Nozzle cooling and thrust vector control apparatus

Claim 1

IN A ROCKET MOTOR, NOZZLE COOLING AND THRUST VECTOR CONTROL APPARATUS COMPRISING: A CONVERGENT-DIVERGENT NOZZLE HAVING INNER AND OUTER WALLS DISPOSED IN SPACED, CONCENTRIC RELATION AND SEALABLY JOINED AT THE FORWARD AND AFT ENDS THEREOF, AN ANNULAR PARTITION EXTENDING BETWEEN SAID WALLS ADJACENT THE THROAT OF SAID NOZZLE AND DIVIDING THE ANNULAR SPACE BETWEEN SAID WALLS INTO FORWARD AND AFT CHAMBERS, SAID NOZZLE BEING PROVIDED WITH A PLURALITY OF CIRCUMFERENTIALLY SPACED COOLING PORTS FORMED IN SAID INNER WALL AT SAID THROAT AND IN COMMUNICATION WITH SAID FORWARD CHAMBER, A PLURALITY OF CIRCUMFERENTIALLY SPACED INJECTION PORTS FORMED IN SAID-INNER WALL AFT OF SAID THROAT, AT LEAST ONE FLUID SUPPLY PORT FORMED IN SAID OUTER WALL AND IN COMMUNICATION WITH THE FORWARD PORTION OF SAID AFT CHAMBER, A PLURALITY OF CIRCUMFERENTIALLY SPACED PRESSURIZED-FLUID OUTLET PORTS FORMED IN SAID OUTER WALL AND IN COMMUNICATION WITH THE AFT PORTION OF SAID AFT CHAMBER, AND A PLURALITY OF CIRCUMFERENTIALLY SPACED COOLANT SUPPLY PORTS FORMED IN SAID OUTER WALL AND IN COMMUNICATION WITH SAID FORWARD CHAMBER; FLUID RESERVOIR AND FIRST CONDUIT MEANS CARRIED BY SAID ROCKET MOTOR, SAID MEANS BEING CONNECTED TO SAID SUPPLY PORT AND ADAPTED TO SUPPLY FLUID TO SAID AFT CHAMBER UNDER PRESSURE; A PLURALITY OF SECOND CONDUIT MEANS EACH COMMUNICATIVELY CONNECTED TO A RESPECTIVE ONE OF SAID PRESSURIZED-FLUID OUTLET PORTS;