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Boron-containing fuel-rich propellant

A fuel-rich propellant and fuel technology, which is applied in the direction of offensive equipment, compressed gas generation, explosives, etc., can solve the problem of low combustion efficiency, achieve the effect of improving combustion and promoting oxygen transfer

Pending Publication Date: 2020-05-19
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The fuel-rich propellant formula containing boron-metal oxide core-shell structure of the present invention is used in ramjet engines, and part of the common boron powder is replaced by core-shell type composite boron powder containing boron-metal oxide core-shell structure, which solves the problem of Boron propellants have low combustion efficiency due to insufficient combustion of boron powder, which meets the needs of advanced ramjet missiles for high-performance fuel-rich propellants

Method used

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Examples

Experimental program
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Effect test

Embodiment 1

[0023] Test and Analysis of Thermal Oxidation Characteristics of Core-Shell Boron Powder

[0024] with Fe 2 o 3 As an example, the influence of transition metal oxide-coated boron powder on the thermal oxidation characteristics of boron powder is investigated, and the effect on B-Fe 2 o 3 The core-shell boron powder has been tested by TG-DSC thermal oxidation performance, and the results are as follows: figure 1 As shown, (a) is the TG curve of the sample, (b) is the DSC curve of the sample, and the curves 1, 2, and 3 marked in the figure represent the No. 1 sample, the No. 2 sample, and the No. 3 sample respectively. The sample is ordinary boron powder, the No. 2 sample is 5% Fe 2 o 3 Coated boron powder, sample No. 3 is 10% Fe 2 o 3 The coated boron powder was tested with a NETZSCH STA 449F3 thermal analyzer, the temperature range and temperature rise rate were 40°C / 20.0(°C / min) / 1400°C, and the atmosphere was 20OXYGEN 60NITROGEN. to B-Fe 2 o 3 The core-shell boron ...

Embodiment 2

[0029] B-Fe 2 o 3 Composition of core-shell boron powder: boron content 95%, Fe 2 o 3 Content 5%.

[0030] ⑴Propellant composition

[0031]

[0032] ⑵Propellant performance

[0033]

Embodiment 3

[0035] B-Cr 2 o 3 Composition of core-shell boron powder: boron content 95%, Cr 2 o 3 Content 5%.

[0036] ⑴Propellant composition

[0037]

[0038] ⑵Propellant performance

[0039]

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Abstract

The invention relates to a boron-containing fuel-rich propellant for a ramjet engine. Core-shell type composite boron powder containing a boron-metal oxide core-shell structure is adopted to replace apart of common boron powder; boron is taken as the core of the composite boron powder, a transition metal oxide is takenas a surface layer, in the combustion process, boron is combusted, the metal oxide is reduced into simple substance metal or a low-valence oxide, and then a reduction product is oxidized again by oxygen in the environment to generate the metal oxide. The metal oxide is taken asthecarrier of oxygen, so that oxygen transfer is promoted, and boron combustion is improved. The problem that the combustion efficiency of the boron-containing propellant is low due to insufficient boron combustion is solved, and the process performance and the combustion performance of the propellant are improved on the premise that the comprehensive performance of the propellant is not affected.The problem that a ramjet engine needs a high-performance fuel-rich propellant can be solved, and the application prospect is wide.

Description

technical field [0001] The invention belongs to the technical field of fuel-rich propellant for solid rocket ramjet, and in particular relates to a boron-containing fuel-rich propellant. Background technique [0002] The solid rocket ramjet uses solid fuel-rich propellant as the power source, and the fuel content reaches 30-50%. Therefore, fuel performance is one of the key factors that determine whether the potential excellent performance of the solid rocket ramjet can be fully exerted. Boron-rich fuel propulsion The propellant has a high calorific value and is the preferred propellant for solid impulse engines. [0003] However, the melting point and boiling point of boron powder are higher, it is difficult to melt and gasify, the ignition temperature is higher (1900K), and boron oxides (B 2 o 3 ) covering the surface of the boron powder, making it difficult to ignite and fully burn the boron powder. [0004] In addition, the presence of B on the surface of boron powder...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B33/06C06B33/12C06D5/06
CPCC06B33/06C06B33/12C06D5/06
Inventor 庞爱民肖金武张先瑞陈涛刘建江黄凌李建华王园园王锐
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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