Low-temperature solid propellant

A solid propellant and low-temperature technology, applied to explosives and other fields, to achieve the effects of easy availability of raw material resources, cost savings, and high efficiency

Active Publication Date: 2017-12-01
HARBIN ENG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the combustion efficiency and specific impulse of the existing low-temperature solid propellants still need to be improved.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] The mass ratio of each component is: metal magnesium powder (Mg): 45.1%; magnesium dihydride (MgH 2 ): 11.3%; deionized water: 41.6%; functional additives: 2%.

[0023] The magnesium powder is a composite magnesium powder composed of ultra-fine magnesium powder and conventional magnesium powder. The particle size of the ultra-fine magnesium powder is 100 nm-1 μm; the particle size of the conventional magnesium powder is 1 μm-100 μm. In the composite magnesium powder, the ultrafine magnesium powder accounts for 60% of the mass of the composite magnesium powder, and the rest is conventional magnesium powder. The purity of the ultrafine magnesium powder is greater than 99%.

[0024] The particle size of the magnesium dihydride is 1 μm-100 μm.

[0025] The functional aid is a combination of stabilizer, process aid and combustion aid. The stabilizer is MNA (N-methyl-p-nitroaniline) with a content of 0.5%; the process aid is sodium dodecyl sulfonate with a content of 1%; t...

Embodiment 2

[0031] Table 2 below provides 2#Mg / MgH of the present invention 2 / H 2 Formulation components and properties of low-temperature solid propellants

[0032] Table 2 Mg / MgH 2 / H 2 O

[0033]

[0034] It can be seen from Table 2 that when Mg / MgH 2 / H 2 MgH in low temperature solid propellants 2 When the mass fraction increased to 15.4%, the density of the propellant was 1.59 g / cm lower than that of Example 1. 3 , the specific impulse increased to 3147m / s, and the flame temperature decreased to 2590K.

Embodiment 3

[0036] Table 3 below provides 3#Mg / MgH of the present invention 2 / H 2 Formulation components and properties of low-temperature solid propellants

[0037] Table 3 Mg / MgH 2 / H 2 O

[0038]

[0039] It can be seen from Table 3 that when Mg / MgH 2 / H 2 MgH in low temperature solid propellants 2 When the mass fraction increased to 18.9%, the propellant density was further reduced to 1.51g / cm 3 , the specific impulse increases to 3258m / s, and the flame temperature drops to 2420K.

[0040] It can be seen from the above examples that the present invention greatly improves the specific impulse of the propellant and other properties of the propellant.

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Abstract

The invention provides a low-temperature solid propellant comprising fuel, an oxidant, a binding agent and a functional adjuvant; the fuel is metal fuel magnesium powder and magnesium hydride; the oxidant and the binding agent are water; and all the components are in the mass ratio: 38%-46% of metal magnesium powder, 11%-19% of magnesium hydride, 40%-44% of water and 2% of functional adjuvant. According to the low-temperature solid propellant, magnesium hydride is used as a fuel additive, so that the hydrogen content of the fuel is increased, meanwhile, the flame temperature of the propellant is lowered, and the specific impulse of the propellant is increased; water is used as the oxidant and is also used as the binding agent of the propellant, the melting point of water is 0 DEG C, and when the temperature is lower than 0 DEG C, propellant slurry is frozen and solidified to be prepared into the low-temperature solid propellant; compared with other oxidants, water can be used for effectively increasing the temperature for freezing the low-temperature propellant; and meanwhile, due to the adoption of a low-temperature environment, the reaction of the fuel and the oxidant is inhibited, and the service life of the propellant is prolonged.

Description

technical field [0001] The present invention relates to a solid propellant, specifically a low-temperature solid propellant. Background technique [0002] Low-temperature solid propulsion technology is a new type of chemical rocket propulsion technology. The propellant used in low-temperature solid propulsion technology is low-temperature solid propellant. The energy level of traditional solid propellants has reached a plateau, and the standard theoretical specific impulse of high-energy solid propellant NEPE reaches 2646m / s, which is still far lower than that of liquid propellants. Concept is presented. [0003] Low-temperature solid propellant is a green high-energy solid propellant at low temperature. Its main feature is that at least one of the fuel and oxidant of the propellant is in a gaseous or liquid state at normal temperature, and is frozen into a solid at low temperature for manufacturing and storage. and launch. The propellant can be a homogeneous single-compo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B27/00
CPCC06B27/00
Inventor 刘平安常浩王文超许一楠刘俊鹏吕方伟丁涛
Owner HARBIN ENG UNIV
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