GB298508A - Improvements in means for controlling aeroplanes - Google Patents
Improvements in means for controlling aeroplanesInfo
- Publication number
- GB298508A GB298508A GB1827527A GB1827527A GB298508A GB 298508 A GB298508 A GB 298508A GB 1827527 A GB1827527 A GB 1827527A GB 1827527 A GB1827527 A GB 1827527A GB 298508 A GB298508 A GB 298508A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- section
- links
- sections
- main wing
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
- B64C9/24—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
298,508. Page, F. H., and Page, Ltd., H. July 9, 1927. Balancing, and regulating altitude; planes and the like, construction of.-A wing-member is mounted on links or slides on the front or rear of the main wing so that at small angles of incidence it is in contact with the main wing, but as the angle of incidence increases, owing to the change in pressure on the auxiliary wing surfaces, the latter automatically moves away from the main wing to a position of equilibrium or to a position limited by a stop, thus forming a slot between the two wing members. In one modification, Fig. 2, the forward wing-section B is mounted on links E, F pivoted to a bracket G on the main wing A, when the latter is not deep enough to enclose the links. When closed, the section B preferably forms part of the main wing, and the forward link E is the shorter so that, when forward, the slot is wider at its entrance. In this modification, the section B takes up a position of equilibrium. In the construction shown in Fig. 5, the forward section B carries a channel member H which engages rollers J, J' on the main plane bracket. The roller J<1> is vertically adjustable to vary the path of the section B, and a buffer K and stop L limit the movement thereof. In Figs. 9 and 10, the section B is hinged to horizontally-swinging links N, pivoted to brackets R carried by the forward spar S of the wing. A spring T may be provided as shown to prevent the section B sticking at the dead centre of the links, or alternatively, stops may be provided at the pivots of the links to prevent the links exceeding an angle of 60‹, say, with the leading edge. Controlling springs may be provided for any modification. The forward section may extend across the major portion of the wings in large or small sections. The movement of the forward sections may be damped by dashpots, elastic cushions or the like. Automatic forward wing-members may be located in front of the ailerons either alone or conjointly with the members along the leading edge, and the said members may be mechanically connected by lostmotion devices to the ailerons so that abnormal upward movment of the latter tends to close the slot, as for instance in Specification 223,202. The automatic forward-sections may be connected to pivoted flaps on the trailing edge of the main wing so that forward movement of the said sections pulls down the flap. Forward and rearward sections adapted to move automatically in the manner described may be used in conjunction with each other. According to the Provisional Specification, the automatic operation of the forwardly-located aerofoil may be assisted by hand-operated means.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1827527A GB298508A (en) | 1927-07-09 | 1927-07-09 | Improvements in means for controlling aeroplanes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1827527A GB298508A (en) | 1927-07-09 | 1927-07-09 | Improvements in means for controlling aeroplanes |
Publications (1)
Publication Number | Publication Date |
---|---|
GB298508A true GB298508A (en) | 1928-10-09 |
Family
ID=10109654
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1827527A Expired GB298508A (en) | 1927-07-09 | 1927-07-09 | Improvements in means for controlling aeroplanes |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB298508A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2311969A (en) * | 1996-04-13 | 1997-10-15 | Michael Craig Broadbent | Variable camber wing mechanism |
US6015117A (en) * | 1996-04-13 | 2000-01-18 | Broadbent; Michael C | Variable camber wing mechanism |
US6682023B2 (en) | 2001-06-15 | 2004-01-27 | Michael Craig Broadbent | Contiguous variable camber device |
EP3395679A1 (en) * | 2017-04-28 | 2018-10-31 | Airbus Operations GmbH | Wing for an aircraft |
WO2018197265A1 (en) * | 2017-04-28 | 2018-11-01 | Airbus Operations Gmbh | Wing for an aircraft |
RU2746479C1 (en) * | 2017-04-28 | 2021-04-14 | Эйрбас Оперейшнз Гмбх | Aircraft wing console |
US11286033B2 (en) * | 2019-03-29 | 2022-03-29 | Airbus Operations Gmbh | Wing for an aircraft |
-
1927
- 1927-07-09 GB GB1827527A patent/GB298508A/en not_active Expired
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2311969A (en) * | 1996-04-13 | 1997-10-15 | Michael Craig Broadbent | Variable camber wing mechanism |
GB2311969B (en) * | 1996-04-13 | 1999-09-22 | Michael Craig Broadbent | Variable camber wing mechanism |
US6015117A (en) * | 1996-04-13 | 2000-01-18 | Broadbent; Michael C | Variable camber wing mechanism |
US6682023B2 (en) | 2001-06-15 | 2004-01-27 | Michael Craig Broadbent | Contiguous variable camber device |
JP2020517524A (en) * | 2017-04-28 | 2020-06-18 | エアバス オペレーションズ ゲーエムベーハーAirbus Operations GmbH | Aircraft wing |
RU2752205C2 (en) * | 2017-04-28 | 2021-07-23 | Эйрбас Оперейшнз Гмбх | Aircraft wing console |
CN108791809A (en) * | 2017-04-28 | 2018-11-13 | 空中客车运作有限责任公司 | Aircraft wing |
CN110573422A (en) * | 2017-04-28 | 2019-12-13 | 空中客车运作有限责任公司 | Wing of an aircraft |
EP3395679A1 (en) * | 2017-04-28 | 2018-10-31 | Airbus Operations GmbH | Wing for an aircraft |
RU2746479C1 (en) * | 2017-04-28 | 2021-04-14 | Эйрбас Оперейшнз Гмбх | Aircraft wing console |
US11034433B2 (en) | 2017-04-28 | 2021-06-15 | Airbus Operations Gmbh | Wing for an aircraft |
WO2018197265A1 (en) * | 2017-04-28 | 2018-11-01 | Airbus Operations Gmbh | Wing for an aircraft |
US11186356B2 (en) | 2017-04-28 | 2021-11-30 | Airbus Operations Gmbh | Wing for an aircraft |
EP4151522A1 (en) * | 2017-04-28 | 2023-03-22 | Airbus Operations GmbH | Wing for an aircraft |
CN108791809B (en) * | 2017-04-28 | 2022-10-11 | 空中客车运作有限责任公司 | Aircraft wing |
US11565789B2 (en) | 2017-04-28 | 2023-01-31 | Airbus Operations Gmbh | Wing for an aircraft |
US11577819B2 (en) | 2017-04-28 | 2023-02-14 | Airbus Operations Gmbh | Wing for an aircraft |
US11286033B2 (en) * | 2019-03-29 | 2022-03-29 | Airbus Operations Gmbh | Wing for an aircraft |
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