A kind of composite solid propellant and preparation method based on multiscale modified nitramine oxidant

A solid propellant and oxidant technology, which is used in offensive equipment, compressed gas generation, explosives, etc., can solve the problems of sudden increase in high-pressure burning rate, inability to accurately catalyze the burning rate catalyst, and low combustion efficiency of solid propellant, and achieve a solution to the problem. Paradoxical issues, effects of increased production and safety of use

Active Publication Date: 2022-06-07
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
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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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  • A kind of composite solid propellant and preparation method based on multiscale modified nitramine oxidant
  • A kind of composite solid propellant and preparation method based on multiscale modified nitramine oxidant
  • A kind of composite solid propellant and preparation method based on multiscale modified nitramine oxidant

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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 inactivated modified nitramine crystals: Triaminoguanidine hydrochloride TAG (2.5 mmol, 119.2 mg) was dissolved in dimethyl sulfoxide (DMSO, 7.3 mL), and heated to 100° C., stirred for 30 min, then nitramine (RDX / HMX / CL-20, 5 mmol) was added to the solution, stirred for 30 min, and the solution gradually changed 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 aqueous glyoxal was added. The 2D flexible TAGP material can be generated within 1 hour of cross-linking reaction. Finally, at 1.008mL·min -1 Add the anti-solvent (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 inactivated modified nitramine crystals.

[0045] (2) Preparation of dopa...

example 1

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

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

[0052] (b) Fully mixing the propellant components: Weigh the propellant components of a certain mass according to the formula, and add AP, HTPB, DOS, IPDI, RDX, and micron aluminum powder to the mixer in turn, under the condition of 60 ℃ water bath Stir to make it evenly mixed;

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

[0054] (d) Curing: The propellant slurry that has bee...

example 2

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

[0057] qy-RDX is more insensitive than RDX, and no cracks are generated 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 value is reduced; compared with Example 1, the exothermic peak temperature 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 propellant in the uncontrollable reaction zone of Example 2 increased by 4.42%, and the residual mass of thermal decomposition decreased by 4.52% ( Figure 10 ). The burning rate of the propellant in Example 2 was increased to 3.37 mm s at 0.5 MPa -1 , the burning rate pressure index n is 0.314 ( Figure 11). qy-RDX can only improve its own reactivity, ...

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Abstract

The invention relates to a composite solid propellant based on a multi-scale modified nitramine oxidant, which is based on a high-nitrogen two-dimensional conjugated structure doped with modified nitramine, and through the inactivation modification of the main component nitramine oxidant, in the Increase the energy of the nitramine oxidant while reducing its sensitivity, effectively solving the contradictory problem of high energy and insensitivity, and increasing the production and use safety of the propellant. Coating PDA on the surface of modified nitramine, using the hydroxyl group on the surface of PDA as the active site of coordination reaction, using hydrothermal reaction to grow nano-CuO and nano-Fe in situ on the surface of PDA 2 o 3 Catalyst, obtained catalyst / oxidant integrated core-shell structure (qy‑RDX@CuO and qy‑RDX@Fe 2 o 3 ), used to replace nitramines and catalysts in traditional propellant formulations. The modified nitramine catalytic coating can significantly improve the catalytic efficiency of the propellant and reduce the pressure sensitivity of its decomposition rate, thereby reducing the pressure index of the propellant.

Description

technical field [0001] The invention belongs to the field of combustion performance regulation of composite solid propellants, relates to a composite solid propellant based on a multi-scale modified nitramine oxidant, and in particular relates to a surface in-situ growth catalyst modified nitramine and a method for 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, solid propellants are usually expected to have a wide range of combustion rates and a lower combustion rate and pressure index. Adding combustion catalyst to solid propellant is the main way to adjust the combustion performance of propellant . However, the probability of directly adding a burning rate catalyst to contact with the nitramine oxidant is not high. In order to improve the catalytic effect, simply increasing the amount of catalyst will red...

Claims

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Application Information

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Patent Type & Authority Patents(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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