Multifunctional aircraft attitude adjustment assembly tool

Abstract

The utility model discloses a multifunctional aircraft attitude adjustment assembly tool which comprises symmetrically-arranged elevator fixing supports, elevators, hanging beams, connecting shafts, positioning discs and mounting discs. The lifter is installed at the top of the lifter fixing support, one end of the connecting shaft is fixed to the lifter, the other end of the connecting shaft is fixed to the hanging beam, the fixing position of the connecting shaft and the hanging beam can be adjusted relative to the axis direction of the hanging beam, a positioning disc is installed on one side of the bottom of the hanging beam, and an installation disc is installed on the other side of the bottom of the hanging beam and used for installing an aircraft. And the mounting disc and the positioning disc rotate synchronously. According to the device, posture adjustment such as supporting, lifting, overturning and limiting in the aircraft assembling process can be achieved, and safety, reliability and convenience in the assembling operation process are improved.

Description

Technical Field

[0001] The utility model relates to the field of assembly tooling design, in particular to a multi-functional aircraft attitude adjustment assembly tooling. Background Technique

[0002] With the development of aerospace, aviation, and weapon system technologies, small aircraft are increasingly widely used. Such products have a relatively large individual mass, usually greater than 40 kg, and the product attitude needs to be flexibly adjusted during the production process to meet the convenience of assembly. Relying solely on manual attitude adjustment poses safety risks, but using large special equipment such as cranes for attitude adjustment is too cumbersome. Therefore, the safety, reliability, and convenience of attitude adjustment measures such as support, lifting, flipping, and limiting during the assembly process of large-mass products are crucial. Content of the Utility Model

[0003] The technical problem solved by the utility model is: overcoming the deficiencies of the prior art, providing a multi-functional aircraft attitude adjustment assembly tooling, realizing attitude adjustments such as support, lifting, flipping, and limiting during the aircraft assembly process, and improving the safety, reliability, and convenience of the assembly operation process.

[0004] The technical solution of the utility model is: a multi-functional aircraft attitude adjustment assembly tooling, including: symmetrically arranged elevator fixed brackets, elevators, lifting beams, connecting shafts, positioning disks, and mounting disks; the elevators are installed on the tops of the elevator fixed brackets, one end of the connecting shaft is fixed to the elevator, and the other end is fixed to the lifting beam, perpendicular to the lifting beam. The fixed position of the connecting shaft and the lifting beam can be adjusted relative to the axis direction of the lifting beam. A positioning disk is installed on one side of the bottom of the lifting beam, and a mounting disk is installed on the other side. The mounting disk is used to install the aircraft, and the mounting disk and the positioning disk rotate synchronously.

[0005] Further, the elevator fixed bracket adopts an isosceles trapezoid structure, the bottom plane is fixed to the ground or the test bench, and the top plane is used to fix the elevator.

[0006] Further, a plurality of connecting shaft mounting holes are evenly opened along the axis direction of the lifting beam on the lifting beam for adjusting the fixed position with the connecting shaft.

[0007] Further, the connecting shaft adopts a cylindrical structure, the connecting shaft passes through the connecting shaft mounting hole on the lifting beam for fixation, and the diameter of the column part passing through is the same as the diameter of the connecting shaft mounting hole.

[0008] Further, a bearing hole is also opened at the bottom of the lifting beam, and a bearing is installed in the bearing hole; a through hole is opened at the center of the positioning disk, which is the same as the diameter of the bearing hole of the lifting beam; a convex column is provided at the center of the mounting disk for passing through the bearing hole of the lifting beam and the center through hole of the positioning disk for fixation, so that the mounting disk and the positioning disk rotate synchronously.

[0009] Further, the convex cylinder at the center of the mounting disc has threads. After passing through the bearing at the bottom of the suspension beam and the central through-hole of the positioning disc, it is fixed by a nut.

[0010] Further, the mounting disc and the positioning disc have the same diameter.

[0011] Further, a circle of through-holes are evenly formed on the outer sides of the disc surfaces of the positioning disc and the mounting disc. The aperture diameter is consistent with the mounting holes of the connecting shafts on the suspension beam. The positioning pins pass through the overlapping through-holes of the positioning disc, the mounting holes of the connecting shafts, and the through-holes of the mounting disc in sequence from one side of the positioning disc to limit the aircraft.

[0012] Further, symmetrical aircraft mounting holes are formed on the disc surface of the mounting disc for mounting the aircraft.

[0013] The advantages of the present utility model compared with the prior art are as follows:

[0014] A multi-functional attitude adjustment assembly tooling is designed for the aircraft. Through the cooperation of the lift, the suspension beam, the positioning disc and the mounting disc, the multi-functional attitude adjustment functions such as the support, lifting, flipping and limiting of the aircraft are realized, the operability and convenience in the processes of assembly, inspection and fault repair are improved, the production efficiency and production quality are improved, and the safety of personnel and products is ensured at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic structural diagram of the present utility model;

[0016] Figure 2 is a schematic structural diagram of the fixed bracket of the lift of the present utility model;

[0017] Figure 3 is a schematic structural diagram of the suspension beam of the present utility model;

[0018] Figure 4 is a schematic structural diagram of the connecting shaft of the present utility model;

[0019] Figure 5 is a schematic structural diagram of the positioning disc of the present utility model;

[0020] Figure 6 is a schematic structural diagram of the mounting disc of the present utility model. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0021] In order to better understand the technical solution of the present utility model, the embodiments of the present utility model will be specifically described below with reference to the drawings.

[0022] As shown in this embodiment Figure 1 mainly includes symmetrically arranged lift fixed brackets 1, suspension beams 2, lifts 3, connecting shafts 4, positioning discs 5 and mounting discs 6.

[0023] The lift 3 is installed at the top of the lift fixing bracket 1. One end of the connecting shaft 4 is fixed to the lift 3, and the other end is fixed to the hanging beam 2, being perpendicular to the hanging beam 2. The fixing position of the connecting shaft 4 relative to the axis direction of the hanging beam 2 can be adjusted. A positioning disk 5 is installed on one side of the bottom of the hanging beam 2, and a mounting disk 6 is installed on the other side. The mounting disk 6 is used to mount the aircraft (i.e., the large-mass product), and the mounting disk 6 and the positioning disk 5 rotate synchronously.

[0024] During use, after the large-mass product to be assembled is installed together with the mounting disk 6, the lift 3 is used to realize the support and lifting functions of the large-mass product. After the large-mass product is lifted, the flipping function of the large-mass product is realized by rotating the mounting disk 6 and the positioning disk 5. Subsequently, the positioning function of the large-mass product is realized by sequentially passing the positioning pin through the holes of the overlapping positioning disks, the hanging beam, and the mounting disk from one side of the positioning disk.

[0025] The structure of the lift fixing bracket 1 is as Figure 2 shown, adopting an isosceles trapezoid structure. The bottom plane is fixed to the ground or the test bench, and the top plane is used to fix the lift.

[0026] The structure of the hanging beam 2 is as Figure 3 shown. The inner hole on the left side in the figure is a bearing hole, inlaid with a standard 6204ZZ metal-sealed bearing. Except that the bearing hole diameter of the hanging beam matches the outer diameter of the bearing, all other hole diameters can be 20 mm.

[0027] The lift 3 is a commercially available product. It can be selected preferably according to the constraint conditions such as product quality, external dimensions, and lifting height requirements. It is preferably SWL2.5T-1A-II-6:1-200, a screw-lifting type lift with a 200 mm stroke.

[0028] When selecting the height of the lift fixing bracket 1 and the effective stroke of the lift 3, it should be avoided that the large-mass product to be assembled forms interference with the ground due to insufficient lifting height during the flipping process.

[0029] The structure of the connecting shaft 4 is as Figure 4 shown. The diameter of the cylindrical part should be consistent with the 20 mm hole diameter of the hanging beam 2.

[0030] The structure of the positioning disk is as Figure 5 shown. The hole diameter of the through holes around the outer circumference of the disk surface should be consistent with the 20 mm hole diameter of the hanging beam, and the central through hole should be consistent with the bearing hole diameter of the hanging beam.

[0031] The structure of the mounting disk is as Figure 6As shown, the aperture of the through holes on the outer circumference of the disk surface should be consistent with the aperture of the suspension beam and the positioning disk, which is 20mm; the central raised cylindrical part has threads for passing through the bearing of the suspension beam and the central through hole of the positioning disk, and is fastened with nuts. The thread specification should match the bearing hole of the suspension beam and the corresponding aperture of the positioning disk; symmetric aircraft mounting holes are also opened at the center of the disk surface for connecting with the lifting process holes of large-mass products through screws. The hole positions are selected according to the centroid position of the large-mass products, and it should be ensured as much as possible that the centroid of the large-mass products is near the center of the mounting disk after installation.

[0032] The positioning pins can be selected according to the apertures of the suspension beam, the positioning disk, and the mounting disk. Pins with a diameter of Φ20mm and a length of 50mm can be used.

[0033] It can be understood that the present utility model is described through embodiments. Those skilled in the art know that without departing from the spirit and scope of the present utility model, various changes or equivalent substitutions can be made to these features and embodiments. In addition, under the teaching of the present utility model, these features and embodiments can be modified to adapt to specific situations without departing from the spirit and scope of the present utility model. Therefore, the present utility model is not limited by the specific embodiments disclosed herein, and the embodiments that can fall within the scope of the claims of this application all belong to the scope protected by the present utility model.

[0034] The content not described in detail in the specification of the present utility model belongs to the well-known technology of those skilled in the art.

Claims

1. A multifunctional aircraft attitude adjustment assembly tool, characterized in that: include: The elevator fixing bracket, elevator, hanging beam, connecting shaft, positioning plate and installation plate are symmetrically arranged; the elevator is installed on the top of the elevator fixing bracket, one end of the connecting shaft is fixed to the elevator, and the other end is fixed to the hanging beam, which is perpendicular to the hanging beam. The fixing positions of the connecting shaft and the hanging beam can be adjusted relative to the axial direction of the hanging beam. A positioning plate is installed on one side of the bottom of the hanging beam, and a mounting plate is installed on the other side. The mounting plate is used to install the aircraft, and the mounting plate and the positioning plate rotate synchronously.

2. The multifunctional aircraft attitude adjustment assembly tool according to claim 1, characterized in that: The elevator fixing bracket adopts an isosceles trapezoidal structure, the bottom plane is fixed to the ground or the test bench, and the top plane is used to fix the elevator.

3. The multifunctional aircraft attitude adjustment assembly tool according to claim 1, characterized in that: A plurality of connecting shaft mounting holes are evenly opened on the hanging beam along the axial direction of the hanging beam, which are used to adjust the fixed position of the connecting shaft.

4. The multifunctional aircraft attitude adjustment assembly tool according to claim 3, characterized in that: The connecting shaft adopts a cylindrical structure, and the connecting shaft passes through the connecting shaft installation hole on the hanging beam for fixing, and the diameter of the passing part of the cylinder is consistent with the hole diameter of the connecting shaft installation hole.

5. The multifunctional aircraft attitude adjustment assembly tool according to claim 3, characterized in that: A bearing hole is also provided at the bottom of the hanging beam, in which a bearing is installed; a through hole is provided in the center of the positioning plate, which is consistent with the aperture of the bearing hole of the hanging beam; a raised column is provided in the center of the mounting plate, which is used to pass through the bearing hole of the hanging beam and the center through hole of the positioning plate for fixing, so that the mounting plate and the positioning plate rotate synchronously.

6. The multifunctional aircraft attitude adjustment assembly tool according to claim 5, characterized in that: The raised column at the center of the mounting plate is provided with threads, which pass through the bearing at the bottom of the hanging beam and the center through hole of the positioning plate and are fixed by nuts.

7. The multifunctional aircraft attitude adjustment assembly tool according to claim 5, characterized in that: The mounting plate and the positioning plate have the same diameter.

8. The multifunctional aircraft attitude adjustment assembly tool according to claim 7, characterized in that: There is a circle of through holes evenly opened on the outer side of the positioning plate and the mounting plate, and the hole diameter is consistent with the connecting shaft mounting hole on the hanging beam, so that the positioning pin can pass through the overlapping positioning plate through holes, connecting shaft mounting holes, and mounting plate through holes from one side of the positioning plate in sequence to limit the aircraft.

9. The multifunctional aircraft attitude adjustment assembly tool according to claim 5, characterized in that: Symmetrical aircraft mounting holes are also provided on the surface of the mounting plate for mounting the aircraft.

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