A high energy low burning rate temperature sensitive coefficient propellant

A technology of temperature sensitivity coefficient and propellant, used in explosives and other directions to achieve the effect of increasing the range

Active Publication Date: 2017-11-14
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the high-energy propellant currently developed has a high energy level, the temperature sensitivity coefficient of the burning rate is generally 0.35%K -1 The above cannot meet the complex ambient temperature requirements of tactical weapon models

Method used

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  • A high energy low burning rate temperature sensitive coefficient propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] (1) Propellant composition

[0034] components

gaps

TEGDN

AP

HMX

Al

Content (%wt)

13.5

10

15

50

10

components

TPB

MNA

BAG-78C

LM-100

TDI

Content (%wt)

0.1

0.3

0.3

0.5

0.3

[0035] (2) Propellant performance

[0036] Measured specific impulse: 2451N.s / kg (6.86MPa, measured specific impulse efficiency 0.944)

[0037] Density: 1.76g / cm 3

[0038] Burning rate temperature sensitivity coefficient: 0.13% K -1 (-30°C~40°C).

Embodiment 2

[0040] (1) Propellant composition

[0041] components

gaps

TEGDN

AP

HMX

Al

Content (%wt)

12

12

18

38

18

components

TPB

MNA

BAG-78C

LM-100

Content (%wt)

0.1

0.2

0.4

1.3

[0042] (2) Propellant performance

[0043] Measured specific impulse: 2480N.s / kg (6.86MPa, measured specific impulse efficiency 0.938)

[0044] Density: 1.79g / cm 3

[0045] Burning rate temperature sensitivity coefficient: 0.15% K -1 (-30°C~40°C).

Embodiment 3

[0047] (1) Propellant composition

[0048] components

gaps

TEGDN

AP

HMX

Al

Content (%wt)

13

13

16

42.3

14

components

TPB

MNA

BAG-78C

LM-100

Content (%wt)

0.1

0.3

0.4

0.9

[0049] (2) Propellant performance

[0050] Measured specific impulse: 2474N.s / kg (6.86MPa, measured specific impulse efficiency 0.940)

[0051] Density: 1.77g / cm 3

[0052] Burning rate temperature sensitivity coefficient: 0.14 %K -1 (-30°C~40°C).

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Abstract

A propellant with high energy and low burning rate temperature sensitivity coefficient, comprising the following components: binder 12%~15%; plasticizer 10%~13%; oxidizer 15%~18%; energetic explosive 38%~50% ;Metal fuel 10%~18%; small component: 1.5%~2.0%. Wherein the binder is polyazide glycidyl ether; the plasticizer is triethylene glycol dinitrate or 2,4-dinitro-2,4-diazaalkane; the oxidizing agent is ammonium perchlorate; The energetic explosive is Octojin; the metal fuel is aluminum powder. The invention has the characteristics of high propellant energy (the standard measured specific impulse is greater than 2450N.s / kg) and low burning rate temperature sensitivity coefficient (the burning rate temperature sensitivity coefficient is not greater than 0.15%K-1), and is suitable for applications requiring long range, A tactical missile engine with strong penetration capability, high reliability and precise guidance.

Description

technical field [0001] The invention relates to a GAP high-energy low-burning-velocity temperature-sensitivity coefficient propellant suitable for tactical missiles requiring long firing range, strong penetration capability, high reliability and precise guidance. Background technique [0002] The temperature sensitivity coefficient of burning rate is one of the very important performance indicators of solid propellants, which characterizes the influence of changes in the initial temperature of the propellant on the burning rate or the pressure of the combustion chamber. Under certain pressure conditions, the relative change in burning rate caused by a change in propellant temperature of 1K within a certain initial temperature range is expressed as: [0003] [0004] The development and progress of military technology has put forward higher requirements for the performance of missile weapons. The information revolution urgently needs to improve the long-distance precision ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06B33/06
Inventor 徐海元唐根周立罗传志倪凤翔冯勇吴芳包玺李伟徐星星王伟
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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