Abstract: Solid composite propellants for rocket motors normally consist of an oxidizer and and aluminum powder cured in a polymeric binder system. The oxidizer, ammonium perchlorate, can be readily removed by suitable solvents leaving a residue consisting primarily of aluminum and polymer. The aluminum and polymer are separated by a process that is based upon the differential oxidation of the polymer leaving the aluminum in its original powder form. Aluminum metal forms, on exposure to air, an extremely tough inert aluminum oxide coating. Because of this, aluminum is extremely resistant to further oxidation even at temperatures up to its melting point at 660.degree. C. Most organic compounds, including polymers, are oxidized to carbon dioxide at much lower temperatures (400.degree.-600.degree. C.). Due to this difference in reactivity, it is possible to remove the polymer from the aluminum as carbon dioxide leaving the aluminum residue.