Braking Device for Aircraft Gyroscope.

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Abstract:

The patent application provides means for electronically braking gyroscope rotation and for reducing the normal unbraked rundown time of an aircrafts 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 Lenzs Law and dynamic braking of the gyroscope is accomplished.

Author(s):
Lyon, Erwin B.
Author Organization(s):
DEPARTMENT OF THE AIR FORCE WASHINGTON D C
Descriptive Note:
Patent Application,
Pagination:
0009

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Government-owned Invention Available For Licensing. Copy Of Application Available Ntis.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
PAT-APPL-492 076
 Subject Terms
Communities of Interest:
Air Platforms
Descriptor(s):
*Aircraft, *Gyroscopes, *Braking, Patents, Silicon controlled rectifiers, Direct current, Timing circuits
Field(s)/Group(s):
Aircraft
Keyword(s):
*Patent applications, PAT CL 318 212
Report Date:
1974 Jul 26