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Solid propellant containing core-shell modified oxidant and preparation method of solid propellant

A solid propellant and oxidant technology, which is used in offensive equipment, explosives processing equipment, and compressed gas generation to achieve the effects of high thermal conductivity, optimized stacking state, and improved process performance and safety performance.

Active Publication Date: 2020-04-10
SHANGHAI AEROSPACE CHEM ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the problem of high sensitivity has become the main restrictive factor for the application of high burning rate solid propellants. How to balance the relationship between propellant burning rate and sensitivity, or to reduce the sensitivity while maintaining the burning rate is an urgent problem to be solved.

Method used

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  • Solid propellant containing core-shell modified oxidant and preparation method of solid propellant
  • Solid propellant containing core-shell modified oxidant and preparation method of solid propellant
  • Solid propellant containing core-shell modified oxidant and preparation method of solid propellant

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preparation example Construction

[0040] The preparation method of described core-shell modified oxidant comprises the following steps:

[0041] 1) Add deionized water to potassium perchlorate, stir fully under heating conditions for 1 to 3 hours, then add dispersant and reducing agent in turn, and stir to form a potassium perchlorate suspension;

[0042] 2) Under stirring conditions, add ammonia water dropwise to the silver nitrate aqueous solution until the precipitate that is produced at the beginning just dissolves to obtain a solution;

[0043] 3) under stirring condition, the solution that step (2) is obtained is added dropwise in the potassium perchlorate suspension of step (1), and continues to stir until unreacted silver ion is not detected in the solution;

[0044] 4) filtering out the solid components in the solution in step (3), repeatedly washing with an organic solvent, and drying to obtain the finished product of the modified oxidant.

[0045] The amount of deionized water added in step (1) is ...

Embodiment 1

[0073] A solid propellant comprising a core-shell modified oxidant, the main composition of which (by mass percentage) is as follows: core-shell modified oxidant KP, 32%; conventional oxidizer AP, 36%; binder HTPB, 6.8%; Metal fuel Al, 18%; burning rate catalyst GFP, 2.5%; plasticizer DOS, 4%; curing agent TDI, 0.5%; function regulator is graphene, 0.2%.

[0074] A solid propellant comprising a core-shell modified oxidizer, the preparation method of which is as follows:

[0075] (1) Using potassium perchlorate with a size of about 300 μm, after surface silverization treatment, a core-shell modified oxidant KP with a silver metal core-shell thickness of about 1 μm is obtained, and the particle size D is selected by sieving 50 About 300μm products;

[0076] (2) According to the formula ratio, the formula raw materials are weighed respectively;

[0077] (3) First add HTPB, GFP, and DOS components into the premix container in sequence, and stir evenly by hand; then add graphene,...

Embodiment 2

[0083] A solid propellant comprising a core-shell modified oxidant, the formula of which is mainly composed (calculated by mass percentage) is as follows: core-shell modified oxidant KP, 51%; conventional oxidant AP, 17%; binder HTPB, 6.8%; Metal fuel Al, 18%; burning rate catalyst GFP, 2.5%; plasticizer DOS, 4%; curing agent TDI, 0.5%; function regulator is graphene, 0.2%.

[0084] A solid propellant comprising a core-shell modified oxidizer, the preparation method of which is as follows:

[0085] (1) Using potassium perchlorate with a size of about 300 μm, after surface silverization treatment, a core-shell modified oxidant KP with a silver metal core-shell thickness of about 1 μm is obtained, and the particle size D is selected by sieving 50 About 300μm products;

[0086] (2) According to the formula ratio, the formula raw materials are weighed respectively;

[0087] (3) First add the weighed HTPB, GFP, and DOS components into the premix container in turn, and stir evenly...

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Abstract

The invention belongs to the field of solid propellants, and particularly relates to a solid propellant containing a core-shell modified oxidant and a preparation method of the solid propellant. The solid propellant comprises the following components in parts by weight: 20-55% of the core-shell modified oxidant, 15%-55% of a conventional oxidant, 5%-9% of an adhesive, 14%-20% of a metal fuel, 2.5%-12% of a plasticizer, 0.5%-3% of a combustion rate catalyst, 0.4%-1% of a curing agent, and 0%-2% of a function regulator. Compared with a propellant prepared from ammonium perchlorate under the samecondition, the propellant prepared by the invention has higher propellant combustion rate and volume heat value and better safety performance, and is particularly suitable for advanced tactical and strategic weapon type charging with higher requirements on the combustion rate, energy and safety performance of the propellant.

Description

technical field [0001] The invention relates to the technical field of solid rocket motor propellants, in particular to a solid propellant containing a core-shell modified oxidizer and a preparation method thereof. Background technique [0002] With the development of combat readiness technology, missiles and aerospace technology, some special weapons have put forward more stringent requirements on the performance of solid propellants, and it is constantly hoped to generate large thrust in a short time to meet the requirements of combating high-speed and high-mobility aircraft. Ballistic performance requirements, at the same time, it is also necessary to ensure that its own personnel and property are not harmed. Therefore, there is an urgent need for high burning rate propellants with excellent safety performance. [0003] However, as a kind of energetic material, solid propellant generally has conflicts and constraints between its burning rate and safety performance. The ...

Claims

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Application Information

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IPC IPC(8): C06B33/12C06B21/00C06D5/06
CPCC06B21/0058C06B33/12C06D5/06
Inventor 卢国强陈淑秉王惠时志权沈伟民陈树芳翟峰沈肖胤
Owner SHANGHAI AEROSPACE CHEM ENG INST
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