GB1337423A - Actuators particularly for aircraft power control systems - Google Patents

Actuators particularly for aircraft power control systems

Info

Publication number
GB1337423A
GB1337423A GB2499070A GB1337423DA GB1337423A GB 1337423 A GB1337423 A GB 1337423A GB 2499070 A GB2499070 A GB 2499070A GB 1337423D A GB1337423D A GB 1337423DA GB 1337423 A GB1337423 A GB 1337423A
Authority
GB
United Kingdom
Prior art keywords
mechanical
electrical
input
feedback
valve
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
Application number
GB2499070A
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.)
British Aircraft Corp Ltd
Original Assignee
British Aircraft Corp 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.)
Filing date
Publication date
Application filed by British Aircraft Corp Ltd filed Critical British Aircraft Corp Ltd
Publication of GB1337423A publication Critical patent/GB1337423A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B13/00—Details of servomotor systems ; Valves for servomotor systems
    • F15B13/10—Special arrangements for operating the actuated device with or without using fluid pressure, e.g. for emergency use
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Pressure Circuits (AREA)
  • Control Of Position Or Direction (AREA)

Abstract

1337423 Fluid-pressure servomotor systems; automatic control of aircraft BRITISH AIRCRAFT CORP Ltd 21 May 1971 [22 May 1970] 24990/70 Headings G3P and G3R An aircraft rudder or aileron 12 is actuated by a jack 10 controlled by a valve 14a adjusted by an electrical system 18 and a mechanical system 19, the joint effect of the two systems being measured by an element 25 and supplied to a feedback loop 26 in the electrical system whereby the effect of the mechanical system is over-ridden while the electrical system is operative. The system 18 incorporates an amplifier 17 receiving a feedback signal from a pick-off 23 on the jack as well as from the element 25. The latter signals the position of the valve 14a which is operated by the electrical system through an electro-hydraulic actuator 15 and by the mechanical system through a floating "follow-up" lever 20 and a link 22. The element 25 thus provides a feedback signal corresponding to both the electrical and mechanical inputs so that the actuator 15 is moved to a position which differs from that dictated by the electrical input alone by an amount sufficient to cancel the mechanical input. When the valve 14a is in the required position, the feedback from the element 25 balances the input to the amplifier 17 and the jack moves until the feedback from the pick-off 23 reduces the input to actuator 15 to zero. The two systems receive inputs from an autopilot 16c and a transducer 16a on the pilot's contol column 16b.
GB2499070A 1970-05-22 1970-05-22 Actuators particularly for aircraft power control systems Expired GB1337423A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2499070 1970-05-22

Publications (1)

Publication Number Publication Date
GB1337423A true GB1337423A (en) 1973-11-14

Family

ID=10220447

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2499070A Expired GB1337423A (en) 1970-05-22 1970-05-22 Actuators particularly for aircraft power control systems

Country Status (3)

Country Link
DE (1) DE2125358A1 (en)
FR (1) FR2090237B1 (en)
GB (1) GB1337423A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2832898A1 (en) * 1978-07-27 1980-02-14 Messerschmitt Boelkow Blohm IRREVERSIBLE, HYDRAULIC ACTUATOR

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2657657B1 (en) * 1990-01-26 1992-04-17 Neyrpic ELECTROHYDRAULIC ACTUATOR WITH MECHANICAL MEMORY.
FR2740838B1 (en) * 1995-11-08 1997-12-05 Clotures Le Brun Sarl DEVICE FOR RELEASING A HYDRAULIC ACTUATOR ASSEMBLY

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB803575A (en) * 1955-07-29 1958-10-29 Sperry Gyroscope Co Ltd Improvements relating to aircraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2832898A1 (en) * 1978-07-27 1980-02-14 Messerschmitt Boelkow Blohm IRREVERSIBLE, HYDRAULIC ACTUATOR

Also Published As

Publication number Publication date
FR2090237B1 (en) 1977-01-28
DE2125358A1 (en) 1971-12-02
FR2090237A1 (en) 1972-01-14

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Legal Events

Date Code Title Description
PS Patent sealed
732 Registration of transactions, instruments or events in the register (sect. 32/1977)
732 Registration of transactions, instruments or events in the register (sect. 32/1977)
PCNP Patent ceased through non-payment of renewal fee