Pneumatic missile guidance system

Claim 1

A PNEUMATIC SYSTEM FOR MAINTAINING THE PREDETERMINED ATTITUDE OF A FLIGHT COMPRISING CONTROL MEANS MOVABLE IN RESPONSE TO A FORCE CAUSING DEVIATION OF THE MISSILE FROM ITS PREDETERMINED ATTITUDE, PNEUMATIC SENSING MEANS MOUNTED STATIONARY ON THE MISSILE AND OPERABLE TO PRODUCE A FIRST PNEUMATIC SIGNAL REPRESENTATIVE OF THE DISPLACEMENT OF SAID CONTROL MEANS, PNEUMATIC BALANCING MEANS OPERATIVELY CONNECTED TO SAID CONTROL MEANS AND COOPERABLE WITH SAID SENSING MEANS TO PROVIDE A BALANCING FORCE TO SAID CONTROL MEANS DURING SENSING, PNEUMATIC MEANS OPERATIVELY CONNECTED TO SAID SENSING MEANS FOR DIFFERENTIATING SAID FIRST SIGNAL TO PRODUCE A SECOND PNEUMATIC SIGNAL REPRESENTATIVE OF THE RATE OF DISPLACEMENT OF SAID CONTROL MEANS, PNEUMATIC MEANS FOR AMPLIFYING THE FIRST AND SECOND SIGNALS, A SUMMING PNEUMATIC RELAY FOR ADDING THE FIRST AND SECOND AMPLIFIED SIGNALS, PNEUMATIC SERVO REGULATOR MEANS OPERATIVELY CONNECTED TO THE OUTPUT OF SAID SUMMING MEANS, AND PNEUMATIC THRUST MEANS FIXED ON THE MISSILE, OPERATIVELY CONNECTED TO AND CONTROLLED BY SAID SERVO REGULATOR MEANS FOR PROVIDING A CORRECTIVE FORCE TO THE MISSILE IN A DIRECTION AND MAGNITUDE OPPOSITE TO THE INITIAL FORCE CAUSING DEVIATION OF THE MISSILE.