A double-t type multi-box structure radar all-carbon fiber case integral forming die and method

Abstract

The present application relates to a kind of double T type multi-box structure radar whole carbon fiber machine box integral forming die and method, die includes bottom plate die, front end mid-cabin die, front end upper cabin die and fan cabin die.Forming method includes the following steps: mold cleaning;Split die screw assembly;Each front end cabin skin is laid;After front end cabin die is assembled, front end cabin middle skin is laid;Fan cabin inner skin and middle skin are laid;After fan cabin die and front end cabin die are assembled, outer skin is laid;Part forming;Demoulding, post-processing.The present application is combined with the use of multiple forming dies, uses metal mold thermal expansion extrusion auxiliary autoclave forming technology, through the design method of the layering of subarea layering again combination overall coating, realizes the once co-curing forming new technical method of whole carbon fiber electronic machine box with double T type, central web and other difficult forming structure.

Description

Technical Field

[0001] This invention belongs to the field of radar radio frequency front-end processing and manufacturing, and relates to an integrated molding mold and molding method for radar full carbon fiber electronic chassis with a double T-shaped reinforced multi-box structure. It is mainly used in radar front-end components such as chassis and modules that require lightweight and high strength. Background Technology

[0002] The electronic enclosure is a key structural component of the radar radio frequency front end. It provides external mounting interfaces for various electrical components inside the enclosure and ensures that it has reliable mechanical structural rigidity, excellent impact resistance, weather resistance and other functional requirements. It is an integrated structural and functional component.

[0003] Electronic chassis have complex structures with numerous interface surfaces, mounting surfaces, and mating surfaces, making their manufacturing process challenging. Currently, there are three main methods for manufacturing electronic chassis. One method involves machining aluminum alloys using milling or casting. Another method uses engineering plastics such as PEEK through milling or injection molding. The third method uses carbon fiber skin parts and metal beams and ribs, joined by secondary adhesive bonding or mechanical connection. However, these methods have the following drawbacks:

[0004] (1) The processing method of making electronic chassis by milling or casting aluminum alloy is not suitable for processing electronic chassis with demanding requirements for lightweighting because the material is aluminum alloy, which has a high material density and results in a large weight of electronic equipment structure.

[0005] (2) When engineering plastics are milled or injection molded into electronic enclosures, the rigidity of the engineering plastics is generally low and the load-bearing capacity of the enclosure is poor, so they cannot be used in electronic enclosures with high load-bearing requirements.

[0006] (3) The processing method of forming a complex structural component such as carbon fiber skin panel parts and metal beams and ribs, and then connecting and assembling the two into an electronic chassis has disadvantages such as low weight reduction rate of chassis structure and easy cracking of connection joints under stress. It is not suitable for use in electronic chassis with high load-bearing capacity and high weight reduction requirements.

[0007] The radar electronic chassis of a certain product has external dimensions of 550mm×420mm×115.5mm. The design requires the weight to be controlled within 2kg, and the components must meet the requirements of 40g overload impact and 50kg load. The existing chassis manufacturing methods can no longer meet the product's requirements for lightweight and high strength. Summary of the Invention

[0008] Technical problems to be solved

[0009] To overcome the shortcomings of existing radar electronic chassis molding methods, this invention utilizes a molding method of integral lay-up and one-time co-curing of carbon fiber composite materials. Through the high-precision use of multiple sets of combined molds and the thermal expansion-assisted autoclave technology of metal molds, this invention proposes a new one-time co-curing molding technology for a multi-box structure radar all-carbon fiber electronic chassis with a double T-shaped central web plate. This avoids the disadvantages of existing radar electronic chassis structures such as large weight or insufficient load-bearing strength, and meets the requirements of lightweight and high overload performance for airborne radar electronic chassis.

[0010] Technical solution

[0011] A single-piece molding die for a double-T-shaped multi-box structure radar all-carbon fiber chassis is disclosed. The electronic chassis comprises a fan nacelle, a front end nacelle, and a central web. The front end nacelle includes a lower front end nacelle, a middle front end nacelle, an upper front end nacelle, and two T-shaped wall panel structures. The die is characterized by including a base plate mold, a middle front end nacelle mold, an upper front end nacelle mold, and a fan nacelle mold, with each mold assembled and positioned using locating pins. The base plate mold has a stepped structure, comprising a bottom platform, a middle step, and an upper step. The bottom platform is a cuboid structure, with a length and width 120mm and 60mm larger on each side than the outer surface dimensions of the electronic chassis, respectively, and a thickness of 25mm. The middle step has the same shape as the outer surface of the electronic chassis and a height of 15mm. The geometry of the upper step matches the geometry of the inner surface of the lower front end nacelle. The front-end nacelle mold is a combined mold, which is divided into two long-side nacelle molds, four corner nacelle molds, and two wide-side nacelle molds according to the four corners, long side, and wide side of the front-end nacelle. The eight molds are connected by threads to form a whole. The geometry of the combined front-end nacelle mold is consistent with the geometry of the inner surface of the front-end nacelle. The front-end upper nacelle mold is an integral structure, and its geometry is consistent with the geometry of the inner surface of the front-end upper nacelle of the chassis. The wind turbine nacelle mold is a combined mold, which is divided into two oblique-side molds and one central nacelle mold according to the two oblique sides and center of the wind turbine nacelle. The three molds are connected by threads to form a whole. The geometry of the combined wind turbine nacelle mold is consistent with the geometry of the inner surface of the wind turbine nacelle.

[0012] A further technical solution of the present invention: the base plate mold, the front middle cabin mold, the front upper cabin mold, the wind turbine nacelle mold, and the positioning pin are all made of 45 steel.

[0013] A further technical solution of the present invention: the electronic chassis is formed by extrusion molding using the thermal expansion force between the fan nacelle mold and the front end nacelle mold, and the thickness t of the central web plate satisfies... Where: d1 is the width of the wind turbine nacelle mold, in mm; d2 is the width of the front nacelle assembly mold, in mm; α mThe coefficient of thermal expansion of the mold material, in units of ×10⁻¹⁰. -6 / ℃; ΔT is the temperature difference between the curing temperature of the molding material and the ambient temperature, in ℃; w is the percentage of material compression during carbon fiber autoclave curing, in %.

[0014] A method for integral molding of a double-T-shaped multi-box structure radar all-carbon fiber chassis, characterized by the following steps:

[0015] Step 1: Clean the base plate mold, 8 front mid-section molds, front upper hull mold, and 3 wind turbine nacelle molds with alcohol. After air drying at room temperature, apply release agent to the surface at least twice, with an interval of at least 10 minutes.

[0016] Step 2: Screw together and assemble 8 front-end mid-cabin split molds and 3 wind turbine nacelle split molds;

[0017] Step 3: Lay the inner skin of the lower front hull, the middle front hull, and the upper front hull separately on the bottom plate mold, the front mid-hull mold, and the front upper hull mold, respectively, in a layup sequence of ±45°. (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ;

[0018] Step 4: The bottom plate mold, the front mid-cabin mold, and the front upper cabin mold are assembled into one piece using locating pins, and then aligned at (±45°). (织物)2 / (orthogonal) (织物)3 / (±45°) (织物)2 The middle skin of the front cabin is laid in sequence, and pre-compaction is carried out after the laying is completed.

[0019] Step 5: Apply ±45° angles to the wind turbine nacelle mold. (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) / (±45°) (织物)2 / (orthogonal) (织物)3 / (±45°) (织物)2 The inner skin and intermediate skin of the wind turbine nacelle are laid in sequence, and pre-compaction is carried out after the laying is completed.

[0020] Step 6: The assembly mold of the nacelle, base plate mold, middle nacelle mold, and upper nacelle mold is then assembled into a whole mold using positioning pins. The outer skin of the chassis is then laid out in the following order: (orthogonal). (织物)3 / ±45° (织物)3 / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ;

[0021] Step 7: Make a vacuum bag, cure and shape it in an autoclave, demold, and perform post-processing to finally prepare the electronic chassis component.

[0022] A further technical solution of the present invention: the prepreg of the fabric in the layup is T300 carbon fiber epoxy material with a layer thickness of 0.25mm.

[0023] A further technical solution of the present invention: the unidirectional tape in the layup is T800 carbon fiber epoxy material with a layer thickness of 0.12mm.

[0024] Beneficial effects

[0025] This invention provides a molding die and method for integrally molding a double-T-shaped multi-box structure radar all-carbon fiber chassis. By combining and using multiple molding dies, and employing metal mold thermal expansion extrusion-assisted autoclave molding technology, and through a layered design method of partitioned layup followed by overall lamination, a new one-time co-curing molding technique is achieved for all-carbon fiber electronic chassis with difficult-to-form structures such as double-T shapes and central webs. This solves the problems of secondary mechanical connection and assembly required for carbon fiber electronic chassis and the difficulty in demolding after molding in existing molding methods. Verification using multiple sets of electronic chassis for a military product demonstrates that the all-carbon fiber electronic chassis prepared by this method is lightweight, has high mechanical strength, and exhibits stable and reliable quality. Attached Figure Description

[0026] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0027] Figure 1 Carbon fiber electronic chassis structural diagrams: (a) 3D view of the chassis; (b) Cross-sectional view of the chassis layering.

[0028] Figure 2 Base plate mold structure diagram;

[0029] Figure 3 Schematic diagram of the front-end mid-cabin mold structure: (c) Disassembled mid-cabin mold; (d) Assembled mid-cabin mold;

[0030] Figure 4 Front upper cabin mold structure diagram;

[0031] Figure 5 Wind turbine nacelle mold structure diagram: (e) Exploded view of wind turbine nacelle mold; (f) Assembled view of wind turbine nacelle mold

[0032] Figure 6 The present invention relates to a molding schematic diagram.

[0033] In the diagram, 1-carbon fiber electronic chassis; 2-wind turbine nacelle; 3-front nacelle; 4-central web; 5-lower front nacelle; 6-middle front nacelle; 7-upper front nacelle; 8-T-shaped wall panel structure; 9-bottom plate mold; 10-middle front nacelle mold; 11-upper front nacelle mold; 12-wind turbine nacelle mold; 13-assembly positioning pin between front nacelle molds; 14-assembly positioning pin between wind turbine nacelle mold and front nacelle mold; 15-first middle nacelle long side split mold; 16-second middle nacelle long side split mold; 17-first middle nacelle four corner split molds 18-Second mid-cabin corner split mold; 19-Third mid-cabin corner split mold; 20-Fourth mid-cabin corner split mold; 21-First mid-cabin wide side split mold; 22-Second mid-cabin wide side split mold; 23-First wind turbine nacelle inclined side split mold; 24-Second wind turbine nacelle inclined side split mold; 25-Wind turbine nacelle center split mold; 26-Bottom platform of the bottom plate mold; 27-Middle step of the bottom plate mold; 28-Upper step of the bottom plate mold; 29-Inner skin; 30-Middle skin; 31-Outer skin. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0035] This invention provides an integral molding mold for a double-T-shaped multi-box structure radar all-carbon fiber chassis. The electronic chassis 1 consists of a fan nacelle 2, a front end nacelle 3, and a central web plate 4. The front end nacelle 3 includes a lower front end nacelle 5, a middle front end nacelle 6, an upper front end nacelle 7, and two T-shaped wall panel structures 8. The invention is characterized by including a base plate mold 9, a middle front end nacelle mold 10, an upper front end nacelle mold 11, and a fan nacelle mold 12. The three parts of the front end nacelle 3 are assembled and positioned with each other and with the fan nacelle mold 12 via positioning pins 13 and 14. The base plate mold 9 has a stepped structure, including a bottom platform 26, a middle step 27, and an upper step 28. The bottom platform 26 is a cuboid structure, with a length and width 120mm and 60mm larger on each side than the outer surface dimensions of the electronic chassis 1, respectively, and a thickness of 25mm. The middle step 27 has the same shape as the outer surface of the electronic chassis 1 and a height of 15mm. The upper step 28 has the same geometry as the inner surface of the lower front end nacelle 5. The front-end mid-cabin mold 10 is a combined mold. It is divided into eight separate molds according to the four corners, long side, and wide side of the front-end mid-cabin 6: long side molds 15-16, four corner molds 17-20, and wide side molds 21-22. These eight separate molds 15-22 are connected as a whole by threads. The geometry of the combined front-end mid-cabin mold 10 is consistent with the geometry of the inner surface of the front-end mid-cabin 6. The front-end upper cabin mold 11 is an integral structure, and its geometry is consistent with the geometry of the inner surface of the front-end upper cabin 7 of the chassis. The wind turbine nacelle mold 12 is a combined mold. It is divided into three separate molds according to the two oblique sides and center direction of the wind turbine nacelle 2: oblique side molds 23-24 and a center mold 25. These three separate molds 23-25 ​​are connected as a whole by threads. The geometry of the combined wind turbine nacelle mold 12 is consistent with the geometry of the inner surface of the wind turbine nacelle 2. The central web plate 4 of the electronic chassis 1 is formed by thermal expansion force extrusion between the fan nacelle mold 12 and the front nacelle molds 9-11, and the thickness of the central web plate is t. The bottom plate mold 9, the front middle nacelle mold 10, the front upper nacelle mold 11, the fan nacelle mold 12, and the positioning pins 13-15 are all made of 45 steel.

[0036] This invention also provides a method for integral molding of a double-T-shaped multi-box structure radar all-carbon fiber chassis, the steps of which are as follows:

[0037] Step 1: Clean the base plate mold 9, the split molds 15-22 of the front middle cabin mold 10, the split molds 23-25 ​​of the front upper cabin mold 11 and the wind turbine cabin mold 12 with alcohol. After drying at room temperature, apply release agent to the surface at least twice, with an interval of at least 10 minutes.

[0038] Step 2: The split molds 15-22 of the front-end mid-cabin mold 10 and the split molds 23-25 ​​of the wind turbine nacelle mold 12 are assembled by screwing.

[0039] Step 3: Lay the inner skin 29 separately on the bottom plate mold 9, the front mid-cabin mold 10, and the front upper cabin mold 11, with the layering sequence being ±45°. (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ;

[0040] Step 4: The bottom plate mold 9, the front mid-cabin mold 10, and the front upper cabin mold 11 are assembled into one piece using locating pins 13, and then aligned according to (±45°). (织物)2 / (orthogonal) (织物)3 / (±45°) (织物)2 The middle skin 30 is laid in sequence, and pre-compaction is carried out after the laying is completed;

[0041] Step 5: Install the wind turbine nacelle mold 12 at ±45° (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物)3 / (orthogonal) (织物)3 / (±45°) (织物)2 The inner skin 29 and the middle skin 30 are laid in sequence, and pre-compaction is carried out after the laying is completed.

[0042] Step 6: The wind turbine nacelle mold 12 is assembled and positioned with the front nacelle mold in Step 4 using positioning pins 14. Then, the outer skin 31 is laid out in the following order: (orthogonal). (织物)3 / ±45° (织物)3 / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ;

[0043] Step 7: Make a vacuum bag, cure it in an autoclave, demold it, and perform post-processing (machining, polishing) to finally produce the electronic chassis component.

[0044] The prepreg of the fabric is T300 carbon fiber epoxy material with a single layer thickness of 0.25 mm.

[0045] The unidirectional tape is made of T800 carbon fiber epoxy material, with a single layer thickness of 0.12mm.

[0046] Example:

[0047] See appendix Figure 1As shown, the electronic enclosure 1 is a double-T-shaped, multi-box carbon fiber laminate structure with a central web, consisting of a fan nacelle 2, a front end nacelle 3, and a central web 4. The front end nacelle 3 includes a lower front end nacelle 5, a middle front end nacelle 6, an upper front end nacelle 7, and two T-shaped wall panel structures 8. The thickness of the fan nacelle 2 and the front end nacelle 3 is 5.0 mm, and the thickness of the central web 4 is 4.0 mm. The design requirement for the electronic enclosure 1 is to control the weight within 2 kg, and the components must meet the requirements of 40 g overload impact and 50 kg load capacity.

[0048] See appendix Figure 2 As shown, the base plate mold 9 has a stepped structure, including three parts: a bottom platform 26, a middle step 27, and an upper step 28. The bottom platform 26 is a cuboid structure, with a length and width that are 120mm and 60mm larger on each side than the outer surface dimensions of the electronic chassis 1, and a thickness of 25mm. The outer dimensions of the middle step 27 are consistent with the outer surface shape of the electronic chassis 1, and the height is 15mm. The geometry of the upper step 28 is consistent with the geometry of the inner surface of the front lower compartment 5.

[0049] See appendix Figure 3 As shown, the front-end mid-cabin mold 10 is a combined mold. According to the four corners, long side and wide side of the front-end mid-cabin 6, the mid-cabin mold 10 is divided into eight separate molds: mid-cabin long side separate mold 15-16, mid-cabin four corner separate mold 17-20, mid-cabin wide side separate mold 21-22, etc. The eight separate molds 15-22 are connected into a whole by threads. The geometry of the combined front-end mid-cabin mold 10 is consistent with the geometry of the inner surface of the front-end mid-cabin 6.

[0050] See appendix Figure 4 As shown, the front upper compartment mold 11 is an integral structure, and its geometry is consistent with the geometry of the inner surface of the front upper compartment 7 of the chassis.

[0051] See appendix Figure 5 As shown, the wind turbine nacelle mold 12 is a combined mold. The wind turbine nacelle mold 12 is divided into three separate molds, namely the two inclined sides and the center direction of the wind turbine nacelle 2, and the center of the wind turbine nacelle mold 25. The three separate molds 23 to 25 are connected as a whole by threads. The geometry of the combined wind turbine nacelle mold 12 is consistent with the geometry of the inner surface of the wind turbine nacelle 2.

[0052] See appendix Figure 6 As shown, during the molding process of the electronic chassis 1, the inner skin 29, middle skin 30, and outer skin 31 of the fan nacelle 2, the lower front nacelle 5, the middle front nacelle 6, and the upper front nacelle 7 are formed by the hot pressure provided by the autoclave. The inner skin 29 and middle skin 30 of the central web plate 4 are formed by the thermal expansion force between the fan nacelle mold 12 and the front nacelle molds 9-11. The thickness of the central web plate 4 is t.

[0053] In this embodiment, the thickness t of the central web 4 is determined by the following formula:

[0054]

[0055] In the formula: d1 is the width of the wind turbine nacelle mold 12 (unit: mm); d2 is the width of the front nacelle assembly mold (unit: mm); α m The coefficient of thermal expansion of the mold material (unit: ×10) -6 / ℃); ΔT is the temperature difference between the curing temperature of the molding material and the ambient temperature (unit: ℃); w is the percentage of material compression during carbon fiber autoclave curing (unit: %).

[0056] The base plate mold 9, the front middle cabin mold 10, the front upper cabin mold 11, the wind turbine cabin mold 12, and the positioning pins 13-14 are all made of 45 steel.

[0057] The preparation process used to achieve the purpose of this invention includes the following steps:

[0058] (1) Clean the bottom plate mold 9, the eight separate molds 15-22 of the front middle cabin mold 10, the three separate molds 23-25 ​​of the front upper cabin mold 11 and the wind turbine cabin mold 12 with alcohol. After drying at room temperature, apply release agent to the surface at least twice, with an interval of at least 10 minutes.

[0059] (2) The eight separate molds 15-22 of the front-end mid-cabin mold 10 and the three separate molds 23-25 ​​of the wind turbine nacelle mold 12 are assembled by screwing;

[0060] (3) The inner skin 29 of the chassis is laid separately on the bottom plate mold 9, the front mid-cabin mold 10, and the front upper cabin mold 11, with the layering sequence being ±45°. (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ;

[0061] (4) The bottom plate mold 9, the front middle compartment mold 10, and the front upper compartment mold 11 are assembled into one piece by positioning pins 13, and then arranged according to (±45°). (织物)2 / (orthogonal) (织物)3 / (±45°) (织物)2 The inner skin of the chassis is laid in sequence 30, and pre-compaction is performed after the laying is completed;

[0062] (5) The wind turbine nacelle mold 12 is set at ±45° (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物)3 / (orthogonal) (织物)3 / (±45°) (织物)2The inner skin 29 and the middle skin 30 of the chassis are laid in sequence, and pre-compaction is carried out after the laying is completed.

[0063] (6) The wind turbine nacelle mold 12 and the front nacelle mold assembly in step 4 are assembled and positioned by positioning pins 14, and then the outer skin 31 of the chassis is laid. The layering sequence is: (orthogonal). (织物)3 / ±45° (织物)3 / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ;

[0064] (7) Make vacuum bags, solidify and mold them in a hot autoclave, demold and post-process them to finally prepare electronic chassis parts.

[0065] The fabric prepreg (±45°) (织物)2 It is a T300 carbon fiber epoxy material with a single layer thickness of 0.25mm.

[0066] The unidirectional band (±45°) (织物) It is a T800 carbon fiber epoxy material with a single layer thickness of 0.12mm.

[0067] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the scope of the technology disclosed in the present invention, and such modifications or substitutions should all be covered within the scope of protection of the present invention.

Claims

1. A molded integral formwork for a double-T-shaped multi-box structure radar all-carbon fiber chassis, wherein the electronic chassis (1) is composed of a fan nacelle (2), a front end nacelle (3), and a central web plate (4), wherein the front end nacelle (3) includes a lower front end nacelle (5), a middle front end nacelle (6), an upper front end nacelle (7), and two T-shaped wall panel structures (8); characterized in that The system includes a base plate mold (9), a front mid-cabin mold (10), a front upper cabin mold (11), and a wind turbine nacelle mold (12). The molds are assembled and positioned using locating pins. The base plate mold (9) is a stepped structure, comprising a bottom platform (26), a middle step (27), and an upper step (28). The bottom platform (26) is a cuboid structure, with a length and width 120mm and 60mm larger on each side than the outer surface dimensions of the electronic chassis (1), and a thickness of 25mm. The middle step (27) has the same external dimensions as the outer surface of the electronic chassis (1) and a height of 15mm. The upper step (28) has the same geometry as the inner surface of the front lower cabin (5). The front mid-cabin mold (10) is a combined mold, constructed according to the four corners, long sides, and... Along the wide side, the middle cabin mold (10) is divided into two middle cabin long side split molds, four middle cabin four corner split molds, and two middle cabin wide side split molds. The eight split molds are connected into a whole by threads. The geometry of the combined front middle cabin mold (10) is consistent with the geometry of the inner surface of the front middle cabin (6). The front upper cabin mold (11) is an integral structure, and its geometry is consistent with the geometry of the inner surface of the front upper cabin (7) of the chassis. The wind turbine nacelle mold (12) is a combined mold. Along the two oblique sides and the center direction of the wind turbine nacelle (2), the wind turbine nacelle mold (12) is divided into two oblique side split molds and one wind turbine nacelle center split mold. The three split molds are connected into a whole by threads. The geometry of the combined wind turbine nacelle mold (12) is consistent with the geometry of the inner surface of the wind turbine nacelle (2).

2. The integral molding mold for a double-T-shaped multi-box structure radar all-carbon fiber chassis according to claim 1, characterized in that... The base plate mold (9), the front middle cabin mold (10), the front upper cabin mold (11), the wind turbine cabin mold (12), and the positioning pin are all made of 45 steel.

3. The integral molding mold for a double-T-shaped multi-box structure radar all-carbon fiber chassis according to claim 1, characterized in that... The electronic chassis (1) is formed by extrusion molding using the thermal expansion force between the fan nacelle mold and the front end nacelle mold, and the thickness t of the central web plate (4) satisfies Where: d1 is the width of the wind turbine nacelle mold (12), in mm; d2 is the width of the front nacelle assembly mold, in mm; α m The coefficient of thermal expansion of the mold material, in units of ×10⁻¹⁰. -6 / ℃; ΔT is the temperature difference between the curing temperature of the molding material and the ambient temperature, in ℃; w is the percentage of material compression during carbon fiber autoclave curing, in %.

4. A method for integral molding of a double-T-shaped multi-box structure radar all-carbon fiber chassis using the mold described in claim 1, characterized in that... The steps are as follows: Step 1: Clean the base plate mold, 8 front mid-section molds, front upper hull mold, and 3 wind turbine nacelle molds with alcohol. After air drying at room temperature, apply release agent to the surface at least twice, with an interval of at least 10 minutes. Step 2: Screw together and assemble 8 front-end mid-cabin split molds and 3 wind turbine nacelle split molds; Step 3: Lay the inner skin of the lower front hull, the middle front hull, and the upper front hull separately on the bottom plate mold, the front mid-hull mold, and the front upper hull mold, respectively, in a layup sequence of ±45°. (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ; Step 4: The bottom plate mold, the front mid-cabin mold, and the front upper cabin mold are assembled into one piece using locating pins, and then aligned according to (±45°). (织物)2 / (orthogonal) (织物)3 / (±45°) (织物)2 The middle skin of the front cabin is laid in sequence, and pre-compaction is carried out after the laying is completed. Step 5: Apply ±45° angles to the wind turbine nacelle mold. (织物) / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) / (±45°) (织物)2 / (orthogonal) (织物)3 / (±45°) (织物)2 The inner skin and intermediate skin of the wind turbine nacelle are laid in sequence, and pre-compaction is carried out after the laying is completed. Step 6: The assembly mold of the nacelle, base plate mold, middle nacelle mold, and upper nacelle mold is then assembled into a whole mold using positioning pins. The outer skin of the chassis is then laid out in the following order: (orthogonal). (织物)3 / ±45° (织物)3 / 0°3 / 90° / 0° / 90° / 0°3 / ±45° (织物) ; Step 7: Make a vacuum bag, cure and shape it in an autoclave, demold, and perform post-processing to finally prepare the electronic chassis component.

5. The integral molding method for a double-T-shaped multi-box structure radar all-carbon fiber chassis according to claim 4, characterized in that: The prepreg in the layup is T300 carbon fiber epoxy material with a layer thickness of 0.25 mm.

6. The integral molding method for a double-T-shaped multi-box structure radar all-carbon fiber chassis according to claim 4, characterized in that: The unidirectional tape in the layup is made of T800 carbon fiber epoxy material with a layer thickness of 0.12 mm.

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