阅读说明：本技术 一种单向纤维强化的航天级防隔热涂层材料 (Unidirectional fiber reinforced aerospace-grade heat-insulation-preventing coating material ) 是由 成小雨 乐斌 王欣 李慧晓 于 2021-09-28 设计创作，主要内容包括：本发明公开了一种单向纤维强化的航天级防隔热涂层材料,包括两种交替出现的层状材料A层与B层,所述A层为航天抗热振涂料SR-107系列涂料,所述B层为单向纤维强化层。本发明所述的一种单向纤维强化的航天级防隔热涂层材料,材料以航天用SR-107涂料为基质,使用单向纤维进行强化,不仅提高涂层的机械性能、耐高温性、耐候性等性能,而且使涂层在高压氧化焰加热下,高温发生陶瓷化反应后,可以承受1500℃的加热并在较长时间内不被烧穿,从而可以大幅度降低所需的涂层厚度和施工重量,同时提高涂层的安全系数。(The invention discloses a unidirectional fiber reinforced aerospace-level heat-insulation-preventing coating material which comprises an A layer and a B layer which are two layered materials and appear alternately, wherein the A layer is an aerospace thermal-vibration-resistant coating SR-107 series coating, and the B layer is a unidirectional fiber reinforced layer. The unidirectional fiber reinforced aerospace-level heat-insulating coating material takes the aerospace SR-107 coating as a substrate, is reinforced by unidirectional fibers, not only improves the mechanical property, high temperature resistance, weather resistance and other properties of the coating, but also enables the coating to bear 1500 ℃ heating and not to be burnt through for a long time after ceramic reaction occurs at high temperature under the heating of high-pressure oxidizing flame, thereby greatly reducing the required coating thickness and construction weight and simultaneously improving the safety factor of the coating.)

1. The one-way fiber reinforced aerospace-grade heat-insulating coating material is characterized in that: the coating comprises an A layer (1) and a B layer (2) which are two layered materials and alternately appear, wherein the A layer (1) is an aerospace thermal vibration resistant coating SR-107 series coating, and the B layer (2) is a unidirectional fiber reinforced layer.

2. The unidirectional fiber reinforced aerospace grade thermal barrier coating material as claimed in claim 1, wherein: the thickness of the layer A (1) is 0.2-3.0mm, and the thickness of the layer B (2) is not calculated independently.

3. The unidirectional fiber reinforced aerospace grade thermal barrier coating material as claimed in claim 1, wherein: the material of the unidirectional fiber reinforced layer is at least one of glass fiber, carbon fiber and rock wool fiber.

4. The unidirectional fiber reinforced aerospace grade thermal barrier coating material as claimed in claim 1, wherein: the heat-insulating layer coating, the ablation layer coating and the radiation layer coating of the SR107 series coating products can be used for preparing the unidirectional fiber reinforced heat-insulating prevention coating material.

5. The unidirectional fiber reinforced aerospace grade thermal barrier coating material as claimed in claim 1, wherein: the unidirectional fiber reinforcing layer needs to be subjected to surface treatment by using a silane coupling agent before use, and the silane coupling agent is at least one of KH550, KH540 and KH 792.

6. The unidirectional fiber reinforced aerospace grade thermal barrier coating material as claimed in claim 1, wherein: the unidirectional fiber layer is coated using a unidirectional fiber cloth or a fiber router.

7. The unidirectional fiber reinforced aerospace grade thermal barrier coating material as claimed in claim 1, wherein: the proportion of fibre layers in the final product is about 5% to 40% by mass.

8. The unidirectional fiber reinforced aerospace grade heat-proof and heat-insulating coating material as claimed in claim 1, wherein the preparation method comprises the following steps: s1: uniformly stirring the SR107 aerospace thermal shock resistant coating and a curing agent; s2: uniformly stirring the material obtained in the step S1 in an operation time window, and spraying the material on the surface of a workpiece; s3: when the coating is cured to 40-60% of final hardness, the unidirectional fiber cloth is attached to the surface of the coating; s4: after the coating is solidified to 70-90% of the final hardness, the coating can be sprayed repeatedly; s5: repeating the steps S1 to S3 one to ten times until a unidirectional fiber-reinforced thermal barrier coating of a predetermined thickness is obtained.

9. The unidirectional fiber reinforced aerospace grade thermal insulation coating material according to any one of claims 1-8, applied to the field of spacecraft thermal insulation.

Technical Field

The invention relates to the field of heat preservation and fire prevention, in particular to a unidirectional fiber reinforced aerospace-grade heat-insulating coating material.

Background

Heavy and reusable launch vehicles are one of the main development directions of commercial aerospace technology in recent years, and are also the key points of technical competition in the aerospace field. With the increasing volume and weight of rockets, the thermal protection requirements for the outer shell are higher and higher, and the traditional protection materials such as cork sheets and the like can not meet the performance requirements at all. At present, organic-inorganic composite heat-proof and heat-insulation coatings based on ceramizable have gradually become mainstream protective materials. Because the material body is the coating and can be applied to the arrow body surface with complex contour by spraying, a complete and uniform heat-insulating layer can be obtained at lower cost. However, because of the spray application, the type and amount of reinforcing fibers that can be added to the coating is limited. For example, only chopped carbon fibers can be used, and the maximum length cannot exceed 5 mm.

In the aspect of the instantaneous high-temperature protection of a spacecraft, a ceramizable organic silicon-based composite material is a research hotspot in recent years, for example, Chinese patent application with the application number of CN201910020907.7 discloses a sprayable silicon rubber-based light ablation-resistant heat-insulating coating and application thereof, and Chinese patent application with the application number of CN201910020908.1 discloses an organic silicon resin and barium phenolic resin composite ablation-resistant heat-insulating coating and application thereof. The coating products can have good heat-proof and heat-insulating effects under the environment of infrared heating and mechanical vibration, and can even endure high temperature of more than 1500 ℃ for a long time. However, if a flame with a higher gas pressure, such as an acetylene oxidizing flame, is used for impingement, the through-hole burn-out phenomenon still occurs in a shorter time. The general solution is to use rare earth elements with higher density and high price to strengthen the coating product, which causes the cost and weight of the protective layer to rise greatly. Therefore, the prior art has a large room for improvement.

The unidirectional fiber reinforcement technology is a technology mainly developed from aerospace material manufacturing, has the advantages of easiness in construction, good damping effect, small expansion, high reinforcement selectivity, difficulty in integral failure and the like, and is a technology capable of effectively improving the integral performance of a composite material.

Disclosure of Invention

The invention mainly aims to provide a unidirectional fiber reinforced aerospace-grade heat-insulating coating material, which can generate ceramic reaction at a high temperature of more than 500 ℃, and the generated ceramic phase is combined with a unidirectional fiber material reinforced framework, so that the material can bear high-pressure airflow flame heating at about 1500 ℃ and can not be burnt through for a long time, and the problems in the background art can be effectively solved.

In order to achieve the purpose, the invention adopts the technical scheme that:

the unidirectional fiber reinforced aerospace-level heat-insulating coating material comprises an A layer and a B layer which are two layered materials and appear alternately, wherein the A layer is an aerospace thermal-vibration-resistant coating SR-107 series coating, and the B layer is a unidirectional fiber reinforced layer.

Preferably, the thickness of the A layer is 0.2-3.0mm, and the thickness of the B layer is not separately calculated.

Preferably, the material of the unidirectional fiber reinforced layer is at least one of glass fiber, carbon fiber and rock wool fiber.

Preferably, the thermal insulation layer coating, the ablation layer coating and the radiation layer coating of the SR107 series coating products can be used for preparing the unidirectional fiber reinforced thermal insulation prevention coating material.

Preferably, the unidirectional fiber reinforced layer is subjected to surface treatment by using a silane coupling agent before use, and the silane coupling agent is at least one of KH550, KH540 and KH 792.

Preferably, the unidirectional fiber layer is coated using a unidirectional fiber cloth or a fiber wirer.

Preferably, the proportion of fibre layers in the final product is about 5% to 40% by mass.

Preferably, the preparation method comprises the following steps: s1: uniformly stirring the SR107 aerospace thermal shock resistant coating and a curing agent; s2: uniformly stirring the material obtained in the step S1 in an operation time window, and spraying the material on the surface of a workpiece; s3: when the coating is cured to 40-60% of final hardness, the unidirectional fiber cloth is attached to the surface of the coating; s4: after the coating is solidified to 70-90% of the final hardness, the coating can be sprayed repeatedly; s5: repeating the steps S1 to S3 one to ten times until a unidirectional fiber-reinforced thermal barrier coating of a predetermined thickness is obtained.

Preferably, the unidirectional fiber reinforced aerospace-grade heat-insulation-preventing coating material is applied to the field of heat insulation prevention of spacecrafts.

Compared with the prior art, the invention has the following beneficial effects:

the material in the invention takes the SR-107 coating for spaceflight as a substrate, and is reinforced by using the unidirectional fiber, thereby not only improving the mechanical property, high temperature resistance, weather resistance and other properties of the coating, but also leading the coating to bear 1500 ℃ heating and not to be burnt through in a longer time after ceramic reaction at high temperature under the heating of high-pressure oxidizing flame, further greatly reducing the required coating thickness and construction weight, and simultaneously improving the safety factor of the coating.

Drawings

FIG. 1 is a schematic composition diagram of a unidirectional fiber-reinforced thermal barrier coating material of example 1 after curing;

FIG. 2 is a schematic view of a unidirectional fiber-reinforced thermal barrier coating material of example 1 forming a vitrified layer at an elevated temperature above 500 ℃;

in the figure: 1. SR-107 series aerospace thermal shock resistant heat insulation coating; 2. a unidirectional fiber layer; 3. a ceramic layer.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.

As shown in figure 1-2, a unidirectional fiber reinforced aerospace-grade heat-insulation coating material comprises an A layer 1 and a B layer 2 which are two layered materials which are alternately arranged, wherein the A layer 1 is aerospace thermal-vibration-resistant coating SR-107 series coating, the B layer 2 is a unidirectional fiber reinforced layer, the thickness of the A layer 1 is 0.2-3.0mm, the thickness of the B layer 2 is not independently calculated, the unidirectional fiber reinforced layer is made of at least one of glass fiber, carbon fiber and rock wool fiber, the heat-insulating layer coating, ablation layer coating and radiation layer coating of SR107 series coating products can be used for preparing the unidirectional fiber reinforced heat-insulation coating material, the unidirectional fiber reinforced layer is required to be subjected to surface treatment by using silane coupling agent before use, the silane coupling agent is at least one of KH550, KH540 and KH792, the unidirectional fiber layer is coated by using unidirectional fiber cloth or a fiber wiring device, the proportion of fibre layers in the final product is about 5% to 40% by mass.

The preparation method of the unidirectional fiber reinforced aerospace-grade heat-insulating coating material comprises the following steps: s1: uniformly stirring the SR107 aerospace thermal shock resistant coating and a curing agent; s2: uniformly stirring the material obtained in the step S1 in an operation time window, and spraying the material on the surface of a workpiece; s3: when the coating is cured to 40-60% of final hardness, the unidirectional fiber cloth is attached to the surface of the coating; s4: after the coating is solidified to 70-90% of the final hardness, the coating can be sprayed repeatedly; s5: and repeating the steps S1-S3 for one to ten times until a unidirectional fiber reinforced heat-insulation coating with a preset thickness is obtained, wherein the unidirectional fiber reinforced aerospace-level heat-insulation coating material is applied to the field of heat insulation prevention of spacecrafts, takes the aerospace SR-107 coating as a substrate and is reinforced by unidirectional fibers, so that the mechanical property, the high temperature resistance, the weather resistance and other properties of the coating are improved, and the coating can bear 1500 ℃ heating and cannot be burnt out within a long time after being heated by high-pressure oxidizing flame and subjected to ceramic reaction at high temperature, so that the required coating thickness and construction weight can be greatly reduced, and the safety coefficient of the coating is improved.

Example 1:

the unidirectional fiber reinforced heat-insulating coating material with the thickness of 2.0mm +/-0.2 mm comprises the following preparation raw materials: SR107-TI coating and unidirectional glass fiber cloth (specification G10000).

Wherein, the SR107-TI coating is a resin material coating with low heat transfer coefficient and taking hollow glass microspheres and hollow ceramic microspheres as fillers.

The preparation method of the unidirectional fiber reinforced heat insulation prevention coating material comprises the following steps: (1) uniformly stirring the SR107-TI coating and a curing agent; (2) spraying SR107-TI paint onto the mold plate covered with the release film while stirring, and spraying in a reciprocating manner until the thickness is about 1.0 mm; (3) after the coating is cured to the Shore hardness of 25-30, adhering unidirectional glass fiber cloth G10000 to the surface of the semi-dry coating; (4) and (3) after the coating is cured until the Shore hardness reaches 35, continuously spraying the SR107-TI coating, and repeating the operation (3) after the total thickness reaches 2.0 mm.

Example 2:

the unidirectional fiber reinforced heat-insulating coating material with the thickness of 4.0mm +/-0.4 mm comprises the following preparation raw materials: SR107-TA coating, unidirectional glass fiber cloth (specification G17500).

Wherein, the SR107-TA coating is a resin-based high-temperature-resistant ablation type coating of ceramic nano powder and ceramic precursor, and the density of the coating after complete curing is about 1.27g/cm 3.

The preparation method of the unidirectional fiber reinforced heat insulation prevention coating material comprises the following steps: (1) uniformly stirring the SR107-TA coating and a curing agent; (2) spraying SR107-TA coating onto the mold plate covered with the release film while stirring, and spraying repeatedly until the thickness is about 1.0 mm; (3) after the coating is solidified to the Shore hardness of 30-35, adhering unidirectional glass fiber cloth G17500 to the surface of the semi-dry coating; (4) and (3) repeating the operations (1) to (3) until the total thickness reaches 4.0mm after the coating is cured until the Shore hardness reaches 45.

Comparative example 1:

the thickness of the heat-proof coating material is 4.0mm +/-0.4 mm, and the preparation raw materials comprise the following components: SR107-TA coating.

The preparation method of the heat-proof coating material comprises the following steps: (1) uniformly stirring the SR107-TA coating and a curing agent; (2) spraying SR107-TA coating onto the mold plate covered with the release film while stirring, and spraying repeatedly until the thickness is about 1.0 mm; (3) and (3) repeating the operations (1) to (3) until the total thickness reaches 4.0mm after the coating is cured to the Shore hardness of above 45.

Table 1 comparison of the main properties of example 2 with comparative example 1

By comparing the example 2 with the comparative example 1, it can be seen that the flame airflow impact resistance and the shear strength of the obtained ablation-resistant coating are greatly improved by adding the unidirectional glass fiber into the structure, and the lighter and thinner heat-insulation-preventing coating is favorably used on a spacecraft.

The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.