GB807111A - Pitch control of aircraft - Google Patents
Pitch control of aircraftInfo
- Publication number
- GB807111A GB807111A GB27637/56A GB2763756A GB807111A GB 807111 A GB807111 A GB 807111A GB 27637/56 A GB27637/56 A GB 27637/56A GB 2763756 A GB2763756 A GB 2763756A GB 807111 A GB807111 A GB 807111A
- Authority
- GB
- United Kingdom
- Prior art keywords
- amplifier
- signal
- inductive
- altitude
- rate
- 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
- 230000001939 inductive effect Effects 0.000 abstract 11
- 230000001419 dependent effect Effects 0.000 abstract 6
- 230000006698 induction Effects 0.000 abstract 1
- 238000002955 isolation Methods 0.000 abstract 1
- 238000004804 winding 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
- G05D1/04—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
- G05D1/0615—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind
- G05D1/0623—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind by acting on the pitch
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
807,111. Automatic control systems for aircraft. BENDIX AVIATION CORPORATION. Sept. 10, 1956 [Sept. 22, 1955], No.27637/56. Class 38 (4). In an aircraft control system the elevators are controlled by a signal dependent on rate of change of altitude combined with a decaying signal which is initially dependent on change of pitch. As shown a signal dependent on altitude is developed in a winding 26 of an inductive pick-off 24 associated with an aneroid 20. This signal is applied through an amplifier 27 to control an induction motor 29 which adjusts pick-off 24 to give zero output. An inductive device 41 and an inductive generator 33, both driven by motor 29, thus respectively produce signals, representative of altitude and rate of change of altitude, which are applied through an isolation amplifier 54 to an amplifier 80 controlling a servomotor 70 adjusting the elevators to maintain constant altitude. A signal dependent on pitch altitude is also developed by an inductive pick-off 87 associatd with a gyro vertical 85 and applied through an inductive device 90 to amplifier 80. This signal is however gradually reduced to zero by a motor 97 which is controlled through an amplifier 95 by the signal from inductive device 90. The speed of motor 97 is made dependent on the signal from inductive device 90 by virtue of rate feedback from a tachometer generator 99. A signal dependent on rate of change of pitch, developed by an inductive pick-off 60 associated with a pitch rate gyro 64, is applied to amplifier 80. Positional and rate follow-up signals, developed by an inductive device 69 and inductive generator 67 respectively, are also applied to amplifier 80. Climb or dive is effected by (a) operating a push button 40 to open switch 45 and thereby deenergizing a clutch 44 so that pick-up 41 no longer responds to altitude changes and (b) moving a lever 39 to set the desired rate of climb or dive by adjusting an inductive device 37 the output of which is applied to amplifier 80.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US807111XA | 1955-09-22 | 1955-09-22 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB807111A true GB807111A (en) | 1959-01-07 |
Family
ID=22159125
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB27637/56A Expired GB807111A (en) | 1955-09-22 | 1956-09-10 | Pitch control of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB807111A (en) |
-
1956
- 1956-09-10 GB GB27637/56A patent/GB807111A/en not_active Expired
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