WO1999067537A1 - Systeme d'actionnement pour fonctions et unites de commande aerospatiales - Google Patents

Systeme d'actionnement pour fonctions et unites de commande aerospatiales Download PDF

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Publication number
WO1999067537A1
WO1999067537A1 PCT/GB1999/001926 GB9901926W WO9967537A1 WO 1999067537 A1 WO1999067537 A1 WO 1999067537A1 GB 9901926 W GB9901926 W GB 9901926W WO 9967537 A1 WO9967537 A1 WO 9967537A1
Authority
WO
WIPO (PCT)
Prior art keywords
fluid
actuator
annular chamber
mode
chamber
Prior art date
Application number
PCT/GB1999/001926
Other languages
English (en)
Inventor
Andrew Edward Uttley
Original Assignee
Bae Systems Plc
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 Bae Systems Plc filed Critical Bae Systems Plc
Priority to EP99926635A priority Critical patent/EP1090232A1/fr
Priority to JP55892099A priority patent/JP2002511135A/ja
Priority to AU43814/99A priority patent/AU4381499A/en
Publication of WO1999067537A1 publication Critical patent/WO1999067537A1/fr

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
    • F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
    • F15B11/02—Systems essentially incorporating special features for controlling the speed or actuating force of an output member
    • F15B11/024—Systems essentially incorporating special features for controlling the speed or actuating force of an output member by means of differential connection of the servomotor lines, e.g. regenerative circuits
    • 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
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/305—Directional control characterised by the type of valves
    • F15B2211/30505—Non-return valves, i.e. check valves
    • 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
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/305—Directional control characterised by the type of valves
    • F15B2211/30525—Directional control valves, e.g. 4/3-directional control valve
    • 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
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/305—Directional control characterised by the type of valves
    • F15B2211/3056—Assemblies of multiple valves
    • F15B2211/30565—Assemblies of multiple valves having multiple valves for a single output member, e.g. for creating higher valve function by use of multiple valves like two 2/2-valves replacing a 5/3-valve
    • F15B2211/3058—Assemblies of multiple valves having multiple valves for a single output member, e.g. for creating higher valve function by use of multiple valves like two 2/2-valves replacing a 5/3-valve having additional valves for interconnecting the fluid chambers of a double-acting actuator, e.g. for regeneration mode or for floating mode
    • 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
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/315—Directional control characterised by the connections of the valve or valves in the circuit
    • F15B2211/31505—Directional control characterised by the connections of the valve or valves in the circuit being connected to a pressure source and a return line
    • F15B2211/31511—Directional control characterised by the connections of the valve or valves in the circuit being connected to a pressure source and a return line having a single pressure source
    • 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
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/30—Directional control
    • F15B2211/315—Directional control characterised by the connections of the valve or valves in the circuit
    • F15B2211/3157—Directional control characterised by the connections of the valve or valves in the circuit being connected to a pressure source, an output member and a return line
    • F15B2211/31576—Directional control characterised by the connections of the valve or valves in the circuit being connected to a pressure source, an output member and a return line having a single pressure source and a single output 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
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/70—Output members, e.g. hydraulic motors or cylinders or control therefor
    • F15B2211/775—Combined control, e.g. control of speed and force for providing a high speed approach stroke with low force followed by a low speed working stroke with high force, e.g. for a hydraulic press

Definitions

  • This invention concerns actuator systems for aerospace controls and for other aerospace functions, for example for operating the control surfaces of an aircraft such as the ailerons, elevators, spoilers, rudder, and wing leading edge and trailing edge flaps and slats, or for controlling the airbrakes, arrester hook, flight refuelling probe, the undercarriage or pallets, doors and locks generally.
  • Fluid pressure operated actuator systems for powering aircraft control surfaces and for other aerospace functions are well known and basically comprise a piston and cylinder arrangement in which a piston rod is extended for actuating the control surface and retracted for returning the control surface to its original condition.
  • a known actuator system comprises an actuator having a piston moveable within a cylinder and a piston rod extending from the piston for actuating the aircraft control surface, the piston dividing the cylinder into a cylindrical chamber and an annular chamber.
  • the system also comprises a fluid supply line, a fluid return line, and a fluid direction control valve for controlling the supply of fluid to the cylindrical and annular chambers respectively for extension and retraction of the piston rod.
  • This known actuator system has two different modes of operation during actuator rod extension, which offer different maximum no-load rates of rod extension, and for the purposes of selecting and controlling the mode of operation the actuator system includes a number of control valves operable by the overall control system of the aircraft under pilot control.
  • the fluid supply line is arranged to supply pressure to the cylindrical chamber and the annular chamber is arranged to exhaust to the fluid return line.
  • the effective piston area is the full circular area of the piston exposed to the cylindrical chamber.
  • the fluid supply line is arranged to supply pressure to the cylindrical chamber, while the annular chamber is connected to the cylindrical chamber.
  • the supply pressure is therefore supplied simultaneously both to the cylindrical chamber and to the annular chamber, and the effective piston area is the difference in area between the full circular area of the piston exposed in the cylindrical chamber and the annular area of the piston exposed in the annular chamber, ie it is the cross-sectional area of the piston rod.
  • the actuator system When applied to the leading edge slats of an aircraft, the actuator system is normally required to extend the leading edge slats much more rapidly than the rate at which it is required to retract them, and rapid extension usually takes place at high angles of attack where the air loads tend to encourage extension. Since the air loads are assisting extension, the rapid rate of the second mode of operation may be employed in these conditions.
  • extension of the leading edge slats often takes place at low angles of incidence and rapid deployment is undesirable. In these circumstances, high air loads tend to oppose extension of the leading edge and then the first mode of operation is preferable since a higher thrust is possible.
  • actuator system possesses a number of advantages in terms of its versatility but, nonetheless, it incorporates a number of significant disadvantages in terms of the complexity of the control system required for determining and selecting the preferred mode of operation and for then controlling the actuator system to operate in the desired mode.
  • Actuator systems for use in other applications are also known from GB-A-2 313 413, EP- A-0 629 781 and US-4 434 708.
  • GB-A-2 313 413 and EP-A-0 629 781 both relate to hydraulic circuits for construction vehicles, such as hydraulic excavators, in which a regeneration device is provided for feeding fluid back from a return line extending from the actuator to a supply line extending to the actuator.
  • the actuator is controlled by a direction changeover valve, and a separate recovery control valve is provided for operating the regeneration device in dependence upon the delivery pressure in the supply line.
  • US-4 434 708 concerns a control valve for double acting piston and cylinder assemblies, for raising a load against the force of gravity and lowering the same, for example.
  • the aim of this patent is to prevent cavitation on the expanding side of the piston and cylinder assembly when the capacity of the hydraulic pump in the system is insufficient.
  • the control valve includes a regeneration check piston responsive on the one hand to the delivery pressure supplied by the hydraulic pump to the expanding side of the piston and cylinder assembly and on the other hand to fluid pressure in a chamber of the control valve connected between the retracting side of the piston and cylinder assembly and the return line.
  • Another aim of the present invention is to provide an actuator system which overcomes these disadvantages of the known arrangements. Another aim of the present invention is to provide an actuator system having two modes of operation during actuator extension and having a reliable and simple method of converting between these two modes of operation.
  • the invention at least in its preferred form, further seeks to provide an actuator system having two modes of operation during actuator extension and an automatic switch over arrangement for converting from one mode of operation to another.
  • an actuator system comprising:
  • an actuator having a piston moveable within a cylinder, and a piston rod extending from the piston and providing an actuator ram, the piston dividing the cylinder into a cylindrical chamber and an annular chamber,
  • a fluid direction control valve for controlling the supply of fluid to the cylindrical and annular chambers, respectively, for extension and retraction of the piston rod
  • the actuator being arranged to have first and second modes of operation during extension of the piston rod, the actuator in the first mode having the fluid supply line in communication with the cylindrical chamber and the annular chamber in communication with the fluid return line and in the second mode having the fluid supply line in communication with the cylindrical chamber and the annular chamber connected directly or indirectly to the cylindrical chamber, and means for automatically switching the actuator from one mode to the other mode in response to a change in pressure in the annular chamber.
  • an actuator system comprising:
  • an actuator having a piston moveable within a cylinder, and a piston rod extending from the piston and providing an actuator ram, the piston dividing the cylinder into a cylindrical chamber and an annular chamber,
  • a fluid direction control valve for controlling the supply of fluid to the cylindrical and annular chambers, respectively, for extension and retraction of the piston rod
  • the actuator being arranged to have first and second modes of operation during extension of the piston rod, the actuator in the first mode having the fluid supply line in communication with the cylindrical chamber and the annular chamber in communication with the fluid return line and in the second mode having the fluid supply line in communication with the cylindrical chamber and the annular chamber connected directly or indirectly to the cylindrical chamber,
  • a non return valve provided between the annular chamber and the cylindrical chamber and openable in response to a build up of pressure in the annular chamber to connect the same to the cylindrical chamber
  • the combination of the non return valve and the means for providing a restricted flow ensures that the actuator switches automatically from the first mode to the second mode of operation in response to a build up of pressure in the annular chamber.
  • a restrictor is provided in a fluid flow passage between the annular chamber and the return line to permit a restricted flow of fluid therebetween.
  • the actuator system will effectively revert automatically from the second mode of operation to the first mode of operation whenever the opposing load provided by the aircraft control surface increases during actuator extension to the point where the velocity of the actuator slows and the actuator approaches a stall situation, because at this point substantially all the fluid emerging from the annular chamber will leak via the restrictor to the return line and so the non return valve will close as the pressure in the annular chamber drops.
  • the effective area of the piston becomes the full circular area and the thrust of the actuator may be several times higher than in the second mode of operation.
  • the actuator characteristics may be matched to the required aerodynamic rate and load requirements.
  • FIGS 1 to 3 illustrate diagrammatically the operation of an actuator system for aircraft control surfaces according to the invention.
  • FIGS. 4 and 5 illustrate schematically a preferred embodiment of actuator system according to the invention.
  • FIGS 1 to 3 show in schematic form an actuator system 10 for controlling an actuator 12 having an actuator ram 14, which in use is connected by way of a linkage (not shown) to an aircraft control surface such as an aileron, an elevator, the rudder, or a wing leading edge slat or trailing edge flap, for extending and retracting the same.
  • an aircraft control surface such as an aileron, an elevator, the rudder, or a wing leading edge slat or trailing edge flap, for extending and retracting the same.
  • the actuator 12 comprises a piston and cylinder arrangement 16, having a piston 18 slideably received in a cylinder 20.
  • a piston rod 22 extends from one surface of the piston 18 and emerges from the cylinder 20 to serve as the actuator ram 14. Consequently, the piston 18 divides the cylinder 20 into a cylindrical chamber 24 which is expandable to extend the actuator ram 14 and an annular chamber 26 which is expandable to retract the actuator ram 14.
  • the actuator system 10 further comprises a fluid supply line 30 for supplying fluid to the actuator 12 at high pressure, and a fluid return line 32 for receiving fluid back from the actuator 12 at low pressure.
  • the fluid supply and return lines 30, 32 may, for example, be connected to a fluid supply (not shown), eg a hydraulic supply, which may typically consist of a pump and a fluid reservoir.
  • the fluid supply line 30 and the fluid return line 32 are both in communication with the actuator 12 by way of a fluid direction control valve 34, which is responsive to the aircraft control system for controlling the supply of fluid to and the exhaustion of fluid from the cylindrical chamber 24 and the annular chamber 26 of the actuator 12 for effecting extension and retraction of the actuator ram 14.
  • the actuator system 10 is shown with the fluid supply line 30 in communication with the cylindrical chamber 24 and with the annular chamber 26 in communication with the fluid return line 32 for extending the actuator ram 14.
  • Retraction of the actuator ram 14 involves switching over the fluid direction control valve 34 to place the fluid supply line 30 in communication with the annular chamber 26 and the cylindrical chamber 24 in communication with the fluid return line 32.
  • the actuator system 10 of Figures 1 to 3 also includes firstly a return line isolation valve 36 located in the return line 32, and secondly a non-return valve 38 situated between the fluid supply line 30 and the fluid return line 32.
  • the non-return valve 38 is normally resiliently biased into a closed position, but is openable in response to an increase of pressure in the remrn line 32 upstream of the return line isolation valve 36 to communicate this portion 40 of the return line 32 with the fluid supply line 30.
  • the return line isolation valve 36 In the normal mode of extension shown in Figure 1 , the return line isolation valve 36 is open and the non-return valve 38 remains in its closed position. However, when the return line isolation valve 36 is closed during the extension mode of the actuator ram 14, as shown in Figure 2, a situation arises where a build-up of pressure occurs in the annular chamber 26 and hence in the line portion 40. In response to this build-up of pressure, the non-return valve 38 opens automatically to place the annular chamber 26 in communication with the cylindrical chamber 24.
  • the actuator system can be adapted both to the prevailing flight conditions and to the loads exerted on the aircraft control surface being operated by the actuator system.
  • FIG. 3 A further situation is represented in Figure 3, which enables the actuator system 10 to switch between the normal and alternative modes of extension of the actuator ram 14 automatically, as opposed to switching between these modes through opening and closing of the remrn line isolation valve 36 in response to signals from the aircraft control system.
  • the actuator 12 has automatically switched from the alternative mode of extension in which the effective area of the piston 18 is the difference in areas between that of the circular face 42 presented to the cylindrical chamber 20 and the annular face 44 presented to the annular chamber 26, ie the area of the piston rod 22, to the normal mode of extension in which the effective piston area is the full circular area of the face 42 presented to the cylindrical chamber 20. Consequently, the available thrust of the actuator ram 14 is automatically increased to its full capacity.
  • the remrn line isolation valve 36 may in practice be implemented by a permanent restrictor or by a flow control device such as a constant flow device operable in the automatic switching situation to provide a restricted flow, subject to appropriate connections of the fluid supply line 30 and fluid return line 32 through the fluid direction control valve 34 to permit the actoator 12 to operate solely in the normal mode of extension and of retraction when required. If a constant flow device is employed, its effective orifice size may be variable in order to maintain a constant leakage flow to the fluid return line 32.
  • This actoator system 100 features some of the same elements as the actoator system 10 described with reference to Figures 1 to 3 and the same parts are designated by the same reference numerals. Only the differences will be described in detail.
  • the actoator system 100 features an actoator 12 connected by way of a fluid direction control valve 34 to a fluid supply line 30 and fluid return line 32 as before.
  • Figure 4 shows the actoator 12 connected for the automatic switching mode of extension indicated above
  • Figure 5 shows the actuator 12 connected for retraction of the actuator ram 14.
  • the fluid direction control valve 34 connects the fluid supply line 30 to the annular chamber 26 of the actuator 12 by way of a non-return valve 102.
  • the cylindrical chamber 24 of the actoator 12 is connected directly to the fluid return line 32 through the fluid direction control valve 34. Consequently, fluid is supplied under pressure to the annular chamber 26 and is exhausted from the cylindrical chamber 24 to the fluid return line 32 so that the actuator ram 14 is retracted.
  • the fluid direction control valve 34 connects the fluid supply line 30 directly with the cylindrical chamber 24 while the annular chamber 26 is connected firstly with the fluid supply line 30 by way of a non-return valve 104, which is normally biased into a closed position, and secondly to the fluid return line 32 by way of a restrictor 106, for example a viscosity compensating restrictor, and the fluid direction control valve 34.
  • a non-return valve 104 which is normally biased into a closed position
  • a restrictor 106 for example a viscosity compensating restrictor
  • the retraction rate of the actoator ram 14 is not limited by the restrictor since a second non-return valve 104 is provided as a bypass.
  • the combination of two non-return valves and a fixed restrictor may be replaced by one non-return valve and a one-way restrictor, ie a device which allows a free flow of fluid in one direction while restricting the flow of fluid in the other direction.
  • restricting means include a constant flow device or a valve of alternative construction.
  • the invention as described has the advantage that commercially available components may be built into standard or existing hydraulic fittings and pipework without the need for overall system re-design.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid-Pressure Circuits (AREA)

Abstract

L'invention se rapporte à un actionneur (12) comportant un piston (18) susceptible de se déplacer à l'intérieur d'un cylindre (20) et une tige de piston (22) en saillie à partir du piston et constituant un poussoir d'actionnement (14). Ce piston divise le cylindre en une chambre cylindrique (24) et une chambre annulaire (26). Un robinet de commande de la direction d'écoulement (34) commande l'alimentation en fluide entre d'une part, les chambres précitées et d'autre part, une conduite d'alimentation en fluide (30) et une conduite de retour de fluide (32). Ledit actionneur est conçu de façon à posséder un premier et un second mode de fonctionnement au cours de l'extension de la tige du piston. Dans ledit premier mode, l'actionneur est tel que la conduite d'alimentation en fluide est en communication avec la chambre cylindrique et la chambre annulaire est en communication avec la conduite de retour de fluide. Dans le second mode, la conduite d'alimentation en fluide est en communication avec la chambre cylindrique et la chambre annulaire est reliée directement ou indirectement à la chambre cylindrique. Ledit système d'actionnement comporte également un organe (36, 38; 102, 104, 106) permettant de basculer automatiquement l'actionneur d'un mode dans l'autre mode.
PCT/GB1999/001926 1998-06-24 1999-06-17 Systeme d'actionnement pour fonctions et unites de commande aerospatiales WO1999067537A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP99926635A EP1090232A1 (fr) 1998-06-24 1999-06-17 Systeme d'actionnement pour fonctions et unites de commande aerospatiales
JP55892099A JP2002511135A (ja) 1998-06-24 1999-06-17 航空宇宙制御及び機能用アクチュエータシステム
AU43814/99A AU4381499A (en) 1998-06-24 1999-06-17 Actuator system for aerospace controls and functions

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB9813660.9A GB9813660D0 (en) 1998-06-24 1998-06-24 Actuator system for aerospace controls and functions
GB9813660.9 1998-06-24

Publications (1)

Publication Number Publication Date
WO1999067537A1 true WO1999067537A1 (fr) 1999-12-29

Family

ID=10834323

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1999/001926 WO1999067537A1 (fr) 1998-06-24 1999-06-17 Systeme d'actionnement pour fonctions et unites de commande aerospatiales

Country Status (5)

Country Link
EP (1) EP1090232A1 (fr)
JP (1) JP2002511135A (fr)
AU (1) AU4381499A (fr)
GB (1) GB9813660D0 (fr)
WO (1) WO1999067537A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007107428A3 (fr) * 2006-03-17 2007-11-08 Hydraulik Ring Gmbh Circuit hydraulique, destiné en particulier à des dispositifs de réglage d'arbre à cames, et élément de commande correspondant
US7836857B2 (en) 2006-03-17 2010-11-23 Hydraulik-Ring Gmbh Hydraulic circuit, particularly for camshaft adjusters, and corresponding control element
CN111550469A (zh) * 2019-02-11 2020-08-18 古德里奇驱动系统有限公司 致动器控制阀布置
CN111550469B (zh) * 2019-02-11 2024-06-11 古德里奇驱动系统有限公司 致动器控制阀布置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10227951B2 (en) 2017-02-02 2019-03-12 Woodward, Inc. Limited flow thrust reverser actuating

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2367682A (en) * 1943-04-09 1945-01-23 Adel Prec Products Corp Landing gear by-pass valve
DE1601740A1 (de) * 1967-02-15 1971-01-14 Langen & Co Schaltung fuer doppeltwirkenden hydraulischen Spannzylinder
US4434708A (en) 1982-03-05 1984-03-06 General Signal Corporation Control valve for double-acting piston and valve assemblies
EP0629781A1 (fr) 1992-12-04 1994-12-21 Hitachi Construction Machinery Co., Ltd. Regenerateur hydraulique
GB2313413A (en) 1996-05-21 1997-11-26 Samsung Heavy Ind Variable-regeneration directional control valve for constructional vehicles
EP0831181A1 (fr) * 1996-09-20 1998-03-25 Shin Caterpillar Mitsubishi Ltd. Circuit hydraulique

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2367682A (en) * 1943-04-09 1945-01-23 Adel Prec Products Corp Landing gear by-pass valve
DE1601740A1 (de) * 1967-02-15 1971-01-14 Langen & Co Schaltung fuer doppeltwirkenden hydraulischen Spannzylinder
US4434708A (en) 1982-03-05 1984-03-06 General Signal Corporation Control valve for double-acting piston and valve assemblies
EP0629781A1 (fr) 1992-12-04 1994-12-21 Hitachi Construction Machinery Co., Ltd. Regenerateur hydraulique
GB2313413A (en) 1996-05-21 1997-11-26 Samsung Heavy Ind Variable-regeneration directional control valve for constructional vehicles
EP0831181A1 (fr) * 1996-09-20 1998-03-25 Shin Caterpillar Mitsubishi Ltd. Circuit hydraulique

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007107428A3 (fr) * 2006-03-17 2007-11-08 Hydraulik Ring Gmbh Circuit hydraulique, destiné en particulier à des dispositifs de réglage d'arbre à cames, et élément de commande correspondant
US7836857B2 (en) 2006-03-17 2010-11-23 Hydraulik-Ring Gmbh Hydraulic circuit, particularly for camshaft adjusters, and corresponding control element
US7946266B2 (en) 2006-03-17 2011-05-24 Hydraulik-Ring Gmbh Hydraulic circuit, particularly for camshaft adjusters, and corresponding control element
CN111550469A (zh) * 2019-02-11 2020-08-18 古德里奇驱动系统有限公司 致动器控制阀布置
CN111550469B (zh) * 2019-02-11 2024-06-11 古德里奇驱动系统有限公司 致动器控制阀布置

Also Published As

Publication number Publication date
GB9813660D0 (en) 1998-08-26
EP1090232A1 (fr) 2001-04-11
JP2002511135A (ja) 2002-04-09
AU4381499A (en) 2000-01-10

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