Vertical assembly tool system for truncated-cone-shaped nose of large airplane

Abstract

The invention discloses a vertical assembly tool system for a truncated cone-shaped nose of a large aircraft, which comprises a wallboard assembly component and a general assembly component, the wallboard assembly component is used for assembling a side wallboard of the truncated cone-shaped nose of the large aircraft and comprises a first assembly base, a wallboard tool framework, a skin shape-preserving clamping plate, a skin bandage presser and a wallboard assembly positioning piece; the final assembly assembly is used for folding and final assembly of the multiple assembled side wall plates and comprises a second assembly base, a final assembly tool framework, a side wall plate mounting piece and a folding assembly positioning piece; according to the assembly tool system, the side wall plates of the circular-truncated-cone-shaped nose and the nose of the large aircraft are integrally and independently assembled through the wall plate assembly assembly and the final assembly assembly assembly, a complete assembly process is formed, synchronous assembly with a cockpit assembly is not needed, and the nose part assembly technology is separated from a main production line; and the production and assembly efficiency of the machine nose can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft manufacturing, and particularly to a vertical assembly tooling system for the frustum-shaped nose of a large aircraft. Background Art

[0002] The nose is a typical structure of a large aircraft. It is often located between the aircraft radome and the aircraft airtight pressurization frame, and mainly consists of a skin, a frame, stringers, a nose maintenance access frame, an aircraft connection joint, etc. The nose has various structural forms, such as a frustum structure, a quadrangular frustum structure, a lower open special-shaped structure, etc., among which the frustum-shaped nose is the most widely used.

[0003] Currently, the assembly of the frustum-shaped nose of a large aircraft mainly relies on the solution integrated into the cockpit component alignment tooling. Specifically, that is, the nose tooling and the assembly tooling of the cockpit component are combined into one, and during the assembly process, the cockpit alignment and the nose positioning and installation need to be completed synchronously. This solution has the following characteristics: First, tooling integration. The frustum-shaped nose tooling is an accessory part of the cockpit alignment tooling, sharing the same assembly space and structural framework; Second, operation synchronization. The nose assembly needs to wait until the cockpit component alignment is completed before it can be carried out, and the assembly processes are interdependent. These two characteristics also cause the following problems in this solution: The integration of the cockpit component assembly and the nose tooling leads to a crowded assembly space, and multi-type operations are prone to interference, with poor personnel mobility. The operator needs to complete the nose positioning and installation in a narrow space, and it is difficult to guarantee the use of tools and the assembly accuracy, which affects the assembly efficiency; The nose assembly progress is completely restricted by the alignment cycle of the cockpit component, and the cockpit's standing time on the rack is usually long, resulting in the nose being unable to be taken off the rack alone and the production process unable to be optimized; In addition, because the tooling attitude is the same as the aircraft attitude, the operator inevitably needs to directly step on the nose skin for assembly, which is likely to cause local deformation of the skin or offset of the connection joint, affecting the aerodynamic shape and structural strength of the product and the product quality. Summary of the Invention

[0004] The main purpose of the present invention is to provide a vertical assembly tooling system for the frustum-shaped nose of a large aircraft, so as to solve the problem of poor production efficiency caused by the inability to be independent during the assembly process of the frustum-shaped nose of a large aircraft in the prior art.

[0005] To achieve the above object, the present invention provides the following technical solution: A vertical assembly tooling system for the frustum-shaped nose of a large aircraft, the vertical assembly tooling system includes: A panel assembly component for assembling the side panels of the frustum-shaped nose of the large aircraft, including a first assembly base, a panel tooling framework, a skin conformal clamping plate, a skin bandage compressor, and a panel assembly positioning member; wherein, the side panel includes a frame part and a skin part; The panel tooling framework is vertically arranged on the first assembly base; The skin conforming fixture is horizontally and parallelly installed on the panel tooling framework, and includes at least two layers, and the outer edge of each layer is configured with the arc of the circumferential surface of a frustum of a cone; At least two skin bandage compressors are installed along the edge of the first assembly base, and apply tension to the skin through the bandage to make the skin closely adhere to the skin conforming fixture; A plurality of panel assembly positioning members are configured, and are respectively installed on the skin conforming fixture and the panel tooling framework to fix the frame part and the skin part respectively; The general assembly component is used for aligning and assembling a plurality of the side panels that have been assembled, and includes a second assembly base, a general assembly tooling framework, side panel mounting members, and alignment assembly positioning members; wherein, The general assembly tooling framework is vertically arranged on the second assembly base; At least two groups of side panel mounting members are configured, and are respectively arranged on both sides of the general assembly tooling framework for installing two side panels with opposite openings in alignment; A plurality of alignment assembly positioning members are configured, and are respectively installed on the general assembly tooling framework and the side panel mounting members to fix the assembled side panels.

[0006] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, the panel tooling framework includes: A first installation frame, and the first installation frame is installed on the first assembly base in the form of a frustum contour; A truss, and the truss is installed on the axial direction of the frustum contour of the first installation frame.

[0007] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, the panel assembly positioning members include an opening frame angle section locator, an opening frame cross beam web block, an opening frame cross beam end face block, a connection joint locator, a panel frame locator, and a stringer locator; wherein, The opening frame angle section locators are symmetrically installed on the first installation frame; The opening frame cross beam web blocks are symmetrically installed at the ends of each layer of skin conforming fixtures; The opening frame cross beam end face blocks are symmetrically installed on one side of the first installation frame close to the first assembly base; The connection joint locator is installed on the first assembly base; The panel frame locator is installed on each layer of skin conforming fixtures; The stringer locator is installed on the truss.

[0008] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, the skin panel assembly positioning member further includes a skin lug locator, and the skin lug locator is installed on the first assembly base.

[0009] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, two or more sets of the wall panel assembly components are arranged on the first assembly base.

[0010] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, the general assembly tooling framework includes a second installation frame and an auxiliary frame. The second installation frame is installed on the second assembly base in the form of a frustum contour. The auxiliary frame is installed on the second assembly base and is connected to the second installation frame.

[0011] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, each set of side wall panel mounting members includes a support frame and a skin trimming clamping plate, and the skin trimming clamping plate is fixed on the second assembly base through the support frame.

[0012] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, the skin trimming clamping plate is arranged at intervals in a segmented form and / or in a whole-segment form.

[0013] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, the alignment assembly positioning member includes a belt plate locator, a plate frame locator, a wall panel limit stop, and a radar frame locator; wherein, The belt plate locator is installed on the skin support clamping plate; The plate frame locator is installed on the support frame; The wall panel limit stop is installed on the second installation frame; The radar frame locator is installed on the auxiliary frame.

[0014] For example, in the vertical assembly tooling system provided by at least one embodiment of the present invention, a plurality of framework leveling supports are arranged at the bottom of the wall panel tooling framework and / or the general assembly tooling framework.

[0015] Compared with the existing nose assembly tooling and related methods and processes, the vertical assembly tooling system of the present invention has at least the following beneficial effects: first, part of the side wall panels of the nose are vertically assembled through the wall panel assembly components, for example, the skin and frame are accurately positioned and accurately shaped through the skin conformal clamps, skin bandage pressers and wall panel assembly positioning parts, ensuring that the specifications of the side wall panels meet the requirements; then, multiple assembled side wall panels are vertically aligned according to their position characteristics through the final assembly assembly components, for example, the alignment distribution position of the side wall panels is determined by the side wall panel mounting parts, and the positioning and fixing of each part of the side wall panels are performed through the alignment assembly positioning parts, so that the overall nose structure is obtained through the corresponding mechanical connection process. The most prominent advantage of nose assembly achieved using this tooling system is that the nose components are assembled and manufactured separately during the production process, and do not compete with the cockpit components for operating space, thereby improving the openness of the assembly operation; at the same time, it also solves the problem of the cone-shaped nose occupying the frame for a long time, breaking through the efficiency bottleneck of mass production and manufacturing; in addition, the vertical assembly method adopted changes the traditional nose assembly posture, making the nose stand upright in the assembly space, avoiding operators stepping on the product, and making assembly operations easier, which significantly improves the nose assembly quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a front view of an embodiment of a wall panel assembly component of the present invention; Figure 2 for Figure 1 A left side view of an embodiment of a mid-wall panel assembly assembly; Figure 3 It is a front view of an embodiment of the final assembly component of the present invention; Figure 4 for Figure 3 A front view of an embodiment of a mid-level assembly assembly; Serial number description: 100, wall panel assembly components; 101, first assembly base; 110, wall panel tooling frame; 111, first installation frame; 112, truss; 120, skin conformal clamp; 130, skin bandage presser; 140, wall panel assembly positioning piece; 141, mouth frame angle material positioning piece; 142, mouth frame cross beam web stopper; 143, mouth frame cross beam end stopper; 144, connection joint positioning piece; 145, wall panel frame positioning piece; 146, long stringer positioning piece; 147, skin ear positioning piece; 15 0. Wall panel frame leveling support; 200. Final assembly assembly component; 201. Second assembly base; 210. Final assembly tool frame; 211. Second installation frame; 212. Auxiliary frame; 220. Side wall panel mounting piece; 221. Support frame; 222. Left skin trimming card; 223. Right skin trimming card; 230. Assembly positioning piece; 231. Strip plate positioner; 232. Final assembly plate frame positioner; 233. Wall panel limit block; 234. Radar frame positioner; 240. Final assembly frame leveling support; The realization, functional features, and advantages of the purpose of this application will be further described in combination with the embodiments with reference to the accompanying drawings. Specific Embodiments

[0017] Next, the technical solutions in the embodiments of this application will be clearly and completely described in combination with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of this application.

[0018] The terms "first", "second", and "third" in this application are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first", "second", and "third" may explicitly or implicitly include at least one of such features. In the description of this application, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined. All directional indications (such as up, down, left, right, front, back...) in the embodiments of this application are only used to explain the relative positional relationship and movement conditions between components in a specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indications will also change accordingly. In addition, 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 optionally further includes steps or units not listed, or optionally further includes other steps or units inherent to these processes, methods, products, or devices.

[0019] Referring to "embodiments" herein means that the specific features, structures, or characteristics described in combination with the embodiments may be included in at least one embodiment of this application. The phrase appearing at various positions in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art will explicitly and implicitly understand that the embodiments described herein may be combined with other embodiments.

[0020] In view of the related problems existing in the nose assembly in the prior art, the present invention proposes a vertical assembly tooling system for the frustum-shaped nose of a large aircraft, providing a new assembly mode for the nose assembly.

[0021] See Figures 1 to 4, the vertical assembly tooling system for the frustum-shaped nose of the large aircraft of the present invention includes two assembly components that are sequentially related in the process, namely the panel assembly component and the general assembly component. The panel assembly component assembles the side panels of the frustum-shaped nose, and the general assembly component is used to align and assemble two or more assembled side panels to form a complete nose component. The utilization of these two assembly components enables this key structure of the nose to be no longer restricted by the cockpit synchronization, and can be independently realized and the efficiency can be improved in the production and assembly process.

[0022] For the panel assembly component, in the embodiment provided by the present invention, it includes a first assembly base, a panel tooling skeleton, a skin conformal clamping plate, a skin bandage compressor, and panel assembly positioning parts; wherein, the panel tooling skeleton is vertically arranged on the first assembly base; the skin conformal clamping plate is horizontally and parallelly installed on the panel tooling skeleton, at least including two layers, and the outer edge of each layer is configured with the arc of the frustum circumference; at least two skin bandage compressors are installed along the edge of the first assembly base, and apply tension to the skin through the bandage to make the skin closely adhere to the skin conformal clamping plate; a number of panel assembly positioning parts are configured and installed on the skin conformal clamping plate and the panel tooling skeleton respectively to fix the frame part and the skin part of the side panel respectively.

[0023] See Figure 1 , Figure 2 , which is a specific form of an embodiment of the panel assembly component 100 of the present invention. The panel assembly component 100 includes a first assembly base 101. On one side of the first assembly base 101, a first installation frame 111 and a truss 112 are vertically installed to form the panel tooling skeleton 110 of the panel assembly component 100; More specifically, to adapt to the side panel structure of the frustum-shaped nose, the first installation frame 111 is also configured in the form of a frustum contour, that is, installed on the first assembly base 101 in a frame structure similar to a trapezoid, and the truss 112 is obliquely installed on the frustum contour or the trapezoid axis, so that the first installation frame 111 and the truss 112 are in a divergent form from top to bottom.

[0024] Based on the skeleton formed by the first installation frame 111 and the truss 112, the panel assembly component 100 further includes a skin conformal clamping plate 120. In this embodiment, the skin conformal clamping plate 120 is realized in the form of arc segments. The skin conformal clamping plate 120 has three layers and is parallelly installed on the first installation frame 111 and the truss 112, and the arc length of each layer of the skin conformal clamping plate 120 gradually increases from top to bottom.

[0025] The skin bandage presser 130 is installed on the first assembly seat and is located below the lowermost layer of skin conformal templates 120, which is also near the edge of the first assembly seat. It can install a special skin bandage and generate a tensile force on the skin by adjusting the winding degree, so that the skin is closely attached to the skin conformal template 120. The skin bandage presser 130 can be installed in two, as shown in the figure, or more, which can be set according to the corresponding tension requirements.

[0026] The panel assembly positioning part 140 is used as a part for positioning and fixing the panel to be assembled in the panel assembly component 100. The specific types and numbers used need to be selected and designed according to the characteristics of the nose component in combination with the structure of the panel assembly component 100. For example, in this embodiment, the panel assembly positioning part 140 includes a frame angle section locator 141, a frame cross beam web stopper 142, a frame cross beam end face stopper 143, a connection joint locator 144, a panel frame locator 145, and a stringer locator 146.

[0027] Combined with Figure 1 、 Figure 2 , the frame angle section locator 141 is symmetrically installed on the first mounting frame 111 and is located above the uppermost layer of skin conformal templates 120. This locator can accurately position the nose maintenance frame and ensure that its position and angle meet the design requirements.

[0028] The frame cross beam web stopper 142 is symmetrically installed at the ends of each layer of skin conformal templates 120 and is used to restrict the position of the nose frame cross beam web and prevent it from shifting during assembly.

[0029] The frame cross beam end face stopper 143 is symmetrically installed on the first mounting frame 111 and is located below the lowermost layer of skin conformal templates 120. It is used to fix the end face position of the nose frame cross beam and restrict its axial movement. The connection joint locator 144 is installed on the first assembly base 101 and is used to fix the connection joint between the nose and other components of the aircraft to ensure the accuracy of the installation position and angle.

[0030] The panel frame locator 145 is distributed on each layer of skin conformal templates 120 and is used to position the frame parts inside the nose.

[0031] The stringer locator 146 is installed on the truss 112 and is distributed back and forth along the aircraft heading. There are two of them, which are used to ensure the linear alignment of the stringers.

[0032] In addition, in a possible implementation, the panel assembly positioning part 140 further includes a skin lug locator 147. This locator is installed on the first assembly base 101 and is symmetrically distributed with the truss 112 as the midpoint. It can position the lug structure on the skin and ensure its accurate alignment with the subsequent connection joint.

[0033] Through the functions of the various panel assembly positioning members 140 described above, the frame and the skin can be fixed on the panel assembly component 100 in the assembled posture, and subsequent processing and connection can be carried out by an operator.

[0034] In some other possible embodiments, more panel assembly components 100 as in the foregoing embodiments can be provided on the same first assembly base 101. For example, Figure 1 in the form of two groups symmetrically arranged as in this example, or multiple groups can be arranged in multiple directions so that more side panels can be assembled simultaneously.

[0035] In particular, a number of panel fixture skeletons leveling supports 150 are provided at the bottom of the panel fixture skeleton 110, for example, Figure 1 as shown in the bottom of the first assembly base 101.

[0036] During the assembly process of the side panels by the panel assembly component 100 in the above embodiments, its longitudinal structure makes the assembly of the side panels also in a vertical posture. This can not only avoid the problem of easily stepping on the skin horizontally and in the assembly mode of the cockpit component system, but also reduce the occupation of a large space for assembly operations, and improve the openness of the operation space in the form of separate assembly.

[0037] For the general assembly component, in the embodiments provided by the present invention, it includes a general assembly fixture skeleton, side panel mounting members, and alignment assembly positioning members; wherein, the general assembly fixture skeleton is vertically arranged on the second assembly base; the side panel mounting members are at least two groups, respectively arranged on both sides of the general assembly fixture skeleton for installing two side panels with opposite openings in alignment; the alignment assembly positioning members are configured in several numbers and are respectively installed on the general assembly fixture skeleton and the side panel mounting members to fix the assembled side panels.

[0038] Referring to Figure 3 and Figure 4 , it is a specific form of an embodiment of the general assembly component 200 of the present invention. The general assembly component 200 includes a second assembly base 201. A second mounting frame 211 is vertically installed at the middle position of the second assembly base 201. Similar to the first mounting frame 111 in the foregoing embodiments, the second mounting frame 211 is also configured in the form of a frustum contour, and can adapt to the butting edge of the side panel to assemble some fixing and positioning devices. In addition, an auxiliary frame 212 is vertically installed on the second assembly base 201, and the auxiliary frame 212 is connected to the second mounting frame 211 to form a structural reinforcement; the second mounting frame 211 and the auxiliary frame 212 constitute the structure of the general assembly fixture skeleton 210.

[0039] The side wall panel mounting members 220 include two or more groups. Taking two groups as an example, they are respectively installed on both sides of the second assembly base 201 with the second installation frame 211 as the boundary. Both groups of side wall panel mounting members 220 are installed on the second assembly base 201 through the support frame 221. Specifically, either the left skin trimming clamping plate 222 is connected and fixed through the support frame 221, or the right skin trimming clamping plate 223 is connected and fixed through the support frame 221. For example Figure 4 in Figure 4 , the left skin trimming clamping plate 222 is installed on the left side of the second installation frame 211, and the right skin trimming clamping plate 223 is installed on the right side of the second installation frame 211; when the assembled side wall panels are installed in an opposing manner, the side wall panels can be riveted, bolted, or other connection process operations in an installation posture with the openings facing each other on the general assembly component 200.

[0040] Specifically, the side wall panel mounting members 220 are used in the above two forms - that is, the left skin trimming clamping plate 222 and the right skin trimming clamping plate 223 are used in combination or alone; among them, the left skin trimming clamping plate 222 is set as a complete arc segment, and this form can provide a complete skin trimming reference for the assembled side wall panel skin trimming work that can be directly aligned; the right skin trimming clamping plate 223 is set with multiple arc segments at intervals, and the space between each arc segment is used to draw the theoretical skin marking line after the nose assembly is completed to complete the skin trimming. The alignment assembly positioning member 230 has the same nature and function as the wall panel assembly positioning member 140 in the foregoing embodiments, and both are used to position and fix the side wall panel. As Figure 3 shown in Figure 3 , the alignment assembly positioning member 230 includes a belt plate locator 231, a general assembly plate frame locator 232, a wall panel limit block 233, and a radar frame locator 234.

[0041] In this embodiment, the belt plate locator 231 is installed on the left skin trimming clamping plate 222 and is used to accurately position the belt plate parts on the frustum-shaped nose assembly to ensure the accurate connection position of the belt plate with components such as the wall panel and the plate frame.

[0042] The general assembly plate frame locator 232 is installed on the support frame 221. By grasping the tooling positioning holes on the wall panel assembly and cooperating with the wall panel limit block 233, the end face positioning of the wall panel assembly is completed.

[0043] The wall panel limit block 233 is installed on the second installation frame 211 and cooperates with the general assembly plate frame locator 232 to restrict the end face position of the wall panel assembly and prevent deviation during the assembly process.

[0044] The radar frame locator 234 is installed on the auxiliary frame 212 and can accurately fix the position of the radar frame to ensure the alignment accuracy of the radar frame with the nose structure.

[0045] Similarly, a number of general assembly jig framework leveling supports 240 are also provided at the bottom of the general assembly jig framework 210. For example, they are provided at the bottom of the second assembly base 201 as shown in Figure 3 or Figure 4 .

[0046] The vertical assembly jig system of the present invention can achieve the phased and precise assembly of the frustum-shaped nose of a large aircraft through the panel assembly component 100 and the general assembly component 200. For example, the panel assembly component 100 used in the pre-assembly process can form the side wall panels of the nose separately through a vertical frame structure, and further achieve the accurate assembly of the skin and the framework through modular positioning parts such as the skin conforming clamping plate 120 and various panel assembly positioning parts 140, ensuring the theoretical shape and internal structure accuracy of the panel assembly; as the general assembly component 200 used in the subsequent assembly process undertakes the alignment and integration of double-sided or multi-sided wall panels, uses the side wall panel mounting parts 220 to achieve the precise docking of multiple side wall panels, and can complete the final shaping of some side wall panels by adjusting the structural form of the side wall panel mounting parts 220. The two jig components operate in stages, not only meeting the requirements of the forming accuracy of the side wall panels, but also achieving the effect of consistent double-sided alignment, forming a complete assembly process, and solving the problem that the assembly accuracy and efficiency cannot be satisfied simultaneously in large-scale assembly processes such as the synchronous installation of the cockpit component and the nose component used in traditional integrated jigs; on the other hand, whether it is the pre-assembly or subsequent work of the jig system of the present invention, based on the vertical design of the assembly component, it can greatly reduce the space occupied by the assembly, improve the utilization rate of the operation space, and also effectively avoid the possible human damage to the product in the horizontal assembly method, improving the quality of the assembled product.

[0047] The specific embodiments of the invention have been described in detail above, but they are only examples, and the present invention is not limited to the specific embodiments described above. For those skilled in the art, any equivalent modification or substitution of the invention is also within the scope of the present invention. Therefore, all equal transformations, modifications, improvements, etc. made without departing from the spirit and principle of the present invention should be covered within the scope of the present invention.

Claims

1. A vertical assembly tooling system for the frustum-shaped nose of a large aircraft, characterized in that, Comprising: A panel assembly component for assembling the side panels of the frustum-shaped nose of the large aircraft, including a first assembly base, a panel tooling skeleton, a skin conformal clamping plate, a skin bandage compressor, and panel assembly positioning parts; wherein, the side panel includes a frame part and a skin part. The panel tooling skeleton is vertically arranged on the first assembly base. The skin conformal clamping plate is horizontally and parallelly installed on the panel tooling skeleton, including at least two layers, and the outer edge of each layer is configured with the arc of the frustum circumferential surface. At least two skin bandage compressors are installed along the edge of the first assembly base, and apply tension to the skin through the bandage to make the skin closely adhere to the skin conformal clamping plate. A number of panel assembly positioning parts are configured and respectively installed on the skin conformal clamping plate and the panel tooling skeleton to respectively fix the frame part and the skin part. A general assembly component for general assembly of a plurality of the assembled side panels in alignment, including a second assembly base, a general assembly tooling skeleton, side panel mounting parts, and alignment assembly positioning parts; wherein, The general assembly tooling skeleton is vertically arranged on the second assembly base. At least two groups of side panel mounting parts are respectively configured on both sides of the general assembly tooling skeleton for installing two side panels with open ends in alignment. A number of alignment assembly positioning parts are configured and respectively installed on the general assembly tooling skeleton and the side panel mounting parts to fix the assembled side panels.

2. The vertical assembly tooling system according to claim 1, wherein The panel tooling skeleton includes: A first installation frame, which is installed on the first assembly base in the form of a frustum contour. A truss, which is installed on the axial direction of the frustum contour of the first installation frame.

3. The vertical assembly tooling system according to claim 2, wherein, The panel assembly positioning parts include a frame angle section locator, a frame cross beam web block, a frame cross beam end face block, a connection joint locator, a panel frame locator, and a stringer locator; wherein, The frame angle section locators are symmetrically installed on the first installation frame. The frame cross beam web blocks are symmetrically installed at the ends of each layer of skin conformal clamping plate. The frame cross beam end face blocks are symmetrically installed on one side of the first installation frame close to the first assembly base. The connection joint locator is installed on the first assembly base. The panel frame locators are installed on each layer of skin conformal clamping plate. The stringer locators are installed on the truss.

4. The vertical assembly tooling system according to claim 2, characterized in that, The panel assembly positioning parts further include a skin lug locator, which is installed on the first assembly base.

5. The vertical assembly tooling system according to claim 2, characterized in that, Two or more groups of the panel assembly components are configured on the first assembly base.

6. The vertical assembly tooling system according to claim 1, wherein, The general assembly tooling skeleton includes a second installation frame and an auxiliary frame. The second installation frame is installed on the second assembly base in the form of a frustum contour. The auxiliary frame is installed on the second assembly base and is connected to the second installation frame.

7. The vertical assembly tooling system according to claim 6, wherein Each group of side panel mounting parts includes a support frame and a skin trimming clamping plate, and the skin trimming clamping plate is fixed on the second assembly base through the support frame.

8. The vertical assembly tooling system according to claim 7, characterized in that, The skin trimming clamping plate is arranged at intervals in a segmented form and / or in a whole-segment form.

9. The vertical assembly tooling system according to claim 7, characterized in that The involute assembly locator includes a strip locator, a panel frame locator, a panel limit stop, and a radar frame locator; among them, the strip locator is installed on the skin support pallet; the panel frame locator is installed on the support frame; the panel limit stop is installed on the second installation frame; the radar frame locator is installed on the auxiliary frame.

10. The vertical assembly tooling system according to claim 1, characterized in that, A number of skeleton leveling supports are provided at the bottom of the panel tooling skeleton and / or the general assembly tooling skeleton.

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