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

ISSN Imprimer: 2150-766X
ISSN En ligne: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2019028001
pages 1-9

EFFECTS OF ALUMINUM-BASED MUTLIMETAL PARTICLES ON SOLID PROPELLANTS

Zhao Qin
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, Xi'an, 710065, China; Nanjing University of Science and Technology, Chemical Engineering School, No. 200 Xiaolingwei Street, Xuanwu District, Nanjing, 210094, China
Bei Qu
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, Xi'an 710065, China
Jian-hua Yi
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, Xi'an, 710065, China
Hui Xiang Xu
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, Xi'an 710065, China
Er-gang Yao
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, 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
Ning Hao
Science and Technology on Combustion and Explosion Laboratory, Xi'an Modern Chemistry Research Institute, No. 168 Zhangbadonglu, Yanta District, Xi'an 710065, China

RÉSUMÉ

Aluminum is well known to increase the specific impulse of composite propellants due to a higher adiabatic flame temperature associated with it. Aluminized propellants typically produce large agglomerates on the burning surface of solid propellants. These agglomerates are the main drawback of using aluminum in composite solid propellants, as they give rise to two-phase flow losses and slag accumulation, resulting in as much as 10% reduction in specific impulse. Nanosized aluminum powder enhances the burning rate of solid propellants significantly; however, the oxide content in it is much higher than micron-aluminum due to its considerable specific surface. This paper discusses an experimental investigation focused on the effects of micron-sized AlMg on the combustion behavior of solid propellants. Combustion characteristics and combustion condensed particles of solid propellants loaded with AlMg were investigated here. The results show that AlMg is more effective than Al in increasing the burning rate of hydroxyl-terminated polybutadiene based propellant since much heat was released with the help of the reaction between Al and Mg. The particle size of condensed combustion particles was reduced greatly thanks to the use of AlMg.

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