GB577779A - Improvements relating to wing flaps for aircraft - Google Patents
Improvements relating to wing flaps for aircraftInfo
- Publication number
- GB577779A GB577779A GB9797/38A GB979738A GB577779A GB 577779 A GB577779 A GB 577779A GB 9797/38 A GB9797/38 A GB 9797/38A GB 979738 A GB979738 A GB 979738A GB 577779 A GB577779 A GB 577779A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flap
- wing
- link
- jack
- aircraft
- 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
- 235000021538 Chard Nutrition 0.000 abstract 1
- 238000006073 displacement reaction Methods 0.000 abstract 1
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
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
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
-
- 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
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
577,779. Controlling aircraft. GENERAL AIRCRAFT, Ltd., and WILLIAMS, L. C. March 30, 1938, No. 9797. [Class 4] An aircraft flap arrangement includes an auxiliary aerofoil housed in its inoperative position in a recess in the upper side of a main aerofoil and connected thereto by mechanism permitting the auxiliary aerofoil to be displaced bodily in a rearward and vertical sense, the angle of incidence of the auxiliary aerofoil being increased during at least part of such displacement. In one form, the flap B is nested normally in the trailing portion of the upper surface of the wing A and is connected to the wing by links 10, 11. The flap is extended by operation of a jack 16 connected to an arm 19 secured to a torque tube 20 carrying the link 10. The flap has a chord 20 per cent to 30 per cent of the wing chard. In a modification, the link 11 is pivoted to a bracket 28, the link 10 is pivoted to an arm 29. On extension of a jack 16 the flap may be adjusted to the position B<3>, Fig. 2A, and on turning the arm 29 to the position B<2>. In a further modication, the link 11 is constituted by a jack and both the jack and the link 10 are pivoted to a bracket beneath the wing. In this form the flap may uncover a wing slot. In another form the link 10 consists of a jack the upper end of which moves in a fixed guide. In further forms the flap is operatively interconnected with a further flap nested normally beneath the trailing leverportion of the wing. In still further forms the flap is adjustable to a position symmetrically above and below the trailing edge of the wing and in one such case the links carrying the flap have a common pivot on a bracket on the wing. According to the Provisional Specification the trailing edge of the flap may be guided rearwardly whilst the leading edge is displaced upwards and rearwardly.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9797/38A GB577779A (en) | 1938-03-30 | 1938-03-30 | Improvements relating to wing flaps for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9797/38A GB577779A (en) | 1938-03-30 | 1938-03-30 | Improvements relating to wing flaps for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB577779A true GB577779A (en) | 1946-05-31 |
Family
ID=9878953
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9797/38A Expired GB577779A (en) | 1938-03-30 | 1938-03-30 | Improvements relating to wing flaps for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB577779A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3260477A (en) * | 1964-01-31 | 1966-07-12 | William E Grahame | Flap assembly for aircraft |
US4007896A (en) * | 1975-08-08 | 1977-02-15 | Reynolds Iii Collins J | Upwardly extendible wing flap system |
CN110562442A (en) * | 2019-08-29 | 2019-12-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Flap device adopting semi-flexible drive control |
CN115924060A (en) * | 2023-02-22 | 2023-04-07 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Asymmetric airfoil inversion mechanism based on connecting rod assembly and use method thereof |
-
1938
- 1938-03-30 GB GB9797/38A patent/GB577779A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3260477A (en) * | 1964-01-31 | 1966-07-12 | William E Grahame | Flap assembly for aircraft |
US4007896A (en) * | 1975-08-08 | 1977-02-15 | Reynolds Iii Collins J | Upwardly extendible wing flap system |
CN110562442A (en) * | 2019-08-29 | 2019-12-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Flap device adopting semi-flexible drive control |
CN110562442B (en) * | 2019-08-29 | 2022-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Flap device adopting semi-flexible drive control |
CN115924060A (en) * | 2023-02-22 | 2023-04-07 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Asymmetric airfoil inversion mechanism based on connecting rod assembly and use method thereof |
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