CN218875623U

CN218875623U - Quick cutting fixture for airplane I-shaped stringer

Info

Publication number: CN218875623U
Application number: CN202320120559.2U
Authority: CN
Inventors: 薛奥; 刘晓雪; 许桐; 林超; 蒋纯瑶
Original assignee: Guanglian Aviation Industry Co ltd
Current assignee: Guanglian Aviation Industry Co ltd
Priority date: 2023-01-16
Filing date: 2023-01-16
Publication date: 2023-04-18
Anticipated expiration: 2033-01-16

Abstract

The utility model provides a quick cutting jig of aircraft I-shaped stringer, belongs to the aviation field, and the concrete scheme is as follows: the quick cutting fixture for the I-shaped airplane stringer comprises two outer side plates and two inner side plates, wherein the two outer side plates are fixedly arranged on two opposite outer side surfaces of a forming die of the I-shaped airplane stringer respectively, the two inner side plates are fixedly arranged on two opposite inner side surfaces of the two outer side plates respectively, two side edge strips of the I-shaped airplane stringer are fixedly arranged between the outer side plates and the inner side plates on two sides of the forming die respectively, and surface profiles of the two outer side plates and surface profiles of the two inner side plates are consistent with surface profiles of corresponding side edge strips of the I-shaped airplane stringer. The utility model can improve the precision requirement of composite material cutting and ensure the production quality; the scrap rate of the tool is reduced, and the cost is reduced; the use mode is convenient, the manufacturing cost is low, and the utilization rate is high.

Description

Quick cutting fixture for airplane I-shaped stringer

Technical Field

The utility model belongs to the aviation field especially relates to an aircraft I-shaped stringer fly-cutting anchor clamps.

Background

Composite materials are widely used in aerospace products, and their main benefits are weight reduction, ease of assembly, and performance advantages and reduced aircraft structural weight are the primary driving forces for the development of military aircraft composite materials.

Stringers, also known as stringers, are members that connect the skin and ribs, and are subjected to aerodynamic loads, torsional loads, and the like. In modern wings, the part of axial force caused by wing bending moment is one of important stress components in longitudinal skeleton. In addition to the force bearing function, the stringer and the rib play a certain supporting role for the skin together.

The composite material is hot-pressed and molded on the tool through hot-pressing glue, a product formed by the composite material needs to be cut according to process requirements to remove redundant rim charge, but the existing cutting method comprises the steps of manually marking and cutting by using a measuring tool according to the drawing size and marking and cutting according to the reservation of a molding tool, the two methods have the problems of low precision, large deviation and high operation working hour, cutting burrs are easily generated on the surface of a part, and the part has poor surface quality, ultra-poor appearance, longer production period and low production efficiency. The line of cut is reserved on shaping frock and when carrying out manual cutting can cause the damage of different degrees to shaping frock surface, and the precision value that the product surface can not reach the demand when can leading to the secondary to use also does not benefit to batch production's demand.

Disclosure of Invention

In order to simplify the operation process of cutting edge among the prior art to aircraft I-shaped stringer part, guarantee simultaneously that part edge cutting precision is high, surface quality is good, the utility model provides an aircraft I-shaped stringer fly-cutting anchor clamps guarantees the part qualification rate more than 95%.

The purpose is achieved, the utility model adopts the following technical proposal:

the quick cutting clamp for the aircraft I-shaped stringer comprises two outer side plates and two inner side plates, wherein the two outer side plates are fixedly arranged on two opposite outer side surfaces of a forming die of the aircraft I-shaped stringer respectively, the two inner side plates are fixedly arranged on two opposite inner side surfaces of the two outer side plates respectively, two side flanges of the aircraft I-shaped stringer are fixedly arranged between the outer side plates and the inner side plates on two sides of the forming die respectively, and surface profiles of the two outer side plates and surface profiles of the two inner side plates are consistent with surface profiles of corresponding side flanges of the aircraft I-shaped stringer.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model can improve the precision requirement of composite material cutting and ensure the production quality; the scrap rate of the tool is reduced, and the cost is reduced; the use mode is convenient, the manufacturing cost is low, and the utilization rate is high.

Drawings

FIG. 1 is a schematic view of a rapid cutting fixture for an I-shaped stringer of an aircraft according to the present invention;

FIG. 2 is a top view of FIG. 1;

FIG. 3 is an enlarged end view of the aircraft I-beam fly cutting fixture;

FIG. 4 is a schematic structural view of a cutting positioning assembly I;

FIG. 5 is a schematic structural view of a cutting positioning assembly II;

FIG. 6 is a top plan view of an aircraft carrier stringer;

FIG. 7 is a cross-sectional view of an aircraft carrier stringer;

fig. 1, an outer side plate, 2, an inner side plate, 3, a forming die, 4, an aircraft I-shaped stringer, 5, positioning pins I, 6, cutting positioning components I, 7, positioning pins II, 8, cutting positioning components II, 9, positioning pins III, 41, a flange strip, 42 and a middle beam.

Detailed Description

The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiments of the present invention, but not all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the scope of the present invention based on the embodiments of the present invention.

Example 1:

a quick cutting clamp for an airplane I-shaped stringer comprises two outer side plates 1 and two inner side plates 2, wherein the two outer side plates 1 are fixedly arranged on two opposite outer side surfaces of an airplane I-shaped stringer forming die 3 respectively, the two inner side plates 2 are fixedly arranged on two opposite inner side surfaces of the two outer side plates 1 respectively, two side edge strips 41 of the airplane I-shaped stringer 4 are fixedly arranged between the outer side plates 1 and the inner side plates 2 on two sides of the forming die 3 respectively, and surface profiles of the two outer side plates 1 and surface profiles of the two inner side plates 2 are consistent with surface profiles of the corresponding side edge strips 41 of the airplane I-shaped stringer 4.

Further, coaxial locating holes are formed in the two outer side plates 1 and the two inner side plates 2, and the locating pin I5 penetrates through the locating holes to fix the two outer side plates 1 and the two inner side plates 2 on two sides of the forming die 3 respectively.

Further, the rapid cutting fixture further comprises a cutting positioning assembly I6, the cutting positioning assembly I6 is located at the end of the aircraft I-shaped truss 4 and fixed on the forming die 3 or the two outer side plates 1 through a positioning pin II 7, the middle beam 42 of the aircraft I-shaped truss 4 is located between the cutting positioning assembly I6 and the forming die 3, and the end of the part is cut at the edge line of the cutting positioning assembly I6 through a cutter manually.

Further, the rapid cutting fixture further comprises a cutting positioning assembly II 8, the cutting positioning assembly II 8 is located at the tail of the aircraft I-shaped truss 4 and fixed on the forming die 3 or the two outer side plates 1 through a positioning pin III 9, the middle beam 42 of the aircraft I-shaped truss 4 is located between the cutting positioning assembly II 8 and the forming die 3, and the tail of the part is cut at the edge line of the cutting positioning assembly II 8 through a cutter manually.

Furthermore, the planes of the upper surfaces of one of the outer side plates 1 and the corresponding inner side plate 2 are both inclined downwards and form an included angle of 30 degrees with the horizontal plane, and the upper surfaces of the other one of the outer side plates 1 and the corresponding inner side plate 2 are both horizontal planes. The inclination of the upper surfaces of the two outer panels 1 and of the two inner panels 2 is identical to the inclination of the upper surfaces of the two flanges of the aircraft stringers 4, and the parts are trimmed along the upper surfaces of the outer panels 1 and of the inner panels 2.

Further, the rapid cutting fixture further comprises at least one clip, and the at least one clip is clamped in the middle of the outer side plate 1 and the inner side plate 2 on the same side, so that the outer side plate 1 is tightly attached to the inner side plate 2. In specific implementation, after the solidification of the aircraft I-shaped stringer 4 is completed, the upper half die of the forming die 3 is demoulded when the shapes of the edge strips 41 on the two sides of the aircraft I-shaped stringer 4 are cut, the outer side plate 1, the inner side plate 2 and the positioning holes reserved on the forming die 3 are installed in a matched mode through the positioning pins I5, due to the fact that the lengths of the stringers are different, the middle position can be clamped by the aid of the C-shaped clamps when the lengths are too long, the shapes of the stringer edge strips 41 can be cut after the installation is completed, the upper half die of the forming die is reassembled after one-side cutting is completed, and then the lower half die of the forming die is demoulded and is installed with the quick cutting clamp for cutting according to the method, as shown in fig. 3. When the end and the tail of the stringer are cut, the cutting positioning assembly I6 and the cutting positioning assembly II 8 are installed at the reserved mounting holes of the end and the tail of the lower half die of the forming die 3 and are installed in a matched mode through the positioning pin II 7 and the positioning pin III 9, the reserved hand-screwed nuts on the workpiece are clamped tightly after the position is fixed, and the end and the tail of the stringer are cut after the installation is finished, as shown in figures 4 and 5.

The utility model discloses can realize the cutting of multiple I-shaped stringer.

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 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. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides a quick cutting anchor clamps of aircraft I-shaped stringer which characterized in that: the forming die comprises two outer side plates (1) and two inner side plates (2), wherein the two outer side plates (1) are fixedly arranged on two opposite outer side surfaces of a forming die (3) of an airplane I-shaped stringer (4) respectively, the two inner side plates (2) are fixedly arranged on two opposite inner side surfaces of the two outer side plates (1) respectively, two side edge strips (41) of the airplane I-shaped stringer (4) are fixedly arranged between the outer side plates (1) and the inner side plates (2) on two sides of the forming die (3) respectively, and surface profiles of the two outer side plates (1) and surface profiles of the two inner side plates (2) are consistent with surface profiles of the corresponding side edge strips (41) of the airplane I-shaped stringer (4).

2. The aircraft stringer fly-cutting fixture of claim 1, wherein: the two outer side plates (1) and the two inner side plates (2) are provided with coaxial positioning holes, and the positioning pin I (5) penetrates through the positioning holes to fix the two outer side plates (1) and the two inner side plates (2) on two sides of the forming die (3) respectively.

3. The aircraft stringer fly-cutting fixture of claim 1, wherein: the rapid cutting fixture further comprises a cutting positioning assembly I (6), the cutting positioning assembly I (6) is located at the end of the aircraft I-shaped truss (4) and fixed on the forming die (3) or the two outer side plates (1) through a positioning pin II (7), and the middle beam (42) of the aircraft I-shaped truss (4) is located between the cutting positioning assembly I (6) and the forming die (3).

4. The aircraft stringer fly-cutting fixture of claim 1, wherein: the rapid cutting fixture further comprises a cutting positioning assembly II (8), the cutting positioning assembly II (8) is located at the tail of the aircraft I-shaped truss (4) and fixed on the forming die (3) or the two outer side plates (1) through a positioning pin III (9), and the middle beam (42) of the aircraft I-shaped truss (4) is located between the cutting positioning assembly II (8) and the forming die (3).

5. The aircraft stringer fly-cutting fixture of claim 1, wherein: the planes of the upper surfaces of one of the outer side plates (1) and the corresponding inner side plates (2) are all inclined downwards and form an included angle of 30 degrees with the horizontal plane, and the upper surfaces of the other outer side plate (1) and the corresponding inner side plate (2) are all horizontal planes.

6. The aircraft stringer fly-cutting fixture of claim 1, wherein: the rapid cutting clamp further comprises at least one clamp, and the at least one clamp is clamped in the middle of the outer side plate (1) and the inner side plate (2) on the same side.