GB819665A - Improvements in or relating to high speed aircraft - Google Patents
Improvements in or relating to high speed aircraftInfo
- Publication number
- GB819665A GB819665A GB2467156A GB2467156A GB819665A GB 819665 A GB819665 A GB 819665A GB 2467156 A GB2467156 A GB 2467156A GB 2467156 A GB2467156 A GB 2467156A GB 819665 A GB819665 A GB 819665A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- aircraft
- occur
- control
- flutter
- 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
- B64C39/00—Aircraft not otherwise provided for
- B64C39/04—Aircraft not otherwise provided for having multiple fuselages or tail booms
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
819,665. Aircraft control surfaces. NATIONAL RESEARCH DEVELOPMENT CORPORATION. July 19, 1957, No. 24671/56. Class 4. An aircraft has separate pitch and/or roll control surfaces carried forwardly or rearwardly of the main wing on port and starboard substantially rigid supporting means extending from and rigid with the wing, and secured to the wing inboard of the tips and outboard of 0À4 of the semi-span from the wing root. An aircraft with a fuselage 11, swept back wings 12, a fin 13, and a rudder 14 is shown. Booms 16 formed by forward extensions of the engine assemblies support surfaces 15, on which are movable together about axes parllel to the aircraft OY axis for pitch control, and are movable differentially about those axes for roll control, either by a pilot's control column or an automatic pilot. Each boom is preferably located at between 0À5 and 0À7 of the wing semi-span from the wing root. By these means the speed at which flutter would occur and that at which aileron control reversal would occur are raised. In another embodiment, the wings are swept forward and the surfaces 15 are mounted on rearwardly extending booms. In this case, the speed at which flutter would occur and that at which aero-elastic divergence of the wing would occur are raised.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2467156A GB819665A (en) | 1956-08-13 | 1956-08-13 | Improvements in or relating to high speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2467156A GB819665A (en) | 1956-08-13 | 1956-08-13 | Improvements in or relating to high speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB819665A true GB819665A (en) | 1959-09-09 |
Family
ID=10215429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2467156A Expired GB819665A (en) | 1956-08-13 | 1956-08-13 | Improvements in or relating to high speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB819665A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3030728A1 (en) * | 1980-08-14 | 1982-02-18 | Dornier Gmbh, 7990 Friedrichshafen | Steering gear, partic. rudders, for aircraft or missiles - use delta-wing fins outboard on elevator rotatable about two perpendicular axes |
| DE3133957A1 (en) * | 1981-08-27 | 1983-03-10 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | Aircraft having a canard wing configuration |
-
1956
- 1956-08-13 GB GB2467156A patent/GB819665A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3030728A1 (en) * | 1980-08-14 | 1982-02-18 | Dornier Gmbh, 7990 Friedrichshafen | Steering gear, partic. rudders, for aircraft or missiles - use delta-wing fins outboard on elevator rotatable about two perpendicular axes |
| DE3133957A1 (en) * | 1981-08-27 | 1983-03-10 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | Aircraft having a canard wing configuration |
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