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High temperature resistant putty and its preparation method

A technology of high temperature resistance and putty, applied in the direction of filling slurry, etc., can solve problems such as filling and repairing of heat-resistant coating, and achieve the effect of excellent process performance and good static heat insulation.

Inactive Publication Date: 2013-01-30
贵州航天风华精密设备有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to overcome the problem of filling and repairing the heat-resistant coating on the outer surface of the existing aerospace carrier, and to provide a high-temperature resistant putty and its preparation method. The putty can withstand high temperatures of 500°C and has excellent Excellent static heat insulation, effectively solve the problem of supporting the application of heat-resistant coatings

Method used

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  • High temperature resistant putty and its preparation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0014] Table 1 Formula of high temperature resistant putty

[0015]

[0016] Note: The curing agent is added when the high temperature putty is prepared

[0017] Preparation method: Take silicone resin, acrylic resin, filler and solvent, mix them, stir them evenly with a nylon rod, then put them into a three-roll mill, adjust the speed ratio of the front roller, middle roller and rear roller of the three-roll mill to 1:3 : 9, the speed of the fast roller is 4-5m / s, start the three-roller mill to disperse evenly, reach the fineness required by the putty, scrape it to the discharge hopper with a scraper, and prepare the A component of the high temperature resistant putty, and the B component is solidified agent, component A and component B are packaged separately. When using, just mix the A component and the B component evenly.

Embodiment 2

[0018] Embodiment 2: performance test of high temperature resistant putty

[0019] (a) Putty preparation: Weigh 300g of component A and 15g of component B in Example 1, and scrape back and forth on the scraper to mix evenly.

[0020] (b) Scratching:

[0021] Anodization of aluminum test piece (100×100×1.2): the thickness of the aluminum test piece is 0.7mm (scratched multiple times);

[0022] Tin plating on tinplate: thickness of tinplate coating is 0.1mm;

[0023] Use multiple scraping methods to achieve the required thickness (every scraping is dried, polished and then scraped again).

[0024] (c) Curing: The test piece was dried naturally for 48 hours.

[0025] (d) Test piece test: Perform performance test on the test piece according to the relevant standards, and the test indicators are shown in Table 2.

[0026] Table 2 Performance test of high temperature thermal insulation coating

[0027] project performance requirements Test results experiment meth...

Embodiment 3

[0030] Embodiment 3: the high-temperature-resistant putty of embodiment 1 is applied on the heat-resistant coating of the second first cabin, the second second cabin, the third cabin and the fifth cabin of a certain new model:

[0031] (a) Putty preparation: Mix component A and component B on the scraper evenly, and scrape back and forth with a scraper.

[0032] (b) Scratching: Scrape high-temperature-resistant putty on the sunken parts of the outer surface of the heat-resistant coating of the cabin, the butt joints of the cabin, and around the antenna. After each coating and scraping, it is dried and then polished and then scraped again to ensure that the outer surface of the coating is dense and smooth. Excessively sleek.

[0033] (c) Curing of the putty layer: the curing of the putty layer is natural drying for 48 hours.

[0034] (d) Usage: From the analysis of the usage of old products and new models, high temperature resistant putty can be mass-produced to meet the needs...

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Abstract

The invention discloses a high temperature resistant putty and its preparation method. The high temperature resistant putty comprises 100 parts by weight of a component A and 4-7 parts by weight of a component B, wherein the component A and the component B are packaged in a separate manner; the component A comprises 13-16 parts by weight of an organic silicon resin, 13-16 parts by weight of an acrylic resin, 48-55 parts by weight of a filler and 15-25 parts by weight of a solvent; and the component B is a curing agent. Compared with putties in the prior art, the high temperature resistant putty provided by the invention enables a putty film to be good and have a very good static heat insulation property when the putty film tolerates a high temperature of 500DEG C, and is a good filling and repairing material for heat-resistant coats of aviation and spaceflight products. The high temperature resistant putty has been applied to some new-model products, and multi-time target tests prove that the high temperature resistant putty can completely satisfy product design requirements.

Description

technical field [0001] The invention relates to the technical field of putty, in particular to a high-temperature resistant putty and a preparation method thereof. Background technique [0002] With the improvement of comprehensive performance of aerospace carriers in terms of range, flight speed, hit accuracy, and defense penetration capabilities, designers must take into account the weight of the carrier, the structural strength of the material, and the safety of the internal components of the carrier. The outer surface of the aerospace carrier is generally sprayed with heat-resistant paint for heat protection, but during the production and use of the heat-resistant coating, the filling and repair of the outer surface is a technical problem faced by the application technology of the heat-resistant coating. [0003] The temperature of the aerospace carrier is high when it is working, especially for the new aerospace carrier. Due to the fast flight speed, the aerodynamic hea...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C09D5/34
Inventor 张绍波
Owner 贵州航天风华精密设备有限公司
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