Rocket projectiles

Claim 1

A ROCKET PROJECTILE HAVING A NOSE MEMBER; A CYLINDRICAL AUXILIARY COMBUSTION CHAMBER SCREWED ON TO THE NOSE MEMBER; A PLURALITY OF SUBSIDIARY NOZZLES SYMMETRICALLY SPACED AROUND THE WALL OF SAID AUXILIARY COMBUSTION CHAMBER FOR DISCHARGING PROPELLANT GASES TO IMPART SPIN TO THE PROJECTILE, EACH SUBSIDIARY NOZZLE BEING DISPOSED SUBSTANTIALLY NORMAL TO THE PROJECTILE AXIS AND TO THE PERPENDICULAR FROM THE SUBSIDIARY NOZZLE TO THAT AXIS, THE TRANSVERSE REAR WALL OF THE SAID AUXILIARY COMBUSTION CHAMBER HAVING AN AXIAL ORIFICE THEREIN; AN AUXILIARY CHARGE WITHIN THE SAID AUXILIARY COMBUSTION CHAMBER WHICH CHARGE COMPRISES A STACK OF CORDITE DISCS, SEPARATING WASHERS BETWEEN THE DISCS AND TWO SCREWS PASSING THROUGH THE DISCS AND WASHERS FOR ATTACHING THE CHARGE TO THE NOSE MEMBER; A BURSTING DISC SUPPORTED WITHIN THE AXIAL ORIFICE IN THE REAR WALL OF THE AUXILIARY COMBUSTION CHAMBER; A CYLINDRICAL SECONDARY CHAMBER SCREWED ON TO THE REAR END OF THE AUXILIARY COMBUSTION CHAMBER AND HAVING IN ITS REAR WALL AN AXIAL ORIFICE; A MAIN MOTOR CASING SCREWED ON TO THE REAR END OF THE SECONDARY CHAMBER; A MAIN PROPELLANT CHARGE HAVING THEREIN AN AXIAL BORE WITHIN THE MAIN MOTOR CASING; A MAIN JET FOR DISCHARGE OF GASES FROM SAID PROPELLANT CHARGE; AND A DUCT MEMBER SUPPORTED IN THE AXIAL ORIFICE IN THE REAR WALL OF THE SECONDARY CHAMBER AND EXTENDING REARWARD INTO THE AXIAL BORE OF THE MAIN PROPELLANT CHARGE, WHICH DUCT MEMBER COMPRISES A HOLLOW STEM CLOSED AT ITS REAR END, A CIRCULAR FLANGE SURROUNDING THE REAR END OF THE STEM AND HAVING TWO SMALL TRANSVERSE BORES THEREIN WHICH INTERSECT THE BORE OF THE HOLLOW STEM THEREBY PROVIDING A RESTRICTED ENTRY FOR PROPELLANT GASES FROM THE MAIN CHARGE INTO THE SECONDARY CHAMBER TO RETARD THE BUILD UP OF PRESSURE ON THE REAR FACE OF THE BURSTING DISC AND DELAY THE BURSTING THEREOF AND THE SUBSEQUENT IGNITION OF THE AUXILIARY CHARGE.