EP2193594A2 - Actionneur lineaire telescopique double action a systeme d'entraînement a moteur unique - Google Patents

Actionneur lineaire telescopique double action a systeme d'entraînement a moteur unique

Info

Publication number
EP2193594A2
EP2193594A2 EP08845602A EP08845602A EP2193594A2 EP 2193594 A2 EP2193594 A2 EP 2193594A2 EP 08845602 A EP08845602 A EP 08845602A EP 08845602 A EP08845602 A EP 08845602A EP 2193594 A2 EP2193594 A2 EP 2193594A2
Authority
EP
European Patent Office
Prior art keywords
rod
drive
translation
output shaft
intended
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.)
Withdrawn
Application number
EP08845602A
Other languages
German (de)
English (en)
French (fr)
Inventor
Pierre André Marcel Baudu
Guy Bernar Vauchel
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.)
Safran Nacelles SAS
Original Assignee
Aircelle 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.)
Filing date
Publication date
Application filed by Aircelle SA filed Critical Aircelle SA
Publication of EP2193594A2 publication Critical patent/EP2193594A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/06—Means for converting reciprocating motion into rotary motion or vice versa
    • 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
    • Y10T74/00—Machine element or mechanism
    • Y10T74/18—Mechanical movements
    • Y10T74/18568—Reciprocating or oscillating to or from alternating rotary
    • 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
    • Y10T74/00—Machine element or mechanism
    • Y10T74/18—Mechanical movements
    • Y10T74/18568—Reciprocating or oscillating to or from alternating rotary
    • Y10T74/18576—Reciprocating or oscillating to or from alternating rotary including screw and nut
    • Y10T74/18672—Plural screws in series [e.g., telescoping, etc.]

Definitions

  • the present invention relates to a drive system for a double action telescopic linear actuator intended to allow the displacement of a first and a second element relative to a fixed element, these three elements belonging in particular to a thrust reverser for turbojet engine nacelle as described for example in the French patent application not yet published and registered under No. 06.05512 in the name of the applicant.
  • An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.
  • These ancillary actuating devices comprise in particular a mechanical system for actuating thrust reversers.
  • a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing a thrust reverser means and intended to surround the combustion chamber of the turbojet engine. , and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • the modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle.
  • the two air flows are ejected from the turbojet engine from the rear of the nacelle.
  • the role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine.
  • the inverter obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
  • the means implemented to achieve this reorientation of the cold flow vary according to the type of inverter.
  • an inverter comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a position retraction in which they close this passage.
  • These covers can perform a deflection function or simply activation other means of deflection.
  • a grid inverter also known as a cascade inverter
  • the reorientation of the air flow is carried out by deflection grids, the hood having only a simple sliding function aimed at discover or cover these grids, the translation of the movable hood being effected along a longitudinal axis substantially parallel to the axis of the nacelle.
  • Additional locking doors activated by the sliding of the cowling, generally allow a closure of the vein downstream of the grids so as to optimize the reorientation of the cold flow.
  • the sliding cowl belongs to the rear section and has a downstream side forming an ejection nozzle for channeling the ejection of the air flows.
  • This nozzle can come in addition to a primary nozzle channeling the hot flow and is then called secondary nozzle.
  • Document FR 06.05512 addresses the problems of adapting the section of the nozzle to the various flight phases encountered, in particular the take-off and landing phases of the aircraft.
  • a thrust reverser comprising, on the one hand, deflection grids 1 1 of at least a portion of an air flow of the turbojet engine, and secondly, at least one cover 10 movable in translation in a substantially longitudinal direction of the nacelle adapted to pass alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle and covers the deflection grids 1 1 , at an open position in which it opens a passage in the nacelle and discovers the deflection grids 1 1.
  • the movable cover 10 comprises an outer portion 10a and an inner portion 10b mounted each movable in translation and connected to a telescopic actuating jack 30 adapted to allow their longitudinal translation (see Figure 2).
  • the outer part 10a (downstream side of the cover 10) forms an exhaust nozzle for channeling the ejection of the air flows.
  • the movable cowl 10 By dividing the movable cowl 10 into an inner portion 10b and an outer portion 10a movable at least partially independently of one another, it is possible to adapt to the flight conditions the relative positions of the outer portion 10a and of the inner portion 10b so as to vary the section of the ejection nozzle formed by the movable cowl 10 by varying the length of the inner aerodynamic line of the movable cowl 10, both when the movable cowl 10 is in position closing and covers the deflection grids 1 1, and when the movable cover 10 is in the open position.
  • the telescopic ram 30 has a first rod 30b for moving the inner portion 10b and a second rod 30a slidably mounted in the first rod 30b to displace the hood outer portion 10a.
  • the attachment of the inner portion 10b to the first rod 30b is formed by means of oblong eyelets 32 disposed on either side of the rod 30b, so as to reduce the overhang of the point of attachment and avoid any hyperstaticity constraint in the alignment of the three points of attachment of the jack 30 to the fixed front frame and to the outer portions 10a and 10b of the inner movable cowl.
  • a double-acting electric jack generally has operating difficulties. Indeed, the second rod being movable relative to the base of the cylinder, it is difficult to group the actuating means in said base of the cylinder and the second rod must generally be equipped with its own motor, which will also be mobile.
  • a telescopic linear actuator for moving a first and a second element relative to a fixed element, comprising a base, intended to be attached to the fixed element, and serving as a housing for a first rod locked in rotation.
  • first rod being intended to be attached by one end to the first element to be displaced, the first rod supporting a second rod disposed in the extension thereof and intended to be attached by one end to the second element to move, said second rod being adapted to be locked in rotation and driven in translation through a second shaft passing through the base and connected to rotational drive means
  • Such an arrangement allows to group the actuating means of the two rods of the actuator in the base of the latter.
  • the present invention aims to provide a simple and reliable actuating system for actuating the two rods by a single motor.
  • this drive system must allow a control of the moving parts in accordance with the aeronautical application envisaged, namely that a variable nozzle section is generally controlled when the thrust reverser is locked in the closed position, the variable nozzle being reciprocally in a maximum deployment position when the thrust reverser is deployed.
  • the present invention relates to a telescopic linear actuator for moving a first and a second element relative to a fixed element, comprising a base, intended to be attached to the fixed element, and serving as housing for a first rod.
  • the rod drive means comprise a motor adapted to drive an input shaft of at least one differential, said differential having, on the one hand, a first output shaft connected to one of the first or second drive shafts, and on the other hand, a second output shaft connected in turn to the second or first drive shaft.
  • Differential means any mechanical means for distributing a drive speed to a plurality of output axes by distribution of the kinematic force.
  • the output shafts of the differential are associated with independent rotational locking means.
  • Such a configuration makes it possible to control the movements of one or the other of the movable parts that can be controlled by the locking or braking of the shafts.
  • the locking in rotation of at least one output shaft is obtained by locking in translation of the corresponding rod.
  • the blocking of the shafts can be advantageously obtained by locking the rods with the locking means specific to the latter.
  • the movable cowl is associated with three bolts ensuring its closed position or opening. These locks then also allow locking in rotation of the shaft, even indirectly.
  • At least one output shaft comprises at least one reduction stage.
  • At least one output shaft is equipped with manual drive means.
  • the two output shafts are concentric.
  • the differential is in the form of an epicyclic gear train.
  • the present invention also relates to a thrust reverser for a turbojet engine nacelle comprising, on the one hand, means for deflecting at least a portion of an air flow of the turbojet, and secondly, at least one movable cowl in translation in a direction substantially parallel to a longitudinal axis of the nacelle adapted to pass alternately a closing position in which it ensures the aerodynamic continuity of the nacelle and covers the deflection means, at an open position in which it opens a passage in the nacelle and discovers the deflection means, the movable cowl comprising at least one end portion forming a nozzle said portion being mounted movable in translation relative to the remainder of the cover, characterized in that it also comprises an actuator according to the invention for moving the movable cover and the nozzle.
  • FIG. 1 is a schematic partial view in longitudinal section of a thrust reverser according to the prior art, equipped with a movable cowl separated into an inner part and an outer part movable relative to the 'other.
  • FIG. 2 represents a telescopic jack actuating the inner and outer bonnet parts of the pneumatic or hydraulic type according to the prior art for actuating the thrust reverser forming a variable nozzle of FIG.
  • FIG. 3 schematically represents an example of a double action telescopic linear actuator, applicable to a thrust reverser of the type illustrated in FIGS. 1 and 2 for the displacement of the inner and outer parts of its movable cowl.
  • FIG. 4 is a representation of the actuator of FIG. 3 equipped with a differential drive system according to the invention.
  • the telescopic linear actuator illustrated in FIG. 3 is intended to allow a first element to be displaced - here, the internal hood portion 10b of FIGS. 1 and 2 - and a second element - here, the hood outer part 10a - relative to a fixed element, here a fixed front frame 102 of the thrust reverser.
  • the actuator comprises a base 101 of generally tubular shape, intended to be attached to the fixed front frame 102 by a cardan 103.
  • a tubular tube 106 forming a first rod of the telescopic actuator, designed to be attached at one end, by a gimbal 108, to the inner part 10b, is mounted to be movable in axial translation but locked in rotation by the gimbal 108.
  • driving screw 104 of ball screw type is rotatably mounted in the tube 106 that it drives in translation.
  • First motorized electrical drive means 107 are provided for rotating the drive screw 104 so as to deploy the tube 106 out of the base 101 or retract it into the latter.
  • a tubular slide 1 1 1 is rotatably mounted in the drive screw 104.
  • a first rod 1 12, linked in axial translation with the sheath 106, is mounted to move in axial translation in the tubular slide 1 1 1.
  • Second motorized electric drive means 1 13 are provided for rotating the slide 1 1 1.
  • the drive means comprise a single electric motor M adapted to drive an axis 210 constituting an input axis of an epicyclic gear train 206.
  • the rotational movement animating the input axis 210 is then distributed by the epicyclic gear train, on the one hand, to a first output shaft 203 linked to the first drive shaft 104, and on the other hand, to a second output shaft 207 via planetary gear 204, the second output shaft 207 being adapted to drive the sleeve 1 1 1, possibly via a reduction stage.
  • the epicyclic gear train 206 also incorporates manual drive means 221, 222 for driving, possibly by connecting an external electric motor or a suitable tool, respectively the first output shaft 203, and the second output shaft. output 207.
  • the drive movement of the input shaft 210 by the motor M rotates the epicyclic gear train 206 which remains integral with the sun gear 204 (these are also locked in rotation due to the locking of the second output shaft), the set of planetary gear 204 then driving the first shaft 203 whose rotational movement is transmitted to the first drive shaft 204 and transformed as previously explained in translation movement of the mobile A.
  • the manual opening substantially follows the same operation, the output shaft of which The drive is not desired being locked in rotation.
  • the drive system according to the invention has the advantage of allowing the displacement of one or the other mobile A, B by a single motor and a single control, the displacement depending solely on maintaining the locked position mobile B, A opponent.
  • the blocking of mobile A, B will be mainly by locks usually integral, for security reasons, these devices.
  • a movable cowl 10 is necessary associated with three locking systems.
  • the variable nozzle system also has internal stops limiting the translation of the nozzle.
  • the loss of the displacement function of the mobile A involves the return to the locked position of the mobile B, typically the nozzle.
  • the motor M will first cause the deployment or return of the mobile B to one of its race stops.
  • actuators according to the invention are particularly intended to actuate the parts of a thrust reverser cover.
  • actuators depending on the size of the cover to move, it may be necessary to use one or more actuators.
  • the synchronization of the two rods with the other actuators can be performed by electrical synchronization between the different motors.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Transmission Devices (AREA)
  • Retarders (AREA)
EP08845602A 2007-10-04 2008-08-20 Actionneur lineaire telescopique double action a systeme d'entraînement a moteur unique Withdrawn EP2193594A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0706964A FR2922059B1 (fr) 2007-10-04 2007-10-04 Actionneur lineaire telescopique double action a systeme d'entrainement a moteur unique
PCT/FR2008/001201 WO2009056713A2 (fr) 2007-10-04 2008-08-20 Actionneur lineaire telescopique double action a systeme d'entraînement a moteur unique

Publications (1)

Publication Number Publication Date
EP2193594A2 true EP2193594A2 (fr) 2010-06-09

Family

ID=39577556

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08845602A Withdrawn EP2193594A2 (fr) 2007-10-04 2008-08-20 Actionneur lineaire telescopique double action a systeme d'entraînement a moteur unique

Country Status (8)

Country Link
US (1) US8931253B2 (zh)
EP (1) EP2193594A2 (zh)
CN (1) CN101809849B (zh)
BR (1) BRPI0817588A2 (zh)
CA (1) CA2700085A1 (zh)
FR (1) FR2922059B1 (zh)
RU (1) RU2472272C2 (zh)
WO (1) WO2009056713A2 (zh)

Families Citing this family (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9759087B2 (en) 2007-08-08 2017-09-12 Rohr, Inc. Translating variable area fan nozzle providing an upstream bypass flow exit
CN101939528B (zh) 2007-08-08 2013-07-24 罗尔股份有限公司 具有旁通流的面积可调风扇喷嘴
FR2920204B1 (fr) * 2007-08-20 2009-10-30 Aircelle Sa Procede et systeme de commande d'au moins un actionneur de capots d'un inverseur de poussee pour turboreacteur
FR2922059B1 (fr) * 2007-10-04 2014-07-04 Aircelle Sa Actionneur lineaire telescopique double action a systeme d'entrainement a moteur unique
FR2922058B1 (fr) * 2007-10-04 2009-12-04 Aircelle Sa Actionneur lineaire telescopique pour deplacer un premier et un second elements relativement a un element fixe
FR2945680B1 (fr) * 2009-05-15 2016-01-22 Snecma Actionneur lineaire electromecanique pour turbomachine
EP2278146B1 (en) * 2009-06-16 2013-07-24 Rohr, Inc. Actuation system for a translating variable area fan nozzle
IT1399971B1 (it) * 2010-03-31 2013-05-09 Modelway S R L Sistemi di attuazione dei comandi per il volo di un profilo alare di potenza per la conversione di energia eolica in energia elettrica o meccanica
FR2958979B1 (fr) 2010-04-20 2012-03-16 Aircelle Sa Systeme de commande de type hydraulique pour dispositif d'inversion de poussee
FR2958910B1 (fr) * 2010-04-20 2012-04-27 Aircelle Sa Nacelle pour moteur d'aeronef a tuyere de section variable
US8875486B2 (en) 2010-05-17 2014-11-04 Rohr, Inc. Guide system for nacelle assembly
FR2960917B1 (fr) 2010-06-03 2012-05-18 Aircelle Sa Inverseur de poussee a section de tuyere variable verrouillable
US8511973B2 (en) 2010-06-23 2013-08-20 Rohr, Inc. Guide system for nacelle assembly
FR2964703B1 (fr) * 2010-09-13 2012-08-24 Aircelle Sa Dispositif de verrouillage/deverrouillage pour inverseur de poussee a capot coulissant et a tuyere adaptative pour nacelle de moteur d'aeronef
FR2966434B1 (fr) 2010-10-21 2013-05-31 Sagem Defense Securite Systeme d'actionnement pour un ensemble de propulsion d'un avion
US9416751B2 (en) * 2010-12-07 2016-08-16 Hamilton Sundstrand Corporation Actuation system
CN102672514B (zh) * 2011-03-09 2016-01-20 汪涛 一种同心差动的两个轴组成的合成进给机构
CN102720820A (zh) * 2011-03-30 2012-10-10 张维国 轮椅调差差速器
FR2978516B1 (fr) * 2011-07-29 2013-08-02 Aircelle Sa Actionneur lineaire double action
US9581109B1 (en) * 2013-04-11 2017-02-28 Geoffrey P. Pinto Axially translating and radially tilting fan nozzle segments with combined actuation and position sensing
US10040563B1 (en) * 2013-04-11 2018-08-07 Geoffrey P. Pinto Dual panel actuator system for jet engines
FR3008741B1 (fr) * 2013-07-17 2017-04-28 Aircelle Sa Systeme inverseur de poussee electrique pour nacelle de moteur d'aeronef et nacelle de moteur d'aeronef ainsi equipee
FR3010456B1 (fr) 2013-09-09 2015-09-11 Sagem Defense Securite Dispositif d'entrainement d'actionneurs pour inverseur de poussee comprenant une unite d'entrainement manuel debrayable
US9765867B2 (en) * 2014-04-23 2017-09-19 Nabtesco Corporation Electromechanical actuator
DE102014219068B4 (de) * 2014-09-22 2021-02-18 Premium Aerotec Gmbh Fluggasturbinenschubumkehrvorrichtung mit Führungselementen
US10473057B2 (en) 2015-12-14 2019-11-12 Rohr, Inc. Thrust reverser system with translating elements
US9976696B2 (en) 2016-06-21 2018-05-22 Rohr, Inc. Linear actuator with multi-degree of freedom mounting structure
EP3282132B1 (en) * 2016-08-08 2019-10-02 Goodrich Actuation Systems Limited Actuator with a coupling
US10731738B2 (en) 2017-11-27 2020-08-04 Rohr, Inc. Kinematic system with motion control device
EP3572659B1 (en) 2018-05-25 2024-09-25 Goodrich Actuation Systems Limited Thrust reverser actuation system
US10816070B2 (en) 2018-09-26 2020-10-27 Woodward, Inc. Geared rotary power distribution unit with mechanical differential gearing for multiple actuator systems
FI129927B (en) * 2021-10-28 2022-11-15 Motiomax Oy Electromechanical system
US11788490B1 (en) * 2022-12-05 2023-10-17 Woodward, Inc. Traveling finger lock for an actuator
CN117850126B (zh) * 2024-03-04 2024-05-10 杭州方千科技有限公司 一种可伸缩、旋转的切换机构及氙气爆闪补光装置

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3829020A (en) * 1973-06-13 1974-08-13 Boeing Co Translating sleeve variable area nozzle and thrust reverser
US4521707A (en) * 1983-12-12 1985-06-04 The Boeing Company Triple redundant electromechanical linear actuator and method
US5144851A (en) * 1991-08-01 1992-09-08 Sundstrand Corp. Jam tolerant linear actuator
US5313852A (en) * 1992-11-06 1994-05-24 Grumman Aerospace Corporation Differential linear actuator
US5778659A (en) * 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
FR2755730B1 (fr) * 1996-11-14 1999-01-08 Hispano Suiza Sa Systeme de commande electrique pour inverseur de poussee de turboreacteur
FR2760047B1 (fr) * 1997-02-27 1999-05-07 Hispano Suiza Sa Inverseur de poussee de turboreacteur a portes associees a un dispositif de synchronisation de commande
GB9923116D0 (en) * 1999-10-01 1999-12-01 Franksson Gretar Linear actuator
US6584763B2 (en) * 2001-08-01 2003-07-01 Rohr, Inc. Lock for the translating sleeve of a turbofan engine thrust reverser
RU2215168C2 (ru) * 2001-10-25 2003-10-27 Открытое акционерное общество "Авиадвигатель" Реверсивное устройство наружного контура газотурбинного двигателя
US6684623B2 (en) * 2002-02-27 2004-02-03 Honeywell International, Inc. Gearless electric thrust reverser actuators and actuation system incorporating same
RU2265147C1 (ru) * 2004-03-15 2005-11-27 Московский авиационный институт (государственный технический университет) Исполнительный механизм на основе волновой передачи поступательного действия
UA78810C2 (en) * 2005-01-24 2007-04-25 State Entpr Zaporizhia Academi Appliance for reversing propulsion of two-contour turbo-jet engine
US20060266146A1 (en) * 2005-05-31 2006-11-30 Waide William M Direct drive electromechanical linear actuators
FR2895483B1 (fr) * 2005-12-23 2008-10-24 Messier Bugatti Sa Actionneur telescopique a tige principale et tige auxiliaire, et procede faisant application
FR2895482B1 (fr) * 2005-12-23 2008-10-24 Messier Bugatti Sa Actionneur telescopique a tige principale et tige auxiliaire et procede faisant application
GB0604131D0 (en) * 2006-03-01 2006-04-12 Airbus Uk Ltd Jam-tolerant actuator
FR2902839B1 (fr) * 2006-06-21 2011-09-30 Aircelle Sa Inverseur de poussee formant une tuyere adaptative
FR2917788B1 (fr) * 2007-06-19 2009-07-24 Aircelle Sa Actionneur double action a effet programme
CN101939528B (zh) * 2007-08-08 2013-07-24 罗尔股份有限公司 具有旁通流的面积可调风扇喷嘴
FR2922058B1 (fr) * 2007-10-04 2009-12-04 Aircelle Sa Actionneur lineaire telescopique pour deplacer un premier et un second elements relativement a un element fixe
FR2922059B1 (fr) * 2007-10-04 2014-07-04 Aircelle Sa Actionneur lineaire telescopique double action a systeme d'entrainement a moteur unique
GB0818701D0 (en) * 2008-10-13 2008-11-19 Goodrich Actuation Systems Ltd Actuator
FR2946696B1 (fr) * 2009-06-10 2012-04-20 Aircelle Sa Dispositif d'inversion de poussee

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009056713A2 *

Also Published As

Publication number Publication date
WO2009056713A2 (fr) 2009-05-07
US8931253B2 (en) 2015-01-13
CN101809849A (zh) 2010-08-18
US20100205931A1 (en) 2010-08-19
FR2922059A1 (fr) 2009-04-10
CA2700085A1 (fr) 2009-05-07
CN101809849B (zh) 2012-06-13
RU2010117009A (ru) 2011-11-10
BRPI0817588A2 (pt) 2015-03-31
RU2472272C2 (ru) 2013-01-10
FR2922059B1 (fr) 2014-07-04
WO2009056713A3 (fr) 2010-02-18

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