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A kind of platform combustion high burning rate propellant and preparation method thereof

A technology of propellant and combustion regulator, which is applied in the field of high burning rate propellant and its preparation, can solve unreported problems and achieve the effects of improving mechanical properties, reducing pressure index, and improving mechanical properties

Active Publication Date: 2022-04-08
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] But there is no report on high burning rate (greater than 20mm / s) platform propellant

Method used

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  • A kind of platform combustion high burning rate propellant and preparation method thereof
  • A kind of platform combustion high burning rate propellant and preparation method thereof
  • A kind of platform combustion high burning rate propellant and preparation method thereof

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preparation example Construction

[0066] The present invention also provides a method for preparing a platform-burning high-burning-velocity propellant, comprising the steps of:

[0067] 1) In a dry environment, weigh the raw materials according to the composition and mass percentage of the propellant;

[0068] 2) adding the bonding agent, the combustion regulator and the performance regulator to the adhesive and mixing evenly, then adding the plasticizer for manual premixing and mixing to obtain a premixed syrup;

[0069] 3) Add the premixed slurry into the mixer, add fuel and auxiliary fuel, and mix well;

[0070] 4) adding the oxidant to the mixer in batches for mixing;

[0071] 5) After the slurry is mixed evenly, add a curing agent and continue mixing to obtain a propellant slurry;

[0072] 6) Vacuum pour the propellant slurry into the mold or engine, and place it in a dry environment at about 70°C to cure for 7 days to obtain the finished propellant.

[0073] Wherein, the component and mass percent of...

Embodiment 1

[0084] (1) Composition of high burning rate propellant

[0085]

[0086] (2) High burning rate propellant performance

[0087]

[0088]

Embodiment 2

[0090] (1) Composition of high burning rate propellant

[0091]

[0092] (2) High burning rate propellant performance

[0093]

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Abstract

The invention relates to a high burning rate propellant for platform combustion, which comprises the following components in mass percentage: binder system: 10-15%; fuel: 14-18%; auxiliary fuel: 2-5%; oxidizer: 65% ~70%; combustion regulator: 0.5~3%; performance regulator: 0.5~2%; wherein, the combustion regulator includes the main combustion regulator, and the main combustion regulator is iron polyacrylate. The invention also provides a platform Process for the preparation of combusted high burning rate propellants. The high burning rate propellant of the invention has the effects of low pressure index, high theoretical specific impulse and excellent mechanical properties.

Description

technical field [0001] The invention relates to the field of solid rocket motors, in particular to a high burning rate propellant for platform combustion and a preparation method thereof. Background technique [0002] The burning rate pressure index of solid propellant is an important symbol to characterize the combustion stability of solid propellant. General strategic and tactical solid rocket motors require solid propellant to have a low pressure index, which can reduce the pressure of propellant in the combustion process. The dependence on the pressure in the engine can improve the reliability of the engine. Within a certain pressure range of the engine combustion chamber, the propellant with a pressure index as low as 0-0.2 is called a platform propellant. In the 1970s and 1980s, Western countries use a large number of double-base platform propellants for tactical missiles. The US "TOW" heavy-duty anti-tank missile speed-up engine charge uses a high-pressure platform do...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06B33/12C06B33/06C06B23/00C06B21/00C06D5/06
CPCC06B33/12C06B33/06C06B23/007C06B23/009C06B21/0058C06D5/06
Inventor 庞爱民肖金武代志龙张运刚杨伯涵张先瑞陈涛黄凌李建华王园园刘建红王锐
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY