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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

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

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012003772
pages 209-220

A NOVEL HYBRID BINDER SYSTEM FOR EXTRUDABLE COMPOSITE PROPELLANT

V. D. Deuskar
High Energy Materials Research Laboratory, Sutarwadi, Pune, India
K. S. Mulage
High Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, India
A. K. Mishra
High Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, India
R. N. Patkar
High Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, India
S. H. Kharat
High Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, India
Seema Dilip Kakade
High Energy Materials Research Laboratory, Pune, 411021, India

SINOPSIS

Extrudable composite propellant is an entirely new thrust area in the development of composite propellants. These are based on high-density thermoplastic elastomer as a propellant binder with ammonium perchlorate as an oxidizer and aluminum as a metallic fuel. The present paper reports the evaluation of a combination of binders (Irostic, a thermoplastic polyurethane, and Viton, a fluoropolymer) as a binder for extrudable composite propellant. Both polymers were completely characterized before use. The feasibility of propellant processing was studied and processing parameters such as the rolling temperature, number of passes, extrusion temperature, and pressure have been established. The propellant formulations were characterized for burning rate, density, mechanical properties, and thermal analysis. The results reveal that as the Irostic content increases the density decreases and the mechanical properties (i.e., the tensile strength and percentage of elongation) increase. Due to the energetic nature of Viton, the burn rates are on the higher side for the composition containing Viton as binder compared to the Irostic-based composition. The details of propellant processing, characterization, and thermal analyses are presented.