GB930695A - Improvements in or relating to gyro-magnetic compass systems - Google Patents
Improvements in or relating to gyro-magnetic compass systemsInfo
- Publication number
- GB930695A GB930695A GB679661A GB679661A GB930695A GB 930695 A GB930695 A GB 930695A GB 679661 A GB679661 A GB 679661A GB 679661 A GB679661 A GB 679661A GB 930695 A GB930695 A GB 930695A
- Authority
- GB
- United Kingdom
- Prior art keywords
- detector
- gyro
- aircraft
- magnetic
- discrepancy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/02—Rotary gyroscopes
- G01C19/34—Rotary gyroscopes for indicating a direction in the horizontal plane, e.g. directional gyroscopes
- G01C19/36—Rotary gyroscopes for indicating a direction in the horizontal plane, e.g. directional gyroscopes with north-seeking action by magnetic means, e.g. gyromagnetic compasses
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Control Of Electric Motors In General (AREA)
Abstract
930,695. Gyro-magnetic compasses. S. SMITH & SONS (ENGLAND) Ltd. Feb. 23, 1962 [Feb. 24,1961), No. 6796/61. Class 40 (1). A gyro-magnetic compass system for an aircraft has a servo-loop including a gyroscope 1, a course defining device to generate signals representing the aircraft heading relative to a reference direction provided by the gyroscope, a magnetic detector 17 generating a signal representing the aircraft heading relative to the direction of the horizontal component of the earth's magnetic field, means 13 for generating a discrepancy signal representing any difference between the two aircraft heading signals, and means for controlling the course defining device to reduce any discrepancy towards zero, and the system further includes means 25 (Fig. 2) for measuring the vertical component of the earth's field, means 21, 22, 24 for modifying the signal in accordance with the angle of tilt of the detector caused by Coriolis' force and means for combining the modified signal with the signals from the magnetic detector so as to compensate for errors thereof due to tilting by Coriolis' force. Associated with gyro 1 is a synchro transmitter 3 connected to synchro control transformer 7 arranged in a subsidiary seivo loop 10, 11 so that the position of shaft 9, registered at 12, indicates the aircraft heading relative to the gyro reference. Magnetic heading detector 17 is gimbal mounted to normally lie horizontally and feeds to the stator windings of synchro resolver 14 a signal representing the aircraft heading relative to the horizontal component of the earth's field. Shaft 9 positions the rotor of rotor 14 and any discrepancy output is applied to torque motor 2 to precess the gyro and reduce the discrepancy. Alternatively the resolver output may be applied to a motor driving one part of a differential synchro between transmitter 3 and transformer 7. A corrector circuit (Fig. 2) is connected in series with transverse winding 16 of detector 17 and includes, in series with vertical field coil 25, a potentiometer 24 tapped in accordance with the aircraft speed V. Further potentiometer 22 is tapped in accordance with the sine of the latitude A of the aircraft. The angle of tilt of detector 17 caused by Coriolis' force is stated to be proportional to V sin # and the consequent error in output from the magnetic detector is stated to be proportional to the sine of this angle, or since it is small, to the angle itself. The speed and latitude may be set manually or automatically. The speed-setting potentiometer may be a switchable network, rather than continuously variable, and a network of this type, having substantially constant input and output impedance is described (Fig. 3, not shown).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB679661A GB930695A (en) | 1961-02-24 | 1961-02-24 | Improvements in or relating to gyro-magnetic compass systems |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB679661A GB930695A (en) | 1961-02-24 | 1961-02-24 | Improvements in or relating to gyro-magnetic compass systems |
Publications (1)
Publication Number | Publication Date |
---|---|
GB930695A true GB930695A (en) | 1963-07-10 |
Family
ID=9820919
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB679661A Expired GB930695A (en) | 1961-02-24 | 1961-02-24 | Improvements in or relating to gyro-magnetic compass systems |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB930695A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2917532A1 (en) * | 1978-05-01 | 1979-11-08 | Sperry Rand Corp | METHOD AND DEVICE FOR COMPENSATING ERRORS IN THE LEVEL OUTPUT SIGNAL OF A MAGNETIC AZIMUTH DETECTOR |
DE3736386A1 (en) * | 1986-10-27 | 1988-07-14 | Pioneer Electronic Corp | VEHICLE BORING PROCESS |
-
1961
- 1961-02-24 GB GB679661A patent/GB930695A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2917532A1 (en) * | 1978-05-01 | 1979-11-08 | Sperry Rand Corp | METHOD AND DEVICE FOR COMPENSATING ERRORS IN THE LEVEL OUTPUT SIGNAL OF A MAGNETIC AZIMUTH DETECTOR |
DE3736386A1 (en) * | 1986-10-27 | 1988-07-14 | Pioneer Electronic Corp | VEHICLE BORING PROCESS |
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