CN216830577U

CN216830577U - Quick sectional fixture of aircraft wing

Info

Publication number: CN216830577U
Application number: CN202220148124.4U
Authority: CN
Inventors: 薛国航
Original assignee: Zhuhai Triton Technology Co ltd
Current assignee: Zhuhai Triton Technology Co ltd
Priority date: 2022-01-20
Filing date: 2022-01-20
Publication date: 2022-06-28
Anticipated expiration: 2032-01-20

Abstract

The utility model discloses a quick sectional fixture of aircraft wing that assembly precision is high, improve assembly efficiency and convenient observation measurement. The utility model discloses a grudging post that two symmetries set up, two be provided with the swivel mount between the grudging post, the one end of swivel mount be provided with the wing of aircraft wing with the locking Assembly of looks adaptation, the other end of swivel mount be provided with the aircraft wing on the lightening hole looks adaptation the lightening hole insert fixed subassembly, the aircraft wing passes through locking Assembly with the lightening hole insert fixed subassembly to be fixed in on the quick sectional fixture of aircraft wing. The utility model discloses be applied to space flight and aviation's technical field.

Description

Quick sectional fixture of aircraft wing

Technical Field

The utility model relates to a quick sectional fixture, in particular to quick sectional fixture of aircraft wing.

Background

In recent years, with the reform and development of China and the great improvement of the living standard of the material culture of people, light airplanes as the category of general aviation have more and more operation flights in the aspects of tourism, entertainment, advertisement photography, cultural sports and the like, and have formed great demand markets in coastal areas, along rivers, edgeways and economically developed areas. In the past, few manufacturers for producing light airplanes in China have a sharp increase trend in recent years, and the existing wing assembly of the light airplane is to assemble hundreds of parts on a flat large desktop, so that the defect that the assembly precision is influenced due to the fact that distortion and deformation exist among various sub-assemblies of the wing, particularly the assembly with large size span, in the whole assembly process, the parts exist, the sub-assemblies need 360-degree rotation observation and measurement, and certain difficulty exists in space positioning.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that overcome prior art not enough, provide an assembly precision height, improve assembly efficiency and convenient observation measuring aircraft wing quick sectional fixture.

The utility model adopts the technical proposal that: the utility model discloses a grudging post that two symmetries set up, two be provided with the swivel mount between the grudging post, the one end of swivel mount be provided with the wing of aircraft wing with the locking Assembly of looks adaptation, the other end of swivel mount be provided with the aircraft wing on the lightening hole looks adaptation the lightening hole insert fixed subassembly, the aircraft wing passes through locking Assembly with the lightening hole insert fixed subassembly be fixed in on the quick sectional fixture of aircraft wing.

Furthermore, the rotating frame comprises a rotating frame plate, a rotating bearing and a rotating disc, the rotating bearing is installed on one of the vertical frames, the rotating disc is installed on the other vertical frame, the rotating bearing and the rotating disc are located on the same axis, and two ends of the rotating frame plate are respectively connected with the rotating bearing and the rotating disc.

Further, locking Assembly includes first connection side siphunculus and second connection side siphunculus, first connection side siphunculus with the second is connected the side siphunculus and is fixed in respectively the upper and lower both sides of rotatory deckle board one end, the end of first connection side siphunculus is provided with the angle yard board, be equipped with the first screw hole of a plurality of on the angle yard board, the end of second connection side siphunculus is provided with the connecting plate, be equipped with a plurality of second screw hole on the connecting plate, first screw hole with the second screw hole respectively with the wing of aircraft wing with the connecting hole looks adaptation of upper and lower both sides.

Further, the lightening hole inserts fixed subassembly and includes the horizontal square through pipe of a plurality of, the one end of horizontal square through pipe with the other end of rotatory framed panel is connected, the other end of horizontal square through pipe is provided with the elastic disc subassembly, the elastic disc subassembly includes first elastic disc and second elastic disc, first elastic disc with the second elastic disc sets up with one heart, just the diameter of first elastic disc is greater than the diameter of second elastic disc, the diameter of second elastic disc and the lightening hole on the aircraft wing are clearance fit.

Furthermore, a plurality of first pin holes are formed in the annular array on the rotating disc, a plurality of second pin holes matched with the first pin holes are formed in the annular array on the vertical frame fixed with the rotating disc, and rotation stopping pin columns are arranged between the first pin holes and the second pin holes.

Furthermore, the lightening hole inserting and fixing assembly further comprises a longitudinal square through pipe, one end of the longitudinal square through pipe is fixed on one side of the rotating frame plate, and the other end of the longitudinal square through pipe is connected with all the transverse square through pipes.

Furthermore, a supporting bottom rod is arranged between the bottoms of the two vertical frames, and an object placing frame is arranged between the tops of the two vertical frames.

Further, the first elastic disc and the second elastic disc are both nylon discs.

The utility model has the advantages that: because the utility model discloses a stand that two symmetries set up, two be provided with the swivel mount between the stand, one end of swivel mount is provided with the locking Assembly with the wing of aircraft wing is with the looks adaptation, the other end of swivel mount is provided with the lightening hole that the lightening hole on with the aircraft wing looks adaptation inserts fixed subassembly, the aircraft wing passes through the locking Assembly with the lightening hole inserts fixed subassembly and is fixed in on the quick erection fixture of aircraft wing, so the assembly benchmark of aircraft wing can both be given through quick erection fixture, so can effectively improve the precision of assembly, avoid sub-assembly distortion, and quick erection fixture can effectively make things convenient for workman's assembly, improves assembly efficiency; in addition, the rotating frame can perform 360-degree rotation observation measurement on the airplane wing.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

FIG. 2 is a schematic view of the assembly of the present invention with an aircraft wing;

FIG. 3 is an enlarged schematic view of a portion of FIG. 1A;

fig. 4 is an enlarged schematic view of a portion of fig. 2B.

Detailed Description

As shown in fig. 1 to 4, in this embodiment, the utility model discloses a grudging post 1 that two symmetries set up, two be provided with swivel mount 2 between the grudging post 1, the one end of swivel mount 2 is provided with the wing with the aircraft wing with the locking Assembly 4 of 3 looks adaptations, the other end of swivel mount 2 is provided with the lightening hole that 5 looks adaptations of lightening hole on the aircraft wing insert fixed subassembly 6, the aircraft wing passes through locking Assembly 4 with lightening hole insert fixed subassembly 6 and be fixed in on the quick sectional fixture of aircraft wing.

In this embodiment, the rotating frame 2 includes a rotating frame plate 21, a rotating bearing 22 and a rotating disc 23, the rotating bearing 22 is installed on one of the stands 1, the rotating disc 23 is installed on the other of the stands 1, the rotating bearing 22 and the rotating disc 23 are located on the same axis, two ends of the rotating frame plate 21 are respectively connected with the rotating bearing 22 and the rotating disc 23, and the stands 1 and the rotating frame plate 21 are formed by welding through a square steel structure.

In this embodiment, locking Assembly 4 includes first square siphunculus 41 and the square siphunculus 42 is connected to the second, first square siphunculus 41 of connecting with the second is connected square siphunculus 42 and is fixed in respectively the upper and lower both sides of rotatory framed lamella 21 one end, the end of first square siphunculus 41 of connecting is provided with angle sign indicating number board 43, be equipped with three first screw hole 44 on the angle sign indicating number board 43, the end of the square siphunculus 42 is connected to the second is provided with connecting plate 45, be equipped with two second screw holes on the connecting plate 45, first screw hole 44 with the second screw hole respectively with the wing of aircraft wing with the connecting hole adaptation of 3 upper and lower both sides, this design can be in with the wing of aircraft with the wing 3 upside through three screw 431 locking angle sign indicating number board 43, with the wing of aircraft wing with the 3 downside through two screw locking on the connecting plate 45.

In this embodiment, the lightening hole inserting and fixing assembly 6 comprises two transverse square-through pipes 61, one end of each transverse square-through pipe 61 is connected with the other end of the rotary frame plate 21, the other end of each transverse square-through pipe 61 is provided with an elastic disc assembly, the elastic disc assembly comprises a first elastic disc 62 and a second elastic disc 63, the first elastic disc 62 and the second elastic disc 63 are concentrically arranged, the diameter of the first elastic disc 62 is larger than that of the second elastic disc 63, the diameter of the second elastic disc 63 is in clearance fit with the lightening holes 5 on the wings of the airplane, and the lightening hole inserting and fixing assembly can be inserted into the lightening holes 5 on the wingtips of the airplane through the two second elastic discs 63.

In this embodiment, the annular array on the rotating disc 23 has a plurality of first pin holes 231, the annular array on the stand 1 fixed with the rotating disc 23 has a plurality of second pin holes adapted to the first pin holes 231, and rotation-stopping pin posts are arranged between the first pin holes 231 and the second pin holes, so that the design can lock the rotating frame plate 21 between the two stands 1 by inserting the rotation-stopping pin posts into the first pin holes 231 and the second pin holes when the rapid installation fixture does not need to rotate for observation and measurement.

In this embodiment, the lightening hole inserting and fixing assembly 6 further comprises a longitudinal square through pipe 65, one end of the longitudinal square through pipe 65 is fixed on one side of the rotating frame plate 21, the other end of the longitudinal square through pipe 65 is connected with all the transverse square through pipes 61, and the longitudinal square through pipe 65 can improve the stability of the lightening hole inserting and fixing assembly 6

In this embodiment, a supporting bottom rod 7 is arranged between the bottoms of the two vertical frames 1, a storage frame 8 is arranged between the tops of the two vertical frames 1, the supporting bottom rod 7 can improve the stability between the two vertical frames 1, and the storage frame 8 can store parts of the aircraft wing.

In this embodiment, the first elastic disc 62 and the second elastic disc 63 are both nylon discs.

The utility model discloses be applied to aerospace's technical field.

While the embodiments of the present invention have been described in terms of practical embodiments, they are not intended to limit the scope of the invention, and modifications of the embodiments and combinations with other embodiments will be apparent to those skilled in the art in light of the present description.

Claims

1. The utility model provides a quick sectional fixture of aircraft wing which characterized in that: it includes grudging post (1) that two symmetries set up, two be provided with swivel mount (2) between grudging post (1), the one end of swivel mount (2) be provided with the wing of aircraft wing with locking Assembly (4) of (3) looks adaptation, the other end of swivel mount (2) be provided with the lightening hole of lightening hole (5) looks adaptation on the aircraft wing insert fixed subassembly (6), the aircraft wing passes through locking Assembly (4) with lightening hole insert fixed subassembly (6) and be fixed in on the quick sectional fixture of aircraft wing.

2. An aircraft wing quick install clamp according to claim 1, wherein: the rotating frame (2) comprises a rotating frame plate (21), a rotating bearing (22) and a rotating disc (23), the rotating bearing (22) is installed on one of the vertical frames (1), the rotating disc (23) is installed on the other vertical frame (1), the rotating bearing (22) and the rotating disc (23) are located on the same axis, and two ends of the rotating frame plate (21) are respectively connected with the rotating bearing (22) and the rotating disc (23).

3. An aircraft wing quick install clamp according to claim 2, wherein: locking Assembly (4) are including first connection square through pipe (41) and second connection square through pipe (42), first connection square through pipe (41) with second connection square through pipe (42) are fixed in respectively the upper and lower both sides of rotatory framed lamella (21) one end, the end of first connection square through pipe (41) is provided with angle code plate (43), be equipped with the first screw hole of a plurality of (44) on angle code plate (43), the end of second connection square through pipe (42) is provided with connecting plate (45), be equipped with a plurality of second screw hole on connecting plate (45), first screw hole (44) with the second screw hole respectively with the wing of aircraft wing with the connecting hole looks adaptation of (3) upper and lower both sides.

4. An aircraft wing quick install clamp according to claim 2, wherein: the lightening hole inserting and fixing assembly (6) comprises a plurality of transverse square through pipes (61), one end of each transverse square through pipe (61) is connected with the other end of the rotary frame plate (21), the other end of each transverse square through pipe (61) is provided with an elastic disc assembly, each elastic disc assembly comprises a first elastic disc (62) and a second elastic disc (63), each first elastic disc (62) and each second elastic disc (63) are concentrically arranged, the diameter of each first elastic disc (62) is larger than that of each second elastic disc (63), and the diameter of each second elastic disc (63) is in clearance fit with lightening holes (5) in airplane wings.

5. An aircraft wing quick install clamp according to claim 2, wherein: the annular array has a plurality of pinhole one (231) on swivel disc (23), be fixed with on swivel disc (23) grudging post (1) annular array have a plurality of with pinhole one (231) looks adaptation pinhole two, pinhole one (231) with be provided with between the pinhole two and stop rotating the cotter pin post.

6. An aircraft wing quick install clamp according to claim 4, wherein: the lightening hole inserting and fixing assembly (6) further comprises a longitudinal square through pipe (65), one end of the longitudinal square through pipe (65) is fixed on one side of the rotating frame plate (21), and the other end of the longitudinal square through pipe (65) is connected with all the transverse square through pipes (61).

7. An aircraft wing quick install clamp according to claim 2, wherein: a supporting bottom rod (7) is arranged between the bottoms of the two vertical frames (1), and an object placing frame (8) is arranged between the tops of the two vertical frames (1).

8. An aircraft wing quick install clamp according to claim 4, wherein: the first elastic disc (62) and the second elastic disc (63) are both nylon discs.