High-energy nitrine propellant and preparation method thereof

Abstract

The invention provides a high-energy nitrine propellant and a preparation method thereof. A formula of the high-energy nitrine propellant contains a blending adhesive and a plasticizer, wherein the blending adhesive contains poly-nitrine glycidyl ether, 3,3-bis(azidomethyl)butylene oxide and tetrahydrofuran, wherein the mass ratio of 3,3-bis(azidomethyl)butylene oxide to 3,3-bis(azidomethyl)butylene oxide and tetrahydrofuran is 1 / 3-1 / 2, the plasticizer is a mixture of nitrate and N-butyl-2-nitroethyl ammonium nitrate, and the plastifying ratio is 2.4-3.0. The solid content of the propellant can be increased to be over 80%, the specific impulse of the propellant is more than or equal to 243s, the glass transition temperature Tg of the propellant can be as low as -74 DEG C, the maximum elongation rate epsilonm can reach over 48%, the maximum extension strength sigmam at 70 DEG C is more than equal to 0.78MPa, and the maximum rate elongation rate epsilon is more than or equal to 42%.

Description

technical field [0001] The invention relates to an azide high-energy propellant and a preparation method thereof, belonging to the technical field of solid propellants. Background technique [0002] The competition of various missile weapons in different battlefields has become the most distinctive feature of modern warfare. In order to meet the complex and changeable combat environments of different arms, various missile weapons are gradually developing towards high reliability and strong adaptability. Solid propellant is the main power source of various types of missile weapons, and its comprehensive performance is very important to improve the combat effectiveness of missile weapons. As the continuous phase matrix of solid propellants, the binder system directly determines the energy level, mechanics, safety, combustion and other properties of the propellant, and becomes a key symbol for the replacement of solid propellants, such as polysulfide propellants, HTPB propellan...

AI Technical Summary

Problems solved by technology

[0004] Due to the strong polarity and high rigidity of the GAP molecular chain, its own glass transition temperature Tg≥-40°C, the glass transition temperature of the propellant with nitrate plasticized GAP as the binder system Tg≥-53°C, below -55°C In a brittle glass state, the maximum elongation ε at -60°C m ≤10%; at the same time, the high temperature strength and elongation are also low, and the maximum tensile strength at 70°C is σ m ≤0.6MPa, maximum elongation ε m ≤30%, the problem of poor mechanical properties at high and low temperatures limits the application of this type of propellant in a wide temperature range

Secondly, the number of atoms carried by the main chain of the GAP molecular chain is small, the plasticization ratio of the GAP adhesive system is generally below 2.0, and the wettability of the adhesive system is poor, resulting in a solid mass percentage of the propellant generally ≤ 75%, which limits the propulsion. Further increase in dose energy levels

In addition, another problem currently existing in GAP propellants is that the propellant burning rate pressure index is high (n≥0.5), and with the increase of the relative content of GAP binder in the formula, the propellant burning rate pressure index increases

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