Thrust vector control arrangement

Claim 1

A CONTROL FOR DIRECTING THE FLIGHT PATH OF A ROCKET PROPELLED VEHICLE BY MODIFYING THE MAIN THRUST JET OF THE ROCKET THROUGH THE USE OF THRUST VECOTR CONTROL SECONDARY INJECTION COMPRISING: A NOZZLE THROUGH WHICH EXHAUSTS THE MAIN THRUST JET; A SOURCE OF LIQUID TO BE GASIFIED AND INJECTED ANGULARLY INTO THE MAIN THRUST JET TO CONTROL ITS THRUST VECTOR; A GASIFYING CHAMBER INCLUDING AN INTERIOR WALL SURFACE RECEIVNG LIQUID FROM THE SOURCE AND HAVING AN OUTLET COMMUNICATION WITH THE MAIN THRUST JET IN THE NOZZLE, SAID CHAMBER BEING JACKETED AND THE SPACED BETWEEN THE INTERIOR AND EXTERIOR WALLS THEREOF BEING IN COMMINICATION WITH THE MAIN JET STREAM, THE INTERIOR WALL SURFACE BEING HEATED BY A PORTION OF HOT GAS BLED FROM THE MAIN JET, SAID GASIFYING CHAMBER BEING EXTERIOR OF THE NOZZLE; A SPRAY NOZZLE RECEIVING AND DISTRIBUTING THE LIQUID OVER THE WALL SURFACE OF THE CHAMBER; AND VALVE MEANS CONTROLLING THE FLOW OF LIQUID FROM THE SOURCE THROUGH THE SPRAY NOZZLE.