Boron-containing fuel-rich propellant

Abstract

The invention discloses a boron-containing fuel-rich propellant. The boron-containing fuel-rich propellant comprises the following components by weight percent: 20 to 30 percent of binder system, 22 to 35 percent of oxidant, 35 to 44 percent of fuel, and 0.5 to 4 percent of performance regulator. By virtue of a technical means for adding energizing additive and novel additive into the propellant system, the injection efficiency and primary combustion efficiency of the boron-containing fuel-rich propellant can be significantly improved, the weather resistance of the propellant on the premise ofnot influencing the comprehensive performance of the propellant can be improved, and the comprehensive performance of the boron-rich fuel-rich propellant can be improved.

Description

technical field [0001] The invention relates to the technical field of fuel-rich propellants for solid ramjet engines, in particular to a boron-containing fuel-rich propellant. 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] Th...

AI Technical Summary

Problems solved by technology

[0007] In order to solve the above-mentioned problems in the prior art, the present invention provides a boron-containing fuel-rich propellant, which solves the problems of the existing boron-containing propellant by adding energetic additives and new additives to the propellant system. Because the binder absorbs heat during the primary decomposition process, resulting in a decrease in combustion temperature, which leads to low propellant primary injection efficiency and low combustion efficiency.

Images