GB630930A - Improvements in or relating to helicopters - Google Patents
Improvements in or relating to helicoptersInfo
- Publication number
- GB630930A GB630930A GB13256/47A GB1325647A GB630930A GB 630930 A GB630930 A GB 630930A GB 13256/47 A GB13256/47 A GB 13256/47A GB 1325647 A GB1325647 A GB 1325647A GB 630930 A GB630930 A GB 630930A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- effected
- pivots
- lever
- tilting
- 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
630,930. Helicopters. UNITED HELICOPTERS, Inc. May 16, 1947, No. 13256. Convention date, Nov. 25, 1946. [Class 4] A helicopter sustaining rotor is mounted on the driving shaft by means of a universal enabling cyclic pitch adjustment to be effected about one axis and bodily tilting of the rotor to take place about a perpendicular axis. In the form shown the rotor comprises two blades 21 carried by a hub 34 mounted on the drive shaft 22 by perpendicular pivots 44, 46. Cyclic pitch control is effected by gimbal-mounted rings 62, 63, the latter being operated by a control lever 17. The inner ring 62 is connected to the rotor hub by vertical arms 53 and pivots 51 which are coaxial with the pivots 46 carried by the drive shaft 22. Fore-andaft tilting of the ring 63 is effected through links 72, 74 by forward or rearward movement of the lever 17, while lateral tilting is effected through links 87, 89 by rotating the lever about a pivot 83. In the helicopter shown in Fig. 1, the reaction torque from the rotor is balanced by a jet of air supplied by a fan 97 and discharged through a lateral tail opening 96 under the control of a byepass valve or flaps 101.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US630930XA | 1946-11-25 | 1946-11-25 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB630930A true GB630930A (en) | 1949-10-24 |
Family
ID=22046875
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB13256/47A Expired GB630930A (en) | 1946-11-25 | 1947-05-16 | Improvements in or relating to helicopters |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB630930A (en) |
-
1947
- 1947-05-16 GB GB13256/47A patent/GB630930A/en not_active Expired
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