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

ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2015013743
pages 25-33

EXTRUSION TECHNIQUE FOR EXTRUDED COMPOSITE PROPELLANT GRAIN

Ashwani K. Mishra
High Energy Materials Research Laboratory, Pune 411 021, India
A. N. Patil
High Energy Materials Research Laboratory, Pune 411 021, India
A. B. Dange
High Energy Materials Research Laboratory, Pune 411 021, India
R. N. Patkar
High Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, India
Pawan Kumar Khanna
Department of Applied Chemistry, Defence Institute of Advanced Technology, Pune, 411025, India
Seema Dilip Kakade
High Energy Materials Research Laboratory, Pune, 411021, India

要約

Extrusion techniques for double-base propellant are well established and are operational worldwide. Indian ordnance factories have facilities to extrude propellants of diameters ranging from 10 to 160 mm, but the extruded composite propellant (ECP) is an entirely new thrust area in the field of composite propellant. The research and development work on ECP is being carried out at the High Energy Materials Research Laboratory (HEMRL). These are based on high-density thermoplastic elastomers (TPEs) used as propellant binder with ammonium perchlorate (AP) as the oxidizer and aluminum (Al) as metallic fuel. This class of propellant not only provides higher energy, but also yields higher density impulses. It can also take up higher solid loadings (up to 90%) and has good dimensional stability. The extrusion of ECP with large diameters (Ø 120 mm) has not been reported in literature so far. This paper presents the establishment of an extrusion technique for ECP grains with large diameters, which is the first of its kind. At the HEMRL, Viton-based ECP has been developed, characterized, and evaluated. Due to its higher dimensional stability and higher density of the order of 1.97 g/cc, the developed extruded composite propellant obtained by our extrusion technique can have various applications, such as for gas generators, thrusters, and auxiliary motors of advanced missiles.


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