Pure fluid amplifier and pure fluid amplifier attitude control system for missiles

Claim 1

IN A MISSILE DISPOSED FOR FLIGHT IN A TRAJECTORY ENDING IN A TARGET, SAID MISSILE PROVIDED WITH CONTROL APPARATUS TO MAINTAIN THE MISSILE IN THE TRAJECTORY COMPRISING: (A) MECHANISM FOR DETECTING THE ATTITUDE OF THE MISSLE AND FOR PROVIDING A SIGNAL REPRESENTATIVE OF SAID ATTITUDE, (B) MEANS PROVIDING AN ERROR SIGNAL REPRESENTING THE DIFFERENCE BETWEEN SAID ATTITUDE SIGNAL AND A PREDETERMINED ATTITUDE REFERENCE SIGNAL, (C) A GAS GENERATOR CARRIED BY SAID MISSILE AND DISPOSED TO PRODUCE GAS AT A CONSTANT RATE DURING FLIGHT OF SAID MISSILE, (D) FLUID AMPLIFIER MEANS CARRIED BY SAID MISSILE IN COMMUNICATION WITH SAID GAS GENERATOR, SAID FLUID AMPLIFIER MEANS INCLUDING AN INLET DISPOSED TO RECEIVE SAID GAS FROM SAID GAS GENERATOR, A CHAMBER DISPOSED IN SAID AMPLIFIER IN COMMUNICATION WITH SAID INLET, A PAIR OF OUTLETS COMMUNICATING WITH SAID CHAMBER FOR EXPULSION OF SAID GAS THEREFROM, AND CONTROL MEANS FOR SELECTIVELY OPENING OPPOSITE SIDES OF SAID CHAMBER TO THE ATMOSPHERE TO ADMIT ATMOSPHERIC PRESSURE INTO SAID CHAMBER TO CREATE PRESSURE DIFFERENTIALS ACROSS SAID GAS FLOW AND THUS DIRECT SAID GAS THROUGH A PRESELECTED ONE OF SAID OUTLETS TO CONTROL YAW, PITCH AND ROLL ATTITUDE OF SAID MISSILE.