EP0767310A2 - Dispositif de manoeuvre hydraulique - Google Patents

Dispositif de manoeuvre hydraulique Download PDF

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Publication number
EP0767310A2
EP0767310A2 EP96115789A EP96115789A EP0767310A2 EP 0767310 A2 EP0767310 A2 EP 0767310A2 EP 96115789 A EP96115789 A EP 96115789A EP 96115789 A EP96115789 A EP 96115789A EP 0767310 A2 EP0767310 A2 EP 0767310A2
Authority
EP
European Patent Office
Prior art keywords
control
valve
piston
hydraulic
hydraulic actuator
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.)
Granted
Application number
EP96115789A
Other languages
German (de)
English (en)
Other versions
EP0767310B1 (fr
EP0767310A3 (fr
Inventor
Robert Sollinger
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 Helicopters Deutschland GmbH
Original Assignee
Eurocopter Deutschland GmbH
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 Eurocopter Deutschland GmbH filed Critical Eurocopter Deutschland GmbH
Publication of EP0767310A2 publication Critical patent/EP0767310A2/fr
Publication of EP0767310A3 publication Critical patent/EP0767310A3/fr
Application granted granted Critical
Publication of EP0767310B1 publication Critical patent/EP0767310B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F15B9/02—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 with servomotors of the reciprocatable or oscillatable type
    • F15B9/08—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 with servomotors of the reciprocatable or oscillatable type controlled by valves affecting the fluid feed or the fluid outlet of the servomotor
    • F15B9/10—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 with servomotors of the reciprocatable or oscillatable type controlled by valves affecting the fluid feed or the fluid outlet of the servomotor in which the controlling element and the servomotor each controls a separate member, these members influencing different fluid passages or the same passage

Definitions

  • the invention relates to a hydraulic actuator, in particular for the blade angle control of a helicopter, according to the preamble of claim 1.
  • valves of this type such as those used in connection with helicopters as main drives for rotor blade angle adjustment, but also as power amplifiers in control signal transmission paths
  • the valve is controlled via a mixing gear connected upstream of the valve spool, on the one hand the control commands and on the other hand in opposite directions Actuate the output movements of the actuator via a mechanical connection to the actuating piston.
  • Such actuators have a relatively large installation volume and weight, which is common with helicopters cramped space and strict weight requirements are disadvantageous, especially since a large number of such actuators are usually required there. Added to this is the fact that the mixing gear has to be constructed in a complex, precision constructional manner for reasons of exact control behavior.
  • hydraulic actuators are known in which the actuator piston is fixed, but the housing of the actuator, on the other hand, is arranged displaceably together with the servo valve housing.
  • a mixing gearbox for the valve feedback control is unnecessary, but instead, due to the displaceable arrangement of the common actuator / valve housing, increased storage costs and an increased installation volume and weight of the actuator have to be accepted.
  • the object of the invention is to design the hydraulic actuator of the type mentioned in such a way that a substantial design simplification is achieved and a problem-free installation is possible even in confined spaces.
  • the installation space required otherwise for the servo valve is saved by the claimed inclusion of the servo valve in the piston rod of the actuator actuating piston which is required anyway and at the same time an immediate, mixed-gear-free signal feedback from the actuator to the servo valve is achieved.
  • the actuator according to the invention is therefore particularly suitable for applications which - such as in helicopter blade angle controls - are subject to strict requirements in terms of space requirement and structural weight.
  • control of the working chamber for the hydraulic pressure source and for the return is effected according to claim 2 via two mechanically separate valves, namely, on the one hand, the servo valve and, on the other hand, a control valve which switches over depending on the working chamber pressure.
  • the servo valve included in the piston section is designed as a rotary slide valve with a control edge which is inclined with respect to the actuating piston displacement axis.
  • gearbox-free valve feedback controls in which the transmission ratio of the actuator between the input movement of the valve spool and the output movement of the hydraulic actuator is always fixed at one - by any suitable choice of the angle of inclination of the control edge, any desired transmission characteristic of the actuator achieve.
  • the one control surface of the servo valve is preferably provided with two control edges in the form of a control slot which is closed by the counter surface in the locked position of the servo valve and extends obliquely to the valve longitudinal direction.
  • a particularly preferred embodiment of the invention in this connection consists in that the control edge or the control slot runs at a non-uniform incline with respect to the piston axis.
  • the transmission ratio is less than one, while towards the stroke ends the angle of inclination of the control edge or the control slot with respect to the piston axis decreases and the transmission ratio increases accordingly.
  • Such a progressive translation characteristic is aimed in particular in connection with pilot-controlled blade angle adjustment devices of helicopters.
  • a three-position valve connected on the output side to both working chambers is preferably integrated into the piston rod of the actuator as a servo valve.
  • a bypass valve which can be selectively switched from a closed to an open position to switch the actuator open, is preferably provided between the working chambers of the actuator.
  • the bypass valve preferably contains an additional valve stage, which supplies the pressure to both working chambers locks when they are hydraulically connected to each other via the bypass valve, i.e. the actuator is activated. In this way it is prevented that control commands, which are still entered on the valve spool, can cause a hydraulic short circuit between the pressure medium source and the return via the interconnected working chambers.
  • the hydraulic actuator shown in FIG. 1 contains, as main components, a hydraulic actuator 2 and a servo valve 4.
  • the hydraulic actuator 2 is a double-acting linear drive, consisting of a fixed hydraulic cylinder 6 and an actuating piston 12 dividing it into the working chambers 8 and 10, with an actuating piston 12 on both sides of the control piston 12 extending piston rod 16 provided at one end with the output 14 of the actuator.
  • the piston rod 16 is designed so that it forms a part of the servo valve 4 and for this purpose contains a central, in the axial direction of the control piston 12 receiving bore 18 in which the control command operated valve spool 20 of the servo valve 4 is sealingly and slidably guided.
  • the valve slide 20 In the valve slide 20 there is a hydraulic channel 22 which is connected to a flexible hydraulic line 24 leading to the return R and is opened to a circumferential groove 26 on the control surface 30 of the valve slide 20 which cooperates with the inner surface 28 of the piston rod 16.
  • the valve chamber on the working chamber side consists of two control openings 32 and 34 on the inner surface 28 which laterally adjoin the circumferential groove 26 and which penetrate the piston rod section 16 and each open into the working chamber 8 or 10 directly next to the actuating piston 12.
  • the actuator On the pressure source P side, the actuator contains a solenoid-operated, two-stage bypass valve 36, which in the valve position shown releases the pressure supply line 38 and separates the connecting lines 40 and 42 to the working chambers 8 and 10, as well as one between the pressure supply line 38 and the connecting lines 40 and 42-acting control valve 44, which switches over to the servo valve 4 as a function of the pressure difference between the working chambers 8, 10 and, with a pressure equilibrium of the working chambers 8, 10, the middle position occupies in which it prevents the hydraulic flow to the working chambers 8, 10.
  • valve slide 20 If the valve slide 20 is in the neutral position shown with respect to the piston rod 16, then both control openings 32, 34 and consequently also the working chambers 8, 10 are blocked for the return R.
  • the pressure level in the working chambers 8, 10 is the same, and the working piston 12 remains in its position.
  • an input command for example in the sense of FIG. 1
  • the control opening 32 is opened by the circumferential groove 26 and thus the working chamber 8 via the hydraulic channel 22 and Return line 24 is depressurized, while the control opening 34 and thus also the working chamber 10 continue to be separated from the return R by the valve slide 20.
  • the control valve 44 switches to the right switching position, in which it completely separates the working pressure line 38 from the connecting line 40 and releases the pressure medium supply via the connecting line 42 to the working chamber 10.
  • the actuating piston 12 thus moves to the right with the piston rod 16 and the actuator output 14.
  • the servo valve 4 is controlled back at the same time until the control opening 32 migrates over the side edge of the circumferential groove 26 in the opposite direction and the two working chambers 8 and 10 are separated from the return R.
  • the actuator remains in this position until the valve spool 20 is again relative to the control command Piston rod 16 is adjusted, for example in the sense of FIG. 1 to the left, whereupon the process described above is repeated in the opposite direction.
  • control command inputs are passed on at the output 14 of the actuator, for example as part of a helicopter blade angle control, not shown, with a transmission ratio of one, ie a control command input is converted by the actuator into an equally large, force-amplified output movement.
  • the bypass valve 36 is used to activate the actuator if it is used, for example, together with further, similar actuators in a redundant arrangement or as a power amplifier in the course of a mechanical signal transmission path acting parallel to a normally activated fly-by-wire control and only in an auxiliary manner must be activated in the event of a malfunction of the fly-by-wire control.
  • the pressure supply line 38 is separated from the control valve 44 and the working chambers 8, 10 are hydraulically short-circuited.
  • the output 14 of the actuator is decoupled from the control command input 46 and the piston rod 16 is freely adjustable, regardless of whether and in what size control commands are given to the valve slide 20.
  • the actuator according to FIGS. 2 and 3, where the components corresponding to the first exemplary embodiment are indicated by a reference symbol increased by 100 are distinguished from this mainly in that it can be carried out with a largely arbitrary, if desired also non-linear translation characteristic.
  • the valve slide 120 is rotatably arranged in the receiving bore 118 of the piston rod 116 and additionally on a bearing support 48, while the actuating piston 112 together with the piston rod 116 is linearly displaceable but non-rotatably on the hydraulic cylinder 106 via a linkage 50.
  • the input member 146 consists of a rocker arm, via which the valve slide 120 is rotatably positioned with respect to the piston rod 116 in accordance with the control command inputs.
  • a control slot 52 with oblique valve control edges 54 and 56 runs obliquely in the axial direction of the valve slide 120.
  • the control rod 128 on the piston rod side contains two hydraulic chambers 58, 60 of small axial width, which extend into the control piston 112 in a kidney shape, which are each connected via a hydraulic opening 132 or 134 in the control piston 112 to the working chamber 108 or 110 and from one another by a central web 62 on the control surface 128 are separated, which in the neutral position of the servo valve 104 shown in FIG. 3 covers the control slot 52 and thereby separates both working chambers 108 and 110 from the return R.
  • valve slide 120 is rotated as a result of a control command input, one or the other control edge 54 or 56 is opened, depending on the direction of rotation, and the corresponding working chamber 108 or 110 with the Return R connected, while the other working chamber remains blocked for the return R and is now supplied with an unimpeded pressure medium inflow via the control valve 144, which now switches over in the same manner as in the first exemplary embodiment.
  • the gear ratio is dependent on the inclination of the control slot 52 with respect to the servo valve axis. If the control slot 52 is inclined flat, a relatively small angular adjustment of the input lever 146 results in a comparatively large output movement of the actuator 102, and vice versa. In this way, the actuator can be designed with any desired translation characteristic, including a non-linear one, such that the control slot 52 is not formed with a constant angle of inclination, but is bent with an angle of inclination that changes in the longitudinal direction of the slot.
  • the actuator for example in connection with a rotor blade angle control in the middle position of the actuating piston 112 is to react very sensitively to the control command inputs, but the transmission ratio to the stroke ends is to increase steeply, the control slot 52 must be opposite the longitudinal axis of the valve relatively inclined in the middle of the slot, but increasingly flatter towards the slot ends.
  • a check valve 64 or 66 which opens to the connecting line 140 or 142, is also provided on both sides of the control valve 144. This ensures that the actuating piston 112 is locked hydraulically when an external load which exceeds the maximum actuating or holding force of the actuator 102 acts on the output 114. Otherwise, the construction and operation of the actuator according to FIGS. 2 and 3 is the same as in the first embodiment.

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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)
  • Actuator (AREA)
EP96115789A 1995-10-07 1996-10-02 Dispositif de manoeuvre hydraulique Expired - Lifetime EP0767310B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19537417 1995-10-07
DE19537417A DE19537417C2 (de) 1995-10-07 1995-10-07 Hydraulischer Stellantrieb

Publications (3)

Publication Number Publication Date
EP0767310A2 true EP0767310A2 (fr) 1997-04-09
EP0767310A3 EP0767310A3 (fr) 1999-09-01
EP0767310B1 EP0767310B1 (fr) 2005-04-20

Family

ID=7774293

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96115789A Expired - Lifetime EP0767310B1 (fr) 1995-10-07 1996-10-02 Dispositif de manoeuvre hydraulique

Country Status (2)

Country Link
EP (1) EP0767310B1 (fr)
DE (2) DE19537417C2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0894982A2 (fr) * 1997-07-29 1999-02-03 Ebara Corporation Dispositif asservi hydraulique
CN114215804A (zh) * 2022-02-22 2022-03-22 中国空气动力研究与发展中心高速空气动力研究所 一种用于驱动弯刀支撑机构的电液伺服系统

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19820102B4 (de) * 1998-05-06 2004-02-05 Kracht Gmbh Oszillier-Zylinder
DE19841855B4 (de) * 1998-09-14 2006-10-26 Zf Luftfahrttechnik Gmbh Einzelblatt-Steuerungsvorrichtung für einen Hubschrauberhauptrotor
DE29818762U1 (de) 1998-10-21 1998-12-24 Festo AG & Co, 73734 Esslingen Fluidbetätigte Arbeitsvorrichtung

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB654415A (en) * 1947-02-28 1951-06-20 Rene Leduc Improvements in control systems especially for aircraft
GB841995A (en) * 1955-10-31 1960-07-20 Boulton Aircraft Ltd Improvements in or relating to fluid-pressure servo mechanisms
US3135164A (en) * 1959-11-16 1964-06-02 Bosch Arma Corp Servo mechanism
US3646849A (en) * 1970-02-10 1972-03-07 Lucas Industries Ltd Servomechanism
DE2207579A1 (de) * 1972-02-18 1973-08-30 Claas Maschf Gmbh Geb Anordnung zum steuern von regelbaren hydraulikpumpen
US3757640A (en) * 1971-12-01 1973-09-11 Avco Corp Simplified follower servomechanism
DE2211994A1 (de) * 1972-03-09 1973-09-13 Ronald Arthur Foley Hydraulische schaltvorrichtung
DE2300161A1 (de) * 1973-01-03 1974-07-11 Tadashi Saito Fluid-impulszylinder fuer numerische steuerung
GB2072886A (en) * 1980-02-22 1981-10-07 Asea Ab Servo assembly
EP0088017A2 (fr) * 1982-02-26 1983-09-07 COMPAGNIE PARISIENNE D'OUTILLAGE A AIR COMPRIME Société anonyme dite: Dispositif de distribution hydraulique à tiroir
WO1993019300A1 (fr) * 1992-03-23 1993-09-30 C.W.F. Hamilton & Co. Limited Commande a retroaction pour verin hydraulique

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2832898C2 (de) * 1978-07-27 1985-12-19 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Irreversibler, hydraulischer Stellantrieb

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB654415A (en) * 1947-02-28 1951-06-20 Rene Leduc Improvements in control systems especially for aircraft
GB841995A (en) * 1955-10-31 1960-07-20 Boulton Aircraft Ltd Improvements in or relating to fluid-pressure servo mechanisms
US3135164A (en) * 1959-11-16 1964-06-02 Bosch Arma Corp Servo mechanism
US3646849A (en) * 1970-02-10 1972-03-07 Lucas Industries Ltd Servomechanism
US3757640A (en) * 1971-12-01 1973-09-11 Avco Corp Simplified follower servomechanism
DE2207579A1 (de) * 1972-02-18 1973-08-30 Claas Maschf Gmbh Geb Anordnung zum steuern von regelbaren hydraulikpumpen
DE2211994A1 (de) * 1972-03-09 1973-09-13 Ronald Arthur Foley Hydraulische schaltvorrichtung
DE2300161A1 (de) * 1973-01-03 1974-07-11 Tadashi Saito Fluid-impulszylinder fuer numerische steuerung
GB2072886A (en) * 1980-02-22 1981-10-07 Asea Ab Servo assembly
EP0088017A2 (fr) * 1982-02-26 1983-09-07 COMPAGNIE PARISIENNE D'OUTILLAGE A AIR COMPRIME Société anonyme dite: Dispositif de distribution hydraulique à tiroir
WO1993019300A1 (fr) * 1992-03-23 1993-09-30 C.W.F. Hamilton & Co. Limited Commande a retroaction pour verin hydraulique

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0894982A2 (fr) * 1997-07-29 1999-02-03 Ebara Corporation Dispositif asservi hydraulique
EP0894982A3 (fr) * 1997-07-29 2000-05-24 Ebara Corporation Dispositif asservi hydraulique
CN114215804A (zh) * 2022-02-22 2022-03-22 中国空气动力研究与发展中心高速空气动力研究所 一种用于驱动弯刀支撑机构的电液伺服系统

Also Published As

Publication number Publication date
DE19537417C2 (de) 1997-07-24
DE19537417A1 (de) 1997-04-10
EP0767310B1 (fr) 2005-04-20
EP0767310A3 (fr) 1999-09-01
DE59611218D1 (de) 2005-05-25

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