On the Microstructure of Composite Propellants
- Creators
- Blatz, Paul J.
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.
Attached Files
Submitted - ON_THE_MICROSTRUCTURE_OF_COMPOSITE_PROPELLANTS__MAR_1966.pdf
Files
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Additional details
- Eprint ID
- 62648
- Resolver ID
- CaltechAUTHORS:20151207-103048945
- Created
-
2015-12-09Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field