GB418542A - Device for automatically regulating the altitude of aircraft - Google Patents
Device for automatically regulating the altitude of aircraftInfo
- Publication number
- GB418542A GB418542A GB33205/33A GB3320533A GB418542A GB 418542 A GB418542 A GB 418542A GB 33205/33 A GB33205/33 A GB 33205/33A GB 3320533 A GB3320533 A GB 3320533A GB 418542 A GB418542 A GB 418542A
- Authority
- GB
- United Kingdom
- Prior art keywords
- disc
- motor
- indicator
- altitude
- contacts
- 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
- G05D1/04—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
- G05D1/063—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind by acting on the motors
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)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Abstract
418,542. Regulating. SIEMENS & HALSKE AKT.-GES., Siemensstadt, Berlin. Nov. 27, 1933, Nos. 33205, 33206, and 33207. Convention dates, Nov. 26, 1932, March 18, 1933, and April 7, 1933. [Class 7 (vi).] In a device for automatically regulating the altitude of an aircraft by placing the propelling-force under the control of an altimeter which is adjusted to the desired altitude, a lever or like member of the control is adapted also for hand actuation, the hand and altimeter adjustments being independent of each other. In the construction shown in Fig. 1, a controlled member or indicator 1 of the altimeter is periodically depressed through the medium of a timing- device 5 upon an adjustable bank of contacts 2, which are connected individually with a set of contacts 6 on a fixed ring 7 co-operating with a rotatable contact disc 8, the position of which is alterable by a motor 15. The disc 8 is provided with two substantially semicircular contacts 9 with interposed insulation 10, and at the desired altitude, when the indicator 1 is depressed, it becomes associated with an insulated portion 10 of the disc 8 so that no electric circuit through the motor is completed. Should any deviation from the desired altitude occur, the indicator makes contact either to the right or left of its previous position and, by way of one of the contacts 6 and alternative circuits including the contacts 9, terminals 11, leads 12, relays 13 controlling the motor switch 14, battery 15<1>, and motor 15, drives the motor 15 in the appropriate direction to effect an adjustment of the engine control lever 21 and of the contact disc 8, which latter tends to move until the insulated portion 10 corresponds to the new position of the indicator 1. The mechanical connections from the motor include a worm shaft 16, wheel 17, shaft 18 on which is mounted an actuating-lever 20 for the control lever 21, an hydraulic damping-device 22, cranks 18<1>, 18<11> with a pin-and-slot connection 23, and shaft 25, a spring 24 tending to restore the position of the shaft 25 and disc 8. A sliding clutch 19 acting between the shaft 18 and lever 20 permits the pilot to adjust the levers 21 and 20 without affecting the elements of the connection on either side of it. By damping the movement imparted to the disc 8, the damping-device 22 prevents hunting of the aircraft about the desired altitude, while the spring 24 tends to restore the disc 8 and damper casing to their normal position. Adjustment for a new altitude is obtained by re-setting the indicator 1 and /or contact bank 2. Preferably, switches 121, 12<11> are arranged to break the motor circuit as the lever 21 reaches the limits of its movement. Modifications. In another construction (Fig. 2, not shown), the damping-device 22 is dispensed with and the disc 8 is replaced by a curved arm comprising two conducting-strips with an intervening insulating-portion. According to a further modification (Fig. 3, not shown), the indicator 1, in addition to being influenced by an aneroid barimeter or altimeter, is also subject to the influence of a vertical speed indicator or variometer, with the object of preventing hunting. Or in another arrangement, the additional control may be one regulated by the vertical acceleration, such as a pendulum weight operating in conjunction with a dashpot. In a still further modification, Fig. 6, hunting is prevented by inserting between the motor 15 and the rotary contacts 8<1>, 8<11> a velocity-ratio change gear comprising essentially a disc 73 rotated at a constant speed and a co-operating disc 69 normally disposed dentrally in relation to the disc 73, but displaceable to an eccentric position when the change of altitude is sufficiently rapid to influence a damping-device 65.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE418542X | 1932-11-26 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB418542A true GB418542A (en) | 1934-10-26 |
Family
ID=6448860
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB33205/33A Expired GB418542A (en) | 1932-11-26 | 1933-11-27 | Device for automatically regulating the altitude of aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB418542A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112180964A (en) * | 2020-10-10 | 2021-01-05 | 中国人民解放军海军航空大学 | Attitude tracking method of four-rotor aircraft based on nonlinear sliding mode |
-
1933
- 1933-11-27 GB GB33205/33A patent/GB418542A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112180964A (en) * | 2020-10-10 | 2021-01-05 | 中国人民解放军海军航空大学 | Attitude tracking method of four-rotor aircraft based on nonlinear sliding mode |
CN112180964B (en) * | 2020-10-10 | 2022-07-22 | 中国人民解放军海军航空大学 | Attitude tracking method of four-rotor aircraft based on nonlinear sliding mode |
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