinal frame. The cabin roof longitudinal frame is connected between the second main support frame and the assembly base. The multiple cabin roof transverse frames are installed parallel to the cabin roof longitudinal frame, and their two ends are respectively installed on the second main support frame to form the arched profile of the aircraft cabin roof, which is used to support the frame and skin required for assembling the cabin roof panel. Several wall panel assembly positioning components are installed on the cabin roof wall panel assembly frame and correspond to the various structural positions of the cabin roof wall panel, used to fix the frame and skin required for assembling the cabin roof wall panel.

2. The assembly tooling according to claim 1, characterized in that, Several windshield assembly positioning components are respectively installed on the first main support frame, multiple windshield longitudinal frames, the windshield transverse frame, and the assembly base, for fixing the frame and skin of the aircraft windshield respectively.

3. The assembly tooling according to claim 1, characterized in that, Several wall panel assembly positioning components are respectively installed on the second main support frame, the longitudinal frame of the cabin roof, multiple transverse frames of the cabin roof, and the assembly base, for fixing the frame and skin of the assembled cabin roof wall panel respectively.

4. The assembly tooling according to claim 2, characterized in that, Several windshield assembly positioning components include telescopic frame positioning devices, fixed frame positioning devices, and skin lug hole positioning devices; Multiple telescopic frame positioners are configured and are respectively installed on the first main support frame and each windshield longitudinal frame; Multiple fixed frame positioners are configured and installed on each windshield longitudinal frame and the windshield transverse frame, respectively. At least two skin lug hole positioners are symmetrically arranged and installed on the assembly base.

5. The assembly tooling according to claim 3, characterized in that, Several panel assembly positioning components include fixed frame positioning devices and skin lug hole positioning devices; Multiple fixed frame positioners are configured and are respectively installed on each transverse frame on the top of the compartment and on the assembly base; At least two skin lug hole positioners are symmetrically arranged and installed on the assembly base.

6. The mating and integration tooling according to claim 5, characterized in that, The cabin roof panel assembly frame also includes a windshield fixing bracket and a telescopic frame positioner; wherein... Multiple telescopic frame positioners are configured and installed on the second main support frame; The windshield fixing bracket is connected to the longitudinal frame on the top of the cabin and is equipped with a windshield frame locator; The telescopic frame positioner and the windshield frame positioner are used to secure the assembled aircraft windshield.

7. The mating and integration tooling according to claim 5, characterized in that, Several panel assembly positioning components also include stringer positioners and stringer end face stops, among which, The stringer positioner is configured as a plurality of them, and is installed on each of the transverse frames on the top of the compartment; The stringer end face is configured as multiple, and is respectively installed on the assembly base.

8. The assembly tooling according to claim 1, characterized in that, The bottom of the assembly base is equipped with several leveling supports.

9. The assembly tooling according to claim 1, characterized in that, The cabin roof panel assembly also includes a skin tensioning strap, the two ends of which are installed on the cabin roof panel assembly frame and are tightened and fixed by fitting the skin.

10. The assembly tooling according to claim 2, characterized in that, The windshield assembly also includes a skin marking template, which is mounted on the assembly base and close to the windshield transverse frame for marking and trimming the skin edges.

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