Composite solid propellant based on multi-scale modified nitramine oxidant and preparation method

A technology of solid propellant and oxidant, which is applied in the direction of offensive equipment, compressed gas generation, explosives, etc. It can solve the problems of sudden increase in high-pressure burning rate, inaccurate catalysis of burning rate catalyst, and low combustion efficiency of solid propellant. Contradictory problems, the effect of increasing production and use safety

Active Publication Date: 2021-11-09
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to avoid the deficiencies of the prior art, the present invention proposes a composite solid propellant based on a multi-scale modified nitramine oxidant, aiming at the low combustion efficiency of solid propellants, the sudden increase of high-pressure burning rate, and the inability of the burning rate catalyst to be accurately catalyzed, etc. Problem, the present invention provides a surface in-situ growth catalyst, multi-scale modified nitramine to regulate the combustion performance of propellant, which can increase the combustion rate of propellant and reduce the pressure index while reducing the amount of catalyst

Method used

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  • Composite solid propellant based on multi-scale modified nitramine oxidant and preparation method
  • Composite solid propellant based on multi-scale modified nitramine oxidant and preparation method
  • Composite solid propellant based on multi-scale modified nitramine oxidant and preparation method

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preparation example Construction

[0043] The preparation process of the embodiment can be divided into the following four steps:

[0044] (1) Preparation of passivated modified nitramine crystals: Dissolve triaminoguanidine hydrochloride TAG (2.5mmol, 119.2mg) in dimethyl sulfoxide (DMSO, 7.3mL), and heat to Stir at 100°C for 30min, then add nitramine (RDX / HMX / CL-20, 5mmol) to the solution, stir for 30min, the solution gradually changes from colorless and transparent to pink. The above solution was kept in an oil bath at a temperature of 105° C., and then 2.5 mmol (290.2 μL) of glyoxal aqueous solution was added. The 2D flexible TAGP material can be produced after 1 hour of cross-linking reaction. Finally, at 1.008mL·min -1 The flow rate of the antisolvent (H 2 O). DMSO and anti-solvent H 2 The volume ratio of O was kept at 1:2. Finally, the precipitated crystals were filtered out and washed with distilled water to obtain passivated modified nitramine crystals.

[0045] (2) Preparation of dopamine-coate...

example 1

[0050] Example 1: A composite solid propellant without a burn rate catalyst. The ammonium perchlorate (AP) content is 57wt%, the μ-Al content is 18wt%, and the RDX content is 10wt%. The binder adopts hydroxyl-terminated polybutadiene (HTPB, 11.5wt%), and the plasticizer adopts sunflower Acid diisooctyl ester (DOS, 2.5wt%), curing agent adopts isophorone diisocyanate (IPDI, 1wt%). The propellant preparation method is as follows:

[0051] (a) Drying treatment of raw materials: dry the solid material in an oven at 60°C for 96 hours;

[0052] (b) Propellant components are fully mixed: Weigh a certain mass of propellant components according to the formula, and add AP, HTPB, DOS, IPDI, RDX, and micron aluminum powder into the mixer in sequence, and place them in a water bath at 60°C Stir to make it evenly mixed;

[0053] (c) Vacuum pouring: pour the propellant slurry into the customized mold, and the vacuuming time is greater than 12h;

[0054] (d) Curing: heat and cure the vacu...

example 2

[0056] Example 2: The propellant formula and preparation steps are the same as Example 1, only the RDX in Example 1 is replaced by inactivated modified qy-RDX;

[0057] qy-RDX is more insensitive than RDX, and no cracks are produced under the action of electron beam ( Figure 9 ). The melting endothermic peak of Example 2 is slightly lower than that of Example 1, which is 204.2°C, but the endothermic heat is reduced; compared with Example 1, the peak temperature of the exothermic peak of AP in Example 2 is reduced by 5.6°C, and the heat of decomposition is increased to 1011.0 J·g -1 , the thermal weight loss of the example 2 propellant in the uncontrollable reaction zone increases by 4.42%, and the thermal decomposition remaining mass decreases by 4.52% ( Figure 10 ). The burning rate of the propellant in Example 2 increased to 3.37mm·s at 0.5MPa -1 , the burning rate pressure exponent n is 0.314( Figure 11). qy-RDX can only improve its own reactivity and slightly incr...

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Abstract

The invention relates to a composite solid propellant based on a multi-scale modified nitramine oxidant. The propellant is based on high-nitrogen two-dimensional conjugated structure doped modified nitramine, and through insensitive modification of the main component nitramine oxidant, the sensitivity of the nitramine oxidant is reduced while the energy of the nitramine oxidant is improved, and the contradictory problem of high energy and insensitive is effectively solved, and the production and use safety of the propellant is improved. According to the preparation method, PDA is wrapped on the surface of modified nitramine, hydroxyl on the surface of the PDA is taken as an active site of a coordination reaction, a nano CuO and nano Fe2O3 catalyst is grown in situ on the surface of the PDA by utilizing a hydrothermal reaction, and a catalyst/oxidant integrated core-shell structure (qy-RDX coated CuO and qy-RDX coated Fe2O3) is obtained and is used for replacing nitramine and a catalyst in a traditional propellant formula. The catalytic coating of the modified nitramine can significantly improve the catalytic efficiency of the propellant and reduce the decomposition rate and pressure sensitivity of the propellant, so that the pressure index of the propellant is reduced.

Description

technical field [0001] The invention belongs to the field of regulating and controlling the combustion performance of composite solid propellants, and relates to a composite solid propellant based on a multi-scale modified nitramine oxidant, in particular to a method for modifying nitramine with a surface in-situ growth catalyst and regulating the combustion performance of the propellant . Background technique [0002] Solid rocket motors generate thrust through propellant combustion. In order to meet the performance requirements of the engine, it is generally desired that the solid propellant has a wide range of burning rate and a low burning rate pressure index. Adding combustion catalysts to solid propellants is the main way to adjust the combustion properties of propellants . However, the probability of directly adding the burning rate catalyst and the nitramine oxidant is not high. In order to improve the catalytic effect, simply increasing the amount of catalyst will...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B33/12C06D5/06
CPCC06B33/12C06D5/06
Inventor 严启龙张雪雪薛智华陈书文聂洪奇
Owner NORTHWESTERN POLYTECHNICAL UNIV
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