Attitude control system for sounding rockets

Claim 1

IN COMBINATION WITH A BALLISTIC VEHICLE HAVING A PROPELLANT SYSTEM, AN ATTITUDE CONTROL SYSTEM COMPRISING: A PAIR OF GYROSCOPES MOUNTED IN SAID VEHICLE EACH HAVING AN AXIS FIXED PARALLEL TO THE ROLL AXIS OF THE VEHICLE AND EACH HAVING A SECOND AXIS NORMALLY MUTUALLY ORTHOGONAL TO EACH OTHER, AND ONE OF SAID GYROSCOPES HAVING AN AXIS PARALLEL TO THE PITCH AXIS AND ONE OF SAID GYROSCOPES HAVING AN AXIS PARALLEL TO THE YAW AXIS OF THE VEHICLE; ROLL NOZZLE MEANS POSITIONED TO EXPEL GAS FROM THE VEHICLE TANGENTIALLY TO PRODUCE CORRECTION ROLL TORQUE UPON THE VEHICLE; PITCH NOZZLE MEANS POSITIONED TO EXPEL GAS FROM THE VEHICLE NORMAL TO THE PITCH AXIS OF THE VEHICLE; YAW NOZZLE MEANS POSITIONED TO EXPEL GAS FROM THE VEHICLE NORMAL TO THE YAW AXIS OF THE VEHICLE; A SUPPLY OF GAS FOR SAID NOZZLE MEANS; MEANS FOR SEQUENTIALLY APPLYING TORQUING SIGNALS TO SAID GYROSCOPE TO INTRODUCE ROLL, PITCH AND YAW CORRECTIONS INTO THE VEHICLE ORIENTATION; AND MEANS RESPONSIVE TO THE TERMINATION OF POWERED FLIGHT OF THE VEHICLE FOR COMMENCING OPERATION OF SAID LAST MEANS.