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Thermal protection coating material structure for rocket launching pad and application of structure

A coating material and rocket launch technology, applied in the direction of layered products, synthetic resin layered products, chemical instruments and methods, etc., can solve the problems of thick thickness, inability to move the launch pad, heavy weight, etc., to reduce thermal burn Corrosion and thermal shock, lower back temperature, strong adhesion

Inactive Publication Date: 2016-10-05
DALIAN INST OF CHEM PHYSICS CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In foreign countries, the Ariane rocket launch platform of the European Space Agency in Guyana, South America is a concrete launch platform. This type of launch platform constructed of inorganic non-metallic materials has better gas purging and ablation resistance than organic ablation coatings, but the disadvantage is that it is thick. , heavy, and the launch pad cannot be moved

Method used

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  • Thermal protection coating material structure for rocket launching pad and application of structure
  • Thermal protection coating material structure for rocket launching pad and application of structure
  • Thermal protection coating material structure for rocket launching pad and application of structure

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Embodiment 1

[0033] The preparation of embodiment 1 thermal protection coating material

[0034] Such as figure 1 Shown:

[0035] 1. Preparation of the first organic layer: mix epoxy resin, curing agent modified polyamine, and toughening agent liquid rubber according to the mass ratio of 7:2:1, and coat it on the rust-removed 190×120×5mm On the surface of one side of the steel plate, the coating thickness is 2mm.

[0036] 2. Preparation of the refractory brick layer: place the clay refractory brick (NZ)-2 with a thickness of 5mm on the organic layer, so that the clay refractory brick layer is attached to the organic layer, and fix the refractory brick layer on the steel plate.

[0037] 3. Preparation of the second organic layer: After mixing epoxy resin, curing agent modified polyamine, and toughening agent liquid rubber in a mass ratio of 7:2:1, coat it on the clay refractory brick layer, and coat The thickness is 2mm.

[0038] 4. Preparation of the amorphous refractory layer: First, ...

Embodiment 2

[0043] Embodiment 2 The preparation of thermal protection coating material structure

[0044] 1. Preparation of the first organic layer: mix epoxy resin, curing agent modified polyamine, and toughening agent liquid rubber according to the mass ratio of 7:2:1, and coat it on the rust-removed 190×120×5mm On the surface of one side of the steel plate, the coating thickness is 4mm.

[0045] 2. Preparation of the refractory brick layer: place the clay refractory brick (NZ)-2 with a thickness of 15mm on the organic layer, so that the clay refractory brick layer is attached to the organic layer, and fix the refractory brick layer on the steel plate.

[0046]3. Preparation of the second organic layer: mix epoxy resin, curing agent modified polyamine, and toughening agent liquid rubber according to the mass ratio of 7:2:1, and then coat it on the clay refractory brick. is 2mm.

[0047] 4. Preparation of the amorphous refractory layer: First, mix the 5-3mm and 3-1mm mullite evenly acc...

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Abstract

The invention discloses a thermal protection coating material structure for a rocket launching pad and application of the structure. The thermal protection coating material is composed of a first organic layer, a refractory brick layer, a second organic layer and an unshaped refractory material layer, wherein the two organic layers are same in composition and are both composed of epoxy resin, curing agent modified polyamine and toughening agent liquid rubber, and the unshaped refractory material layer is composed of mullite, cordierite, aluminate cement and silica fume. The thermal protection coating material is high in adhesive force and can bear simulated combustion-gas flow scour of a rocket and greatly reduce thermal ablation and thermal shock of a metallic substrate; the thermal protection coating material has good high-temperature combustion-gas flow scour resistance and thermal insulating performance, the temperature of the back face of metal does not exceed 80 DEG C, and therefore an effective thermal protection effect on the rocket launching pad is achieved.

Description

technical field [0001] The invention belongs to the field of high temperature resistance and heat insulation protection, and in particular relates to a structure of a heat protection coating material for a rocket launching platform and an application thereof. Background technique [0002] With the development of aerospace and aerospace industry, thermal protective coating materials have opened up new application fields. In addition to the thermal protection of the aircraft itself, thermal protection measures have also been added to ground facilities such as rocket launch pads in China. If the rocket launch pad is coated with a thermal protective coating material, it can insulate the metal surface, reduce thermal ablation and thermal shock, and prevent the rocket launch pad from thermal fatigue, thermal cracking and thermal shock under the action of multiple thermal shock loads. Fracture, so as to ensure the reliability of the rocket launch pad and prolong the service life o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B15/09B32B15/18B32B27/04B32B9/04B32B33/00
Inventor 张巍马磊王国鹏王晓东张涛
Owner DALIAN INST OF CHEM PHYSICS CHINESE ACAD OF SCI
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