Aircraft skin drilling clamp

Abstract

The utility model discloses an aircraft skin drilling clamp, and relates to the technical field of aircraft skin drilling, the aircraft skin drilling clamp comprises two groups of front stand columns which are symmetrically arranged left and right, a lower mounting beam is arranged between the two groups of front stand columns, and a plurality of groups of mounting blocks are arranged on the rear side of the lower mounting beam; arc-shaped mounting strips are arranged on the rear sides of the multiple sets of mounting blocks, and the other set of mounting blocks are arranged at the upper ends of the arc-shaped mounting strips. According to the aircraft skin drilling clamp, the arc-shaped mounting strip is arranged, for the arc-shaped aircraft skin, it can be guaranteed that the arc-shaped aircraft skin is stably placed to the maximum extent through the arc-shaped mounting strip, and the aircraft skin is clamped through the arc-shaped mounting strip and the two sets of mounting blocks; in addition, the parallel and level rods are arranged among the multiple sets of arc-shaped mounting strips, the parallel and level rods can guarantee that the horizontal position of the aircraft skin clamped on the clamp is kept consistent, the arc-shaped aircraft skin is clamped, and therefore it can be guaranteed that errors do not occur to the maximum extent during punching.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft skin drilling, in particular to an aircraft skin drilling fixture. Background Technique

[0002] Previously, due to the limitations of assembly and sheet metal part manufacturing technology levels, aircraft skin parts were often manufactured in a large-margin and on-site assembly repair mode, resulting in a long aircraft manufacturing cycle. With the rapid development of aviation manufacturing technology, the gradual application of digital and pulsating assembly, and the shortening of the aircraft manufacturing cycle, the manufacturing requirements for aircraft skin parts are getting higher and higher. To further improve the assembly efficiency, the manufacturing method of aircraft skin parts is gradually changing towards precise machining and rapid positioning. Among them, the method of adding positioning holes to parts is the most common, which has the advantages of strong operability, small modification of existing tooling, convenience, reliability, and can greatly reduce the part positioning time during assembly.

[0003] When drilling the existing aircraft skin, for the drilling of the aircraft skin with a curved surface structure, most of them are completed manually. Workers need to drill and rivet in different directions. However, without support, the drilling operation will inevitably damage the aircraft skin. In addition, most of them drill multiple times in different places and proceed step by step, which is extremely cumbersome and brings certain adverse effects to the using process. To solve the deficiencies of the existing technology, we propose an aircraft skin drilling fixture. Content of the Utility Model

[0004] The main purpose of the utility model is to provide an aircraft skin drilling fixture, which can effectively solve the problems in the background technique.

[0005] To achieve the above purpose, the technical solution adopted by the utility model is as follows:

[0006] An aircraft skin drilling fixture includes front columns. There are two groups of front columns symmetrically arranged on the left and right. A lower installation beam is arranged between the two groups of front columns. A plurality of installation blocks are arranged at the rear side of the lower installation beam. Arc-shaped installation strips are arranged at the rear sides of the plurality of installation blocks. Another group of installation blocks is arranged at the upper end of the arc-shaped installation strips. An upper installation beam is arranged at the front end of the other group of installation blocks. A plurality of leveling rods are arranged inside the plurality of arc-shaped installation strips. A plurality of installation bolts are arranged inside the plurality of installation blocks. Fixed bolts are arranged inside the arc-shaped installation strips.

[0007] Preferably, a fixed crossbeam is arranged at the rear side of multiple groups of the arc-shaped mounting strips. Rear columns are arranged on both sides of the fixed crossbeam. Mounting plates are arranged at the lower ends of the front column and the rear column. First mounting holes are arranged on the inner sides of multiple groups of the mounting plates. Multiple groups of second mounting holes are arranged on the inner side of the front column. Multiple groups of second mounting holes are arranged on the inner side of the rear column. Fastening bolts are arranged between multiple groups of the arc-shaped mounting strips and the upper and lower mounting blocks. A mounting thread is arranged at the front end of the upper fastening bolt. A knob is arranged at the front end of the mounting thread. A detachable rotating rod is arranged inside the upper fastening bolt. A rotating cylinder is arranged at the front end of the lower fastening bolt.

[0008] Preferably, through holes are arranged on the inner side of the lower mounting beam. Multiple mounting bolts are detachably connected to the lower mounting beam through the through holes of the lower mounting beam. Through holes are arranged on the inner sides of multiple groups of the mounting blocks. Multiple groups of mounting bolts are detachably connected to the mounting blocks through the through holes of the mounting blocks. Multiple groups of the mounting blocks are detachably connected to the lower mounting beam through the mounting bolts.

[0009] Preferably, through holes are arranged on the inner sides of multiple groups of the arc-shaped mounting strips. The fixing bolts are detachably connected to the arc-shaped mounting strips through the through holes of the arc-shaped mounting strips. Through holes are arranged on the inner side of the fixed crossbeam. The fixing bolts are detachably connected to the fixed crossbeam through the through holes of the fixed crossbeam. Multiple groups of the arc-shaped mounting strips are detachably connected to the fixed crossbeam through the fixing bolts. The flush rod is detachably connected to the arc-shaped mounting strips through the through holes of the arc-shaped mounting strips.

[0010] Preferably, the lower mounting beam is detachably connected to the front column through the second mounting holes. The upper mounting beam is detachably connected to the front column through the second mounting holes. The fastening bolts are detachably connected to the arc-shaped mounting strips through the through holes of the arc-shaped mounting strips. Through holes are arranged inside the fastening bolts. The detachable rotating rod is detachably connected to the fastening bolts through the through holes of the fastening bolts. Through holes are arranged on the inner side of the rotating cylinder. The detachable rotating rod is detachably connected to the rotating cylinder through the through holes of the rotating cylinder.

[0011] Preferably, a threaded hole is arranged on the inner side of the knob. The mounting thread is detachably connected to the knob through the threaded hole of the knob. The fastening bolt is detachably connected to the knob through the mounting thread. A threaded hole is arranged on the inner side of the rotating cylinder. The mounting thread is detachably connected to the rotating cylinder through the threaded hole of the rotating cylinder. The fastening bolt is detachably connected to the rotating cylinder through the mounting thread.

[0012] Advantageous Effects

[0013] Compared with the prior art, the present utility model has the following advantageous effects:

[0014] 1. In the present utility model, through the provided arc-shaped mounting strips, for the arc-shaped aircraft skin, the arc-shaped mounting strips can ensure the stable placement of the arc-shaped aircraft skin to the greatest extent. And the aircraft skin is clamped by the arc-shaped mounting strips and two groups of mounting blocks. In addition, a leveling rod is arranged between multiple groups of arc-shaped mounting strips, and the leveling rod can ensure that the horizontal positions of the aircraft skins clamped on this fixture are consistent, clamping the arc-shaped aircraft skin. In this way, when drilling holes, errors can be minimized to the greatest extent.

[0015] 2. In the present utility model, through the provided front column and rear column, the aircraft skin is installed inside the fixture between the front column and the rear column. Only through the lower mounting beam, the fixed cross beam and the upper mounting beam, the fixture is connected and fixed, ensuring the maximum exposure of the drilling space. In this way, the entire drilling operation space can accommodate more workers. When drilling holes simultaneously, there is no need to divide into multiple steps, greatly reducing the labor for drilling and streamlining the assembly process steps. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is the overall structural schematic diagram of the present utility model;

[0017] Figure 2 is the structural schematic diagram of the front column and rear column of the present utility model;

[0018] Figure 3 is the structural schematic diagram of the fixture of the present utility model;

[0019] Figure 4 is the structural schematic diagram of the fastening bolt of the present utility model;

[0020] Figure 5 is the schematic diagram of the knob of the present utility model;

[0021] Figure 6 is the structural schematic diagram of the rotating cylinder of the present utility model.

[0022] In the figure: 1. Front column; 2. Mounting plate; 3. Lower mounting beam; 4. Rear column; 5. Fixed cross beam; 6. Upper mounting beam; 7. Arc-shaped mounting strip; 8. Fixed bolt; 9. Mounting block; 10. Mounting bolt; 11. Fastening bolt; 12. Removable rotating rod; 13. Mounting thread; 14. Knob; 15. Rotating cylinder; 16. Leveling rod; 17. First mounting hole; 18. Second mounting hole. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] In order to make the technical means, creative features, achieved purposes and effects of the present utility model easy to understand, the present utility model will be further described below in conjunction with specific embodiments.

[0024] Such as Figure 1 、 2, as shown in FIGS. 3, an aircraft skin drilling fixture, installs the aircraft skin into the gap between the arc-shaped mounting strip 7 and the upper and lower groups of mounting blocks 9, and is fixedly connected to the lower mounting beam 3 and the upper mounting beam 6 through multiple groups of mounting bolts 10 respectively. In this way, by moving the position of the rear column 4, the gap between the arc-shaped mounting strip 7 and the mounting bolts 10 can be adjusted, which can accommodate aircraft skins of different thicknesses, and the arc-shaped mounting strip 7 can protect the arc-shaped aircraft skin from being damaged during the drilling process.

[0025] As Figures 3-6 shown, for an aircraft skin drilling fixture, by rotating the detachable rotating rod 12 or the knob 14, the distance between the arc-shaped mounting strip 7 and the mounting block 9 provided at the upper end can be adjusted. By inserting the detachable rotating rod 12 into the inside of the rotating cylinder 15 or the lower fastening bolt 11, the distance between the arc-shaped mounting strip 7 and the mounting block 9 provided at the lower end can be adjusted. For aircraft skins with complex shapes, the clamping thickness can be adjusted separately, which can adapt to more different processes to facilitate better drilling operations.

[0026] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft skin drilling fixture, including a front column (1), characterized in that: There are two groups of the front columns (1) symmetrically arranged left and right. A lower mounting beam (3) is arranged between the two groups of the front columns (1). A plurality of mounting blocks (9) are arranged at the rear side of the lower mounting beam (3). Arc-shaped mounting strips (7) are arranged at the rear sides of the plurality of mounting blocks (9). Another group of mounting blocks (9) is arranged at the upper end of the arc-shaped mounting strips (7). An upper mounting beam (6) is arranged at the front end of the other group of mounting blocks (9). A flush rod (16) is arranged inside the plurality of arc-shaped mounting strips (7). A plurality of mounting bolts (10) are arranged inside the plurality of mounting blocks (9). A fixing bolt (8) is arranged inside the arc-shaped mounting strips (7).

2. The aircraft skin drilling fixture according to claim 1, wherein: A fixing cross beam (5) is arranged at the rear sides of the plurality of arc-shaped mounting strips (7). Rear columns (4) are arranged at both sides of the fixing cross beam (5). Mounting plates (2) are arranged at the lower ends of the front columns (1) and the rear columns (4). First mounting holes (17) are arranged inside the plurality of mounting plates (2). A plurality of second mounting holes (18) are arranged inside the front columns (1). A plurality of second mounting holes (18) are arranged inside the rear columns (4). Fastening bolts (11) are arranged between the plurality of arc-shaped mounting strips (7) and the upper and lower two groups of mounting blocks (9). Mounting threads (13) are arranged at the front end parts of the upper fastening bolts (11). Knobs (14) are arranged at the front ends of the mounting threads (13). Removable rotating rods (12) are arranged inside the upper fastening bolts (11). Rotating cylinders (15) are arranged at the front ends of the lower fastening bolts (11).

3. The aircraft skin drilling fixture according to claim 1, characterized in that: Through holes are arranged inside the lower mounting beam (3). The plurality of mounting bolts (10) are detachably connected to the lower mounting beam (3) through the through holes of the lower mounting beam (3). Through holes are arranged inside the plurality of mounting blocks (9). The plurality of mounting bolts (10) are detachably connected to the mounting blocks (9) through the through holes of the mounting blocks (9). The plurality of mounting blocks (9) are detachably connected to the lower mounting beam (3) through the mounting bolts (10).

4. The aircraft skin drilling fixture according to claim 2, characterized in that: Through holes are arranged inside the plurality of arc-shaped mounting strips (7). The fixing bolts (8) are detachably connected to the arc-shaped mounting strips (7) through the through holes of the arc-shaped mounting strips (7). Through holes are arranged inside the fixing cross beam (5). The fixing bolts (8) are detachably connected to the fixing cross beam (5) through the through holes of the fixing cross beam (5). The plurality of arc-shaped mounting strips (7) are detachably connected to the fixing cross beam (5) through the fixing bolts (8). The flush rod (16) is detachably connected to the arc-shaped mounting strips (7) through the through holes of the arc-shaped mounting strips (7).

5. The aircraft skin drilling fixture according to claim 2, wherein: The lower mounting beam (3) is detachably connected to the front column (1) through the second mounting hole (18), the upper mounting beam (6) is detachably connected to the front column (1) through the second mounting hole (18), the fastening bolt (11) is detachably connected to the arc-shaped mounting strip (7) through the through hole of the arc-shaped mounting strip (7), a through hole is provided inside the fastening bolt (11), the detachable rotating rod (12) is detachably connected to the fastening bolt (11) through the through hole of the fastening bolt (11), a through hole is provided inside the rotating cylinder (15), and the detachable rotating rod (12) is detachably connected to the rotating cylinder (15) through the through hole of the rotating cylinder (15).

6. The aircraft skin drilling fixture according to claim 2, characterized in that: A threaded hole is provided inside the knob (14), the mounting thread (13) is detachably connected to the knob (14) through the threaded hole of the knob (14), the fastening bolt (11) is detachably connected to the knob (14) through the mounting thread (13), a threaded hole is provided inside the rotating cylinder (15), the mounting thread (13) is detachably connected to the rotating cylinder (15) through the threaded hole of the rotating cylinder (15), and the fastening bolt (11) is detachably connected to the rotating cylinder (15) through the mounting thread (13).

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