Aircraft body assembly tool

Abstract

The utility model discloses an aircraft body assembly tool which comprises a base, a framework assembly mechanism and a skin assembly mechanism, the framework assembly mechanism comprises an upper cabin fixing column and a plurality of cantilever positioning columns, and the upper cabin fixing column and the cantilever positioning columns are fixedly installed on the base; the skin assembling mechanism comprises skin mounting frames on the two sides, and sliding blocks are arranged at the bottoms of the skin mounting frames; guide rails are arranged on the two sides of the base, and the skin mounting frame can slide along the guide rails. According to the utility model, the framework assembling mechanism and the skin assembling mechanism are integrated together, so that the interference to the assembling work of the framework can be avoided, trial assembly can be carried out during cementing, the body state before cementing can be simulated, and the body framework assembling efficiency, the outer skin cementing efficiency and the overall assembling quality are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft assembly, in particular to an aircraft body assembly tool. Background Art

[0002] A multi-rotor aircraft is a special unmanned helicopter with three or more rotor cantilevers. The head of each cantilever is fixed to the wing, and an independent motor is installed on the tail. The motor on each cantilever rotates to drive the rotor, thereby generating lift thrust. A multi-rotor aircraft includes a skeleton structure and a skin structure. The skin structure surrounds the skeleton structure to form the fuselage of the aircraft. During assembly, it is necessary to first install the beams and ribs separately, rivet the ribs to the beams through tooling positioning to form the skeleton of the wing, and finally glue the skin to the skeleton composed of the beams and ribs. At present, the skeleton structure has its own set of positioning tooling, and the outer skin also has corresponding assembly tooling. After the two are assembled separately, they need to be put on the shelf for the second time to realize the overall assembly. However, after the outer skin and the skeleton are put on the shelf for the second time, coordination errors may occur, and the number of tooling used in the entire assembly process is large, and the assembly cost is high. Utility Model Content

[0003] In order to solve the above problems, the utility model provides an aircraft body assembly tool, which can realize the overall assembly of the skeleton and the skin, has high assembly efficiency, reduces the number of assembly tools, and saves assembly costs.

[0004] To this end, the technical solution of the utility model is: an aircraft body assembly tool, including a base, a skeleton assembly mechanism and a skin assembly mechanism, the skeleton assembly mechanism includes an upper cabin fixing column and a plurality of cantilever positioning columns, the upper cabin fixing column and the cantilever positioning column are fixedly mounted on the base; the skin assembly mechanism includes skin mounting frames on both sides, and a slider is provided at the bottom of the skin mounting frames; guide rails are provided on both sides of the base, and the skin mounting frames can slide along the guide rails.

[0005] On the basis of the above scheme and as a preferred scheme of the above scheme: skin mounting plates are provided on the opposite sides of the skin mounting frames on both sides, and a plurality of C-shaped positioning clips are provided on the skin mounting plates.

[0006] On the basis of the above scheme and as a preferred scheme of the above scheme: a skeleton positioning clamp and a positioning mounting plate are provided on the side of the skin mounting frame.

[0007] On the basis of the above scheme and as a preferred scheme of the above scheme: a support plate and a positioning pin are provided on the top of the upper cabin body fixing column, the front end of the support plate is a C-shaped structure and is provided with a positioning pin hole, and the positioning pin passes through the positioning pin hole.

[0008] On the basis of the above scheme and as a preferred scheme of the above scheme: a positioning shaft is provided at the top end of the cantilever positioning column, and a locking block is provided above the positioning shaft.

[0009] During assembly, the outer skins on both sides can be installed on the skin mounting plates, and the skin mounting frame can be moved along the guide rail away from the middle skeleton assembly mechanism. The upper cabin body can be placed on the upper cabin body fixing column, and then the cantilever can be installed on the cantilever positioning column, so that the cantilever mounting seat of the upper cabin body is opposite to the cantilever position, and can be accurately positioned and installed; when the skeleton is installed, the skin mounting frame can be pushed to make the outer skin fit the skeleton to simulate the state of the fuselage before gluing. If there is no problem, the fuselage skin can be directly glued to complete the overall assembly of the aircraft body.

[0010] Compared with the prior art, the beneficial effects of the utility model are:

[0011] 1. The frame assembly mechanism and the skin assembly mechanism are integrated together. The skin assembly mechanism is set to a sliding structure, which can not only avoid interference with the frame assembly work, but also allow trial assembly during gluing, simulate the state of the fuselage before gluing, and improve the efficiency of the frame assembly, the gluing efficiency of the outer skin, and the overall assembly quality;

[0012] 2. The skeleton and the outer skin can be assembled in parallel on the same assembly tool, which reduces the number of jigs and jigs, and reduces the manufacturing and assembly costs of the jigs. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The following is a further detailed description of the embodiments of the present invention in conjunction with the accompanying drawings.

[0014] Figure 1 It is a schematic diagram of the structure of the utility model;

[0015] Figure 2 It is a top view of the structure of the utility model;

[0016] Figure 3 This is a structural schematic diagram of the utility model in which the single-side skin mounting frame is in an open state;

[0017] Figure 4 It is a top view of the structure of the single-side skin mounting frame of the utility model in an open state;

[0018] Figure 5 It is a structural schematic diagram of the utility model in an assembled state;

[0019] Figure 6 It is a top view of the structure of the utility model in the assembled state.

[0020] Marked in the figure are: base 1, guide rail 11, upper cabin fixing column 2, support plate 21, positioning pin 22, cantilever positioning column 3, positioning shaft 31, locking block 32, upper cabin 4, cantilever mounting seat 41, cantilever 5, skin mounting frame 6, slider 61, skin mounting plate 62, C-type positioning clamp 63. DETAILED DESCRIPTION

[0021] In the description of the present invention, it should be noted that directional words, such as the terms "center", "lateral (X)", "longitudinal (Y)", "vertical (Z)", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating directions and positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of narrating the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and cannot be understood as limiting the specific protection scope of the present invention.

[0022] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features. Therefore, the definition of "first" and "second" features can explicitly or implicitly include one or more of the features. In the description of the utility model, the meaning of "several" and "a number" is two or more, unless otherwise clearly and specifically defined.

[0023] The aircraft fuselage assembly tooling of this embodiment includes a base 1, a skeleton assembly mechanism and a skin assembly mechanism, wherein the skeleton assembly mechanism includes upper cabin fixing columns 2 on both sides and a plurality of cantilever positioning columns 3, and the upper cabin fixing columns 2 and the cantilever positioning columns 3 are both fixedly mounted on the base 1 and cannot be moved.

[0024] A support plate 21 and a positioning pin 22 are provided on the top of the upper cabin fixing column 2. The front end of the support plate 21 is a C-shaped structure and is provided with a positioning pin hole. The positioning pin 22 passes through the positioning pin hole. A plurality of cantilever mounting seats 41 are provided on the outer side of the upper cabin 4 of the multi-rotor aircraft for subsequent installation of the cantilever 5. The C-shaped structure at the front end of the support plate 21 is inserted into the cantilever mounting seat 41. The positioning pin 22 passes through the cantilever mounting seat 41 and the support plate 21 to position the upper cabin 4.

[0025] The top of the cantilever positioning column 3 is provided with a positioning shaft 31, and a locking block 32 is provided above the positioning shaft 31. The end of the cantilever 5 is provided with an axial hole, which is sleeved on the positioning shaft 31, and the locking block 32 is tightened. The head end of the cantilever 5 is a connecting end, which needs to be opposite to the cantilever mounting seat 41 and locked and fixed by fasteners to assemble the frame.

[0026] The skin assembly mechanism includes skin mounting frames 6 on both sides, and sliders 61 are provided at the bottom of the skin mounting frames 6; guide rails 11 are provided on both sides of the base 1, and the skin mounting frames 6 can slide along the guide rails 11. The skin mounting frames 6 on both sides are provided with skin mounting plates 62 on the opposite sides, and a plurality of C-shaped positioning clips 63 are provided on the skin mounting plates 62, which can be used to fix the skin. At the same time, the side of the skin mounting frame 61 is provided with a skeleton positioning clip and a positioning mounting plate, which can fix the skeleton during gluing, so that the skeleton and the skin are accurately glued and not misaligned.

[0027] During assembly, the outer skins on both sides can be installed on the skin mounting plates 62, and the skin mounting frame 6 can be moved along the guide rail 11, away from the middle frame assembly mechanism, and the upper cabin 4 can be placed on the upper cabin fixing column 2, and then the cantilever 5 can be installed on the cantilever positioning column 3, so that the cantilever mounting seat 41 of the upper cabin 4 is opposite to the cantilever 5, and can be accurately positioned and installed; when the frame is installed, the skin mounting frame 6 can be pushed to make the outer skin fit the frame to simulate the state of the fuselage before gluing. If there is no problem, the fuselage skin can be directly glued to complete the overall assembly of the aircraft body.

[0028] The above is only a preferred embodiment of the present invention. The protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. An aircraft body assembly tool, characterized in that: It includes a base, a skeleton assembly mechanism and a skin assembly mechanism. The skeleton assembly mechanism includes an upper cabin fixing column and a plurality of cantilever positioning columns. The upper cabin fixing column and the cantilever positioning columns are fixedly mounted on the base. The skin assembly mechanism includes skin mounting frames on both sides. Slide blocks are provided at the bottom of the skin mounting frames. Guide rails are provided on both sides of the base, and the skin mounting frames can slide along the guide rails.

2. The aircraft body assembly tool according to claim 1, characterized in that: Skin mounting plates are arranged on the opposite sides of the skin mounting frames on both sides, and a plurality of C-shaped positioning clips are arranged on the skin mounting plates.

3. The aircraft body assembly tool according to claim 2, characterized in that: A skeleton positioning clamp and a positioning mounting plate are provided on the side of the skin mounting frame.

4. The aircraft body assembly tool according to claim 1, characterized in that: A support plate and a positioning pin are provided on the top of the upper cabin body fixing column. The front end of the support plate is a C-shaped structure and is provided with a positioning pin hole, and the positioning pin passes through the positioning pin hole.

5. The aircraft body assembly tool according to claim 1, characterized in that: A positioning shaft is arranged at the top end of the cantilever positioning column, and a locking block is arranged above the positioning shaft.

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