Blatz, Paul J. (1966) On the Microstructure of Composite Propellants. California Institute of Technology , Pasadena, CA. (Unpublished) https://resolver.caltech.edu/CaltechAUTHORS:20151207-103048945
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Abstract
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) |
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Record Number: | CaltechAUTHORS:20151207-103048945 |
Persistent URL: | https://resolver.caltech.edu/CaltechAUTHORS:20151207-103048945 |
Usage Policy: | No commercial reproduction, distribution, display or performance rights in this work are provided. |
ID Code: | 62648 |
Collection: | CaltechAUTHORS |
Deposited By: | INVALID USER |
Deposited On: | 09 Dec 2015 00:10 |
Last Modified: | 03 Oct 2019 09:20 |
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