A method for manufacturing a honeycomb sandwich for a radome, and a radome and a method for manufacturing the same
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING COMPOSITE MATERIALS CO LTD
- Filing Date
- 2025-05-30
- Publication Date
- 2026-07-21
Smart Images
Figure CN120606554B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the fields of composite material manufacturing and UAV component design, and more specifically, it relates to a method for preparing a honeycomb sandwich for a radome, as well as the radome and the method for preparing it. Background Technology
[0002] The radome is a critical component at the front end of a drone, and its design must strike a balance between protection, electromagnetic performance, aerodynamics, and stealth capabilities. For example, the radome protects the radar system from harsh environmental factors such as rain, hail, sandstorms, and ultraviolet radiation, extending equipment lifespan. During high-speed flight or collisions (such as bird strikes), the radome absorbs impact, preventing damage to the radar hardware. The radome must also ensure minimal attenuation of electromagnetic waves transmitted and received by the radar during penetration, avoiding signal distortion. In summary, the radome needs excellent electromagnetic wave transmission, lightweight design, high strength, and resistance to environmental corrosion.
[0003] Furthermore, with increasingly stringent requirements for low energy consumption in drones, there is a growing demand for further weight reduction in radomes. In recent years, researchers have commonly used composite materials to fabricate radomes to reduce their weight, among which sandwich structure technology has emerged and become the mainstream design for high-performance radomes. Sandwich structures typically consist of high-strength upper and lower panels (skin) and a lightweight core material in between. The core principle lies in using the core layer to separate the two panels, forming a mechanical structure similar to an I-beam, thereby significantly improving the specific stiffness and specific strength of the structure with minimal weight gain.
[0004] However, due to the shape of the radome, the existing molding process often has unstable problems. For example, improper process operation can lead to problems such as high porosity and deformation in the product. In particular, the material at the splicing seam is prone to wrinkles, collapses, and voids. Summary of the Invention
[0005] This application provides a method for preparing a honeycomb sandwich for a radome, as well as the radome itself and the method for preparing it. The radome of this application achieves lightweight design, good mechanical strength, and a stable molding process, effectively reducing the porosity of the product and minimizing material deformation.
[0006] In a first aspect, this application provides a method for preparing a honeycomb sandwich layer for a radome, employing the following technical solution:
[0007] A method for preparing a honeycomb sandwich for a radome includes the following steps:
[0008] Preparation of flattened splicing plate: According to the required shape of the honeycomb sandwich, a flattened splicing plate is prepared. The splicing seam of the flattened splicing plate along the generatrix passes through the maximum curvature change of the radome head and side wall. The angle between the end wall of the flattened splicing plate at the radome head and the side wall of the flattened splicing plate at the outer peripheral wall of the radome is α, where α = arc tan (a / b), where a is the thickness of the honeycomb sandwich and b is the difference between the distance from the vertices of the honeycomb sandwich head to two symmetrical points on the inner and outer walls of the honeycomb sandwich located at the splicing seam.
[0009] Honeycomb sandwich assembly: In the molding die, the flattened splicing panels are assembled into a honeycomb sandwich.
[0010] By adopting the above technical solutions, this application, in preparing the flattened splicing plate with honeycomb sandwich layer, not only meets the basic requirements for the required honeycomb sandwich layer and area, but also performs special chamfering treatment on the splicing seam position and the end wall of the flattened splicing plate located in the radar head, and specifies the method for obtaining the included angle α. This chamfering and splicing seam setting can effectively reduce the gaps and deformation of the honeycomb sandwich layer head splicing, and also reduce the amount of foam adhesive used, thereby reducing its impact on the radar dome's wave transmission performance. This results in a radar dome with good wave transmission and mechanical strength, and the molding process is stable and the manufacturing process is simple.
[0011] Furthermore, each of the flattened splicing panels includes an upper panel and a lower panel, which are spliced relative to each other along the radome generatrix direction, and the splicing seam is located at a position one-third to one-half of the distance from the radome head end along the radome height direction.
[0012] Furthermore, in the honeycomb sandwich assembly step, an adhesive film is pasted in the molding mold, a flattened splicing plate is attached to the adhesive film at a specified position, then adhesive is placed at the splicing end, the next flattened splicing plate is attached to the adhesive film at a specified position and bonded to the splicing end of the previous flattened splicing plate, until the splicing is completed, then an adhesive film is pasted on the assembled flattened splicing plate, and it is placed in an oven for pre-forming.
[0013] Furthermore, the temperature of the oven is 60-150°C and the drying time is 1-4 hours.
[0014] Furthermore, the adhesive is a modified epoxy film-type foam adhesive.
[0015] Secondly, this application provides a method for manufacturing a radome, employing the following technical solution:
[0016] A method for manufacturing a radome using the above-mentioned honeycomb sandwich layer includes the following steps:
[0017] Outer skin lining: The outer skin prepreg is laid in the mold;
[0018] Honeycomb sandwich installation: The pre-formed honeycomb sandwich is laid on the outer skin prepreg;
[0019] Inner skin paving: Inner skin prepreg is laid on the inner peripheral wall of the honeycomb sandwich layer;
[0020] The product is obtained by heating and curing, followed by cooling.
[0021] Furthermore, a vacuum bag was used to cure the product for 90~240 minutes at a curing temperature of (127±5) ℃ and a curing pressure of 0.31±0.035 MPa, followed by cooling.
[0022] Furthermore, in the laying steps of the outer and inner skins, the prepreg is laid in multiple layers, with staggered laying joints between different layers. Further, the laying joints here refer to lap joints and butt joints.
[0023] Furthermore, the prepreg is an epoxy glass fiber prepreg, wherein the reinforcing material glass fiber accounts for 60%-70%, the epoxy resin material accounts for 30%-40%, the overlap width of the prepreg is 10-20mm, and the butt joint is ≤2mm.
[0024] Thirdly, this application provides a radar dome, which adopts the following technical solution:
[0025] A radar dome, wherein the radar dome has a fiberglass skin honeycomb sandwich structure, the honeycomb sandwich of the radar dome is the aforementioned honeycomb sandwich, and a lightning protection aluminum strip is installed on the outer sidewall of the radar dome.
[0026] In summary, this application has the following beneficial effects:
[0027] This application uses high-strength lightweight composite materials to achieve weight reduction. In the process of preparing the honeycomb sandwich, the flattened splicing plate of the honeycomb sandwich is specially treated so that the honeycomb sandwich can effectively achieve weight reduction when used in the preparation of the radome, with good mechanical strength and wave transmission, and the molding process is stable. Attached Figure Description
[0028] Figure 1 This is a planar schematic diagram to illustrate the required honeycomb interlayer depth of the radome in the embodiments of this application.
[0029] Figure 2 This is a planar schematic diagram to illustrate the major and minor axes of the honeycomb sandwich layer required for the radome in the embodiments of this application.
[0030] Figure 3 This is a planar schematic diagram to illustrate the angles in the flattened splicing panel of the embodiments of this application.
[0031] Figure 4This is a planar schematic diagram to illustrate the required side length of the honeycomb interlayer in the radome of the present application embodiment.
[0032] Figure 5 This is a planar schematic diagram to illustrate the shape of the flattened splicing panel in Embodiment 1 of this application.
[0033] Figure 6 This is a planar schematic diagram to illustrate the shape of the flattened splicing panel in Embodiment 2 of this application.
[0034] Figure 7 This is a physical image of Embodiment 4 of this application.
[0035] Explanation of reference numerals in the attached diagram: 1. Honeycomb sandwich layer; 2. Flattened splicing panel; 3. Upper display panel; 4. Lower display panel. Detailed Implementation
[0036] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. Example
[0037] In the embodiments of this application, the prepreg used can be epoxy glass fiber prepreg, wherein the glass fiber reinforcing material accounts for 60%-70% by mass and the epoxy resin material accounts for 30%-40% by mass.
[0038] Fiberglass can be made from continuous unidirectional fabric, woven fabric or chopped strands.
[0039] Epoxy resin materials consist of a matrix, curing agent, accelerator, and functional additives.
[0040] The matrix can be bisphenol A type (DGEBA), multifunctional epoxy (such as TGDDM), etc.
[0041] Curing agents (1%-5% of epoxy resin materials) can be acid anhydrides, amines, and latent curing agents. Specifically, acid anhydride curing agents can be methyltetrahydrophthalic anhydride (MTHPA), and amines can be DDS, 4,4'-diaminodiphenyl sulfone, dicyandiamide, or DICY. Accelerators (0.5%-2% of epoxy resin materials by mass) can be 2-methylimidazole (2-MI), benzyl dimethylamine (BDMA), etc. Functional additives (2%-10% of epoxy resin materials by mass) can be toughening agents, flame retardants, etc. Toughening agents can be carboxyl-terminated nitrile butadiene rubber, and flame retardants can be aluminum hydroxide, phosphorus compounds, etc.
[0042] Specifically, the prepreg formulation used in this embodiment is as follows:
[0043] Prepreg composition: 65% glass fiber reinforcement and 35% epoxy resin. In this embodiment, the glass fibers are all woven fabric.
[0044] The curing agent is methyltetrahydrophthalic anhydride, accounting for 4% of the epoxy resin material; the accelerator is benzyl dimethylamine (BDMA), accounting for 1% of the epoxy resin material by mass; the toughening agent is carboxyl-terminated nitrile butadiene rubber, accounting for 6% of the epoxy resin material by mass; and the flame retardant is aluminum hydroxide, accounting for 5% of the epoxy resin material by mass.
[0045] The foaming adhesive used in this embodiment is modified epoxy film-type foaming adhesive MF9010.
[0046] Additionally, it should be noted that the relevant parameters involved in the embodiments of this application are explained as follows:
[0047] Regarding the radome, the radome prepared in this embodiment is a radome for unmanned aerial vehicles (UAVs), and its shape resembles a bird's beak, such as... Figure 1 and Figure 2 As shown, in the honeycomb interlayer 1 corresponding to the radome, the depth is h, the major axis is m, and the minor axis is n.
[0048] Regarding flattened splicing panels, such as Figure 3 and Figure 4 As shown, the thickness of the flattened splicing plate 2 is 'a', which is the thickness of the honeycomb interlayer. The honeycomb interlayer of the radome corresponding to the splicing seam of the flattened splicing plate has a required shape. The difference in length between the two symmetrical points on the inner and outer walls and the corresponding vertices of the honeycomb interlayer head of the required shape of the radome is 'b', i.e., b = b1 - b2. The two symmetrical points on the inner and outer walls refer to two symmetrical points that are opposite each other and whose tangents are parallel at this point.
[0049] The angle α between the end wall of the flattened splicing plate located at the head of the radome and the side wall of the flattened splicing plate located at the outer peripheral wall of the radome is α = arc tan(a / b).
[0050] The following explanation is provided through specific examples. Example 1
[0051] The radome prepared in this embodiment is a radome for UAVs, with a depth of 478mm and an end length of 1008mm in the major axis direction and 924mm in the minor axis direction.
[0052] This embodiment first provides a method for preparing a honeycomb interlayer for a radome, including the following steps:
[0053] The required honeycomb interlayer is made of aramid fiber, with the following dimensions: thickness a is 15cm, and the side length difference b for the honeycomb interlayer of the required shape of the radome is 5.5cm.
[0054] Flattened splicing panel preparation: Based on the required honeycomb sandwich shape, a flattened splicing panel is prepared. The splicing seam of the flattened splicing panel along the generatrix direction passes through the point of maximum curvature change in the radome head and sidewalls, such as... Figure 5As shown, there are two flattened splicing panels 2 in this embodiment.
[0055] The angle between the end wall of the flattened splicing plate located at the head of the radome and the side wall of the flattened splicing plate located on the outer periphery of the radome is α, where α = arc tan (a / b) = 70°.
[0056] Honeycomb sandwich assembly: In the molding die, the flattened splicing panels are assembled into a honeycomb sandwich.
[0057] Specifically, the assembly process of the honeycomb interlayer includes the following steps:
[0058] A layer of adhesive film is pasted onto the mold fixture and pre-compacted (vacuum degree ≥ -0.06MPa, time ≥ 5min); after applying foaming film to the adhesive surface of a flattened splicing plate to be spliced, the flattened splicing plate is positioned on the tool according to the required radome shape; another flattened splicing plate is positioned in the specified position of the mold; then the two flattened splicing plates are tightly pressed together for assembly; at the halfway point near the outer side of the tail end wall of the spliced honeycomb sandwich, potting compound is injected into the honeycomb of the honeycomb sandwich and a layer of adhesive film is pasted to strengthen the strength at this point, and then it is placed in an oven for pre-forming, the oven temperature is 127±5°C and the drying time is 3 hours.
[0059] This embodiment also discloses a method for manufacturing a radome, including the following steps:
[0060] Outer skin installation: The outer skin prepreg is laid in the mold. The specific operation is as follows:
[0061] The outer skin consists of three layers of prepreg and one layer of adhesive film. After the first layer of prepreg and the fourth layer of adhesive film are laid, they are vacuum compacted, with a vacuum degree ≥ -0.06 MPa and a time ≥ 5 min.
[0062] If each layer of prepreg overlaps, the overlap should be 10-20mm. If it does not overlap, the butt joint should be ≤2mm. Furthermore, the overlaps or butt joints of each layer should be staggered.
[0063] Honeycomb sandwich installation: The pre-formed honeycomb sandwich is laid on the outer skin prepreg;
[0064] Inner skin paving: Inner skin prepreg is laid on the inner peripheral wall of the honeycomb sandwich layer; the specific operation is as follows:
[0065] The inner skin has nine layers of prepreg. After the first, seventh, and eighth layers of prepreg are laid, they are vacuum compacted with a vacuum degree of ≥-0.06MPa and a time of ≥5min.
[0066] If each layer of prepreg overlaps, the overlap should be 10-20mm. If it does not overlap, the butt joint should be ≤2mm. Furthermore, the overlaps or butt joints of each layer should be staggered.
[0067] The product is obtained by heating to cure and then cooling. The specific operation is as follows:
[0068] Using a vacuum bag, the product was cured for 150 minutes at a curing temperature of (127±5) ℃ and a curing pressure of 0.31±0.035 MPa, followed by cooling. The curing heating rate was (0.5~1.5) ℃ / min; the cooling rate did not exceed 3 ℃ / min or natural cooling was adopted; thus, product S1 was obtained. Example 2
[0069] The difference between Example 2 and Example 1 is that:
[0070] Preparation of flattened splicing panels: Flattened splicing panels are prepared according to the required honeycomb sandwich shape. The splicing seams of the flattened splicing panels along the generatrix direction pass through the points of maximum curvature change in the radome head and sidewalls. In this embodiment, there are two sets of flattened splicing panels, such as... Figure 6 As shown, each set of flattened splicing panels 2 includes an upper panel 3 and a lower panel 4. The upper and lower panels are spliced opposite each other along the radome generatrix direction, and the mating surfaces are flat. The splicing seam is located at one-third of the distance from the head end of the radome along the height direction, meaning there are four panels to be spliced at this point. During the honeycomb sandwich assembly process, the two panels closest to the head of the radome are assembled first, followed by the two panels closest to the tail of the radome. This yields product S2. Example 3
[0071] The difference between Example 3 and Example 1 is that:
[0072] The radome prepared in this embodiment is a radome for UAVs, with a depth of 478mm and an end length of 988mm in the major axis direction and 824mm in the minor axis direction.
[0073] This embodiment first provides a method for preparing a honeycomb interlayer for a radome, including the following steps:
[0074] The required honeycomb interlayer is an aramid honeycomb interlayer with the following dimensions: thickness a is 14cm, and the side length difference b for the honeycomb interlayer of the required shape of the radome is 4cm.
[0075] This embodiment first provides a method for preparing a honeycomb interlayer for a radome, including the following steps:
[0076] The required honeycomb sandwich layer is an aramid honeycomb sandwich layer. The angle α between the end wall of the flattened splicing plate located at the head of the radome and the side wall of the flattened splicing plate located at the outer peripheral wall of the radome is α = arc tan(a / b) = 74°. The resulting product is S3. Example 4
[0077] The difference between Example 4 and Example 1 is that, as Figure 6 As shown, in Example 4, six lightning protection aluminum strips are evenly installed on the outer sidewall of the radome. In the corresponding area of the honeycomb interlayer, countersunk rivets are installed using a wet installation method. The operator applies adhesive 9394 to both sides of the rivet shank, under the rivet head, and at the point where the lightning protection aluminum strip and the workpiece are to be bonded, and then rivets are used. This yields product S4. The finished product of Example 4 is shown below. Figure 7 As shown.
[0078] Comparative Example
[0079] Comparative Example 1
[0080] The difference between Comparative Example 1 and Example 1 is that the splicing seam of the flattened splicing plate along the generatrix direction passes through the symmetrical surface of the honeycomb interlayer required for the radome, resulting in product D1.
[0081] Comparative Example 2
[0082] The difference between Comparative Example 2 and Example 1 is that the end wall of the flattened splicing plate at the head of the radome is a straight end wall. The length of the flattened splicing plate is equal to the outer side length of the required honeycomb interlayer of the radome, resulting in product D2.
[0083] Comparative Example 3
[0084] The difference between Comparative Example 3 and Example 1 is that α is 45°, resulting in product D3.
[0085] Performance testing
[0086] The performance of the radome was tested on the products obtained in the examples and comparative examples, as follows:
[0087] 1. Appearance quality - visual inspection
[0088] Detection is performed on S1, S2, S3 and D1, D2, D3.
[0089] 1.1 The surface of composite material parts should be smooth and flat, with clearly visible fabric fibers. The surface fibers should be uniformly covered with resin, and there should be no obvious resin accumulation.
[0090] 1.2 Cracks are not allowed on the surface of the workpiece.
[0091] 1.3 Severe dents, scratches, or dents are not allowed on the surface of the parts.
[0092] 1.4 No other defects that significantly affect the overall strength of the component are allowed on the surface of the part.
[0093] Judgment: Pass / Fail.
[0094] 2. Internal Quality - Transmittance Inspection
[0095] Detection is performed on S1, S2, S3 and D1, D2, D3.
[0096] 2.1 Maximum permissible defect size
[0097] 2.1.1 Delamination, voids, or debonding defects shall be controlled according to Level C. The maximum permissible defect size shall not exceed 2Z = X + Y, where Z is 19 mm, and X and Y are the maximum length and width of the defect, respectively.
[0098] 2.1.2 The minimum distance between the edges of two or more defective areas should be greater than 100mm.
[0099] 2.1.3 For clusters of diffuse defects (such as porosity, looseness, and oily areas), if the defects exceed the specified limits (per 155cm²), 2 If the maximum cumulative defects are ≤25%, the product is deemed unqualified.
[0100] 3. Internal quality of honeycomb sandwich structure - light transmittance inspection
[0101] Further observation of the quality of the honeycomb sandwich structure was conducted for S1, S2, S3 and D1, D2, D3.
[0102] 3.1 Degumming
[0103] The degumming range must not exceed the provisions of 2.1.1 and 2.1.2.
[0104] 3.2 Panel - Sandwich Vent
[0105] The scope of this defect must not exceed the provisions of 2.1.1 and 2.1.2.
[0106] 3.3 Cellular Defects
[0107] a) Defects such as honeycomb deformation and honeycomb wrinkling must not accumulate to more than 3cm within any 30cm x 30cm area. 2 Furthermore, the distance between the edges of the defective area shall not be less than 200mm, and the distance between it and the edge of the normally sandwiched core shall not be less than 100mm.
[0108] b) Within any Ф254mm range, the number of nodes that are completely or partially separated shall not exceed 10. Partial node separation means that more than half of the node is separated.
[0109] c) No more than four unbonded sandwich walls are allowed within any 150mm length in a honeycomb splicing.
[0110] e) The shrinkage of the honeycomb interlayer on one side of the part after curing shall not exceed 5 mm.
[0111] 4. Mechanical Strength Testing: Performance tests were conducted on the furnace-loaded components of Examples 1-3 and the comparative examples, including interlaminar shear strength, flexural strength, and roller peel strength of the honeycomb panels. Interlaminar shear strength was tested according to ASTM D2344 (Test Procedure for Short Beam Strength of Polymer Matrix), flexural strength according to ASTM D790 (Standard Test Method for Bending Properties of Unreinforced and Reinforced Plastics and Electrical Insulators), and roller peel strength according to ASTM D1781 (Standard Test Method for Roller Peeling of Adhesives).
[0112] The test results are shown in Table 1.
[0113] Table 1 Performance test results of the examples and comparative examples
[0114]
[0115] Performance testing according to the embodiments shows that the radome component prepared in this application has good mechanical strength, and because this application uses composite materials, it has the advantage of being lightweight. Furthermore, the molding process of this application results in a high product qualification rate and stable process.
[0116] Furthermore, in the fabrication process of the honeycomb sandwich layer, analysis of the performance of Comparative Example 1 and Comparative Example 2 reveals that in the finished product of Comparative Example 1, the honeycomb lattice deforms or fails to contact the outer skin at the point of maximum curvature change, resulting in voids and other phenomena. The appearance, internal quality, and internal quality of the honeycomb sandwich structure are all substandard. In Comparative Example 2, the inner side of the honeycomb sandwich end face contacts first at the splicing point, preventing the outer side from contacting and creating sharp-angle gaps at the splicing position. The appearance, internal quality, and internal quality of the honeycomb sandwich structure are all substandard. Although Comparative Example 3 uses a chamfer, the angle is not determined according to the technical requirements of this application. This results in voids on the inner side of the splicing end after the honeycomb sandwich layer is spliced, requiring additional foaming adhesive filling. In addition to being substandard in appearance, internal quality, and internal quality of the honeycomb sandwich structure, it also affects the product's wave transmittance.
[0117] This application describes a special chamfering treatment applied to the joint positions of the flattened splicing panels and the end walls of the flattened splicing panels located in the radar head, and specifies the method for obtaining the included angle α. This chamfering and splicing joint positioning effectively reduces gaps and deformation at the honeycomb sandwich head splicing, and also reduces the amount of expanding foam used, thereby reducing its impact on the radar dome's wave transmission performance. This results in a radar dome with good wave transmission and mechanical strength, and a stable molding process with a simple manufacturing process.
[0118] This specific embodiment is merely an explanation of this application and is not intended to limit it. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this application.
Claims
1. A method for preparing a honeycomb sandwich for a radome, characterized in that, Includes the following steps: Preparation of flattened splicing plate: According to the required shape of the honeycomb sandwich, a flattened splicing plate is prepared. The splicing seam of the flattened splicing plate along the generatrix direction passes through the maximum curvature change of the radome head and side wall. The angle between the end wall of the flattened splicing plate at the radome head and the side wall of the flattened splicing plate at the outer peripheral wall of the radome is α, where α=arctan(a / b), where a is the thickness of the honeycomb sandwich and b is the difference between the distance from the vertex of the honeycomb sandwich head to two symmetrical points on the inner and outer walls of the honeycomb sandwich located at the splicing seam. Honeycomb sandwich assembly: In a molding die, flattened splicing panels are assembled into a honeycomb sandwich; Each of the flattened splicing panels includes an upper panel and a lower panel, which are spliced together relative to each other along the direction of the radome generatrix, and the splicing seam is located at a position one-third to one-half away from the head end of the radome along the height direction of the radome. Symmetrical points on the inner and outer walls refer to two points that are opposite each other and whose tangents are parallel.
2. The method for preparing a honeycomb sandwich for a radome according to claim 1, characterized in that, In the honeycomb sandwich assembly step, an adhesive film is pasted in the molding mold, a flattened splicing plate is attached to the adhesive film at a specified position, adhesive is then placed at the splicing end, the next flattened splicing plate is attached to the adhesive film at a specified position and bonded to the splicing end of the previous flattened splicing plate, until the splicing is completed, then an adhesive film is pasted on the completed flattened splicing plate and placed in an oven for pre-forming.
3. The method for preparing a honeycomb sandwich for a radome according to claim 2, characterized in that, The oven temperature is 60-150℃ and the drying time is 1-4 hours.
4. The method for preparing a honeycomb sandwich for a radome according to claim 2, characterized in that, The adhesive is a modified epoxy film-type foam adhesive.
5. A method for preparing a radome using the honeycomb sandwich layer according to any one of claims 1-4, characterized in that, Includes the following steps: Outer skin lining: The outer skin prepreg is laid in the mold; Honeycomb sandwich installation: The pre-formed honeycomb sandwich is laid on the outer skin prepreg; Inner skin paving: Inner skin prepreg is laid on the inner peripheral wall of the honeycomb sandwich layer; The product is obtained by heating and curing, followed by cooling.
6. The method for manufacturing a radome according to claim 5, characterized in that, During the curing process, a vacuum bag was used. The curing temperature was 127±5 ℃ and the curing pressure was 0.31±0.035 MPa. The product was cured for 90~240 minutes and then cooled down.
7. The method for manufacturing a radome according to claim 5, characterized in that, In the laying steps of the outer and inner skin, the prepreg is laid in multiple layers, and the laying joints between different layers are staggered.
8. The method for manufacturing a radome according to claim 6, characterized in that, The prepreg is an epoxy glass fiber prepreg, wherein the reinforcing material glass fiber accounts for 60%-70%, the epoxy resin material accounts for 30%-40%, the overlap of the prepreg is 10-20mm wide, and the butt joint is ≤2mm.
9. A radar dome using the honeycomb sandwich structure according to any one of claims 1-4, characterized in that, The radome has a fiberglass skin honeycomb sandwich structure, and the honeycomb sandwich of the radome is the aforementioned honeycomb sandwich structure. Lightning protection aluminum strips are installed on the outer sidewall of the radome.