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On the Microstructure of Composite Propellants

Blatz, Paul J. (1966) On the Microstructure of Composite Propellants. California Institute of Technology , Pasadena, CA. (Unpublished)

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The term composite propellant as commonly used in the solid rocket industry refers to a heterogeneous mixture of several phases of solid particles entrained in a rubberlike binder. The two principal solid phases are aluminum fuel and ammonium perchlorate oxidizer; together with a small amount of additives which control adhesive and ballistic properties, they constitute the filler. Either a branched polyurethane or crosslinked polybutadiene network serves as a typical binder. Performance calculations based on the assumption that the enthalpy of the composite balances the enthalpy of the combustion products at their flame temperature lead to the demand for a composite filled with slightly more than 88 wt. % of solid phases, about 25% of which is aluminum. At this point a little arithmetic is in order.

Item Type:Report or Paper (Technical Report)
Record Number:CaltechAUTHORS:20151207-103048945
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ID Code:62648
Deposited On:09 Dec 2015 00:10
Last Modified:03 Oct 2019 09:20

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