GB1344373A - Electrohydraulic control of a hydraulic actuator - Google Patents

Electrohydraulic control of a hydraulic actuator

Info

Publication number
GB1344373A
GB1344373A GB3581871A GB3581871A GB1344373A GB 1344373 A GB1344373 A GB 1344373A GB 3581871 A GB3581871 A GB 3581871A GB 3581871 A GB3581871 A GB 3581871A GB 1344373 A GB1344373 A GB 1344373A
Authority
GB
United Kingdom
Prior art keywords
pressure
servovalves
spool
comparator
gate
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
GB3581871A
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of GB1344373A publication Critical patent/GB1344373A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15BSYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B21/00Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C13/00Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15BSYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B18/00Parallel arrangements of independent servomotor systems

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Pressure Circuits (AREA)
  • Servomotors (AREA)
  • Magnetically Actuated Valves (AREA)

Abstract

1344373 Fluid-pressure servomotor systems MESSERSCHMITT-BOLKOW-BLOHM GmbH 29 July 1971 [21 Aug 1970] 35818/71 Heading G3P A hydraulic actuator is controlled by a spool valve 2, Fig.1, having one end subjected to pressure from a motive fluid supply 8 and the other end connected by a common line 4 to two or more servovalves 1 which also supply signals to an error monitoring system. The servovalves are operated by solenoids 16 and have their outputs from ports 12 connected to a comparator 13 which connects a pressure port 20 through an orifice 25 to a drain 23 when the pressures from the ports 12 are unequal. The change in pressure operates a warning device or a safety circuit. The circuit shown in Fig. 1 may be duplicated and the outputs from the two comparators fed to an AND gate so that the system continues to operate if only one circuit develops a fault. A further modification is shown in Fig.3 in which the outputs from three comparators 59 are fed to an AND gate 60 so that no safety switching operation occurs until two spurious servovalve output signals are produced. The warning device shown in Fig. 4 may be interposed between each comparator and the AND gate when the circuit of Fig. 1 is duplicated and has outlets 67 and 68 connected to the comparator and the AND gate, respectively, while a third outlet 69 supplies the servovalves from a pressure source 65. When the comparator reduces the pressure in outlet 67, a spool 71 is moved to the left by the supply pressure so that the servovalves are connected to a drain 66. An orifice 72 prevents pressure fluid flowing to drain through the comparator. The spool 71 is returned by the spring 73 when a solenoid valve 70 is de-energized for a brief period. The supply to the servovalves may alternatively be discontinued by de-energization of the solenoid valve 70. In modified forms of the warning device, the spool is first displaced by flow through a restrictor, the solenoid valve is replaced by a pair of valves or by a valve which can be energized to move to either side of a neutral position. In the last modification, a delay valve is also provided to isolate the line 67 from direct connection with the pressure medium inlet while the spool is re-set. The line 67 is recharged through a restrictor and the spool is retained in the re-set position only when the outlet pressures from the servovalves are again uniform. The lines 68 from the warning devices may be connected as shown to the duplicated AND gate of Fig.17 in which failure of pressure in either the upper or lower pair of lines 68 causes loss of pressure in the other pair through lines 131 so that springs 126 operate safety switches 128 through plungers 122...125.
GB3581871A 1970-08-21 1971-07-29 Electrohydraulic control of a hydraulic actuator Expired GB1344373A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2041681A DE2041681C2 (en) 1970-08-21 1970-08-21 Method and device for the electrohydraulic control of a hydraulic actuator

Publications (1)

Publication Number Publication Date
GB1344373A true GB1344373A (en) 1974-01-23

Family

ID=5780425

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3581871A Expired GB1344373A (en) 1970-08-21 1971-07-29 Electrohydraulic control of a hydraulic actuator

Country Status (4)

Country Link
US (1) US3834279A (en)
DE (1) DE2041681C2 (en)
FR (1) FR2103437B1 (en)
GB (1) GB1344373A (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2615345C3 (en) * 1976-04-08 1984-05-10 Liebherr-Aero-Technik Gmbh, 8998 Lindenberg Self-monitored actuator, in particular for aircraft rudders
US4143583A (en) * 1977-09-23 1979-03-13 Pneumo Corporation Redundant EHV fault detector
US4538504A (en) * 1983-11-18 1985-09-03 General Electric Company Fail-safe servovalve system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1401296A1 (en) * 1958-07-15 1968-10-24 Erich Herion Multi-way valve with auxiliary valve control, especially multi-way solenoid valve
US3391611A (en) * 1965-08-23 1968-07-09 Bell Aerospace Corp Hydraeric control system
US3496836A (en) * 1968-01-02 1970-02-24 Bell Aerospace Corp Redundant control system having fail-operate fail-neutral and channel emergency select
GB1272859A (en) * 1969-11-25 1972-05-03 Hobson Ltd H M Improvements in position control servo systems

Also Published As

Publication number Publication date
DE2041681B2 (en) 1972-03-16
DE2041681C2 (en) 1978-06-22
FR2103437B1 (en) 1975-07-11
FR2103437A1 (en) 1972-04-14
US3834279A (en) 1974-09-10
DE2041681A1 (en) 1972-03-16

Similar Documents

Publication Publication Date Title
US3992979A (en) Hydraulic actuating arrangements
US9528534B2 (en) Hydraulic or pneumatic drive for actuating a fitting comprising a control valve or selector valve
US2775982A (en) Differential-piston valve and dual pilot-valve control therefor
US3874269A (en) Hydraulic actuator controls
US3872773A (en) Position controlling
US3474828A (en) Fluid control switching arrangements
US3702575A (en) Redundant hydraulic control system for actuators
US3212523A (en) Fluid system and relief valve assembly therefor
US3029061A (en) Air-hydraulic control unit
EP0021742B1 (en) Hydraulic actuator control
US3927602A (en) Pressure follow-up control system for servo steering gears or similar devices
GB1140221A (en) Improvements in or relating to fluid flow control
US3790127A (en) Hydraulic valve
GB1344373A (en) Electrohydraulic control of a hydraulic actuator
US3987702A (en) Method and device for electrohydraulic control of a hydraulic actuator
US3543641A (en) Control for spoilers and like aerodynamic actuators of aircraft
GB1152771A (en) Hydraeric Control System
GB1292162A (en) Improvements in and relating to the electro-hydraulic remote control of hydraulic multi-position valves
US4155288A (en) Control system for a fluid pressure operated actuator arrangement
GB1291888A (en) Improvements in or relating to the electrohydraulic remote control of hydraulic control valves
US3488029A (en) Return pressure compensated hydraeric signal comparator
US3143042A (en) Electro-hydraulic servomotor
US4576198A (en) Servovalve with integrated failure monitoring
GB2082799A (en) Hydraulic actuator systems
US4054154A (en) Self monitoring redundant hydraeric control system

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee