Gyro controller

Abstract

Abstract A MISSILE SYSTEM HAVING A GYROSCOPE CONTROL MECHANISM FOR PROVIDING THE BALANCING TORQUE REQUIRED TO MAINTAIN A SPINNING MISSILE ON ITS PREDETERMINED FLIGHT COURSE. THE SYSTEM INCLUDES A MISSILE HAVING A CENTER OF GRAVITY, AN AXIS, A THROAT FOR EMITTING HOT GASES INTO OPPOSED EXHAUST PORTS. THE CONTROL MECHANISM FOR THE SYSTEM INCLUDES A GYROSCOPE HAVING A SPIN AXIS DISPOSED FOR COINCIDENCE WITH THE MISSILE AXIS. A RING IN THE GYROSCOPE MOUNTS A GIMBAL SHAFT THAT IS DISPOSED ACROSS THE THROAT AND IN NORMAL RELATION TO THE AXIS OF THE MISSILE. A SPLITTER VANE IS SECURED TO THE GIMBAL SHAFT IN THE THROAT TO INCREASE THE FLOW OF HOT GASES THROUGH ONE OF THE EXHAUST PORTS WHEN A DISTURBING TORQUE HAS CAUSED THE MISSILE AXIS TO BE OUT OF COINCIDENCE WITH THE GYROSCOPE AXIS. THIS INCREASE FLOW OF HOT GASES THROUGH ONE OF THE EXHAUST PORTS WILL PROVIDE A RESTORING TORQUE TO THE MISSILE AND RESTORE COINCIDENCE OF THE MISSILE AND GYROSCOPE AXES. THE MOVEMENT ARM OF THE GASES ACTING ON THE VANE ARE BALANCED OUT OR KEPT SMALL BY HAVING IT ACT ON THE CENTER OF GRAVITY OF THE GYROSCOPE CONTROL MECHANISM TO THEREBY ELIMINATE GYROSCOPE PRECESSION.

Inventors

• 👤 James V Johnston

Bibliographic Details