GB807423A - Improvements relating to helicopters - Google Patents
Improvements relating to helicoptersInfo
- Publication number
- GB807423A GB807423A GB397256A GB397256A GB807423A GB 807423 A GB807423 A GB 807423A GB 397256 A GB397256 A GB 397256A GB 397256 A GB397256 A GB 397256A GB 807423 A GB807423 A GB 807423A
- Authority
- GB
- United Kingdom
- Prior art keywords
- hub
- shaft
- control shaft
- blades
- hollow
- 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
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
- B64C27/41—Rotors having articulated joints with flapping hinge or universal joint, common to the blades
-
- 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)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
807,423. Helicopters. FAIREY AVIATION CO. Ltd. Feb. 7, 1957 [Feb. 8, 1956], No. 3972/56. Class 4. [Also in Group XXXII] A helicopter rotor head comprises a tiltable hub 11 on which the inner ends of the blades 10 are mounted, an upwardly extending tiltable control shaft 21, connections between the control shaft and the blades for varying the blade pitch in accordance with movement of the control shaft, and a bridle coupling 23 between the control shaft and the hub, which coupling is resilient, whereby the transmission of vibrations between the hub and the control shaft is reduced. In Fig. 1, the hub 11 is universally mounted through a gimbal ring 12 to a ring 13 rotatably mounted on a pylon 14 fixed to the helicopter fuselage. The control shaft 21 is universely mounted at the centre of tilting 22 of the hub 11. A member 25 is fixed to the shaft, and each of two links the length of which are adjustable by turnbuckles (not shown) is universally mounted at its two ends to the member 25 and to a blade pitch change horn 17 respectively, so that tilting of the control shaft controls the blade pitch cyclically, and vertical movement of the shaft effects collective pitch control. An inverted U-shaped member 23 is slidably and non-rotatably mounted on shaft 21 e.g. by splines, and the arms 29 of the U are connected to pivots 30 on the hub, so that the hub is tilted as cyclic pitch is applied. Transmission of vibration from the hub to the shaft is reduced by making arms 29 leaf springs, which may be laminated, or by including a piston and cylinder type shock absorbing unit in each arm, relative movement of the piston and cylinder being restrained by springs or rubber blocks (see Group XXXII). In the embodiment of Figs. 2 and 3 (not shown), flyweights are mounted on the ends of arms extending radially from the hub in a vertical plane at right angles to that containing the blades. The vertical shaft 21 is hollow, and contains a hollow tube rotating with the blades and supplied with fuel through a rotary pipe joint which fuel is supplied to blade tip jet engines through a distributer at the top of the tube. The tube also carries electrical cables connected to slip rings at the bottom of the tube for the engines ignition supply. The interior of the hollow hub is sealed from the atmosphere and acts as a distributer for compressed air fed to the engines through the hollow blades. The hollow tube also drives a revolution counter and rotational speed indicator, and a rotor brake is provided for stopping the rotor when power is cut off.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB397256A GB807423A (en) | 1956-02-08 | 1956-02-08 | Improvements relating to helicopters |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB397256A GB807423A (en) | 1956-02-08 | 1956-02-08 | Improvements relating to helicopters |
Publications (1)
Publication Number | Publication Date |
---|---|
GB807423A true GB807423A (en) | 1959-01-14 |
Family
ID=9768376
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB397256A Expired GB807423A (en) | 1956-02-08 | 1956-02-08 | Improvements relating to helicopters |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB807423A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3026942A (en) * | 1959-07-07 | 1962-03-27 | Bell Helicopter Corp | Helicopter rotor system |
FR2420052A1 (en) * | 1978-03-16 | 1979-10-12 | Wright Barry Corp | EXTREME LAMINATED ELASTOMER BEARINGS FOR ARTICULATED CONNECTING RODS |
EP1900636A1 (en) * | 2006-09-15 | 2008-03-19 | Yellowfin Limited | Marine propulsion and constructional details thereof |
EP1900634A1 (en) * | 2006-09-15 | 2008-03-19 | Yellowfin Limited | Marine propulsion and constructional details thereof |
EP3533710A1 (en) | 2018-02-28 | 2019-09-04 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A passive pitch angle adjustment apparatus |
US11958594B2 (en) | 2021-05-05 | 2024-04-16 | Airbus Helicopters Deutschland GmbH | Cyclic pitch angle adjustment apparatus |
-
1956
- 1956-02-08 GB GB397256A patent/GB807423A/en not_active Expired
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3026942A (en) * | 1959-07-07 | 1962-03-27 | Bell Helicopter Corp | Helicopter rotor system |
FR2420052A1 (en) * | 1978-03-16 | 1979-10-12 | Wright Barry Corp | EXTREME LAMINATED ELASTOMER BEARINGS FOR ARTICULATED CONNECTING RODS |
EP1900636A1 (en) * | 2006-09-15 | 2008-03-19 | Yellowfin Limited | Marine propulsion and constructional details thereof |
EP1900634A1 (en) * | 2006-09-15 | 2008-03-19 | Yellowfin Limited | Marine propulsion and constructional details thereof |
WO2008032121A3 (en) * | 2006-09-15 | 2009-05-22 | Yellowfin Ltd | Marine propulsion and constructional details thereof |
WO2008032120A3 (en) * | 2006-09-15 | 2009-06-04 | Yellowfin Ltd | Marine propulsion and constructional details thereof |
EP3533710A1 (en) | 2018-02-28 | 2019-09-04 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A passive pitch angle adjustment apparatus |
US10723450B2 (en) | 2018-02-28 | 2020-07-28 | Airbus Helicopters Deutschland GmbH | Passive pitch angle adjustment apparatus |
US11958594B2 (en) | 2021-05-05 | 2024-04-16 | Airbus Helicopters Deutschland GmbH | Cyclic pitch angle adjustment apparatus |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2519762A (en) | Gyrodynamic damper | |
GB1454835A (en) | Swashplate assembly for a rotor assembly of a rotorcraft | |
GB916894A (en) | Improvements relating to cyclic pitch control mechanisms for rotary wing aircraft | |
ES484030A1 (en) | Soft inplane helicopter rotor | |
GB898203A (en) | Boundary layer control means | |
GB1278489A (en) | Helicopter rotor hub assembly | |
GB807423A (en) | Improvements relating to helicopters | |
GB1145887A (en) | Helicopter rotor control system | |
GB652817A (en) | Improvements in means for controlling the pitch of rotor blades of helicopters | |
GB901505A (en) | Helicopter torque control device | |
US2475318A (en) | Rotor | |
GB1467712A (en) | Helicopter rotor hub | |
US2252544A (en) | Aircraft having rotative sustaining wings or blades | |
GB608459A (en) | Improvements in rotors for rotary-wing aircraft | |
GB791474A (en) | Improvements relating to helicopter rotors | |
GB643474A (en) | Improvements in or relating to damping devices for aircraft rotors | |
GB600013A (en) | Improvements in helicopter aircraft | |
GB769206A (en) | Improvements in or relating to rotary wing aircraft | |
GB754033A (en) | Rotor and stabilising mechanism, especially for helicopters | |
GB1439237A (en) | Elastomeric helicopter rotor head with dynamic and static blade coning and droop stops | |
GB760471A (en) | Improvements in or relating to lift rotors for aircraft | |
GB886582A (en) | Improvements in helicopter blade control apparatus | |
GB643875A (en) | Improvements in blade mounting for rotary wing aircraft | |
GB751837A (en) | Gyroscopic device for stabilizing the rotors of helicopters | |
GB649910A (en) | Improvements in or relating to stablising devices for helicopters and like rotary-wing aircraft |