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Composite solid propellant based on aluminum powder coated with nitramine oxidant and preparation method

A solid propellant and oxidant technology, applied in offensive equipment, explosive processing equipment, compressed gas generation, etc., can solve the problems of reducing propellant combustion efficiency, intensifying the erosion and ablation of the insulation layer, and engine two-phase flow loss, etc. Achieve the effects of inhibiting adverse effects, reducing content, and increasing energy levels

Pending Publication Date: 2020-03-17
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, some aluminum powder will agglomerate on the propellant burning surface and form large-sized agglomerates, which will bring two-phase flow loss to the engine, reduce the propellant combustion efficiency, and aggravate the erosion and ablation of the thermal insulation layer (Ao Wen, Liu Peijin, Lu Xiang, et al. Research progress on aluminum agglomeration during solid propellant combustion[J]. Acta Astronautics Sinica, 2016,37(4):371-380.)

Method used

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  • Composite solid propellant based on aluminum powder coated with nitramine oxidant and preparation method
  • Composite solid propellant based on aluminum powder coated with nitramine oxidant and preparation method
  • Composite solid propellant based on aluminum powder coated with nitramine oxidant and preparation method

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preparation example Construction

[0030] The preparation process of the embodiment can be divided into the following three steps:

[0031] (1) Preparation of polydopamine surface-modified aluminum powder: Add 0.36g dopamine and 0.2g TRIS buffer solution (PH=8.5) into 200ml of distilled water, stir for 10min to partially polymerize dopamine molecules, and then add 3.6g of μ -Al (1-2 μm) and stirred for 1 h to make polydopamine grow in situ on the surface of aluminum powder to form a polydopamine layer, and dry the solution to obtain aluminum powder μ-Al@PDA whose surface is uniformly coated with polydopamine; it should be noted that , the content of PDA in μ-Al@PDA is less than 0.5wt%, so its mass is negligible for the entire propellant formulation, and the mass ratio of Al and RDX in the microspheres can be considered to be 1:1;

[0032] (2) Preparation of aluminum powder microspheres coated with nitramine oxidant: Dissolve 5.0 g of RDX in 25 ml of dimethyl sulfoxide (DMSO) solution, then add the same mass of ...

Embodiment 1

[0035] Example 1: A composite solid propellant without a burning rate catalyst. Wherein binder adopts hydroxyl-terminated polybutadiene (HTPB), and content is 12wt%; Plasticizer adopts diisooctyl sebacate (DOS), and content is 2wt%; Curing agent adopts isophorone diisocyanate ( IPDI), content is 1wt%; μ-Al content is 18wt%; RDX content is 18wt%; Ammonium perchlorate (AP) content is 49wt%; The theoretical specific impulse of this formula is 2567m s -1 . Concrete propellant preparation method is as follows:

[0036] 1) Raw material treatment: put the solid material in an oven at 60°C and dry for 96-120 hours;

[0037] 2) Weighing and mixing: weigh 100g of each component according to the formula, and stir for 120min in a water bath at 40-50°C to make a composite propellant slurry;

[0038] 3) Vacuum pouring: Vacuum pour the propellant slurry into the customized mold, and the vacuum pouring time is not less than 2 hours;

[0039] 4) Curing pharmaceutical strips: heating and cu...

Embodiment 2

[0041] Embodiment 2: Others are the same as in Embodiment 1, and all μ-Al is replaced by dopamine-surface-modified aluminum powder μ-Al@PDA of the same quality;

[0042] From image 3 It can be seen that the AP, RDX and μ-Al@PDA particles in Example 2 are also randomly distributed in the binder system, and there is no interfacial contact between the components; the apparent density of Example 2 is 1.69 g cm -3 , the heat of reaction is 5.42kJ·g -1 , with an energy density of 9.15kJ cm -3 (Table 2). The pressure index of embodiment 2 is 0.236, has increased 51% (table 3) compared with embodiment 1; From Figure 5 It can be seen that the particle size distribution of the condensed phase combustion products also presents a trimodal distribution, and the particle size of the largest aggregate is ~70.9 μm.

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Abstract

The invention relates to a composite solid propellant based on aluminum powder coated with a nitramine oxidant and a preparation method. Dopamine surface-modified aluminum powder (Al@PDA) is coated with a nitramine oxidant (such as cyclotrimethylenetrinitramine, RDX) through a spraying drying technology to form compact core-shell-structured microspheres (Al@PDA@RDX) so as to replace RDX and Al intraditional propellant. Composite microspheres adopting interface interactions between the metal aluminum powder and the nitramine oxidant are adopted so that the oxidant and the aluminum powder in the propellant are in close contact, and can rapidly react when the propellant is combusted, and adverse influences of oxidant decomposition product diffusion and agglomeration of aluminum powder on propellant combustion can be suppressed. The preparation is simple and convenient, a spray granulation process, and industrialized production is liable to achieve. The composite solid propellant is simple in preparation method, and contents of components in a formula can be accurately controlled.

Description

technical field [0001] The invention belongs to the technical field of composite solid propellant manufacture, and relates to a composite solid propellant based on nitramine oxidant-coated aluminum powder and a preparation method. Background technique [0002] Composite solid propellant is a composite energetic material that can rapidly release energy and generate thrust through combustion, and generally consists of a binder system, metal fuel, oxidizer, catalyst and process additives. Regulating the combustion performance of composite propellants is a necessary way to realize its engineering application. Catalysts are usually used to increase the burning rate of composite propellants, reduce their pressure index, and improve combustion efficiency (Yan Qilong. On the evaluation criteria of solid propellant combustion catalysts [J]. Energetic Materials, 2019, 27(4): 266-269.). Traditional catalysts include ammonium salts and organic amines, transition metal oxides, transitio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B33/14C06B33/12C06B33/08C06B45/32C06B45/34C06B21/00C06D5/06
CPCC06B33/14C06B33/12C06B33/08C06B45/32C06B45/34C06B21/0058C06B21/0025C06D5/06
Inventor 严启龙吕杰尧齐晓飞何伟刘佩进何国强
Owner NORTHWESTERN POLYTECHNICAL UNIV
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