Carbon Nanotube Filled Copper Metal Complex Nanocomposite Burning Rate Catalyst

A metal complex, burning rate catalyst technology, applied in non-explosive/non-thermal agent components, explosives, offensive equipment and other directions, can solve the problem that the combustion catalytic performance of composite materials has not been studied, and achieve improved combustion catalytic performance and catalytic performance. Improve, good catalytic effect
CN113548932BActive Publication Date: 2022-03-11SHAANXI NORMAL UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
SHAANXI NORMAL UNIV
Publication Date
2022-03-11

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Abstract

The invention discloses a carbon nanotube-filled copper metal complex nanocomposite burning rate catalyst. Multi-wall carbon nanotubes with different diameters are ultrasonically treated with a mixed acid solution to obtain oxidized carbon nanotubes with openings at both ends. The oxidized carbon nanotubes are Add Cu(NO 3 ) 2 ·3H 2 O, [Cu(TMEDA) 2 ](NO 3 ) 2 (TMEDA=Tetramethylethylenediamine), [Cu(MIM) 4 ] (DCA) 2 (MIM=1‑methylimidazole, DCA=dicyanamide anion) or [Cu(NMIM) 4 ] (DCA) 2 (NMIM=2-nitro-1-methylimidazole, DCA=dicyanamide anion) in a saturated solution, ultrasonic treatment, so that these copper metal complexes are filled in the official cavity of the oxidized carbon nanotubes, thereby obtaining carbon nanotubes filled Copper metal complex nanocomposite burning rate catalyst. The preparation method of the invention is simple, and the obtained nanocomposite burning rate catalyst has good catalytic effect and is easy to enlarge and prepare.
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Description

technical field

[0001] The invention belongs to the technical field of solid propellants, in particular to a carbon nanotube filled copper metal complex nanocomposite burning rate catalyst. Background technique

[0002] Solid propellant is a commonly used rocket engine power source, and its combustion state will directly affect the performance of aerospace rockets. After long-term research, solid propellants have formed a development trend of high energy, high specific impulse, and low signal characteristics. Ammonium perchlorate (AP), a strong oxidant, is a common energetic material component in solid propellants, especially in double-base propellants and their modified propellants. Since ammonium perchlorate generally has a relatively large proportion, the combustion rate, thermal decomposition peak temperature and heat release of its decomposition process have a great influence on the combustion of solid propellants. Among the existing methods for improving the combustio...

Claims

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