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

Abstract

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), C 60 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 C 60 /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.

Synthesis and Characterization of [60]Fullerene-Glycidyl Azide Polymer and Its Thermal Decomposition

“…C60 and its functionalized derivatives are important and can be remarkably applied in various studies because of their unique structure and physical properties [3][4][5]. As C60 has good features such as thermal stability, antioxidation, etching resistance, good compatibility with propellant components, and beneficial for preventing aging [6], C60 can replace carbon black as the solid rocket fuel additive that can increase the burning rate and combustion catalytic efficiency and decrease the amount of NOx in the exhaust gas [7,8]. If some energetic groups, such as the nitro group, would be added into C60, an enhanced fuel additive may be obtained [9].…”

Highly energetic compositions based on functionalized carbon nanomaterials

“…A comparative study showed 287 that the ignition temperature was lowered and burning rates were increased for colloidal suspensions of nitromethane with graphene, compared to liquid nitromethane monopropellant alone. It has been further reported 288 that the addition of raw fullerene soot (FS), extracted FS (EFS), pure C 60 and CB additives to nitroglycerine (NG) markedly accelerated its liquid phase decomposition. The effect of these nanomaterials on the combustion properties of double-base propellants (DB) has been also evaluated.…”

Unravelling the Effect of Anthraquinone Metal Salts as Wide-range Plateau Catalysts to Enhance the Combustion Properties of Solid Propellants

“…Solid rocket propellants are extensively used in almost all operational rockets, missiles, satellites and space shuttle launch vehicles [1][2][3]. Efforts have been mainly devoted to the development of novel propellants with high performance and a wide-range plateau in order to fulfill the ever-growing and challenging requirements, i.e.…”