GB486823A - Improvements in or relating to aircraft wings - Google Patents
Improvements in or relating to aircraft wingsInfo
- Publication number
- GB486823A GB486823A GB17021/37A GB1702137A GB486823A GB 486823 A GB486823 A GB 486823A GB 17021/37 A GB17021/37 A GB 17021/37A GB 1702137 A GB1702137 A GB 1702137A GB 486823 A GB486823 A GB 486823A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- main wing
- auxiliary
- trailing edge
- main
- 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
- B64C9/16—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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Details Of Gearings (AREA)
Abstract
486,823. Trimming aircraft. DORNIER METALLBANTEN GES., and DORNIER, C. June 18, 1937, No. 17021. Convention date, Aug. 3, 1936. [Class 4] In a wing unit for aircraft in which a rigid main wing and at least one rigid or movable auxiliary wing are spaced a fractional part of the main wing chord from the main wing, the trailing edge of the main wing and the trailing edges of the auxiliary wings, other than the last one, if more than one auxiliary wing be provided, are each provided with one or more members displaceable in an upward or downward direction and extending over the length of the respective wing or part thereof. In one form, a main wing 1 and an auxiliary wing 2 are provided respectively with strips 4, 5 riveted, soldered or welded thereto. The strips 4, 5 are deformable but not resilient. In a modification, the auxiliary wing is disposed below and to the rear of the trailing edge of the main wing and in such a case the trailing edge is formed as a pivoted flap adjustable prior to flight through screw-and-nut mechanism. In a further modification, a pivoted flap 19 is adjustable by displacement of a cam slot 22. Specification 135,829, [Class 4], is referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE486823X | 1936-08-03 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB486823A true GB486823A (en) | 1938-06-10 |
Family
ID=6543508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB17021/37A Expired GB486823A (en) | 1936-08-03 | 1937-06-18 | Improvements in or relating to aircraft wings |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB486823A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3987983A (en) * | 1974-12-20 | 1976-10-26 | The Boeing Company | Trailing edge flaps having spanwise aerodynamic slot opening and closing mechanism |
-
1937
- 1937-06-18 GB GB17021/37A patent/GB486823A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3987983A (en) * | 1974-12-20 | 1976-10-26 | The Boeing Company | Trailing edge flaps having spanwise aerodynamic slot opening and closing mechanism |
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