GB877172A - Improvements in or relating to automatic blind landing systems for aircraft - Google Patents
Improvements in or relating to automatic blind landing systems for aircraftInfo
- Publication number
- GB877172A GB877172A GB29682/58A GB2968258A GB877172A GB 877172 A GB877172 A GB 877172A GB 29682/58 A GB29682/58 A GB 29682/58A GB 2968258 A GB2968258 A GB 2968258A GB 877172 A GB877172 A GB 877172A
- Authority
- GB
- United Kingdom
- Prior art keywords
- amplifier
- rate
- heading
- control
- aircraft
- 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
- 230000001133 acceleration Effects 0.000 abstract 1
- 230000001419 dependent effect Effects 0.000 abstract 1
- 230000010355 oscillation Effects 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
- G05D1/02—Control of position or course in two dimensions
- G05D1/0202—Control of position or course in two dimensions specially adapted to aircraft
- G05D1/0204—Control of position or course in two dimensions specially adapted to aircraft to counteract a sudden perturbation, e.g. cross-wind, gust
-
- 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
- G05D1/04—Control of altitude or depth
- G05D1/06—Rate of change of altitude or depth
- G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
- G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
- G05D1/0676—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing
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
877,172. Automatic control systems for aircraft. AVIATION, MINISTER OF. Sept. 14, 1959 [Sept. 16, 1958], No. 29682/58. Class 38 (4). In an automatic blind landing system for aircraft, means responsive to height above the runway render signals proportional to the aircraft heading relative to the runway effective to determine rate of rudder application, and a supplementary control signal is applied to the ailerons in dependence on change of heading thereafter. As applied to an aircraft being flown by an automatic pilot to follow a radio defined approach and landing-path the control system shown is automatically rendered effective by means, e.g. a radio altimeter (not shown), when the aircraft descends to a height of 20 feet just prior to touchdown. Signals from a compass 11 are then applied to a selector 12 which is set to the heading of the runway so that a heading error signal is derived and applied through a gain control 21 and amplifier 19 to correct the heading by control of a servomotor 17 operating the rudder 15. Rate feedback from servomotor 17 to amplifier 19 ensures rudder operation at a rate corresponding to the output of amplifier 19. A rate of heading error signal derived by a resistance-capacity differentiating circuit 22 is applied through a gain control 23 as an anti-hunting signal to amplifier 19. A yaw acceleration signal derived through a differentiator 24 from a yaw rate gyro 14 is applied through a gain control 25 to amplifier 19 to suppress short-term yaw oscillations. Signals from a roll rate gyro 13 are applied through a gain control 27 and amplifier 20 to correct roll by control of a servomotor 18 operating ailerons 16. Rate feedback from servomotor 18 to amplifier 20 ensures aileron operation at a rate corresponding to the output of amplifier 20. Bank resulting from turn is countered by applying the signal from yaw rate gyro 14 through gain controls 26, 27 to amplifier 20. Instead of rate signals, signals dependent on angle of bank and change of heading may be used to control the ailerons.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB29682/58A GB877172A (en) | 1958-09-16 | 1958-09-16 | Improvements in or relating to automatic blind landing systems for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB29682/58A GB877172A (en) | 1958-09-16 | 1958-09-16 | Improvements in or relating to automatic blind landing systems for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB877172A true GB877172A (en) | 1961-09-13 |
Family
ID=10295421
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB29682/58A Expired GB877172A (en) | 1958-09-16 | 1958-09-16 | Improvements in or relating to automatic blind landing systems for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB877172A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110687780A (en) * | 2019-06-18 | 2020-01-14 | 蓝箭航天空间科技股份有限公司 | Carrier rocket rate gyro gain self-adaptive adjusting method, adjusting system and storage medium |
-
1958
- 1958-09-16 GB GB29682/58A patent/GB877172A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110687780A (en) * | 2019-06-18 | 2020-01-14 | 蓝箭航天空间科技股份有限公司 | Carrier rocket rate gyro gain self-adaptive adjusting method, adjusting system and storage medium |
| CN110687780B (en) * | 2019-06-18 | 2022-02-08 | 蓝箭航天空间科技股份有限公司 | Carrier rocket rate gyro gain self-adaptive adjusting method, adjusting system and storage medium |
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