CN214135644U

CN214135644U - Novel integral type aircraft nose positioning fixture

Info

Publication number: CN214135644U
Application number: CN202021581012.5U
Authority: CN
Inventors: 魏章淼; 何纪江
Original assignee: Zhejiang Zhaohan Electromechanical Co ltd
Current assignee: Zhejiang Zhaohan Electromechanical Co ltd
Priority date: 2020-08-03
Filing date: 2020-08-03
Publication date: 2021-09-07
Anticipated expiration: 2030-08-03

Abstract

The utility model discloses a novel integral type aircraft nose positioning fixture, its characterized in that: the machine head positioning clamp is arranged on the reference surface of the shuttle box body and comprises a handle, a lower shaft clamping block, a longitudinal control positioning device, a transverse control positioning device, a handle and a lower shaft clamping block, wherein the lower shaft clamping block is clamped with a lower shaft. The utility model discloses can solve the weak point that exists among the prior art, the structure is simpler, and it is more convenient to operate, and height, the head of aircraft nose are apart from unified, and do not receive the human error influence, and positioning accuracy and installation effectiveness are higher.

Description

Novel integral type aircraft nose positioning fixture

Technical Field

The utility model relates to a novel integral type aircraft nose positioning fixture.

Background

In the existing assembly process, the height and the verticality of the machine head relative to the shuttle box body and the distance between vertical projections are controlled through a measuring tape and a height dial indicator. The assembly mode has low efficiency and large personal error, and particularly under the condition that the number of the machine heads is large, the accumulated error is larger, so that the precision of equipment is influenced; the applicant provides further improvement on the basis and designs a novel integrated machine head positioning clamp so as to meet the requirements of the existing market.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is to overcome current defect, provide a novel integral type aircraft nose positioning fixture, the structure is simpler, and it is more convenient to operate, and height, the head of aircraft nose are apart from unified, and do not receive human error to influence, and positioning accuracy and installation effectiveness are higher.

In order to solve the technical problem, the utility model provides a following technical scheme:

the utility model provides a novel integral type aircraft nose positioning fixture which characterized in that: the machine head positioning clamp is arranged on the reference surface of the shuttle box body and comprises a handle, a lower shaft clamping block, a longitudinal control positioning device, a transverse control positioning device, a handle and a lower shaft clamping block, wherein the lower shaft clamping block is clamped with a lower shaft.

It is right to the utility model discloses do further optimization, longitudinal control positioner includes the anchor clamps base, sets up high benchmark piece on the anchor clamps base, with the shuttle box body benchmark guide rail of the laminating of anchor clamps base below both sides, with the pearl frame guide rail clamp splice of the laminating of high benchmark piece top to and the tight fork in pearl frame guide rail top.

It is right the utility model discloses do further optimization, be equipped with a plurality of base through holes on the anchor clamps base, the height reference piece is equipped with transverse through hole and two location through holes, be equipped with the stubborn mouth of a tight perforation in top, two location through holes and cooperation pearl frame guide rail on the pearl frame guide rail clamp splice.

Right the utility model discloses do further optimization, the tight perforation inside in top is equipped with the internal thread.

To the utility model discloses do further optimization, be equipped with on the tight fork in pearl rack guide rail top and perforate complex external screw thread with fixed gold.

Right the utility model discloses do further optimization, lateral control positioner is including setting up at driving shaft benchmark fork and rotating shuttle axle position sleeve.

It is right to the utility model discloses do further optimization, driving shaft benchmark fork runs through the axle sleeve, driving shaft benchmark fork one end be equipped with driving shaft complex semi-circular ring cover.

Right the utility model discloses do further optimization, rotating shuttle axle position sleeve and rotating shuttle axle cooperation, and rotating shuttle axle position sleeve establishes rotating shuttle is epaxial, and the last plane of rotating shuttle axle position sleeve and the lower plane laminating of anchor clamps base.

Compared with the prior art the utility model discloses the beneficial effect who reaches is:

the utility model relates to a aircraft nose location integral type anchor clamps, aircraft nose positioning fixture of above-mentioned structure, through shuttle box benchmark guide rail, the anchor clamps base, high reference block, pearl frame guide rail clamp splice turn into the lower reference plane of pearl frame guide rail clamp splice with the locating surface on the aircraft nose installation benchmark shuttle box, and interval control between the reference plane on pearl frame guide rail clamp splice notch lower reference plane and the shuttle box the aircraft nose for the height of shuttle box, and through driving shaft benchmark fork, thereby two points at a thread and controlled the transverse position of aircraft nose and guaranteed the straightness that hangs down with rotating shuttle axle center by rotating shuttle axle position sleeve control needle bar driving shaft center, the utility model discloses well structure is very simple to the structure is comparatively firm, and is accurate effective, can simply control the adjustment and the control of the perpendicular of aircraft nose and horizontally distance.

According to the above, the utility model discloses can solve the weak point that exists among the prior art, the structure is simpler, and it is more convenient to operate, and height, the head of aircraft nose are apart from unified, and do not receive human error to influence, and positioning accuracy and installation effectiveness are higher.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention.

In the drawings:

fig. 1 is an exploded view of the present invention;

fig. 2 is a front view of the present invention;

FIG. 3 is a schematic view of the circled portion of FIG. 2;

fig. 4 is a partial structural schematic view of the embroidery machine;

fig. 5 is a schematic structural diagram of a circled portion in fig. 4.

Detailed Description

The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are presented herein only to illustrate and explain the present invention, and not to limit the present invention.

As shown in fig. 1-5, the utility model relates to a novel integral type aircraft nose positioning fixture, its characterized in that: the machine head positioning clamp is arranged on the reference surface of the shuttle box body 12 and comprises a handle 4, a lower shaft clamping block 7, a longitudinal control positioning device, a transverse control positioning device, a handle 4, a lower shaft clamping block 7, and a lower shaft 11 clamped by the lower shaft clamping block 7.

It is right to the utility model discloses do further optimization, longitudinal control positioner includes that anchor clamps base 1 sets up high benchmark piece 2 on the anchor clamps base 1, with the shuttle box benchmark guide rail 8 of the laminating of 1 below both sides of anchor clamps base, with the pearl frame guide rail clamp splice 5 of the laminating of 2 tops of high benchmark piece to and the tight fork 10 in 14 tops of pearl frame guide rail. The utility model discloses in the laminating of the datum plane of shuttle box body datum guide rail 8 and shuttle box body 12.

It is right the utility model discloses do further optimization, be equipped with a plurality of base through holes on the anchor clamps base 1, the height reference piece is equipped with transverse through hole and two location through holes, be equipped with a tight perforation in top, two location through holes and the stubborn mouth of cooperation pearl frame guide rail 14 on the pearl frame guide rail clamp splice 5. The utility model discloses in the laminating of the lower reference surface of the pergola guide rail 14 lower surface of aircraft nose and pergola guide rail clamp splice 5 stubborn for the aircraft nose can be more firm, and height reference block and pergola guide rail clamp splice 5 can fix a position through the location through hole, make both connect the fastening, also convenient change to height reference block simultaneously.

The utility model is further optimized, the bead frame guide rail 14 is tightly supported on the fork 10 and is provided with an external thread which is matched with the fixed metal through hole. The utility model discloses in tight fork 10 in pearl frame guide rail 14 top can push up tightly through the screw thread rotation pearl frame guide rail 14 and pearl frame guide rail clamp splice 5 for in the course of the work, highly carry out auxiliary control and guarantee can not change in operation Qijiang to the aircraft nose, guaranteed the precision and the quality of embroidery product.

It is right to the utility model discloses do further optimization, lateral control positioner is including setting up at driving shaft benchmark fork 9 and rotating shuttle axle 13 position sleeve 6.

It is right to the utility model discloses do further optimization, driving shaft benchmark fork 9 runs through

axle sleeve

3, 9 one ends of driving shaft benchmark fork are equipped with the 15 complex semi-circular ring covers of driving shaft. The utility model discloses in driving shaft benchmark fork 9 is equipped with the semi-circular ring cover of driving shaft 15 complex, can block into driving shaft 15, can carry out the transverse adjustment to the aircraft nose.

Right the utility model discloses do further optimization, 13 position sleeves 6 of rotating shuttle axle cooperate with 13 of rotating shuttle axle, and 6 covers of 13 position sleeves of rotating shuttle axle are established on 13 of rotating shuttle axle, and the last plane of 13 position sleeves 6 of rotating shuttle axle laminates with the lower plane of anchor clamps base 1.

In the installation process, the rear positioning surface of the machine head is only required to be attached to the installation surface of the machine head plate, the whole clamp is placed on the reference surface of the shuttle box body 12, the reference guide rail 8 of the shuttle box body is attached to the reference surface of the shuttle box body 12, the lower surface of the bead frame guide rail 14 of the machine head is attached to the lower reference plane of the notch of the bead frame guide rail clamping block 5, the bead frame guide rail 14 is used for tightly jacking the fork 10, the lower shaft clamping block 7 is clamped into the lower shaft 11, the rotating shuttle shaft 13 is sleeved with the positioning sleeve 6 of the rotating shuttle shaft 13, and the driving shaft reference fork 9 is used for clamping the driving shaft 15, so that the machine head can be fixed through bolts. Compared with the mode of positioning the machine head through the tape measure and the height dial indicator in the prior art, the structure is simpler, the operation is more convenient, the height and the head distance of the machine head are unified, the influence of human errors is avoided, and the positioning precision and the installation efficiency are higher.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides a novel integral type aircraft nose positioning fixture which characterized in that: the machine head positioning clamp is arranged on the reference surface of the shuttle box body and comprises a handle, a lower shaft clamping block, a longitudinal control positioning device, a transverse control positioning device, a handle and a lower shaft clamping block, wherein the lower shaft clamping block is clamped with a lower shaft.

2. The novel integrated machine head positioning clamp of claim 1, which is characterized in that: the longitudinal control positioning device comprises a clamp base, a height reference block arranged on the clamp base, a shuttle box body reference guide rail attached to two sides below the clamp base, a bead frame guide rail clamping block attached to the upper side of the height reference block, and a bead frame guide rail jacking fork.

3. The novel integrated machine head positioning clamp as claimed in claim 2, wherein: the fixture comprises a fixture base, and is characterized in that a plurality of base through holes are formed in the fixture base, a transverse through hole and two positioning through holes are formed in a height reference block, and a fastening through hole, two positioning through holes and a notch matched with a bead frame guide rail are formed in a bead frame guide rail clamping block.

4. The novel integrated machine head positioning clamp as claimed in claim 3, wherein: and internal threads are arranged inside the jacking through holes.

5. The novel integrated machine head positioning clamp as claimed in claim 2, wherein: and the bead frame guide rail tightening fork is provided with an external thread matched with the fixed metal through hole.

6. The novel integrated machine head positioning clamp of claim 1, which is characterized in that: the transverse control positioning device comprises a driving shaft reference fork and a rotating shuttle shaft positioning sleeve.

7. The novel integrated machine head positioning clamp as claimed in claim 6, wherein: the driving shaft reference fork penetrates through the shaft sleeve, and a semicircular ring sleeve matched with the driving shaft is arranged at one end of the driving shaft reference fork.

8. The novel integrated machine head positioning clamp as claimed in claim 6, wherein: the rotating shuttle shaft positioning sleeve is matched with the rotating shuttle shaft, the rotating shuttle shaft positioning sleeve is sleeved on the rotating shuttle shaft, and the upper plane of the rotating shuttle shaft positioning sleeve is attached to the lower plane of the clamp base.