A method for preparing a flexible and high-strength matrix honeycomb

Abstract

The invention discloses a method for preparing a flexible and extended high-strength matrix honeycomb, which is composed of multiple groups of honeycomb core unit structures welded in an offset manner, wherein the honeycomb core unit structure is composed of six regular trapezoidal composite material sheets embossed and folded, wherein the upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite material sheets extend a 1-2 mm welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the angle between the upper bottom surface and the waist of the regular trapezoidal composite material sheet is 60-85°; the method is suitable for complex curved surfaces, including concave, convex and irregular surfaces, reducing the collapse caused by the honeycomb splicing process, ensuring the integrity of the honeycomb structure, and improving its stress strength; the honeycomb unit structure with a small aperture is used to increase the strength by 10-30%, which is suitable for new military aircraft and other aerospace fields; the method is suitable for complex curved surfaces to avoid damage and collapse of honeycomb cells, reducing the uncertainty of non-destructive testing of honeycomb structures, and reducing the risk of use.

Description

Technical Field

[0001] The invention relates to the technical field of polymer composite materials, and in particular to a method for preparing a flexible, extended, high-strength matrix honeycomb. Background Art

[0002] Polymer composite materials have a wide range of applications. The honeycomb core structure prepared by composite materials has good mechanical strength. Polymer composite materials are widely used in modern military fields, such as aerospace, missiles, radars, etc., due to their light weight, high temperature resistance and high strength. Especially for modern military aircraft, in order to improve the thrust-to-weight ratio of the engine, lightweight and high-strength polymer composite materials are indispensable materials. They are also widely used in various fields such as high-speed rail, ships, automobiles, construction, sports equipment, etc. in the civilian field.

[0003] However, the hexagonal cells of the honeycomb core structure made of polymer composite materials cannot be bent, and the fields in which honeycomb cores are widely used, such as radar surfaces, military aircraft interior bulkheads, missile shell supports, etc., are all curved surfaces. The existing honeycomb cores can only be applied to curved surfaces by cutting and splicing, which causes the cells of the honeycomb core to collapse, that is, reduces its strength. CN205424392 discloses a flexible honeycomb material of convex units, the flexible honeycomb material comprises at least two groups of convex layers arranged front and back, each group of convex layers comprises at least one convex unit connected end to end in sequence; each convex unit consists of a first plane, a first protrusion, a second plane, and a second protrusion, the height of the first protrusion is greater than the height of the second protrusion, and the outer width of the first protrusion is less than the inner width of the second protrusion; the front part of the first protrusion in the rear row of convex units is embedded in the second protrusion of the front row of convex units, and their end faces are connected by an adhesive layer. A flexible honeycomb material with convex units improves the strength and modulus ratio of the honeycomb. The flexible area embedded in the honeycomb appropriately reduces the rigidity of the structure. Under the same deformation conditions, the internal stress of the honeycomb structure is low and the honeycomb warping phenomenon will not occur. Although this product solves the technical problem that the honeycomb core material cannot be deformed and bent on the curved surface, and the honeycomb cells will not warp and collapse, the local force on the honeycomb core support surface is uneven, that is, there are gaps between the hexagonal structures of the honeycomb core units, which affects the uniform force of the honeycomb core material and reduces the strength of the honeycomb core material. Especially in modern supersonic military aircraft, the uneven local force intensity causes the wing surface to instantly shatter when the military aircraft flies at high speed. Therefore, providing a flexible polymer composite honeycomb core structure with uniform force intensity is a technical problem that urgently needs to be solved. Summary of the invention

[0004] To this end, the present invention provides a method for preparing a flexible and extended high-strength matrix honeycomb. The matrix honeycomb prepared by the method solves the technical problem of honeycomb core materials for curved surface applications proposed in the background technology.

[0005] To achieve the above object, the present invention provides a flexible and ductile high-strength matrix honeycomb, which is composed of multiple groups of honeycomb core unit structures that are staggered and welded, wherein the honeycomb core unit structure is composed of six regular trapezoidal composite material sheets that are embossed and folded, wherein the upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite material sheets extend 1-2 mm from the welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the upper bottom surface and waist angle of the regular trapezoidal composite material sheet are 60-85°;

[0006] Furthermore, the length of the regular hexagonal aperture of the upper bottom surface of the honeycomb core unit structure is 2-5 mm, and the length of the regular hexagonal aperture of the lower bottom surface is 1-3 mm;

[0007] Furthermore, the four sides of the trapezoidal composite material sheet on the bottom surface of the honeycomb core unit structure are provided with node glues with a width of 1-2mm; the node glues of adjacent honeycomb core unit structures are welded after being offset and corresponding, and the offset correspondence means that the first piece of the trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the sixth piece of the trapezoidal composite material sheet of the adjacent honeycomb core unit structure; the second piece of the trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the third piece of the trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the sixth piece of the trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the fourth piece of the trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the first piece of the trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the fifth piece of the trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the second piece of the trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the sixth piece of the trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the third piece of the trapezoidal composite material sheet of another adjacent honeycomb core unit structure;

[0008] Furthermore, the regular trapezoidal composite material sheet is any one of aramid paper, polyimide paper, carbon fiber, and glass cloth;

[0009] Furthermore, gaps are formed between the multiple groups of honeycomb core unit structures, and the gaps are narrow near the upper bottom surface and wide near the lower bottom surface; the width of the gap near the lower bottom surface is the difference between the side lengths of the upper bottom surface and the lower bottom surface.

[0010] Furthermore, the gap is the adjustment angle range for the upper bottom surface to adapt to the complex curved surface, and the adjustment angle range threshold is the angle between the upper bottom surface of the honeycomb core unit structure and the upper bottom surface of the adjacent honeycomb core unit structure of 10-60 degrees.

[0011] A method for preparing a flexible and extended high-strength matrix honeycomb, the steps of which are as follows:

[0012] 1) Embossing: unfolding any composite material roll of aramid paper, polyimide paper, carbon fiber, or glass cloth and then embossing it to form six connected regular trapezoidal composite material sheets; the embossing width of the first or sixth regular trapezoidal composite material sheet is extended by 1-2 cm; forming a group of six regular trapezoidal composite material sheet processing embryos, repeating the above steps to emboss the entire composite material roll;

[0013] 2) Cutting: the remaining parts of the six regular trapezoidal composite material sheets after embossing are cut off by a cutting device to form a group of six regular trapezoidal composite material sheets, which is a group, and the above steps are repeated;

[0014] 3) One-time glue laying: glue is laid at the first or sixth extension of a group of six regular trapezoidal composite sheets in a node-type manner, and the node glue laying interval is 0.5-1mm and the interval is uniform;

[0015] 4) Folding: fold a group of six regular trapezoidal composite material sheets along the embossing, and pay attention to aligning the nodes where the first or sixth sheet is extended to ensure that the upper and lower bottom surfaces of the regular trapezoidal composite material sheets are flush, and then form a honeycomb core unit structure;

[0016] 5) Secondary glue distribution and staggered welding, the nodes are uniformly distributed with node glue around the upper bottom surface of the honeycomb core unit structure, and then the node glues of adjacent honeycomb core unit structures are staggered and welded, and ultrasonic welding is used for welding. The staggered correspondence means that the first piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the sixth piece of the regular trapezoidal composite material sheet of the adjacent honeycomb core unit structure; the second piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the third piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; The sixth piece of the regular trapezoidal composite sheet of the core unit structure; the fourth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the first piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; the fifth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the second piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; the sixth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the third piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; in this way, the length and width of the combined honeycomb core unit structure are adjusted as needed to form the required honeycomb core unit structure group;

[0017] 6) Shaping: shaping the honeycomb core unit structure group, using a lining frame slightly smaller than the honeycomb core unit structure, embedding the honeycomb core unit structure into the lining frame for shaping, the initial shaping environment temperature is 250-280℃, the shaping time is 3-5 hours, and the cooling rate is 20-30℃ / min;

[0018] 7) Glue impregnation and curing: the honeycomb core unit structure after shaping is impregnated and cured. The glue impregnation needs to be carried out in a specific glue impregnation mechanism, and the glue liquid is formulated according to different materials. After the glue impregnation, the honeycomb core unit structure is cured in a special oven at a curing temperature of 180-280°C and a curing time of 1-2 hours. The glue impregnation and curing process are repeated to obtain flexible, ductile, high-strength matrix honeycombs of different densities.

[0019] Furthermore, in the staggered welding, a support bar is embedded in the load-bearing honeycomb core unit structure, and the outer diameter of the support bar is slightly smaller than the inner diameter of the honeycomb core unit structure, corresponding to the regular hexagonal structure of the honeycomb core unit structure, wherein the front end is slightly smaller corresponding to the aperture of the lower surface of the honeycomb core unit structure, and the end is slightly larger corresponding to the aperture of the upper surface of the honeycomb core unit structure, and the support bar corresponds to multiple groups fixed on the frame.

[0020] The flexible and stretchable high-strength matrix honeycomb prepared as described above finally presents that the upper bottom surfaces are connected and flush with each other, while the middle of the lower bottom surface forms a prism-like structure with gaps between the prisms. When the present invention is applied to a curved surface, the upper bottom surface conforms to the curved surface, and the lower bottom surface is perpendicular to the curved surface. Since there is a gap in the middle of the lower bottom surface, the present invention can be adjusted accordingly according to the curvature of the curved surface. When the curved surface is concave, the lower bottom surfaces of the honeycomb core unit structures of the present invention are close to each other. When the curved surface is convex, the lower bottom surfaces deviate from each other, while the upper bottom surface and the curved surface are always in a conformable and supportive state.

[0021] The beneficial effects of the present invention are as follows: the flexible, extended, high-strength matrix honeycomb prepared by the present invention has the following advantages:

[0022] Applicable to complex curved surfaces, including concave, convex and irregular surfaces, to reduce the collapse caused by the honeycomb splicing process, ensure the integrity of the honeycomb structure, and improve its stress strength;

[0023] The small-aperture honeycomb core unit structure is used to increase the strength by 10-30%, which is suitable for new military aircraft and other aerospace fields;

[0024] It is suitable for complex curved surfaces to avoid damage and collapse of honeycomb cells, reducing the uncertainty of non-destructive testing of honeycomb structures and reducing the risk of use. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the structure of a flexible and extended high-strength matrix honeycomb of the present invention;

[0026] Figure 2 This is a schematic diagram of an embossed structure of a flexible, extended, high-strength matrix honeycomb of the present invention;

[0027] Figure 3 This is a schematic diagram of a structure of multiple groups of honeycomb core units of a flexible and extended high-strength matrix honeycomb of the present invention;

[0028] Figure 4 This is a schematic diagram of a flexible and extended high-strength matrix honeycomb suitable for a concave structure of the present invention;

[0029] Figure 5 This is a schematic diagram of a flexible and extended high-strength matrix honeycomb suitable for a convex structure of the present invention;

[0030] Figure 6 It is a schematic diagram of a process for preparing a flexible and extended high-strength matrix honeycomb according to the present invention;

[0031] In the figure, 1-upper bottom surface; 2-lower bottom surface; 3-regular trapezoidal composite material sheet; 4-node glue; 5-gap. DETAILED DESCRIPTION

[0032] In order to make the objects and advantages of the present invention more clearly understood, the present invention is further described below in conjunction with embodiments; it should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0033] The preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the protection scope of the present invention.

[0034] It should be noted that, in the description of the present invention, terms such as "up", "down", "left", "right", "inside" and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings. This is merely for the convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present invention.

[0035] In addition, it should be noted that in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] Embodiment 1, as Figure 1-Figure 5A flexible and stretchable high-strength matrix honeycomb is shown, which is composed of multiple groups of honeycomb core unit structures that are staggered and welded. The honeycomb core unit structure is composed of six embossed and folded regular trapezoidal composite material sheets. The upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite material sheets extend 1-2mm from the welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the angle between the upper bottom surface and the waist of the regular trapezoidal composite material sheet is 60-85°.

[0037] Embodiment 2, as Figure 1-Figure 5 A flexible and extended high-strength matrix honeycomb is shown, which is composed of multiple groups of honeycomb core unit structures that are staggered and welded. The honeycomb core unit structure is composed of six regular trapezoidal composite thin sheets embossed and folded. The upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite thin sheets extend 1-2mm from the welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the upper bottom surface and waist angle of the regular trapezoidal composite thin sheet are 60-85°. The side length of the regular hexagonal aperture of the upper bottom surface of the honeycomb core unit structure is 2-5mm, and the side length of the regular hexagonal aperture of the lower bottom surface is 1-3mm.

[0038] Embodiment 3, as Figure 1-Figure 5 A flexible and stretchable high-strength matrix honeycomb is shown, which is composed of multiple groups of honeycomb core unit structures welded in an offset manner. The honeycomb core unit structure is composed of six embossed and folded regular trapezoidal composite material sheets. The upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite material sheets extend 1-2mm from the welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the angle between the upper bottom surface and the waist of the regular trapezoidal composite material sheet is 60-85°, and the four sides of the regular trapezoidal composite material sheet on the upper bottom surface of the honeycomb core unit structure are provided with node glue with a width of 1-2mm; the node glues of adjacent honeycomb core unit structures are welded after the node glues are offset and corresponded, and the offset correspondence is that the first sheet of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the regular trapezoidal composite material sheet of the adjacent adjacent honeycomb core unit structure. the sixth piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the third piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the sixth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the fourth piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the first piece of the regular trapezoidal composite material sheet of another adjacent adjacent honeycomb core unit structure; the fifth piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the second piece of the regular trapezoidal composite material sheet of another adjacent adjacent honeycomb core unit structure; the sixth piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the third piece of the regular trapezoidal composite material sheet of another adjacent adjacent honeycomb core unit structure.

[0039] Embodiment 4, as Figure 1-Figure 5A flexible and extended high-strength matrix honeycomb is shown, which is composed of multiple groups of honeycomb core unit structures welded in an offset manner. The honeycomb core unit structure is composed of six regular trapezoidal composite material sheets embossed and folded. The upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite material sheets extend 1-2mm welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the upper bottom surface and waist of the regular trapezoidal composite material sheet are 60-85°, and the regular trapezoidal composite material sheet is any one of aramid paper, polyimide paper, carbon fiber, and glass cloth; a gap is formed between the multiple groups of honeycomb core unit structures, the gap is narrow near the upper bottom surface and wide near the lower bottom surface; the gap width near the lower bottom surface is the difference between the side length of the upper bottom surface and the side length of the lower bottom surface. The gap is the adjustment angle range for the upper bottom surface to adapt to complex curved surfaces, and the threshold value of the adjustment angle range is the angle between the upper bottom surface of the honeycomb core unit structure and the upper bottom surface of the adjacent honeycomb core unit structure, which is 10-60°.

[0040] Embodiment 5, as Figure 6 As shown, the present invention provides a method for preparing a flexible and extended high-strength matrix honeycomb, and the steps are as follows:

[0041] 1) Embossing, unfolding any composite material roll of aramid paper, polyimide paper, carbon fiber, or glass cloth and then embossing it, forming six connected regular trapezoidal composite material sheets after embossing; the embossing width of the first or sixth regular trapezoidal composite material sheet is extended by 1-2 cm; the above is a group, repeating the above steps to emboss the entire composite material roll;

[0042] 2) Cutting: the remaining parts of the six regular trapezoidal composite material sheets after embossing are cut off by a cutting device to form a group of six regular trapezoidal composite material sheets, which is a group, and the above steps are repeated;

[0043] 3) One-time glue laying: glue is laid at the first or sixth extension of a group of six regular trapezoidal composite sheets in a node-type manner, and the node glue laying interval is 0.5-1mm and the interval is uniform;

[0044] 4) Folding: fold a group of six regular trapezoidal composite material sheets along the embossing, and pay attention to aligning the nodes where the first or sixth sheet is extended to ensure that the upper and lower bottom surfaces of the regular trapezoidal composite material sheets are flush, and then form a honeycomb core unit structure;

[0045] 5) Secondary glue distribution and staggered welding, the nodes are uniformly distributed with node glue around the upper bottom surface of the honeycomb core unit structure, and then the node glues of adjacent honeycomb core unit structures are staggered and welded, and ultrasonic welding is used for welding. The staggered correspondence means that the first piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the sixth piece of the regular trapezoidal composite material sheet of the adjacent honeycomb core unit structure; the second piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the third piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; The sixth piece of the regular trapezoidal composite sheet of the core unit structure; the fourth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the first piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; the fifth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the second piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; the sixth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the third piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; in this way, the length and width of the combined honeycomb core unit structure are adjusted as needed to form the required honeycomb core unit structure group;

[0046] 6) Shaping: shaping the honeycomb core unit structure group, using a lining frame slightly smaller than the honeycomb core unit structure, embedding the honeycomb core unit structure into the lining frame for shaping, the initial shaping environment temperature is 250-280℃, the shaping time is 3-5 hours, and the cooling rate is 20-30℃ / min;

[0047] 7) Glue impregnation and curing: the honeycomb core unit structure after shaping is impregnated and cured. The glue impregnation needs to be carried out in a specific glue impregnation mechanism, and the glue liquid is formulated according to different materials. After the glue impregnation, the honeycomb core unit structure is cured in a special oven at a curing temperature of 180-280°C and a curing time of 1-2 hours. The glue impregnation and curing process are repeated to obtain flexible, ductile, high-strength matrix honeycombs of different densities.

[0048] In the staggered welding, the support bar is embedded in the load-bearing honeycomb core unit structure, and the outer diameter of the support bar is slightly smaller than the inner diameter of the honeycomb core unit structure, corresponding to the regular hexagonal structure of the honeycomb core unit structure, wherein the front end is slightly smaller corresponding to the aperture of the lower surface of the honeycomb core unit structure, and the end is slightly larger corresponding to the aperture of the upper surface of the honeycomb core unit structure, and the support bar corresponds to multiple groups fixed on the frame.

[0049] The flexible and stretchable high-strength matrix honeycomb prepared as described above finally presents that the upper bottom surfaces are connected and flush with each other, while the middle of the lower bottom surface forms a prism-like structure with gaps between the prisms. When the present invention is applied to a curved surface, the upper bottom surface conforms to the curved surface, and the lower bottom surface is perpendicular to the curved surface. Since there is a gap in the middle of the lower bottom surface, the present invention can be adjusted accordingly according to the curvature of the curved surface. When the curved surface is concave, the lower bottom surfaces of the honeycomb core unit structures of the present invention are close to each other. When the curved surface is convex, the lower bottom surfaces deviate from each other, while the upper bottom surface and the curved surface are always in a conformable and supportive state.

[0050] So far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

Claims

1. A method for preparing a flexible and high-strength matrix honeycomb, characterized in that: The matrix honeycomb is composed of multiple groups of honeycomb core unit structures welded in an offset manner. The honeycomb core unit structure is composed of six regular trapezoidal composite material sheets embossed and folded. The upper and lower bottoms of the first or sixth sheet of the six regular trapezoidal composite material sheets extend a 1-2mm welding surface, and the embossed width of the sixth sheet or the first sheet corresponds to the welding surface; the angle between the upper bottom surface and the waist of the regular trapezoidal composite material sheet is 60-85°; the side length of the regular hexagonal aperture of the upper bottom surface of the honeycomb core unit structure is 2-5mm, and the side length of the regular hexagonal aperture of the lower bottom surface is 1-3mm; gaps are formed between the multiple groups of honeycomb core unit structures, the gaps are narrow near the upper bottom surface and wide near the lower bottom surface; the width of the gap near the lower bottom surface is the difference between the side length of the upper bottom surface and the side length of the lower bottom surface; the gap is the adjustment angle range for the upper bottom surface to adapt to complex curved surfaces, and the threshold value of the adjustment angle range is the angle between the upper bottom surface of the honeycomb core unit structure and the upper bottom surface of the adjacent honeycomb core unit structure, which is 10-60°; The steps are as follows: 1) Embossing: unfold any composite material roll of aramid paper, polyimide paper, carbon fiber, or glass cloth and then emboss it, and after embossing, six connected regular trapezoidal composite material sheets are formed; the embossed width of the first or sixth regular trapezoidal composite material sheet is extended by 1-2 cm; a group of six regular trapezoidal composite material sheet processing embryo sheets are formed, and the entire roll of composite material is embossed; 2) Cutting: the remaining parts of the six regular trapezoidal composite material sheets after embossing are cut off by a cutting device to form a group of six regular trapezoidal composite material sheets; 3) One-time glue laying: glue is laid at the first or sixth extension of a group of six regular trapezoidal composite sheets in a node-type manner, and the node glue is laid at an interval of 0.5-1mm and evenly spaced; 4) Folding: fold a group of six regular trapezoidal composite material sheets along the embossing, and pay attention to aligning the nodes where the first or sixth sheet is extended to ensure that the upper and lower bottom surfaces of the regular trapezoidal composite material sheets are flush, and then form a honeycomb core unit structure; 5) Secondary glue distribution and staggered welding, the nodes are uniformly distributed with node glue around the upper bottom surface of the honeycomb core unit structure, and then the node glues of adjacent honeycomb core unit structures are staggered and welded, and ultrasonic welding is used for welding. The staggered correspondence means that the first piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the sixth piece of the regular trapezoidal composite material sheet of the adjacent honeycomb core unit structure; the second piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; the third piece of the regular trapezoidal composite material sheet of the honeycomb core unit structure corresponds to the fifth piece of the regular trapezoidal composite material sheet of another adjacent honeycomb core unit structure; The sixth piece of the regular trapezoidal composite sheet of the core unit structure; the fourth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the first piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; the fifth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the second piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; the sixth piece of the regular trapezoidal composite sheet of the honeycomb core unit structure corresponds to the third piece of the regular trapezoidal composite sheet of another adjacent honeycomb core unit structure; in this way, the length and width of the combined honeycomb core unit structure are adjusted as needed to form the required honeycomb core unit structure group; 6) Shaping: shaping the honeycomb core unit structure group, using a lining frame slightly smaller than the honeycomb core unit structure, embedding the honeycomb core unit structure into the lining frame for shaping, the initial shaping environment temperature is 250-280℃, the shaping time is 3-5 hours, and the cooling rate is 20-30℃ / min; 7) Glue impregnation and curing: the honeycomb core unit structure after shaping is impregnated and cured. The glue impregnation needs to be carried out in a specific glue impregnation mechanism, and the glue liquid is formulated according to different materials. After the glue impregnation, the honeycomb core unit structure is cured in a special oven at a curing temperature of 180-280°C and a curing time of 1-2 hours. The glue impregnation and curing process are repeated to obtain flexible, ductile, high-strength matrix honeycombs of different densities.

2. The method for preparing a flexible and extended high-strength matrix honeycomb according to claim 1, characterized in that: In the staggered welding, the support bar is embedded in the load-bearing honeycomb core unit structure, and the outer diameter of the support bar is slightly smaller than the inner diameter of the honeycomb core unit structure, corresponding to the regular hexagonal structure of the honeycomb core unit structure, wherein the front end is slightly smaller corresponding to the aperture of the lower surface of the honeycomb core unit structure, and the end is slightly larger corresponding to the aperture of the upper surface of the honeycomb core unit structure, and the support bar corresponds to multiple groups fixed on the frame.

3. The method for preparing a flexible and extended high-strength matrix honeycomb according to claim 1, characterized in that: The regular trapezoidal composite material sheet is any one of aramid paper, polyimide paper, carbon fiber and glass cloth.

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