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Thermoplastic composite solid propellant and preparation method thereof

A solid propellant, thermoplastic technology, applied in the field of thermoplastic composite solid propellant, can solve hidden dangers, thermoplastic propellant safety and other problems, and achieve the effect of improving safety, improving intrinsic safety, and broad application prospects

Active Publication Date: 2018-04-03
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Traditional thermoplastic propellants are usually mixed at higher temperatures (>120°C), which poses a greater safety hazard in the preparation process of thermoplastic propellants. In order to improve the intrinsic safety of the production process of thermoplastic propellants, low-mixing Research on thermoplastic propellants at high temperature (<90°C) is particularly necessary

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] (1) Composition of thermoplastic composite solid propellant (mass percentage)

[0036] Binder (EVA420): 11.5%; Oxidizer (Ammonium Perchlorate): 55%; Oxidizer (Hexogen): 10%; Plasticizer (Dioctyl Sebacate): 10.5%; Metal Fuel (Aluminum Powder): 10%; Auxiliary (tris[1,-(2-methylaziridine)]phosphine oxide): 0.4%; Auxiliary (silane coupling agent): 0.5%; Auxiliary (N,N- Diphenyl-p-phenylenediamine): 0.6%; additive (carbon black): 0.4%; additive (ferric oxide): 1.1%.

[0037] The preparation process of the present invention includes: weighing the oxidizing agent, adhesive, plasticizer, metal fuel, and auxiliary agent according to the ratio; putting the adhesive into a vertical mixer to heat and melt, and the melting temperature is 84 ~ 88 ℃;

[0038] Put the rest of the weighed components into a vertical mixer and mix, the mixing temperature is 84~88°C, and the mixing time is 60~110min to make a slurry; the slurry is vacuum sprayed into the mold or poured into the engine, ...

Embodiment 2

[0042] (1) Composition of thermoplastic composite solid propellant (mass percentage)

[0043] Binder (EVA420): 10%; Oxidizer (Ammonium Perchlorate): 58%; Oxidizer (Ammonium Dinitramide): 4%; Plasticizer (Acetyl Triethyl Citrate): 10%; Metal Fuel (aluminum powder): 12%; metal fuel (magnesium powder): 3%; additive (alcohol amine complex): 0.5%; additive (aluminate coupling agent): 0.6%; additive (N, N-diphenyl-p-phenylenediamine): 0.5%; additive (carbon black): 0.5%; additive (catocin): 0.9%.

[0044] The preparation method is the same as in Example 1.

[0045] (2) Properties of thermoplastic composite solid propellants

[0046] Density: 1.62 g / cm 3 ; Combustion temperature: 2538.66°C; Characteristic velocity: 1523.06 m / s; Specific impulse: 2462.69 N*s / kg; Average molecular weight of gas: 24.71 g / mol; Melting point: 82~84°C; 0.56MPa; maximum elongation (25°C): 20.6%; elongation at break (25°C): 26.4%; pressure index (3MPa~9MPa): 0.41.

Embodiment 3

[0048] (1) Composition of thermoplastic composite solid propellant (mass percentage)

[0049] Binder (EVA420): 12%; Oxidizer (Ammonium Perchlorate): 57%; Oxidizer (Octogen): 4%; Plasticizer (Mineral Oil): 10.5%; Metal Fuel (Aluminum Powder): 11%; metal fuel (boron powder): 2%; additive (tris[1,-(2-methylaziridine)]phosphine oxide): 0.5%; additive (aluminate coupling agent): 0.8 %; Auxiliary (N,N-diphenyl-p-phenylenediamine): 0.8%; Auxiliary (carbon black): 0.6%; Auxiliary (ferric oxide): 0.5%; Auxiliary (catocin) : 0.3%.

[0050] The preparation method is the same as in Example 1.

[0051] (2) Properties of thermoplastic composite solid propellants

[0052] Density: 1.57 g / cm 3 ; Combustion temperature: 2041.85°C; Characteristic velocity: 1465.75 m / s; Specific impulse: 2368.85 N*s / kg; Average molecular weight of gas: 23.27 g / mol; Melting point: 80~83°C; 0.61MPa; maximum elongation (25°C): 21.2%; elongation at break (25°C): 28.3%; pressure index (3MPa~9MPa): 0.38.

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Abstract

The invention provides a thermoplastic composite solid propellant applicable to a solid booster. The thermoplastic composite solid propellant is prepared from components in percentage by mass as follows: 55%-70% of an oxidant, 10%-20% of a thermoplastic resin adhesive, 10%-20% of a plasticizer, 5%-20% of metal fuel and 3%-8% of auxiliaries. According to the prepared thermoplastic composite solid propellant, relative independence of mixing and pouring, integrated formation of the propellant and secondary formation of engine charge can be realized according to temperature adjustment, and melt mixing and formation of the thermoplastic propellant can be realized at relatively low temperature lower than 90 DEG C, so that inherent safety of preparation of the thermoplastic propellant is greatlyimproved; compared with a traditional thermosetting propellant, crosslinking curing process is omitted, technological process is shortened, recovery and repeated processing of waste products can be realized, and production cost is reduced. The thermoplastic propellant is prepared with a hot melt mixing-cooling formation technology, and application of components absorbing moisture easily in the propellant is realized.

Description

technical field [0001] The invention relates to a thermoplastic composite solid propellant suitable for a solid booster, belonging to the field of composite solid propellants. Background technique [0002] At present, the composite solid propellants widely used in China are thermosetting propellants. Although this type of propellant has high energy and mature production technology, the waste products and expired products are usually incinerated, which has caused great damage. waste, but also push up the production cost of propellant. The thermoplastic propellant with thermoplastic resin as the binder does not need to be cured, and there is no limitation on the "pot life" of casting, which can greatly shorten the process flow. The thermoplastic propellant has the property of repeatable processing, which can realize the continuous production of propellant And zero scrap rate, thereby improving the production efficiency of propellant and reducing the cost of propellant product...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B23/00C06B29/22C06B31/28C06D5/06
CPCC06B23/001C06B29/22C06B31/28C06D5/06
Inventor 刘轩鲁国林乔应克李志勇
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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