Method for manufacturing a three-dimensional lattice structure of composite material

Abstract

The application provides a preparation method of a composite three-dimensional lattice structure, which comprises the following steps: weaving silicon carbide fibers to form a silicon carbide fiber cloth, rolling the silicon carbide fiber cloth into rod-shaped lattice bars, and sewing the joints of the lattice bars with carbon fibers; weaving the silicon carbide fibers to form a panel, and forming positioning holes on the panel for mounting the lattice bars; clamping the lattice bars in the positioning holes, sewing the joints between the lattice bars and the panel with carbon fibers, and forming a preform; placing the preform into a mold, injecting resin into the mold, wrapping the preform with the resin, heating the mold, and cracking the resin to form a carbon matrix; under a high-temperature vacuum environment, infiltrating molten silicon into the carbon matrix, and reacting to form a silicon carbide matrix, so as to form a metal-ceramic matrix composite three-dimensional lattice structure. The composite three-dimensional lattice structure prepared by the method has excellent heat resistance and load bearing capacity.

Description

Technical Field

[0001] This invention relates to the field of high-temperature resistant structural technology, and more specifically, to a method for preparing a three-dimensional lattice structure of composite materials. Background Technology

[0002] Lattice structures are spatial plate-rod structures with high porosity, high connectivity, and low density, composed of micro-elements such as rods and panels arranged in a certain regular pattern. They feature high specific strength, high specific stiffness, and strong spatial designability. Unlike low-density porous structures such as aperiodic foams, lattice structures are spatially interconnected porous structures with periodic rods as connecting units, making them lighter and more designable.

[0003] Three-dimensional lattice structures made of ceramic matrix composites, high-temperature resistant metals, or a mixture of both materials possess both excellent load-bearing and thermal insulation properties, making them an ideal integrated structure and function for future high-speed aircraft.

[0004] When preparing three-dimensional lattice structures using existing methods, a split approach is generally adopted, with bolts used to connect the panel and the rod. Under this connection method, the bonding force between the panel and the rod is low, and the connection strength is not high. Summary of the Invention

[0005] (a) Technical problems to be solved

[0006] The technical problem to be solved by this invention is that the bonding force between the panel and the rod is low and the connection strength is not high when preparing a three-dimensional lattice structure.

[0007] (II) Technical Solution

[0008] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0009] A method for preparing a three-dimensional lattice structure of a composite material is provided, comprising the following steps:

[0010] Step 1: Silicon carbide fibers are woven into silicon carbide fiber cloth using a two-dimensional weaving method. The silicon carbide fiber cloth is then rolled into rod-shaped lattice ribs, and the seams of the lattice ribs are sewn together with carbon fiber.

[0011] Step 2: Silicon carbide fibers are woven into an upper panel and a lower panel using a three-dimensional weaving method. Positioning holes for installing the lattice ribs are formed on the upper panel and the lower panel.

[0012] Step 3: Attach the dot matrix ribs to the positioning holes so that the dot matrix ribs are connected to the panel, and sew the seam between the dot matrix ribs and the panel preform with carbon fiber to form the preform;

[0013] Step 4: Place the preform into a mold, inject resin into the mold, the resin coats the preform, and heat the mold to cause the resin to decompose and form a carbon matrix;

[0014] Step 5: In a vacuum environment at a temperature of 1500℃~1700℃, molten silicon is impregnated into the carbon matrix to react and generate a silicon carbide matrix, thereby forming a three-dimensional lattice structure of the metal-ceramic matrix composite material.

[0015] Preferably, the panel includes an upper panel and a lower panel arranged opposite to each other, and before step five, a high-temperature resistant panel is covered on the side of the upper panel away from the dot matrix ribs.

[0016] Preferably, the high-temperature resistant panel is formed by selective laser cladding.

[0017] Preferably, the positioning hole is a round hole or an elliptical hole.

[0018] Preferably, the lattice ribs are cylindrical or hollow tubular.

[0019] Preferably, the material of the high-temperature resistant panel is tungsten or tantalum.

[0020] Preferably, the molten silicon is reacted with a carbon matrix at a temperature of 1500℃~1700℃ for 2 hours through a vacuum infiltration process to generate a silicon carbide matrix. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of a three-dimensional lattice structure of composite materials provided in an embodiment of the present invention.

[0022] In the attached image:

[0023] 1. Dot matrix ribs; 11. Joints; 2. Top panel; 3. Bottom panel; 4. Positioning holes.

[0024] (III) Beneficial Effects

[0025] The above-described technical solution of the present invention has at least the following advantages:

[0026] 1. Silicon carbide fibers possess high temperature resistance and strength. By weaving silicon carbide fibers to form a three-dimensional lattice structure, the overall load-bearing capacity of the lattice structure can be improved. Resin is heated and decomposed to form a carbon matrix, and molten silicon reacts with the carbon matrix to form a silicon carbide matrix, thereby preparing a three-dimensional lattice structure of silicon carbide ceramic matrix composite material reinforced with silicon carbide fibers. The silicon carbide ceramic matrix composite three-dimensional lattice structure prepared by this method exhibits excellent load-bearing and thermal insulation properties, making it an ideal structure for manufacturing high-speed aircraft.

[0027] 2. By using soft carbon fiber to stitch the seams of the lattice ribs, as well as to stitch the seams between the top panel, bottom panel and the lattice ribs, the components have good bonding strength, are not easy to crack, and improve the overall load-bearing performance.

[0028] 3. The top panel, bottom panel, and lattice ribs are formed by integrated sintering or vacuum infiltration of silicon melt, resulting in high connection quality and good tensile and shear resistance. Detailed Implementation

[0029] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present 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 of the present invention and are not intended to limit the present invention.

[0030] It should be noted that when a component is referred to as "fixed to" or "set on" another component, it can be located directly on or indirectly on the other component. When a component is referred to as "connected to" another component, it can be directly or indirectly connected to the other component.

[0031] It should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate that the device or element must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0032] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating relative importance or the number of technical features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. The specific implementation of this invention will be described in more detail below with reference to specific embodiments:

[0033] like Figure 1 As shown, this embodiment of the invention provides a method for preparing a three-dimensional lattice structure of composite materials, including the following steps:

[0034] Step 1: Silicon carbide fibers are woven into a silicon carbide fiber cloth using a two-dimensional weaving method. The silicon carbide fiber cloth is then rolled into rod-shaped lattice ribs 1, and the seams 11 of the lattice ribs are sewn with carbon fiber. Silicon carbide fibers have high temperature resistance and strength. By weaving silicon carbide fibers to form the overall skeleton of a three-dimensional lattice structure, the overall load-bearing capacity of the three-dimensional lattice structure can be improved. Carbon fiber is relatively soft, making it easy to sew along the seams.

[0035] Step 2: Silicon carbide fibers are woven into a panel (including an upper panel 2 and a lower panel 3) using a three-dimensional weaving method. Positioning holes 4 are formed on the panel for installing the lattice ribs 1. The positioning holes 4 have a certain depth to limit the lattice ribs 1 within the positioning holes 4, thereby improving the bonding stability between the lattice ribs 1 and the panel and the lower panel 3.

[0036] Step 3: Attach the dot matrix rib 1 to the positioning hole 4 so that the dot matrix rib 1 is connected to the panel, and sew the joint between the dot matrix rib 1 and the panel with carbon fiber to form a preform.

[0037] Step 4: Place the preform into the mold, inject resin into the mold, the resin coats the preform, and heat the mold to cause the resin to decompose and form a carbon matrix; the resin includes, but is not limited to, phenolic resin, epoxy resin, etc. The resin decomposes at high temperature to form carbon, thus forming a carbon matrix; the specific heating temperature is determined by the composition of the resin, and different resin compositions require different heating temperatures.

[0038] Step 5: In a vacuum environment with a temperature of 1500℃~1700℃, molten silicon is impregnated into the carbon matrix to react and generate a silicon carbide matrix, thereby forming a three-dimensional lattice structure of metal-ceramic matrix composite material.

[0039] As one of the optional implementations of this embodiment, the panel includes an upper panel 2 and a lower panel 3 arranged opposite to each other. Before step five, a high-temperature resistant panel is covered on the side of the upper panel 2 away from the lattice ribs 1 to further improve the temperature resistance of the overall structure.

[0040] As one of the optional implementations of this embodiment, the high-temperature resistant panel is formed by selective laser cladding.

[0041] As one optional implementation of this embodiment, the positioning hole 4 is a round hole or an elliptical hole. The shape of the positioning hole 4 is adapted to the shape of the end face of the lattice rib 1. That is, when the end face of the lattice rib 1 is round, the positioning hole 4 is preferably a round hole; when the end face of the lattice rib 1 is elliptical, the positioning hole 4 is preferably an elliptical hole.

[0042] As one optional implementation of this embodiment, the lattice rib 1 is cylindrical or hollow tubular. The shape of the lattice rib 1 is selected according to different practical application requirements. For example, when the overall mass of the component needs to be reduced, hollow tubular lattice ribs are preferred; when the component has high requirements for the strength of the overall structure, cylindrical lattice ribs are preferred.

[0043] As one of the optional embodiments of this example, the material of the high-temperature resistant panel is tungsten or tantalum; tungsten or tantalum has higher temperature resistance and oxidation resistance.

[0044] In one optional implementation of this embodiment, molten silicon reacts with a carbon matrix through a vacuum infiltration process to form a silicon carbide matrix. Molten silicon infiltrates into the carbon matrix under vacuum via capillary action and reacts with the carbon matrix to form the silicon carbide matrix.

[0045] As one of the optional implementation methods of this embodiment, molten silicon is reacted with a carbon matrix at a temperature of 1600°C for 2 hours through a vacuum infiltration process to generate a silicon carbide matrix.

[0046] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for preparing a three-dimensional lattice structure of composite materials, characterized in that, Includes the following steps: Step 1: Silicon carbide fibers are woven into silicon carbide fiber cloth using a two-dimensional weaving method. The silicon carbide fiber cloth is then rolled into rod-shaped lattice ribs, and the seams of the lattice ribs are sewn together with carbon fiber. Step 2: Silicon carbide fibers are woven into a panel using a three-dimensional weaving method. The panel has positioning holes for installing the lattice ribs. Step 3: Attach the dot matrix ribs to the positioning holes so that the dot matrix ribs are connected to the panel, and sew the seam between the dot matrix ribs and the panel preform with carbon fiber to form the preform; Step 4: Place the preform into a mold, inject resin into the mold, the resin encapsulates the preform, heat the mold to cause the resin to decompose and form a carbon matrix; the panel includes an upper panel and a lower panel arranged opposite to each other, and a high-temperature resistant panel is covered on the side of the upper panel away from the lattice ribs. Step 5: In a vacuum environment at a temperature of 1500℃~1700℃, molten silicon is impregnated into the carbon matrix to react and generate a silicon carbide matrix.

2. The method for preparing a three-dimensional lattice structure of composite materials as described in claim 1, characterized in that, The high-temperature resistant panel is formed by selective laser cladding.

3. The method for preparing a three-dimensional lattice structure of composite materials as described in claim 1, characterized in that, The positioning hole is either a round hole or an elliptical hole.

4. The method for preparing a three-dimensional lattice structure of composite materials as described in claim 1, characterized in that, The lattice ribs are hollow tubular.

5. The method for preparing a three-dimensional lattice structure of composite materials as described in claim 1, characterized in that, The high-temperature resistant panel is made of tungsten or tantalum.

6. The method for preparing a three-dimensional lattice structure of composite materials as described in claim 1, characterized in that, The molten silicon reacts with the carbon matrix through a vacuum infiltration process to generate a silicon carbide matrix.

7. The method for preparing a three-dimensional lattice structure of composite materials as described in claim 6, characterized in that, The molten silicon is reacted with a carbon matrix at a temperature of 1500℃~1700℃ for 2 hours through a vacuum infiltration process to generate a silicon carbide matrix.

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