A telescopic card device for fuselage assembly
Patent Information
- Application Number
- CN202522076411.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-26
- Publication Date
- 2026-09-18
- Estimated Expiration
- 2035-09-26
AI Technical Summary
但是，在飞机机身装配中，传统卡板工装多为固定式结构，特别是在机身内保型工装上，其卡板数量很多，而且会遮挡制孔铆接区域，非常影响操作人员的工作以及产品装配
本实用新型通过卡板、直线导轨、安装板、定位销和定位销座的设置，达到了便于蒙皮制孔铆接时，进行避让的作用，在使用过程中，松开定位销，卡板可以沿直线导轨方向进行移动，移动至缩回位置，通过定位销进行定位固定，避让该部位蒙皮的制孔铆接空间；制孔铆接工作完成后，松开定位销，卡板沿直线导轨方向进行移动，移动至伸出位置，再通过定位销进行定位固定，对蒙皮进行保形支撑。
Smart Images
Figure CN224767029U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft manufacturing and assembly technology, and more specifically, it relates to a telescopic clamping device for fuselage assembly. Background Technology
[0002] Conformal fixtures are critical tools in aerospace manufacturing used to ensure that aircraft components maintain the shape, size, and positional relationships required by design during assembly. Conformal fixtures use rigid or flexible support structures to fix parts, preventing deformation caused by gravity, residual stress, or external loads, and ensuring that components strictly conform to their design geometry during assembly.
[0003] A clamping plate is a component structure in aircraft assembly tooling, typically made of aluminum alloy. The clamping plate directly contacts the outer or inner surfaces of the aircraft skin, and multiple clamping plates are used in combination to ensure the aircraft's shape. However, in aircraft fuselage assembly, traditional clamping plate tooling is mostly a fixed structure, especially in fuselage internal conformal tooling, where the number of clamping plates is large, and they can obstruct the riveting and drilling areas, significantly impacting operator work and product assembly. Utility Model Content
[0004] In view of the problems existing in the prior art, this utility model provides a telescopic clamping plate device for fuselage assembly to solve the technical problems mentioned in the background art.
[0005] To achieve the above objectives, this utility model provides the following technical solution: a telescopic clamping plate device for machine body assembly, comprising a clamping plate, a mounting plate, a positioning pin, and a linear guide rail. The clamping plate is positioned and connected to the mounting plate via the positioning pin. The positioning pin is connected to the clamping plate. A measuring bushing is provided on the clamping plate. The clamping plate is connected to the mounting plate via the linear guide rail.
[0006] The present invention is further configured such that two limiting blocks are installed at both ends of the linear guide rail.
[0007] The present invention is further provided that the mounting plate is provided with a positioning pin seat that cooperates with the pin.
[0008] The present invention is further configured such that there are two of each of the pin and the positioning pin seat.
[0009] The present invention is further configured to include a conformal tooling frame and a fuselage skin, wherein the mounting plate is connected to the conformal tooling frame, the clamping plate supports the fuselage skin from the inside, and the curved surface of the clamping plate in contact with the fuselage skin is CNC machined according to the profile of the fuselage skin.
[0010] Compared with the prior art, this utility model provides a telescopic clamping plate device for fuselage assembly, which has the following advantages: This utility model, through the arrangement of a clamping plate, linear guide rail, mounting plate, positioning pin, and positioning pin seat, achieves the function of facilitating avoidance during the drilling and riveting of the skin. During use, the positioning pin is released, and the clamping plate can move along the linear guide rail to the retracted position, where it is positioned and fixed by the positioning pin, avoiding the drilling and riveting space of the skin in that part. After the drilling and riveting work is completed, the positioning pin is released, and the clamping plate moves along the linear guide rail to the extended position, where it is again positioned and fixed by the positioning pin, providing shape-preserving support for the skin. Attached Figure Description
[0011] Figure 1 This is a front view of the present utility model; Figure 2 This is a side view of the present invention; Figure 3 This is an axial view of the present invention.
[0012] In the diagram: 1. Clamping plate; 2. Mounting plate; 3. Positioning pin; 4. Measuring bushing; 5. Limiting block; 6. Positioning pin seat; 7. Linear guide rail; 8. Conformal tooling frame; 9. Machine body skin. Detailed Implementation
[0013] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.
[0014] It should be noted that, unless otherwise specified, all technical and scientific terms used in this application have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains.
[0015] In this utility model, unless otherwise stated, the orientations used, such as "up" and "down", usually refer to the direction shown in the accompanying drawings, or to the vertical, perpendicular, or gravitational direction; similarly, for ease of understanding and description, "left" and "right" usually refer to the left and right shown in the accompanying drawings; "inner" and "outer" refer to the inner and outer contours of each component itself, but the above directional terms are not used to limit this utility model.
[0016] Please see Figures 1-3 A telescopic clamping plate device for fuselage assembly is connected to a conformal tooling frame 8 via an mounting plate 2 and fixed on the conformal tooling frame 8. The clamping plate 1 supports the fuselage skin 9 from the inside. The curved surface of the clamping plate 1 in contact with the fuselage skin 9 is CNC machined according to the profile of the fuselage skin 9, which plays a role in conformal support for the fuselage skin 9.
[0017] The clamping plate 1 is equipped with three measuring bushings 4 for mounting the target ball of the laser tracker. The laser tracker measures and determines the position of the clamping plate 1 within the conformal tooling coordinate system, and adjusts the clamping plate 1 to within the tolerance range. The clamping plate 1 is movably connected to the mounting plate 2 via a linear guide rail 7, which is installed radially along the conformal surface of the clamping plate. The clamping plate 1 can move along the linear guide rail 7 to achieve a collision avoidance function. Moreover, two limit blocks 5 are installed at both ends of the linear guide rail to limit the movement range of the clamping plate 1 and prevent the slider of the linear guide rail 7 from disengaging from the guide rail. The clamping plate 1 is positioned to the mounting plate 2 via positioning pins 3. The positioning pins 3 are installed on the clamping plate 1, and the positioning pin seats 6 are installed on the mounting plate 2. The clamping plate 1 has two positions: an extended position and a retracted position. The two positions are achieved by the cooperation of the two positioning pin seats 6 and the positioning pins 3.
[0018] When the fuselage skin 9 needs to be drilled and riveted, the clamping plate 1 is retracted to leave room for drilling and riveting operations. After the drilling and riveting work is completed, the clamping plate 1 is extended to continue to maintain the shape of the skin.
[0019] Of all the solutions mentioned above, those involving connections between two components can be selected based on the actual situation, such as welding, bolt and nut connection, bolt or screw connection, or other well-known connection methods. These will not be elaborated on here. For all the fixed connections mentioned above, welding is the preferred option. In all the solutions mentioned above, the operation of electrical components, unless otherwise specified, is controlled by a controller. Since the devices matched with the controllers are common devices, their control principles and wiring connections are existing, well-known, and mature technologies, and their specific circuit structures will not be described in detail here. The specific models and specifications of the electrical components involved in this solution need to be selected and determined according to the actual specifications of the device. The specific selection and calculation methods adopt existing technologies in this field, and therefore will not be described in detail. Of all the solutions mentioned above, those involving motors can be combined with reducers if necessary. The connection structure and working principle between the motor and the reducer are existing known technologies and will not be described in detail in this utility model. Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A telescoping caul plate device for fuselage assembly, characterized by, It includes a clamping plate, a mounting plate, a positioning pin, and a linear guide rail. The clamping plate is connected to the mounting plate through the positioning pin. The positioning pin is connected to the clamping plate. A measuring bushing is provided on the clamping plate. The clamping plate is connected to the mounting plate through the linear guide rail.
2. The telescoping caul plate assembly of claim 1, wherein: Two limit blocks are installed at both ends of the linear guide rail.
3. A telescoping caul plate assembly for use in fuselage assembly according to claim 2, wherein: The mounting plate is provided with a positioning pin seat that cooperates with the pin.
4. A telescoping caul plate assembly for use in fuselage assembly according to claim 3, wherein: Two of each are provided for the pin and the locating pin seat.
5. The telescoping caul plate assembly of claim 3, wherein: It also includes conformal tooling frames and fuselage skin, with mounting plates connected to the conformal tooling frames and clamping plates supporting the fuselage skin from the inside.