GB856139A - Improvements in automatic pilots for aircraft - Google Patents
Improvements in automatic pilots for aircraftInfo
- Publication number
- GB856139A GB856139A GB33702/56A GB3370256A GB856139A GB 856139 A GB856139 A GB 856139A GB 33702/56 A GB33702/56 A GB 33702/56A GB 3370256 A GB3370256 A GB 3370256A GB 856139 A GB856139 A GB 856139A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rate
- signals
- control
- aircraft
- pitch
- 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
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/02—Control of position or course in two dimensions
- G05D1/0202—Control of position or course in two dimensions specially adapted to aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
856,139. Automatic control systems for aircraft. SMITH & SONS (ENGLAND) Ltd., S. Nov. 5, 1957 [Nov. 5, 1956], No. 33702/56. Class 38 (4). In an aircraft automatic piloting system the elevators are deflected at a rate corresponding to the actual rate of pitch about a horizontal axis as computed from the rates of turn about athwartship and vertical axes in the aircraft and the actual roll angle. Elevator control.-As shown, electrical signals from gyros 1 and 2 rigidly mounted on an aircraft and respectively responsive to rates of roll about the athwartship and vertical aircraft axes are applied to the stator of a resolver 3 the rotor of which is positioned in accordance with actual roll angle by a repeater motor 4 controlled by signals from a gyro vertical 5. The output signal from the rotor of resolver 3, which is thus proportional to the rate of pitch about a truly horizontal axis, is applied to a servomotor system 13 which, by virtue of rate feedback, corrects pitch by adjusting the elevators (not shown) at a rate corresponding to the rate of pitch. Signals from any one of three devices 8, 9, 10 respectively responsive to altitude, air speed or radio glide path deviations may also be selected to control servomotor 13 and thus maintain a desired altitude or speed. A computer 7 adds differential and integral components to the altitude or speed control. Aileron control.-To maintain a desired course, signals from a magnetic or radio compass 16 are combined with signals dependent on roll angle, rate of turn, and rate of roll to control a rate servomotor system 21 adjusting the ailerons. Signal limiters 33, 36, signal smoother 34, and a device 35 to set the relative magnitude of the control components, are provided. Rudder control.-Course deviation signals combined with roll angle signals and rate of turn signals are differentiated by a computer 24 and serve to control, in conjunction with signals from a side-slip detector 26, a rate servomotor system 28 adjusting the rudder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB33702/56A GB856139A (en) | 1956-11-05 | 1956-11-05 | Improvements in automatic pilots for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB33702/56A GB856139A (en) | 1956-11-05 | 1956-11-05 | Improvements in automatic pilots for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB856139A true GB856139A (en) | 1960-12-14 |
Family
ID=10356357
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB33702/56A Expired GB856139A (en) | 1956-11-05 | 1956-11-05 | Improvements in automatic pilots for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB856139A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114248911A (en) * | 2021-12-24 | 2022-03-29 | 兰州飞行控制有限责任公司 | Helicopter electric series steering engine control signal adjusting method |
-
1956
- 1956-11-05 GB GB33702/56A patent/GB856139A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114248911A (en) * | 2021-12-24 | 2022-03-29 | 兰州飞行控制有限责任公司 | Helicopter electric series steering engine control signal adjusting method |
| CN114248911B (en) * | 2021-12-24 | 2024-03-01 | 兰州飞行控制有限责任公司 | Helicopter electric series steering engine control signal adjustment method |
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