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Solvent-free silicon-based ablation-resistant material

An ablation-resistant and solvent-free technology, which is applied in the field of thermal protection materials for solid rocket motors, can solve problems such as environmental pollution, human harm, and long material preparation cycles, and achieve good oxidation resistance, high temperature resistance, and oxidation resistance performance effect

Inactive Publication Date: 2017-05-03
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problems in the prior art that the silicone resin containing benzene solvents is harmful to the human body and pollutes the environment as the base material of the ablation of the solid rocket motor, the solvent needs to be removed during the molding process of the material, and the material preparation cycle is long. A solvent-free silicon-based ablation-resistant material that can be cured at room temperature with good thermal stability and oxidation resistance

Method used

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Examples

Experimental program
Comparison scheme
Effect test

preparation example Construction

[0036] The preparation technology of composite material of the present invention:

[0037] (1) mixed

[0038] Weigh the liquid silicone resin, silicon carbide, silicon dioxide, metal oxide and silicate, and chopped carbon fiber in proportion, then add them to the barrel of the small laboratory disperser, cover the barrel cover, and start the adjustment. Speed ​​device switch, set the speed at 500-6000rmp / min, so that the materials are fully mixed under the drive of the stirring paddle, the stirring time is controlled within 30-50 minutes, turn off the speed control device switch, open the barrel box, and add the curing agent In the premix, start the speed regulating device again, set the speed at 200-2000rmp / min, fully mix the curing agent and the premix, control the stirring time within 5-10 minutes, turn off the switch of the speed regulating device, and open the barrel Box, take out the mixed material.

[0039] (2) curing

[0040] The premix is ​​poured into the metal te...

Embodiment 1

[0045] name parts by mass liquid silicone 100 Silicon carbide 30 metal oxide or silicate 45 Chopped Aramid Fiber 5 silica 0 Hardener 1.5

Embodiment 2

[0047] name parts by mass liquid silicone 100 Silicon carbide 80 metal oxide or silicate 0 chopped carbon fiber 10 silica 5 Hardener 2

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PUM

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Abstract

The invention provides a solvent-free silicon-based ablation-resistant material. The solvent-free silicon-based ablation-resistant material comprises 100 parts of liquid silicone resin, 0 to 20 parts of carbon fibers, 0 to 100 parts of silicon carbide, 0 to 10 parts of silica, 0 to 50 parts of metal oxide or silicate and 1 to 5 parts of a curing agent. The invention overcomes the problem that conventional silicone resin containing benzene solvents poses harm to human beings and pollutes environment when used as a matrix material for ablation of a solid rocket engine, the solvents need to be removed in the process of material molding and the period of material preparation is long; and the ablation-resistant material provided by the invention has high heat stability, good antioxidation performance and good ablation resistance, can realize casting or compression molding at normal temperature and is applicable to structural protection of aircrafts with complex structures and severe ablation.

Description

technical field [0001] The invention relates to an ablation composite material used for aircraft with complex structure and severe ablation and its parts, such as secondary combustion chamber of solid rocket ramjet engine, flow regulating mechanism, engine nozzle, etc., which belongs to thermal protection material of solid rocket engine field. Background technique [0002] Ablation-resistant materials are usually used in aircraft and missile solid rocket motors. The friction between the aircraft and the atmosphere during flight will generate a high temperature of thousands of degrees Celsius, which will burn the entire aircraft; the high-temperature and high-pressure gas generated by the propellant will damage the engine structure; The engine nozzle is subjected to severe erosion by propellant gas and metal particles. In order to ensure the structural integrity of the rocket engine and other components, a layer of heat insulating material must be pasted on the surface of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C08L83/04C08L77/10C08L79/08C08K13/02C08K13/04C08K7/06C08K3/34C08K3/36C08K3/22C08K7/10
CPCC08K3/22C08K3/34C08K3/36C08K7/06C08K7/10C08K13/02C08K13/04C08K2003/222C08K2003/2224C08K2003/2227C08K2201/003C08K2201/004C08K2201/014C08L83/04C08L2201/08C08L2205/16C08L77/10C08L79/08
Inventor 陈春娟王江詹穹李洋方陆军彭正贵
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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