GB727513A - Improvements in and relating to aircraft controls - Google Patents
Improvements in and relating to aircraft controlsInfo
- Publication number
- GB727513A GB727513A GB2916852A GB2916852A GB727513A GB 727513 A GB727513 A GB 727513A GB 2916852 A GB2916852 A GB 2916852A GB 2916852 A GB2916852 A GB 2916852A GB 727513 A GB727513 A GB 727513A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cylinder
- pilot
- piston
- lever
- yoke
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/14—Special measures for giving the operating person a "feeling" of the response of the actuated device
-
- 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
- B64C13/24—Transmitting means
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Transmission Devices (AREA)
Abstract
727,513. Aircraft controls. ENGLISH ELECTRIC CO., Ltd. Nov. 6, 1953 [Nov. 18, 1952], No. 29168/52. Class 4. A feel simulator for aircraft controls of the kind in which the pilot's control member is coupled to the piston or cylinder of a hydraulic mechanism by a linkage having a dead-centre attitude so that the piston or cylinder is moved always in the same sense relative to its associated cylinder or piston, respectively, against the hydraulic pressure regardless of the sense in which the pilot's control member is displaced from the position corresponding to the dead-centre attitude of the linkage, is provided with spring means tending to restore the linkage to its dead-centre attitude and the pilot's member to its corresponding position with a force substantially lower than the forces normally applied by the pilot and resisted by the feel system, but larger than the values which these forces have at very small deflections of the pilot's control member. As illustrated in Figs. 2 and 3, a double lever 11 connected to the pilot's control is pivoted on a common axle 14 with a hydraulic cylinder 13, the piston 16 of which is connected by rod 18 and axle 19 to links 15 pivoted at their other ends to lever 11. The cylinder 13 is fixed to a yoke 20, the position of which can be varied to pivot cylinder 13 about axis 14 for trim purposes. The space between piston 16 and cylinder 13 is connected to a source of hydraulic pressure dependent on the pitot pressure. The lower end of the yoke 20 carries an axle 24 bearing a bridge piece 23, each end of which is connected by a coil spring 22 to a lug on yoke 20. An extension of lever 11 mounts a roller 26 adapted to contact bridge piece 23, the surface of which is shaped so that a small deflection of lever 11 lengthens one or other spring 22, but further displacement of lever 11 does not further rock the bridge piece. Screws 28 threaded into bridge piece 23 and abutting the yoke are used for initial adjustment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2916852A GB727513A (en) | 1952-11-18 | 1952-11-18 | Improvements in and relating to aircraft controls |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2916852A GB727513A (en) | 1952-11-18 | 1952-11-18 | Improvements in and relating to aircraft controls |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB727513A true GB727513A (en) | 1955-04-06 |
Family
ID=10287211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2916852A Expired GB727513A (en) | 1952-11-18 | 1952-11-18 | Improvements in and relating to aircraft controls |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB727513A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3058701A (en) * | 1958-04-18 | 1962-10-16 | English Electric Co Ltd | Hydraulic servo flying controls for aircraft |
| FR2213870A1 (en) * | 1973-01-17 | 1974-08-09 | Lucas Aerospace Ltd | |
| DE4228390A1 (en) * | 1992-08-26 | 1994-03-03 | Deutsche Aerospace Airbus | Centering unit for an aircraft rudder |
-
1952
- 1952-11-18 GB GB2916852A patent/GB727513A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3058701A (en) * | 1958-04-18 | 1962-10-16 | English Electric Co Ltd | Hydraulic servo flying controls for aircraft |
| FR2213870A1 (en) * | 1973-01-17 | 1974-08-09 | Lucas Aerospace Ltd | |
| DE4228390A1 (en) * | 1992-08-26 | 1994-03-03 | Deutsche Aerospace Airbus | Centering unit for an aircraft rudder |
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