CN219114823U

CN219114823U - Bonding tool for composite material and reinforcing rib of airplane beam

Info

Publication number: CN219114823U
Application number: CN202223536342.4U
Authority: CN
Inventors: 赵维
Original assignee: Chengdu Jialun Machinery Co ltd
Current assignee: Chengdu Jialun Machinery Co ltd
Priority date: 2022-12-29
Filing date: 2022-12-29
Publication date: 2023-06-02
Anticipated expiration: 2032-12-29

Abstract

The utility model relates to the technical field of processing equipment, and provides an adhesion tool for composite materials and reinforcing ribs of an aircraft beam, which comprises a base and a limiting frame, wherein a plurality of pressing mechanisms are arranged on the outer side of the limiting frame and are arranged at intervals along the circumferential direction; the compressing mechanism comprises a transverse plate, a fixed disc, a guide rod, a limiting plate and a pressure spring, wherein the transverse plate is arranged above the base and fixedly connected with the base, the fixed disc is fixedly arranged at the top of the transverse plate, a guide hole which transversely penetrates through the fixed disc is formed in the fixed disc, the guide rod is arranged in the guide hole and is in sliding connection with the inner wall of the guide hole, the limiting plate is arranged between the guide rod and the limiting frame and is fixedly connected with the guide rod, an inwards extending limiting groove is formed in the outer side face of the limiting plate and is adaptive to the reinforcing rib, and the pressure spring is sleeved on the guide rod and enables the guide rod to have a trend of approaching the limiting frame.

Description

Bonding tool for composite material and reinforcing rib of airplane beam

Technical Field

The utility model relates to the technical field of processing equipment, in particular to an adhesion tool for a composite material and a reinforcing rib of an aircraft beam.

Background

The composite material is a composite material, and has special positions in the aerospace field in terms of high specific strength, high specific modulus, heat resistance, ablation resistance, light weight, electric conduction, heat conduction and other performances. The bonding molding of the composite material and the reinforcing ribs has important significance for improving the strength of the composite material.

The Chinese patent of patent No. CN207454465U discloses a bonding tool for bonding a composite material of an airplane beam and a reinforcing rib, which can assist a worker to bond the reinforcing rib on the composite material. But it is easy for the reinforcing bars to fall off between the composite material and the screw when in use.

Disclosure of Invention

Aiming at the defects in the prior art, the utility model aims to provide an adhesion tool for a composite material and a reinforcing rib of an aircraft beam, so that the reinforcing rib is not easy to fall off from between the composite material and a screw when the adhesion tool is used.

In order to achieve the above object, the present utility model is realized by the following technical scheme: the bonding tool for the composite material and the reinforcing ribs of the airplane beam comprises a base and a limiting frame, wherein a plurality of pressing mechanisms are arranged on the outer side of the limiting frame, and are arranged at intervals along the circumferential direction;

the compressing mechanism comprises a transverse plate, a fixed disc, a guide rod, a limit plate and a pressure spring, wherein the transverse plate is arranged above the base and fixedly connected with the base, the fixed disc is fixedly arranged at the top of the transverse plate, a guide hole penetrating transversely is formed in the fixed disc, the guide rod is arranged in the guide hole and is in sliding connection with the inner wall of the guide hole, the limit plate is arranged between the guide rod and the limit frame and is fixedly connected with the guide rod, an inwards extending limit groove is formed in the outer side face of the limit plate and is matched with the reinforcing rib, and the pressure spring is sleeved on the guide rod and enables the guide rod to have a trend of approaching the limit frame.

Further, the compressing mechanism further comprises a locking column and a locking plate, the locking column is fixedly arranged at the top of the fixed disc, a first end of the locking plate is rotationally connected with the fixed disc, and a second end of the locking plate is provided with a locking hole which is matched with the locking column.

Further, a rubber pad is fixedly arranged on the inner wall of the limiting groove.

Further, the number of the pressing mechanisms is 6-8.

Further, the pressing mechanism is made of steel materials.

The utility model has the beneficial effects that: according to the bonding tool for the composite material and the reinforcing rib of the airplane beam, provided by the utility model, the limiting groove is designed to prevent the reinforcing rib from falling from between the composite material and the screw. The pressure spring can continuously provide pressure to enable the reinforcing ribs to be pressed on the outer wall of the composite material and matched with glue, so that the composite material and the reinforcing ribs are stably bonded together.

Drawings

FIG. 1 is a schematic perspective view of the present utility model;

FIG. 2 is a schematic elevational view of the present utility model;

fig. 3 is a schematic perspective view of the pressing mechanism.

Reference numerals: 10-base, 20-limit frame, 30-hold-down mechanism, 31-diaphragm, 311-connecting rod, 32-fixed disk, 33-guide bar, 34-limit plate, 35-pressure spring, 36-guiding hole, 37-limit groove, 38-locking post, 39-locking plate.

Detailed Description

The utility model is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the utility model easy to understand.

In the present application, unless explicitly specified and limited otherwise, the terms "coupled," "affixed" and "fixedly attached" are to be construed broadly, and may be, for example, fixedly attached, detachably attached, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

In the description of the present application, it should be understood that the terms "longitudinal," "transverse," "horizontal," "top," "bottom," "upper," "lower," "inner" and "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present utility model and simplify the description, and do not indicate or imply that the tools or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present utility model.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. In the description of the present utility model, the meaning of "plurality" is two or more unless specifically defined otherwise.

As shown in fig. 1-3, the utility model provides an adhesion fixture for composite materials and reinforcing ribs of an aircraft beam, which comprises a base 10 and a limiting frame 20. The outside of spacing frame 20 is provided with a plurality of hold-down mechanisms 30, and a plurality of hold-down mechanisms 30, a plurality of hold-down mechanisms 30 are arranged along the circumference of spacing frame 20 at intervals in proper order.

The pressing mechanism 30 includes a cross plate 31, a fixed plate 32, a guide rod 33, a limiting plate 34, and a compression spring 35. The cross plate 31 is disposed above the base 10 and is fixedly connected with the base 10 through a connecting rod 311. The fixed disk 32 is fixedly installed on the top of the transverse plate 31, and a guide hole 36 penetrating transversely is formed in the fixed disk 32. The guide rod 33 is disposed in the guide hole 36 in the lateral direction and slidably connected to the inner wall of the guide hole 36. The limiting plate 34 is arranged between the guide rod 33 and the limiting frame 20 and is fixedly connected with the guide rod 33, the outer side surface of the limiting plate 34 is provided with a limiting groove 37 extending inwards, and the limiting groove 37 is adapted to the reinforcing rib. The pressure spring 35 is sleeved on the guide rod 33, the first end of the pressure spring 35 is in contact with the limiting plate 34, the second end of the pressure spring 35 is in contact with the fixed disc 32, and the pressure spring 35 enables the guide rod 33 to have a trend of approaching the limiting frame 20.

The specific using process is as follows: firstly, a worker sleeves the composite material on the periphery of the limiting frame 20, and glue is coated on the corresponding position of the outer wall of the limiting frame 20; then, the worker places the reinforcing ribs in the corresponding limiting grooves 37, and the design of the limiting grooves 37 can prevent the reinforcing ribs from falling from between the composite material and the screws; then, under the action of the pressure spring 35, the limit plate 34 compresses the reinforcing ribs on the outer wall of the composite material, and the composite material and the reinforcing ribs are stably bonded together by matching with glue.

In one embodiment, the hold down mechanism 30 further includes a locking post 38 and a locking plate 39. A locking post 38 is fixedly mounted on top of the fixed disk 32. The locking plate 39 is arranged above the limiting plate 34 in the transverse direction, a first end of the locking plate 39 is rotatably connected with the fixed disk 32, and a second end of the locking plate 39 is provided with a locking hole which is matched with the locking column 38.

In the initial state, the limit posts are matched with the limit holes on the locking plate 39, and in this time, the compression springs 35 are compressed, so that the staff can conveniently place the reinforcing ribs in the limit grooves 37.

After the reinforcing ribs are placed in the limiting grooves 37, a worker rotates the locking plate 39, so that the limiting holes are separated from contact with the limiting columns, and at the moment, the reinforcing ribs are pressed on the outer wall of the composite material by the limiting plate 34 under the action of the pressure springs 35.

In one embodiment, a rubber pad is fixedly mounted on the inner wall of the limiting groove 37. The friction force between the rubber pad and the reinforcing rib is larger, so that the reinforcing rib can be stably limited in the limiting groove 37, the work of the tool is more stable,

in one embodiment, the number of hold-down mechanisms 30 is 6-8.

In one embodiment, the components of the hold-down mechanism 30 are all made of steel material.

While the fundamental and principal features of the utility model and advantages of the utility model have been shown and described, it will be apparent to those skilled in the art that the utility model is not limited to the details of the foregoing exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model 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.

Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.

Claims

1. The utility model provides an adhesion frock of composite material and strengthening rib of aircraft roof beam, includes base and spacing frame, its characterized in that: the outer side of the limiting frame is provided with a plurality of pressing mechanisms, the pressing mechanisms are arranged at intervals along the circumferential direction;

2. The bonding tool for composite materials and reinforcing ribs of an aircraft beam according to claim 1, wherein the bonding tool is characterized in that: the pressing mechanism further comprises a locking column and a locking plate, the locking column is fixedly arranged at the top of the fixed disc, the first end of the locking plate is rotationally connected with the fixed disc, and the second end of the locking plate is provided with a locking hole which is adaptive to the locking column.

3. The bonding tool for composite materials and reinforcing ribs of an aircraft beam according to claim 1, wherein the bonding tool is characterized in that: and a rubber pad is fixedly arranged on the inner wall of the limiting groove.

4. The bonding tool for composite materials and reinforcing ribs of an aircraft beam according to claim 1, wherein the bonding tool is characterized in that: the number of the pressing mechanisms is 6-8.

5. The bonding tool for composite materials and reinforcing ribs of an aircraft beam according to claim 1, wherein the bonding tool is characterized in that: the pressing mechanism is made of steel materials.