EP0248986B1 - Hydraulisches Schwenkflügelstellglied - Google Patents

Hydraulisches Schwenkflügelstellglied Download PDF

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Publication number
EP0248986B1
EP0248986B1 EP19870104197 EP87104197A EP0248986B1 EP 0248986 B1 EP0248986 B1 EP 0248986B1 EP 19870104197 EP19870104197 EP 19870104197 EP 87104197 A EP87104197 A EP 87104197A EP 0248986 B1 EP0248986 B1 EP 0248986B1
Authority
EP
European Patent Office
Prior art keywords
shaft
vane
housing
internal chamber
seals
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
EP19870104197
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English (en)
French (fr)
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EP0248986A1 (de
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
AlliedSignal Inc
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Filing date
Publication date
Application filed by AlliedSignal Inc filed Critical AlliedSignal Inc
Publication of EP0248986A1 publication Critical patent/EP0248986A1/de
Application granted granted Critical
Publication of EP0248986B1 publication Critical patent/EP0248986B1/de
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 are 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 movable 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.
  • a rotary vane actuator is disclosed in US-A-2984221 and has a split housing having a generally cylindrical internal chamber with end walls covering each end of the housing.
  • a shaft passes through the centre of the housing and is supported in the wall cap passages, and a pair of diametrically opposed radially extending vanes are attached to the shaft to be movable therewith.
  • the housing has flattened diametrically opposed walls and the internal chamber has elongated axially directed ribs formed internally of the flattened walls, the ribs including arcuate surfaces adjacent to said shaft.
  • the vanes include arcuate surfaces adjacent walls of the internal chamber.
  • O-rings are provided in grooves in the housing with a pair extending longitudinally opposite each radially outer end of each vane and the grooves also extending around the ends of the housing and opposite each of the two "unbladed" faces of the shaft.
  • 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.
  • a rotary vane hydraulic actuator including: a housing having diametrically opposed substantially parallel externally flattened walls and a generally cylindrical internal chamber with ends walls covering each end of the housing; a shaft extending longitudinally axially through said housing and rotatably supported in axial end wall passages; at least one radially extending vane attached to said shaft and movable with said shaft in said housing, said vane including an arcuate surface adjacent the cylindrical wall of said internal chamber; at least one elongated longitudinal axially extending rib formed with said housing and located in said internal chamber, said rib including an arcuate surface adjacent said shaft; first seal means located in the wall of said internal chamber and adapted to radially seal against the arcuate surface of said vane and axially against the end surfaces of said vane; second seal means located in the arcuate surface of said rib and adapted to seal against the surface of said shaft; third seal means located in said end wall passages for circumferentially sealing against said shaft; and port means provided for entry and
  • 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 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, 20 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 18, 20.
  • a pair of static seals 26 and 28 are positoned between endcaps l2 and l4, respectively, and the cylinder barrel l0.
  • Shaft 18, 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 18, 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 the 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 18 carries vane 50 which makes contact against seal 66.
  • Seal 66 is carried in barrel 10 through its length and extends into slots 70 and 72 in endcaps 12 and 14, 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 10.
  • 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 105 in the end caps 12 and 14 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 10.
  • Seal 34 extends into notches in ring seals 105 in endcaps 12 and 14 or otherwise makes an interference fit against the seals 105 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 10 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 the 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)

Claims (8)

  1. Hydraulischer Drehflügelmotor mit
       einem Gehäuse (10, 90), das einander dismetral gegenüberliegende, im wesentlichen parallele, außen abgeflachte Wände und eine allgemein zylindrische Innenkammer mit Stirnwänden (12, 14) besitzt, die je ein Ende des Gehäuses bedecken;
       einer Welle (18, 20, 94) die in ihrer Längsrichtung das Gehäuse (10, 90) axial durchsetzt und in axialen Stirnwanddurchlässen drehbar gelagert ist;
       mindestens einem sich radial erstreckenden Flügel (50, 52; 100), der an der Welle (18, 20, 94) befestigt und mit der Welle in dem Gehäuse (10, 90) bewegbar ist, wobei der Flügel im Bereich der zylindrischen Wandung der genannten Innenkammer eine bogenförmige Fläche (54, 56) besitzt;
       mindestens einer langgestreckten Rippe (42, 44), die sich in ihrer Längsrichtung axial erstreckt und mit der das Gehäuse (10, 90) ausgebildet ist und die in der Innenkammer angeordnet ist, wobei die Rippe (42, 44) im Bereich der Welle (18, 20, 90) eine bogenförmige Fläche (46, 48) besitzt;
       in der Wand der Innenkammer angeordneten, ersten Dichtungsmitteln (66, 68, 104), die zum radialen Abdichten an der bogenförmigen Fläche (54, 56) des Flügels (50, 52, 100) und zum axialen Abdichten an den Stirnflächen des Flügels geeignet sind;
       zweiten Dichtungsmitteln (34, 36, 102), die in der bogenförmigen Fläche (46, 48) der Rippe (42, 44) angeordnet und zum Abdichten an der Oberfläche der Welle (18, 20, 94) geeignet sind;
       dritten Dichtungsmitteln (22, 22'), die in den genannten Stirnwanddurchlässen angeordnet sind und zum Abdichten an der Welle (18, 20, 94) in der Umfangsrichtung dienen; und
       Anschlußmitteln (72; 82, 84; 106, 108) für den Eintritt und Austritt eines unter Druck stehenden Hydraulikmediums in die bzw. aus der Innenkammer;
       dadurch gekennzeichnet, daß das Gehäuse von einem einstückigen trommelartigen Körper (10, 90) gebildet wird, der an beiden Enden von getrennten Stirnkappen (12, 14) bedeckt ist; daß zwischen jeder der Stirnkappen (12, 14) und dem trommelartigen Körper (19, 90) vierte Dichtungsmittel (26, 28) angeordnet sind; und daß in den Sitrnkappen (12, 14) fünfte Dichtungsmittel in Form von Dichtungsringen (105) angeordnet sind, die zum Abdichten an der Welle (18, 20, 94) in der Umfangsrichtung und zum axialen Abdichten an den entsprechenden Enden der ersten und zweiten Dichtungsmittel (66, 68, 104; 34, 36, 102) dienen.
  2. Drehflügelmotor nach Anspruch 1, gekennzeichnet durch langgestreckte Rippen (42, 44), die sich in ihrer Längsrichtung axial erstrecken und mit denen das Gehäuse (10) einwärts von den abgeflachten Wänden ausgebildet ist.
  3. Drehflügelmotor nach Anspruch 1, dadurch gekennzeichnet, daß zwei Flügel (50, 52) vorgesehen sind, von denen jeder derart einstückig mit der Welle (18, 20) ausgebildet ist, daß die Flügel und die sich axial erstreckenden Rippen (42, 44) die Innenkammer effektiv in vier langgestreckte Abteile (58, 60, 62, 64) zum Empfang von Fluid von einer Quelle unterteilen.
  4. Drehflügelmotor nach Anspruch 3, dadurch gekennzeichnet, daß die Endkappen (12, 14) Fluidkanäle (74, 76, 78, 80) besitzen, die durch einen der genannen Anschlüsse (72) derart mit der genannten Quelle verbunden sind, daß Fluid Abteilen auf der Oberseite eines Flügels und auf der Unterseite des anderen Flügels zugeführt wird, um eine Drehung der Welle in einem Drehsinn zu bewirken, und der Unterseite des einen Flügels und der Oberseite des anderen Flügels, um eine Drehung der Welle (18) im entgegengesetzten Drehsinn zu bewirken.
  5. Drehflügelmotor nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die genannten Dichtungen in den Wendungen der Innenkammer (66, 88) und in den bogenförmigen Flächen der Rippen (34, 36) in Nuten abgestützt sind und durch zwischen dem Grund der genannten Nuten und den Dichtungen angeordnete Belastungselemente mit den bogenförmigen Flächen der Flügel und mit der Oberfläche der Welle in Berührung gehalten werden.
  6. Drehflügelmotor nach Anspruch 3, dadurch gekennzeichnet, daß die Anschlüsse (82, 84) in der Seitenwand des Gehäuses (10) abgestützt sind und mit zweien der genannten vier Abteile (58, 60, 62, 64) in Verbindung stehen, und daß die Welle (18, 20) diametral von Kanälen (86, 88) durchsetzt sind, die jedes der genannten zwei Abteile mit einem anderen Abteil verbinden, das in einem Winkelabstand von etwa einhundertachtzig Grad auf der anderen Seite der Welle (18, 20) angeordnet ist.
  7. Drehflügelmotor nach Anspruch 1, dadurch gekennzeichnet, daß die bogenförmigen Flächen (54, 56), der Flügel (50, 52) eine solche Länge haben, daß die Wandungen der Innenkammer angeordneten, ersten Dichtungen (66, 88) innerhalb der Grenzen der Bewegung der Flügel (50, 52) mit den bogenförmigen Flächen (54, 56) in Berührung bleiben.
  8. Hydraulischer Drehflügelmotor nach Anspruch 1, dadurch gekennzeichnet, daß ein einziger Flügel (100) vorgesehen ist, der derart einstückig mit der Welle (94) ausgebildet ist, daß der Flügel die Innenkammer effektiv in zwei langgestreckte Abteile (96, 98) unterteilt, die zum Empfang von Fluid von einer Quelle dienen.
EP19870104197 1986-06-09 1987-03-21 Hydraulisches Schwenkflügelstellglied Expired EP0248986B1 (de)

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 EP0248986A1 (de) 1987-12-16
EP0248986B1 true EP0248986B1 (de) 1992-03-04

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EP19870104197 Expired EP0248986B1 (de) 1986-06-09 1987-03-21 Hydraulisches Schwenkflügelstellglied

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EP (1) EP0248986B1 (de)
JP (1) JPS62292902A (de)
DE (1) DE3776972D1 (de)

Families Citing this family (14)

* 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
DE4435491C2 (de) * 1993-11-05 1997-07-03 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
DE19821435C2 (de) * 1998-05-13 2000-05-04 Bar Pneumatische Steuerungssys Schwenkantrieb zur Betätigung einer Armatur
DE102006014018A1 (de) * 2006-03-27 2007-10-04 Robert Bosch Gmbh Hydraulischer Schwenkmotor
IT1398128B1 (it) * 2009-03-27 2013-02-14 Rovel S R L Attuatore azionato da un fluido in pressione
DE102011118321B4 (de) 2011-11-11 2023-01-19 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
US9897114B2 (en) 2013-08-29 2018-02-20 Aventics Corporation Electro-hydraulic actuator
US10072773B2 (en) 2013-08-29 2018-09-11 Aventics Corporation Valve assembly and method of cooling
US11047506B2 (en) 2013-08-29 2021-06-29 Aventics Corporation Valve assembly and method of cooling
DE102013112455A1 (de) 2013-11-13 2015-05-13 C. & E. Fein Gmbh Oszillierend antreibbare Werkzeugmaschine
ES2847978T3 (es) 2015-03-02 2021-08-04 Aventics Corp Montaje de válvula y método de enfriamiento
JP6646570B2 (ja) * 2016-12-28 2020-02-14 川崎重工業株式会社 ロボット鉗子
JP2020002966A (ja) * 2018-06-26 2020-01-09 川崎重工業株式会社 ロータリアクチュエータおよびロボット鉗子

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Publication number Priority date Publication date Assignee Title
US2984221A (en) * 1958-07-01 1961-05-16 Douglas Aircraft Co Inc Rotary actuator
US3277796A (en) * 1963-09-17 1966-10-11 Houdaille Industries Inc Method of and means for assembling wingshafts and abutments in rotary fluid pressure devices
FR2492908A1 (fr) * 1980-10-29 1982-04-30 Renault Verin rotatif d'asservissement
DE3222982C2 (de) * 1982-06-19 1986-04-30 Südhydraulik Kork-Steinbach GmbH & Co KG, 2400 Lübeck Drehkolbenzylinder

Also Published As

Publication number Publication date
DE3776972D1 (de) 1992-04-09
JPS62292902A (ja) 1987-12-19
EP0248986A1 (de) 1987-12-16

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