GB595988A - Improvements in or relating to helicopters - Google Patents
Improvements in or relating to helicoptersInfo
- Publication number
- GB595988A GB595988A GB1783245A GB1783245A GB595988A GB 595988 A GB595988 A GB 595988A GB 1783245 A GB1783245 A GB 1783245A GB 1783245 A GB1783245 A GB 1783245A GB 595988 A GB595988 A GB 595988A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- trunnions
- frame
- rod
- axis
- 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
- B64C27/001—Vibration damping devices
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
595,988. Helicopters. FAIREY AVIATION CO., Ltd., and BENNETT, J. A. J. July 12, 1945, No. 17832. [Class 4] A helicopter rotor comprises a single blade counterweighted for rotational balance and rigidly mounted without freedom to flap or to lag relatively to the counterweight, the blade, or a control surface on the blade, being provided with a feathering pivot so that the blade pitch, or blade surface angle, may be varied sinusoidally for control purposes. The blade may be sufficiently flexible to allow inclination of the blade-tip path relative to a plane normal to the axis of rotation. As shown, a rotary hub c is mounted in bearings d in a fixed hub a mounted on a support b, and is formed with apertured lugs e provided with bearings f for trunnions g on a frame h, the root of the blade k and the root m of a counterweight n being fixed in the trunnions g. A cross-piece p is mounted by trunnions o in the frame h, and carries a rod q, the lower end of which is connected by a ball-and-socket joint r, s to a control rod t pivoted in a fork u integral with a pintle v. The latter is rotatable about an axis V-V in a sleeve w pivoted to the support b about a perpendicular axis. Movement of the rod t produces an inclination of the frame h and a sinusoidal variation of blade pitch.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB595988A true GB595988A (en) | 1947-12-24 |
Family
ID=1733451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1783245A Expired GB595988A (en) | 1945-07-12 | Improvements in or relating to helicopters |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB595988A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2491733A (en) * | 1946-11-25 | 1949-12-20 | United Helicopters Inc | Helicopter |
-
1945
- 1945-07-12 GB GB1783245A patent/GB595988A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2491733A (en) * | 1946-11-25 | 1949-12-20 | United Helicopters Inc | Helicopter |
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