GB1249658A - Improvements in or relating to servo-control systems, especially for aircraft controls - Google Patents

Improvements in or relating to servo-control systems, especially for aircraft controls

Info

Publication number
GB1249658A
GB1249658A GB53391/68A GB5339168A GB1249658A GB 1249658 A GB1249658 A GB 1249658A GB 53391/68 A GB53391/68 A GB 53391/68A GB 5339168 A GB5339168 A GB 5339168A GB 1249658 A GB1249658 A GB 1249658A
Authority
GB
United Kingdom
Prior art keywords
jet tube
movement
pistons
piston
spring
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
GB53391/68A
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.)
Honeywell Inc
Original Assignee
Honeywell Inc
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 Honeywell Inc filed Critical Honeywell Inc
Publication of GB1249658A publication Critical patent/GB1249658A/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
    • F15B9/00—Servomotors with follow-up action, e.g. obtained by feed-back control, i.e. in which the position of the actuated member conforms with that of the controlling member
    • 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
    • F15B18/00—Parallel arrangements of independent servomotor systems
    • 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
    • G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
    • G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Fluid-Pressure Circuits (AREA)
  • Supply Devices, Intensifiers, Converters, And Telemotors (AREA)

Abstract

1,249,658. Fluid-pressure servomotor systems. HONEYWELL Inc. Nov. 11, 1968 [Nov. 17, 1967], No. 53391/68. Heading G3P. A positioning system for an aircraft control surface has four redundant channels each of which includes an amplifier 25 which receives a pilots control signal and transmits it to a torque motor 26 connected to a jet tube 52 controlling a servopiston 60. The servopistons control a main valve (not shown) through link 63 and the main valve positions a main servomotor linked to the control surface. A spring 64 provides positional feedback to the jet tube; alternatively, an electrical feedback signal could be transmitted to amplifier 25. If the latter should fail, the large pressure difference created by the jet tube, due to movement thereof by spring 64 following movement of piston 60 by link 63, causes movement of one of pistons 93, 94 to actuate switch 72 to de-energize coil 102 to allow closure of valve 50 thereby stopping flow to the jet tube. If piston 60 should sieze, or, due to lack of complete synchronism, be unable to follow the movement of 63, the pressure difference thereacross eventually causes movement of piston 67 which, via spring 69, moves the jet tube to neutral. This ensures load equalization among pistons 60. Under normal conditions, supply valve 50 opens following momentary closing of switch 80 which energizes coils 86, 102 if pistons 93, 94 are positioned as shown due to normal pressures from the jet tube.
GB53391/68A 1967-11-17 1968-11-11 Improvements in or relating to servo-control systems, especially for aircraft controls Expired GB1249658A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US68399467A 1967-11-17 1967-11-17

Publications (1)

Publication Number Publication Date
GB1249658A true GB1249658A (en) 1971-10-13

Family

ID=24746290

Family Applications (1)

Application Number Title Priority Date Filing Date
GB53391/68A Expired GB1249658A (en) 1967-11-17 1968-11-11 Improvements in or relating to servo-control systems, especially for aircraft controls

Country Status (6)

Country Link
US (1) US3554084A (en)
DE (1) DE1809344A1 (en)
FR (1) FR1593218A (en)
GB (1) GB1249658A (en)
NL (1) NL6816366A (en)
SE (1) SE341692B (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3679156A (en) * 1970-07-20 1972-07-25 Ltv Electrosystems Inc Fly-by-wire
US3727520A (en) * 1970-11-06 1973-04-17 Sperry Rand Corp Digital electrohydraulic servo system
US3662550A (en) * 1971-01-11 1972-05-16 Sundstrand Corp Actuator system
US3826174A (en) * 1971-03-03 1974-07-30 Bendix Corp Quadruple redundant closed loop electro-hydraulic servo system
FR2158124B1 (en) * 1971-11-04 1974-10-31 Gen Electric
GB1578537A (en) * 1976-07-10 1980-11-05 Lucas Industries Ltd Control system for a fluid pressure operated actuator arrangement
US4338965A (en) * 1980-06-02 1982-07-13 Moog Inc. Self-monitoring dual-spool servovalve
IL115248A (en) * 1994-09-29 2000-07-16 Gen Electric Hydraulic failsafe system and method for an axisymmetric vectoring nozzle
US5740988A (en) * 1995-04-13 1998-04-21 General Electric Company Axisymmetric vectoring nozzle actuating system having multiple power control circuits
SE513900C2 (en) * 1999-01-19 2000-11-20 Abb Ab Device for monitoring the operation of a drive device

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2947286A (en) * 1958-01-29 1960-08-02 Bell Aerospace Corp Integrated actuator
US3190185A (en) * 1961-07-11 1965-06-22 Honeywell Inc Servomotor with monitor
US3171329A (en) * 1963-05-06 1965-03-02 Honeywell Regulator Co Control apparatus
US3270623A (en) * 1964-04-13 1966-09-06 Moog Inc Fluid powered servomechanism of a redundant, monitor type
US3272062A (en) * 1965-10-07 1966-09-13 Ltv Electrosystems Inc Servo valve synchronizer

Also Published As

Publication number Publication date
SE341692B (en) 1972-01-10
DE1809344A1 (en) 1969-07-10
US3554084A (en) 1971-01-12
NL6816366A (en) 1969-05-20
FR1593218A (en) 1970-05-25

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