GB576125A - Improvements in aircraft supporting surfaces - Google Patents
Improvements in aircraft supporting surfacesInfo
- Publication number
- GB576125A GB576125A GB1039942A GB1039942A GB576125A GB 576125 A GB576125 A GB 576125A GB 1039942 A GB1039942 A GB 1039942A GB 1039942 A GB1039942 A GB 1039942A GB 576125 A GB576125 A GB 576125A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- tip
- aircraft
- flaps
- tips
- 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
- B64C5/00—Stabilising surfaces
- B64C5/08—Stabilising surfaces mounted on, or supported by, wings
Abstract
576,125. Controlling aircraft. PHILLIPS & POWIS AIRCRAFT, Ltd., and HEAL, L. C. July 24, 1942, No. 10399. [Class 4] An aircraft wing tip is pivoted about a fore- and-aft axis so as to be turnable upwards or downwards into a vertical position, and split flaps at' the trailing edges of the tip portions are independently or differentially operable while the tip portions are in their vertical position. The tips may be movable simultaneously with retractable landing gear. Fig. 1 shows a plan of a swept-back wing having a tip portion 21 which is normally locked in line with the wing but can be turned about a hinge 22 into a vertical plane. Control surfaces 23' are provided' on the main part of the wing. The rear edge of the tip mounts a split flap 24, the flaps on the two sides of the machine being operable independently for manoeuvring the aircraft. Owing to the hinge 26 of each split flap being rearwardly inclined when the tip is in the vertical position, any opening of the flap results not only in an increased drag but also introduces a downward force on the wing. When the main wing is at a dihedral angle, the wing tip may be turned upwards into a position perpendicular to it. Fig. 7 shows hydraulic means for simultaneously raising the wing tip 21 and lowering a retractable undercarriage for which purpose they are respectively connected to pistons 32, 29 working in a cylinder 32 divided by a partition 28 and having ports 38, 39, 40. A single control valve may effect the movement and locking of the pistons or separate valves may be used. The tips 21 and undercarriage may be independently movable. The invention is particularly applicable to a tail-less aircraft, elevators and flaps being provided on the main part of the wing and the adjustable surfaces on the tips acting as ailerons during normal flight.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1039942A GB576125A (en) | 1942-07-24 | 1942-07-24 | Improvements in aircraft supporting surfaces |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1039942A GB576125A (en) | 1942-07-24 | 1942-07-24 | Improvements in aircraft supporting surfaces |
Publications (1)
Publication Number | Publication Date |
---|---|
GB576125A true GB576125A (en) | 1946-03-20 |
Family
ID=9967103
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1039942A Expired GB576125A (en) | 1942-07-24 | 1942-07-24 | Improvements in aircraft supporting surfaces |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB576125A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2872137A (en) * | 1955-07-11 | 1959-02-03 | United Aircraft Corp | Sectional aircraft fuselage |
US2940693A (en) * | 1954-09-20 | 1960-06-14 | Fairey Aviat Ltd | Aircraft fins |
FR2521520A1 (en) * | 1982-02-15 | 1983-08-19 | Daude Martine | MARGINAL FINS WITH VARIABLE ANGLES OF ATTACK |
GB2282996A (en) * | 1993-10-19 | 1995-04-26 | Short Brothers Plc | Aircraft flight control system |
US7988099B2 (en) | 2001-06-21 | 2011-08-02 | Airbus Operations Limited | Winglet |
CN105480406A (en) * | 2015-12-31 | 2016-04-13 | 歌尔科技有限公司 | Single-axis aircraft |
-
1942
- 1942-07-24 GB GB1039942A patent/GB576125A/en not_active Expired
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2940693A (en) * | 1954-09-20 | 1960-06-14 | Fairey Aviat Ltd | Aircraft fins |
US2872137A (en) * | 1955-07-11 | 1959-02-03 | United Aircraft Corp | Sectional aircraft fuselage |
FR2521520A1 (en) * | 1982-02-15 | 1983-08-19 | Daude Martine | MARGINAL FINS WITH VARIABLE ANGLES OF ATTACK |
GB2282996A (en) * | 1993-10-19 | 1995-04-26 | Short Brothers Plc | Aircraft flight control system |
GB2282996B (en) * | 1993-10-19 | 1997-04-09 | Short Brothers Plc | Aircraft flight control system |
US7988099B2 (en) | 2001-06-21 | 2011-08-02 | Airbus Operations Limited | Winglet |
CN105480406A (en) * | 2015-12-31 | 2016-04-13 | 歌尔科技有限公司 | Single-axis aircraft |
CN105480406B (en) * | 2015-12-31 | 2017-07-21 | 歌尔科技有限公司 | A kind of single shaft aircraft |
US10336434B2 (en) | 2015-12-31 | 2019-07-02 | Goertek Technology Co., Ltd. | Single-shaft aerial vehicle |
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