Solid hydrocarbon resin rocket propellants and method of propulsion

Claim 1

A METHOD FOR DEVELOPING THRUST IN A ROCKET FROM FINELY-DIVIDED SOLID PROPELLANT COMPONENTS OF HIGH-ENERGY VALUE IN THE COMBUSTION CHAMBER OF THE ROCKET WHICH COMPRISES, COMBUSTING SAID COMPONENTS COMPOSITED AND HELD TOGETHER IN A MOLD GRAIN CONTAINING 1 TO 10 WT. PERCENT OF A HYDROCARBON RESIN BINDER THAT GIVES THE GRAIN INCREASED TENSILE STRENGTH, SAID HYDROCARBON RESIN BEING MADE BY POLYMERIZING WITH A FRIEDEL-CRAFTS CATALYST A STEAM-CRACKED PETROLEUM FRACTION BOILING IN THE RANGE OF 20* TO 280*C. AND CONTAINING C5 TO C9 OLEFINS, DIOLEFINS AND AROMATICS, SAID RESIN HAVING A MOLECULAR WEIGHT OF ABOUT 1,000 TO 5,000, SAID FINELY-DIVIDED COMPONENTS INCLUDING A FINELY-DIVIDED FUEL FROM THE GROUP CONSISTING OF LITHIUM, ALUMINUM, BERYLLIUM, BORON, MAGNESIUM, HYDRAZINE DIBORANE AND HYDRAZINE MONOBORANE, AND A COMPATIBLE OXIDIZER FROM THE GROUP CONSISTING OF AMMONIUM PERCHLORATE, LITHIUM PERCHLORATE, SODIUM PERCHLORATE, NITROCELLULOSE HEXANITROETHANE, AND SODIUM NITRATE.