CN210704387U

CN210704387U - Aircraft steel wire cutting clamp

Info

Publication number: CN210704387U
Application number: CN201921138143.3U
Authority: CN
Inventors: 甘耿昌
Original assignee: Zhuhai Shunzhen Technology Co Ltd
Current assignee: Zhuhai Shunzhen Technology Co Ltd
Priority date: 2019-07-18
Filing date: 2019-07-18
Publication date: 2020-06-09
Anticipated expiration: 2029-07-18

Abstract

The utility model discloses an aircraft steel wire cuts anchor clamps, including first press from both sides shell, second press from both sides shell and hinge, first press from both sides shell bottom surface intermediate position shaping has first recess, and the inside top of first recess is equipped with the shaping and has the first spacer strip of a plurality of evenly distributed range, and the clearance between the first spacer strip of a plurality of evenly distributed range constitutes first thing groove of putting, the inside left side department shaping of first press from both sides shell has the screw siphunculus, and the inside cover of screw siphunculus has connecting screw, second press from both sides shell surface shaping has the second recess, and the inside bottom shaping of second recess has the second spacer strip of a plurality of evenly distributed range, the clearance between the second spacer strip of a plurality of evenly distributed range constitutes the second and puts the thing groove, the inside left side department shaping of second press from both sides shell has the screw siphunculus.

Description

Aircraft steel wire cutting clamp

Technical Field

The utility model belongs to the technical field of aircraft steel and specifically relates to an aircraft steel line cuts anchor clamps is related to.

Background

The wire cutting process for metal steel is a common process, and has high requirements on the stability and accuracy of wire cutting of steel, so that the steel is often required to be clamped and positioned, and wire cutting equipment is convenient to perform wire cutting on the steel. In the production process, steel materials in various shapes can be cut in a line mode, so that the production requirements can be met. Therefore, the positioning clamp corresponding to the steel products in various shapes needs to be designed to accurately position the steel products, but the steel products are usually placed by only adopting one large fixing groove and are fixed, so that the positioning precision is not accurate enough, the stability and the accuracy of the wire cutting equipment for processing the steel products are influenced, and the airplane steel wire cutting clamp is provided.

SUMMERY OF THE UTILITY MODEL

The utility model discloses an it is not enough to overcome above-mentioned condition, aims at providing the technical scheme that can solve above-mentioned problem.

An aircraft steel wire cutting clamp comprises a first clamping shell, a second clamping shell and hinges, wherein a first groove is formed in the middle of the bottom surface of the first clamping shell, a plurality of first partition strips which are uniformly distributed and arranged are formed in the top end of the interior of the first groove, a first storage groove is formed by gaps among the plurality of first partition strips which are uniformly distributed and arranged, a screw through pipe is formed in the left side of the interior of the first clamping shell, a connecting screw is sleeved in the screw through pipe, a third groove is formed in the bottom end of the right side of the bottom surface of the first clamping shell, the hinges are welded in the third groove, and the top end of each hinge is located in the third groove; first double-layered shell rotates with the second double-layered shell through the hinge to be connected, and the right side department shaping on second double-layered shell surface has the fourth recess to the bottom of hinge welds in the fourth recess, makes first double-layered shell can turn on the surface of second double-layered shell, second double-layered shell surface shaping has the second recess, and the inside bottom shaping of second recess has the second spacer strip that a plurality of evenly distributed arranged, clearance between the second spacer strip that a plurality of evenly distributed arranged constitutes the second and puts the thing groove, the inside left side department shaping of second double-layered shell has the screw siphunculus.

Preferably, the screw through pipe is in threaded fixed fit with the connecting screw.

Compared with the prior art, the beneficial effects of the utility model are that: the first object containing groove and the second object containing groove formed by the first object separating strip and the second object separating strip are used for fixing aircraft steel needing to be processed, and then a plurality of connecting screws are used for fixing the clamping shell, so that the clamp has higher positioning accuracy, the defect that the conventional positioning clamp is insufficient in precision is overcome, and the wire cutting equipment is convenient to perform accurate positioning processing on the aircraft steel.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.

FIG. 1 is a schematic structural view of an aircraft steel wire cutting jig;

fig. 2 is an exploded view of an aircraft steel wire cutting fixture.

Shown in the figure: 1. the first clamping shell, 2, a first groove, 3, a connecting screw, 4, a first partition strip, 5, a second clamping shell, 6, a hinge, 7, a second groove, 8, a second partition strip, 9, a screw through pipe, 10, a first object placing groove, 11, a third groove, 12, a fourth groove, 13 and a second object placing groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-2, in an embodiment of the present invention, an aircraft steel wire cutting fixture includes a first clamping shell 1, a second clamping shell 5 and a hinge 6, a first groove 2 is formed in a middle position of a bottom surface of the first clamping shell 1, a plurality of first spacer strips 4 are uniformly distributed and arranged on a top end inside the first groove 2, a first object placing groove 10 is formed in a gap between the plurality of first spacer strips 4 uniformly distributed and arranged, so that aircraft steel is placed, a screw through pipe 9 is formed in a left side inside the first clamping shell 1, a connecting screw 3 is sleeved inside the screw through pipe 9, a third groove 11 is formed in a bottom end on a right side of the bottom surface of the first clamping shell 1, a hinge 6 is welded inside the third groove 11, and a top end of the hinge 6 is located in the third groove 11.

The first clamping shell 1 is rotatably connected with the second clamping shell 5 through a hinge 6, a fourth groove 12 is formed in the right side of the surface of the second clamping shell 5, the bottom end of the hinge 6 is welded in the fourth groove 12, so that the first clamping shell 1 can be turned over on the surface of the second clamping shell 5, a second groove 7 is formed in the surface of the second clamping shell 5, a plurality of second partition strips 8 are uniformly distributed and arranged at the bottom end inside the second groove 7, a second storage groove 13 is formed by gaps among the plurality of second partition strips 8 uniformly distributed and arranged so as to facilitate the placement of steel, a screw through pipe 9 is formed at the left side inside the second clamping shell 5, when the first clamping shell 1 is covered on the second clamping shell 5, a connecting screw 3 on the first clamping shell 1 can be inserted into the screw through pipe 9, and the screw through pipe 9 is in threaded fixed fit with the connecting screw 3, thereby fixing the steel material in the first and

second pods

1, 5.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.

Claims

1. An aircraft steel wire cutting clamp comprises a first clamping shell, a second clamping shell and a hinge, and is characterized in that a first groove is formed in the middle of the bottom surface of the first clamping shell, a plurality of first partition strips which are uniformly distributed and arranged are formed at the top end of the interior of the first groove, a first object placing groove is formed by gaps among the first partition strips which are uniformly distributed and arranged, a screw through pipe is formed at the left side of the interior of the first clamping shell, a connecting screw is sleeved in the screw through pipe, a third groove is formed at the bottom end of the right side of the bottom surface of the first clamping shell, the hinge is welded in the third groove, and the top end of the hinge is located in the third groove;

first double-layered shell rotates with the second double-layered shell through the hinge to be connected, and the right side department shaping on second double-layered shell surface has the fourth recess to the bottom of hinge welds in the fourth recess, makes first double-layered shell can turn on the surface of second double-layered shell, second double-layered shell surface shaping has the second recess, and the inside bottom shaping of second recess has the second spacer strip that a plurality of evenly distributed arranged, clearance between the second spacer strip that a plurality of evenly distributed arranged constitutes the second and puts the thing groove, the inside left side department shaping of second double-layered shell has the screw siphunculus.

2. An aircraft steel wire cutting fixture as claimed in claim 1, wherein the screw through tube is in threaded fixed engagement with the connection screw.