Liquid propellant rocket motor

Claim 1

A ROCKET MOTOR COMPRISING AN OUTER CASING PROVIDED AT ONE END WITH A NOZZLE, A TUBULAR MEMBER MOUNTED IN SPACE RELATION WITHIN SAID OUTER CASING TO PROVIDE A NARROW ANNULAR OUTER REACION CHAMBER AND PASSAGEWAY BETWEEN SAID OUTER CASING AND SAID TUBULAR MEMBER AND TO FURTHER PROVIDE AN INNER RECATION CHAMBER WITHIN SAID TUBULAR MEMBER OPEN THE END ADJACENT TO SAID NOZZLE, A PLURALITY OF APERTURES IN SAID TUBULAR MEMBER NEAR THE END REMOTE FROM SAID NOZZLE TO EQUALIZE THE PRESSURES WITHIN SAID OUTER AND INNER REACTION CHAMBERS, MEANS FOR INTRODUCING A LIQUID REACTING MEDIUM AND A CATALYST INTO SAID OUTER REACTION CHAMBER TO ADMIX THEREIN AND PROVIDE A LOW HEAT PRODUCING GASEOUS PROPELLANT, AND MEANS FOR SPRAYING LIQUID FUEL AND LIQUID OXIDIZING AGENT INTO SAID INNER REACTION CHAMBER AND THUS PROVIDE UPON COMBUSTION OF SAID LIQUID FUEL A HIGH HEAT PRODUCING GASEOUS PROPELLANT, THEREBY PROVIDING LARGE VOLUMES OF GASEOUS PROPELLANTS FOR STUDY FLOW FROM SAID CHAMBERS INTO AND THROUGH SAID NOZZLE, WITH A LAYER OF LOW TEMPERATURE GESEOUS PROPELLANT ADJACENT TO THE CASING WALL TO PROTECT SAID WALL FROM THE EXCESSIVE HEAT OF THE HIGH TEMPERATURE GASEOUS PROPELLANT FLOWWING FROM SAID INNER REACTION CHAMBER WHILE AT THE SAME TIME PROVIDING A HIGH TEMPERATURE AND HIGH THRUST PRODUCING GASEOUS CORE.