GB1081792A - Creation of Inventions and Patents with Artificial Intelligence

GB1081792A – Electrical transmission system
– Google Patents

GB1081792A – Electrical transmission system
– Google Patents
Electrical transmission system

Info

Publication number
GB1081792A

GB1081792A
GB3128/65A
GB312865A
GB1081792A
GB 1081792 A
GB1081792 A
GB 1081792A
GB 3128/65 A
GB3128/65 A
GB 3128/65A
GB 312865 A
GB312865 A
GB 312865A
GB 1081792 A
GB1081792 A
GB 1081792A
Authority
GB
United Kingdom
Prior art keywords
actuator
driven
actuators
nozzles
amplifier
Prior art date
1965-01-25
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

Application number
GB3128/65A
Inventor
John Edward Bourne
John Albert Simpson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

Sperry Gyroscope Co Ltd

Original Assignee
Sperry Gyroscope Co Ltd
Priority date (The priority date 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 date listed.)
1965-01-25
Filing date
1965-01-25
Publication date
1967-08-31

1965-01-25
Application filed by Sperry Gyroscope Co Ltd
filed
Critical
Sperry Gyroscope Co Ltd

1965-01-25
Priority to GB3128/65A
priority
Critical
patent/GB1081792A/en

1966-01-14
Priority to US520762A
priority
patent/US3454852A/en

1967-08-31
Publication of GB1081792A
publication
Critical
patent/GB1081792A/en

Status
Expired
legal-status
Critical
Current

Links

Espacenet

Global Dossier

Discuss

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

G05D1/0055—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements

G05D1/0077—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements using redundant signals or controls

B—PERFORMING OPERATIONS; TRANSPORTING

B64—AIRCRAFT; AVIATION; COSMONAUTICS

B64C—AEROPLANES; HELICOPTERS

B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers

B64C13/24—Transmitting means

B—PERFORMING OPERATIONS; TRANSPORTING

B64—AIRCRAFT; AVIATION; COSMONAUTICS

B64C—AEROPLANES; HELICOPTERS

B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers

B64C13/24—Transmitting means

B64C13/38—Transmitting means with power amplification

B64C13/50—Transmitting means with power amplification using electrical energy

B64C13/505—Transmitting means with power amplification using electrical energy having duplication or stand-by provisions

Abstract

1,081,792. Controlling V.T.O.L. aircraft. SPERRY GYROSCOPE CO. Ltd. Jan. 7, 1966 [Jan. 25, 1965], No. 3128/65. Heading B7G. [Also in Division G3] The pitch-angle of a hovering aircraft may be stabilized partially by movement of stick 9 to swivel flaps 8 at puffer nozzles 4, 5, but, if a disturbance is not counteracted completely a signal is produced at terminal 20A which is connected through R.C.-networks with rate gyro unit 16A and stick pick-off 17A. This signal passes to amplifier 15A so that motor 14A adjusts actuator A which is duplicated by actuator B controlled in the same manner. The amplifiers 15A, 15B, receive feedback signals from potentiometers associated with the actuators, the potentiometers 25A, 25B being crosscoupled and potentiometers 28A, 28B, being straight-coupled. Unequal resistors are placed in feedback leads 21A, 22A, to prevent reaching equilibrium with the actuators in dissimilar altitudes. If the actuator A is jammed at maximum extension, a large negative feedback signal is fed to amplifier 15A through lead 22A, but the motor 14A is not moved. A corresponding signal is supplied to amplifier 15B over lead 21B so that actuator B contracts. The length of the transmission link 10 is very nearly what it would be if both actuators were working properly. A fault-indicating device 30 responds to the voltages at points 27A, 27B, which normally should be equal. If automatic operation is to continue after the actuator A has jammed as described, lead 21B is earthed through capacitor 29, and potentiometer 28B must now develop twice its previous potential to counteract signals from the rate gyro unit and stick pick-off. If wiper 27A is open-circuited, it is driven with the wiper 25A to the negative end of its potentioneter. Actuator B is driven in the opposite direction, channel B operating at an increased gain. When positive power is removed accidentally from potentiometers 28A, 25A, the system operates normally while the wipers lie on the negative portions. When the wipers move on to the positive portions, motor 14A is driven to an end position, and motor 14B is driven to compensate. If wiper 24A is opencircuited, the gain of actuators A and B are respectively decreased and increased. In the event of amplifier 15A not responding to an input signal, leaving actuator A offset from null, then actuator B is driven to a nearly equal and opposite offset. The outputs from the rate gyro and pilot’s stick pick-off are cross-coupled between the two channels to ensure that the control signals applied to the channels are substantially identical. Puffer nozzles, similar to nozzles 4, 5, are provided at the wing tips, all nozzles being fed from jet-lift engines 2, 3 and all are swivelable to provide yaw control.

GB3128/65A
1965-01-25
1965-01-25
Electrical transmission system

Expired

GB1081792A
(en)

Priority Applications (2)

Application Number
Priority Date
Filing Date
Title

GB3128/65A

GB1081792A
(en)

1965-01-25
1965-01-25
Electrical transmission system

US520762A

US3454852A
(en)

1965-01-25
1966-01-14
Redundant servo control system with crossfeeding of feedback for use in an autopilot

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

GB3128/65A

GB1081792A
(en)

1965-01-25
1965-01-25
Electrical transmission system

Publications (1)

Publication Number
Publication Date

GB1081792A
true

GB1081792A
(en)

1967-08-31

Family
ID=9752443
Family Applications (1)

Application Number
Title
Priority Date
Filing Date

GB3128/65A
Expired

GB1081792A
(en)

1965-01-25
1965-01-25
Electrical transmission system

Country Status (2)

Country
Link

US
(1)

US3454852A
(en)

GB
(1)

GB1081792A
(en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

GB1295859A
(en)

1969-09-03
1972-11-08

US3573587A
(en)

1969-09-16
1971-04-06
Smiths Industries Ltd
Multiplex systems

US4035705A
(en)

1975-03-17
1977-07-12
Sperry Rand Corporation
Fail-safe dual channel automatic pilot with maneuver limiting

JP3012644B1
(en)

1999-03-18
2000-02-28
株式会社コミュータヘリコプタ先進技術研究所

Servo actuator device and aircraft operation control device

Family Cites Families (3)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US3027878A
(en)

1959-06-10
1962-04-03
Honeywell Regulator Co
Fluid motor control apparatus

US3070071A
(en)

1960-03-11
1962-12-25
North American Aviation Inc
Failure protected signal translating system

US3269676A
(en)

1965-04-30
1966-08-30
Sperry Rand Corp
Valve actuator apparatus

1965

1965-01-25
GB
GB3128/65A
patent/GB1081792A/en
not_active
Expired

1966

1966-01-14
US
US520762A
patent/US3454852A/en
not_active
Expired – Lifetime

Also Published As

Publication number
Publication date

US3454852A
(en)

1969-07-08

Contact information