Fuel-rich propellant with boron-based composite metal powder

A fuel-rich propellant and composite metal technology, which is applied in the direction of offensive equipment, compressed gas generation, non-explosive/non-thermal agent components, etc., can solve the problems of high ignition temperature and low combustion efficiency of boron powder, and achieve improved combustion performance and energy performance, improved process performance, and the effect of addressing the need for high-performance fuel-rich propellants

Inactive Publication Date: 2018-11-02
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the above problems in the prior art, the present invention provides a fuel-rich propellant containing boron-based composite metal powder for ramjet, the propellant composition replaces part of the metal fuel with boron-based composite metal powder, It solves the problems of high ignition temperature and low combustion efficiency of boron powder, meets the needs of advanced ramjet missiles for high-performance fuel-rich propellants, and improves the process performance and combustion performance of propellants without affecting the overall performance of propellants

Method used

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Embodiment 1

[0038] Composition of boron-based composite metal powder: boron content 95%, magnesium content 5%.

[0039] (1) Composition of propellant formula

[0040]

[0041] (2) Propellant performance

[0042]

[0043] Can know from embodiment 1, measured calorific value=32.3MJ·kg -1 , Combustion efficiency = 90.8%, excellent propellant performance.

Embodiment 2

[0045] Composition of boron-based composite metal powder: boron content 90%, magnesium content 10%.

[0046] (1) Composition of propellant formula

[0047]

[0048]

[0049] (2) Propellant performance

[0050]

[0051]Can know from embodiment 2, measured calorific value=31.7MJ·kg -1 , Combustion efficiency = 90.9%, excellent propellant performance.

Embodiment 3

[0053] Composition of boron-based composite metal powder: boron content 85%, magnesium content 15%.

[0054] (1) Composition of propellant formula

[0055]

[0056] (2) Propellant performance

[0057]

[0058] Can know from embodiment 3, measured calorific value=33.6MJ·kg -1 , Combustion efficiency = 90.8%, excellent propellant performance.

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Abstract

The invention relates to a fuel-rich propellant with boron-based composite metal powder. The fuel-rich propellant comprises, by weight, 30%-50% of fuel, 25%-40% of oxidizing agents, 15%-25% of bindersand 3%-10% of performance regulators. The fuel comprises the boron-based composite metal powder with core-shell type structures. The fuel-rich propellant has the advantages that the boron-based composite metal powder with the core-shell structures is introduced into a formula for the fuel-rich propellant as high-energy fuel, accordingly, the problems of high ignition temperature and low combustion efficiency of boron powder can be solved, the combustion performance and the energy performance of the fuel-rich propellant can be enhanced, the processing properties further can be improved, the requirements of ramjet engines on high-performance fuel-rich propellants can be met, and the fuel-rich propellant has a broad application prospect.

Description

technical field [0001] The invention relates to the field of fuel-rich propellants, in particular to a fuel-rich propellant containing boron-based composite metal powder. Background technique [0002] The solid rocket ramjet organically combines the advantages of solid rocket motors and air-breathing engines. Compared with solid rocket motors, due to the use of oxygen in the air as the oxidant, the energy of the propellant is greatly increased, and the specific impulse is 2 to 4 times that of solid rocket motors; compared with air-breathing motors, due to the use of internal surface The principle of compressed air intake omits complex structures such as rotating parts, and the engine structure is simplified. Therefore, the missile powered by the solid impulse engine has the characteristics of small size, light weight, and long range. It can realize full powered flight and enhance the missile's defense penetration capability and terminal attack capability. [0003] The soli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06D5/06C06B23/00C06B33/06C06B33/12C06B33/14
CPCC06B23/00C06B33/06C06B33/12C06B33/14C06D5/06
Inventor 庞爱民肖金武陈涛张先瑞刘建红黄凌李建华王园园王锐
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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