GB886228A - Improvements in automatic stabilising apparatus for aircraft - Google Patents
Improvements in automatic stabilising apparatus for aircraftInfo
- Publication number
- GB886228A GB886228A GB20102/58A GB2010258A GB886228A GB 886228 A GB886228 A GB 886228A GB 20102/58 A GB20102/58 A GB 20102/58A GB 2010258 A GB2010258 A GB 2010258A GB 886228 A GB886228 A GB 886228A
- Authority
- GB
- United Kingdom
- Prior art keywords
- signals
- control
- rate
- potentiometer
- amplifiers
- 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
- 230000003019 stabilising effect Effects 0.000 title 1
- 101100446506 Mus musculus Fgf3 gene Proteins 0.000 abstract 2
- 101000767160 Saccharomyces cerevisiae (strain ATCC 204508 / S288c) Intracellular protein transport protein USO1 Proteins 0.000 abstract 2
- 230000000087 stabilizing effect Effects 0.000 abstract 2
- 238000001514 detection method Methods 0.000 abstract 1
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
- G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls
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)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
886,228. Automatic control systems for aircraft. SHORT BROS. & HARLAND Ltd. Aug. 5, 1959 [June 23, 1958], No. 20102/58. Class 38 (4). In an aircraft automatic stabilizing system, signals from each of a number of gyroscopes responsive to rate of turn about the same axis are integrated, corrected by comparison with signals from a single attitude gyro, and applied to control servomotors driving common stabilizing means. In Fig. 1 electric signals from a potentiometer-type pick-off R 5 associated with a rate of pitch gyro RG are integrated by a motor-type integrator INT 1 the output from a potentiometer R 2 of which is applied, through a limiting amplifier SA, torque motor TM, hydraulic control valve V, and hydraulic servomotor SM, to control the aircraft through a linkage L so as to maintain a desired angle of pitch. Position and rate feedback signals from pick-offs R 4 and VPO operated by the servomotor and control valve respectively are applied to the input of amplifier SA. Signals from pick-off VPO are also applied to a fault detection circuit as described in Specification 853,674. The control system is triplicated, two other channels (II and III, not shown in detail) involving separate rate gyros, integrators, amplifiers and hydraulic servomotors being provided to control linkage L. To monitor the rate gyros electric signals from a single attitude gyro AG are compared with signals from each integrator in drift-controlled amplifiers DCA the outputs of which are applied to the integrators to correct errors developed in the signals from the rate gyros. Manual pitch adjustments are effected by a control column CC operating potentiometers CR 1 to apply signals to amplifiers SA. The differences between signals from a potentiometer CR 2 also operated by the control column and signals from the attitude gyro AG are integrated by a second integrator INT 2 the outputs of which are applied to amplifiers SA to maintain balance during pitch adjustments. In a modification, Fig. 2 (not shown), potentiometer CR 2 is dispensed with and the differences between signals from potentiometers CR 1 and those from integrators INT 1 control integrator INT 2 . Remote control by radio is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB20102/58A GB886228A (en) | 1958-06-23 | 1958-06-23 | Improvements in automatic stabilising apparatus for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB20102/58A GB886228A (en) | 1958-06-23 | 1958-06-23 | Improvements in automatic stabilising apparatus for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB886228A true GB886228A (en) | 1962-01-03 |
Family
ID=10140414
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB20102/58A Expired GB886228A (en) | 1958-06-23 | 1958-06-23 | Improvements in automatic stabilising apparatus for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB886228A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0058861A1 (en) * | 1981-02-17 | 1982-09-01 | Bell Helicopter Textron Inc. | Multiple loop control system |
| US4542679A (en) * | 1981-02-17 | 1985-09-24 | Textron Inc. | Multiple loop control system |
-
1958
- 1958-06-23 GB GB20102/58A patent/GB886228A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0058861A1 (en) * | 1981-02-17 | 1982-09-01 | Bell Helicopter Textron Inc. | Multiple loop control system |
| US4542679A (en) * | 1981-02-17 | 1985-09-24 | Textron Inc. | Multiple loop control system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA1050633A (en) | Semi-automatic flight control system utilizing limited authority stabilization system | |
| GB1218471A (en) | Automatic pilot systems for aircraft | |
| GB1260223A (en) | Flight control system | |
| US3718293A (en) | Dynamic lead guidance system for homing navigation | |
| GB890264A (en) | Rotatable antenna assembly | |
| US2586034A (en) | Aircraft automatic pilot | |
| GB886228A (en) | Improvements in automatic stabilising apparatus for aircraft | |
| GB1318872A (en) | Stabilized platform | |
| US3071337A (en) | Automatic pilot | |
| GB1395448A (en) | Aircraft control system | |
| US2834563A (en) | Aircraft automatic pilot | |
| US3098627A (en) | Automatic stabilizing apparatus for aircraft | |
| GB963134A (en) | Track guidance apparatus for aircraft | |
| GB929556A (en) | Aircraft maneuver stabilizer | |
| GB1245066A (en) | Electrical autopilot apparatus for ships | |
| US3222013A (en) | Automatic pilots for aircraft | |
| GB845920A (en) | A gyroscopic reference device for an automatic control system | |
| GB829739A (en) | Aircraft control systems | |
| GB1202778A (en) | Improvements relating to flight aid systems | |
| GB839180A (en) | Improvements in or relating to control systems, especially aircraft control systems | |
| GB835265A (en) | Aircraft navigation apparatus | |
| GB845023A (en) | Aircraft automatic control systems | |
| GB643749A (en) | Improvements in or relating to gyro-vertical slaving systems | |
| GB974864A (en) | Improvements in or relating to aircraft attitude automatic control apparatus | |
| JPH0218198A (en) | Attitude controlling method of space flying object by wheel |