GB571979A - Improvements in aircraft controls - Google Patents
Improvements in aircraft controlsInfo
- Publication number
- GB571979A GB571979A GB13946/43A GB1394643A GB571979A GB 571979 A GB571979 A GB 571979A GB 13946/43 A GB13946/43 A GB 13946/43A GB 1394643 A GB1394643 A GB 1394643A GB 571979 A GB571979 A GB 571979A
- Authority
- GB
- United Kingdom
- Prior art keywords
- link
- control
- valve
- pilot
- servo
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
571,979. Construction of links. GENERAL AIRCRAFT, Ltd., LISLE, W. G., and ANDREWS, E. Aug. 26, 1943, No. 13946. [Class 80 (iii)] [Also in Group XXXIII] The control system for an aircraft control surface provided with a servo tab includes a resilient link between the pilotactuated control member and the main control surface, which link may positively control both the main and servo control elements or may be rendered less effective or ineffective, in which latter case the servo tab only is actuated by the pilot's control member. In the arrangement shown, a control surface 2 carries a servo tab 3 actuated by a hydraulic jack 10 as described in Specification 555,635, [Group XXXIII], the resilient link being in the form of a hydraulic link 4, 6 joining levers 1a, 5, respectively connected to the pilot's control member and the main control surface 2. The link comprises a plunger rod 6 attached to the lever 1a, and moving inside the cylinder 4 attached to the lever 5. The cylinder has two compartments 7, 11, the former being connected by pipes 8, 8a to the jack 10 and the latter by pipes 24, 25 to a remotely-controllable valve 23. A plunger 6a operates in the compartment 7, and opposed pistons 15, 16 loaded by springs 21, 22 are provided in the compartment 11. By closing the valve 23 a positive resilient connection is provided between the pilot's control member and both surfaces 2, 3 ; the connection may be rendered less effective or ineffective by opening the valve 23 in which latter event the tab 3 only is operated. The degree of resilience may be varied by adjusting the extent of restriction of the valve 23.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB13946/43A GB571979A (en) | 1943-08-26 | 1943-08-26 | Improvements in aircraft controls |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB13946/43A GB571979A (en) | 1943-08-26 | 1943-08-26 | Improvements in aircraft controls |
Publications (1)
Publication Number | Publication Date |
---|---|
GB571979A true GB571979A (en) | 1945-09-18 |
Family
ID=10032226
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB13946/43A Expired GB571979A (en) | 1943-08-26 | 1943-08-26 | Improvements in aircraft controls |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB571979A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2640665A (en) * | 1948-06-02 | 1953-06-02 | Cons Vultee Aircraft Corp | Aircraft trim tab control |
US2843344A (en) * | 1948-06-02 | 1958-07-15 | Gen Dynamics Corp | Aircraft trim tab control |
GB2132962A (en) * | 1982-12-29 | 1984-07-18 | Brunswick Corp | No feedback steering system for marine drives |
-
1943
- 1943-08-26 GB GB13946/43A patent/GB571979A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2640665A (en) * | 1948-06-02 | 1953-06-02 | Cons Vultee Aircraft Corp | Aircraft trim tab control |
US2843344A (en) * | 1948-06-02 | 1958-07-15 | Gen Dynamics Corp | Aircraft trim tab control |
GB2132962A (en) * | 1982-12-29 | 1984-07-18 | Brunswick Corp | No feedback steering system for marine drives |
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