Composite propellant containing burning rate depressant and method of use

Claim 1

IN THE METHOD OF DEVELOPING THRUST WHEREIN A SOLID PROPELLANT CHARGE CONTAINED IN A COMBUSTION CHAMBER OF A ROCKET MOTOR IS IGNITED AND 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: FROM 75 TO 95 PERCENT BY WEIGHT OF AN OXIDIZER COMPONENT SELECTED FROM THE GROUP OF SOLID INORGANIC OXIDIZING SALTS CONSISTING OF AMMONIUM PERCHLORATE, THE ALIKALI METAL PERCHLORATES, AMMONIUM NITRATE, THE ALKALI METAL NITRATES, AND MIXTURES THEREOF, AT LEAST A MAJOR PORTION OFSAID OXIDIZER COMPONENT BEING AT LEAST ONE OF SAID PERCHLORATES; AND FROM 25 TO 5 PERCENT BY WEIGHT OF A BINDER COMPONENT COMPRISED OF A RUBBERY MATERIAL SELECTED FROM THE GROUP CONSISTING OF NATURAL RUBBER, SYNTHETIC RUBBER POLYMERS, AND MIXTURES THEREOF; AND FROM 0.1 TO 20 PARTS BY WEIGHT PER 100 PARTS BY WEIGHT OF THE TOTAL AMOUNT OF SAID OXIDIZER COMPONENT PLUS SAID BINDER COMPONENT OF A BURNING RATE DEPRESSING AGENT SELECTED FROM THE GROUP CONSISTING OF HYDROXYLAMINE, INORGANIC SALTS OF HYDROXYLAMINE, SEMICARBAZIDE, INORGANIC SALTS OF SEMICARBAZIDE, AND MIXTURES THEREOF.