CN219311811U

CN219311811U - Multi-curved-surface structure aircraft composite part forming tool

Info

Publication number: CN219311811U
Application number: CN202223371141.3U
Authority: CN
Inventors: 黄支友; 吴谦; 何崇
Original assignee: Jingdezhen Changhe Aviation Equipment Technology Co ltd
Current assignee: Jingdezhen Changhe Aviation Equipment Technology Co ltd
Priority date: 2022-12-15
Filing date: 2022-12-15
Publication date: 2023-07-07
Anticipated expiration: 2032-12-15

Abstract

The utility model discloses a multi-curved-surface structure aircraft composite material part forming tool which comprises a base plate and a top plate, wherein the base plate is fixedly connected with the top plate through a vertical plate. The beneficial effects are that: according to the utility model, the heating mechanisms are arranged in the outer module and the inner module of the split block, the inner module and the outer module are synchronously heated when the multi-curved-surface structure aircraft composite material part is subjected to hot press molding, the multi-curved-surface structure aircraft composite material part positioned between the outer module and the inner module is subjected to hot press molding, after the multi-curved-surface structure aircraft composite material part is subjected to hot press molding, the inner cylinder and the outer cylinder are synchronously shortened, the inner module and the outer module are driven to be separated from the molded multi-curved-surface structure aircraft composite material part at the same time, then the electric push rod is shortened, the molded multi-curved-surface structure aircraft composite material part can be pulled out, the demolding and the mold closing process are automatically carried out, the demolding is very convenient and simple, the trouble of manual demolding is saved, and the demolding efficiency and the convenience in use are improved.

Description

Multi-curved-surface structure aircraft composite part forming tool

Technical Field

The utility model relates to the technical field of machining of aircraft multi-curved-surface composite material parts, in particular to a multi-curved-surface structural aircraft composite material part forming tool.

Background

The composite material is a material with new performance formed by two or more materials with different properties on a macroscopic (microscopic) scale by a physical or chemical method, and the materials complement each other in performance to generate a synergistic effect, so that the comprehensive performance of the composite material is superior to that of the original composition material to meet various different requirements, the application of the composite material on an airplane is wider, the composite material is used for building an airplane on the basis of aerodynamics, more curved surfaces and multiple curved surfaces exist, and a certain trouble is brought to molding.

After searching, the publication number is CN106976187A, the name is a multi-curved surface closed angle structure aircraft composite part forming tool, the application provides that the traditional irregular shape structure aircraft composite part can be manufactured by adopting a rubber shrinkage die, foam, gypsum and other parts after being formed, the parts can be obtained by damaging the dies, but the dies are only suitable for one-time or several times of forming, which is not beneficial to batch production, the surface precision, quality and the like of the composite part manufactured by adopting the dies are generally inferior to those of a metal die, the overall dimensional precision of the part is ensured by matching the rigid split dies, and meanwhile, the problem of demoulding of the multi-curved surface closed angle structure is solved by adopting a reasonable pattern drawing angle design and a demoulding mode, so that the demoulding process after the part forming can be carried out by firstly detaching a support base from the multi-curved surface closed angle structure aircraft composite part, a front split module, a left split module, a middle split module, a right split module and a rear split module, then taking the middle split module out from the whole die by utilizing a prying bar, then taking the left split module and the right split module out, and finally taking the front split module and the part out the part from the whole die. The mold design method can solve the demolding problem of almost all complex closed angle structure composite material parts, and simultaneously ensures the operability of the part manufacturing process and the quality of the molded parts, but as can be easily seen from the application, the mold needs to be manually demolded by a worker, and tools such as a crow bar and the like are also needed to be used, so that the mold is more troublesome, and the mold can be further improved.

For the problems in the related art, no effective solution has been proposed at present.

Disclosure of Invention

(one) solving the technical problems

Aiming at the defects of the prior art, the utility model provides a multi-curved-surface structure aircraft composite part forming tool which has the advantages of convenience and simplicity in demolding and further solves the problems in the background art.

(II) technical scheme

In order to realize the advantages of convenience and simplicity in demolding, the utility model adopts the following specific technical scheme:

the utility model provides a many curved surface structure aircraft combined material part shaping frock, includes bed plate and roof, the bed plate passes through riser fixedly connected with roof, and the bed plate top surface is located vertical fixedly connected with center plate between the riser below the roof to center plate surface fixedly connected with inside cylinder, inside cylinder's piston rod other end fixed mounting has interior module, riser and roof surface fixed mounting have outside cylinder, and outside cylinder's piston rod other end fixed mounting has outer module, outer module and interior module one end slip butt have the end plate, and the end plate passes through mount and bed plate fixed connection, the bed plate other end has the electric putter through mounting bracket fixed mounting, and the dead lever other end fixedly connected with closure plate of electric putter to closure plate bottom surface and bed plate top surface sliding connection.

Further, a controller is fixedly arranged on the outer wall of one side of the vertical plate, and the output end of the controller is respectively and electrically connected with the input ends of the internal cylinder, the external cylinder and the electric push rod.

Further, the heating mechanism is fixedly arranged in the outer module and the inner module, and the heating mechanism is an electric heating wire.

Further, the number of the external cylinders corresponding to the number of the external modules is provided with a plurality of groups, and the number of the external cylinders is twice the number of the external modules.

Further, the number of the internal cylinders corresponding to the number of the internal modules is provided with a plurality of groups, and the number of the internal cylinders is twice the number of the internal modules.

Further, the blocking plate is a smooth rectangular plate.

Further, the inner wall of the outer module and the outer wall of the inner module are polished.

(III) beneficial effects

Compared with the prior art, the utility model provides a multi-curved-surface structure aircraft composite material part forming tool, which has the following beneficial effects:

(1) According to the utility model, the heating mechanisms are arranged in the outer module and the inner module of the split block, when the multi-curved-surface structure aircraft composite material part is subjected to hot press forming, the inner cylinder is started to stretch at first, the inner module is pushed to form a continuous structure, the multi-curved-surface structure aircraft composite material part can be paved outside the inner module layer by layer, the outer cylinder is pushed to stretch, the outer module is pushed to be closed, one end of the inner module and one end of the outer module are blocked by the end plate, the electric push rod stretches, the other end of the inner module and the other end of the outer module are blocked by the blocking plate, material leakage is avoided, the inner module and the outer module are synchronously heated, after the multi-curved-surface structure aircraft composite material part between the outer module and the inner module is subjected to hot press forming, the inner cylinder and the outer cylinder are synchronously shortened, the inner module and the outer module are driven to be separated from the formed multi-curved-surface structure aircraft composite material part at the same time, then the electric push rod is shortened, the formed multi-curved-surface structure aircraft composite material part can be pulled out, the demoulding and the mould closing process is carried out automatically, the demoulding is very convenient and simple, the trouble of demoulding is omitted, and the convenience of use is improved.

(2) The combined outer module and the combined inner module are adopted, and continuous multi-curved surfaces can be converted into segmented curved surfaces, so that the multi-curved surface part is opened and closed in a mode of combining oblique movement and vertical movement, the multi-curved surface part is convenient to demould, the combined multi-curved surface part forming machine is more suitable for forming streamline parts such as airplanes, and the combined multi-curved surface part forming machine is high in working efficiency, simple in structure and convenient to use.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic structural view of a multi-curved surface structure aircraft composite part forming tool according to the present utility model;

FIG. 2 is a front view of a multi-curved surface structure aircraft composite part forming tool according to the present utility model;

FIG. 3 is a side view of a multi-curved surface structure aircraft composite part forming tool according to the present utility model;

fig. 4 is a schematic view of the installation of the closure plate according to the present utility model.

In the figure:

1. a vertical plate; 2. a top plate; 3. an outer module; 4. an inner module; 5. an external cylinder; 6. a controller; 7. a center plate; 8. an internal cylinder; 9. a base plate; 10. an end plate; 11. a fixing frame; 12. a closure plate; 13. a mounting frame; 14. an electric push rod.

Detailed Description

For the purpose of further illustrating the various embodiments, the present utility model provides the accompanying drawings, which are a part of the disclosure of the present utility model, and which are mainly used to illustrate the embodiments and, together with the description, serve to explain the principles of the embodiments, and with reference to these descriptions, one skilled in the art will recognize other possible implementations and advantages of the present utility model, wherein elements are not drawn to scale, and like reference numerals are generally used to designate like elements.

According to the embodiment of the utility model, a multi-curved-surface structure aircraft composite material part forming tool is provided.

The utility model will now be further described with reference to the drawings and the detailed description, as shown in fig. 1-4, a multi-curved-surface structure aircraft composite part forming tool according to an embodiment of the utility model, which comprises a base plate 9 and a top plate 2, wherein the base plate 9 is fixedly connected with the top plate 2 through the vertical plate 1, the vertical plate 1 is convenient for installing an external cylinder 5, the top surface of the base plate 9 is positioned below the top plate 2 and is vertically and fixedly connected with a center plate 7 between the vertical plates 1, the center plate 7 is convenient for installing an internal cylinder 8, and the surface of the center plate 7 is fixedly connected with the internal cylinder 8, the other end of a piston rod of the internal cylinder 8 is fixedly provided with an internal module 4, the surfaces of the vertical plate 1 and the top plate 2 are fixedly provided with the external cylinder 5, the other end of the piston rod of the external cylinder 5 is fixedly provided with an external module 3, the external module 3 and the internal module 4 are arranged according to the size of the multi-curved-surface structure aircraft composite part, one end of the external module 3 and the internal module 4 are slidably abutted against an end plate 10, the end plate 10 is fixedly connected with the base plate 9 through a fixing frame 11, the other end of the base plate 9 is fixedly provided with an electric push rod 14, the other end of the electric push rod 14 is fixedly connected with a plate 12, and the bottom surface 12 of the top surface of the center plate is fixedly connected with the inner module 9, the inner module 4 is fixedly connected with the bottom surface of the inner module 4, the inner module 4 and the inner module 4 is heated, the inner module 4 is continuously heated, and the composite part is continuously heated, the composite part is formed, and the inner part is stretched, and the inner part is formed, and the inner part is continuously, and the structure 4 is heated, the electric push rod 14 stretches to push the blocking plate 12 to block the other ends of the inner module 4 and the outer module 3, material leakage is avoided, the inner module 4 and the outer module 3 are heated synchronously, the multi-curved-surface structure aircraft composite material part between the outer module 3 and the inner module 4 is subjected to hot press molding, after molding, the inner cylinder 8 and the outer cylinder 5 are shortened synchronously, the inner module 4 and the outer module 3 are driven to be separated from the molded multi-curved-surface structure aircraft composite material part at the same time, then the electric push rod 14 is shortened, the molded multi-curved-surface structure aircraft composite material part can be pulled out, the demolding and the mold closing process are automated, the demolding is very convenient and simple, the trouble of manual demolding is omitted, the demolding efficiency and the convenience of use are improved, the combined outer module 3 and the inner module 4 can be converted into segmented curved surfaces, and accordingly the multi-curved-surface parts can be opened and closed in a combined manner through oblique movement, the demolding of the multi-curved-surface structure aircraft part is convenient to mold, the multi-curved-surface aircraft part and the like streamline part molding is more suitable for molding, the working efficiency is high, and the structure is simple, and the use is convenient.

In one embodiment, the controller 6 is fixedly installed on the outer wall of one side of the vertical plate 1, and the output end of the controller 6 is electrically connected with the input ends of the internal cylinder 8, the external cylinder 5 and the electric push rod 14 respectively, so that the control structure is a common control structure and is convenient to control.

In one embodiment, the number of the external cylinders 5 corresponding to the number of the external modules 3 is provided with a plurality of groups, and the number of the external cylinders 5 is twice as large as the number of the external modules 3, so that the moving stability of the external modules 3 is improved.

In one embodiment, the number of the internal cylinders 8 corresponding to the number of the internal modules 4 is provided with a plurality of groups, and the number of the internal cylinders 8 is twice as large as the number of the internal modules 4, so that the moving stability of the internal modules 4 is improved.

In one embodiment, the closure plate 12 is a smooth rectangular plate that reduces sticking.

In one embodiment, the inner wall of the outer module 3 and the outer wall of the inner module 4 are both polished to reduce blocking.

Working principle:

when the multi-curved surface structure aircraft composite material part is hot-pressed and molded, the inner cylinder 8 is started to stretch at first, the inner module 4 is pushed to form a continuous structure, the multi-curved surface structure aircraft composite material part can be paved outside the inner module 4 layer by layer, the outer cylinder 5 is stretched, the outer module 3 is pushed to be closed, the end plate 10 seals one end of the inner module 4 and one end of the outer module 3, the electric push rod 14 is stretched, the plug plate 12 is pushed to seal the other end of the inner module 4 and the other end of the outer module 3, material leakage is avoided, the inner module 4 and the outer module 3 are synchronously heated, the multi-curved surface structure aircraft composite material part between the outer module 3 and the inner module 4 is hot-pressed and molded, after molding, the inner cylinder 8 and the outer cylinder 5 are synchronously shortened, the inner module 4 and the outer module 3 are driven to be separated from the molded multi-curved surface structure aircraft composite material part at the same time, then, the electric push rod 14 is shortened, the molded multi-curved surface structure aircraft composite material part can be pulled out, the demolding and die assembly processes are automated, the demolding is very convenient and simple, the trouble of manual demolding is saved, the demolding efficiency and the convenience of use are improved, the combined outer module 3 and the inner module 4 are adopted, continuous multi-curved surfaces can be converted into segmented curved surfaces, and accordingly, the multi-curved surface structure aircraft composite material part is opened and closed in a combined mode of oblique movement and vertical movement, the multi-curved surface structure aircraft composite material part is convenient to demolding, and is more suitable for molding of streamline parts such as aircraft and the like, and has the advantages of high working efficiency, simple structure and convenience in use.

In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "configured," "connected," "secured," "screwed," and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intermediaries, or in communication with each other or in interaction with each other, unless explicitly defined otherwise, the meaning of the terms described above in this application will be understood by those of ordinary skill in the art in view of the specific circumstances.

The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.

Claims

1. The utility model provides a many curved surface structure aircraft combined material part shaping frock, its characterized in that, includes bed plate (9) and roof (2), bed plate (9) are through riser (1) fixedly connected with roof (2), and bed plate (9) top surface is located vertical fixedly connected with center board (7) between riser (1) below roof (2), and center board (7) fixed surface is connected with inside cylinder (8), the piston rod other end fixed mounting of inside cylinder (8) has interior module (4), riser (1) and roof (2) fixed surface have outside cylinder (5), and the piston rod other end fixed mounting of outside cylinder (5) has outer module (3), outside module (3) and interior module (4) one end slip butt have end plate (10), and end plate (10) are through mount (11) and bed plate (9) fixed connection, the bed plate (9) other end is through mounting bracket (13) fixed mounting electric push rod (14), and the movable rod other end fixedly connected with closure plate (12) of electric push rod (14), and bottom surface and bed plate (9) sliding connection.

2. The multi-curved-surface structure aircraft composite part forming tool according to claim 1, wherein a controller (6) is fixedly arranged on the outer wall of one side of the vertical plate (1), and the output end of the controller (6) is electrically connected with the input ends of the inner cylinder (8), the outer cylinder (5) and the electric push rod (14) respectively.

3. The multi-curved-surface structure aircraft composite part forming tool according to claim 1 is characterized in that heating mechanisms are fixedly arranged inside the outer module (3) and the inner module (4), and the heating mechanisms are heating wires.

4. The multi-curved-surface structure aircraft composite part forming tool according to claim 1, wherein a plurality of groups of external cylinders (5) are arranged corresponding to the number of the external modules (3), and the number of the external cylinders (5) is twice the number of the external modules (3).

5. The multi-curved-surface structure aircraft composite part forming tool according to claim 1, wherein a plurality of groups of internal cylinders (8) are arranged corresponding to the number of the internal modules (4), and the number of the internal cylinders (8) is twice the number of the internal modules (4).

6. The multi-curved-surface structure aircraft composite part forming tool according to claim 1, wherein the blocking plate (12) is a smooth rectangular plate.

7. The multi-curved-surface structure aircraft composite part forming tool according to claim 1, wherein the inner wall of the outer module (3) and the outer wall of the inner module (4) are polished.