GB423371A - Improvements relating to aircraft - Google Patents
Improvements relating to aircraftInfo
- Publication number
- GB423371A GB423371A GB23355/33A GB2335533A GB423371A GB 423371 A GB423371 A GB 423371A GB 23355/33 A GB23355/33 A GB 23355/33A GB 2335533 A GB2335533 A GB 2335533A GB 423371 A GB423371 A GB 423371A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- shaft
- hub
- wings
- incidence
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
423,371. Aircraft with rotary wing systems. FLETTNER, A., 7, Neue Bayreutherstrasse, Berlin. Aug. 22, 1933, No. 23355. [Class 4] An aircraft having rotating wings hinged to a freely movable wing hub has its wings hinged to members rotatably mounted in the hub and furnished with levers connected by links with a movable controller. Normally the links prevent rotation of the wings about their axes as the hub tilts Provision may also be made for automatically changing the incidence of the wings from an autorotative position to one suitable for a positive drive and vice versa dependent upon the speed of rotation of the system or upon variation of torque upon the hub. Fig. 2 shows a wing 2 hinged to a member 15 journalled in a hub 14 mounted upon gimbals on a shaft 3. The member 15 has an arm 17 extending to a point in a plane passing through the shaft 3 at right angles to a plane containing the shaft 3 and member 15. The end of the lever is connected by a link 19, Fig. 3, to a controller 22 mounted on gimbals on the shaft 3 and tiltable in any direction by a ring 23 having a handle 24. Instead of the whole wing being pivoted to the member 15 only the wing tip 2<a> or a rear flap may be connected to a member 15<a> as also shown in Fig. 2. Alternatively, the main blades 2 may be hinged to the hub 14 and smaller blades placed between them connected to the control member 22. A counter propeller on a transverse axis may be provided at the rear of the machine to counteract driving torque and forward thrust may be given by a tractor propeller or by arranging the shaft 3 at a forward inclination. To ensure a change of incidence of the wings with variation of speed, each wing may be mounted to move axially along a shaft 26, Fig. 5, under control of a spring 27, screwed parts 28, 29 co-operating with screwed sleeves on the wing frame to produce a change of incidence as the wing moves axially. By using screwed parts of different pitch a helical twist can be given to the blade as the mean pitch increases. Fig. 6 shows a modification in which the wing is carried by a sleeve 32 which slides over a nut 35, axial movement being controlled by a light spring arranged between arms 37, 38. A wing tip 2a is mounted on a sleeve 34 rotating in the sleeve 32 and engaging a screw 33 on the control rod 31. The wing tip consequently changes its incidence as the wing moves axially while remaining under the control of the rod 31 and lever 17. Provision for giving a helical twist to the wing and its tip may be made. Fig. 9 shows the hub 14 connected to an extension 39 of the shaft 3 by a quick threaded screw so that failure of the driving torque causes relatively axial movement of the parts 3, 39 and the incidence of the wings is reduced through their connection to the controller 22 which is mounted as shown on the member 3. A freewheel is disposed between the engine and the shaft 3.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB23355/33A GB423371A (en) | 1933-08-22 | 1933-08-22 | Improvements relating to aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB23355/33A GB423371A (en) | 1933-08-22 | 1933-08-22 | Improvements relating to aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB423371A true GB423371A (en) | 1935-01-31 |
Family
ID=10194320
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB23355/33A Expired GB423371A (en) | 1933-08-22 | 1933-08-22 | Improvements relating to aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB423371A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2643724A (en) * | 1947-02-21 | 1953-06-30 | United Aircraft Corp | Helicopter rotor |
GB2299562A (en) * | 1995-04-01 | 1996-10-09 | Nigel Howard Mckrill | Actuator for helicopter rotor blade aileron |
-
1933
- 1933-08-22 GB GB23355/33A patent/GB423371A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2643724A (en) * | 1947-02-21 | 1953-06-30 | United Aircraft Corp | Helicopter rotor |
GB2299562A (en) * | 1995-04-01 | 1996-10-09 | Nigel Howard Mckrill | Actuator for helicopter rotor blade aileron |
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