Solid propellant and propellant burning rate catalyst system

Claim 1

IN THE METHOD OF DEVELOPING THRUST WHEREIN A SOLID PROPELLANT CHARGE CONTAINED IN A COMBUSTION CHAMBER OF A ROCKET MOTOR IS IGNITED ND THEN BURNED WITH THE EVOLUTION OF COMBUSTION GASES WHICH ARE EXHAUSTED FROM SAID COMBUSTION CHAMBER, THE STEP WHICH COMPRISES BURNING IN SAID COMBUSTION CHAMBER A PROPELLANT CHARGE COMPRISING: AS A BASE PROPELLANT, A SOLID INORGANIC OXIDIZING SALT AS AN OXIDIZER COMPONENT AND A SUITABLE BINDER COMPONENT; AND A BURNING RATE CATALYST SYSTEM CONSISTING ESSENTIALLY OF FROM 3 TO 10 PARTS BY WEIGHT PER 100 PARTS BY WEIGHT OF SAID BASE PROPELLANT OF AMMONIUM DICHROMATE, FROM 0.5 TO 7 PARTS BY WEIGHT PER 100 PARTS BY WEIGHT OF SAID BASE PROPELLANT OF A COPPER COMPONENT SELECTED FROM THE GROUP CONSISTING OF FINELY DIVIDED COPPER METAL, COPPER CHROMITE, AND COPPER OXIDES, AND FROM 2 TO 20 PARTS BY WEIGHT PER 100 PARTS BY WEIGHT OF SAID BASE PROPELLANT OF A SALT OF A TRINITROPHENOLIC COMPOUND SELECTED FROM THE GROUP CONSISTING OF 2,4,6-TRINITROPHENOL AND 2,4,6-TRINITRORESORCINOL.