GB541258A - Improvements relating to aeroplane flaps - Google Patents
Improvements relating to aeroplane flapsInfo
- Publication number
- GB541258A GB541258A GB11598/40A GB1159840A GB541258A GB 541258 A GB541258 A GB 541258A GB 11598/40 A GB11598/40 A GB 11598/40A GB 1159840 A GB1159840 A GB 1159840A GB 541258 A GB541258 A GB 541258A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- front portion
- pivoted
- link
- control link
- 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
- 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
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
-
- 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)
- Air-Flow Control Members (AREA)
Abstract
541,258. Controlling aircraft. YOUNGMAN, R. T. July 12, 1940, No. 11598. [Class 4] In an aircraft split flap &c. comprising front and rear portions a, c, the latter being pivotally mounted in relation to the former and partaking of its movement, the rear portion is provided with a control link b which causes it to pivot relatively to the front portion to an extent corresponding, with the extent of movement of this portion and to rotate in the opposite direction to the front portion. This causes a slot to be formed between the positions and the rear portion to be at a negative angle of incidence to the air stream. In the form shown in Fig. 1, the portions are of the cross-sections illustrated, the front portion being pivoted at g to the wing d and the rear portion being pivotally mounted at e on brackets f extending rearwardly from the front portion. The control link is pivoted at j to the wing d and to the rear portion at k rearwardly of the pivotal axis at e. In a modification, the split flat a-c, Fig. 2, comprises the whole thickness of the wing, the front portion being pivotally mounted on an axis g beneath the wing d by means of brackets m so that in operation a slot n is formed therebetween. The front end of the control link h is pivoted at j to a bracket o extending rearwardly from the wing, the axis j being positioned as shown. In a modified mounting of the form of split flap shown in Fig. 1, the front portion a, Fig. 3, is carried by two links p, q of unequal length, the link p being pivoted at one end r to the wing and at its other end to the undersurface of the front portion at s near its trailing edge, and the link q being pivoted at one end u to the wing in the region shown and at its other end to the upper surface of the front portion at t near its leading edge. The front end of the control link h is pivotally connected to the link q at a point v about midway of its length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB11598/40A GB541258A (en) | 1940-07-12 | 1940-07-12 | Improvements relating to aeroplane flaps |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB11598/40A GB541258A (en) | 1940-07-12 | 1940-07-12 | Improvements relating to aeroplane flaps |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB541258A true GB541258A (en) | 1941-11-19 |
Family
ID=9989186
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB11598/40A Expired GB541258A (en) | 1940-07-12 | 1940-07-12 | Improvements relating to aeroplane flaps |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB541258A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572381A (en) * | 2022-04-19 | 2022-06-03 | 中国商用飞机有限责任公司 | Tail cone with speed reducing assembly and airplane provided with tail cone |
-
1940
- 1940-07-12 GB GB11598/40A patent/GB541258A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572381A (en) * | 2022-04-19 | 2022-06-03 | 中国商用飞机有限责任公司 | Tail cone with speed reducing assembly and airplane provided with tail cone |
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