Accession Number : ADD000387

Title :   Braking Device for Aircraft Gyroscope.

Descriptive Note : Patent Application,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Lyon,Erwin B

Report Date : 26 Jul 1974

Pagination or Media Count : 9

Abstract : The patent application provides means for electronically braking gyroscope rotation and for reducing the normal unbraked rundown time of an aircraft's gyroscope driving motor. The devices disclosed provide for temporary application of DC current from the aircraft battery to the stator of the gyroscope drive motor. This is automatically accomplished with a fail safe circuit which connects one polarity DC voltage from the aircraft battery to two of the three phase windings of the gyroscope drive motor stator and the other polarity of DC voltage to the third winding. A direct current produced magnetic field is thus set up in the stator windings. The spinning rotor (during rundown) interacts with the magnetic field in accordance with Lenz's Law and dynamic braking of the gyroscope is accomplished.

Descriptors :   *Aircraft, *Gyroscopes, *Braking, Patents, Silicon controlled rectifiers, Direct current, Timing circuits

Subject Categories : Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE