CN216032029U - Composite material's pressure forming device for aircraft - Google Patents
Composite material's pressure forming device for aircraft Download PDFInfo
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- CN216032029U CN216032029U CN202122363271.1U CN202122363271U CN216032029U CN 216032029 U CN216032029 U CN 216032029U CN 202122363271 U CN202122363271 U CN 202122363271U CN 216032029 U CN216032029 U CN 216032029U
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Abstract
The utility model discloses a composite material pressurization forming device for an aircraft, which relates to the technical field of pressurization forming devices and aims to solve the problems that a traditional demolding mechanism is easy to cause uneven stress on a workpiece during demolding and the optimal temperature range of the workpiece during molding or demolding cannot be well guaranteed; the demoulding device is provided with the multiunit, because the compressible characteristic of gas, every demoulding device can obtain comparatively more even effort that makes it go upward relatively, is favorable to even realization drawing of patterns work, avoids the demoulding process to damage the work piece, simultaneously, can be favorable to improving shaping and drawing of patterns efficiency with the temperature range of the temperature adjustment of second mould to optimum forming process and drawing of patterns process through temperature adjustment mechanism.
Description
Technical Field
The utility model relates to the technical field of a compression molding device, in particular to a compression molding device for composite materials for an aircraft.
Background
The pressure forming device is a mould pressing device, and is a device which firstly puts powdery, granular or fibrous materials into a mould cavity at the forming temperature, and then closes the mould to press so as to form and solidify the materials;
in the field of aircraft, combined material's work piece is mostly through the pressure forming device realization shaping, but after the shaping finishes, take place the adhesion of certain degree between the work piece after the shaping and the mould, lead to drawing of patterns work unsmooth, traditional demoulding mechanism is difficult to keep unanimous to the dragging or the lift distance of work piece, lead to the work piece atress uneven when the drawing of patterns, can destroy the structure of work piece to a certain extent, reduce its bulk strength, and there is not temperature regulation and control device on the work piece mould, the most suitable temperature range when leading to the shaping of work piece or drawing of patterns can not be fine guarantees.
The present invention is directed to a solution to the above-mentioned problems.
SUMMERY OF THE UTILITY MODEL
In order to solve the above problems, that is, the problems of the background art, the present invention provides a composite material pressure molding device for an aircraft, including a first mold driven by a preset pressure device, and a second mold arranged on a preset worktable, wherein the second mold is provided with a demolding mechanism and a temperature adjusting mechanism;
the first die descends and cooperates with the second die to realize workpiece molding, the demolding is realized through the demolding mechanism, and the temperature of the first die is changed through the temperature adjusting mechanism;
the demolding mechanisms are provided with a plurality of groups, each group of demolding mechanisms comprises a lifting rod and a sliding cavity, two ends of each lifting rod are respectively provided with a conical block and a piston, each sliding cavity is arranged on the second mold, each lifting rod is located in each sliding cavity, each second mold is further provided with an air passage communicated with each sliding cavity, and each air passage is connected with a preset air supply device;
inputting high-pressure air into the air passage through a preset air supply device, and realizing that the piston drives the lifting rod and the conical block to move upwards so as to realize demoulding;
the temperature of the second mold is adjusted to a temperature range optimum for the molding process and the demolding process by the temperature adjustment mechanism.
The utility model is further provided with: the temperature adjusting mechanism comprises a heating channel arranged on the second die, and the heating channel is connected with a preset medium circulating device;
and the temperature of the second die is adjusted by circulating a specific heating medium with a preset temperature in the heating channel.
The utility model is further provided with: the heating channel is arranged in the second die in a serpentine shape.
The utility model is further provided with: after the lifting rod moves downwards to the extreme position, one end of the sliding cavity is completely sealed by the conical block.
The utility model is further provided with: the cross-sectional shape of the piston is matched with that of the sliding cavity.
The utility model is further provided with: the piston is also provided with an elastic piston ring.
The beneficial technical effects of the utility model are as follows: according to the utility model, the demoulding devices are provided with a plurality of groups, and each group of demoulding devices are driven to operate by high-pressure gas, and due to the characteristic of gas compressibility, each demoulding device can obtain relatively uniform acting force for enabling the demoulding device to move upwards, so that the demoulding operation can be uniformly realized, the workpiece can be prevented from being damaged in the demoulding process, and meanwhile, the temperature of the second mould can be adjusted to the temperature range which is most suitable for the forming process and the demoulding process by the temperature adjusting mechanism, so that the forming and demoulding efficiency can be improved.
Drawings
FIG. 1 shows a schematic front cross-sectional structure of the present invention;
FIG. 2 shows a schematic top view of a second mold of the present invention;
FIG. 3 is a schematic cross-sectional view taken along the line A-A of FIG. 1 according to the present invention;
fig. 4 is a schematic diagram showing a partial enlarged structure at B in fig. 1 according to the present invention.
Reference numerals: 1-a first mould, 2-a second mould, 3-a lifting rod, 4-a sliding cavity, 5-a conical block, 6-a piston, 7-an air channel, 8-a heating channel and 9-a piston ring.
Detailed Description
Preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention, and are not intended to limit the scope of the present invention.
Example (b):
referring to fig. 1-4, fig. 1 shows a schematic sectional structure view from the front, fig. 2 shows a schematic structural view from the top of a second mold of the present invention, fig. 3 shows a schematic sectional structure view from the a-a side of fig. 1 of the present invention, fig. 4 shows a schematic structural view of a part enlarged at the B position of fig. 1 of the present invention, the present invention provides a composite material pressure forming device for an aircraft, which includes a first mold 1 driven by a preset pressure device to operate, a second mold 2 arranged on a preset worktable, and the second mold 2 is provided with a demolding mechanism and a temperature adjusting mechanism.
The first die 1 is detachably connected with a preset pressurizing device which drives the first die to operate, the second die 2 is detachably connected with a preset workbench, and the connection modes can be flange bolt connection.
The workpiece processed in the embodiment is composite plastic, the second mold 2 is provided with a mold cavity, the workpiece is molded through the cooperation of the first mold 1 moving downwards and the second mold 2, demolding is realized through the demolding mechanism, and the temperature of the first mold 1 is changed through the temperature adjusting mechanism.
The demolding mechanisms are provided with a plurality of groups, each group of demolding mechanisms comprises a lifting rod 3 and a sliding cavity 4, two ends of each lifting rod 3 are respectively provided with a conical block 5 and a piston 6, each piston 6 is also provided with an elastic piston ring 9, in the embodiment, each piston ring 9 is a rubber ring and is sleeved in a preset groove in each piston 6, each sliding cavity 4 is arranged on the second mold 2, each lifting rod 3 is positioned in each sliding cavity 4, each second mold 2 is also provided with an air passage 7 communicated with each sliding cavity 4, and each air passage 7 is connected with a preset air supply device;
after the lifting rod 3 descends to the extreme position, the conical block 5 completely seals one end of the sliding cavity 4, in the embodiment, after the conical block 5 descends to the extreme position, the upper end of the sliding cavity 4 can be completely sealed, the situation that the position, provided with the sliding cavity 4, on the second die 2 is not sunken or protruded can be ensured, and the flatness of the position, provided with the sliding cavity 4, is maintained; .
The temperature of the second mold 2 is adjusted to a temperature range optimum for the molding process and the demolding process by the temperature adjusting mechanism.
In the embodiment, the preset gas supply device can be a gas pump, the gas pump conveys high-pressure gas into the gas passage 7 through a guide pipe, and the piston 6 drives the lifting rod 3 and the conical block 5 to move upwards so as to realize demoulding;
the demoulding devices are provided with a plurality of groups, each group of demoulding devices are driven to operate by high-pressure gas, and each demoulding device can obtain relatively uniform acting force for enabling the demoulding devices to go upwards due to the characteristic of gas compressibility, so that the demoulding device is beneficial to uniform demoulding.
In this embodiment, in order to ensure smooth demolding operation, for the mold cavities arranged in a matrix, a set of demolding mechanisms is disposed between each adjacent mold cavity in the transverse direction.
In this embodiment, the temperature adjustment mechanism includes a heating channel 8 disposed on the second mold 2, the heating channel 8 is connected to the preset medium circulation device, and the heating channel 8 is arranged in the second mold 2 in a serpentine shape and is located below the mold cavity;
the temperature of the second die 2 is adjusted by flowing a specific heating medium with a preset temperature in the heating channel 8;
in this embodiment, the medium liquid circulating in the heating channel 8 may be heating oil, and the heating oil heats the second mold, so that the heating temperature can be controlled more conveniently;
in this embodiment, the preset medium circulating device includes a circulating pump, an oil tank, and an electric heater, and the three and the heating pipeline form a loop.
While the utility model has been described with reference to a preferred embodiment, various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the utility model, and particularly, features shown in the various embodiments may be combined in any suitable manner without departing from the scope of the utility model. It is intended that the utility model not be limited to the particular embodiments disclosed, but that the utility model will include all embodiments falling within the scope of the appended claims.
In the description of the present invention, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like, which indicate directions or positional relationships, are based on the directions or positional relationships shown in the drawings, which are for convenience of description only, and do not indicate or imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The terms "comprises," "comprising," or any other similar term are intended to cover a non-exclusive inclusion, such that a process, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, article, or apparatus.
So far, the technical solutions of the present invention have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present invention is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the utility model, and the technical scheme after the changes or substitutions can fall into the protection scope of the utility model.
Claims (6)
1. A composite material's pressure forming device for aircraft characterized in that: the device comprises a first die (1) driven to operate by a preset pressurizing device and a second die (2) arranged on a preset workbench, wherein the second die (2) is provided with a demolding mechanism and a temperature adjusting mechanism;
the first die (1) descends to be matched with the second die (2) to realize workpiece forming, the demolding is realized through the demolding mechanism, and the temperature of the first die (1) is changed through the temperature adjusting mechanism;
the demolding mechanism is provided with a plurality of groups, each group of demolding mechanism comprises a lifting rod (3) and a sliding cavity (4), two ends of each lifting rod (3) are respectively provided with a conical block (5) and a piston (6), each sliding cavity (4) is arranged on the second mold (2), each lifting rod (3) is positioned in each sliding cavity (4), each second mold (2) is further provided with an air passage (7) communicated with each sliding cavity (4), and each air passage (7) is connected with a preset air supply device;
high-pressure air is input into the air passage through a preset air supply device, so that the piston (6) drives the lifting rod (3) and the conical block (5) to move upwards to realize demoulding;
the temperature of the second mold (2) is adjusted to a temperature range optimum for the molding process and the demolding process by the temperature adjusting mechanism.
2. The composite material press-molding apparatus for an aircraft according to claim 1, wherein: the temperature adjusting mechanism comprises a heating channel (8) arranged on the second die (2), and the heating channel (8) is connected with a preset medium circulating device;
the temperature of the second mould (2) is adjusted by flowing a specific heating medium with a preset temperature in the heating channel (8).
3. The composite material press-molding apparatus for an aircraft according to claim 2, wherein: the heating channel (8) is arranged in the second die (2) in a snake shape.
4. The composite material press-molding apparatus for an aircraft according to claim 1, wherein: after the lifting rod (3) moves downwards to a limit position, one end of the sliding cavity (4) is completely sealed by the conical block (5).
5. The composite material press-molding apparatus for an aircraft according to claim 1, wherein: the cross section shape of the piston (6) is matched with that of the sliding cavity (4).
6. The composite material press-molding apparatus for an aircraft according to claim 5, wherein: the piston (6) is also provided with an elastic piston ring (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122363271.1U CN216032029U (en) | 2021-09-28 | 2021-09-28 | Composite material's pressure forming device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122363271.1U CN216032029U (en) | 2021-09-28 | 2021-09-28 | Composite material's pressure forming device for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216032029U true CN216032029U (en) | 2022-03-15 |
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ID=80607250
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122363271.1U Active CN216032029U (en) | 2021-09-28 | 2021-09-28 | Composite material's pressure forming device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216032029U (en) |
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2021
- 2021-09-28 CN CN202122363271.1U patent/CN216032029U/en active Active
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