Solid propellant and horizontal additive manufacturing method thereof

A solid propellant and propellant technology, applied in the direction of additive processing, offensive equipment, compressed gas generation, etc., can solve the problems of plastic deformation and curing time, achieve the effect of reducing curing temperature, shortening curing time, and speeding up prototype manufacturing

Inactive Publication Date: 2020-06-26
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem to be solved by the present invention is to overcome the defects that the solid propellant in the prior art is prone to plastic deformation and the curing time is long during the heating and curing molding process, and provides a solid propellant and its horizontal additive manufacturing method

Method used

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  • Solid propellant and horizontal additive manufacturing method thereof
  • Solid propellant and horizontal additive manufacturing method thereof
  • Solid propellant and horizontal additive manufacturing method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0037] The solid propellant of the present embodiment includes: metal additives, binders, oxidizing agents, plasticizers and curing agents, and also includes: neutral bonding agents, burning rate catalysts and curing catalysts. Wherein said curing agent is isocyanate. The curing agent includes: at least one of toluene diisocyanate and isophorone diisocyanate.

[0038] The solid propellant of this embodiment is a ternary hydroxybutyl propellant, and the mass percentages of each component in the ternary hydroxybutyl propellant are: ammonium perchlorate 69.5%, aluminum powder 18.5%, hydroxyl-terminated polybutylene 8.4% of diene, 3.5% of diisooctyl sebacate, 0.058% of toluene diisocyanate, 0.02% of isophthaloyl, 0.020% of iron oxide, and 0.002% of triphenylbismuth.

[0039] Wherein, ammonium perchlorate is used as an oxidizing agent, and its percentage that accounts for the mass of raw material is between 47%~70%;

[0040] Aluminum powder is used as a metal additive, and its ma...

Embodiment 2

[0050] The solid propellant of this embodiment is a quaternary butylated hydroxy propellant, and the mass percentages of the components of the quaternary butylated hydroxy propellant are: ammonium perchlorate 47%, aluminum powder 18%, octogold 25%, hydroxyl-terminated polybutadiene 7%, diisooctyl sebacate 2.83%, toluene diisocyanate 0.048%, isophthaloyl 0.1%, iron oxide 0.02%, triphenylbismuth 0.002%.

[0051] In the above-mentioned quaternary hydroxybutyl propellant, the particle size gradation of ammonium perchlorate is as follows: the particle size is 250 μm, the content is 30%, the particle size is 120 μm, the content is 20%, the particle size is 20 μm, the content is 30%, The content of the particle size is 1 μm is 20%; the particle size gradation of the aluminum powder is: the content of the particle size of 165 μm is 50%, the content of the particle size of 30 μm is 20%, and the content of the particle size of 20 μm is 30%.

Embodiment 3

[0053] This embodiment provides a horizontal additive manufacturing method for a solid propellant, comprising the following steps:

[0054] Step 1: premixing the raw materials of the solid propellant into at least two groups, so that the metal additive and the oxidant are processed separately;

[0055] In the group where the metal additive is located, the adhesive is premixed with the metal additive to form a main ingredient;

[0056] In the group where the oxidizing agent is located, the oxidizing agent is pre-mixed with a curing agent to form a slurry;

[0057] The main material and the slurry are mixed into a propellant material in a mixer.

[0058] Step 2: Transport the propellant raw material to the channel of the propellant printing nozzle 1; and adjust the output flow rate of the propellant printing nozzle 1 as required; the propellant printing nozzle 1 has a plurality of concentric channels with different diameters, which can According to the required printing size a...

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Abstract

The invention provides a solid propellant and a horizontal additive manufacturing method thereof, and belongs to the technical field of preparation of solid propellants. The solid propellant comprisesthe following components in percentage by mass: 18-19% of a metal additive, 5-8% of an adhesive, 1-2% of an oxidant, 1-2% of a plasticizer and the balance of a curing agent. The mass percent of the adhesive is 7%-9%; wherein the mass percent of the oxidizing agent is 47%-70%; wherein the mass percent of the plasticizer is 3.0%-4.0%; and the mass percent of the curing agent is 0.05%-0.06%. Whereinthe curing agent is isocyanate. After the solid propellant is heated to a certain temperature, a chemical reaction is generated, the solid propellant is cured in a cross-linking manner and becomes hard, the change is irreversible, and the solid propellant cannot become soft and flow after being heated again, so that the phenomenon of plastic deformation cannot occur in the heating curing process.

Description

technical field [0001] The invention relates to the technical field of preparation of solid propellants, in particular to a solid propellant and a horizontal additive manufacturing method thereof. Background technique [0002] Solid propellants are composed of curing agents, metal additives, oxidants, energetic materials and other components. In the traditional solid propellant preparation process, the components of the solid propellant need to be uniformly mixed to form a slurry, and then the slurry is transported to a molding device for solidification and molding; among them, in order to prevent explosions caused by friction with oxidizers, metal Additives are coated with binders during mixing. The traditional propellant wall-mounted casting process requires a combined mandrel, poor mechanical properties of the grain, large shrinkage and deformation after curing, low molding precision of the grain, complex process, long cycle, and high cost. Contents of the invention ...

Claims

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Application Information

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IPC IPC(8): C06D5/06C06B33/12C06B33/02C06B21/00B33Y10/00B33Y30/00B33Y40/00B33Y70/10
CPCB33Y10/00B33Y30/00B33Y40/00B33Y70/00C06B21/0033C06B21/005C06B33/02C06B33/12C06D5/06
Inventor 彭小波李志洪施发树
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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