GB623322A - Sustaining blade for rotating wing aircraft - Google Patents
Sustaining blade for rotating wing aircraftInfo
- Publication number
- GB623322A GB623322A GB11494/47A GB1149447A GB623322A GB 623322 A GB623322 A GB 623322A GB 11494/47 A GB11494/47 A GB 11494/47A GB 1149447 A GB1149447 A GB 1149447A GB 623322 A GB623322 A GB 623322A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- members
- spar
- skin
- wing aircraft
- 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)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
623,322. Rotary-wing aircraft. SOC. RATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU NORD. April 29, 1947, No. 11494. Convention date, Nov. 14, 1946. [Class 4] A blade for a rotary wing system comprises a spar, metal skin and a series of shaping members extending between the leading and trailing edges, at least two of these members being separable to press the others into engagement with each other and with the metal skin. In the form of blade shown in Figs. 2 and 3, two formers 2, 3 are provided in front of the tubular spar 1, while the rear portion of the blade consists of ribs 5 integral with a trailing edge member 7, to which the rear edges of the covering skin 9 are secured. The members 2, 3 are pressed apart by screws 11, 12 so that the member 2 and ribs 5 are forced against the skin 9. The ends of the screws 11, 12 are made flush with the leading edge of the blade after adjustment of the members 2, 3. In the modification shown in Fig. 5, an inflatable tube 24 is used to separate the leading edge members 2, 3. As shown in Fig. 4, the end of the spar 1 may be connected to a root member 23 by a welded sleeve 17 and lock-nuts 18, 20.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR623322X | 1946-11-14 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB623322A true GB623322A (en) | 1949-05-16 |
Family
ID=8986384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB11494/47A Expired GB623322A (en) | 1946-11-14 | 1947-04-29 | Sustaining blade for rotating wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB623322A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2941603A (en) * | 1956-05-01 | 1960-06-21 | Drago K Jovanovich | Helicopter rotor blade |
| US3013614A (en) * | 1956-03-14 | 1961-12-19 | Haviland H Platt | Rotor blade |
| EP4316981A1 (en) * | 2022-08-04 | 2024-02-07 | Lockheed Martin Corporation | Commonly manufactured rotor blade |
-
1947
- 1947-04-29 GB GB11494/47A patent/GB623322A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3013614A (en) * | 1956-03-14 | 1961-12-19 | Haviland H Platt | Rotor blade |
| US2941603A (en) * | 1956-05-01 | 1960-06-21 | Drago K Jovanovich | Helicopter rotor blade |
| EP4316981A1 (en) * | 2022-08-04 | 2024-02-07 | Lockheed Martin Corporation | Commonly manufactured rotor blade |
| US11919627B2 (en) | 2022-08-04 | 2024-03-05 | Lockheed Martin Corporation | Commonly manufactured rotor blade |
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