Solid propellant containing bimetallic oxide combustion accelerator and preparation method of solid propellant

A bimetallic oxide and solid propellant technology, which is applied in offensive equipment, explosive processing equipment, compressed gas generation, etc., can solve the problems that solid propellants cannot meet high burning rate and high energy release, and achieve strong catalysis and high The effect of thermal decomposition of ammonium chlorate exothermic, high explosive heat, and simple preparation method

Active Publication Date: 2020-12-04
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problem that the existing solid propellant is difficult to meet high burning rate and high energy release, and provides a solid propellant containing a double metal oxide burning rate agent and a preparation method thereof

Method used

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  • Solid propellant containing bimetallic oxide combustion accelerator and preparation method of solid propellant

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specific Embodiment approach 1

[0025] Specific embodiment one: a kind of solid propellant comprising bimetallic oxide burning rate agent described in this embodiment, it is by mass parts by 1~5 parts of bimetallic oxide burning rate agent, 60~80 parts Composed of oxidizing agent, 15-20 parts of metal fuel, 8-12 parts of binder, 0.5-3 parts of curing agent and 1-5 parts of plasticizer;

[0026] Described double metal oxide burning rate agent is CuZnO, CuCo 2 o 4 、CuFe 2 o 4 or CuNiO.

[0027] The CuZnO described in this embodiment is composed of CuO / ZnO composite, CuO and ZnO; the CuCo 2 o 4 by CuO / Co 3 o 4 Composite, CuO and Co 3 o 4 Composition; the CuFe 2 o 4 by CuO / Fe 3 o 4 Composite, CuO and Fe 3 o 4 Composition; the CuNiO is composed of CuO / NiO composite, CuO and NiO.

[0028] Due to the violent thermite reaction between metal oxides and aluminum powder, and the ability to effectively catalyze the decomposition reaction of ammonium perchlorate, it can significantly improve the combustio...

specific Embodiment approach 2

[0032] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the described double metal oxide burning rate agent is prepared according to the following steps:

[0033] Dissolve copper nitrate trihydrate and metal salts in deionized water to obtain a mixed solution, and add NaOH and NaHCO dropwise to the mixed solution 3 aqueous solution until the pH of the mixed solution is 10-12, then stir for 4h-8h at a stirring speed of 300rpm-500rpm, and finally centrifuge, wash, filter and dry to obtain a dried solid; place the dried solid in In a muffle furnace at a temperature of 500°C to 800°C, calcining for 2h to 6h to obtain a double metal oxide burning rate agent;

[0034] The mol ratio of the copper ion in the copper nitrate trihydrate and the metal ion in the metal salt is 1: (0.2~5); Described NaOH and NaHCO 3 The concentration of NaOH in the aqueous solution is 0.02mmol / mL~0.05mmol / mL; the NaOH and NaHCO 3 NaHCO in aqueous solution 3 ...

specific Embodiment approach 3

[0035] Embodiment 3: This embodiment differs from Embodiment 1 or Embodiment 2 in that the metal salt is zinc nitrate hexahydrate, nickel acetate tetrahydrate, iron nitrate nonahydrate or cobalt nitrate hexahydrate. Others are the same as in the first or second embodiment.

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Abstract

The invention relates to a solid propellant and a preparation method thereof, in particular to a solid propellant containing a bimetallic oxide combustion accelerator and a preparation method of the solid propellant. The invention aims to solve the problem that an existing solid propellant difficultly meets the requirements of high combustion speed and high energy release. The solid propellant containing a bimetallic oxide combustion accelerator is composed of the bimetallic oxide combustion accelerator, an oxidizing agent, a metal fuel, an adhesive, a curing agent and a plasticizer. The method comprises the following steps: 1, weighing; 2, premixing; 3, pouring; 4, curing; and 5, chemical cutting. The invention is used for the solid propellant containing the bimetallic oxide combustion accelerator and the preparation of the solid propellant.

Description

technical field [0001] The invention relates to a solid propellant and a preparation method thereof. Background technique [0002] Solid propellant is an energetic composite material with specific properties. It is the power source of various solid engines such as missiles and space vehicles. The energy generated by the combustion and reaction of solid propellant is used as the thrust of the engine. Solid propellant technology is a common technology, supporting technology, and restrictive technology for weapons and equipment. Its performance directly affects the survivability and combat effectiveness of strategic and tactical missiles. In order to meet the continuously developing strategic and tactical needs at this stage, the development of solid propellants with higher energy, faster burning rate and better safety is of great national defense significance. [0003] Solid propellants are mainly composed of oxidizers, metal fuels, burning rate additives, binders, curing ag...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B33/06C06B21/00C06D5/00
CPCC06B33/06C06B21/0058C06D5/00
Inventor 杨玉林扈颖慧林凯峰范瑞清夏德斌王平张健
Owner HARBIN INST OF TECH
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