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Preparation method of spaceflight projectile body heat shielding structure

A heat-resistant and projectile technology, applied in the direction of offensive equipment, self-propelled bombs, projectiles, etc., can solve the problems of long cycle, high cost, and high operating threshold, and achieve the effect of low threshold, light weight, and guaranteed production cycle

Active Publication Date: 2017-11-07
绍兴宝旌复合材料技术研发有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003]However, tape winding requires special equipment, site, parameter setting and personnel training, with high cost, long cycle and high operation threshold
General non-mature professional units cannot be manufactured in this way

Method used

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  • Preparation method of spaceflight projectile body heat shielding structure
  • Preparation method of spaceflight projectile body heat shielding structure
  • Preparation method of spaceflight projectile body heat shielding structure

Examples

Experimental program
Comparison scheme
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Embodiment 1

[0037] In this embodiment, the heat-proof structure of the aerospace projectile combines figure 1 , consisting of a heat-resistant layer body 1, a high-temperature structural adhesive layer 2, a heat-resistant coating 3 and a metal cabin section 4, the heat-resistant layer body 1 is bonded together with the metal cabin section 4 through a high-temperature structural adhesive layer 2, and the anti- The outer surface of the thermal layer body 1 is sprayed with a heat-resistant coating 3 .

[0038] Specifically in this embodiment, after the heat-proof layer body 1 is paved and solidified, it is cut into sections after being added by an external circular machine. The high-temperature structural adhesive layer 2 is a liquid adhesive with poor fluidity. The heat-resistant coating is 3 minutes It is an inner coating and an outer coating, and the metal cabin section 4 is a metal part.

[0039] combine figure 2 , the heat-proof layer body 1 is a ring-shaped / conical thin-walled struc...

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PUM

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Abstract

The invention relates to a preparation method of a spaceflight projectile body heat shielding structure. The spaceflight projectile body heat shielding structure is composed of a heat shielding layer body, a high-temperature structure adhesive layer and a heat shielding coating, wherein a heat shielding layer is connected with a metal cabin section through the high-temperature structure adhesive layer, and the external part is coated with the heat shielding coating. The heat shielding layer body is a high silica-phenolic aldehyde composite laminated board. The preparation method is used for manufacturing the spaceflight projectile body heat shielding structure and has the advantages of simple structure, light weight, mature technology, low cost and low operating threshold; and through verification of multiple times of flight tests, the spaceflight projectile body heat shielding structure works normally and the heat shielding meets the flight requirements.

Description

technical field [0001] The invention relates to the technical field of aerospace materials, in particular to a method for preparing a heat-resistant structure of an aerospace projectile. Background technique [0002] When the rocket passes through the air at high speed, it encounters harsh aerodynamic heating. In order to ensure that the metal cabin is not burned, heat-resistant materials must be used to cover the metal cabin, so that the metal cabin is not exposed to high-temperature air and plays the role of heat insulation. Usually choose high silica glass fiber cloth and phenolic resin two kinds of materials. High silica cloth is used as a reinforcing material of high silica / phenolic composite material, and the SiO2 content in the chemical composition of the fiber fabric is more than 96%. Due to the composition of SiO 2 The content is high because of its good heat resistance and insulation properties. High-silica cloth can be melted into a liquid with high viscosity ...

Claims

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Application Information

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IPC IPC(8): F42B15/34B29C70/34B29C65/48
CPCF42B15/34B29C65/48B29C70/342Y02T50/40
Inventor 张卉梓戈家荣
Owner 绍兴宝旌复合材料技术研发有限公司
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