Multiple jet pneumatic pulse duration modulation gyro

Abstract

Abstract A PULSE DURATION MODULATION GYRO SYSTEM FOR SENSING ATTITUDE DEVIATIONS OF A MISSLE FROM A PRESELECTED TRAJECTORY. THE GYRO SYSTEM INCLUDES A SPACE ORIENTED ROTOR THAT SPINS ON A HYDROSTATIC AIR BEARING ABOUT THE STATOR THEREFOR. TO PROVIDE THE AIR BEARING, A GAS IS INTRODUCED INTO A PLENUM CHAMBER WITHIN THE STATOR HOUSING. THE GAS IS DISPERSED THROUGH PASAGES RADIATING FROM THE CHAMBER TO THE SPHERICAL SURFACE OF THE STATOR, TERMINATING ADJACENT THE INNER SPHERICAL SURFACE OF THE ROTOR OR SPINNING WHEEL. THE EXHAUST OF THE AIR BEARING IS FEED INTO A PICKOFF CHAMBER WITHIN THE ROTOR AND EXHAUSTS AIR FROM A MULTIPLE OF AIR PORTS SPACED SYMMERTICALLY AROUND THE CIRCMFERENCE OF THE ROTOR AT AN ANGLE TO THE ROTOR EQUATOR. FOUR EVENLY SPACED PICKOFFS PROVIDE AN OUTPUT SIGNAL IN RESPONSE TO GAS ESCAPTING THROUGH THE AIR PORTS, PERIODICALLY IMPINGING ON THE PICKOFF INPUTS. WHEN THE GYRO IS SUBJECTED TO AN INPUT RATE, THE ROTOR AND STATOR ARE CHANGE IN REFERENCE TO EACH OTHER, CHANGING THE NUMBER OF PORTS ROTATING PAST EACH PICKOFF AND THEREBY CHANGING THE PERIOD THAT THE GAS IMPINGS ON THE PICKOFFS. THUS, A VARIABLE OUTPUT SIGNAL INDICATING THE DIRECTION OF CHANGE IN TRAJECTORY IS PROVIDED.

Inventors

• 👤 William W Stripling
• 👤 David L Jones

Bibliographic Details