GB654757A - Control mechanism for jet driven sustaining rotor blades - Google Patents
Control mechanism for jet driven sustaining rotor bladesInfo
- Publication number
- GB654757A GB654757A GB29576/48A GB2957648A GB654757A GB 654757 A GB654757 A GB 654757A GB 29576/48 A GB29576/48 A GB 29576/48A GB 2957648 A GB2957648 A GB 2957648A GB 654757 A GB654757 A GB 654757A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor blades
- contacts
- valves
- nov
- jet
- 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
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
- B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
Abstract
654,757. Helicopters. AUTOGIRO CO. OF AMERICA. Nov. 15, 1948, No. 29576. Convention date, Nov. 15, 1947. [Class 4] In a jet-driven helicopter rotor, the operation of the jets is controlled by the relative lag-lead movements of the rotor blades. As shown, the blade drag pivots 13 carry double-armed levers 26 connected by vibration dampers 27, 28 embodying electric contacts connected in series and controlling solenoid valves 19 in the fuel pipes 18 of the jet nozzles 17. The dampers comprise relatively slidable members 27, 28 with interposed strips 29 of friction material, pressed into engagement by springs 31, the strips 27, 28 carrying the electric contacts 33, 35. Equal lag-lead movements of all the rotor blades have no effect on any of the contacts, but excessive relative movement of any blade beyond a predetermined value results in separation of the associated contacts and closure of all the fuel valves 19. An over-riding manual switch is provided to control the valves 19.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US654757XA | 1947-11-15 | 1947-11-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB654757A true GB654757A (en) | 1951-06-27 |
Family
ID=22062978
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB29576/48A Expired GB654757A (en) | 1947-11-15 | 1948-11-15 | Control mechanism for jet driven sustaining rotor blades |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB654757A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4915585A (en) * | 1988-04-29 | 1990-04-10 | Aerospatiale Societe National Industrielle | Rotary-wing aircraft rotor head having resilient-return interblade ties with built-in damping |
-
1948
- 1948-11-15 GB GB29576/48A patent/GB654757A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4915585A (en) * | 1988-04-29 | 1990-04-10 | Aerospatiale Societe National Industrielle | Rotary-wing aircraft rotor head having resilient-return interblade ties with built-in damping |
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