Polymer/porous ceramics structure and function integrated gradient composite material and preparation method thereof

Abstract

The invention relates to a function-integration gradient composite material with polymer / porous ceramic structure and a preparation method. The invention solves the problems that single material can not meet the requirement for the performance of the material made by the application condition in an extreme environment and the multilayer composite-structure material is easily layered and has poor safety and reliability. The product of the invention is made from a polymer layer, a gradient connecting layer and a ceramic layer from the inside to the outside. The preparation method comprises the following steps that: 1. the polymer layer, the gradient connecting layer and the ceramic layer are sequentially paved and then are put into a die to be formed by compression so as to obtain the green body of the composite material; 2. the ceramic layer of the green body of the composite material is loaded with high-density heat flux and then is naturally cooled. The composite-structure material of the invention has the advantages of small weight, strong structural strength and high effective heat insulation, is suitable for being used under the extreme working conditions of high temperature, airflow washout, etc., and is safe as well as reliable. The preparation method of the invention is simple and easy to be operated, and can prepare large-scale products with a complicated shape.

Description

technical field

[0001] The invention relates to a functional gradient composite material and a preparation method thereof. Background technique

[0002] When a space vehicle (missile, rocket, spacecraft, etc.) rushes out of the atmosphere at hypersonic speed and returns to the ground (that is, reentry), its surface temperature can reach 1000-5000°C under aerodynamic heating, and it must also withstand high-pressure airflow ablation and Particle cloud erosion; when the solid rocket motor is working, the pressure in the combustion chamber can reach 20 atmospheres, generating a high temperature of nearly 4000°C, and the flow rate of the gas at the nozzle throat can reach Mach 1. In such an environment, it is required that the aircraft can continue to fly, and various devices and systems can work normally, and the problems of heat protection and structure of the warhead must be solved.

[0003] Metals and alloys have been used as warhead materials due to their excellent structu...

Examples

specific Embodiment approach 1

[0012] Embodiment 1: In this embodiment, the polymer / porous ceramic structure-function integrated gradient composite material is made from a polymer layer, a gradient connection layer and a ceramic layer from the inside to the outside; the polymer layer is made of polymer-impregnated fibers The gradient connection layer is made of fiber reinforcement impregnated with polymer and ceramic slurry, of which the gradient connection layer has two to five layers, and the content of the ceramic slurry in each layer of the gradient connection layer increases gradually from the inside to the outside. The polymer content gradient is reduced; the ceramic layer is made of fiber reinforcement impregnated with ceramic slurry.

specific Embodiment approach 2

[0013] Embodiment 2: This embodiment is different from Embodiment 1 in that: the fiber reinforcement in the gradient connection layer is quartz fiber or glass fiber. Others are the same as in the first embodiment.

[0014] The fiber reinforcement in this embodiment is in the form of chopped fibers, continuous long fibers or three-dimensional fiber fabrics.

specific Embodiment approach 3

[0015] Embodiment 3: This embodiment is different from Embodiment 1 in that: the fiber reinforcement in the ceramic layer is quartz fiber or glass fiber. Others are the same as in the first embodiment.

[0016] The fiber reinforcement in this embodiment is in the form of chopped fibers, continuous long fibers or three-dimensional fiber fabrics.

technical field

[0001] The invention relates to a functional gradient composite material and a preparation method thereof. Background technique

[0002] When a space vehicle (missile, rocket, spacecraft, etc.) rushes out of the atmosphere at hypersonic speed and returns to the ground (that is, reentry), its surface temperature can reach 1000-5000°C under aerodynamic heating, and it must also withstand high-pressure airflow ablation and Particle cloud erosion; when the solid rocket motor is working, the pressure in the combustion chamber can reach 20 atmospheres, generating a high temperature of nearly 4000°C, and the flow rate of the gas at the nozzle throat can reach Mach 1. In such an environment, it is required that the aircraft can continue to fly, and various devices and systems can work normally, and the problems of heat protection and structure of the warhead must be solved.

[0003] Metals and alloys have been used as warhead materials due to their excellent structu...

Examples

specific Embodiment approach 1

[0012] Embodiment 1: In this embodiment, the polymer / porous ceramic structure-function integrated gradient composite material is made from a polymer layer, a gradient connection layer and a ceramic layer from the inside to the outside; the polymer layer is made of polymer-impregnated fibers The gradient connection layer is made of fiber reinforcement impregnated with polymer and ceramic slurry, of which the gradient connection layer has two to five layers, and the content of the ceramic slurry in each layer of the gradient connection layer increases gradually from the inside to the outside. The polymer content gradient is reduced; the ceramic layer is made of fiber reinforcement impregnated with ceramic slurry.

specific Embodiment approach 2

[0013] Embodiment 2: This embodiment is different from Embodiment 1 in that: the fiber reinforcement in the gradient connection layer is quartz fiber or glass fiber. Others are the same as in the first embodiment.

[0014] The fiber reinforcement in this embodiment is in the form of chopped fibers, continuous long fibers or three-dimensional fiber fabrics.

specific Embodiment approach 3

[0015] Embodiment 3: This embodiment is different from Embodiment 1 in that: the fiber reinforcement in the ceramic layer is quartz fiber or glass fiber. Others are the same as in the first embodiment.

[0016] The fiber reinforcement in this embodiment is in the form of chopped fibers, continuous long fibers or three-dimensional fiber fabrics.

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