GB574177A - Improvements in aircraft control surface actuating means - Google Patents
Improvements in aircraft control surface actuating meansInfo
- Publication number
- GB574177A GB574177A GB468/44A GB46844A GB574177A GB 574177 A GB574177 A GB 574177A GB 468/44 A GB468/44 A GB 468/44A GB 46844 A GB46844 A GB 46844A GB 574177 A GB574177 A GB 574177A
- Authority
- GB
- United Kingdom
- Prior art keywords
- control surface
- control
- axis
- auxiliary
- lever arm
- 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
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
Abstract
574,177. Controlling aircraft. HAWKER AIRCRAFT, Ltd., and PAGE, F. W. Jan. 10, 1944, No. 468. [Class 4] The actuating mechanism for an aircraft control surface of the kind provided with an auxiliary or servo surface operated with the main control surface, and in which the control transmitting mechanism incorporates a lever arm carried by the control surface and under the control of a restraining spring whose lostmotion is transmitted to the auxiliary surface, is so arranged that the lever arm is hinged to the control surface about an axis substantially parallel with the hinge axis of the control surface and displaced therefrom in the direction of the free end of the lever arm, the moment of the restraining spring being exerted about the first mentioned axis. In the construction according to Fig. 1, the main and auxiliary control rods 32, 34 are respectively connected to levers.24, 10 on a hollow shaft 12 carried in brackets 16 projecting from a block 18 secured to the main spar of the control surface, the axis of the shaft being displaced from but parallel to the axis of the hinge lug 22 for the control surface. The restraining spring comprises a torsion rod 26 within the hollow shaft 12, one end 28 being splined to one of the brackets 16, and the other, 30, to the end of the hollow shaft 12. Limit stops 48 are provided in order to prevent over-stressing of the torsion rod. According to a modification, Fig. 3 (not shown), the torsion rod is replaced by a coiled spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB468/44A GB574177A (en) | 1944-01-10 | 1944-01-10 | Improvements in aircraft control surface actuating means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB468/44A GB574177A (en) | 1944-01-10 | 1944-01-10 | Improvements in aircraft control surface actuating means |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB574177A true GB574177A (en) | 1945-12-27 |
Family
ID=9704886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB468/44A Expired GB574177A (en) | 1944-01-10 | 1944-01-10 | Improvements in aircraft control surface actuating means |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB574177A (en) |
-
1944
- 1944-01-10 GB GB468/44A patent/GB574177A/en not_active Expired
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