Multilayer stage heat protection material and preparing method thereof

A thermal protection material, multi-level technology, applied in the direction of weight reduction, fuselage insulation, etc., can solve the problems of cracking and delamination of the inner and outer layers of the thermal protection material, affecting the flight use of the aircraft, and large differences in thermal expansion coefficients, so as to prevent collapse. Failure, guaranteeing the effect of anti-scour and thermal insulation, guaranteeing the effect of bonding force

Active Publication Date: 2020-06-26
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Claims
  • Application Information

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Problems solved by technology

During the flight, due to the large difference in thermal expansion coefficient between the two, during the flight, due to aerodynamic heating and other reasons, it is easy to cause cracking and delamination of the inner and outer layers of the thermal protection material, which directly leads to the failure of the thermal protection material and seriously affects the aircraft. flight use

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  • Multilayer stage heat protection material and preparing method thereof

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preparation example Construction

[0049] According to another embodiment, there is also provided a method for preparing the above-mentioned multi-level thermal protection material, which includes the following steps:

[0050] Step 1, forming the inner layer, including:

[0051] Lay a chopped fiber mesh tire with a set number of layers in the mold and perform needle punching to obtain a fiber reinforcement;

[0052] Prepare the polymerized monomer or low-molecular-weight polymer of the resin in the inner layer with an appropriate amount of solvent mixture to prepare a solution;

[0053] Inject the solution into the fiber reinforcement, so that the fiber reinforcement is fully infiltrated with the solution; then solidify at the resin curing temperature;

[0054] Step 2, forming the strain isolation layer, including:

[0055] Coating a certain thickness of room temperature vulcanizable rubber adhesive on the surface of the inner layer, and vulcanizing and setting the rubber adhesive at room temperature;

[005...

Embodiment 1

[0064] The reinforced body of porous material with low thermal conductivity has a density of 0.12g / cm 3 High-silica fiber felt with a size of 300×300×20mm; the resin matrix is ​​made of polysiloxane-modified phenolic resin with a viscosity of 100cP and a gel time of 100°C / 2min. The RTM molding process is used for molding and curing. The resin curing temperature is 120℃, the curing time is 12 hours, and a low-density heat insulation layer is formed after curing. On the surface of the porous material with low thermal conductivity, coat a layer of 0.5mm thick silicone rubber adhesive, after room temperature vulcanization, lay 3mm on its surface with a density of 1.5g / cm 3 The micro-ablative ceramizable phenolic resin prepreg reinforced with quartz phenolic mixed fibers was sealed with a vacuum bag and cured at 160°C for 4 hours to form a multi-level density gradient thermal protection material.

Embodiment 2

[0066] The reinforcement of the low-density heat insulation layer adopts a density of 0.12g / cm 3 Quartz fiber mat with a size of 300×300×20mm; the resin matrix is ​​made of modified methoxysilane resin with a viscosity of 30cP and a gel time of 100°C / 4h. It is molded and cured by RTM molding process, and the resin curing temperature is 120°C , The curing time is 12 hours, and a low-density heat insulation layer is formed after curing. On the surface of the porous material, a layer of 1.5mm thick methyl phenyl vinyl silicone rubber is coated, and after room temperature vulcanization, it is wound on its surface for 10mm with a density of 1.2g / cm 3 The high-silicone phenolic mixed fiber-reinforced phenolic resin prepreg is sealed with a vacuum bag and cured at 160°C for 4 hours to form a multi-level density gradient thermal protection material.

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Abstract

The invention provides a multilayer stage heat protection material and a preparing method thereof. The material comprises an outer layer, a strain isolation layer and an inner layer which are connected in sequence, the outer layer is a fiber reinforced resin-based composite, the strain isolation layer is a high-temperature-resisting rubber layer, the inner layer is a fiber reinforced resin-based porous composite, the high-temperature-resisting rubber layer is vulcanized to be connected with the inner layer, prepreg of the outer layer is cured and then connected to the strain isolation layer, and the method comprises the steps of forming the inner layer, wherein short cut fiber net blanks of the set layer number are laid in a mold, and needling is carried out to obtain a fiber reinforced body; injecting a solution of resin of the inner layer into the fiber reinforced body to be cured; forming the strain isolation layer, wherein the surface of the inner layer is coated with a certain thickness of rubber adhesive capable of being vulcanized at the room temperature, and vulcanizing and shaping are carried out; and forming the outer layer, wherein prepreg of the outer layer is mounted on the strain isolation layer to be cured. The technical problems that according to an existing heat protection material, inner and outer layers are prone to cracking and layering, and the heat protection material fails directly can be solved.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and in particular relates to a multi-level thermal protection material and a preparation method thereof. Background technique [0002] With the development of hypersonic aircraft, the flight speed of the aircraft is getting faster and faster, and the flight distance is getting larger and larger. The thermal protection system needs to deal with the aerodynamic environment characterized by high heat flow, high enthalpy, and high stagnation point pressure. Most of the current thermal protection systems use a combination of external heat protection structure and internal heat insulation structure. Most of the external heat protection structures use resin-based ablation materials, and most of the internal heat insulation structures use silica airgel materials. During the flight, due to the large difference in thermal expansion coefficient between the two, during the flight, due to aerodyna...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/68B29C35/18B64C1/40
CPCB29C70/34B29C70/68B29C35/18B64C1/40Y02T50/40
Inventor 许学伟许孔力夏雨谢永旺赵跃杰朱八一
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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