GB643815A - Control of aircraft - Google Patents
Control of aircraftInfo
- Publication number
- GB643815A GB643815A GB9703/48A GB970348A GB643815A GB 643815 A GB643815 A GB 643815A GB 9703/48 A GB9703/48 A GB 9703/48A GB 970348 A GB970348 A GB 970348A GB 643815 A GB643815 A GB 643815A
- Authority
- GB
- United Kingdom
- Prior art keywords
- tube
- plate
- pins
- rod
- lost
- 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)
- Tires In General (AREA)
- Actuator (AREA)
- Transmission Devices (AREA)
Abstract
643,815. Locking rods. ARMSTRONG WHITWORTH AIRCRAFT, Ltd., Sir W. G., and LLOYD, J: April 7, 1948, No. 9703. [Class 80(iii)] [Also in Group XXIX] An arrangment for locking a rod in a push-pull connection until lost-motion has been taken up and, on return movement, for bringing the rod back to its initial position before the lost motion is again effective, comprises a tube 26 pivoted at 31 to a plate 29 itself pivoted on a fixed pin 30, and an actuating rod 25 slidable in the tube 26 and having a pair of pins 27 working in slots 28 in the tube and engaging surfaces 33 of the plate 29. The rod to be actuated is fixed to the right-hand end of the tube 26. The arrangement is such that the pins 27 prevent angular movement of the plate 29 about the pivot 31, and therefore prevent axial displacement of the tube 26, until the lost motion provided by the pins and slots 27, 28 has been taken up, when one of the pins will have moved beyond one of the surfaces 33 to permit movement of the plate 29. On return movement. the plate 29 must come back to its initial position before the lost-motion is again available. The device is described as employed in a fluid-pressure servomotor system (see Group XXIX).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9703/48A GB643815A (en) | 1948-04-07 | 1948-04-07 | Control of aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9703/48A GB643815A (en) | 1948-04-07 | 1948-04-07 | Control of aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB643815A true GB643815A (en) | 1950-09-27 |
Family
ID=9877133
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9703/48A Expired GB643815A (en) | 1948-04-07 | 1948-04-07 | Control of aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB643815A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2753134A (en) * | 1952-03-10 | 1956-07-03 | North American Aviation Inc | Aircraft control system |
-
1948
- 1948-04-07 GB GB9703/48A patent/GB643815A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2753134A (en) * | 1952-03-10 | 1956-07-03 | North American Aviation Inc | Aircraft control system |
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