WO2011128441A1 - Actionneur electromecanique a regulation hydraulique, et atterrisseur equipe d'un tel actionneur pour sa manœuvre - Google Patents
Actionneur electromecanique a regulation hydraulique, et atterrisseur equipe d'un tel actionneur pour sa manœuvre Download PDFInfo
- Publication number
- WO2011128441A1 WO2011128441A1 PCT/EP2011/056042 EP2011056042W WO2011128441A1 WO 2011128441 A1 WO2011128441 A1 WO 2011128441A1 EP 2011056042 W EP2011056042 W EP 2011056042W WO 2011128441 A1 WO2011128441 A1 WO 2011128441A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- actuator
- output shaft
- fluid
- rotation
- chamber
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D57/00—Liquid-resistance brakes; Brakes using the internal friction of fluids or fluid-like media, e.g. powders
- F16D57/06—Liquid-resistance brakes; Brakes using the internal friction of fluids or fluid-like media, e.g. powders comprising a pump circulating fluid, braking being effected by throttling of the circulation
Definitions
- the present invention relates to an electromechanical actuator with hydraulic regulation, and an undercarriage equipped with such an actuator for its maneuver.
- the actuator of the invention may also be used in other applications, particularly in those in which the rotation of the output shaft must also be controlled in case of non power supply or malfunction of the electric motor.
- Aircraft undercarriages are known whose operation between an extended position and a retracted position is effected by means of a hydraulic type actuator, for example a jack.
- a hydraulic type actuator for example a jack.
- the undercarriage is allowed to descend under the effect of gravity, the jack being used as a regulator to limit the speed of descent of the undercarriage.
- the jack being used as a regulator to limit the speed of descent of the undercarriage.
- it causes a rolling of the expelled fluid from the cylinder chamber whose volume is reduced during the descent. This braking is automatic and therefore occurs even if the hydraulic generation had to fail, which represents a great security.
- rotary electromechanical actuators which cooperate with the undercarriage either directly at a pivot of the landing gear, or indirectly via a connecting rod hitched between a crank secured to the actuator and the box of one undercarriage.
- the descent of the undercarriage is under the effect of gravity, and the electromechanical actuator is used as a descent regulator.
- the electric motor of the actuator is fed so that it exerts a resistant torque, thus regulating the speed of descent of the undercarriage.
- the object of the present invention is to provide an electromechanical actuator for passive speed regulation when the actuator is driven by an external cause.
- the invention relates to an electromechanical actuator comprising an electric motor for driving a shaft in rotation through a gearbox and control means for controlling the speed of rotation of the shaft.
- the regulation means are passive and comprise a braking member disposed between an output of the gearbox and the shaft to be driven, said braking member being arranged to provide two different braking levels depending on the direction of rotation of the gearbox. the tree.
- the braking means oppose a resistance to movement of the shaft which differs according to its direction of rotation.
- This characteristic is particularly advantageous in the case of an application to a landing gear actuator for which the resistance allowing the control of the descent can be chosen relatively high while the resistance to be opposed during the ascent of the undercarriage can be chosen. limited, or even zero, to reduce the amount of energy needed for the ascent.
- the braking member is of the hydraulic type and comprises means for transferring fluid from one chamber to another under the effect of the rotation of the output shaft through a selective rolling member which, in the direction of rotation of the actuator, opposes two distinct resistors to the transfer of the fluid from one chamber to another.
- Figure 1 shows a longitudinal sectional view of an actuator according to the invention
- FIG. 2 is a section along the line II-II of FIG. 1, at the control stage of the actuator shown in FIG.
- FIG. 3 represents an exemplary embodiment of the hydraulic circuit of the actuator of FIGS. 1 and 2;
- the actuator 1 of the invention comprises a drive stage 10, a reduction stage 20 and a regulation stage 30.
- the drive stage 10 comprises an electric motor 11 the stator 12 of which can be seen and the rotor 13 which has an output shaft 14 penetrating into the reduction stage 20 to cooperate with the input member 21 of a gearbox, here a "harmony drive” gearbox 22 This gearbox is well known for presenting a significant reduction ratio.
- the output shaft 24 associated with the deformable bell 23 enters the regulation stage 30 to cooperate with a braking member which comprises an output shaft 4 which constitutes the output shaft of the actuator 1.
- the braking member comprises a casing 31 of circular section in which a rotor 32 provided with a pallet 33 rotates while being driven by the output shaft 24 of the gearbox 22.
- a fixed sector 38 extends in the housing 31 to define with the rotor 32 and the pallet 33 two chambers 34 and 35 whose volume varies with the rotation of the rotor 32 and the pallet 33 so that when the volume of one of the chambers increases, the volume of the other rooms decreases.
- the two chambers 34, 35 are placed in fluid communication with an accumulator 36 (visible in FIG. 1) by means of a hydraulic block 37 comprising a number of hydraulic components which are now detailed in relation to FIG. which fluidic communications are represented by thick lines.
- the chamber 34 is connected by a first fluid branch 40 to the accumulator 36.
- the first fluidic branch 40 comprises two hydraulic components 41 placed in series and each having a restrictor 42 associated with a non-return valve 43 forcing the fluid to pass through the restrictors 42 when the fluid passes from the chamber 34 to the accumulator 36.
- the chamber 35 is connected by a second fluid branch 44 to the accumulator 36.
- the second fluidic branch 44 comprises a regulating restrictor 45.
- the operation of the braking member is as follows.
- the pallet 33 rotates in the direction indicated by the arrow in Figure 2 which is the one for which the chamber 34 sees its volume decrease, fluid is expelled from the chamber 34 to the accumulator 36 by the first fluid branch 40 through the restrictors 42 which exert a strong resistance to the passage of fluid, and thus contributes to slowing the rotation of the pallet 33, and, consequently, the rotation of the output shaft 4 of the actuator.
- fluid passes from the accumulator 36 to the chamber 35 through the restrictor 45 of the second fluid branch 44.
- this restrictor 45 is sufficiently open and the pressure of the accumulator 36 is large enough that no cavitation is observed in the chamber 35.
- the transfer from one chamber to another is done by forcing the fluid to pass through rolling members which selectively laminate (strong rolling in one direction, rolling low or almost zero in the other direction), so that the braking member offers two distinct braking levels, according to the direction of rotation of the output shaft 4 of one actuator.
- This braking is purely passive, and occurs especially when the output shaft 4 is driven by an external cause.
- Such an actuator can be advantageously used for the maneuvering of a landing gear between its deployed position and its retracted position. It can be arranged along a hinge axis of the box to directly attack it, or disposed parallel to the axis of articulation of the box 1 landing gear to attack it via a toothed sector, or be hitched to the subwoofer 1 by a rod connected to a crank driven by one actuator.
- the direction of rotation for which greater braking is generated corresponds to that which the undercarriage imposes on the actuator when the undercarriage descends to the deployed position under the effect of gravity or pressure. relative wind.
- the actuator of the invention may be coupled to one of the elements of the bracing, provided that the element concerned has a monotonous movement without recoil when the undercarriage moves from the deployed position to the retracted position.
- a landing gear 50 whose housing 51 is articulated on the structure of an aircraft.
- a breaker strut 52 having two arms articulated between them is articulated on the one hand on the structure of the aircraft and on the other hand on the box.
- a locking member 53 here also comprising two articulated arms extends between the strut 52 and the structure of the aircraft, as shown in Figure 4, or the box of the undercarriage, as shown in Figure 5.
- the actuator 1 of the invention is coupled to one of the arms of the strut 52 by means of a connecting rod 54 which cooperates with a crank 55 driven by the output shaft 4 of the actuator 1 .
- the braking member of the regulation stage described here is of the pallet type, it will be possible to use any other braking member, as long as this member exerts distinct braking levels according to the direction of rotation of the the actuator, one of the braking levels may be zero or negligible compared to the other braking level.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Braking Arrangements (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Actuator (AREA)
- Fluid-Pressure Circuits (AREA)
- Transmission Devices (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112012025987A BR112012025987A2 (pt) | 2010-04-15 | 2011-04-15 | acionador eletromecânico com regulagem hidráulica, e trem de aterragem equipado com tal acionador para sua manobra |
CN201180019153.5A CN102859225B (zh) | 2010-04-15 | 2011-04-15 | 液压调节的电磁致动器和装配有此类致动器用以控制的起落架 |
US13/640,809 US9056672B2 (en) | 2010-04-15 | 2011-04-15 | Hydraulically regulated electromagnetic actuator, and landing gear fitted with such an actuator for controlling same |
CA2796260A CA2796260C (fr) | 2010-04-15 | 2011-04-15 | Actionneur electromecanique a regulation hydraulique, et atterrisseur equipe d'un tel actionneur pour sa manoeuvre |
EP11714333.9A EP2558742B1 (fr) | 2010-04-15 | 2011-04-15 | Actionneur electromecanique a regulation hydraulique, et atterrisseur equipe d'un tel actionneur pour sa manoeuvre |
RU2012148457/11A RU2520676C1 (ru) | 2010-04-15 | 2011-04-15 | Электромеханический привод с гидравлическим регулированием и шасси, оборудованное таким приводом для управления его перемещением |
JP2013504292A JP5443652B2 (ja) | 2010-04-15 | 2011-04-15 | ハイドロリック形式で調節された電磁機械式のアクチュエーター及び制御のためにそのアクチュエーターが搭載された着陸装置 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1052885 | 2010-04-15 | ||
FR1052885A FR2958981B1 (fr) | 2010-04-15 | 2010-04-15 | Actionneur electromecanique a regulation hydraulique, et atterrisseur equipe d'un tel actionneur pour sa manoeuvre |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011128441A1 true WO2011128441A1 (fr) | 2011-10-20 |
Family
ID=42965387
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2011/056042 WO2011128441A1 (fr) | 2010-04-15 | 2011-04-15 | Actionneur electromecanique a regulation hydraulique, et atterrisseur equipe d'un tel actionneur pour sa manœuvre |
Country Status (9)
Country | Link |
---|---|
US (1) | US9056672B2 (fr) |
EP (1) | EP2558742B1 (fr) |
JP (1) | JP5443652B2 (fr) |
CN (1) | CN102859225B (fr) |
BR (1) | BR112012025987A2 (fr) |
CA (1) | CA2796260C (fr) |
FR (1) | FR2958981B1 (fr) |
RU (1) | RU2520676C1 (fr) |
WO (1) | WO2011128441A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3027015B1 (fr) * | 2014-10-10 | 2016-12-09 | Messier Bugatti Dowty | Atterrisseur d'aeronef. |
ITUA20162712A1 (it) * | 2016-04-19 | 2017-10-19 | Magnaghi Aeronautica S P A | Struttura di Sistema Carrello per Aeromobili provvisto di attuazione elettromeccanica e Aeromobile provvista di tale Struttura |
FR3073494B1 (fr) | 2017-11-15 | 2019-12-13 | Safran Landing Systems | Procede de manoeuvre d'un atterrisseur d'aeronef entre une position retractee et une position deployee |
US10787247B2 (en) | 2018-01-16 | 2020-09-29 | Goodrich Corporation | Hybrid actuator |
FR3089950B1 (fr) * | 2018-12-18 | 2022-06-17 | Safran Landing Systems | Procédé de protection contre les chocs pouvant affecter un atterrisseur d’aéronef |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2429425A (en) * | 1942-09-24 | 1947-10-21 | Bendix Aviat Corp | Driving mechanism |
DE19849756A1 (de) * | 1998-10-28 | 2000-05-11 | Netzsch Mohnopumpen Gmbh | Antriebskopf für ein drehantreibbares Gestänge, insbes. zum Antreiben einer Bohrlochpumpe |
DE102005061364A1 (de) * | 2005-12-21 | 2007-07-05 | Alexander Von Gencsy | Vorrichtung zur Notabsenkung |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3470792A (en) * | 1967-08-02 | 1969-10-07 | Cessna Aircraft Co | Maximum pressure control apparatus for hydraulic actuators |
US3631761A (en) * | 1967-09-18 | 1972-01-04 | Houdaille Industries Inc | Hydraulic action devices with inertia insensitive snubbing circuit |
FR1591645A (fr) * | 1968-10-15 | 1970-05-04 | ||
JPS4617202Y1 (fr) * | 1970-03-31 | 1971-06-16 | ||
US3771422A (en) * | 1971-10-13 | 1973-11-13 | Houdaille Industries Inc | Automatic pressure relief and snubbing in hydraulic actuators |
JPS4885096U (fr) * | 1972-01-21 | 1973-10-16 | ||
US3970009A (en) * | 1973-09-24 | 1976-07-20 | Houdaille Industries, Inc. | Fluid railroad passenger car suspension |
JPS5330155B2 (fr) * | 1973-10-02 | 1978-08-25 | ||
US4759186A (en) * | 1985-12-26 | 1988-07-26 | Sundstrand Corporation | Self-powered rotary actuator utilizing rotation-generated centrifugal head |
JPS62201742U (fr) * | 1986-06-16 | 1987-12-23 | ||
JPS6415509A (en) * | 1987-07-09 | 1989-01-19 | Hitachi Metals Ltd | Oscillating actuator |
US5033265A (en) * | 1989-03-08 | 1991-07-23 | Sundstrand Corporation | Coaxial hydraulic actuator system |
US5020826A (en) * | 1989-11-06 | 1991-06-04 | Southwest Research Institute | Vehicle suspension system |
US5100083A (en) * | 1990-02-13 | 1992-03-31 | The Boeing Company | Retractable landing gear with self-braced folding strut |
US5086995A (en) * | 1990-04-09 | 1992-02-11 | The Boeing Company | Aft cantilevered wing landing gear for heavy airplane with aft center of gravity |
JPH0446227A (ja) * | 1990-06-12 | 1992-02-17 | Nhk Spring Co Ltd | 流体式抵抗発生装置 |
JPH05173642A (ja) * | 1991-11-29 | 1993-07-13 | Mitsui Eng & Shipbuild Co Ltd | 自動固定装置 |
RU2085445C1 (ru) * | 1994-05-19 | 1997-07-27 | Владимир Григорьевич Григорьев | Привод уборки и выпуска шасси летательного аппарата |
US6484675B2 (en) * | 2000-02-23 | 2002-11-26 | Delphi Technologies, Inc. | Hydraulic actuator for variable valve mechanism |
GB0515359D0 (en) * | 2005-07-26 | 2005-08-31 | Airbus Uk Ltd | Landing gear |
GB0616730D0 (en) * | 2006-08-23 | 2006-10-04 | Airbus Uk Ltd | Jam-tolerant actuator |
DE202007005133U1 (de) * | 2007-04-04 | 2008-08-14 | Eto Magnetic Gmbh | Elektromagnetische Stellvorrichtung |
DE102008010646A1 (de) * | 2008-02-22 | 2009-08-27 | Schaeffler Kg | Elektromagnetische Stelleinheit für ein hydraulisches Wegeventil |
US8523107B2 (en) * | 2010-03-12 | 2013-09-03 | The Boeing Company | Fuselage mounted landing gear |
-
2010
- 2010-04-15 FR FR1052885A patent/FR2958981B1/fr active Active
-
2011
- 2011-04-15 CN CN201180019153.5A patent/CN102859225B/zh active Active
- 2011-04-15 EP EP11714333.9A patent/EP2558742B1/fr active Active
- 2011-04-15 RU RU2012148457/11A patent/RU2520676C1/ru not_active IP Right Cessation
- 2011-04-15 CA CA2796260A patent/CA2796260C/fr active Active
- 2011-04-15 US US13/640,809 patent/US9056672B2/en not_active Expired - Fee Related
- 2011-04-15 WO PCT/EP2011/056042 patent/WO2011128441A1/fr active Application Filing
- 2011-04-15 BR BR112012025987A patent/BR112012025987A2/pt not_active IP Right Cessation
- 2011-04-15 JP JP2013504292A patent/JP5443652B2/ja not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2429425A (en) * | 1942-09-24 | 1947-10-21 | Bendix Aviat Corp | Driving mechanism |
DE19849756A1 (de) * | 1998-10-28 | 2000-05-11 | Netzsch Mohnopumpen Gmbh | Antriebskopf für ein drehantreibbares Gestänge, insbes. zum Antreiben einer Bohrlochpumpe |
DE102005061364A1 (de) * | 2005-12-21 | 2007-07-05 | Alexander Von Gencsy | Vorrichtung zur Notabsenkung |
Also Published As
Publication number | Publication date |
---|---|
EP2558742A1 (fr) | 2013-02-20 |
BR112012025987A2 (pt) | 2016-06-28 |
CN102859225B (zh) | 2015-10-07 |
FR2958981A1 (fr) | 2011-10-21 |
CA2796260A1 (fr) | 2011-10-20 |
JP2013524135A (ja) | 2013-06-17 |
CN102859225A (zh) | 2013-01-02 |
CA2796260C (fr) | 2014-10-21 |
US9056672B2 (en) | 2015-06-16 |
US20130092482A1 (en) | 2013-04-18 |
FR2958981B1 (fr) | 2012-08-24 |
JP5443652B2 (ja) | 2014-03-19 |
RU2520676C1 (ru) | 2014-06-27 |
RU2012148457A (ru) | 2014-05-20 |
EP2558742B1 (fr) | 2016-03-16 |
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