EP0132199B1 - Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges - Google Patents

Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges Download PDF

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Publication number
EP0132199B1
EP0132199B1 EP84401466A EP84401466A EP0132199B1 EP 0132199 B1 EP0132199 B1 EP 0132199B1 EP 84401466 A EP84401466 A EP 84401466A EP 84401466 A EP84401466 A EP 84401466A EP 0132199 B1 EP0132199 B1 EP 0132199B1
Authority
EP
European Patent Office
Prior art keywords
plug
sleeve
liner
aircraft
lever
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
EP84401466A
Other languages
English (en)
French (fr)
Other versions
EP0132199A1 (de
Inventor
Gérard Devaud
Serge David
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.)
Societe dApplications des Machines Motrices SAMM SA
Original Assignee
Societe dApplications des Machines Motrices SAMM SA
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.)
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Publication date
Application filed by Societe dApplications des Machines Motrices SAMM SA filed Critical Societe dApplications des Machines Motrices SAMM SA
Publication of EP0132199A1 publication Critical patent/EP0132199A1/de
Application granted granted Critical
Publication of EP0132199B1 publication Critical patent/EP0132199B1/de
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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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/8593—Systems
    • Y10T137/86493—Multi-way valve unit
    • Y10T137/86574—Supply and exhaust
    • Y10T137/86638—Rotary valve
    • Y10T137/86646—Plug type

Definitions

  • the present invention relates to a hydraulic distributor intended to equip an aircraft control, in particular the flaps or "spoilers" of the wings of an aircraft which are used to control the turns thereof, or as air brakes during of the landing.
  • a device is thus produced with "position copying", which requires, when the distributor is not integrated into the actuator, an extremely bulky and complicated system of links and intermediate articulation axes to transmit the order to feedback of the servo position, after a pilot control maneuver.
  • a four-way servo-control distributor performing a function of this type and comprising a central plug and a rotor surrounding the plug, but the realization of which is complicated and bulky.
  • a body is provided in three parts, two end parts and an intermediate ring, the plug and the rotor being arranged concentrically with respect to each other at the level of the intermediate ring. and extending respectively through one of the end parts of the body, by two shafts which are therefore arranged on either side of the body.
  • the object of the invention is to provide a servo-control with a position feedback device which does not present a prohibitive bulk, and the production of which is simplified compared to known systems.
  • the invention provides for using a double distributor comparable to that described in patent FR-A 2 460 435 (EP-A 0 021 977).
  • This front four-way hydraulic distributor has two use chambers and is equipped with a safety device guaranteeing the continuity of the normal operation of the distributor, in the event of seizure or blockage of its central control valve.
  • This distributor therefore includes a central plug rotatably mounted in a fixed fur housed in a body, and connected at one end to a control device, and an annular jacket interposed rotatably between the plug and the fur, bores for the pressure entry and the outlet of a hydraulic fluid being drilled in the fur and in the jacket, as well as passages on the periphery of the plug to ensure the circulation of the hydraulic fluid from one bore to the other of the fur passing through those of the shirt when the bushel turns.
  • one end of the sleeve projects outside the body on the side of the latter where said end of the plug already projects and it is integral in rotation with a lateral lever, transverse to the axis of the plug. and associated with a summing device constituting a feedback control, capable of gradually bringing back, via the aforementioned lever, the liner to its initial angular position relative to the plug, after rotation of the latter by a predetermined angle.
  • the invention transforms the safety jacket of the distributor of the aforementioned patent FR-A2460435 into an element fulfilling a completely different function, since this jacket then constitutes the terminal element of a position feedback device.
  • this solution avoids the implementation of bulky and complicated systems corresponding to rods and joints, to replace them with a single distributor that is compact and simple to produce.
  • the device shown diagrammatically in FIG. 1 is a hydraulic servo-control of a part 1 articulated on a fixed axis 2, and which can for example be a flap or "spoiler" of an aircraft wing.
  • This servo-control comprises a linkage 3 driven by an electric motor not shown, and which can control the rotation of the central plug 4 of a hydraulic distributor 5 connected to a jack 6 whose annular chamber is permanently under pressure, and whose the rod is articulated on the pivoting flap 1.
  • the control of the distributor 5 can also be obtained mechanically, by a linkage 7, in a known manner.
  • the linkages 3 and 7 form a "summator" 8 of a control loop 9 connecting the shutter 1 to the distributor 5.
  • the control loop 9 including the summing device 8 constitutes a “position copying” device after an order from the pilot who has triggered a rotation of the plug 4 by a determined angle and the subsequent tilting of the flap 1.
  • This copying device automatically returns a sleeve 11 coaxial with the plug 4 in the distributor 5 to its initial angular position relative to the plug 4, in order to stabilize the flap 1 in its new position.
  • the distributor according to the invention shown in detail in Figures 2 to 4, has a structure derived from that of the distributor of the above-mentioned French patent 2,460,435.
  • This hydraulic distributor 35 comprises a central plug 12 rotatably mounted in a fixed fur 13 coaxial with this plug, and an annular jacket 14 also coaxial with the plug 12, interposed rotatably between the latter and the fur 13. The latter is secured to a body 15 with interposition of a tubular sealing part 16.
  • the plug 12 has on its periphery two recesses 29a, 29b, diametrically opposite and which extend over equal angular sectors.
  • the bores 19, 21, 22 open outwardly into an annular gap 10 which communicates with a pipe 30 (FIG. 3) for supplying pressurized hydraulic fluid, this fluid being evacuated from the distributor by an outlet 31 formed in the body 15.
  • the rotary jacket 14 protrudes over a determined length 1 outside the body 15 on the same side as the plug, and its external protruding part 14a is rotationally integral with a lateral lever 32 ( Figures 3 and 4).
  • the lever 32 has a toothed end sector 33 engaged with a toothed wheel 34 of a summing device such as 8 ( Figure 1), intended to ensure the copying of the position angle of the plug 12 by the sleeve 14, and this by means of the operating lever 32.
  • the distributor 35 is fixed on a support 36 carrying an axis 37 on which a lever 38 is articulated, on which is in turn articulated the arm 18 for controlling the rotation of the plug 12.
  • a lever 38 is also articulated an arm 41 capable of being driven in translation by a motor member 42, thanks to the invention. All these various elements can be arranged on the same support face 36.
  • the rotary jacket 14 is mounted on a ball bearing 40 and on needle bearings 43, the latter being interposed between the jacket 14 and the fur 13.
  • the bearing 40 is interposed between the liner 14 and a tubular part 44 fixed to the body 15 by bolts 45.
  • Another ball bearing 46 is interposed between the liner 14, the plug 12 and an annular shoulder 47 of the latter.
  • This tubular part 51 is integral in rotation with the plug 12 and the arm 18, by means of teeth or complementary fingers 51 a.
  • the part 51 could be integral in rotation with the jacket 14.
  • Hydraulic fluid under pressure enters the distributor 35 through the bores 19, 23, and 26.
  • the valve 12 is oriented so as to stop the fluid in the recesses 29a, 29b, which do not communicate not with the openings 27, 28. If now the pilot of the aircraft gives the distributor 35, by means of the control members 42, 41, 38, 18 an order which drives the plug 12 in rotation in the anti-direction AR schedule (arrows in Figure 2), the passages 29a, 29b establish communication between the bores 19, 23, 26 on the one hand, and 27, 25, 21 on the other hand, so that the hydraulic fluid flows towards its first use through the bores 21, following the path indicated by the arrows in solid lines in FIG. 2.
  • the flap or “spoiler” of the aircraft tilts at an angle which increases as long as the order of rotation of the plug 12 is maintained and the fluid can flow from the bores 19 to the bores 21
  • the position feedback device comprising the adder triggers the rotation of the toothed wheel 34 in the direction which makes the lever 32 and consequently the jacket 14 rotate so that this the latter rotates in the same direction as the plug 12, the movement of which it thus "follows", with a certain time lag.
  • the invention is not limited to the embodiment described and may include variant embodiments.
  • the fact of copying the angular position of the plug 12 by securing the liner 14 with a lever such as 32 of the servo-control summator considerably reduces the size and complexity of the device which would be necessary if the 'we had adopted a more classic solution.

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

Claims (3)

1. Hydraulischer Verteiler für die Servosteuerung eines Luftfahrzeuges, wie zum Beispiel für die Bremsklappen (1) an den Tragflächen eines Flugzeuges, mit einer drehbar in einem feststehenden, in einem Körper (15) angeordneten und an dem einen Ende (17) mit einer Steuervorrichtung (18, 41, 42) verbundenen Futter (13) gelagerten Verteilernabe (12), einem zwischen der Verteilernabe (12) und dem Futter (13) drehbar angeordneten ringförmigen Mantel (14), Bohrungen (19, 23, 26; 27, 25, 21; 28, 24, 22) in dem Futter (13) und dem Mantel (14) zum Eintritt unter Druck und Austritt einer Hydraulikflüssigkeit und Kanälen (29 a, 29 b) am Umfang der Verteilernabe (12) zur Sicherstellung des Kreislaufes der Hydraulikflüssigkeit von einer Bohrung (23) des Futters (13) zur nächsten (24, 25), wobei die Hydraulikflüssigkeit bei Drehung der Verteilernabe (12) die Bohrungen in dem Mantel (14) durchströmt, dadurch gekennzeichnet, dass ein Ende (14a) des drehbaren Mantels (14) über die Seite des Körpers vorsteht, auf der sich das Ende (17) der Verteilernabe befindet, wobei dieses Ende bei der Drehung mit einem seitlichen Hebel (32) fest verbunden ist, der wiederum mit einer Stellungs-Kopiervorrichtung in Form einer Rücklaufsteuerung (9; 32-34) verbunden ist, welche nach Drehung der Verteilernabe um einen vorbestimmten Winkel mittels des Hebels den Mantel (14) in seine Ausgangs-Drehstellung gegenüber der Verteilernabe (12) fortschreitend zurückführt.
2. Verteiler nach Anspruch 1, dadurch gekennzeichnet, dass neben den über den Körper vorstehenden Enden (17; 14 a) der Verteilernabe (12) und des Mantels (14) ein zwischengeschaltetes Teil (51) vorgesehen ist, das bei der Drehung mit einem der beiden Elemente fest verbunden ist und jeweils mit diesen beiden Elementen zusammenwirkende Abdichtelemente (48, 49) aufweist.
Servosteuerungsvorrichtung für ein Luftfahrzeug, dadurch gekennzeichnet, dass diese einen auf einem Träger (36) befestigten Verteiler (25) nach einem der Ansprüche 1 und 2 aufweist, wobei die Verteilernabe (12) mit einem auf einem Hebel (38) gelenkig angeordneten Arm (18) fest verbunden ist, wobei dieser Hebel auf einem Träger (36) gelenkig angeordnet ist und darauf ein mit den Motorteilen verbundenes Teil (41) gelenkig angeordnet ist, während der mit einem Ende des Verteilermantels (14) fest verbundene Hebel (32) an seinem entgegengesetzten Ende einen mit einem gezahnten Bereich (34) einer Summiervorrichtung (8) in Eingriff stehenden gezahnten Abschnitt (33) aufweist.
EP84401466A 1983-07-13 1984-07-10 Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges Expired EP0132199B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8311714 1983-07-13
FR8311714A FR2549167B1 (fr) 1983-07-13 1983-07-13 Distributeur hydraulique destine a equiper une commande d'aeronef

Publications (2)

Publication Number Publication Date
EP0132199A1 EP0132199A1 (de) 1985-01-23
EP0132199B1 true EP0132199B1 (de) 1988-02-17

Family

ID=9290819

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84401466A Expired EP0132199B1 (de) 1983-07-13 1984-07-10 Hydraulischer Verteiler für die Steuerung eines Luftfahzeuges

Country Status (5)

Country Link
US (1) US4905572A (de)
EP (1) EP0132199B1 (de)
JP (1) JPH0629601B2 (de)
DE (1) DE3469380D1 (de)
FR (1) FR2549167B1 (de)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9217865D0 (en) 1992-08-21 1992-10-07 Unilever Plc Monitoring method
GB9217808D0 (en) 1992-08-21 1992-10-07 Unilever Plc Advisory method
GB9217864D0 (en) 1992-08-21 1992-10-07 Unilever Plc Monitoring method
US7141212B2 (en) 1993-11-12 2006-11-28 Inverness Medical Switzerland Gmbh Reading devices and assay devices for use therewith
DE19536553A1 (de) * 1995-09-30 1997-04-03 Eckehart Schulze Elektrohydraulische Steuerventilanordnung
FR2747174B1 (fr) * 1996-04-03 1998-07-10 Samm Societe D Applic Des Mach Distributeur hydraulique pour servocommandes d'aeronefs, notamment helicopteres
DE69626016T2 (de) 1996-09-27 2004-01-08 Inverness Medical Switzerland Gmbh Test-Kit und Vorrichtungen
DE19733031C2 (de) * 1997-07-31 2000-10-26 Mercedes Benz Lenkungen Gmbh Servoventil
US11998266B2 (en) 2009-10-12 2024-06-04 Otsuka Medical Devices Co., Ltd Intravascular energy delivery
CN103759043B (zh) * 2014-01-02 2016-08-17 武汉船用机械有限责任公司 一种转阀
CZ2014591A3 (cs) * 2014-08-29 2015-09-02 Peveko, Spol. S R.O. Vícecestný ventil pro řízení toku kapalných nebo plynných médií
US11168578B2 (en) * 2018-09-11 2021-11-09 Pratt & Whitney Canada Corp. System for adjusting a variable position vane in an aircraft engine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1729173A (en) * 1924-12-31 1929-09-24 Cie Electromecanique Servo-motor-controlled unclutching device for internal-combustion engines
GB630092A (en) * 1941-12-27 1949-10-05 Sperry Gyroscope Co Inc Improvements in or relating to positional control systems
US2431759A (en) * 1944-03-30 1947-12-02 Westinghouse Air Brake Co Stabilizer for pressure fluid servomotors
US2490509A (en) * 1945-01-26 1949-12-06 Hydraulic Engineering Co Inc Rotary follow valve
US2728404A (en) * 1951-04-16 1955-12-27 Adolphe C Peterson Power steering using hydraulic motors
US3254674A (en) * 1964-08-04 1966-06-07 Airoyal Engineering Company Rotary servo valve
GB1119991A (en) * 1966-02-10 1968-07-17 Airoyal Engineering Company Rotary servo valve
JPS5260598U (de) * 1975-10-31 1977-05-02
FR2460435A1 (fr) * 1979-07-03 1981-01-23 Applic Mach Motrices Distributeur hydraulique, destine notamment a equiper des servo-commandes d'avions et d'helicopteres
JPS5736802U (de) * 1981-04-30 1982-02-26

Also Published As

Publication number Publication date
JPH0629601B2 (ja) 1994-04-20
JPS6084402A (ja) 1985-05-13
DE3469380D1 (en) 1988-03-24
US4905572A (en) 1990-03-06
EP0132199A1 (de) 1985-01-23
FR2549167B1 (fr) 1988-01-29
FR2549167A1 (fr) 1985-01-18

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