GB145459A - Improvements in indicators for the turning of aircraft about a vertical axis - Google Patents
Improvements in indicators for the turning of aircraft about a vertical axisInfo
- Publication number
- GB145459A GB145459A GB16579/20A GB1657920A GB145459A GB 145459 A GB145459 A GB 145459A GB 16579/20 A GB16579/20 A GB 16579/20A GB 1657920 A GB1657920 A GB 1657920A GB 145459 A GB145459 A GB 145459A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pendulum
- aircraft
- turning
- gyroscopic
- deflexion
- 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
- G01C19/42—Rotary gyroscopes for indicating rate of turn; for integrating rate of turn
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Indicating Or Recording The Presence, Absence, Or Direction Of Movement (AREA)
Abstract
145,459. Ansch³tz & Co. March 24, 1917, [Convention date]. Gyroscopic apparatus.- A turn-indicator for aircraft comprises a simple pendulum 6 and a gyroscopic pendulum 10, mounted in co-linear bearings 4, 5 and 7, 8 respectively, the line of these bearings lying in the direction of flight. The axis of rotation of the rotor 12 is parallel to the transverse axis of the aircraft. The pendulums carry pointers 13, 14 moving over a common scale 15, turning of the aircraft about the vertical being indicated by relative movement between the pointers. The dimensions and speed of rotation of the gyroscope are preferably so adjusted that the gyroscopic deflexion on turning is approximately equal and opposite to the deflexion of the pendulum due to centrifugal force, so that the pendulum 10 remains approximately in the true vertical. The pendulum 6 may be replaced by a liquid level.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE145459X | 1917-03-24 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB145459A true GB145459A (en) | 1921-04-21 |
Family
ID=5670759
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB16579/20A Expired GB145459A (en) | 1917-03-24 | 1920-06-18 | Improvements in indicators for the turning of aircraft about a vertical axis |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB145459A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2437175A (en) * | 1942-12-08 | 1948-03-02 | Jr Thomas O Summers | Gyroscopic flight indicating instrument |
AT386197B (en) * | 1986-01-08 | 1988-07-11 | Glaxo Group Ltd | METHOD FOR PRODUCING NEW INDOLDER DERIVATIVES |
-
1920
- 1920-06-18 GB GB16579/20A patent/GB145459A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2437175A (en) * | 1942-12-08 | 1948-03-02 | Jr Thomas O Summers | Gyroscopic flight indicating instrument |
AT386197B (en) * | 1986-01-08 | 1988-07-11 | Glaxo Group Ltd | METHOD FOR PRODUCING NEW INDOLDER DERIVATIVES |
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