A left front collar assembly jig
Patent Information
- Application Number
- CN202522619399.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-10
- Publication Date
- 2026-10-20
- Estimated Expiration
- 2035-12-10
AI Technical Summary
[0004]本实用新型的目的在于提供一种左前襟装配型架，通过设置固定部，解决了现有的装配型架其操作复杂，因此将导致难以快速完成对工件的固定，同时，复杂的操作，还会影响其加工精度，最终降低整体的生产效率的问题
1、通过设置固定部，使用时，先水平调平装配型架，通过卡板定位飞机上翼面，利用肋定位卡板固定加强筋及肋条，再通过定位组件的定位杆支撑前襟翼后缘并制连接孔，快速完成前襟关键部件定位固定，保障安装准确性，为后续装配奠定基础、提升效率；
Smart Images
Figure CN224868612U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of assembly frame technology, and in particular relates to a left front flap assembly frame. Background Technology
[0002] The left front flap assembly jig is a specialized tooling equipment used in the assembly of the left front flap of an aircraft fuselage. Its core function is to accurately fix the skin, frame, connectors and other components of the left front flap through preset positioning references, clamping mechanisms and support structures, to ensure that the relative position, dimensional accuracy and assembly tolerance of each component meet the design requirements, and at the same time provide stable support for the assembly operation, reduce assembly errors, and improve assembly efficiency and consistency. It is a key process equipment to ensure the assembly quality of the left front flap and subsequent aerodynamic performance.
[0003] However, the existing assembly jigs are complex to operate, which makes it difficult to quickly fix the workpieces. At the same time, the complex operation will also affect the processing accuracy and ultimately reduce the overall production efficiency. Utility Model Content
[0004] The purpose of this utility model is to provide a left front flap assembly frame. By setting a fixing part, it solves the problem that the existing assembly frames are complicated to operate, which makes it difficult to quickly fix the workpiece. At the same time, the complicated operation will also affect the processing accuracy and ultimately reduce the overall production efficiency.
[0005] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution: This utility model relates to a left front flap assembly frame, comprising an assembly frame and a rectangular frame disposed on the top of the assembly frame, and further comprising: a fixing part, wherein a plurality of fixing parts are disposed on the assembly frame; a configuration part, wherein the configuration part is disposed on the assembly frame; the fixing part includes a fixing component, wherein the fixing component is mounted on the assembly frame; and a locking component, wherein the locking component is mounted on the assembly frame; the fixing component includes top end supports fixedly connected to both sides of the assembly frame, wherein each of the two top end supports is hinged to a locking plate, and both sides of the assembly frame are fixedly connected to bottom end supports, wherein the ends of the two locking plates away from the top end supports are hinged to the two bottom end supports, and the two locking plates are provided with limiting components located on the left side of the two locking plates.
[0006] Furthermore, the configuration unit includes a positioning component, wherein a plurality of positioning components are provided, and all of the plurality of positioning components are disposed on the assembly frame; and a configuration component, wherein the configuration component is disposed on the assembly frame.
[0007] Furthermore, the locking assembly includes locking fastening assemblies disposed on both sides of the assembly frame. A mounting base is fixedly connected to the assembly frame. An adjusting base is rotatably connected to the mounting base. A pin is slidably connected to the mounting base. The left end of the pin extends into the adjusting base. Two rib positioning plates are disposed on the adjusting base. A limiting component is disposed on the adjusting base. The outer wall of the pin is slidably connected to the adjusting base. The limiting component includes two pins slidably connected to the adjusting base. Both pins slid through the two rib positioning plates and the adjusting base. The outer walls of both pins slidably connect to the two rib positioning plates and the adjusting base.
[0008] Furthermore, the positioning component includes a second mounting base fixedly connected to the assembly frame, an second adjusting base is provided on the right side of the second mounting base, a positioning rod is threadedly connected to the top of the second adjusting base, and a second limiting member is provided on the second mounting base. The second limiting member includes two third pins fixedly connected to the two second mounting bases, and the right ends of the two third pins extend into the second adjusting base.
[0009] Furthermore, the configuration component includes several tool ball mounting seats on the front side of the assembly frame, and skin positioning plate assemblies are provided on both sides of the assembly frame.
[0010] This utility model has the following beneficial effects: 1. By setting up a fixing part, when in use, first level the assembly frame, position the upper wing surface of the aircraft with the clamp plate, fix the reinforcing ribs and ribs with the rib positioning clamp plate, and then support the trailing edge of the front flap with the positioning rod of the positioning component and make the connection hole, quickly complete the positioning and fixing of the key components of the front flap, ensure the accuracy of installation, lay the foundation for subsequent assembly and improve efficiency. 2. By setting up the configuration section, in subsequent operations, the laser positioning tracker on the tool ball mounting base is used to detect the installation position of the parts. After the rivets are fixed, the front edge and bottom end support are installed using the skin positioning plate assembly. The installation accuracy is checked again by the laser positioning tracker. The joints and support positioning holes at the connection between the positioning end and the body are checked to ensure that the relative position with the docking hole of the body is up to standard. Then the rivets are locked. Next, the lower wing surface is positioned by the clamping plate. After inspection and approval, the rivet fixing is completed. Finally, the clamping plate and locking fixing assembly are opened, the limit assembly and positioning assembly are loosened and removed, and the flap is lifted out of the frame through the preset lifting point. The whole set of settings realizes the precise positioning, efficient assembly and convenient unloading of each component of the left front flap, taking into account both assembly accuracy and production efficiency.
[0011] Of course, any product implementing this utility model does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description
[0012] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0013] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a partial cross-sectional view of the fixing part of this utility model; Figure 3 This is a partial cross-sectional view of the configuration part of this utility model; Figure 4 This utility model Figure 2 A magnified structural diagram of A in the middle; Figure 5 This utility model Figure 3 A magnified structural diagram of B in the diagram; Figure 6 This utility model Figure 3 A magnified structural diagram of C; Figure 7 This utility model Figure 2 A magnified structural diagram of D in the diagram.
[0014] The attached diagram lists the components represented by each number as follows: 111. Assembly frame; 112. Rectangular frame; 2. Fixing part; 21. Fixing component; 211. Top end support; 212. Clamping plate; 213. Bottom end support; 214. Limiting component; 22. Locking component; 221. Locking and fixing component; 222. Mounting seat one; 223. Adjusting seat one; 224. Pin one; 225. Rib positioning clamping plate; 226. Pin two; 3. Configuration part; 31. Positioning component; 311. Mounting seat two; 312. Adjusting seat two; 313. Pin three; 314. Positioning rod; 32. Configuration component; 321. Tool ball mounting seat; 322. Skin positioning plate assembly. Detailed Implementation
[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0016] Please see Figure 1-7As shown, this utility model is a left front flap assembly frame, including an assembly frame 111 and a rectangular frame 112 disposed on the top of the assembly frame 111, and further including: a fixing part 2, of which a plurality of fixing parts 2 are disposed on the assembly frame 111; and a configuration part 3, which is disposed on the assembly frame 111.
[0017] The fixing part 2 includes a fixing component 21, which is mounted on the assembly frame 111; and a locking component 22, which is also mounted on the assembly frame 111. The fixing component 21 includes top end supports 211 fixedly connected to both sides of the assembly frame 111, with a locking plate 212 hinged to each of the two top end supports 211. Bottom end supports 213 are fixedly connected to both sides of the assembly frame 111. The ends of the two locking plates 212 away from the top end supports 211 are connected to the two bottom end supports. 213 is hinged, and two clamping plates 212 are provided with limit components 214. The limit components 214 are located on the left side of the two clamping plates 212. The locking component 22 includes locking and fixing components 221 provided on both sides of the assembly frame 111. A mounting base 222 is fixedly connected to the assembly frame 111. An adjusting base 223 is rotatably connected to the mounting base 222. A pin 224 is slidably connected to the mounting base 222. The left end of the pin 224 extends into the adjusting base 223. The adjusting base 223 is provided with... The assembly includes two rib positioning plates 225. A limiting component 1 is provided on the adjusting base 223. The outer wall of the pin 224 is slidably connected to the adjusting base 223. The limiting component 1 includes two pins 226 slidably connected to the adjusting base 223. Both pins 226 penetrate the two rib positioning plates 225 and the adjusting base 223. The outer walls of both pins 226 are slidably connected to the two rib positioning plates 225 and the adjusting base 223. By providing the fixing part 2, in use, the assembly frame 111 is first... The aircraft's upper wing surface is positioned using the leveling plate 212, and the aircraft's reinforcing ribs and slats are fixed using the rib positioning plate 225. Finally, the positioning rod 314 of the positioning assembly supports the trailing edge of the front flap and creates corresponding connection holes. This allows for the rapid positioning and fixing of key components of the aircraft's front flap, ensuring the accuracy of the installation positions of each component. This setup lays a good foundation for subsequent assembly processes and improves assembly efficiency.
[0018] The configuration unit 3 includes a positioning component 31, of which several are provided, all mounted on the assembly frame 111; and a configuration component 32, also mounted on the assembly frame 111. The positioning components 31 include a mounting base 311 fixedly connected to the assembly frame 111, an adjusting base 312 on the right side of the mounting base 311, and a positioning rod 314 threaded to the top of the adjusting base 312. A limiting element 314 is provided on the mounting base 311. The configuration component 32 includes several tool ball mounting bases 321 on the front of the assembly frame 111. Skin positioning plate assemblies 322 are provided on both sides of the assembly frame 111. The limiting element 314 includes two pins 313 fixedly connected to two mounting bases 311, with the right ends of both pins 313 extending into the adjusting base 312. The configuration component 32 is configured with several tool ball mounting bases 321 on the front side of the assembly frame 111. In section 3, the laser positioning tracker installed on the tool ball mounting base 321 checks whether the installation position of each part is qualified. After fixing and locking with rivets, the leading edge and bottom end support 213 of the aircraft are installed through the skin positioning plate assembly 322. The installation accuracy of the parts is checked again with the laser positioning tracker, focusing on checking the joint and support positioning hole at the connection between the positioning end and the fuselage to ensure that the relative position of the positioning end and the fuselage docking hole meets the requirements. Then, it is fixed and locked with rivets. Next, the lower wing surface of the aircraft is positioned through the clamping plate 212. After inspection and measurement, the rivet fixing is completed. Finally, the clamping plate 212 and the locking fixing assembly 221 are opened, the limit assembly 214 and the positioning assembly are loosened and removed, and the flap is lifted through the preset lifting point to smoothly remove it from the frame. Through this setting, the precise positioning, efficient assembly and convenient removal of each component of the left front flap of the aircraft can be achieved, ensuring assembly accuracy and production efficiency.
[0019] One specific application of this embodiment is as follows: In use, the assembly jig 111 is first leveled horizontally. The upper wing surface of the aircraft is positioned using the clamping plate 212. Then, the aircraft reinforcing ribs and ribs are fixed using the rib positioning clamping plate 225. Finally, the positioning rod 314 of the positioning assembly supports the trailing edge of the front flap and creates corresponding connection holes. This allows for the rapid positioning and fixing of key components of the aircraft front flap, ensuring the accuracy of the installation positions of each component. This setup provides a good foundation for subsequent assembly processes and improves assembly efficiency. Subsequently, a laser positioning tracker installed on the tool ball mounting base 321 checks whether the installation positions of each part are qualified and uses rivets for fixing. After locking, the leading edge and bottom end support 213 of the aircraft are installed through the skin positioning plate assembly 322. The installation accuracy of the parts is checked again with the help of a laser positioning tracker. The joints and support positioning holes at the connection between the positioning end and the fuselage are checked to ensure that their relative positions with the docking holes of the fuselage meet the requirements. Then, the parts are fixed and locked with rivets. Next, the lower wing surface of the aircraft is positioned through the clamp plate 212. After inspection and measurement, the rivet fixing is completed. Finally, the clamp plate 212 and the locking fastening assembly 221 are opened, the limit assembly 214 and the positioning assembly are released and removed. The flap is lifted through the preset lifting point to make it easy to get off the stand. Through this setting, the precise positioning, efficient assembly and convenient removal of the components of the left front flap of the aircraft can be achieved, ensuring assembly accuracy and production efficiency.
[0020] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.
[0021] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.
Claims
1. A left front flap assembly frame, comprising an assembly frame (111) and a rectangular frame (112) disposed on top of the assembly frame (111), characterized in that, Also includes: Fixing part (2), a plurality of fixing parts (2) are provided, and the plurality of fixing parts (2) are all provided on the assembly frame (111); Configuration unit (3), which is provided on assembly frame (111); The fixing part (2) includes a fixing component (21), which is mounted on the assembly frame (111); as well as Locking assembly (22), said locking assembly (22) is mounted on assembly frame (111); The fixing component (21) includes top end supports (211) fixedly connected to both sides of the assembly frame (111), and each of the two top end supports (211) is hinged with a clamping plate (212). Both sides of the assembly frame (111) are fixedly connected with bottom end supports (213). The ends of the two clamping plates (212) away from the top end supports (211) are hinged to the two bottom end supports (213). Limiting components (214) are provided on the two clamping plates (212). The limiting component (214) is located on the left side of the two card plates (212).
2. The left front flap assembly frame according to claim 1, characterized in that, The configuration unit (3) includes positioning components (31), and a plurality of positioning components (31) are provided, each of which is disposed on an assembly frame (111); and Configuration component (32) is disposed on assembly frame (111).
3. The left front flap assembly frame according to claim 2, characterized in that, The locking component (22) includes a locking fixing component (221) disposed on both sides of the assembly frame (111). A mounting base (222) is fixedly connected to the assembly frame (111). An adjusting base (223) is rotatably connected to the mounting base (222). A pin (224) is slidably connected to the mounting base (222). The left end of the pin (224) extends into the adjusting base (223). Two rib positioning plates (225) are provided on the adjusting base (223). A limit member is provided on the adjusting base (223). The outer wall of the first pin (224) is slidably connected to the first adjusting seat (223).
4. The left front flap assembly frame according to claim 3, characterized in that, The positioning component (31) includes a second mounting seat (311) fixedly connected to the assembly frame (111), an adjustment seat (312) is provided on the right side of the second mounting seat (311), a positioning rod (314) is threadedly connected to the top of the adjustment seat (312), and a limit member (2) is provided on the second mounting seat (311).
5. A left front flap assembly frame according to claim 4, characterized in that, The configuration component (32) is provided on several tool ball mounting seats (321) on the front of the assembly frame (111), and skin positioning plate assemblies (322) are provided on both sides of the assembly frame (111).
6. A left front flap assembly frame according to claim 5, characterized in that, The limiting component includes two pins (226) that are slidably connected to the adjusting seat (223), and both pins (226) pass through the two rib positioning plates (225) and the adjusting seat (223). The outer walls of the two pins (226) are slidably connected to the two rib positioning plates (225) and the adjusting seat (223).
7. A left front flap assembly frame according to claim 6, characterized in that, The limiting member two includes two pins three (313) fixedly connected to two mounting bases two (311), and the right ends of the two pins three (313) extend into the adjusting base two (312).