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Catalyst for accelerating burning rate used for reducing pressure exponent of nitramine propellant

A technology of propellant and burning rate, applied in physical/chemical process catalysts, nitrated acyclic/alicyclic/heterocyclic amine explosive compositions, chemical instruments and methods, etc., can solve the unsatisfactory combustion performance of NEPE propellants and other problems, to achieve the effect of good compatibility, easy availability of raw materials and easy industrialization

Inactive Publication Date: 2013-07-24
ZHONGBEI UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the toxicity of lead and copper salts and the unsatisfactory combustion performance of NEPE propellants, it is still necessary to carry out research work on burning rate catalysts and propellant combustion performance.

Method used

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  • Catalyst for accelerating burning rate used for reducing pressure exponent of nitramine propellant
  • Catalyst for accelerating burning rate used for reducing pressure exponent of nitramine propellant
  • Catalyst for accelerating burning rate used for reducing pressure exponent of nitramine propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] According to the molar ratio of lanthanum nitrate: manganese chloride: stearic acid=1:1:7, weigh lanthanum nitrate, manganese chloride, and stearic acid. Under the condition of heating in an oil bath, first melt the stearic acid, and under constant temperature magnetic stirring, melt the lanthanum nitrate and manganese chloride solids into the molten stearic acid, and control the temperature at 112°C to form a uniform stearic acid complex Put it in a muffle furnace at 500-600°C and burn it to get the LaOCl-Mn composite oxide.

[0016] Make high-energy NEPE nitramine propellant according to the following ratio. Adopt PET / NG / TG type NEPE propellant formula (Al: 15%~18%, AP: 15~20%), the composition and content are as follows: PET / N-100 is the binder system, the content is 7%~8% ; NG / TEGDN is a plasticizer with a content of 18% to 20%; solid filler reserves of 72% to 75%. Among them, the relative molecular mass of PET is Mn=4280, hydroxyl value: 26.4mgKOH / g, chain segmen...

Embodiment 2

[0021] According to the molar ratio of lanthanum nitrate: manganese chloride: stearic acid=1:1:10, weigh lanthanum nitrate, manganese chloride, and stearic acid. Under the condition of heating in an oil bath, first melt the stearic acid, and under constant temperature magnetic stirring, melt the solid lanthanum nitrate and manganese chloride into the molten stearic acid, and control the temperature at 117°C to form a uniform stearic acid complex The product solution is placed in a muffle furnace at 500-600°C and burned to obtain the LaOCl-Mn composite oxide product.

[0022] The propellant preparation and combustion performance test methods are the same as in Example 1, and 1.0% of the obtained LaOCl-Mn composite oxide product is added to the NEPE propellant.

[0023] The experimental results show that the prepared LaOCl-Mn composite oxide is compatible with the NEPE propellant system, the catalyst has little effect on the curing reaction of the slurry, and the normal propella...

Embodiment 3

[0028] According to the molar ratio of lanthanum nitrate: manganese chloride: stearic acid=1:1:8, weigh lanthanum nitrate, manganese chloride, and stearic acid. Under the condition of heating in an oil bath, first melt the stearic acid, and under constant temperature magnetic stirring, melt the solid lanthanum nitrate and manganese chloride into the molten stearic acid, and control the temperature at 117°C to form a uniform stearic acid complex The product solution is placed in a muffle furnace at 500-600°C and burned to obtain the LaOCl-Mn composite oxide product.

[0029] Preparation of nitramine modified propellant: propellant formula without any catalyst: NC (nitrocellulose) plus NG (nitroglycerin) is 41.5%, RDX is 55.7%, functional additives and others are 2.8%, no catalyst; Catalyst formula: 41.3% of NG plus NC, 55.7% of RDX, 2.0% of functional additives and others, and 1.1% of catalyst. The experimental results obtained are shown in Table 2.

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Abstract

The invention relates to a method for preparing LaOCl-Mn composite oxide by using an eleaostearic acid solution combustion method, which comprises the following steps: 1) weighting lanthanum nitrate, manganese chloride and eleaostearic acid according to mol ratio of 1:1:x(x=7.0-10.0), under the oil bath heating condition, melting eleaostearic acid, performing magnetic stirring at constant temperature, melting lanthanum nitrate and manganese chloride solids in the melted eleaostearic acid, controlling the temperature at 110-118 DEG C to generate an uniform eleaostearic acid complex solution, placing in a muffle furnace at 500-600 DEG C, and then combusting to obtain the LaOCl-Mn composite oxide. The obtained LaOCl-Mn composite oxide can be directly used in the nitramine high energy propellant, thereby the pressure exponent of the propellant is reduced, and the combustion performance of the propellant is increased. The employed preparation technology has the advantages of rapidity, simpleness and convenience, the required raw materials are easily available and nontoxic, the preparation technology can realize industrialization easily.

Description

technical field [0001] The invention relates to the preparation of LaOCl-Mn composite oxide in nitramine solid propellant and its influence on the combustion performance of the propellant. Background technique [0002] The burning rate pressure index of solid propellants (referred to as pressure index) is an important technical parameter of solid rocket motors. Except for special controllable motors that require solid propellants to have a high pressure index, general strategic and tactical solid rocket motors, in order to ensure The stability of the ballistic performance and the reliability of the engine work require the solid propellant to have a low pressure index. Ammonium nitrate propellants (especially high-energy NEPE propellants, that is, nitrate-plasticized polyether propellants) are due to a large amount of cyclotetramethylenetetranitroamine (HMX) or hexogen (RDX, 1, 3, The introduction of 5-trinitro-1,3,5-triazacyclohexane, also known as cyclotrimethylene trinitr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B01J27/138C06B25/34
Inventor 卫芝贤王艳龚磊高原李延斌
Owner ZHONGBEI UNIV
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