Middle-boron-content rich fuel propellant with high burning rate pressure exponent

Abstract

The invention discloses a middle-boron-content rich fuel propellant with a high burning rate pressure exponent. The middle-boron-content rich fuel propellant is prepared from 20-28 wt% of adhesive system which is composed of an adhesive and plasticizer, 20-28 wt% of oxidizing agent, 10-20 wt% of metal fuel, 5-15 wt% of amorphous boron powder, 10-20 wt% of agglomerated boron, 3-6 wt% of burning rate catalyst, 0.5-1.5 wt% of curing agent and 0.5-6 wt% of modifier, wherein the modifier is selected from one of titanium hydride, fluorene, ammonium nitrate, nanometer ferric oxide, adamantane, anthracene and anthraquinone. By means of the middle-boron-content rich fuel propellant, the burning rate pressure exponent can be increased, and the negative influence on the energy performance of the richfuel propellant is reduced.

Description

technical field [0001] The invention belongs to the technical field of boron-containing fuel-rich propellants for solid rocket ramjet engines, and in particular relates to a boron-rich fuel-rich propellant for high-burning-velocity pressure-exponent solid rocket ramjet engines. Background technique [0002] With the development of missile early warning and anti-missile technology, modern high-tech warfare puts forward higher requirements for missile penetration and survivability. Improving flight speed, improving maneuverability and increasing range are important development directions for tactical missiles in the future. This puts higher demands on the power plant of the missile. [0003] The solid rocket motor needs to carry the oxidizer required for fuel combustion, so the energy of the propellant is low. For missiles that use solid rocket motors as power plants, to increase their range must greatly increase the charge of the motors. The solid rocket ramjet uses oxygen ...

AI Technical Summary

Problems solved by technology

[0009] Although the agglomeration of boron particles can effectively improve the burning rate pressure index of boron-containing fuel-rich propellants, in engineering applications, after the content of agglomerated boron in the formulation of boron-containing fuel-rich propellants is determined, the burning rate of boron-containing fuel-rich propellants can be further improved Pressure exponent becomes very difficult and can negatively affect energy performance of boron-rich fuel propellants

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