Demolding device for aircraft composite material processing

Abstract

The invention discloses a demolding device for aircraft composite material processing, and belongs to the technical field of aircraft component processing, the demolding device comprises a box body, a lower mold is mounted at the top end of the box body, a small gear engaged with a large gear is fixed to the output end of a driving motor, a buffer assembly is arranged at the bottom of the box body, and an auxiliary demolding assembly is arranged at the bottom of a forming cavity. An adjusting assembly is arranged outside the box body; airflow is blown upwards through the buffering assembly, so that the aircraft composite material part is buffered through the airflow, the falling composite material part is flexibly buffered and is prevented from directly impacting a workbench or conveying equipment, deformation, scratching or internal structure damage caused by mechanical impact is reduced, the product yield is remarkably increased, and the production cost is reduced. The height position of the buffer assembly can be adjusted through the arranged adjusting assembly, so that the distance between the buffer assembly and the forming cavity in the lower mold can be conveniently adjusted, switching can be completed without mold replacement or complex debugging, and the production preparation time is greatly shortened.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft component processing, and particularly relates to a demolding device for aircraft composite material processing. Background Technique

[0002] Composite materials have the advantages of light weight, high strength, designability, fatigue resistance, and easy realization of structure / function integration. Therefore, after aluminum, titanium, and steel, they have rapidly developed into one of the four major aircraft structural materials. At present, composite materials account for a high proportion in the load-bearing components of aircraft, such as wings, frames, etc. In addition, in the manufacture of pressure vessels, due to the good high strength and fatigue resistance of composite materials, they are also used in the production of pressure vessels. The structural characteristics of pressure vessels on aircraft are mostly cylindrical, and an integral molding manufacturing method is adopted. Therefore, it is relatively common to use standard molds to manufacture pressure vessels on aircraft. However, since most pressure vessels have a cylindrical structure, their molds are mostly composed of two inner and outer molds. The composite material is placed between the inner and outer molds, and the inner and outer molds are removed after molding.

[0003] During the processing of aircraft composite materials, after the composite materials are cured and molded, they are prone to generate a strong adhesion force with the mold surface. Especially when using high-performance matrix materials such as epoxy resin, their excellent bonding characteristics increase the demolding difficulty. At the same time, aircraft composite components often have complex curved surface structures and large sizes. Traditional mechanical ejection devices are difficult to apply force evenly, easily resulting in local stress concentration, causing internal damages such as microcracks and delamination in the components, affecting the qualified rate of finished products, reducing production efficiency, and increasing labor costs.

[0004] Therefore, a demolding device for aircraft composite material processing is needed to solve the problems raised in the above background technique. Summary of the Invention

[0005] The purpose of the present invention is to provide a demolding device for aircraft composite material processing to solve the problems raised in the above background technique.

[0006] To achieve the above purpose, the present invention provides the following technical solution: A demolding device for aircraft composite material processing, including a box body. A lower mold is installed at the top end of the box body. An upper mold cooperating with the lower mold is arranged directly above the lower mold. Molding cavities are provided in both the lower mold and the upper mold. A first shaft rod and a second shaft rod arranged coaxially and rotationally penetrating the side wall of the box body are fixed on the side surface of the lower mold. A large gear is fixed on the first shaft rod. A driving motor is fixed on the outer side wall of the box body. A small gear meshingly connected with the large gear is fixed on the output end of the driving motor. A buffer assembly is arranged at the bottom of the box body. An auxiliary demolding assembly communicated with the buffer assembly is arranged at the bottom of the molding cavity. An adjusting assembly for adjusting the buffer assembly is arranged outside the box body.

[0007] It should be noted that in the solution, the buffer assembly includes a concave plate arranged at the bottom of the box body. A cavity is formed inside the concave plate. An arc-shaped air blowing pipe communicated with the cavity is fixed on the inner side wall of the concave plate. There are multiple arc-shaped air blowing pipes, and the multiple arc-shaped air blowing pipes are equidistantly distributed. An air inlet pipe communicated with the cavity is fixed on the outer side wall of the concave plate.

[0008] Furthermore, it is worth noting that the auxiliary demolding assembly includes a groove formed at the bottom inside the forming cavity. A piston plate is closely fitted to the inner side wall of the groove. A connecting rod is fixed on the side surface of the piston plate. A top demolding plate adapted to the port of the groove is fixed at one end of the connecting rod away from the piston plate.

[0009] Even further, it should be noted that a return spring is arranged inside the groove, and both ends of the return spring are respectively fixed to the bottom end of the groove and the side surface of the piston plate.

[0010] As a preferred implementation manner, a through groove communicated with the groove is formed inside the second shaft rod. A connecting hose communicated with the through groove is rotatably connected inside one end of the second shaft rod away from the lower mold. One end of the connecting hose away from the second shaft rod is communicated with the cavity.

[0011] As a preferred implementation manner, the adjusting assembly includes a first convex plate fixed on the outer side wall of the concave plate. A second convex plate is fixed on the outer side wall of the box body. A nut sleeve is fixed inside the second convex plate. A threaded rod is threadedly connected inside the nut sleeve. One end of the threaded rod is rotatably connected to the first convex plate.

[0012] As a preferred implementation manner, a guiding chute slidably adapted to the first convex plate is formed on the side wall of the box body. An end head plate is fixed on the top end of the threaded rod. A rubber sleeve is fitted on the surface of the end head plate in a fitting manner.

[0013] As a preferred implementation manner, a belt conveyor is arranged at the bottom of the box body. The belt conveyor is located at the center of the concave plate. A rubber sleeve is fitted on the surface of the end head plate in a fitting manner.

[0014] As a preferred implementation manner, a notch is formed on one side surface of the box body. A first cover plate is hinged inside the notch.

[0015] As a preferred implementation manner, a handle is fixed on the outer side wall of the first cover plate. A second cover plate is fixed at one end of the box body. The belt conveyor penetrates through the second cover plate. A rubber sleeve is fitted on the surface of the handle in a fitting manner.

[0016] Compared with the prior art, a demolding device for aircraft composite material processing provided by the present invention has at least the following beneficial effects:

[0017] 1. The buffer component is set to blow out air upward, so as to buffer the aircraft composite parts through the air flow. The structural design of the forming cavity of the lower mold facing downward utilizes the gravity effect, enabling the composite parts to fall off naturally after mold opening without manual intervention or mechanical ejection devices, greatly improving production efficiency and reducing labor operation costs. The air flow ejected upward by the blowing component forms an air cushion to flexibly buffer the falling composite parts, preventing them from directly hitting the workbench or conveying equipment and reducing deformation, scratching or internal structural damage caused by mechanical impact, significantly improving the product yield. The blowing process can synchronously remove the residual particles in the forming cavity, reduce pollution, and ensure the product quality in the next forming cycle;

[0018] 2. The air flow inside the buffer component is diverted and conveyed into the auxiliary ejection component, so as to assist in ejecting the aircraft composite parts in the forming cavity through the auxiliary ejection component, effectively improving the discharging effect. On the one hand, the air flow diversion utilizes the existing blowing system without the need for an additional power source, reducing energy consumption and structural complexity; on the other hand, the pneumatic ejection provides a uniform and gentle demolding force, effectively protecting the integrity of the composite material structure. The air top and air buffer work together to form a complete demolding protection system, which can not only demold reliably but also buffer the falling impact, significantly improving production efficiency and product consistency. This integrated design saves mold space, reduces the overall weight, and is convenient for maintenance;

[0019] 3. The height position of the buffer component can be adjusted through the set adjustment component, so that the distance between the buffer component and the forming cavity on the lower mold can be conveniently adjusted, which is applicable to buffering different aircraft composite parts, effectively improving the applicable range of the overall device and the overall practicality. At the same time, it can accurately match aircraft composite parts of different sizes, shapes and weights, ensuring that the air flow buffering force is always in the best position, avoiding buffer failure caused by insufficient height and preventing waste of air flow dispersion caused by too high a position. It can quickly adapt to the production needs of multi-variety and small-batch aviation composite materials, and can complete the switching without changing the mold or complex debugging, greatly shortening the production preparation time. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is the schematic diagram of the overall structure of the present invention Figure 1 ;

[0021] Figure 2 is the schematic diagram of the overall structure of the present invention Figure 2 ;

[0022] Figure 3 is the schematic diagram of the overall structure of the present invention Figure 3 ;

[0023] Figure 4 is Figure 3 the enlarged schematic diagram of part A in

[0024] Figure 5 is the overall front view structural schematic diagram of the present invention;

[0025] Figure 6 is the front view structural schematic diagram of the interior of the box body of the present invention;

[0026] Figure 7 is the structural schematic diagram of the interior of the box body of the present invention;

[0027] Figure 8 is the cross-sectional structural schematic diagram of the buffer assembly of the present invention;

[0028] Figure 9 is Figure 8 the enlarged structural schematic diagram at position A in

[0029] Figure 10 is the partial structural schematic diagram of the adjustment assembly of the present invention.

[0030] In the figure: 1, auxiliary threshing assembly; 101, through groove; 102, groove; 103, return spring; 104, piston plate; 105, connecting rod; 106, top threshing plate; 107, connecting hose; 2, buffer assembly; 201, concave plate; 202, arc-shaped air blowing pipe; 203, cavity; 204, air inlet pipe; 3, adjustment assembly; 302, threaded rod; 303, end plate; 304, first convex plate; 305, nut sleeve; 306, guide chute; 307, second convex plate; 4, box body; 5, belt conveyor; 6, notch; 7, first cover plate; 8, handle; 9, lower mold; 10, forming cavity; 11, upper mold; 12, drive motor; 13, small gear; 14, large gear; 15, second cover plate; 16, guide post; 17, first shaft rod; 18, second shaft rod. Specific embodiments

[0031] The present invention will be further described below in conjunction with embodiments.

[0032] Please refer to Figures 1-10, the present invention provides a demoulding device for aircraft composite material processing, including a box body 4. At the top of the box body 4, a lower mould 9 is installed. Above the lower mould 9, an upper mould 11 that cooperates with the lower mould 9 is arranged. Forming cavities 10 are provided in both the lower mould 9 and the upper mould 11. On the side of the lower mould 9, a first shaft rod 17 and a second shaft rod 18 that are coaxially arranged and rotatably penetrate the side wall of the box body 4 are fixed. A large gear 14 is fixed on the first shaft rod 17. A driving motor 12 is fixed on the outer side wall of the box body 4. A small gear 13 that meshes with the large gear 14 is fixed on the output end of the driving motor 12. A buffer assembly 2 is arranged at the bottom of the box body 4. At the bottom of the forming cavity 10, an auxiliary demoulding assembly 1 that communicates with the buffer assembly 2 is arranged. An adjusting assembly 3 for adjusting the buffer assembly 2 is arranged outside the box body 4. When in use, an aircraft composite material part is formed by the clamping of the lower mould 9 and the upper mould 11. After the aircraft composite material part is formed, the upper mould notch 6 and the forming cavity 10 of the lower mould are separated in the up and down direction. The driving motor 12 is started to work. The output end of the driving motor 12 drives the small gear 13 to rotate. Thus, the first shaft rod 17 and the lower mould 9 are driven to rotate through the cooperation of the small gear 13 and the large gear 14, so that the forming cavity 10 on the lower mould 9 faces downward, and the aircraft composite material part in the forming cavity 10 automatically falls out. The buffer assembly 2 is provided to blow out air upward, so that the aircraft composite material part is buffered by the air flow. The structural design of the forming cavity 10 on the lower mould 9 facing downward utilizes the gravity effect, enabling the composite material part to naturally fall off after mold opening without manual intervention or mechanical ejection devices, greatly improving the production efficiency and reducing the manual operation cost. The air flow ejected upward by the blowing assembly forms an air cushion to flexibly buffer the falling composite material part, preventing it from directly hitting the workbench or conveying equipment, and reducing deformations, scratches or internal structural damages caused by mechanical impacts, significantly improving the product yield. During the blowing process, the residual particles in the forming cavity 10 can be synchronously removed, reducing pollution and ensuring the product quality in the next forming cycle. At the same time, the air flow inside the buffer assembly 2 is shunted and conveyed into the auxiliary demoulding assembly 1, so that the aircraft composite material part in the forming cavity 10 is assisted to be ejected, effectively improving the discharging effect. On the one hand, the air flow shunting utilizes the existing blowing system without an additional power source, reducing energy consumption and structural complexity. On the other hand, the pneumatic ejection provides a uniform and gentle demoulding force, effectively protecting the structural integrity of the composite material. The cooperation of the air ejection and the air buffer forms a complete demoulding protection system, which can not only reliably demould but also buffer the falling impact, significantly improving the production efficiency and product consistency. This integrated design saves mold space, reduces the overall weight and is convenient for maintenance.The height position of the buffer assembly 2 can be adjusted through the provided adjustment assembly 3, thereby conveniently adjusting the distance between the buffer assembly 2 and the forming cavity 10 on the lower mold 9, being applicable to buffering different aircraft composite parts, effectively improving the applicable range of the overall device, enhancing the overall practicality. At the same time, it can accurately match aircraft composite parts of different sizes, shapes, and weights, ensuring that the air flow buffering force is always in the optimal position, avoiding buffer failure caused by insufficient height and preventing air flow dispersion waste caused by too high a position. It can quickly adapt to the production requirements of multi-variety and small-batch aviation composite materials, and can complete the switching without replacing the mold or complex debugging, significantly shortening the production preparation time.

[0033] Further, as Figure 6 、 Figure 7 、 Figure 8 and Figure 10 shown, it is specifically worth noting that the buffer assembly 2 includes a concave plate 201 provided at the bottom of the box body 4. A cavity 203 is formed inside the concave plate 201. An arc-shaped air blowing pipe 202 communicating with the cavity 203 is fixed on the inner side wall of the concave plate 201. There are multiple arc-shaped air blowing pipes 202, and the multiple arc-shaped air blowing pipes 202 are evenly distributed. An air inlet pipe 204 communicating with the cavity 203 is fixed on the outer side wall of the concave plate 201; the air inlet pipe 204 is externally connected to an air pump, and air flow is transported into the concave plate 201 through the air inlet pipe 204, and then the air flow is blown upward through the multiple arc-shaped air blowing pipes 202, so as to buffer the aircraft composite part through the air flow. The downward structure design of the forming cavity 10 of the lower mold 9 utilizes the gravity effect to make the composite part naturally fall off after mold opening without manual intervention or mechanical ejection device, greatly improving the production efficiency and reducing the manual operation cost. The air flow ejected upward by the air blowing assembly forms an air cushion to flexibly buffer the falling composite part, avoiding its direct impact on the workbench or conveying equipment, reducing deformation, scratching, or internal structure damage caused by mechanical impact, and significantly improving the product yield. The residual particles in the forming cavity 10 can be synchronously removed during the air blowing process, reducing pollution and ensuring the product quality of the next forming cycle.

[0034] Further, as Figure 7 、 Figure 8 and Figure 9As shown, it is worth specifically stating that the auxiliary ejection assembly 1 includes a groove 102 formed in the bottom of the molding cavity 10. A piston plate 104 is closely fitted to the inner side wall of the groove 102. A connecting rod 105 is fixed on the side surface of the piston plate 104. One end of the connecting rod 105 away from the piston plate 104 is fixed with an ejection plate 106 adapted to the port of the groove 102. During specific operation, the air flow inside the concave plate 201 is shunted and conveyed into the second shaft 18 through the connecting hose 107, so that there is air pressure inside the groove 102. The piston plate 104 is pushed by the air pressure, causing the ejection plate 106 to protrude from the bottom surface of the molding cavity 10. Thus, the aircraft composite parts in the molding cavity 10 are assisted to be ejected, effectively improving the discharging effect. On the one hand, the air flow shunting utilizes the existing blowing system without the need for an additional power source, reducing energy consumption and structural complexity. On the other hand, the pneumatic ejection provides a uniform and gentle demolding force, effectively protecting the integrity of the composite material structure. The cooperation of the air ejection and air buffer forms a complete demolding protection system, which can not only reliably demold but also buffer the falling impact, significantly improving production efficiency and product consistency. This integrated design saves mold space, reduces the overall weight, and is convenient for maintenance.

[0035] Further as Figure 9 shown, it is worth specifically stating that a return spring 103 is arranged inside the groove 102. Both ends of the return spring 103 are respectively fixed to the bottom end of the groove 102 and the side surface of the piston plate 104. A through groove 101 communicating with the groove 102 is formed inside the second shaft 18. One end of the second shaft 18 away from the lower mold 9 is rotatably connected with a connecting hose 107 communicating with the through groove 101. The end of the connecting hose 107 away from the second shaft 18 communicates with the cavity 203. During specific operation, the piston plate 104 is pulled back by the arranged return spring 103, so that the ejection plate 106 is reset, and the port of the groove 102 is tightly sealed by the ejection plate 106.

[0036] Further as Figure 3 、 Figure 4 and Figure 10As shown, it is worth specifically explaining that the adjusting component 3 includes a first convex plate 304 fixed to the outer wall of the concave plate 201. A second convex plate 307 is fixed to the outer wall of the box body 4. A nut sleeve 305 is fixed inside the second convex plate 307. A threaded rod 302 is threadedly connected inside the nut sleeve 305. One end of the threaded rod 302 is rotatably connected to the first convex plate 304. During specific operation, the cooperation of the threaded rod 302 and the nut sleeve 305 enables the threaded rod 302 to rotate and adjust, so as to drive the first convex plate 304 and the concave plate 201 to move and adjust through the threaded rod 302, thereby adjusting the height position of the concave plate 201, and thus conveniently adjusting the distance between the arc-shaped air blowing pipe 202 and the forming cavity 10 on the lower mold 9, so that the air flow blown out by the arc-shaped air blowing pipe 202 is applicable to buffering different aircraft composite parts, effectively improving the applicable range of the overall device, enhancing the overall practicability, and at the same time being able to accurately match aircraft composite parts of different sizes, shapes and weights, ensuring that the air flow buffering force is always in the best position, avoiding buffer failure caused by insufficient height and preventing air flow dispersion and waste caused by too high a position, being able to quickly adapt to the production requirements of multi-variety and small-batch aviation composite materials, and completing the switching without replacing the mold or complex debugging, greatly shortening the production preparation time.

[0037] Further, as Figure 4 shown, it is worth specifically explaining that a guiding chute 306 slidably adapted to the first convex plate 304 is provided on the side wall of the box body 4. A end head plate 303 is fixed to the top end of the threaded rod 302. A rubber sleeve is fitted on the surface of the end head plate 303. During specific operation, the cooperation of the provided guiding chute 306 and the first convex plate 304 is used to guide and limit the movement adjustment of the concave plate 201, improving the stability of the movement adjustment of the concave plate 201.

[0038] This solution has the following working process: The output end of the driving motor 12 drives the pinion gear 13 to rotate, thereby driving the first shaft rod 17 and the lower mold 9 to rotate through the cooperation of the pinion gear 13 and the large gear 14, so that the forming cavity 10 on the lower mold 9 faces downward, enabling the aircraft composite parts in the forming cavity 10 to fall out automatically. The air flow is transported into the inside of the concave plate 201 through the air inlet pipe 204, and then the air flow is blown upward through the multiple arc-shaped air blowing pipes 202, so as to buffer the aircraft composite parts through the air flow. At the same time, the air flow inside the concave plate 201 is shunted and transported into the second shaft rod 18 through the connecting hose 107, so that the inside of the groove 102 has air pressure. The piston plate 104 is pushed by the air pressure, so that the ejector plate 106 protrudes from the bottom surface of the forming cavity 10, and thus the aircraft composite parts in the forming cavity 10 are assisted to be ejected by the ejector plate 106. The cooperation of the threaded rod 302 and the nut sleeve 305 enables the threaded rod 302 to be rotated and adjusted, so that the threaded rod 302 drives the first convex plate 304 and the concave plate 201 to move and adjust, thereby adjusting the height position of the concave plate 201, and thus conveniently adjusting the distance between the arc-shaped air blowing pipe 202 and the forming cavity 10 on the lower mold 9, so that the air flow blown out by the arc-shaped air blowing pipe 202 is suitable for buffering different aircraft composite parts.

[0039] Further, as shown in Figure 1 , Figure 2 and Figure 7 it is specifically noted that a belt conveyor 5 is provided at the bottom of the box body 4. The belt conveyor 5 is located at the center of the concave plate 201, and a rubber sleeve is fitted on the surface of the end head plate 303. During specific operation, the aircraft composite parts falling out from the forming cavity 10 fall onto the conveyor belt of the belt conveyor 5, and then the aircraft composite parts are transported and discharged through the belt conveyor 5, improving the material taking efficiency.

[0040] Further, as shown in Figure 1 it is specifically noted that a notch 6 is opened on one side surface of the box body 4, and a first cover plate 7 is hinged inside the notch 6. During specific operation, by opening the first cover plate 7, the inside of the box body 4 can be conveniently overhauled and maintained through the notch 6, improving the overhaul efficiency.

[0041] Further, as shown in Figure 1 it is specifically noted that a handle 8 is fixed on the outer side wall of the first cover plate 7, a second cover plate 15 is fixed at one end of the box body 4, and the belt conveyor 5 penetrates through the second cover plate 15. A rubber sleeve is fitted on the surface of the handle 8.

[0042] In summary: The output end of the drive motor 12 drives the pinion gear 13 to rotate, thereby driving the first shaft rod 17 and the lower mold 9 to rotate through the cooperation of the pinion gear 13 and the large gear 14, so that the molding cavity 10 on the lower mold 9 faces downward, enabling the aircraft composite parts in the molding cavity 10 to fall out automatically. The buffer assembly 2 is provided to blow out air upward, and the air flow buffers the aircraft composite parts. The structural design of the molding cavity 10 on the lower mold 9 facing downward utilizes the gravity effect, enabling the composite parts to fall off naturally after mold opening without manual intervention or mechanical ejection devices, greatly improving production efficiency and reducing manual operation costs. The air flow ejected upward by the blowing assembly forms an air cushion to provide flexible buffering for the falling composite parts, preventing them from directly hitting the workbench or conveying equipment and reducing deformation, scratches or internal structural damage caused by mechanical impact, significantly improving the product yield. The blowing process can synchronously remove the residual particles in the molding cavity 10, reducing pollution and ensuring the product quality in the next molding cycle. At the same time, the air flow inside the buffer assembly 2 is diverted and transported to the auxiliary ejection assembly 1, and the auxiliary ejection assembly 1 is used to assist in ejecting the aircraft composite parts in the molding cavity 10, effectively improving the discharging effect. On the one hand, the air flow diversion utilizes the existing blowing system without the need for an additional power source, reducing energy consumption and structural complexity. On the other hand, the pneumatic ejection provides a uniform and gentle demolding force, effectively protecting the structural integrity of the composite material. The air ejection and air buffering work together to form a complete demolding protection system, which can not only demold reliably but also buffer the falling impact, significantly improving production efficiency and product consistency. This integrated design saves mold space, reduces the overall weight and is convenient for maintenance. The height position of the buffer assembly 2 can be adjusted by the provided adjustment assembly 3, so that the distance between the buffer assembly 2 and the molding cavity 10 on the lower mold 9 can be conveniently adjusted, which is suitable for buffering different aircraft composite parts, effectively improving the applicable range of the overall device and the overall practicality. At the same time, it can accurately match aircraft composite parts of different sizes, shapes and weights to ensure that the air flow buffering force is always in the best position, avoiding buffer failure caused by insufficient height and preventing air flow dispersion and waste caused by too high a position. It can quickly adapt to the production requirements of multi-variety and small-batch aviation composite materials, and can complete the switching without replacing the mold or complex debugging, greatly shortening the production preparation time.

[0043] The drive motor 12 can be purchased on the market. The drive motor 12 is equipped with a power supply, which is a mature technology in this field and has been fully disclosed, so it will not be repeated in the specification.

Claims

1. A demoulding device for aircraft composite material processing, comprising a box (4), characterized in that: A lower mold (9) is installed at the top of the box body (4), and an upper mold (11) matched with the lower mold (9) is arranged directly above the lower mold (9). A molding cavity (10) is arranged in the lower mold (9) and the upper mold (11). A first shaft (17) and a second shaft (18) are fixed on the side of the lower mold (9) and are coaxially arranged and rotate through the side wall of the box body (4). A large gear (14) is fixed on the first shaft (17). A driving motor (12) is fixed on the outer wall of the box body (4). A small gear (13) meshing with the large gear (14) is fixed on the output end of the driving motor (12). A buffer component (2) is arranged at the bottom of the box body (4), and an auxiliary release component (1) connected to the buffer component (2) is arranged at the bottom of the molding cavity (10). An adjustment component (3) for adjusting the buffer component (2) is arranged outside the box body (4).

2. A demoulding device for aircraft composite material processing according to claim 1, characterized in that: The buffer assembly (2) comprises a concave plate (201) arranged at the bottom of the box body (4), a cavity (203) is provided inside the concave plate (201), an arc-shaped blowing pipe (202) communicating with the cavity (203) is fixed on the inner side wall of the concave plate (201), a plurality of the arc-shaped blowing pipes (202) are arranged and the plurality of arc-shaped blowing pipes (202) are distributed at equal intervals, and an air inlet pipe (204) communicating with the cavity (203) is fixed on the outer side wall of the concave plate (201).

3. A demoulding device for aircraft composite material processing according to claim 2, characterized in that: The auxiliary stripping component (1) comprises a groove (102) opened in the bottom of the molding cavity (10), the inner wall of the groove (102) is tightly fitted with a piston plate (104), a connecting rod (105) is fixed on the side of the piston plate (104), and a top stripping plate (106) adapted to the end of the groove (102) is fixed on the end of the connecting rod (105) away from the piston plate (104).

4. A demoulding device for aircraft composite material processing according to claim 3, characterized in that: A return spring (103) is arranged inside the groove (102), and two ends of the return spring (103) are respectively fixed to the bottom end of the groove (102) and the side of the piston plate (104).

5. The demoulding device for aircraft composite material processing according to claim 3, characterized in that: A through groove (101) communicating with the groove (102) is provided inside the second shaft rod (18); a connecting hose (107) communicating with the through groove (101) is rotatably connected inside one end of the second shaft rod (18) away from the lower mold (9); and the end of the connecting hose (107) away from the second shaft rod (18) is communicated with the cavity (203).

6. A demoulding device for aircraft composite material processing according to claim 5, characterized in that: The adjustment assembly (3) comprises a first convex plate (304) fixed on the outer wall of the concave plate (201), a second convex plate (307) fixed on the outer wall of the box body (4), a nut sleeve (305) fixed inside the second convex plate (307), a threaded rod (302) connected to the inner thread of the nut sleeve (305), and one end of the threaded rod (302) is rotatably connected to the first convex plate (304).

7. A demoulding device for aircraft composite material processing according to claim 6, characterized in that: A guide groove (306) slidably matched with the first convex plate (304) is provided on the side wall of the box body (4); an end plate (303) is fixed on the top end of the threaded rod (302); and a rubber sleeve is fitted on the surface of the end plate (303).

8. A demoulding device for aircraft composite material processing according to claim 7, characterized in that: A belt conveyor (5) is provided at the bottom of the box body (4), and the belt conveyor (5) is located at the center of the concave plate (201). A rubber sleeve is provided on the surface of the end plate (303).

9. A demoulding device for aircraft composite material processing according to claim 8, characterized in that: A notch (6) is provided on one side surface of the box body (4), and a first cover plate (7) is hinged inside the notch (6).

10. A demoulding device for aircraft composite material processing according to claim 9, characterized in that: A handle (8) is fixed on the outer wall of the first cover plate (7), a second cover plate (15) is fixed on one end of the box body (4), the belt conveyor (5) is arranged through the second cover plate (15), and a rubber sleeve is fitted on the surface of the handle (8).

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