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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Imprimir: 2150-766X
ISSN En Línea: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2018024804
pages 219-229

COMPARATIVE INVESTIGATION OF DIFFERENT NANO-METAL MATERIALS ON COMBUSTION PROPERTIES OF DB AND CMDB PROPELLANTS

Zhi-feng Yuan
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Feng-qi Zhao
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, Xi'an, 710065, China
Yan-jing Yang
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Xiu-duo Song
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Hong-xu Gao
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Si-yu Xu
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, Xi'an 710065, China

SINOPSIS

In order to understand the effects of different nano-metal materials on the combustion properties of double-base (DB) and composite-modified double-base (CMDB) propellants, five different nanometal (nm) powders including nano-silver (nm-Ag), nano-copper (nm-Cu), nano-nickel (nm-Ni), nano-titanium (nm-Ti), and nano-aluminum (nm-Al) were selected and their effects on the combustion properties of DB and CMDB propellants were investigated. The results show that the five aforementioned nano-materials can enhance the combustion performance of DB and CMDB propellants. The burning rates of DB propellant at 10 MPa, which is the working pressure of many solid rockets, are in the following order: unm - Al > unm - Cu > unm - Ni = unm - Ti > unm - Ag > ublank; the pressure exponents of RDX-CMDB propellant at 6–10 MPa are in the following order: nnm - Ni < nnm - Ag < nnm - Ti < nnm - Cu < nblank < nnm - Al. In particular, 0.6% of nm-Ni can reduce the pressure exponent of RDX-CMDB propellant evidently from 0.26 to - 0.02 at 6-10 MPa, and that nm-Al is effective in increasing the burning rate of DB propellant. In the presence of 0.6% of nm-Al, the burning rate at 10 MPa is increased from 17.12 to 25.84 mm/s, and the pressure exponent at 10–20 MPa is decreased from 0.61 to 0.16.


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