GB671336A - Improvements in or relating to automatic pilots for aircraft - Google Patents
Improvements in or relating to automatic pilots for aircraftInfo
- Publication number
- GB671336A GB671336A GB26310/48A GB2631048A GB671336A GB 671336 A GB671336 A GB 671336A GB 26310/48 A GB26310/48 A GB 26310/48A GB 2631048 A GB2631048 A GB 2631048A GB 671336 A GB671336 A GB 671336A
- Authority
- GB
- United Kingdom
- Prior art keywords
- energized
- aircraft
- valves
- servomotors
- control surface
- 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
- 238000004804 winding Methods 0.000 abstract 4
- 238000009738 saturating Methods 0.000 abstract 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
671,336. Automatic control systems for aircraft. BENDIX AVIATION CORPORATION. Oct. 8, 1948 [Dec. 31, 1947], No. 26310/48. Class 38 (iv). In an automatic pilot control system a main control surface has an auxiliary control surface mounted thereon, both surfaces being operated by separate electric servomotors energized simultaneously from the error detecting means. As shown, the gyro-vertical 14 detects deviation of an aircraft from normal attitude and generates an error signal in the winding 12 which is amplified at triode 21 and applied to the grids of phase discriminator valves 31, 32, the anodes of which are energized by the secondary winding of the transformer 34. The servomotors 15, 16 of the elevator and trim tab, respectively, are in parallel and energized from the opposed secondary windings of the saturable transformers 50, 51 of which the saturating windings 62, 63 are separately energized by the valves 31, 32. A follow-up signal is developed at the generator 25. Specification 662,831 is referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US671336XA | 1947-12-31 | 1947-12-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB671336A true GB671336A (en) | 1952-04-30 |
Family
ID=22073929
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB26310/48A Expired GB671336A (en) | 1947-12-31 | 1948-10-08 | Improvements in or relating to automatic pilots for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB671336A (en) |
-
1948
- 1948-10-08 GB GB26310/48A patent/GB671336A/en not_active Expired
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