A composite material forming die and method for the lower shell structure of a target drone fuselage panel

Abstract

A composite material forming mold and method for the lower shell structure of a target drone fuselage panel belongs to the technical field of composite material part forming. An insert, two positioning blocks and four drilling template mounting seats are respectively positioned and fixed on the upper platform of a frame, the two positioning blocks are symmetrically arranged on the left and right sides of the middle profile area of the frame, the insert is placed in the middle profile area and is arranged at a position corresponding to the R zone of the part to be formed, wherein the two drilling template mounting seats are symmetrically arranged on the left and right sides of the two positioning blocks, the two drilling templates are positioned and fixedly connected to the two drilling template mounting seats, the remaining two drilling template mounting seats are symmetrically arranged behind the two positioning blocks, the two angle drilling templates are positioned and fixedly connected to the remaining two drilling template mounting seats, the two locator assemblies are arranged across the two positioning blocks, and the two locator assemblies are positioned and fixed on the upper platform of the frame. The present invention adopts positioning blocks and inserts to control the rebound of the side wall of the composite material and the profile deformation to avoid deformation of the mold.

Description

Technical Field

[0001] The present invention belongs to the technical field of composite material parts forming, and in particular relates to a composite material forming die and method for a lower shell structure of a target drone fuselage panel. Background Art

[0002] Target drones, used as shooting training targets, are a type of unmanned aircraft. Target drone technology has developed rapidly in recent years, primarily due to their high maneuverability and agility, as well as their universality and modularity.

[0003] The target drone's molding mold structure is complex. To save weight, more weight-reducing designs are being implemented, consolidating many of the drone's components into a single part. However, this approach suffers from complex mold structures, high mold precision requirements, manufacturing difficulties, and demolding challenges. It is prone to mold deformation, resulting in poor mold-to-product fit, low part precision, and prone to surface deviations, failing to meet design requirements. Therefore, a more rationally designed molding mold and accompanying molding method are needed to meet the molding requirements of the lower shell of the target drone's fuselage panel. Summary of the Invention

[0004] The present invention aims to solve the above problems in the prior art and provide a composite material forming die and method for the lower shell structure of the target aircraft fuselage panel. The present invention uses positioning blocks and inserts to control the side wall rebound and surface deformation of the composite material.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0006] A composite material forming die for the lower shell structure of a target drone fuselage panel, comprising two positioning blocks, an insert, a frame, two angled vertical drilling templates, two angled drilling templates, four drilling template mounting seats and two locator assemblies;

[0007] The insert, two positioning blocks and four drilling template mounting seats are respectively positioned and fixed on the upper platform of the frame. The two positioning blocks are symmetrically arranged on the left and right sides of the middle surface area of the frame. The insert is placed in the middle surface area and is set at the position corresponding to the R area of the part to be formed. Two of the four drilling template mounting seats are symmetrically arranged on the left and right sides of the two positioning blocks. The two angled vertical drilling templates are arranged in a one-to-one correspondence with the two drilling template mounting seats, and the two angled vertical drilling templates are respectively positioned and fixed on the corresponding drilling template mounting seats. The remaining two drilling template mounting seats are symmetrically arranged behind the two positioning blocks. The two angled drilling templates are arranged in a one-to-one correspondence with the remaining two drilling template mounting seats, and the two angled drilling templates are respectively positioned and fixed on the corresponding drilling template mounting seats. The two locator assemblies are arranged across the two positioning blocks, and the two locator assemblies are respectively positioned and fixed on the upper platform of the frame.

[0008] Furthermore, the two locator assemblies each include a card plate, two locators, two corner seats and two supports; the two supports are symmetrically arranged on the left and right, and the two supports are positioned and fixed on the upper platform of the frame. The upper end of each support is positioned and fixedly connected to the corresponding corner seat, and the two corner seats are respectively positioned and fixedly connected to the two ends of the card plate. The two locators are symmetrically arranged and the straight handles of the two locators are respectively positioned and fixedly connected to the card plate.

[0009] Furthermore, the positioner consists of a straight handle, a curved handle and a positioning head fixedly connected to the outer end of the curved handle.

[0010] Furthermore, the support is composed of a top plate, a bottom plate, a column and two reinforcing ribs. A column is fixed between the top plate and the bottom plate. Two reinforcing ribs are symmetrically provided on both sides of the column. The two reinforcing ribs are fixedly connected to the column and the bottom plate respectively.

[0011] Furthermore, four lifting rings are symmetrically fixed on the left and right sides of the frame.

[0012] A method for forming a composite material of a lower shell structure of a target drone fuselage panel, the method comprising the following steps:

[0013] Step 1: Cutting materials according to process requirements;

[0014] Step 2: Lay the mold surface on the surface of the middle mold area of the two positioning blocks, the inserts and the frame. After the flat paving is completed, the two positioning blocks and the inserts with the mold surface are packaged in a vacuum bag for one packaging. After the packaging is completed, a full vacuum of at least 0.08MPa is drawn, and then hot compaction is carried out at a temperature of 60-70° and a pressure of 0.2MPa. The temperature and pressure are kept at this temperature for 30 minutes. After that, the vacuum bag is removed;

[0015] Step 3: Place the hot-compacted mold surface, two positioning blocks, and inserts in a vacuum bag, and place a peelable cloth, isolation film, and breathable felt on the mold surface in sequence. After placement, remove the positioner assembly. Place a peelable cloth, isolation film, and breathable felt in the same order on the position where the positioner assembly was removed for secondary packaging. After packaging, fully vacuum the bag to a minimum of 0.08 MPa.

[0016] Step 4: Place the mold into an autoclave for curing, raise the temperature to 120°, increase the pressure to 0.6 MPa, maintain the temperature and pressure for 120-180 minutes, and detect that the vacuum negative pressure reading does not drop by more than 0.017 MPa;

[0017] Step 5: After curing is completed, the peelable cloth, isolation film, breathable felt, and vacuum bag are removed without opening the mold to form a molded part blank. After the mold cools to room temperature, positioning holes are drilled on the molded part blank using an angled vertical drill template and an angled drill template. The mold and the molded part blank are sent to the CNC machining center together. The tooling reference holes set around the frame are used to establish the reference. The edge of the molded part blank is pressed by vacuuming. The edge of the molded part blank is CNC milled, leaving a 0.5mm margin on the thickness without milling through, to form the molded part;

[0018] Step 6: Demolding, mark the molded part as an identification, use the composite demoulding auxiliary tool to apply force on the flange of the molded part, and control the force to be between 1000-2000N;

[0019] Step 7: Inspect the molded parts.

[0020] The beneficial effects of the present invention relative to the prior art are:

[0021] 1) Due to the complex structure and high precision of the lower shell of the target aircraft fuselage panel, it is difficult to demould after molding. To address these problems, the composite material molding mold for the lower shell structure of the target aircraft fuselage panel developed by the present invention can well solve the above problems.

[0022] 2) Improvements have been made to the processing and manufacturing process; the present invention adopts an optimized process scheme and uses positioning blocks and inserts to control the side wall rebound and surface deformation of the composite material, thereby avoiding the influence of factors such as mold deformation and inaccurate surface, thereby improving processing efficiency, greatly reducing processing time and labor, significantly shortening the manufacturing cycle, and reducing manufacturing costs.

[0023] 3) Because the lower shell of the drone's fuselage panels is constructed of composite materials, the traditional composite layup process cannot meet the high precision and complex surface requirements of the final product. However, a composite molding method that uses positioning blocks and inserts to control composite sidewall springback and surface deformation ensures the finished part meets the required precision and reduces worker hours, eliminating the time-consuming and labor-intensive operation issues. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is an axonometric view of a composite material forming die for the lower shell structure of a target drone fuselage panel according to the present invention;

[0025] Figure 2 This is a front view of a composite material forming die for a lower shell structure of a target drone fuselage panel according to the present invention;

[0026] Figure 3 It is a top view of a composite material forming die for the lower shell structure of a target drone fuselage panel according to the present invention;

[0027] Figure 4 It is a left view of a composite material forming die for the lower shell structure of a target drone fuselage panel according to the present invention;

[0028] Figure 5 It is a top view of the two positioning blocks arranged symmetrically;

[0029] Figure 6 yes Figure 5 Left view of;

[0030] Figure 7 yes Figure 5 The main view;

[0031] Figure 8 It is the three-view drawing of the inlay;

[0032] Figure 9 yes Figure 8 Left view of;

[0033] Figure 10 yes Figure 8 A top view of

[0034] Figure 11 is the main view of the frame;

[0035] Figure 12 yes Figure 11 Left view of;

[0036] Figure 13 yes Figure 11 A top view of

[0037] Figure 14 It is the three-view drawing of the drilling template;

[0038] Figure 15 yes Figure 14 Left view of;

[0039] Figure 16 yes Figure 14 A top view of

[0040] Figure 17 This is the main view of the angle drill template;

[0041] Figure 18 yes Figure 17 Left view of;

[0042] Figure 19 yes Figure 17 A top view of

[0043] Figure 20 This is the main view of the drill template mounting base;

[0044] Figure 21 yes Figure 20A top view of

[0045] Figure 22 yes Figure 21 Left view of;

[0046] Figure 23 This is the main view of the locator component;

[0047] Figure 24 yes Figure 23 Left view of;

[0048] Figure 25 yes Figure 23 A top view of

[0049] Figure 26 It is the main view of the locator;

[0050] Figure 27 yes Figure 26 Left view of;

[0051] Figure 28 yes Figure 26 A top view of

[0052] Figure 29 This is the main view of the pallet;

[0053] Figure 30 yes Figure 29 Left view of;

[0054] Figure 31 yes Figure 29 A top view of

[0055] Figure 32 It is the main view of the corner seat;

[0056] Figure 33 yes Figure 32 A top view of

[0057] Figure 34 yes Figure 33 A-direction view;

[0058] Figure 35 It is the main view of the support;

[0059] Figure 36 yes Figure 35 Left view of;

[0060] Figure 37 yes Figure 35 Top view of .

[0061] The names and numbers of the components involved in the above drawings are as follows:

[0062] Positioning block 01, insert 02, frame 03, drilling template 04, angle drilling template 05, drilling template mounting base 06, locator assembly 07, locator 08, clamping plate 09, angle seat 10, support 11, lifting ring 12, straight handle 13, curved handle 14, positioning head 15, top plate 16, bottom plate 17, column 18, reinforcement rib 19, intermediate profile area 20. DETAILED DESCRIPTION

[0063] Specific implementation method 1: Figure 1-Figure 37 As shown, this embodiment discloses a composite material forming die for the lower shell structure of a target aircraft fuselage panel, including two positioning blocks 01, an insert 02, a frame 03, two angled vertical drilling templates 04, two angled drilling templates 05, four drilling template mounting seats 06 and two positioner assemblies 07;

[0064] The insert 02, two positioning blocks 01 and four drilling template mounting seats 06 are respectively positioned and fixed (by screws) on the upper platform of the frame 03 (the frame 03 consists of a frame body and an upper platform fixedly connected to the top of the frame body). The two positioning blocks 01 are symmetrically arranged on the left and right sides of the middle profile area 20 of the frame 03. The insert 02 is placed in the middle profile area 20 and is set at a position corresponding to the R area of the part to be formed. Two of the four drilling template mounting seats 06 are symmetrically arranged on the left and right sides of the two positioning blocks 01. The two angled vertical drilling templates 04 are connected to the two drilling template mounting seats 06. 6 are arranged in a one-to-one correspondence, and the two angle vertical drilling templates 04 are respectively positioned and fixed on the corresponding drilling template mounting seats 06 (by screws), and the remaining two drilling template mounting seats 06 are symmetrically arranged behind the two positioning blocks 01. The two angle drilling templates 05 are arranged in a one-to-one correspondence with the remaining two drilling template mounting seats 06, and the two angle drilling templates 05 are respectively positioned and fixed on the corresponding drilling template mounting seats 06 (by screws). The two locator assemblies 07 are arranged across the two positioning blocks 01, and the two locator assemblies 07 are respectively positioned and fixed on the upper platform of the frame 03 (by screws).

[0065] The structure of the insert 02, the two angle vertical drilling templates 04 and the angle drilling template 05 is prior art.

[0066] Furthermore, the two locator assemblies 07 each include a clamping plate 09, two locators 08, two angle seats 10 and two supports 11; the two supports 11 are symmetrically arranged on the left and right, and the two supports 11 are positioned and fixed on the upper platform of the frame 03 (through screws), and the upper end of each support 11 is positioned and fixedly connected to the corresponding angle seat 10 (through screws), and the two angle seats 10 are respectively positioned and fixedly connected to the two ends of the clamping plate 09 (through screws), and the two locators 08 are symmetrically arranged and the straight handles 13 of the two locators 08 are respectively positioned and fixedly connected to the clamping plate 09 (through screws).

[0067] Furthermore, the positioner 08 is composed of a straight handle 13 , a curved handle 14 and a positioning head 15 fixedly connected to the outer end of the curved handle 14 .

[0068] Furthermore, the support 11 is composed of a top plate 16, a bottom plate 17, a column 18 and two reinforcing ribs 19. The column 18 is fixed between the top plate 16 and the bottom plate 17. Two reinforcing ribs 19 are symmetrically provided on both sides of the column 18. The two reinforcing ribs 19 are fixedly connected to the column 18 and the bottom plate 17 respectively.

[0069] Furthermore, four lifting rings 12 (for lifting the mold) are symmetrically fixed on the left and right sides of the frame 03.

[0070] Specific implementation method 2: Figure 1-Figure 37 As shown, this embodiment discloses a method for forming a composite material of a lower shell structure of a target aircraft fuselage panel using the mold described in the first embodiment, the method comprising the following steps:

[0071] Step 1: Cut the material according to the process requirements (using a cutting machine) (ensure the cutting angle and size);

[0072] Step 2: Lay the mold surface on the surface of the middle mold surface area 20 of the two positioning blocks 01, the insert 02 and the frame 03. After the flat paving is completed, the two positioning blocks 01 and the insert 02 with the mold surface are packaged in a vacuum bag for one packaging. After the packaging is completed, a full vacuum of at least 0.08MPa is drawn. Then, hot compaction is carried out at a temperature of 60-70° and a pressure of 0.2MPa. The temperature and pressure are kept constant for 30 minutes (full vacuum leakage check, full vacuum of at least 0.08MPa is drawn. Before the leak check, it must be connected to the vacuum system for at least 15 minutes, and the vacuum system must be turned off. After 5 minutes, the vacuum gauge reading does not drop by more than 0.017MPa). Then, the vacuum bag is removed.

[0073] Step 3: Place the hot-compacted mold surface, two positioning blocks 01, and insert 02 in a vacuum bag, and place a peelable cloth, an isolation film, and a breathable felt on the mold surface in sequence. After placement, remove the positioner assembly 07. Place a peelable cloth, an isolation film, and a breathable felt in the same order at the position where the positioner assembly 07 was removed for secondary packaging. After packaging, pump a full vacuum to a minimum of 0.08 MPa (full vacuum leak check: pump a full vacuum to a minimum of 0.08 MPa. Before leak checking, connect to the vacuum system for at least 15 minutes, turn off the vacuum system, and after 5 minutes, the vacuum gauge reading should not drop more than 0.017 MPa).

[0074] Step 4: Place the mold into an autoclave for curing, raise the temperature to 120°, increase the pressure to 0.6 MPa, maintain the temperature and pressure for 120-180 minutes, and detect that the vacuum negative pressure reading does not drop by more than 0.017 MPa;

[0075] Step 5: After curing is completed, the peelable cloth, isolation film, breathable felt, and vacuum bag are removed without opening the mold to form a molded part blank. After the mold cools to room temperature, positioning holes are drilled on the molded part blank using the angled vertical drilling template 04 and the angled drilling template 05. The mold and the molded part blank are sent to the CNC machining center together. The tooling reference holes set around the frame 03 are used to establish the reference. The edge of the molded part blank is pressed tightly (vacuum suction) by vacuuming. The edge of the molded part blank is CNC milled, leaving a 0.5mm margin on the thickness without milling through, to form the molded part;

[0076] Step 6: De-molding (a wooden or plastic wedge composite demoulding aid can be used to prevent damage to the molded part or the mold). Mark the molded part as an identification. Use a composite demoulding aid (existing parts) to apply force at the flange of the molded part, and control the force to 1000-2000N. Note that the force should be applied evenly at the four corners of the molded part.

[0077] Step 7: Transfer the molded parts to the three-coordinate inspection equipment, inspect the molded parts, and check the quality of the molded parts: the thickness tolerance is allowed to be ±5%, the beam and wall panel mold fit is ≤0.75mm, the long girder axis (compared to the theoretical position) deviation is ±2mm, the porosity is not more than 2%, and a 100% area defect inspection is carried out. After passing the inspection, it is delivered for use; if it is found that the rebound angle and radius compensation are insufficient, compensation is made according to the actual measurement of the molded parts; if other problems occur, the molded parts are repaired.

[0078] Positioning Block 01 consists of five individual blocks, all constructed of Q235-AF steel and welded together. After welding, stress relief is applied. The aerodynamic profile of Positioning Block 01 is machined using CNC machining methods and a three-dimensional model, creating a machining program. The primary function of Positioning Block 01 is to ensure that composite materials can be molded into a desired product shape. Positioning Block 01 is positioned and secured to the upper platform of Frame 03 using screws (with an H7 / g6 clearance fit for easy demolding).

[0079] Insert 02 is welded from Q235-AF steel, stress-relieved after welding, and machined to aerodynamic profiles. A machining program is compiled based on a 3D digital model, and the profile of Insert 02 is produced using CNC machining. Insert 02's primary function is to create a qualified composite part. Insert 02 is positioned and secured to the upper platform of Frame 03 using screws (an H7 / g6 clearance fit ensures easy demolding).

[0080] Frame 03, the base of the entire mold, is welded from Q235-AF steel. Stress relief is applied after welding. Frame 03's frame is welded from square steel. The top surface of Frame 03 is welded to the upper platform of Frame 03, forming a solid Frame 03. The intermediate profile is machined using a machining program compiled according to the aerodynamic profile and a three-dimensional digital model. Frame 03 serves as the foundation for mounting positioning block 01, insert 02, drill template mounting base 06, positioner assembly 07, and lifting ring 12.

[0081] Drill template 04 (material: aluminum 6061-T651) is programmed according to the 3D model. Five-axis CNC machining is used to drill the template positioning holes, screw holes, and pin mounting holes. Drill template 04 is positioned and fixed to the corresponding drill template mounting seat 06 using screws.

[0082] Angle Drilling Template 05 (Material: Aluminum 6061-T651) is programmed according to the 3D model. Five-axis CNC machining is used to drill template positioning holes, screw holes, and pin mounting holes. Angle Drilling Template 05 is positioned and secured to the corresponding Drilling Template Mounting Block 06 using screws.

[0083] Drill template mounting seat 06 (material: metal Q235-AF), arrange screw holes and pin holes according to the theoretical positions on site, install screws and pins to match with frame 03, and adopt the matching relationship of H7 / g6 clearance matching.

[0084] The positioner assembly 07 includes multiple positioners 08, a clamping plate 09, an angle seat 10, and a support 11.

[0085] The positioning device 08 (material: metal Q235-AF) is programmed according to the three-dimensional digital model, and the positioning holes, screw holes and pin holes are processed on the positioning device 08 by the five-axis CNC machining method. The positioning device 08 and the clamping plate 09 are installed in the appropriate position through screws and pins to locate the reinforcement of the composite material molded parts of the lower panel shell of the fuselage panel.

[0086] The card plate 09 (material: aluminum 6061-T651) is processed according to the three-dimensional digital model and the processing program is compiled. The positioning holes, screw holes and pin holes are processed on the card plate 09 by the five-axis CNC processing method. The card plate 09 and the angle seat 10 are installed in the appropriate position through screws.

[0087] Positioning holes, screw holes and pin holes are processed on the angle seat 10 (material: metal Q235-AF), and the angle seat 10 and the clamping plate 09 are installed in appropriate positions through screws.

[0088] The support 11 (material: metal Q235-AF) is matched with the frame 03 through screws and installed in a suitable position, using a clearance fit of H7 / g6.

[0089] The lifting ring 12 (standard part) is used for lifting the mold, and the lifting ring 12 adopts a universal rotating lifting ring.

[0090] The above are only preferred specific implementation methods of the patent of the present invention, but the scope of protection of the patent of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the patent of the present invention, who makes equivalent replacements or changes based on the technical solution of the patent of the present invention and the invention patent concept of the patent, should be covered by the scope of protection of the patent of the present invention.

Claims

1. A composite material forming die for the lower shell structure of a target drone fuselage panel, characterized by: It includes two positioning blocks (01), an insert (02), a frame (03), two angle vertical drilling templates (04), two angle drilling templates (05), four drilling template mounting bases (06) and two positioner assemblies (07); The insert (02), two positioning blocks (01) and four drilling template mounting seats (06) are respectively positioned and fixed on the upper platform of the frame (03), the two positioning blocks (01) are symmetrically arranged on the left and right sides of the middle profile area (20) of the frame (03), the insert (02) is placed in the middle profile area (20) and is arranged at a position corresponding to the R area of the part to be formed, two drilling template mounting seats (06) of the four drilling template mounting seats (06) are symmetrically arranged on the left and right sides of the two positioning blocks (01), and the two angle vertical drilling templates (04) are connected one by one to the two drilling template mounting seats (06). Correspondingly arranged, and two angled vertical drilling templates (04) are respectively positioned and fixed on the corresponding drilling template mounting seats (06), the remaining two drilling template mounting seats (06) are symmetrically arranged behind the two positioning blocks (01), the two angled drilling templates (05) are arranged in a one-to-one correspondence with the remaining two drilling template mounting seats (06), and the two angled drilling templates (05) are respectively positioned and fixed on the corresponding drilling template mounting seats (06), the two locator assemblies (07) are arranged across the two positioning blocks (01), and the two locator assemblies (07) are respectively positioned and fixed on the upper platform of the frame (03); The two positioner assemblies (07) each include a card plate (09), two positioners (08), two angle seats (10) and two supports (11); the two supports (11) are symmetrically arranged on the left and right sides, and the two supports (11) are positioned and fixed on the upper platform of the frame (03), the upper end of each support (11) is positioned and fixedly connected to the corresponding angle seat (10), the two angle seats (10) are respectively positioned and fixedly connected to the two ends of the card plate (09), the two positioners (08) are symmetrically arranged, and the straight handles (13) of the two positioners (08) are respectively positioned and fixedly connected to the card plate (09); four lifting rings (12) are symmetrically fixed on the left and right sides of the frame (03).

2. The composite material forming die for the lower shell structure of the target drone fuselage panel according to claim 1, characterized in that: The positioner (08) is composed of a straight handle (13), a curved handle (14) and a positioning head (15) fixedly connected to the outer end of the curved handle (14).

3. The composite material forming die for the lower shell structure of the target drone fuselage panel according to claim 1, characterized in that: The support (11) is composed of a top plate (16), a bottom plate (17), a column (18) and two reinforcing ribs (19). The column (18) is fixed between the top plate (16) and the bottom plate (17). Two reinforcing ribs (19) are symmetrically provided on both sides of the column (18). The two reinforcing ribs (19) are fixedly connected to the column (18) and the bottom plate (17), respectively.

4. A method for molding a composite material of a lower shell structure of a target drone fuselage panel using the mold according to any one of claims 1 to 3, characterized in that: The method comprises the following steps: Step 1: Cutting materials according to process requirements; Step 2: Lay the mold surface on the surface of the middle mold surface area (20) of the two positioning blocks (01), the insert (02) and the frame (03). After the flat laying is completed, the two positioning blocks (01) and the insert (02) with the mold surface are packaged in a vacuum bag and packaged once. After the packaging is completed, a full vacuum of at least 0.08MPa is drawn, and then hot compaction is performed at a temperature of 60-70° and a pressure of 0.2MPa. The temperature and pressure are kept constant for 30 minutes, and then the vacuum bag is removed; Step 3: Place the hot-compacted mold surface, two positioning blocks (01) and insert (02) in a vacuum bag, and place a peelable cloth, an isolation film, and a breathable felt on the mold surface in sequence. After placement, remove the positioner assembly (07). Place a peelable cloth, an isolation film, and a breathable felt in the same order at the position where the positioner assembly (07) was removed for secondary packaging. After packaging, draw a complete vacuum of at least 0.08 MPa. Step 4: Place the mold into an autoclave for curing, raise the temperature to 120°, increase the pressure to 0.6 MPa, maintain the temperature and pressure for 120-180 minutes, and detect that the vacuum negative pressure reading does not drop by more than 0.017 MPa; Step 5: After the curing is completed, the peelable cloth, isolation film, breathable felt, and vacuum bag are removed without opening the mold to form a molded part blank. After the mold is cooled to room temperature, a positioning hole is drilled on the molded part blank using an angled vertical drilling template (04) and an angled drilling template (05). The mold and the molded part blank are sent to a CNC machining center together. The tooling reference holes set around the frame (03) are used to establish a reference. The edge of the molded part blank is pressed by vacuuming. The edge of the molded part blank is milled by CNC, leaving a 0.5mm margin on the thickness without milling through, to form a molded part. Step 6: Demolding, mark the molded part as an identification, use the composite demoulding auxiliary tool to apply force on the flange of the molded part, and control the force to be between 1000-2000N; Step 7: Inspect the molded parts.

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