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A kind of electric control solid propellant and preparation method thereof

A solid propellant and electronic control technology, which is applied in the direction of offensive equipment, compressed gas generation, non-explosive/non-thermal agent components, etc., can solve the impact of propellant measured density and mechanical properties, reduce effectiveness and multiple ignition and flameout , affecting the uniformity of the propellant, etc., to save preparation time, improve uniformity and fluidity, and prevent gel clusters

Active Publication Date: 2022-03-04
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In 2005, DSSP Corporation of the United States announced a kind of electronically controlled solid propellant, which is similar to conventional solid propellants, including components such as binders, oxidants and functional additives, but this type of electronically controlled solid propellant burns Will soften or melt, thereby reducing its effectiveness and ability to fire and extinguish multiple times
[0006] There are a large number of gel groups and air bubbles in the slurry obtained from the existing formula, so there are many pores in the final powder column, which seriously affects the uniformity of the propellant, resulting in a greater impact on the measured density and mechanical properties of the propellant. Among them, the measured density is 1.46g / cm 3 About, far lower than the theoretical calculation, the tensile strength at room temperature is less than 1MPa, and the test results fluctuate greatly and the repeatability is poor

Method used

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  • A kind of electric control solid propellant and preparation method thereof
  • A kind of electric control solid propellant and preparation method thereof
  • A kind of electric control solid propellant and preparation method thereof

Examples

Experimental program
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preparation example Construction

[0058] The embodiment of the present invention also provides a method for preparing an electrically controlled solid propellant, comprising the following steps:

[0059] Step 1): Weigh the raw materials according to the formula provided in the above-mentioned raw material formula embodiment;

[0060] For the description and effect of the raw materials, please refer to the above-mentioned formula examples, and will not repeat them here; among them, it is preferable to prepare the mass Hydroxylamine nitrate aqueous solution with a concentration of 5-10%;

[0061] Step 2): adding the weighed binder, secondary oxidizing agent, crosslinking agent and functional auxiliary agent into the aqueous solution of hydroxylamine nitrate to completely dissolve to obtain a uniform slurry;

[0062] Step 3): Concentrating and dewatering the syrup obtained in step 2);

[0063] Step 4): Pour the concentrated syrup into a mold, freeze and solidify to obtain an electronically controlled solid prop...

example 1

[0069] Take the raw material by weighing the formula in Table 1;

[0070] The weighed binder polyvinyl alcohol, secondary oxidant ammonium nitrate, crosslinking agent nano silicon dioxide, buffer stabilizer ammonium dihydrogen phosphate, chelating stabilizer 2,2-bipyridine, fuel additive cyclodextrin, heat The stabilizer pentaaminotetrazole was added to the HAN aqueous solution with a mass concentration of 5%, heated to 80°C, and stirred until it was completely dissolved; the heating device was turned off, and the solution was cooled to 50°C, then concentrated and dewatered by vacuum stirring until The water content in the receiving bottle accounts for 94% of the total mass of the HAN aqueous solution, and the air bubbles in the slurry are removed by using a vacuum environment. Pour the concentrated slurry into a mold, freeze at -40°C for 24 hours, thaw at room temperature, and cycle 3 times to prepare an electronically controlled solid propellant with good uniformity.

[007...

example 2

[0075] Take by weighing raw material according to table 2 formula;

[0076] The weighed binder polyvinyl alcohol, secondary oxidant sodium nitrate, crosslinking agent tetraethyl orthosilicate, buffer stabilizer ammonium dihydrogen phosphate, chelating stabilizer edetate disodium, heat stabilizer five Add aminotetrazole together to 5% HAN aqueous solution, heat to 80°C, stir until completely dissolved; turn off the heating device, wait for the solution temperature to cool to 60°C, and vacuum stir to concentrate and remove water until it reaches the receiving bottle The water content accounts for 94% of the total mass of the HAN aqueous solution, and the air bubbles in the slurry are removed by using a vacuum environment. Pour the concentrated slurry into a mold, freeze at -30°C for 15 hours, thaw at room temperature, and cycle 4 times to prepare an electronically controlled solid propellant with good uniformity.

[0077] Table 2 Example 2 raw material formula table

[0078] ...

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Abstract

The invention relates to an electronically controlled solid propellant and a preparation method thereof, belonging to the field of solid propellants. The electronically controlled solid propellant includes the following raw materials in mass percent: 10% to 14% of a hydroxyl-containing binder, 80% to 85% of a main oxidant, 1% to 4% of a secondary oxidant, and 0.5% to 0.5% of a crosslinking agent 2%, functional additive 1% to 2.5%; wherein, the main oxidant is an aqueous solution of hydroxylamine nitrate with a mass concentration of 5% to 10%, and the crosslinking agent is one of a silicon-containing compound or an organic titanium chelate or a combination. The invention can avoid a lot of gel groups and air bubbles in the slurry, and significantly improve the uniformity of the electronically controlled solid propellant.

Description

technical field [0001] The invention belongs to the technical field of solid propellants, and relates to an electrically controlled solid propellant and a preparation method thereof. Background technique [0002] Solid rocket motors have the advantages of simple structure, fast response, and convenient use and maintenance. Therefore, they are widely used in strategic and tactical missile weapons. However, once the solid propellant is started, it cannot be extinguished, so that the solid rocket motor cannot be started multiple times, and it does not have flexible energy management capabilities, which seriously restricts the wide application of solid propulsion technology. The liquid rocket engine has the characteristics of multiple starts and precise thrust adjustment, but the structure of the liquid engine is complex, and most of the liquid propellant components are highly toxic, flammable, explosive, volatile and corrosive, and the storage period is limited. In the use env...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06D5/06C06B23/00C06B31/02C06B31/28C06B45/10
Inventor 黄印张小平庞爱民李洪旭王拯程红波王艳萍
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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