GB748983A - Improvements in rolling control devices for aircraft powered by jet propulsion engines - Google Patents
Improvements in rolling control devices for aircraft powered by jet propulsion enginesInfo
- Publication number
- GB748983A GB748983A GB3092/54A GB309254A GB748983A GB 748983 A GB748983 A GB 748983A GB 3092/54 A GB3092/54 A GB 3092/54A GB 309254 A GB309254 A GB 309254A GB 748983 A GB748983 A GB 748983A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- blades
- propulsion
- rotation
- annular passage
- 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
- B64C9/38—Jet flaps
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
748,983. Controlling jet-propelled aircraft. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Feb. 2, 1954 [Feb. 26, 1953], No. 3092/54. Class 4. [Also in Group XXVI] An aircraft having jet-propulsion plant has means to act on an annular section of the propulsion gases to tend to cause a change of direction or rotation of said section of gases to produce thereby a force couple to roll the aircraft about its longitudinal axis. The propulsion nozzle 3 aft of the turbine 1 comprises an annular passage enclosed between an outer casing 8 and a centre core 9. Blades 5, mounted for rotation on spigots 6, 7 are mounted diametrically opposite one another within the annular passage and they are geared for rotation in opposite directions by gears 10, 11 driven by a motor 12. Operation of the motor in one direction or the other will deflect the blades 5 which will react on the propulsion gases and roll the aircraft about its longitudinal axis. In alternative embodiments (not shown) the blades 5 may be located between fixed blades or fairings secured to the wall members 8 and 9 or they may extend only partially across the width of each annular passage adjacent either the wall 8 or the wall 9. Further, the forward portion of each blade may be fitted with hinged trailing flaps or pivoted spoilers or fixed blades may be formed on opposite surfaces with ejector nozzles, selectively supplied with pressure gas, preferably from the engine compressor.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR748983X | 1953-02-26 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB748983A true GB748983A (en) | 1956-05-16 |
Family
ID=9148803
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3092/54A Expired GB748983A (en) | 1953-02-26 | 1954-02-02 | Improvements in rolling control devices for aircraft powered by jet propulsion engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB748983A (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3121312A (en) * | 1961-02-28 | 1964-02-18 | United Aircraft Corp | Unified pitch, yaw and roll shock control |
US3134225A (en) * | 1960-03-02 | 1964-05-26 | Thompson Ramo Wooldridge Inc | Thrust control system |
US3156437A (en) * | 1960-09-02 | 1964-11-10 | S F E R M A Soc Fr D Entretien | Fluid flow straightening device in a propelled body |
US3166897A (en) * | 1961-08-21 | 1965-01-26 | United Aircraft Corp | Roll control and thrust vector control |
US3221498A (en) * | 1962-08-06 | 1965-12-07 | Lester T Bankston | Secondary fluid injection thrust vectoring methods and apparatus |
US3229461A (en) * | 1965-05-04 | 1966-01-18 | Burton A Jones | Fluid amplification device for propulsion system roll control |
US3229460A (en) * | 1965-05-04 | 1966-01-18 | Burton A Jones | Tertiary injector for propulsion system roll control |
US3266732A (en) * | 1963-09-03 | 1966-08-16 | United Aircraft Corp | Roll control system |
-
1954
- 1954-02-02 GB GB3092/54A patent/GB748983A/en not_active Expired
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3134225A (en) * | 1960-03-02 | 1964-05-26 | Thompson Ramo Wooldridge Inc | Thrust control system |
US3156437A (en) * | 1960-09-02 | 1964-11-10 | S F E R M A Soc Fr D Entretien | Fluid flow straightening device in a propelled body |
US3121312A (en) * | 1961-02-28 | 1964-02-18 | United Aircraft Corp | Unified pitch, yaw and roll shock control |
US3166897A (en) * | 1961-08-21 | 1965-01-26 | United Aircraft Corp | Roll control and thrust vector control |
US3221498A (en) * | 1962-08-06 | 1965-12-07 | Lester T Bankston | Secondary fluid injection thrust vectoring methods and apparatus |
US3266732A (en) * | 1963-09-03 | 1966-08-16 | United Aircraft Corp | Roll control system |
US3229461A (en) * | 1965-05-04 | 1966-01-18 | Burton A Jones | Fluid amplification device for propulsion system roll control |
US3229460A (en) * | 1965-05-04 | 1966-01-18 | Burton A Jones | Tertiary injector for propulsion system roll control |
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