GB425645A - Improvements in or relating to aircraft - Google Patents
Improvements in or relating to aircraftInfo
- Publication number
- GB425645A GB425645A GB4928/34A GB492834A GB425645A GB 425645 A GB425645 A GB 425645A GB 4928/34 A GB4928/34 A GB 4928/34A GB 492834 A GB492834 A GB 492834A GB 425645 A GB425645 A GB 425645A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fins
- aircraft
- langley
- convergence
- angle
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Surgical Instruments (AREA)
Abstract
425,645. Aircraft. FAIREY AVIATION CO., Ltd., Cranford Lane, Hayes, Middlesex, and LOBELLE, M. J. O., Ludlow, Langley Road, Langley, Buckinghamshire. Feb. 14, 1934, No. 4928. [Class 4] In an aircraft fuselage provided with fins running longitudinally in substantially the direction of the airflow along the aft end thereof in proximity tc the tail unit, the fins being arranged symmetrically in pairs and converging the angle of convergence of the fins may be varied by turning the fins about longitudinal axes. The fins may be of rectangular or semicircular shape and of thin and symmetrical crosssection, or they may have an asymmetrical aerofoil or other aerodynamic section. The angle of convergence of the fins 17 is adjusted through shafts 21, levers 20, 18 and a link 19.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4928/34A GB425645A (en) | 1934-02-14 | 1934-02-14 | Improvements in or relating to aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4928/34A GB425645A (en) | 1934-02-14 | 1934-02-14 | Improvements in or relating to aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB425645A true GB425645A (en) | 1935-03-19 |
Family
ID=9786496
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4928/34A Expired GB425645A (en) | 1934-02-14 | 1934-02-14 | Improvements in or relating to aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB425645A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2573562A (en) * | 1946-07-16 | 1951-10-30 | Maurice A Garbell Inc | Fluid-dynamic stabilizer and damper |
US2630985A (en) * | 1950-12-07 | 1953-03-10 | United Aircraft Corp | Helicopter stabilizer |
US2999657A (en) * | 1958-02-17 | 1961-09-12 | Chance Vought Corp | Stabilizing means for aircraft |
US3384326A (en) * | 1965-08-24 | 1968-05-21 | Francis G. Neubeck | Aerodynamic strake |
US5096143A (en) * | 1989-09-04 | 1992-03-17 | William Nash | Tail unit with rotatable tailplane |
-
1934
- 1934-02-14 GB GB4928/34A patent/GB425645A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2573562A (en) * | 1946-07-16 | 1951-10-30 | Maurice A Garbell Inc | Fluid-dynamic stabilizer and damper |
US2630985A (en) * | 1950-12-07 | 1953-03-10 | United Aircraft Corp | Helicopter stabilizer |
US2999657A (en) * | 1958-02-17 | 1961-09-12 | Chance Vought Corp | Stabilizing means for aircraft |
US3384326A (en) * | 1965-08-24 | 1968-05-21 | Francis G. Neubeck | Aerodynamic strake |
US5096143A (en) * | 1989-09-04 | 1992-03-17 | William Nash | Tail unit with rotatable tailplane |
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