Propellant with high energy and low temperature sensitive coefficient of burning
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A technology of temperature sensitivity coefficient and propellant, which is applied to explosives and other directions to achieve the effect of increasing the range
Active Publication Date: 2015-12-09
HUBEI INST OF AEROSPACE CHEMOTECH
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Although the high-energy propellant currently developed has a high energy level, the temperature sensitivity coefficient of the
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[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 temperature sensitive coefficient of burning comprises 12-15% of an adhesive, 10-13% of a plasticizer, 15-18% of an oxidant, 38-50% of an energetic explosive, 10-18% of a metal fuel and 1.5-2.0% of a small group, wherein the adhesive is glycidyl azide polymer; the plasticizer is triethylene glycol dinitrate or 2,4-dinitro-2,4-diazaalkane; the oxidant is ammonium perchlorate; the energetic explosive is octogen; and the metal fuel is aluminum powder. The propellant has the characteristics of high energy (standard measured specific impulse is greater than 2450N.s/kg) and low temperature sensitive coefficient of burning (not greater than 0.15%K<-1>), and is suitable for tactical missile engines with far required range, strong penetration ability, high reliability and accurate 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 ...
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