EP0715084B1 - Vérin rotatif conique et son application à la commande d'une gouverne d'aéronef - Google Patents

Vérin rotatif conique et son application à la commande d'une gouverne d'aéronef Download PDF

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Publication number
EP0715084B1
EP0715084B1 EP95402648A EP95402648A EP0715084B1 EP 0715084 B1 EP0715084 B1 EP 0715084B1 EP 95402648 A EP95402648 A EP 95402648A EP 95402648 A EP95402648 A EP 95402648A EP 0715084 B1 EP0715084 B1 EP 0715084B1
Authority
EP
European Patent Office
Prior art keywords
rotary actuator
inner body
panel
force transmission
blades
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 - Lifetime
Application number
EP95402648A
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German (de)
English (en)
French (fr)
Other versions
EP0715084A1 (fr
Inventor
Yves Durand
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.)
Aerospatiale Matra
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0715084A1 publication Critical patent/EP0715084A1/fr
Application granted granted Critical
Publication of EP0715084B1 publication Critical patent/EP0715084B1/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
    • 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

  • the invention relates to a rotary actuator.
  • a rotary actuator comprising an inner body and at least one body outside coaxially mounted one inside the other of so that they can be rotated relative, each of the cylinder bodies carrying pallets arranged alternately to define two series sealed variable volume control chambers.
  • Such a jack is known from document US-A-2 870 748.
  • the invention also relates to a control surface. aircraft comprising at least one hinged panel of which pivoting is controlled by such a rotary actuator.
  • the inner body and the outer body of the rotary cylinders have one and the other a cylindrical configuration and the height of pallets carried by each of these bodies is uniform from one end to the other of these pallets.
  • Number of pallets fitted to the actuator mainly depends on the amplitude of the pivoting movement that is desired order.
  • the cylinders rotary knobs are used to control movements of pivoting of limited amplitude between two parts. They have the advantage of having a very low space since they can be placed along the axis relative pivoting between the parts. By comparing, control of the same movement using a cylinder linear requires mounting the cylinder on one of the parts, perpendicular to the pivot axis and the connect to the other room using a mechanism including at least one articulated link.
  • control surfaces present rigidities different from those of the wing, it there are differences between deformations in flight control surfaces and sails. For reasons aerodynamics, the maximum values of these differences should be as small as possible. This can lead to carrying out each control under the form of several panels, which must then be ordered independently of each other. In the assumption that we would use two cylinders cylindrical by panel, installation of cylinders in the steering would require the presence of sixteen or twenty four levels depending on whether the control surface cut into two or three panels.
  • the main object of the invention is a original design rotary actuator with in particular, for a given diametrical size, a significantly higher power than a cylinder classic cylindrical rotary.
  • the invention also relates to a jack rotary whose original design reduces the number of stages necessary for the transmission of forces between the cylinder and the parts and, consequently, the cost of an installation using such cylinders.
  • the invention also relates to a jack rotary whose original design reduces torsional deformations of at least one of the bodies inside and outside of the cylinder, relative to the cylinders conventional rotary.
  • a rotary actuator comprising an inner body and at least one outer body coaxially mounted one inside the other so as to define between them at least one annular space, first pallets and second integral pallets the inner body and the outer body respectively and arranged alternately in said annular space, to alternately define firsts and second volume tight control chambers variable, including alternating pressure control relative rotation between the inner bodies and exterior, characterized in that at least one interior and exterior body has a section scalable, so that the first and second pallets have a height which decreases by one end to end of these pallets.
  • a rotary actuator meeting this definition will be called hereinafter "conical rotary actuator”. This designation, which stems from the evolving nature of the section of the annular space formed between the bodies inside and outside of the cylinder, must not be considered to limit the configuration of this annular space with a precise geometric shape.
  • the outer body is cylindrical and has a constant section while the inner body has an evolving section.
  • the inner body can in particular present a substantially frustoconical part and a substantially cylindrical part extending a relatively small diameter end of the part substantially frustoconical.
  • the relatively large end of the substantially frustoconical part of the inner body then has an outer diameter substantially equal to the inside diameter of the outside body.
  • the inner body constitutes the rotor cylinder while the outer body is the stator.
  • a reverse arrangement can however be adopted in some applications.
  • the internal body of the jack is advantageously a tubular body. This feature allows to connect the inner body to a conditioning circuit in temperature, ensuring circulation, inside of the cylinder of a heat transfer fluid capable of reheat or cool the cylinder as required of use.
  • the rotary actuator comprises two bodies exteriors mounted coaxially on two parts of the inner body, each of these two parts bearing second pallets arranged alternately with the first pallets carried by each body exteriors.
  • the rotary actuator then advantageously has symmetry with respect to a cutting median plane the inner body in the middle.
  • the heights of the first and second pallets decrease from the median plane of the cylinder towards its ends.
  • the internal body comprises, between the two parts carrying the second pallets, a central force transmission part.
  • each of the outer bodies includes a terminal part transmission of forces, close to each ends of the cylinder.
  • the invention also relates to a control surface.
  • aircraft comprising at least one hinged panel on a rear spar of a wing element aircraft, around a hinge axis substantially parallel to this rear spar, and means for panel pivot control around this axis of articulation, characterized in that the means pivot control include at least one cylinder conical rotary machine according to the invention, housed in the panel according to its axis of articulation.
  • each of the first bearings is carried by the beam back so you can turn around a first axis perpendicular to the spar and passing through the axis of articulation of the panel.
  • each of the first bearings is engaged on the terminal parts transmission of cylinder forces by first connecting means in rotation around the axis of articulation of the panel.
  • first connecting means in rotation around the axis of articulation of the panel.
  • second connecting means in rotation about the axis of articulation, by which the second landing is engaged on the central part of force transmission from the jack.
  • each elevons 12 and 14 is cut into three panels adjacent articulated, of substantially equal dimensions, in the direction defined by the rear spar 18. These three panels are designated by the references 12a, 12b and 12c for internal elevons 12 and 14a, 14b and 14c for the middle elevons 14.
  • each of the panels 12a, 1b and 12c and 14a, 14b and 14c is controlled by a conical rotary actuator 16. More specifically, the three rotary cylinders conical 16 associated with each of elevons 12 and 14 are identical.
  • each of the rotary cylinders conical 16 has two transmission end parts of efforts which are connected by two bearings 26 to the rear spar 18 of the corresponding half-wing 10.
  • the rotary actuator conical 16 comprises a body tubular interior 32 forming rotor and two bodies tubular exteriors 34 forming a stator, mounted coaxially.
  • each outer body 34 is identical and each of them is received on one of the parts tubular 38 of the inner body 32, so that delimit between this part 38 and the external body 34 corresponding to a tight annular space vis-à-vis from the outside.
  • each outer body 34 has on its outer surface a terminal part 62 for transmitting forces, intended to be engaged on the corresponding bearing 26, in a way that will be described further detail later.
  • Each of the tubular parts 38 of the body interior 32 carries pallets on its exterior surface 40 oriented radially outwards (figure 5). These pallets 40 are regularly distributed over the periphery of the tubular part 38. They are by example of four in the embodiment represented. The edges of the turned pallets 40 towards the corresponding external body 34 carry seals 42 ensuring the tightness of the contact between these two rooms.
  • each of the external bodies 34 has pallets on its inner surface 44 oriented radially inwards. Pallets 44 are regularly distributed around the axis of the cylinder and their number is the same as that of the pallets 40, so that the pallets 40 and 44 are arranged alternately around the cylinder axis. In the embodiment shown, each of the bodies 34 therefore also has four pallets 44. The edges of the pallets 44 turned towards the body interior 32 have seals 46 which are in tight contact with the outer surface of the corresponding tubular part 38 of the interior body 32.
  • the end of relatively large diameter of the part 38a substantially frustoconical of each of the tubular parts 38 has an outside diameter substantially equal to inner body diameter 34 received on this part tubular 38.
  • Each of the pallets 40 and 44 has an approximately triangular shape. A calculation simple shows that for the same surface activates pallets and for a cylinder with the same outer diameter, the shape given to the pallets 40 and 44 in the conical rotary actuator according to the invention increases the cylinder's efficiency by 16.7% by compared to a design cylindrical rotary actuator traditional.
  • Each of the bearings 26 is mounted on the beam rear 18 of the corresponding half-wing 10 so that it can rotate around a perpendicular axis yy ' to the rear spar 18 and passing through the axis hinge xx 'of the corresponding panel such as the panel 12a in FIG. 5.
  • the arrangement which has just been described ensures the translational connection of the actuator 16 and the spar rear 18 of the corresponding half-wing 10, all by allowing a relative displacement necessary for the bending of the half-wing.
  • the bearing 20 is fixed on a force introduction fitting 78, itself fixed to the front spar 22 and to the rib strong median 24 (Figure 2) of the corresponding panel 12a.
  • the hollow character of the body inner tubular 32 of each of the cylinders 16 allows to connect the internal bodies 32 in series by a line 86 belonging to a conditioning circuit in temperature of a heat transfer fluid. It is thus possible to circulate in the cylinders a heat transfer fluid allowing in particular to heat these to facilitate their activation when the outside temperature is too low.
  • At least one shackle 88 is preferably placed between each pair of adjacent elevon panels, substantially mid-cord of these panels. Shackles 88 allow besides avoiding the rotation of each of the panels around its central rib 24, which could occur due to its rotational drive by a single level 20.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)
  • Actuator (AREA)
EP95402648A 1994-11-28 1995-11-23 Vérin rotatif conique et son application à la commande d'une gouverne d'aéronef Expired - Lifetime EP0715084B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR9414222A FR2727477A1 (fr) 1994-11-28 1994-11-28 Verin rotatif conique et son application a la commande d'une gouverne d'aeronef
FR9414222 1994-11-28
US08/562,761 US5722616A (en) 1994-11-28 1995-11-27 Conical rotary actuator and its application to the control of a rudder

Publications (2)

Publication Number Publication Date
EP0715084A1 EP0715084A1 (fr) 1996-06-05
EP0715084B1 true EP0715084B1 (fr) 2000-05-17

Family

ID=26231568

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402648A Expired - Lifetime EP0715084B1 (fr) 1994-11-28 1995-11-23 Vérin rotatif conique et son application à la commande d'une gouverne d'aéronef

Country Status (3)

Country Link
US (1) US5722616A (enrdf_load_stackoverflow)
EP (1) EP0715084B1 (enrdf_load_stackoverflow)
FR (1) FR2727477A1 (enrdf_load_stackoverflow)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL1003171C2 (nl) * 1996-05-20 1997-11-21 Arie Van Wieringen Video Film Vaancilinder.
US6672540B1 (en) 2002-12-03 2004-01-06 Rockwell Collins, Inc. Actuator for aircraft stabilizers with a failure responsive lock control mechanism
GB2470345A (en) * 2009-03-17 2010-11-24 Vestas Wind Systems A S Rotary actuator hinge for connecting first and second wind turbine components.
GB2472759A (en) 2009-03-17 2011-02-23 Vestas Wind Sys As Retractable hinge apparatus for wind turbine control surface
FR2992629B1 (fr) * 2012-06-27 2014-09-12 Airbus Operations Sas Dispositif de liaison mecanique d'une gouverne a un element structural fixe d'aeronef et element de voilure d'aeronef equipe de ce dispositif
US8973864B2 (en) 2012-08-02 2015-03-10 Bell Helicopter Textron Inc. Independent blade control system with hydraulic cyclic control
US9376205B2 (en) 2012-08-02 2016-06-28 Bell Helicopter Textron Inc. Radial fluid device with variable phase and amplitude
US9162760B2 (en) 2012-08-02 2015-10-20 Bell Helicopter Textron Inc. Radial fluid device with multi-harmonic output
US8857757B2 (en) 2012-08-02 2014-10-14 Bell Helicopter Textron Inc. Independent blade control system with hydraulic pitch link
US9061760B2 (en) 2012-08-02 2015-06-23 Bell Helicopter Textron Inc. Independent blade control system with rotary blade actuator
US8915176B2 (en) 2013-02-06 2014-12-23 Woodward, Inc. Hydraulic blocking rotary actuator
US9234535B2 (en) 2013-02-27 2016-01-12 Woodward, Inc. Rotary piston type actuator
US9816537B2 (en) * 2013-02-27 2017-11-14 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
US9593696B2 (en) * 2013-02-27 2017-03-14 Woodward, Inc. Rotary piston type actuator with hydraulic supply
US9631645B2 (en) 2013-02-27 2017-04-25 Woodward, Inc. Rotary piston actuator anti-rotation configurations
US9163648B2 (en) 2013-02-27 2015-10-20 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
US9476434B2 (en) 2013-02-27 2016-10-25 Woodward, Inc. Rotary piston type actuator with modular housing
US8955425B2 (en) 2013-02-27 2015-02-17 Woodward, Inc. Rotary piston type actuator with pin retention features
US9915241B2 (en) 2013-03-14 2018-03-13 Woodward, Inc. Rotary vane actuator with fluid actuated mechanical lock
US9841021B2 (en) 2013-03-14 2017-12-12 Woodward, Inc. No corner seal rotary vane actuator
BR112015031898A8 (pt) * 2013-06-19 2019-12-31 Woodward Inc sistemas de atuador giratório e métodos de atuação giratória
US9957831B2 (en) * 2014-07-31 2018-05-01 The Boeing Company Systems, methods, and apparatus for rotary vane actuators
US9950782B2 (en) 2014-10-31 2018-04-24 The Boeing Company Methods and apparatus for integrating rotary actuators in flight control systems
US10220938B2 (en) * 2014-12-11 2019-03-05 Gulfstream Aerospace Corporation Aircraft, control surface arrangements, and methods of assembling an aircraft
US10318904B2 (en) 2016-05-06 2019-06-11 General Electric Company Computing system to control the use of physical state attainment of assets to meet temporal performance criteria
US10633080B2 (en) * 2016-07-22 2020-04-28 The Boeing Company Electronically controlled rotary actuator for an aircraft control surface
US11199248B2 (en) 2019-04-30 2021-12-14 Woodward, Inc. Compact linear to rotary actuator
US11333175B2 (en) 2020-04-08 2022-05-17 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
CN115009509B (zh) * 2022-06-10 2025-08-01 天津斑斓航空科技有限公司 一种充气式转动舵机及飞行器

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2870748A (en) * 1953-06-30 1959-01-27 North American Aviation Inc Rotary actuator
DE1024804B (de) * 1956-09-18 1958-02-20 Ernst Heinkel Fahrzeugbau G M Hydraulischer Klappenantrieb, insbesondere fuer Flugzeuge
US3020008A (en) * 1957-10-01 1962-02-06 Houdaille Industries Inc Control surface actuator damper hinge
US2951470A (en) * 1957-10-15 1960-09-06 Richard E Self Oscillating actuator
US2984221A (en) * 1958-07-01 1961-05-16 Douglas Aircraft Co Inc Rotary actuator
US2966144A (en) * 1958-07-15 1960-12-27 C L Norsworthy Jr Oscillatory actuator
US3053232A (en) * 1960-09-08 1962-09-11 Thompson Ramo Wooldridge Inc Damper reservoir gas actuator
ATE37429T1 (de) * 1984-07-20 1988-10-15 Tol O Matic Inc Stellglied fuer drehbewegungen.
US4738415A (en) * 1986-10-17 1988-04-19 Weyer Paul P Hinge line flight actuator
FR2606363B1 (fr) * 1986-11-07 1989-03-03 Aerospatiale Systeme pour la commande des volets hypersustentateurs d'un aeronef
US4838104A (en) * 1987-08-07 1989-06-13 Pneumo Abex Corporation Center mounted and center drive helical spline actuator
US4945779A (en) * 1987-12-22 1990-08-07 Hr Textron, Inc. Ball screw rotary actuator
US5098043A (en) * 1990-02-27 1992-03-24 Grumman Aerospace Corporation Integrated power hinge actuator

Also Published As

Publication number Publication date
FR2727477A1 (fr) 1996-05-31
FR2727477B1 (enrdf_load_stackoverflow) 1997-02-14
EP0715084A1 (fr) 1996-06-05
US5722616A (en) 1998-03-03

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