GB1067771A - Main rotor blade for a helicopter - Google Patents
Main rotor blade for a helicopterInfo
- Publication number
- GB1067771A GB1067771A GB635164A GB635164A GB1067771A GB 1067771 A GB1067771 A GB 1067771A GB 635164 A GB635164 A GB 635164A GB 635164 A GB635164 A GB 635164A GB 1067771 A GB1067771 A GB 1067771A
- Authority
- GB
- United Kingdom
- Prior art keywords
- tube
- section
- edge section
- trailing edge
- sections
- 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
- B64C27/46—Blades
- B64C27/473—Constructional features
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
1,067,771. Helicopter rotor blades. M. L. MILJ, A. E. MALAKHOVSKY. E. V. JABLONSKY, V. V. GRIGORJEV, A. M. GRODZINSKY, B. S. SIROTINSKY. April 14, 1964, No. 6351/64. Heading B7W. A helicopter rotor blade comprises a variable section tube 1, e.g. of circular or elliptical crosssection, a plurality of leading edge sections 2 and a plurality of trailing edge parts 3 adapted to be fastened to the tube. Each trailing edge section is held to the tube by the engagement with a recess in a plate 9 of the section of a peg 18 (Fig. 2, not shown) or lug (Fig. 4, not shown) on an insert 17 fixed to the tube by bonding and by a collar 19, and also by straps 16 which are hinged to the trailing edge section and have threaded ends which pass through blocks 21 and are held thereto by nuts 22. Each leading edge section is secured to the corresponding trailing edge section by riveting and by bonding. Clearances, sealed by gaskets 24, 25, are provided between adjacent sections to relieve the sections of bending stresses. The leading edge section 2 has an electrical de-icing panel 7 covered with abrasive resistant material 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB635164A GB1067771A (en) | 1964-04-14 | 1964-04-14 | Main rotor blade for a helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB635164A GB1067771A (en) | 1964-04-14 | 1964-04-14 | Main rotor blade for a helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1067771A true GB1067771A (en) | 1967-05-03 |
Family
ID=9812906
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB635164A Expired GB1067771A (en) | 1964-04-14 | 1964-04-14 | Main rotor blade for a helicopter |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1067771A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3749517A (en) * | 1971-10-06 | 1973-07-31 | United Aircraft Corp | Helicopter blade with universally replaceable pockets |
| US4095322A (en) * | 1976-08-30 | 1978-06-20 | The Boeing Company | Method of fabricating a composite aerodynamic rotorblade assembly |
-
1964
- 1964-04-14 GB GB635164A patent/GB1067771A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3749517A (en) * | 1971-10-06 | 1973-07-31 | United Aircraft Corp | Helicopter blade with universally replaceable pockets |
| US4095322A (en) * | 1976-08-30 | 1978-06-20 | The Boeing Company | Method of fabricating a composite aerodynamic rotorblade assembly |
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