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Low-burning rate and high-energy HTPB propellant and application of alicyclic diisocyanate

A technology of hydroxybutyl propellant and diisocyanate, which is applied in the field of solid rocket propellants and missile weapons, can solve the problems of not being able to meet high-performance missile weapon models, achieve good aging performance, reduce usage, and reduce energy loss.

Active Publication Date: 2018-06-05
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It can be seen that the existing low burning rate propellant technology and the way to reduce the burning rate cannot meet the needs of high-performance missile weapon models, and there is an urgent need to study low burning rate high-energy propellant technology to meet the needs of missile weapon technology development

Method used

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  • Low-burning rate and high-energy HTPB propellant and application of alicyclic diisocyanate

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0047] The formula (mass percentage) of general low burning rate butylated hydroxyl propellant and the low burning rate high energy butylated hydroxyl using alicyclic diisocyanate as curing agent is shown in Table 1:

[0048] Table 1 The formula of low burning rate and high energy butylated hydroxyl

[0049]

[0050] As can be seen from Table 1, the curing agent TDI in the original low burning rate butyl hydroxy propellant formula (1#) becomes 1- Butyl-2-hexyl-3,4-bis(isocyanate nonyl)cyclohexane, since the reactivity of this type of alicyclic diisocyanate is lower than that of TDI, a curing catalyst tris(3-ethane) has been added to the improved formulation Oxyphenyl) bismuth.

[0051] Table 2 shows the combustion properties of the propellants measured after the two low-burning-rate butylated hydroxybutyl propellant formulations are cured.

[0052] Table 2 Combustion performance of propellant

[0053]

[0054]

[0055] As can be seen from Table 2, with 1-butyl-2-he...

Embodiment 2

[0057] The formula (mass percentage) of general low burning rate butylated hydroxyl propellant and the low burning rate high energy butylated hydroxyl using alicyclic diisocyanate as curing agent is shown in Table 3:

[0058] Table 3 The formula of low burning rate and high energy butylated hydroxyl

[0059]

[0060] As can be seen from Table 3, there are three main differences between the original low-burning-velocity-butylated-hydroxyl propellant formula (3#) and the improved low-burning-rate high-energy butylated-hydroxyl propellant (4#): The curing agent is changed from TDI to 1-pentyl-2-nonyl-3,4-bis(isocyanatoheptyl)cyclohexane; the second is that due to the low reactivity of this type of alicyclic diisocyanate, it is added in the formula Three (ethoxyphenyl) bismuth is used as the curing catalyst; the third is that the amount of the inert deceleration agent LiF in formula 3# is reduced from 1.0% to 0.1%.

[0061] The theoretical calculation of the energy performance...

Embodiment 3

[0066] The formula (mass percentage) of general low burning rate butylated hydroxyl propellant and the low burning rate high energy butylated hydroxyl using alicyclic diisocyanate as curing agent is shown in Table 5:

[0067] Table 5 The formula of low burning rate and high energy butylated hydroxyl

[0068]

[0069]

[0070] It can be seen from Table 5 that the main change between the original low-burning-velocity-butylated hydroxybutyl propellant formulation (5#) and the improved low-burning-rate high-energy butylated-hydroxyl propellant (6#) is that the curing agent is replaced by IPDI Becomes 1-hexyl-2-propyl-3-isocyanatobutyl-4-isocyanatoheptylcyclohexane. Table 6 shows the combustion properties of the propellants measured after the two low-burning-rate HBR propellant formulations are cured.

[0071] Table 6 Various properties of the propellant

[0072]

[0073] As can be seen from Table 6, the low burning rate propellant formulation (6#) with 1-hexyl-2-propyl-...

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Abstract

The invention relates to a low-burning rate and high-energy HTPB propellant and application of alicyclic diisocyanate. The HTPB propellant comprises 6.5-10.0% of hydroxyl-terminated polybutadiene HTPBas an adhesive, 60.0-85.0% of an oxidant AP, 3.0-20% of metal fuel, 2.0-5% of a plasticizer, 1.0-2.0% of alicyclic diisocyanate as a curing agent, 0.05-3.0% of a burning rate inhibitor, 0.01-0.1% ofa curing catalyst and the like. In the HTPB propellant, the alicyclic diisocyanate is used as the curing agent, the oxidant AP, the metal fuel, the plasticizer, the burning rate inhibitor, the curingcatalyst and other components are added, and the using amount of each component is reasonably selected and optimally designed, so that the basic burning rate of the HTPB propellant is significantly reduced; the addition amount of the inert burning rate inhibitor is reduced, so that the energy loss of the propellant is reduced and the combustion efficiency of the propellant is significantly improved; and a formula of the HTPB propellant with low burning rate and high energy is obtained.

Description

technical field [0001] The invention relates to the application of a low-burning-velocity, high-energy butylated hydroxyl propellant and alicyclic diisocyanate, belonging to the technical field of solid rocket propellants and missile weapons. Background technique [0002] Hydroxybutylene propellant has excellent comprehensive performance and moderate energy. It is the most widely used composite solid propellant at present. Hydroxybutylene propellant with low burning rate can meet the long-time working requirements of main engines of strategic and tactical missiles. Research hotspots in the field of propellants. [0003] At present, most of the methods for obtaining low-burning-rate butylated-hydroxyl propellants are to add solid deceleration agents such as various ammonium salts, metal halides, and carbonates to the butylated-hydroxyl propellant. These deceleration agents reduce combustion temperature and inhibit combustion. Reaction chemical balance and other ways reduce t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B33/06C06B23/00C06D5/06
CPCC06B23/009C06B33/06C06D5/06
Inventor 李爽刘学贾方娜胡期伟毛羽高扬程迪
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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