GB945928A - Rotor head for rotary wing aircraft - Google Patents
Rotor head for rotary wing aircraftInfo
- Publication number
- GB945928A GB945928A GB3727562A GB3727562A GB945928A GB 945928 A GB945928 A GB 945928A GB 3727562 A GB3727562 A GB 3727562A GB 3727562 A GB3727562 A GB 3727562A GB 945928 A GB945928 A GB 945928A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- elastomer
- movements
- axis
- transverse
- 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
- B64C27/35—Rotors having elastomeric joints
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
945,928. Rotary wing aircraft. LORD MANUFACTURING CO. Oct. 2, 1962 [Oct. 2, 1961; June 21, 1962], No. 37275/62. Heading B7W. A rotor blade mounting for a rotary wing aircraft comprises a first member 28 attached to the blade (mounted in fork 25) having a surface 30 transverse to the longitudinal blade axis and presented towards the blade and away from a blade mounting arm 22 on the hub, a second member 29 fixed to the arm and having a surface 31 transverse to the longitudinal blade axis and spaced outward of and presented towards the first surface 30, layers of an elastomer 35 between the surface and separated by plates 36 of non-extensible material, such as metal or glass fibre, the layers being bonded to the plates and surfaces, and pitch control means connected to the first member for twisting it relative to the second. Fig. 5 is a part section through the drag axis, and Fig. 8 a section through the flapping axis, the two axes meeting at 32, which is also the centre of curvature of surfaces 30, 31. The elastomer permits dragging and flapping movements, with damping which increases with the amplitude of the movements, and also accommodates pitch change movements. Plates 35 do not affect these functions, but do increase the resistance of the elastomer to the centrifugal force between surfaces 30, 31. The first and second members may have resilient stops to limit flapping and dragging. To assist in resisting movements of the blade transverse to its length, the member 28 on the blade has a stem 42, and further elastomer 38 is bonded between an enlargement 37 on the stem and a surface 40 on the blade arm member 22.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US142223A US3106965A (en) | 1961-10-02 | 1961-10-02 | Rotor head |
| US204117A US3111172A (en) | 1962-06-21 | 1962-06-21 | Rotor head |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB945928A true GB945928A (en) | 1964-01-08 |
Family
ID=26839883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3727562A Expired GB945928A (en) | 1961-10-02 | 1962-10-02 | Rotor head for rotary wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB945928A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2049481A1 (en) * | 1969-10-16 | 1971-05-06 | Societe Nationale Industrielle Aerospatiale, Paris | Device for the damped elastic see connection between the blade and hub on the rotor of aircraft with ro tierendem structure |
| CN111749984A (en) * | 2019-03-29 | 2020-10-09 | 斯凯孚公司 | Laminated bearing assembly with different shim thicknesses |
-
1962
- 1962-10-02 GB GB3727562A patent/GB945928A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2049481A1 (en) * | 1969-10-16 | 1971-05-06 | Societe Nationale Industrielle Aerospatiale, Paris | Device for the damped elastic see connection between the blade and hub on the rotor of aircraft with ro tierendem structure |
| CN111749984A (en) * | 2019-03-29 | 2020-10-09 | 斯凯孚公司 | Laminated bearing assembly with different shim thicknesses |
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