Vector control system, which includes means for introducing an auxiliary exhaust stream into the primary stream of a rocket motor

Claim 1

IN A ROCKET MOTOR HAVING A COMBUSTION CHAMBER, A FUEL WITHIN SAID COMBUSTION CHAMBER FOR CREATING COMBUSTION EXHAUST PRODUCTS THEREIN, A NOZZLE FOR THE EXIT OF THE MAIN EXHAUST STREAM OF SAID COMBUSTION PRODUCTS FROM SAID ROCKET MOTOR, A VECTOR CONTROL SYSTEM COMPRISING A PLURALITY OF AIR SCOOPS MOUNTED ON THE NOZZLE AND EXTENDING LONGITUDINALLY THEREOF, AND HAVING COMMUNICATION WITH THE INTERIOR OF SAID NOZZLE, MEANS IN SAID AIR SCOOPS PROVIDING A PLENUM CHAMBER THEREIN, AND AN IGNITABLE DUCTED ROCKET IN EACH OF SAID AIR SCOOPS POSITIONED TO INJECT AUXILIARY EXHAUST STREAMS INTO THE MAIN EXHAUST STREAM FLOWING THROUGH THE NOZZLE, SAID IGNITABLE DUCTED ROCKET IN EACH OF SAID AIR SCOOPS BEING SELECTIVELY OPERABLE TO PROVIDE THRUST VECTOR CONTROL FOR THE ROCKET MOTOR.