A platform burning boron-containing fuel-rich propellant

A fuel-rich propellant and fuel technology, which is used in offensive equipment, compressed gas generation, explosives, etc., can solve the problems of unstable ballistic performance, large changes in burning rate, and reduced engine reliability, so as to improve ballistic performance and engine reliability. Reliability of work, effect of reducing pressure index

Active Publication Date: 2021-12-10
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Solve the problem that the boron-containing propellant has a large change in burning rate when the working pressure of the ramjet engine changes sharply, which leads to unstable ballistic performance and reduced reliability of engine work

Method used

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  • A platform burning boron-containing fuel-rich propellant
  • A platform burning boron-containing fuel-rich propellant
  • A platform burning boron-containing fuel-rich propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] A boron-containing fuel-rich propellant, the formula composition and content of which are shown in Table 1.

[0021] Table 1: Propellant formulation of Example 1

[0022]

[0023] The properties of the propellants with the above formulations are listed in Table 2.

[0024] Table 2: Properties of the propellants formulated in Table 1

[0025]

Embodiment 2

[0027] A boron-containing fuel-rich propellant, the composition and content of which are shown in Table 3.

[0028] Table 3: Propellant formulation of Example 2

[0029]

[0030] The properties of the propellants formulated above are listed in Table 4.

[0031] Table 4: Properties of the propellants formulated in Table 3

[0032]

Embodiment 3

[0034] A boron-containing fuel-rich propellant, the formula composition and content of which are shown in Table 5.

[0035] Table 5: Propellant formulation of Example 3

[0036]

[0037] The properties of the propellants formulated above are listed in Table 6.

[0038] Table 6: Performance of the formula propellant of embodiment 3

[0039]

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Abstract

The invention relates to a boron-containing fuel-rich propellant for platform combustion. The propellant effectively reduces the pressure index of the propellant by adjusting the type and gradation of the oxidant and introducing new additives, and solves the problem of the boron-containing propellant in stamping. When the working pressure of the engine changes sharply, the burning rate changes greatly, which leads to the problems of unstable ballistic performance and reduced reliability of the engine operation. On the premise of not affecting the comprehensive performance of the propellant, the burning rate of the propellant is kept basically unchanged when the working pressure of the ramjet engine changes sharply, which realizes the platform combustion of the propellant, improves the ballistic performance of the propellant and the working reliability of the engine, and provides The application of solid ramjet provides important technical support and has broad application prospects.

Description

technical field [0001] The invention belongs to the field of fuel-rich propellants for solid ramjet engines, in particular to boron-containing fuel-rich propellants for platform combustion. 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....

Claims

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Application Information

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