Aviation composite material forming device

Abstract

The utility model discloses an aviation composite material forming device which comprises a base, an injection molding machine, a side seat, a sliding column, a top beam, a material taking mechanism and a cooling mechanism, the injection molding machine is fixedly mounted at the top of the base; the tops of the side seats are connected with guide bases; a sliding block is connected to the bottom of the sliding column and slidably connected to the top of the guide base, and a through opening is formed in the sliding column. The top beam is connected to the tops of the sliding columns, and a top sliding groove is formed in the top of the top beam; the material taking mechanism is connected to the top of the top beam. And the cooling mechanism is connected into the material taking mechanism. A hot melting composite material raw material is injected into the mold on one side of the injection molding machine through the injection molding machine, when the raw material enters the mold, molding and shaping are conducted after cooling, demolding is conducted after shaping, and in the demolding process, parts are automatically taken through the material taking mechanism; and the cooling mechanism is used for thoroughly cooling the parts with residual heat in the process, so that workers can conveniently take the parts.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the aviation composite material forming technical field, concretely relates to an aviation composite material forming device. BACKGROUND

[0002] Aviation composite materials have been widely used in modern aircraft manufacturing due to their excellent performance, such as high strength, low density, corrosion resistance and fatigue resistance.

[0003] In the field of aviation composite materials, parts can be produced by injection molding. Hot molten raw materials are injected into the mold by an injection molding machine for shaping, and the material is removed after cooling.

[0004] During the injection molding process, some workpieces are difficult to remove due to high temperature or large size after demolding, so an aviation composite material forming device that can easily remove parts after forming is needed. INVENTION CONTENTS

[0005] Based on the above technical problems, the utility model provides an aviation composite material forming device.

[0006] The specific technical scheme is:

[0007] An aviation composite material forming device comprises:

[0008] a base;

[0009] an injection molding machine fixedly installed on the top of the base;

[0010] a side seat connected with a guide base on the top;

[0011] a sliding column connected with a sliding block on the bottom, the sliding block being slidingly connected to the top of the guide base, and the sliding column being provided with a through opening;

[0012] a top beam connected to the top of a pair of sliding columns, the top beam being provided with a top sliding groove on the top;

[0013] a material taking mechanism connected to the top of the top beam;

[0014] a cooling mechanism connected in the material taking mechanism.

[0015] In the above technical scheme, the material taking mechanism comprises:

[0016] a top sliding block slidingly connected to the top of the top beam;

[0017] a top seat connected with a first hydraulic cylinder on one end, the first hydraulic cylinder being connected with a first side frame on the telescopic end;

[0018] The second hydraulic cylinder is connected to one side of the top beam, and the telescopic end of the second hydraulic rod is connected to one side of the top seat;

[0019] The first end frame is connected to the telescopic end of the first hydraulic cylinder;

[0020] A first clamping frame, which slides in the through-hole and is connected to one side of a first end frame;

[0021] The second end frame is fixedly installed on one side of the top base;

[0022] The second clamping frame slides through a passage located on the other side and is connected to the second end frame.

[0023] In the above technical solution, the cooling mechanism includes:

[0024] The first cooling pipe, and a pair of the first cooling pipes are both connected to the first clamping frame;

[0025] The second cooling pipe, and a pair of the second cooling pipes are both connected to the second clamping frame.

[0026] The above technical solution also includes:

[0027] A movable motor is connected to the bottom of a sliding column, and a movable gear is connected to the drive end of the movable motor;

[0028] A guide rack is connected to one side of the guide base, and the moving gear meshes with the guide rack.

[0029] The above technical solution also includes:

[0030] A limiting frame is connected to one side of the first clamping frame.

[0031] The above technical solution also includes:

[0032] The first cylinder, and a pair of first cylinders are both connected to the limit frame;

[0033] The second cylinder, a pair of the second cylinders, are both connected to one side of the second clamping frame.

[0034] The advantages of this aerospace composite material molding device compared with the prior art are as follows:

[0035] Hot-melt composite material raw materials are injected into a mold on one side of the injection molding machine. After the raw materials enter the mold, they are cooled and shaped. After sizing, they are demolded. During the demolding process, the parts are automatically picked up by the material handling mechanism and removed from the mold. The parts are then thoroughly cooled by the cooling mechanism to make it easier for the staff to handle them. Attached Figure Description

[0036] Fig. 1 This is a schematic diagram of an aerospace composite material molding device according to the present invention;

[0037] Fig. 2 This is a schematic diagram of the present invention;

[0038] Fig. 3 This is a schematic diagram of the present invention.

[0039] in, Figs. 1-3 The correspondence between the reference numerals and component names in the attached drawings is as follows:

[0040] 1. Base; 2. Injection molding machine; 3. Side seat; 4. Sliding column; 5. Top beam; 6. Top slider; 7. Top seat; 8. Second hydraulic cylinder; 9. First end frame; 10. First clamping frame; 11. Second end frame; 12. Second clamping frame; 13. First cooling pipe; 14. Second cooling pipe; 15. Moving motor; 16. Guide rack; 17. Limiting frame; 18. First cylinder; 19. Second cylinder. Detailed Implementation

[0041] The following are specific implementation cases and appendices. Figs. 1-3 The present invention will be further described below, but the present invention is not limited to these embodiments.

[0042] like Figs. 1-3 As shown, this utility model discloses an aerospace composite material molding device, including: a base 1, an injection molding machine 2, a side seat 3, a sliding column 4, a top beam 5, a material handling mechanism, and a cooling mechanism; the injection molding machine 2 is fixedly installed on the top of the base 1; a guide base 1 is connected to the top of the side seat 3; a sliding block is connected to the bottom of the sliding column 4, and the sliding block is slidably connected to the top of the guide base 1, and the sliding column 4 has an opening; the top beam 5 is connected to the top of a pair of sliding columns 4, and a top sliding groove is opened on the top of the top beam 5; the material handling mechanism is connected to the top of the top beam 5; and the cooling mechanism is connected inside the material handling mechanism.

[0043] In embodiments of this utility model, such as Figs. 1-3As shown, the material handling mechanism includes: a top slider 6, a top seat 7, a second hydraulic cylinder 8, a first end frame 9, a first clamping frame 10, a second end frame 11, and a second clamping frame 12; the top slider 6 is slidably connected to the top of the top beam 5; one end of the top seat 7 is connected to the first hydraulic cylinder, and the telescopic end of the first hydraulic cylinder is connected to the first side frame; the second hydraulic cylinder 8 is connected to one side of the top beam 5, and the telescopic end of the second hydraulic cylinder is connected to one side of the top seat 7; the first end frame 9 is connected to the telescopic end of the first hydraulic cylinder; the clamping frame slides in the opening, and the clamping frame is connected to one side of the first end frame 9; the second end frame 11 is fixedly installed on one side of the top seat 7; the second clamping frame 12 slides in the opening located on the other side, and the second clamping frame 12 is connected to the second end frame 11.

[0044] In embodiments of this utility model, such as Figs. 1-3 As shown, the cooling mechanism includes: a first cooling pipe 13 and a second cooling pipe 14; a pair of first cooling pipes 13 are both connected to a first clamping frame 10; a pair of second cooling pipes 14 are both connected to a second clamping frame 12.

[0045] In embodiments of this utility model, such as Figs. 1-3 As shown, it also includes: a moving motor 15 and a guide rack 16; the moving motor 15 is connected to the bottom of the sliding column 4, and the driving end of the moving motor 15 is connected to a moving gear; the guide rack 16 is connected to one side of the guide base 1, and the moving gear meshes with the guide rack 16.

[0046] In embodiments of this utility model, such as Figs. 1-3 As shown, it also includes: a limiting frame 17; the limiting frame 17 is connected to one side of the first clamping frame 10.

[0047] In embodiments of this utility model, such as ​ As shown, it also includes: a first cylinder 18 and a second cylinder 19; a pair of first cylinders 18 are both connected to the limiting frame 17; a pair of second cylinders 19 are both connected to one side of the second clamping frame 12.

[0048] Implementation process: First, injection molding is performed on the mold using injection molding machine 2. After injection molding, the molded parts are cooled and then demolded using an internal ejection device. Before demolding, the moving gear at the drive end of the moving motor 15 is controlled to rotate. Since the moving gear meshes with the guide rack 16, the sliding column 4 slides along the guide base 1, so that the sliding column 4, the first clamping frame 10, and the second clamping frame 12 are located outside the workpiece to be demolded. Then, the first hydraulic cylinder is controlled to extend, so that the part is located inside the limiting frame. The extension end of the first cylinder 18 is controlled to extend, and the extension end of the first hydraulic cylinder is controlled to shorten, so that the part is sent to the second clamping frame 12. When the part is close to the second clamping frame 12, the extension end of the second cylinder 19 is controlled to extend, so that the part is fixed. Then, the second hydraulic cylinder 8 is controlled to move as a whole, so that the part is moved out of the narrow space. During this process, the part can be cooled by ventilation through the first cooling pipe 13 and the second cooling pipe 14 by an external blower to accelerate the cooling speed.

[0049] In the description of this utility model, the term "multiple" refers to two or more. Unless otherwise explicitly defined, the terms "upper," "lower," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. The terms "connection," "installation," "fixing," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection or an indirect connection through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0050] In the description of this utility model, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this utility model. In this utility model, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0051] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An aircraft composite material forming apparatus, characterized by, Include: Base; Injection molding machine, the injection molding machine is fixedly installed on the top of the base; Side seat, the top of the side seat is connected with the guide base; Sliding column, the bottom of the sliding column is connected with the sliding block, the sliding block is slidingly connected to the top of the guide base, and the sliding column is provided with a through hole; Top beam, the top beam is connected to the top of the pair of sliding columns, and the top of the top beam is provided with a top sliding groove; Material taking mechanism, the material taking mechanism is connected to the top of the top beam; Cooling mechanism, the cooling mechanism is connected in the material taking mechanism.

2. The aircraft composite material forming device of claim 1, wherein, The material taking mechanism comprises: Top sliding block, the top sliding block is slidingly connected to the top of the top beam; Top seat, one end of the top seat is connected with the first hydraulic cylinder, and the first hydraulic cylinder is connected with the first side frame at the telescopic end; Second hydraulic cylinder, the second hydraulic cylinder is connected to one side of the top beam, and the second hydraulic cylinder is connected to one side of the top seat at the telescopic end; First end frame, the first end frame is connected to the telescopic end of the first hydraulic cylinder; First clamping frame, the clamping frame is sliding in the through hole, and the clamping frame is connected to one side of the first end frame; Second end frame, the second end frame is fixedly installed on one side of the top seat; Second clamping frame, the second clamping frame is sliding in the through hole on the other side, and the second clamping frame is connected to the second end frame.

3. The aircraft composite material forming device of claim 1, wherein, The cooling mechanism comprises: First cooling pipe, a pair of first cooling pipes are connected to the first clamping frame; Second cooling pipe, a pair of second cooling pipes are connected to the second clamping frame.

4. The aircraft composite forming apparatus of claim 1, wherein, Further comprising: Moving motor, the moving motor is connected to the bottom of the sliding column, and the moving motor is connected with the moving gear at the driving end; Guide rack, the guide rack is connected to one side of the guide base, and the moving gear is engaged with the guide rack.

5. The aircraft composite forming apparatus of claim 4, wherein, Further comprising: Limiting frame, the limiting frame is connected to one side of the first clamping frame.

6. The aircraft composite forming apparatus of claim 1, wherein, Further comprising: First air cylinder, a pair of first air cylinders are connected to the limiting frame; Second air cylinder, a pair of second air cylinders are connected to one side of the second clamping frame.

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