RDX/AP-CMDB Propellants Containing Fullerenes and Carbon Black Additives

Defence Science Journal

L. Y. Zhang¹  X. Han²  S. F. Li²  F. Q. Zhao¹  T. F. Wang²  D. L. Han²  Z. K. Lin² 

[1] Xi’an Modern Chemistry Research Institute, Xi’an;University of Science and Technology of China, Hefei

关键词: Fullerene;    combustion properties;    burning rate;    CMDB propellant;    RDX/AP-CMDB propellants;   

DOI  :  

学科分类：社会科学、人文和艺术（综合）

来源: Defence Scientific Information & Documentation Centre

【 摘 要 】

The influence of fullerene additives on the combustion behaviour of cyclotrimethylene trinitramine/ammonium perchlorate composite modified double-base (RDX/AP-CMDB) propellants are investigated by thermogravimetricdifferential thermogravimetric (TG-DTG) analysis, burning rate tests, and scanning electron microscopy observations. The difference between lead salicylate (F-Pb) and bismuth citrate acid (CP-Bi) as combustion modifiers has also been examined. TG-DTG investigations show that the addition of all additives advanced and accelerated the evaporation of nitroglycerin (NG). The addition of Extracted Fullerene Soot (EFS), C60 and carbon black (CB) additives obviously accelerated the liquid  phase decomposition of NG. Also, the solid phase decomposition of nitrocellulose (NC) and the liquid phase  decomposition of RDX were accelerated by 0.5 per cent Fullerene Soot (FS)/2.5 per cent CP-Bi/0.5 per cent copper adipic acid (J-Cu) composite catalyst. The addition of all composite catalysts promoted the decomposition of ammonium perchlorate (AP) except 0.5 per cent EFS/2.5 per cent CP-Bi/0.5 per cent J-Cu composite catalysts. It is well known that there exists dark zone in the flame structure of RDX-CMDB propellant, but in our observation, the dark zone vanished with the addition of 10 per cent AP to the forenamed propellant. The burning rates were increased at low pressure but reduced at high pressure by all catalysts except 0.5 per cent EFS/2.5 per cent CP-Bi/0.5 per cent J-Cu and 0.5 per cent C60/2.5 per cent CP-Bi/0.5 per cent J-Cu which reduced the burning rates at every tested pressure. The pressure exponents of tested propellants were reduced by 0.5 per cent FS/2.5 per cent CP-Bi/0.5 per cent J-Cu with a factor of 17 per cent . The quenched surface observations significantly differed with the additions of diverse composite catalysts, which were consistent with the burning rate results.Defence Science Journal, 2009, 59(3), pp.284-293, DOI:http://dx.doi.org/10.14429/dsj.59.1522

【 授权许可】

Unknown