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Method for Solving Post-curing Problem of Room Temperature Curing Butyl Hydroxyl Propellant and Prepared Product

A room temperature curing and propellant technology, which is used in the field of solid rocket propellants and missile weapons, can solve problems such as post-curing, and achieve the effect of improving aging performance and solving post-curing problems.

Active Publication Date: 2020-12-22
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention aims at the serious post-curing problem of room temperature curing propellants, and provides a method for solving the post curing problem of room temperature curing butylated hydroxyl propellants, which solves the problem of room temperature curing propellants without affecting the initial mechanical properties and curing process of the propellant. Post-curing problem, to achieve the purpose of improving the aging performance of room temperature curing propellants

Method used

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  • Method for Solving Post-curing Problem of Room Temperature Curing Butyl Hydroxyl Propellant and Prepared Product
  • Method for Solving Post-curing Problem of Room Temperature Curing Butyl Hydroxyl Propellant and Prepared Product
  • Method for Solving Post-curing Problem of Room Temperature Curing Butyl Hydroxyl Propellant and Prepared Product

Examples

Experimental program
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Effect test

Embodiment 1

[0041] The formula (mass percentage) of room temperature curing propellant is as shown in table 1:

[0042] Table 1 Room temperature curing propellant formulation

[0043]

[0044] As can be seen from Table 1, compared with the prior art room temperature curing propellant formula (1#), in the formula (2#) of the room temperature curing propellant of the present invention, only 0.3% of 1-propyl-2 -Heptyl-3-isocyanatenonyl-4-isocyanatebutylcyclohexane. Table 2 shows the room temperature mechanical properties of the propellant cured for different days at 35°C.

[0045] Table 2 Room temperature mechanical properties of room temperature curing propellants (cured at 35°C)

[0046]

[0047] As can be seen from Table 2, the initial mechanical properties of the room temperature curing propellant and prior art formulations and the attainment of vulcanization by adding auxiliary agent 1-propyl-2-heptyl-3-isocyanate nonyl-4-isocyanate butyl cyclohexane The point time is comparabl...

Embodiment 2

[0049] The formula (mass percentage) of room temperature curing propellant is as shown in table 3:

[0050] Table 3 Room temperature curing propellant formulation

[0051]

[0052] As can be seen from Table 3, compared with the prior art room temperature curing propellant formula (3#), in the improved room temperature curing propellant formula (4#), 0.4% 1-butyl-2- Octyl-3,4-bis(isocyanatooctyl)cyclohexane. The room temperature mechanical properties and initial accelerated aging properties of the propellant cured at 40°C for different days are shown in Table 4. Table 4 also lists the mechanical properties of the propellant cured at 50°C for the improved propellant formulation .

[0053] Table 4 Normal temperature mechanical properties of room temperature curing propellants

[0054]

[0055] It can be seen from Table 4 that the room temperature curing propellant added with auxiliary agent 1-butyl-2-octyl-3,4-bis(isocyanate octyl)cyclohexane is cured at 40°C and cured a...

Embodiment 3

[0057] The formula (mass percentage) of room temperature curing propellant is as shown in table 5:

[0058] Table 5 Room temperature curing propellant formulation

[0059]

[0060] As can be seen from Table 5, compared with the prior art room temperature curing propellant formula (5#), in the formula (6#) of the room temperature curing propellant of the present invention, 0.3% of 1-pentyl-2- Nonyl-3,4-bis(isocyanatoheptyl)cyclohexane. Table 6 shows the room temperature mechanical properties of the propellant cured for different days at 35°C.

[0061] Table 6 Room temperature mechanical properties of room temperature curing propellants (cured at 35°C)

[0062]

[0063] As can be seen from Table 6, the room temperature curing propellant of the present invention with the addition of auxiliary agent 1-pentyl-2-nonyl-3,4-bis(isocyanatoheptyl)cyclohexane is compared with the room temperature curing propellant of the prior art , the initial mechanical properties and the time...

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Abstract

The invention discloses a method used for solving post-solidification problems of room temperature solidified hydroxy terminated polybutadiene propellant. According to the method, an auxiliary agent capable of inhibiting room temperature solidified propellant post-solidification is added into the room temperature solidified propellant, the auxiliary agent is isocyanate alkyl substituted cyclohexane, and the mass amount of the auxiliary agent accounts for 0.1 to 2.0% of that of the hydroxy terminated polybutadiene propellant. The method is capable of solving post-solidification problems of theroom temperature solidified propellant without influencing the performance of the room temperature solidified propellant such as initial mechanical properties and solidification technology, improvingthe ageing performance of the room temperature solidified propellant, and providing base for practical applications of the room temperature solidified propellant.

Description

technical field [0001] The invention relates to the technical field of solid rocket propellants and missile weapons, in particular to a room-temperature-cured hydroxybutylene propellant for charge of solid rocket motors. Background technique [0002] Hydroxybutylene propellant has excellent comprehensive performance and is the most widely used composite solid propellant for weapons and aerospace models at home and abroad. The curing temperature of the hydroxybutyl propellant is generally 50°C to 70°C. After the curing is completed, the propellant needs to undergo a cooling process from the curing temperature to normal temperature. Due to the large difference in expansion coefficient between the propellant grain, liner, thermal insulation layer and shell, the grain will generate a large thermal stress during the cooling process, which will easily lead to cracks in the grain and interface debonding, damage The structural integrity of the propellant is compromised, and safety ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06D5/06C06B23/00C06B33/06
CPCC06B23/00C06B33/06C06D5/06
Inventor 庞爱民李爽郭滢泷贾方娜胡期伟刘学侯斌程迪高扬
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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