A forming device of an eVTOL flying car composite reinforcing beam

Abstract

The utility model belongs to low altitude composite material forming technical field, and a kind of eVTOL flying car composite material reinforcing beam forming device, to solve tooling structure and process method technical difficulty, make technical preparation for actual production. Including template assembly, for completing the lower C of reinforcing beam Paste and compaction;Inlay block assembly is set outside template assembly, for completing the laying and compaction of reinforcing beam two sides edge strip;Pressurizing device is set outside inlay block assembly, for the compaction of template assembly two sides;Honeycomb sample plate is placed in template assembly, for completing the middle part of reinforcing beam Paste and preforming. The utility model realizes the lightweight, high strength, corrosion resistance of eVTOL flying car, improves part manufacturing precision, simplifies manufacturing process.

Description

Technical Field

[0001] This utility model belongs to the field of low-altitude composite material molding technology, specifically relating to a molding device for a composite material reinforcing beam of an eVTOL flying car. Background Technology

[0002] Lightweight, high-strength, and corrosion-resistant composite materials play a crucial role in the structural design of eVTOLs. As a key load-bearing component of eVTOLs, the performance of reinforcing beams directly affects the overall safety, payload capacity, and flight efficiency of the aircraft. Therefore, the application of composite reinforcing beams has become a development direction for eVTOL flying cars; however, currently, the molding of composite reinforcing beams still faces challenges. Summary of the Invention

[0003] To address the significant technical challenges in composite material molding technology, this invention provides a molding device for composite material reinforcing beams of eVTOL flying cars. This device resolves technical difficulties related to tooling structure and process methods, thus preparing the vehicle for actual production.

[0004] The technical solution adopted by this utility model is: A molding apparatus for a composite material reinforcing beam of an eVTOL flying car, comprising: The template assembly is used to complete the lower C-laying and compaction of the reinforcing beam; The insert assembly, located on the outside of the template assembly, is used to complete the laying and compaction of the side edge strips of the reinforcing beam; A pressure device, located on the outside of the insert assembly, is used to press the two sides of the template assembly together. The honeycomb template is placed on the template assembly to complete the middle laying and preforming of the reinforcing beam.

[0005] Furthermore, the template assembly includes a template, a mold body, and a release template; the mold body is laid horizontally on the template and is connected by screws and positioned by locating pins; the two release templates are respectively spaced on the left and right outer sides of the template and cooperate with the mold body to form a forming mold for the reinforcing beam.

[0006] Furthermore, each of the demolding templates has a threaded hole pre-drilled on its upper surface for demolding.

[0007] Furthermore, the insert assembly includes multiple inserts, multiple guide keys, and multiple connecting plates; the multiple inserts are arranged in parallel on the left and right sides of the template, and each insert has a groove at its bottom to slide in cooperation with multiple guide keys fixed on the template, and adjacent inserts are connected by connecting plates.

[0008] Furthermore, the pressurizing device includes two seat plates, multiple lead screws, and multiple nuts; two lead screws are provided on the outer side of each insert, the inner end of each lead screw is rotatably connected to the outer side of the corresponding insert through a bearing, the outer end of each lead screw passes through a through hole provided on the seat plate and is threadedly connected to a nut, and the nut is fixedly connected to the seat plate. The two seat plates are provided on the left and right outer sides of the insert assembly, and are connected to the template plate by screws and positioned by locating pins.

[0009] Furthermore, the front and rear ends of the honeycomb template are positioned with the mold body by positioning pins.

[0010] Furthermore, a drill jig is mounted on the insert assembly.

[0011] Compared with the prior art, the present invention has the following advantages: This invention achieves lightweight, high strength, and corrosion resistance in eVTOL flying cars, while improving the manufacturing precision of parts and simplifying the manufacturing process. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of a reinforced beam structure; Figure 2 This is an isometric drawing of this utility model; Figure 3 This is a top view of the present invention; the insert assembly is not shown. The components include: 1. Reinforcing beam; 2. Profile assembly; 201. Profile; 202. Mold body; 203. Release template; 2031. Threaded hole; 3. Insert assembly; 301. Insert; 302. Guide key; 303. Connecting plate; 4. Pressurizing device; 401. Lead screw; 402. Seat plate; 403. Nut; 5. Honeycomb template; 6. Positioning pin; 7. Screw; 8. Drill jig. Detailed Implementation

[0013] To better understand the purpose, structure, and function of this utility model, a more detailed description of this utility model will be provided below with reference to the accompanying drawings.

[0014] like Figures 2-3 As shown, this utility model provides a molding device for a composite material reinforcing beam of an eVTOL flying car, including... The template assembly 2 is used to complete the lower C-laying and compaction of the reinforcing beam 1; The insert assembly 3 is set on the outside of the template assembly 2 and is used to complete the laying and compaction of the edge strips on both sides of the reinforcing beam 1; The pressurizing device 4 is located on the outside of the insert assembly 3 and is used to press the two sides of the template assembly 2. Honeycomb template 5 is placed on template assembly 2 to complete the middle laying and preforming of reinforcing beam 1.

[0015] like Figures 2-3 As shown, the template assembly 2 includes a template 201, a mold body 202, and a release template 203; the mold body 202 is laid horizontally on the template 201 and connected by screws 7 and positioned by positioning pins 6. The two release templates 203 are respectively spaced on the left and right outer sides of the template 201 and cooperate with the mold body 202 to form the forming mold of the reinforcing beam 1.

[0016] like Figures 2-3 As shown, each of the demolding templates 203 has a threaded hole 2031 pre-drilled on its upper surface for demolding.

[0017] like Figures 2-3 As shown, the insert assembly 3 includes multiple inserts 301, multiple guide keys 302, and multiple connecting plates 303. The multiple inserts 301 are arranged in parallel on the left and right sides of the template 203, and each insert 301 has a sliding groove at its bottom, which slides in cooperation with the multiple guide keys 302 fixed on the template 201. Adjacent inserts 301 are connected by connecting plates 303, and the two ends of the connecting plates 303 are connected to the corresponding inserts 301 by screws 7 and positioned by positioning pins 6.

[0018] The guide key 302 is set in the left and right direction.

[0019] like Figures 2-3 As shown, the pressurizing device 4 includes two seat plates 402, multiple lead screws 401, and multiple nuts 403; two lead screws 401 are provided on the outer side of each insert 301, the inner end of each lead screw 401 is rotatably connected to the outer side of the corresponding insert 301 through a bearing, and the outer end of each lead screw 401 passes through a through hole provided on the seat plate 402 and is threadedly connected to the nut 403, and the nut 403 is fixedly connected to the seat plate 402. The two seat plates 402 are provided on the left and right outer sides of the insert assembly 3, and are connected to the template 201 by screws 7 and positioned by positioning pins 6.

[0020] like Figures 2-3 As shown, the front and rear ends of the honeycomb template 5 are positioned with the mold body 202 by positioning pins 6.

[0021] like Figures 2-3 As shown, a drill jig 8 is mounted on the insert assembly 3.

[0022] The surface of the honeycomb template 5 is set according to the middle part of the reinforcing beam 1.

[0023] A method for molding composite material reinforcing beams for eVTOL flying cars has been developed. The method involves separately laying the lower C section of the reinforcing beam 1 and the double-sided edge strips, and then assembling them to complete the molding process. The method includes the following steps: Step 1: Move the tooling into the clean room, clean the surface of the tooling, assemble the mold 202 of the template assembly 2 with the template 201, connect them with screws 7 and position them with positioning pins 6. Complete the laying and compaction of the lower C of the reinforcing beam 1.

[0024] During this process, the ambient temperature and humidity conditions must meet the requirements: a temperature of 18-22℃ and a humidity of less than 25-30%. The purpose is to avoid layup defects and ensure the quality of part molding.

[0025] Step 2: Connect the left and right side inserts 301 sequentially using the connecting plate 303, screws 7, and positioning pins 6. After assembly, use the insert assembly 3 to lay and compact the edge strips on both sides of the reinforcing beam 1.

[0026] Step 3: Using the pressure device 4, push the two side inserts 301 along the guide key 302 to both sides of the mold body 202 and press them tightly. Connect the insert assembly 3 and the mold plate 201 with screws 7 and position them with cylindrical pins. After placing the triangular area filler, continue to lay the upper C of the reinforcing beam 1 using the insert assembly 3 and the mold body 202. Then place the honeycomb template 5 on the mold body 202 and position it with the positioning pins 6 at both ends in the length direction. After placing the honeycomb, continue to complete the laying and preforming of the reinforcing beam 1.

[0027] This step completes the upper C-laying and preforming of the reinforcing beam 1.

[0028] The insert assembly 3 is pressed by the pressure device 4 to ensure a more accurate fit between the insert assembly 3 and the mold body 202.

[0029] The honeycomb template 5 is used to reinforce the beam 1 to ensure more accurate honeycomb positioning.

[0030] Step 4: Encapsulation, container loading, and curing.

[0031] Step 5: After the can is removed from the mold, drilling and demolding processes are carried out. The demolding of the reinforcing beam 1 is assisted by the demolding templates 203 on both sides of the mold body 202.

[0032] During this process, connect the vacuum pipeline, and once the vacuum inside the vacuum bag stabilizes, disconnect the vacuum source after 15 minutes. Within 5 minutes, the vacuum gauge reading should not drop by more than 0.0017 MPa. Continue heating to 130℃ and evacuate to 0.095 MPa. Once the positive pressure reaches 0.6 MPa, allow atmospheric flow and close the vacuum valve. Maintain the temperature and pressure for 120-180 minutes. The negative pressure reading inside the vacuum bag should not drop by more than 0.017 MPa. Then begin cooling at a rate of 1℃ / min. When the temperature drops below 80℃ and the pressure drops to 0 MPa, open the autoclave. Once the mold temperature drops below 20℃, demold the reinforcing beam 1, remove the molded part, clean the surface, remove any burrs, and cut the part along the cutting line. This completes the preparation of the reinforcing beam 1.

[0033] Steps four and five are used to complete the curing, drilling, and demolding of the reinforcing beam 1.

[0034] With the help of the demolding templates 203 on both sides of the mold body 202, the demolding of the reinforcing beam 1 is made easier, and the deformation of the beam is reduced.

[0035] Using this method, composite material reinforcing beams for eVTOL flying cars can be manufactured.

[0036] It is understood that this utility model has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of this utility model. Furthermore, under the teachings of this utility model, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of this utility model.

Claims

1. A molding device for a composite material reinforcing beam of an eVTOL flying car, characterized in that: include The template assembly (2) is used to complete the lower C-laying and compaction of the reinforcing beam (1); The insert assembly (3) is set on the outside of the template assembly (2) and is used to complete the laying and compaction of the edge strips on both sides of the reinforcing beam (1); A pressure device (4) is installed on the outside of the insert assembly (3) to press the two sides of the template assembly (2); The honeycomb template (5) is placed on the template assembly (2) to complete the middle laying and preforming of the reinforcing beam (1).

2. The forming apparatus for a composite material reinforcing beam of an eVTOL flying car according to claim 1, characterized in that: The template assembly (2) includes a template (201), a mold body (202), and a stripping template (203). The mold body (202) is laid horizontally on the template (201) and connected by screws (7) and positioned by positioning pins (6). The two stripping templates (203) are respectively spaced on the left and right sides of the template (201) and cooperate with the mold body (202) to form a forming mold for the reinforcing beam (1).

3. The forming apparatus for a composite material reinforcing beam of an eVTOL flying car according to claim 2, characterized in that: Each of the demolding templates (203) has a threaded hole (2031) pre-drilled on its upper surface for demolding.

4. The forming device for a composite material reinforcing beam of an eVTOL flying car according to claim 2, characterized in that: The insert assembly (3) includes multiple inserts (301), multiple guide keys (302), and multiple connecting plates (303); the multiple inserts (301) are arranged in parallel on the left and right sides of the template (203), and each insert (301) has a groove at the bottom to slide with multiple guide keys (302) fixed on the template (201), and adjacent inserts (301) are connected by connecting plates (303).

5. The forming apparatus for a composite material reinforcing beam of an eVTOL flying car according to claim 4, characterized in that: The pressurizing device (4) includes two seat plates (402), multiple lead screws (401) and multiple nuts (403); two lead screws (401) are provided on the outer side of each insert (301), the inner end of each lead screw (401) is rotatably connected to the outer side of the corresponding insert (301) through a bearing, the outer end of each lead screw (401) passes through a through hole provided on the seat plate (402) and is threadedly connected to the nut (403), and the nut (403) is fixedly connected to the seat plate (402). The two seat plates (402) are provided on the left and right outer sides of the insert assembly (3), and are connected to the template (201) by screws (7) and positioned by positioning pins (6).

6. The forming apparatus for a composite material reinforcing beam of an eVTOL flying car according to claim 1, characterized in that: The honeycomb template (5) is positioned between its front and rear ends and the mold body (202) by positioning pins (6).

7. The forming apparatus for a composite material reinforcing beam of an eVTOL flying car according to claim 4, characterized in that: The insert assembly (3) is equipped with a drill jig (8).

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