GB645234A - Helicopters - Google Patents
HelicoptersInfo
- Publication number
- GB645234A GB645234A GB15004/48A GB1500448A GB645234A GB 645234 A GB645234 A GB 645234A GB 15004/48 A GB15004/48 A GB 15004/48A GB 1500448 A GB1500448 A GB 1500448A GB 645234 A GB645234 A GB 645234A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- rotor
- control
- pitch
- servo
- 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
645,234. Helicopters. UNITED HELICOPTERS, Inc. June 3, 1948, No. 15004. Convention date, June 3, 1947. [Class 4] The cyclic pitch adjustment of the blades of a helicopter rotor is effected by a servo control rotor, the blades of which are subject to cyclic pitch control initiated by the pilot. As shown, the main rotor comprises two non-articulated blades 21, the hub 19 being carried on the drive shaft 22 by a universal mounting, the axes of which are parallel and perpendicular to the longitudinal axes of the blades, and the servo rotor comprises two small blades 56 disposed below and perpendicular to the blades 21. The pitch setting of the servo blades 56 is controlled by a gimbal ring 81 connected by links 80 to a pilot-controlled ring 68. Inclination of the servo rotor tip path plane consequent upon unequal pitch settings of the blades 56 is communicated to the main rotor pitch control arms 79 by links 80<SP>1</SP>. Collective pitch control of the main rotor blades is effected by axial movement of the control ring 81 along the drive shaft 22. Fig. 9 shows the control arrangement for a helicopter with co-axial contrarotating rotors 21, 21a, the collective pitch of the blades being varied by a vertically-movable axial rod 82 inside the drive shaft 22. Such an arrangement may also be used for collective pitch control of a single rotor, Fig. 8 (not shown).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US645234XA | 1947-06-03 | 1947-06-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB645234A true GB645234A (en) | 1950-10-25 |
Family
ID=22056559
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB15004/48A Expired GB645234A (en) | 1947-06-03 | 1948-06-03 | Helicopters |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB645234A (en) |
-
1948
- 1948-06-03 GB GB15004/48A patent/GB645234A/en not_active Expired
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