GB807917A - Control systems for aircraft - Google Patents
Control systems for aircraftInfo
- Publication number
- GB807917A GB807917A GB2192455A GB2192455A GB807917A GB 807917 A GB807917 A GB 807917A GB 2192455 A GB2192455 A GB 2192455A GB 2192455 A GB2192455 A GB 2192455A GB 807917 A GB807917 A GB 807917A
- Authority
- GB
- United Kingdom
- Prior art keywords
- valve
- control
- aircraft
- electrical
- pilot valve
- 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
- B64C13/24—Transmitting means
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
- Feedback Control In General (AREA)
Abstract
807,917. Automatic control systems for aircraft. SPERRY GYROSCOPE CO. Ltd. July 12, 1956 [July 29, 1955], No. 21924/55. Addition to 803,572. Class 38 (4). [Also in Group XXIX and XXXIII] In a system, as in the parent Specification, in which a main hydraulic servomotor actuating a control surface of an aircraft may be automatically or manually controlled through an electrical control system or manually controlled through a mechanical control system, the arrangement for changing over from electrical control to mechanical control is modified. As shown, a differential linkage 310 responsive to the relative displacement of a manual controller and the main servomotor (not shown) positions a pilot valve 308 which controls the main servomotor through a solenoid-operated change-over valve 311 and a sleeve valve 301. Follow-up from valve 301 is provided through a lever 306 operating a sleeve 307 associated with pilot valve 308. Changeover to electrical control is effected by energizing solenoid-operated changeover valve 311 so that pilot valve 308 is no longer effective to control valve 301 and a pilot valve 302 operated by a device 208 responsive to electrical error signals produced manually or by attitude references on the aircraft, becomes effective to control the main servomotor through valves 311 and 301. To prevent a jolt when changing from electrical to mechanical control, valve 301 may be arranged to respond slowly to pilot valve 308. Specification 803,573, [Group XXIX], is referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2192455A GB807917A (en) | 1954-03-17 | 1955-07-29 | Control systems for aircraft |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB7783/54A GB803572A (en) | 1954-03-17 | 1954-03-17 | Control systems for aircraft |
GB2192455A GB807917A (en) | 1954-03-17 | 1955-07-29 | Control systems for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB807917A true GB807917A (en) | 1959-01-21 |
Family
ID=10171098
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2192455A Expired GB807917A (en) | 1954-03-17 | 1955-07-29 | Control systems for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB807917A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4537220A (en) * | 1983-02-28 | 1985-08-27 | Sundstrand Corporation | Two member boost stage valve for a hydraulic control |
-
1955
- 1955-07-29 GB GB2192455A patent/GB807917A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4537220A (en) * | 1983-02-28 | 1985-08-27 | Sundstrand Corporation | Two member boost stage valve for a hydraulic control |
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