GB423752A - Improvements relating to aircraft controls - Google Patents
Improvements relating to aircraft controlsInfo
- Publication number
- GB423752A GB423752A GB2859933A GB2859933A GB423752A GB 423752 A GB423752 A GB 423752A GB 2859933 A GB2859933 A GB 2859933A GB 2859933 A GB2859933 A GB 2859933A GB 423752 A GB423752 A GB 423752A
- Authority
- GB
- United Kingdom
- Prior art keywords
- crank
- wing
- aileron
- arm
- 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
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
423,752. Controlling aircraft. HAWKER AIRCRAFT, Ltd., and CAMM, S., Canbury Park Road, Kingston-on-Thames. Oct. 16, 1933, No. 28599. [Class 4] A control mechanism for aircraft comprises a crank member 10 contained substantially in the thickness of the wing, tail-plane, &c., and is partially rotatable in a plane perpendicular or nearly perpendicular to that of the wing, the crank being connected to a lever 5 projecting from the hinge axis 3 into the thickness of the wing so that virtually no part of the device is external to the profile of the wing and control surface. As shown applied to aileron control gear the crank 10, Fig. 1, is pivoted on a shaft 11 mounted in the wing 1 and is connected by link 7 to the lever 5 fixed to the spar 3 of the aileron 2. A balance 6 for the aileron may be attached to the arm 5 and the aileron is operated through pulley 12 and cables 13. The connection between the crank 10 and arm 5 may be such as to diminish the rate of movement of the aileron toward one extremity or the other of its movement. In Fig. 4 the crank 20 is connected to the arm 5 by a link 18 or the end of the arm 5 may be forked and engage a crank-pin on the crank 20.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2859933A GB423752A (en) | 1933-10-16 | 1933-10-16 | Improvements relating to aircraft controls |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2859933A GB423752A (en) | 1933-10-16 | 1933-10-16 | Improvements relating to aircraft controls |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB423752A true GB423752A (en) | 1935-02-07 |
Family
ID=10278158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2859933A Expired GB423752A (en) | 1933-10-16 | 1933-10-16 | Improvements relating to aircraft controls |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB423752A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2556351A (en) * | 1947-07-17 | 1951-06-12 | Curtiss Wright Corp | Mass load applying means for airfoils |
| US2859925A (en) * | 1953-09-17 | 1958-11-11 | Gerin Jacques Jean-Marie Jules | Automatic balancing arrangement for aircraft control |
-
1933
- 1933-10-16 GB GB2859933A patent/GB423752A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2556351A (en) * | 1947-07-17 | 1951-06-12 | Curtiss Wright Corp | Mass load applying means for airfoils |
| US2859925A (en) * | 1953-09-17 | 1958-11-11 | Gerin Jacques Jean-Marie Jules | Automatic balancing arrangement for aircraft control |
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