EP0248986A1 - Actionneur hydraulique à clapet oscillant - Google Patents

Actionneur hydraulique à clapet oscillant Download PDF

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Publication number
EP0248986A1
EP0248986A1 EP87104197A EP87104197A EP0248986A1 EP 0248986 A1 EP0248986 A1 EP 0248986A1 EP 87104197 A EP87104197 A EP 87104197A EP 87104197 A EP87104197 A EP 87104197A EP 0248986 A1 EP0248986 A1 EP 0248986A1
Authority
EP
European Patent Office
Prior art keywords
shaft
housing
vanes
vane
rotary vane
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
EP87104197A
Other languages
German (de)
English (en)
Other versions
EP0248986B1 (fr
Inventor
Ralph L. Vick
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 International Inc
Original Assignee
Allied Corp
AlliedSignal 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 Allied Corp, AlliedSignal Inc filed Critical Allied Corp
Publication of EP0248986A1 publication Critical patent/EP0248986A1/fr
Application granted granted Critical
Publication of EP0248986B1 publication Critical patent/EP0248986B1/fr
Expired 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
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/08—Characterised by the construction of the motor unit
    • F15B15/12—Characterised by the construction of the motor unit of the oscillating-vane or curved-cylinder type

Definitions

  • This invention relates to rotary vane hydraulic actuators and more particularly to such an actuator designed to operate within the confines of thin wings or control surfaces of modern aircraft.
  • a rotary vane actuator normally includes a housing connected to a source of fluid under pressure, a chamber within the housing, a shaft passing through the housing and vane members attached to the shaft and moveable in the housing in one direction or the other in response to directed hydraulic fluid under pressure to cause rotation of said shaft, usually over a limited travel such as ⁇ forty degrees.
  • a control surface may be attached to the shaft and movable therewith. Suitable seals must be employed to prevent excessive leakage and loss of power.
  • Such rotary vane hydraulic actuators are not new but have come into greater use recently because of advantages as compared with linear actuators for operating control surfaces of aircraft where the space available for the actuator is very limited. Because of the shape of an airfoil such as a wing, for example, it may be advantageous to incorporate a rotary vane actuator which can operate along the hinge line of a movable surface such as an aileron rather than a linear cylinder which may require increasing the thickness of the wing or adding protrusions to the wing to contain the actuator. Recent trends toward unusually thin wing construction for supersonic aircraft has made interest in the rotary actuator even greater because such protrusions or extra thickness adversely affect the performance of the aircraft.
  • the rotary vane hydraulic actuator of the present invention has a generally cylindrical housing having endcaps with flattened walls top and bottom to minimize its height and including a pair of elongated ribs internally of the flattened walls which have arcuate surfaces acting in cooperation with the operating shaft to effectively divide the internal chamber of the housing into what might be termed left and right chambers.
  • the shaft carries oppositely directed vanes, one in each of the left and right chambers, which vanes are quite thick and have an arcuate surface of substantial length adjacent the internal walls of the left and right chambers.
  • a pair of elongated dynamic seals are carried in grooves in the internal walls of the chamber and also in the endcaps such that they seal radially against the arcuate surfaces of the vanes and also axially against the end surfaces of the vanes.
  • Other dynamic seals are carried in the arcuate surfaces of the internal ribs such that they seal against the shaft.
  • Additional static seals are positioned between the housing and endcaps. Dynamic seals are also incorporated into the endcaps to seal against the rotatable shaft.
  • the dynamic seals are carried in the housing and seal against the surfaces of the vanes and the shaft which have minimal distortion as a function of pressure differentials.
  • the seals themselves are of flexible materials such as polytetrafluoroethylene (Teflon), filled Teflon, or polymides such as Vespel or Torlon which will maintain contact by their inherent characteristics or they may be augmented by means of additional spring-type expander members in the seal grooves to provide mechanical spring loading to assure contact with the vanes and shaft.
  • the seals against the vanes are preferably single piece seals which have 90 degree corner projections to assure radial contact on the vane outer diameter and axial contact on the vane end faces. Sufficient end length interference must be provided to accommodate the differential expansion of the seal material and vane material over the required temperature range.
  • Advantages of the present invention are that it provides a vane type linear actuator which has a low height such that it can be placed along a hinge line of control surfaces of thin wing aircraft, it affords a sealing arrangement allowing for minimum leakage at high operating pressures despite physical distortion of the housing with pressure variations and yet the actuator is not excessively costly to manufacture.
  • a generally cylindrical housing or barrel l0 is shown having endcaps l2 and l4 attached thereto by means of screws l6.
  • a shaft l8 is supported in the endcaps l2, l4 which carry dynamic seals 22, 24 and 22 ⁇ , 24 ⁇ , respectively, consisting of combination O-rings and low friction rings in contact with shaft 20.
  • a pair of static seals 26 and 28 are positoned between endcaps l2 and l4, respectively, and the cylinder barrel l0.
  • Shaft 20 actually includes two concentric cylindrical parts including an inner splined output drive member 20 held in axial alignment with member l8 by means of wire retainers 30, 32.
  • shaft 20 may be made of a single piece with a spline output.
  • shaft seals 34 and 36 Carried in slots in barrel l0 and extending into the endcaps l2 and l4 are a pair of elongated shaft seals 34 and 36. These seals are preferably of a flexible plastic material having low friction such as polytetraflouroethelyne (Teflon or filled Teflon) or polymides (such as Vespel or Torlon).
  • Shaft seals 34 and 36 should preferably have an interference fit with or insert in grooves formed in additional ring seals l05 surrounding shaft 20 at each endcap.
  • FIG. 2 is a cross sectional view taken along line 2-2 of Figure l.
  • barrel l0 is formed with parallel flattened surfaces top and bottom and that a pair of inwardly extending ribs 42, 44 are formed on the inside of the barrel directly opposite the flattened sides.
  • Seals 34 and 36 are carried in longitudinal grooves in ribs 42, 44 which have arcuate surfaces 46, 48 respectively adjacent the surface of shaft l8 such that the seals 34, 36 seal against the shaft.
  • Carried on shaft l8 and extending radially into the interior of barrel l0 are a pair of vanes 50, 52 which have considerable thickness and which terminate in arcuate surfaces 54, 56, respectively.
  • Each of vanes 50, 52 serves to separate the half of the internal part of barrel l0 in which it is located into two chambers, vane 50 separating chambers 58 and 60 and vane 52 separating chambers 62 and 64.
  • elongated dynamic seals 66 and 68 which seal against the arcuate surfaces 54 and 56, respectively. These seals are, or may be, essentially the same as shaft seals 34 and 36, and may also include metal spring members to assure contact against the surfaces 54 and 56 irrespective of internal pressures which may tend to distort barrel l0. Also visible in this view are the seal 26, described above and the several threaded holes for receiving screws l6.
  • FIG. 3 is a sectional view taken along line 3-3 of Figure l and gives some detail of the endcap l2 and its internal passages.
  • a boss 70 having an internal port 72 which is suitably connected to a conduit, not shown, from a source of operating fluid under pressure.
  • Boss 70 communicates with an axially directed passage 74 which is connected to chamber 60 and also with channels 76 and 78 which communicate with a second axially directed passage 80 which communicates with chamber 62.
  • the channels 76 and 78 are preferably located between shaft seals 22 and 24 or 22 ⁇ and 24 ⁇ . Passages 74 and 80 must be located away from shaft 20 so that they do no intersect with the seal grooves.
  • FIG 4 is a schematic drawing showing an alternative porting arrangement for my rotary vane hydraulic actuator.
  • a pair of fluid passages 82 and 84 which communicate with a high pressure source are connected to chamber 58 and 60 respectively.
  • a pair of non-intersecting diagonal ports 86 and 88 are drilled through a solid portion of shaft 20 such that high pressure in chamber 58 will be communicated through passage 86 to chamber 64 and at the same time passage 84 will communicate with the low pressure side of the fluid pressure source. This low pressure will also be communicated through port 88 with chamber 62 which would cause the vanes to move counterclockwise.
  • Figure 5 is a partial sectional view showing details of the vane seals and showing the manner in which the seal seals against the vane both along its axial length and against its ends.
  • the shaft l8 carries vane 50 which makes contact against seal 66.
  • Seal 66 is carried in barrel l0 through its length and extends into slots 70 and 72 in endcaps l2 and l4, respectively, making 90 degree corner projections at the ends.
  • the seal member 66 may be backed by metal springs or expander members to assure sealing contact against the vane despite some distortion of the barrel l0.
  • Sufficient end length interference is provided to account for the differential expansion of the seal material and vane material over the required temperature range.
  • This end section will also engage in an interference fit slot on seal rings l05 in the end caps l2 and l4 to provide axial sealing of the shaft, i.e. prevent leaking from one chamber to the adjacent chamber at the shaft ends.
  • Figure 6 is a partial sectional view similar to Figure 5, but displaced approximately ninety degrees to show details of the shaft seal 34 and associated structure.
  • seal 34 and back up springs or expander members 38 are carried in a slot in the longitudinal rib 34 which is part of barrel l0.
  • Seal 34 extends into notches in ring seals l05 in endcaps l2 and l4 or otherwise makes an interference fit against the seals l05 to provide axial sealing as described above.
  • the above described actuator would typically be attached to the main shaft of a control surface forming part of a wing, for example, and would turn the output shaft over a range of up to about forty degrees.
  • the height of the actuator can be reduced substantially to fit within a thin wing or control surface.
  • the longitudinal ribs 42 and 44 provide strength and stiffness to the barrel l0 while also providing means for sealing between operating chambers containing hydraulic fluid.
  • the thick vanes 50 and 52 include arcuate surfaces of such length that the seals 66 and 68 maintain contact against the vanes at all travel positions of the vane.
  • FIG. 7 is a sectional view of another embodiment of my invention utilizing a single vane.
  • This embodiment can be made in a form having even less height for installation in thin section wings or control surfaces.
  • a housing 90 includes an internal cavity 92 which contains a rotatable shaft 94 effectively separated into chambers 96 and 98 by a single vane l00 carried on the shaft.
  • Carried in housing 90 are a single shaft seal l02 and a single vane seal l04 which are of the same type and which seal in the same manner as do shaft seals 34, 36 and vane seals 66, 68.
  • Vane l00 has a long arcuate surface as do vanes 50, 52 so that the sealing engagement is maintained over the entire travel of vane l00.
  • a pair of ports l06 and l08 are connected to a control valve directing fluid under high pressure to chamber 96 and returning to the low pressure side of the fluid source from chamber 98 to cause clockwise rotation of the shaft 94, or directing high pressure fluid to chamber 98 and connecting chamber 96 to the low pressure return side of the source to cause counter-clockwise rotation of shaft 94.
  • the vane seal l04 extends along the length of vane l00 and on the end faces as described with respect to Figure 5.
  • the shaft seal is essentially as described with respect to Figure 6.
  • these endcaps also include slots which carry the ninety degree projections of the vane seals l04 which seal against the ends of vane l00.
  • This single vane embodiment has a practical travel limitation of about ⁇ eighty degrees rotation; however, it is most useful as a flat pack wherein the rotation is limited to not more than about ⁇ thirty degrees from center. It will have higher friction than the two vane embodiment since it is not balanced around the center but will fit in some locations where the two vane actuator will not fit.
  • actuators offer several advantages. Although they have a low height to fit into thin wing sections, they may be made comparatively long so that the high pressure will operate on a substantial area and provide a high actuating force. The use of only one or two vanes simplifies sealing problems and reduces costs. Where space requirements dictate, it is not impractical to make a two vane actuator with one vane longer then the other. By placing the longitudinal internal ribs opposite the flattened barrel portions, the barrel is strengthened in an area where it might otherwise be thin and subject to distortion.
  • the vane seals and shaft seals are both dynamic seals which are carried in the stationary barrel and endcaps rather than on movable parts such as the vanes and these seals may be backed by spring members or expanders to force the seals into contact with the opposing movable surfaces despite any distortion in the housing which might be caused by the large operating pressure variations. It will thus be apparent that the above actuator, while having the desired limited height, is simple and rugged in construction, and provides an effective sealing structure to minimize fluid leakage losses despite operating a substantially higher fluid pressures than are currently in general use.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Actuator (AREA)
EP19870104197 1986-06-09 1987-03-21 Actionneur hydraulique à clapet oscillant Expired EP0248986B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US87194486A 1986-06-09 1986-06-09
US871944 1986-06-09

Publications (2)

Publication Number Publication Date
EP0248986A1 true EP0248986A1 (fr) 1987-12-16
EP0248986B1 EP0248986B1 (fr) 1992-03-04

Family

ID=25358509

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870104197 Expired EP0248986B1 (fr) 1986-06-09 1987-03-21 Actionneur hydraulique à clapet oscillant

Country Status (3)

Country Link
EP (1) EP0248986B1 (fr)
JP (1) JPS62292902A (fr)
DE (1) DE3776972D1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4435491A1 (de) * 1993-11-05 1995-05-11 Fichtel & Sachs Ag Stabilisatoranordnung mit einem Schwenkmotor
US5573265A (en) * 1993-11-05 1996-11-12 Fichtel & Sachs Ag Stabilizer system for a motor vehicle suspension system with a rotary actuator
EP0957270A3 (fr) * 1998-05-13 2001-03-14 bar-pneumatische Steuerungssysteme GmbH Entraínement pivotant pour actionner une robinetterie
DE102006014018A1 (de) * 2006-03-27 2007-10-04 Robert Bosch Gmbh Hydraulischer Schwenkmotor
ITBO20090194A1 (it) * 2009-03-27 2010-09-28 Rovel S R L Attuatore azionato da un fluido in pressione
DE102011118321A1 (de) 2011-11-11 2013-05-16 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
WO2015031587A1 (fr) 2013-08-29 2015-03-05 Llc Vector Horizon Technologies Actionneur électro-hydraulique
WO2015071304A1 (fr) * 2013-11-13 2015-05-21 C. & E. Fein Gmbh Machine-outil pouvant être entraînée en oscillation
WO2016140959A1 (fr) 2015-03-02 2016-09-09 Vector Horizon Technologies, Llc Ensemble soupape et procédé de refroidissement
US10072773B2 (en) 2013-08-29 2018-09-11 Aventics Corporation Valve assembly and method of cooling
CN109996503A (zh) * 2016-12-28 2019-07-09 川崎重工业株式会社 机器人钳子
US11047506B2 (en) 2013-08-29 2021-06-29 Aventics Corporation Valve assembly and method of cooling
EP3816456A4 (fr) * 2018-06-26 2022-03-09 Kawasaki Jukogyo Kabushiki Kaisha Actionneur rotatif et forceps robotique
CN119773959A (zh) * 2025-03-12 2025-04-08 北京航辰机载智能系统科技有限公司 一种用于薄机翼飞机舵面驱动的电静液马达作动器
CN119821661A (zh) * 2025-03-14 2025-04-15 北京航辰机载智能系统科技有限公司 一种分区密封的叶片式航空作动器
CN119821662A (zh) * 2025-03-14 2025-04-15 北京航辰机载智能系统科技有限公司 一种用于驱动飞机舵面旋转的液压摆动马达

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2560857Y2 (ja) * 1990-11-19 1998-01-26 住友精密工業 株式会社 ロータリアクチュエータ

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2984221A (en) * 1958-07-01 1961-05-16 Douglas Aircraft Co Inc Rotary actuator
GB1036829A (en) * 1963-09-17 1966-07-20 Houdaille Industries Inc Improvements in or relating to semi-rotary hydraulic actuators
FR2492908A1 (fr) * 1980-10-29 1982-04-30 Renault Verin rotatif d'asservissement
DE3222982A1 (de) * 1982-06-19 1983-12-22 Südhydraulik Kork-Steinbach GmbH & Co KG, 2400 Lübeck Drehkolbenzylinder

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2984221A (en) * 1958-07-01 1961-05-16 Douglas Aircraft Co Inc Rotary actuator
GB1036829A (en) * 1963-09-17 1966-07-20 Houdaille Industries Inc Improvements in or relating to semi-rotary hydraulic actuators
FR2492908A1 (fr) * 1980-10-29 1982-04-30 Renault Verin rotatif d'asservissement
DE3222982A1 (de) * 1982-06-19 1983-12-22 Südhydraulik Kork-Steinbach GmbH & Co KG, 2400 Lübeck Drehkolbenzylinder

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4435491A1 (de) * 1993-11-05 1995-05-11 Fichtel & Sachs Ag Stabilisatoranordnung mit einem Schwenkmotor
US5573265A (en) * 1993-11-05 1996-11-12 Fichtel & Sachs Ag Stabilizer system for a motor vehicle suspension system with a rotary actuator
US5580079A (en) * 1993-11-05 1996-12-03 Fichtel & Sachs Ag Rotary actuator with stabilizer in a motor vehicle suspension system
EP0957270A3 (fr) * 1998-05-13 2001-03-14 bar-pneumatische Steuerungssysteme GmbH Entraínement pivotant pour actionner une robinetterie
DE102006014018A1 (de) * 2006-03-27 2007-10-04 Robert Bosch Gmbh Hydraulischer Schwenkmotor
ITBO20090194A1 (it) * 2009-03-27 2010-09-28 Rovel S R L Attuatore azionato da un fluido in pressione
DE102011118321A1 (de) 2011-11-11 2013-05-16 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
DE102011118321B4 (de) 2011-11-11 2023-01-19 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
US10072773B2 (en) 2013-08-29 2018-09-11 Aventics Corporation Valve assembly and method of cooling
US10359061B2 (en) 2013-08-29 2019-07-23 Aventics Corporation Electro-hydraulic actuator
WO2015031587A1 (fr) 2013-08-29 2015-03-05 Llc Vector Horizon Technologies Actionneur électro-hydraulique
US9897114B2 (en) 2013-08-29 2018-02-20 Aventics Corporation Electro-hydraulic actuator
US11047506B2 (en) 2013-08-29 2021-06-29 Aventics Corporation Valve assembly and method of cooling
US10093011B2 (en) 2013-11-13 2018-10-09 C. & E. Fein Gmbh Oscillatingly driven machine tool
WO2015071204A1 (fr) * 2013-11-13 2015-05-21 C. & E. Fein Gmbh Machine-outil à entraînement oscillant
WO2015071304A1 (fr) * 2013-11-13 2015-05-21 C. & E. Fein Gmbh Machine-outil pouvant être entraînée en oscillation
WO2016140959A1 (fr) 2015-03-02 2016-09-09 Vector Horizon Technologies, Llc Ensemble soupape et procédé de refroidissement
CN109996503A (zh) * 2016-12-28 2019-07-09 川崎重工业株式会社 机器人钳子
EP3563781A4 (fr) * 2016-12-28 2020-08-12 Kawasaki Jukogyo Kabushiki Kaisha Pince robotisée
EP3816456A4 (fr) * 2018-06-26 2022-03-09 Kawasaki Jukogyo Kabushiki Kaisha Actionneur rotatif et forceps robotique
CN119773959A (zh) * 2025-03-12 2025-04-08 北京航辰机载智能系统科技有限公司 一种用于薄机翼飞机舵面驱动的电静液马达作动器
CN119821661A (zh) * 2025-03-14 2025-04-15 北京航辰机载智能系统科技有限公司 一种分区密封的叶片式航空作动器
CN119821662A (zh) * 2025-03-14 2025-04-15 北京航辰机载智能系统科技有限公司 一种用于驱动飞机舵面旋转的液压摆动马达
CN119821661B (zh) * 2025-03-14 2025-05-30 北京航辰机载智能系统科技有限公司 一种分区密封的叶片式航空作动器
CN119821662B (zh) * 2025-03-14 2025-06-27 北京航辰机载智能系统科技有限公司 一种用于驱动飞机舵面旋转的液压摆动马达

Also Published As

Publication number Publication date
DE3776972D1 (de) 1992-04-09
EP0248986B1 (fr) 1992-03-04
JPS62292902A (ja) 1987-12-19

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