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Short-term high-temperature ablation resistant protective coating and preparation method thereof

A protective coating and high temperature resistance technology, applied in the field of surface engineering, can solve problems such as high temperature cracking of phenolic coatings, and achieve the effects of reducing the surface temperature of the substrate, simple preparation process, and short-term high temperature ablation effect.

Active Publication Date: 2015-10-28
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention mainly aims at the high temperature (2000°C) short-time (50-300s) thermal protection of the aircraft surface and the technical problem of high-temperature cracking of the phenolic coating in the prior art, and proposes a short-time high-temperature ablation-resistant protective coating and its preparation method

Method used

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  • Short-term high-temperature ablation resistant protective coating and preparation method thereof

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] 1) Add 100g of barium phenolic resin, 100g of high silica fiber, and 25g of phenolic pellets in sequence using high-speed shear dispersion equipment and mix them evenly;

[0033] 2) Molded coating preparation: take 100g and put it into the cavity of the flat steel mold on the surface of the carbon / carbon substrate, the size of the flat steel mold is 100mm×100mm×5mm;

[0034] 3) Place the carbon / carbon substrate together with the mold in a flat press to press it into a flat plate with a pressure of 1 ton. After standing at room temperature for 24 hours, it is cured in a flat press at 160°C and a pressure of 1 ton for 5 hours to obtain a coated carbon / carbon substrate. carbon substrate.

[0035] The obtained coated carbon / carbon substrate was subjected to a thermal ablation test, ablated with a plasma flame at 2000°C for 100s, the coating was not completely ablated, the substrate temperature was ≤360°C, and the substrate temperature was as follows: figure 1 As shown, and...

Embodiment 2

[0037] 1) Add 100g of boron phenolic aldehyde, 80g of viscose carbon fiber, 25g of cork powder, and 25g of phenolic pellets in sequence using a three-roller grinding equipment and mix them evenly, and control the distance between the rollers of the three-roller grinding equipment to 1-1.5mm;

[0038] 2) Stir a certain amount of acetone evenly in the uniformly dispersed material to prepare the coating, the amount of acetone added is determined according to the viscosity of the coating, and the viscosity is 10-30s measured with a Tu-4 cup viscometer;

[0039] 3) At room temperature, spray the paint on the surface of the carbon / carbon substrate with a spray thickness of 6mm. After standing at room temperature for 24 hours, it is cured at 160°C for 5 hours to obtain a coated carbon / carbon substrate.

[0040] Coating effect: The coating is ablated with a plasma flame at 2000°C for 100s, the coating is not completely ablated, and the substrate temperature is ≤320°C.

Embodiment 3

[0042] 1) Add 100g of ammonium phenolic resin, 50g of epoxy E51 resin, 150g of high silica fiber, and 50g of phenolic pellets in sequence using high-speed shear dispersion equipment and mix them evenly;

[0043] 2) Molded coating preparation: add 10g polyamide to the uniformly mixed material, take 100g after stirring evenly and put it into the cavity of the flat steel mold on the surface of the carbon / carbon substrate, the size of the flat steel mold is 100mm ×100mm×5mm;

[0044] 3) Place the carbon / carbon substrate together with the mold in a flat press to press it into a flat plate with a pressure of 1 ton. After standing at room temperature for 24 hours, it is cured in a flat press at 160°C and a pressure of 1 ton for 5 hours to obtain a coated carbon / carbon substrate. carbon substrate.

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Abstract

The present invention relates to a short-term high-temperature ablation resistant protective coating and a preparation method thereof. The protective coating is a functional coating and belongs to the technical field of surface engineering. The coating surface can be used for aircraft surface to prevent the matrix material from the direct damage of high-temperature hot-fluid and to reduce the surface temperature of the substrate. Coating of the present invention can be used in the preparation of the aircraft surface to prevent damage to the high-temperature heat directly to the base material, and reduce the surface temperature of the substrate, and has the advantages of good short-term high-temperature ablation resistant effect, simple preparation process, and application to the surface of large and complex structure. The coating can be used for a short time below 2000 DEG C, and the coating does not fall off or crack. For example, a coating of 7mm thick applied to carbon / carbon substrate surface is ablated with 2000 DEG C plasma flame for 100 s, and the coating is not completely ablated, and temperature of the substrate is no higher than 500 DEG C.

Description

technical field [0001] The invention relates to a short-term high-temperature anti-ablation protective coating and a preparation method thereof. The protective coating is a functional coating and belongs to the technical field of surface engineering. The coating can be used on the surface of an aircraft to prevent high-temperature heat flow from affecting the substrate material. Direct damage, lower substrate surface temperature. Background technique [0002] Hypersonic vehicles (hypersonic missiles, reusable vehicles) have become the main development direction of aerospace and weapon systems, and are also the strategic technological commanding heights that major military powers are striving to seize. However, with the improvement of the flying speed of the aircraft, new technical problems are placed in front of people again. For example, when a supersonic missile re-enters the atmosphere at a speed of Mach 8, the surface stagnation point temperature will exceed 2000°C. If ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C09D161/06C09D163/00C09D7/12
Inventor 赵立波罗正平卢鹉李俊峰金珂
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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