Aircraft part assembly fixture

Abstract

The utility model discloses an aircraft part assembling fixture, a structural framework comprises a group of supporting frames, an upper cross beam and a lower cross beam, the upper cross beam and the lower cross beam are arranged between the supporting frames and are arranged in parallel at intervals up and down, and a first fixing mechanism and a second fixing mechanism are arranged between the upper cross beam and the lower cross beam. The first fixing mechanism and the second fixing mechanism are both used for fixing aircraft parts, and a limiting assembly is arranged on the supporting frame and is arranged at the position close to the first fixing mechanism; a hollowed-out hole is formed in a supporting plate in the first fixing mechanism, a limiting assembly is arranged at the position, opposite to one side of the hollowed-out hole, of the supporting frame, and through mutual cooperation of the first fixing mechanism, the second fixing mechanism and the limiting assembly, main parts needing to be assembled on an airplane can be rapidly positioned; the positioned main parts can be kept stable on the structural framework, subsequent assembling and splicing operation of aircraft parts is facilitated, and the structural framework is small in occupied area, simple in fixing mode and convenient to operate.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft assembly, and in particular relates to an aircraft parts assembly jig. Background Art

[0002] The aircraft assembly process usually relies on assembly jigs, where scattered parts are first assembled into a small component, and then gradually assembled into more complex sections and components, just like building blocks, where small parts rely on mutual positioning functions to finally assemble into an overall structural product; aircraft parts also rely on assembly jigs to first position the main parts, and then splice and assemble the scattered parts together. Traditional assembly jigs take up a large space when positioning these aircraft parts, and have a complex structure. It takes a cumbersome process to position the main parts to be assembled, and the assembly process is time-consuming and the production cost is high. Utility Model Content

[0003] The utility model aims to provide an aircraft parts assembly jig, which can quickly locate the main parts to be assembled on the aircraft by arranging a first fixing mechanism and a second fixing mechanism on the structural frame, and the located aircraft parts can remain stable on the structural frame, which is convenient for subsequent assembly and splicing operations of the aircraft parts.

[0004] The utility model is realized by the following technical solutions:

[0005] An aircraft parts assembly jig includes a structural skeleton, the structural skeleton includes a group of support frames, an upper crossbeam and a lower crossbeam, the upper crossbeam and the lower crossbeam are arranged between the support frames and are arranged in parallel with each other with an upper and lower interval, a first fixing mechanism and a second fixing mechanism are arranged between the upper crossbeam and the lower crossbeam, the first fixing mechanism is connected to the upper crossbeam and the lower crossbeam respectively, the second fixing mechanism is connected to the lower crossbeam, the first fixing mechanism and the second fixing mechanism are both used to fix aircraft parts, and a limiting component is arranged on the support frame, and the limiting component is arranged at a position close to the first fixing mechanism.

[0006] Furthermore, the first fixing mechanism includes a support plate, the upper and lower ends of the support plate are respectively connected to the upper crossbeam and the lower crossbeam, and a clamping assembly is provided on one side of the support plate, and the clamping assembly is used to clamp and fix the aircraft part on the support plate.

[0007] Furthermore, the clamping assembly includes at least one group of fixing parts, one group of the fixing parts are arranged opposite to each other, each of the fixing parts is provided with a clamping part, the clamping part includes a clamping rod and a pressure head, the clamping rod is threadedly connected to the fixing part, the pressure head is arranged at the end of the clamping rod, the two clamping parts are arranged opposite to each other, and the fixing part is an L-shaped structure.

[0008] Furthermore, a hollow hole is provided below the support plate, and the hollow hole is used to make way for aircraft parts.

[0009] Furthermore, the limiting assembly includes a connecting piece and a limiting plate, wherein the limiting plate is arranged on one side of the hollow hole, and the limiting plate cooperates with the first fixing mechanism to limit the aircraft part.

[0010] Furthermore, the second fixing mechanism includes a fixing seat, the fixing seat is connected to the lower cross beam, a mounting plate is arranged on the fixing seat, and at least one set of tensioning components is arranged on the mounting plate.

[0011] Furthermore, the tensioning assembly includes a fixed shaft, a screw, a limit pin and a wrench; one end of the fixed shaft passes through the mounting plate and the fixed seat respectively, a thread is provided in the fixed shaft, the screw is threadedly connected to the fixed shaft at one end, the limit pin is plug-fitted to the other end of the fixed shaft, a slot is provided at the end of the screw, and the wrench is plug-fitted to the slot for rotating the screw.

[0012] Furthermore, the second fixing mechanism includes at least one supporting seat, and the supporting seat is arranged on one side of the fixing seat, and the supporting seat is used to support the aircraft part.

[0013] Furthermore, a supporting surface is provided on the supporting seat, and the supporting surface is an arc-shaped groove structure. A limiting block is provided on a side of the supporting seat away from the fixing seat.

[0014] Compared with the prior art, the utility model has the following advantages and beneficial effects:

[0015] 1) In the utility model, a first fixing mechanism and a second fixing mechanism are arranged on the structural frame, a hollow hole is arranged on the support plate of the first fixing mechanism, and a limiting assembly is arranged on the support frame at a position relative to one side of the hollow hole. Through the mutual cooperation of the first fixing mechanism, the second fixing mechanism and the limiting assembly, the main parts to be assembled on the aircraft can be quickly positioned, and the positioned main parts can remain stable on the structural frame, which is convenient for the subsequent assembly and splicing operations of the aircraft parts. The structural frame occupies a small area, and the fixing method is simple and easy to operate.

[0016] 2) In the utility model, a tensioning assembly is arranged on the mounting plate of the fixing seat, and the tensioning assembly includes a fixed shaft, a screw rod, a limit pin and a wrench. One end of the fixed shaft passes through the mounting plate and the fixing seat respectively, and a thread is arranged in the fixed shaft. The screw rod is threadedly connected with the fixed shaft at one end, and the limit pin is plug-fitted with the other end of the fixed shaft. A slot is arranged at the end of the screw rod, and the wrench is plug-fitted with the slot to rotate the screw rod. When fixing the aircraft parts, the fixed shaft is passed through the aircraft parts and then the limit pin is inserted. Then the screw rod is rotated with the wrench to move the fixed shaft to tighten the aircraft parts. When removing the aircraft parts, the fixed shaft does not need to be completely removed. The aircraft parts can be removed by only loosening the fixed shaft and pulling out the limit pin. The operation is simple and can improve the assembly efficiency of the aircraft parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 The utility model is a schematic diagram of the overall structure of the aircraft parts assembly jig.

[0019] Figure 2 The utility model is a schematic diagram of the structure of the tensioning assembly in the aircraft parts assembly jig.

[0020] Among them: 1-structural frame, 11-support frame, 12-upper beam, 13-lower beam, 2-support plate, 21-hollow hole, 3-fixing part, 31-pressing rod, 4-fixing seat, 5-mounting plate, 6-tensioning assembly, 61-fixing shaft, 62-screw, 63-wrench, 64-limiting pin, 7-support seat, 71-limiting block, 8-limiting assembly, 81-connecting part, 82-limiting plate. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the embodiments of the utility model clearer, the technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments.

[0022] Embodiment 1:

[0023] The main structure of this embodiment is an aircraft parts assembly jig, such as Figure 1As shown, the structural skeleton 1 includes a group of support frames 11, an upper crossbeam 12 and a lower crossbeam 13. The group of support frames 11 are arranged at intervals, and the upper crossbeam 12 and the lower crossbeam 13 are arranged between the support frames 11 and are arranged in parallel with each other at upper and lower intervals. The support frames 11, the upper crossbeam 12 and the lower crossbeam 13 in the structural skeleton 1 are all made by welding hollow steel pipes, and legs are arranged under the support frames 11 to keep the support frames 11 stable; a first fixing mechanism and a second fixing mechanism are arranged between the upper crossbeam 12 and the lower crossbeam 13 of the structural skeleton 1, the first fixing mechanism is connected to the upper crossbeam 12 and the lower crossbeam 13 respectively, and the second fixing mechanism is connected to the lower crossbeam 13, the first fixing mechanism and the second fixing mechanism are both used to fix aircraft parts, and the height of the first fixing mechanism is greater than that of the second fixing mechanism. The first fixing mechanism is used to fix the upper part of the aircraft part, and the second fixing mechanism can fix the lower part of the aircraft part; a limiting assembly 8 is provided on the support frame 11, and the limiting assembly 8 is provided at a position close to the first fixing mechanism; the limiting assembly 8 includes a connecting member 81 and a limiting plate 82, the connecting member 81 is connected to the support frame 11, and the limiting plate 82 is provided on the connecting member 81, and the limiting plate 82 cooperates with the first fixing mechanism to limit the aircraft part.

[0024] Embodiment 2:

[0025] On the basis of the above embodiments, the present embodiment further defines a first fixing mechanism, which includes a support plate 2, wherein the upper and lower ends of the support plate 2 are respectively connected to the upper crossbeam 12 and the lower crossbeam 13, and a clamping assembly is provided on one side of the support plate 2, and the clamping assembly is used to clamp and fix the aircraft parts on the support plate 2; the clamping assembly includes two groups of fixing members 3, which are arranged at intervals up and down, and the fixing members 3 of each group are arranged opposite to each other, and the fixing members 3 are L-shaped structural members, and the fixing members 3 are provided with clamping members, and the clamping members include a clamping rod 31 and a pressure head, and the clamping rod 31 is threadedly connected to the fixing member 3, and the pressure head is provided. The two clamping members are arranged at the end of the clamping rod 31, and the two clamping members are arranged opposite to each other. The two clamping members can be rotated to make the two oppositely arranged pressure heads approach each other, so as to clamp and fix the aircraft parts; a hollow hole 21 is arranged below the support plate 2, and the hollow hole 21 is used to make way for the aircraft parts. The limiting plate 82 of the limiting assembly 8 is arranged at the position of the hollow hole 21 on the support plate 2. After the aircraft parts pass through the hollow hole 21 of the support plate 2, they abut against the limiting plate 82, and then the upper part of the aircraft parts is fixed by the two sets of fixing members 3 on the support plate 2, and the lower part of the aircraft parts is supported and fixed by the second fixing mechanism, and finally the aircraft parts are assembled. The other parts of this embodiment are the same as the above embodiment, and will not be repeated here.

[0026] Embodiment 3:

[0027] Based on the above embodiment, this embodiment further defines the second fixing mechanism, such as Figure 1 and Figure 2As shown, the second fixing mechanism includes a fixing seat 4, which is connected to the lower cross beam 13. The fixing seat 4 is also an L-shaped structure, and its bottom is fixedly connected to the lower cross beam 13. A mounting plate 5 is arranged on the fixing seat 4, and the mounting plate 5 is arranged higher than the top of the fixing seat 4. A plurality of tensioning components 6 are arranged on the mounting plate 5; the tensioning components 6 include a fixing shaft 61, a screw rod 62, a limit pin 64 and a wrench 63; one end of the fixing shaft 61 passes through the mounting plate 5 and the fixing seat 4 respectively, and a thread is arranged in the fixing shaft 61. The screw 62 is threadedly connected to the fixing shaft 61 at one end, and the limit pin 64 is plug-fitted and connected to the other end of the fixing shaft 61. A slot is arranged at the end of the screw 62, and a wrench 63 is arranged. 63 is plugged into the slot to rotate the screw 62. When fixing the aircraft parts, the fixed shaft 61 is passed through the aircraft parts and the limit pin 64 is inserted. Then the screw 62 is rotated with the wrench 63 to move the fixed shaft 61 to tighten the aircraft parts. The second fixing mechanism includes at least one support seat 7, which is arranged on one side of the fixing seat 4. The support seat 7 is used to support the aircraft parts. The support seat 7 is provided with a support surface, which is an arc-shaped groove structure. The support surface of the unit is matched with the bottom of the aircraft parts. At the same time, a limit block 71 is provided on the side of the support seat 7 away from the fixing seat 4. The limit block 71 cooperates with the limit plate 82 to limit the two ends of the aircraft parts respectively. The other parts of this embodiment are the same as the above embodiment and will not be repeated here.

[0028] In the description of the present utility model, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. used to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the utility model product is usually placed when used. They are only for the convenience of describing the present utility model 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 therefore cannot be understood as a limitation on the present utility model.

[0029] In addition, if the terms "horizontal" or "vertical" appear in the description of the present invention, it does not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0030] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. An aircraft parts assembly jig, characterized in that: The invention comprises a structural skeleton, which comprises a group of support frames, an upper crossbeam and a lower crossbeam. The upper crossbeam and the lower crossbeam are arranged between the support frames and are arranged in parallel with each other at an upper and lower interval. A first fixing mechanism and a second fixing mechanism are arranged between the upper crossbeam and the lower crossbeam. The first fixing mechanism is connected to the upper crossbeam and the lower crossbeam respectively, and the second fixing mechanism is connected to the lower crossbeam. Both the first fixing mechanism and the second fixing mechanism are used to fix aircraft parts. A limiting assembly is arranged on the support frame, and the limiting assembly is arranged at a position close to the first fixing mechanism.

2. The aircraft parts assembly jig according to claim 1, characterized in that: The first fixing mechanism comprises a support plate, the upper and lower ends of the support plate are respectively connected to the upper crossbeam and the lower crossbeam, and a clamping assembly is provided on one side of the support plate, and the clamping assembly is used to clamp and fix the aircraft parts on the support plate.

3. The aircraft parts assembly jig according to claim 2, characterized in that: The clamping assembly includes at least one group of fixing parts, one group of fixing parts are arranged opposite to each other, each of the fixing parts is provided with a clamping part, the clamping part includes a clamping rod and a pressure head, the clamping rod is threadedly connected to the fixing part, the pressure head is arranged at the end of the clamping rod, the two clamping parts are arranged opposite to each other, and the fixing part is an L-shaped structure.

4. The aircraft parts assembly jig according to claim 3, characterized in that: A hollow hole is arranged below the support plate, and the hollow hole is used to make way for aircraft parts.

5. The aircraft parts assembly jig according to claim 3, characterized in that: The limiting assembly comprises a connecting piece and a limiting plate. The limiting plate is arranged on one side of the hollow hole. The limiting plate cooperates with the first fixing mechanism to limit the aircraft part.

6. The aircraft parts assembly jig according to claim 1, characterized in that: The second fixing mechanism comprises a fixing seat, the fixing seat is connected to the lower cross beam, a mounting plate is arranged on the fixing seat, and at least one set of tensioning components is arranged on the mounting plate.

7. The aircraft parts assembly jig according to claim 6, characterized in that: The tensioning assembly includes a fixed shaft, a screw, a limit pin and a wrench; one end of the fixed shaft passes through the mounting plate and the fixed seat respectively, a thread is provided in the fixed shaft, the screw is threadedly connected to the fixed shaft at one end, the limit pin is plug-fitted to the other end of the fixed shaft, a slot is provided at the end of the screw, and the wrench is plug-fitted to the slot for rotating the screw.

8. The aircraft parts assembly jig according to claim 7, characterized in that: The second fixing mechanism comprises at least one supporting seat, wherein the supporting seat is arranged on one side of the fixing seat, and the supporting seat is used to support the aircraft part.

9. The aircraft parts assembly jig according to claim 8, characterized in that: The support seat is provided with a support surface, the support surface is an arc-shaped groove structure, and a limiting block is provided on a side of the support seat away from the fixing seat.

Images