GB584700A - Improvements in or relating to control flaps or tabs for aircraft - Google Patents
Improvements in or relating to control flaps or tabs for aircraftInfo
- Publication number
- GB584700A GB584700A GB2136044A GB2136044A GB584700A GB 584700 A GB584700 A GB 584700A GB 2136044 A GB2136044 A GB 2136044A GB 2136044 A GB2136044 A GB 2136044A GB 584700 A GB584700 A GB 584700A
- Authority
- GB
- United Kingdom
- Prior art keywords
- control member
- eccentrics
- movement
- link
- tab
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/04—Adjustable control surfaces or members, e.g. rudders with compound dependent movements
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Mechanical Control Devices (AREA)
Abstract
584,700. Controlling aircraft. SPURR, E., SHORT, R. W., TAYLOR, B., and BOYDEN, L. Nov. 1, 1944, No. 21360. [Class 4] Control means for a balance or trimming tab 5 is provided within the structure of the control surface 4, and comprises eccentrics 2, 2a, mounted at the pivotal axes of the main control member 4 and tab respectively, a link 10 connecting the eccentrics such that movement of the control member eccentric, or movement of the link with the control member; causes an angular setting of the tab in relation to the main control member. -Movement of the control member eccentric 2 may be effected by a lever 12 operated by a control lever in the pilot's cockpit. The eccentrics 2, 2a may be set parallel to one another and in the same direction, to give a parallelogram motion, as shown, or may be set in opposite directions. In order to prevent the transmission of load to the fixed portion of the wing structure 8, the connecting link 10 may be enclosed in a sleeve 11, the. ends of which are anchored to the pivotal axes of the eccentrics.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2136044A GB584700A (en) | 1944-11-01 | 1944-11-01 | Improvements in or relating to control flaps or tabs for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2136044A GB584700A (en) | 1944-11-01 | 1944-11-01 | Improvements in or relating to control flaps or tabs for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB584700A true GB584700A (en) | 1947-01-21 |
Family
ID=10161590
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2136044A Expired GB584700A (en) | 1944-11-01 | 1944-11-01 | Improvements in or relating to control flaps or tabs for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB584700A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986004A (en) * | 2017-03-02 | 2017-07-28 | 中国航空研究院 | A kind of servo-actuated synergistic device of rudder of aircraft |
-
1944
- 1944-11-01 GB GB2136044A patent/GB584700A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986004A (en) * | 2017-03-02 | 2017-07-28 | 中国航空研究院 | A kind of servo-actuated synergistic device of rudder of aircraft |
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