WO2009020452A1 - Ensemble actionneur tolérant aux pannes, et procédé de déplacement d'un élément par rapport à un support - Google Patents

Ensemble actionneur tolérant aux pannes, et procédé de déplacement d'un élément par rapport à un support Download PDF

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Publication number
WO2009020452A1
WO2009020452A1 PCT/US2007/017595 US2007017595W WO2009020452A1 WO 2009020452 A1 WO2009020452 A1 WO 2009020452A1 US 2007017595 W US2007017595 W US 2007017595W WO 2009020452 A1 WO2009020452 A1 WO 2009020452A1
Authority
WO
WIPO (PCT)
Prior art keywords
support
actuators
actuator
fault
relative
Prior art date
Application number
PCT/US2007/017595
Other languages
English (en)
Inventor
John D. Kopp
Original Assignee
Moog Inc.
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 Moog Inc. filed Critical Moog Inc.
Priority to PCT/US2007/017595 priority Critical patent/WO2009020452A1/fr
Publication of WO2009020452A1 publication Critical patent/WO2009020452A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/02—Mounting or supporting thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/50—Transmitting means with power amplification using electrical energy
    • B64C13/505—Transmitting means with power amplification using electrical energy having duplication or stand-by provisions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/08—Adjustable control surfaces or members, e.g. rudders bodily displaceable

Definitions

  • the present invention relates generally to devices and mechanisms for controllably moving a member relative to a support, and to an improved method of moving such a member relative to a support.
  • the invention has particular utility in providing a fault-tolerant actuator assembly for moving an airfoil surface on an aircraft.
  • An aircraft typically has a number of airfoil surfaces. These include primary surfaces, such as rudders, elevators and ailerons, that are used to cause the aircraft to rotate about its roll, pitch and yaw axes. However, aircraft also include secondary airfoil surfaces, such as flaps, slats, speed brakes and the like.
  • the present invention broadly provides an improved fault-tolerant actuator assembly (20) that is mounted on a support (21) for controllably moving a member (22) relative to the support, and to an improved method of moving a member relative to a support.
  • the improved actuator assembly broadly includes: a first actuator (24) having a first end connected to the support and having a second end arranged for controlled movement relative to its first end and connected to the member at a first location (X 3 -X 3 ); and a second actuator (25) having a first end connected to the support and having a second end arranged for controlled movement relative to its first end and connected to the member at a second location spaced (X 4 -X 4 ) from the first location such that the actuators may be operated either cooperatively or independently to control movement of the member relative to the support.
  • Each of the actuators may be a linear actuator.
  • the first ends of the actuators may be arranged adjacent one another, and may be pivotally connected to the support along a common axis (xj-xi).
  • the second ends of the actuators may be pivotally connected to the member about substantially parallel axes (X3-X 3 , X4-X 4 ).
  • One of the actuators may be extended and the other of the actuators may be retracted to cause the member to move relative to the support.
  • both of the actuators may be extended or retracted to move the member relative to the support.
  • One of the actuators may be operated to cause the member to pivot about the connection of the second end of the other actuator.
  • the member may be an airfoil surface.
  • the improved method broadly includes the steps of: positioning a first actuator (24) to act between the support and the member, the first actuator having a first end connected to the support and having a second end arranged for controlled movement relative to its first end and connected to the member at a first location; positioning a second actuator (25) to act between the support and the member, the second actuator having a first end connected to the support and having a second end arranged for controlled movement relative to its first end and connected to the member at a second location spaced from the first location; and operating the actuators either cooperatively or independently to control movement of the member relative to the support.
  • one of the actuators may be extended and the other of the actuators may be retracted to cause the member to move relative to the support.
  • both of the actuators may be extended or retracted to move the member relative to the support.
  • One of the actuators may be operated to cause the member to pivot about the connection of the second end of the other actuator.
  • the general object of the invention is to provide an improved fault- tolerant actuator assembly.
  • Another object is to provide an improved method of moving a member relative to a support.
  • Fig. 1 is a schematic side elevation of the improved actuator assembly in association with an airfoil surface and a support.
  • Fig. 2 is a right end elevation of the structure shown in Fig. 1, with the support removed for clarity of illustration.
  • FIG. 3 is left end elevation of the structure shown in Fig. 1, with the support removed for clarity of illustration.
  • Fig. 4 is a top plan view of the structure shown in Fig. 1, with the support removed for clarity of illustration.
  • Fig. 5 is a bottom plan view of the actuator assembly shown in Fig. 1, with the support removed.
  • Fig. 6 is a view generally similar to Fig. 1, but with both actuators fully extended.
  • Fig. 7 is a view generally similar to Fig. 1, with both actuators fully retracted.
  • Fig. 8 is a view generally similar to Fig. 1, but showing one actuator as having been partially retracted and the other actuator as having been fully extended, to cause the member to pivot relative to the support.
  • Fig. 9 is a view generally similar to Fig. 1, with one actuator fiilly retracted and the other partially extended to cause the member to pivot about its connection with the retracted actuator.
  • Fig. 10 is a view generally similar to Fig. 1, showing one of the actuators as having failed in an intermediate position, with the other actuator causing the member to pivot about its connection with the failed actuator.
  • Fig. 11 is a view generally similar to Fig. 1, showing one of the actuators as having failed in its extended position, and the other actuator causing the member to pivot about its connection with the failed actuator.
  • the terms “horizontal”, “vertical”, “left”, “right”, “up” and “down”, as well as adjectival and adverbial derivatives thereof simply refer to the orientation of the illustrated structure as the particular drawing figure faces the reader.
  • the terms “inwardly” and “outwardly” generally refer to the orientation of a surface relative to its axis of elongation, or axis of rotation, as appropriate.
  • the present invention broadly provides an improved fault-tolerant actuator assembly that is mounted on a support for controllably moving a member relative to the support, and to an improved method of moving a member relative to a support.
  • the improved fault-tolerant actuator assembly is generally indicated at 20.
  • the improved actuator assembly is shown as being mounted on a support, schematically indicated at 21 in Fig. 1, for controllably moving a member, such as an airfoil surface, schematically indicated at 22, relative to the support.
  • a member such as an airfoil surface
  • the support has been omitted from Figs. 2-5 in order to more clearly illustrate the structure that is connected to the support. Persons skilled in this art will readily appreciate that this omission is simply for clarity of illustration.
  • the improved actuator is shown as broadly including a bracket member, generally indicated at 23, mounted on the support, a first actuator 24 and a second actuator 25.
  • the airfoil surface 22 is schematically shown as presenting a substantially rectangular outline, when viewed in top or bottom plan, and as having a substantially triangular side elevation. More particularly, the airfoil surface is a vertically-thickened left marginal end portion, which progressively tapers down to a thin right marginal end portion 26. As previously indicated, this representation of airfoil 22 is schematic only, and is simply used to depict the principle of the invention. The actual shape of such an airfoil surface might readily be changed as desired.
  • the first and second actuators are shown as being linear actuators. They may be identical, or different, as desired.
  • the actuators, or either of them, may be hydraulic, pneumatic, electro-hydraulic, electro -mechanical (e.g., a ball screw, etc.), direct-drive electromechanical actuators, or yet some other form.
  • the actuators are depicted as being hydraulic actuators having a piston (not shown) slidably mounted within a cylinder 28.
  • a rod 29 is connected to the piston, and is selectively extendable or retractable relative to the cylinder in the well-known manner.
  • Each of the cylinders has a leftward or first end pivotally connected to the bracket. These two actuators are horizontally spaced from one another, and their left ends are pivotally connected to the bracket along common axis xj-xi- The bracket is pivotally connected to the support along pivotally axis X 2 -X2-
  • the second or extensible ends of the two actuators are connected to the airfoil surface at different locations. More particularly, the movable end of first actuator 24 is pivotally connected to the airfoil surface along axis X 3 -X 3 . Similarly, the extendable end of second actuator is connected pivotally connected to the airfoil surface along pivotal axis X 4 -X 4 . Axes X 3 -X 3 and X4-X4 are substantially parallel to one another but are vertically spaced, as shown in Fig. 1.
  • the actuators also include suitable means (not shown) for selectively extending and retracting rods 29, 29 relative to their associated cylinders, in the well-known manner.
  • the two actuators may be operated either cooperatively or independently to control movement of the member, as schematically shown in Figs. 6-10.
  • Fig. 6 is a view showing both of the actuators having been simultaneously extended
  • Fig. 7 is a view showing both of the actuators as having been simultaneously retracted. This type of arrangement would be useful in selectively extending or retracting a flap, or a slat.
  • Fig. 8 is a schematic view showing the actuators as having been operated in a push- pull mode to selectively pivot the airfoil surface.
  • first actuator 24 has been slightly retracted
  • second actuator 25 has been slightly extended, to cause the airfoil system to pivot.
  • This push-pull mode of operation would be particularly useful in selectively displacing the airfoil surface against an air stream.
  • Fig. 9 schematically illustrates a situation where second actuator 25 has failed in its fully-retracted position. The other actuator is then selectively operable to pivot the airfoil surface about axis
  • Fig. 10 is a schematic view of the second actuator as having failed at an intermediate position, with the first actuator being operated to cause the airfoil surface to again pivot about axis X 4 -X 4 .
  • Fig. 1 1 is a schematic view of the first actuator being in its fully-extended position, either by design or by failure, with the second actuator being used to again cause the airfoil surface to pivot about axis X 4 -X 4 .
  • the first actuator might be used to cause the airfoil surface to pivot about axis X3-X3.
  • the best invention provides an improved fault-tolerant actuator assembly 20 that is mounted on a support 21 for controllably moving a member 22 relative to that support.
  • the improved actuator assembly broadly includes a first actuator having a first end connected to the support and having a second end arranged for controlled movement relative to the first end and connected to the member at a first location (X 3 -X 3 ); and a second actuator having a first end connected to the support and having a second end arranged for controlled movement relative to its first end and connected to the member at a second location (X 4 -X 4 ) spaced from the first location; such that the actuators may be operated either cooperatively or independently to control movement of the member relative to the support.
  • the invention also provides an improved method of moving a member relative to a support, which method broadly includes the steps of: positioning a first actuator to act between the support and the member, the first actuator having a first end connected to the support and having a second end arranged for controlled movement relative to its first end connected to the member at a first location; positioning a second actuator to act between the support and the member, the second actuator having a first end connected to the support and having a second end arranged for controlled movement relative to its first end and connected to the member at a second location spaced from the first location; and operating the actuators either cooperatively or independently to control movement of the member relative to the support.
  • the present invention contemplates that many changes and modifications may be made.
  • the means or manner by which the actuators are connected to the support may be either then in the form illustrated in the accompanying drawings.
  • the actuators may be mechanical, electro-mechanical, electro- hydraulic, hydraulic-pneumatic, or some other form.
  • the member may be an airfoil surface, or may be some other form of member. Accordingly, the invention is not limited to use with an aircraft, but is of general utility. [0053] Therefore, while the preferred form of the improved actuator assembly and method have been shown and described, and several modifications and changes thereof discussed, persons skilled in this art will readily appreciate that various additional changes and modifi- cations may be made without departing from the spirit of the invention, as defined by differentiated by the following claims.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Transmission Devices (AREA)
  • Actuator (AREA)

Abstract

L'ensemble actionneur tolérant aux pannes (20) selon l'invention est monté sur un support (21) pour déplacer de façon contrôlable un élément (22) par rapport au support. Cet ensemble actionneur comprend un premier actionneur (24) doté d'une première extrémité raccordée au support et d'une seconde extrémité disposée pour un déplacement contrôlé par rapport à sa première extrémité et raccordée à l'élément à un premier emplacement (x3- x3) ; et un second actionneur (25) doté d'une première extrémité raccordée au support et d'une seconde extrémité disposée pour un déplacement contrôlé par rapport à la première extrémité et raccordée à l'élément à un second emplacement (x4-x4) faisant face au premier emplacement ; de telle sorte que les actionneurs peuvent être activés, soit conjointement, soit indépendamment, pour contrôler le déplacement de l'élément par rapport au support.
PCT/US2007/017595 2007-08-08 2007-08-08 Ensemble actionneur tolérant aux pannes, et procédé de déplacement d'un élément par rapport à un support WO2009020452A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2007/017595 WO2009020452A1 (fr) 2007-08-08 2007-08-08 Ensemble actionneur tolérant aux pannes, et procédé de déplacement d'un élément par rapport à un support

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2007/017595 WO2009020452A1 (fr) 2007-08-08 2007-08-08 Ensemble actionneur tolérant aux pannes, et procédé de déplacement d'un élément par rapport à un support

Publications (1)

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WO2009020452A1 true WO2009020452A1 (fr) 2009-02-12

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2460721A1 (fr) * 2010-12-03 2012-06-06 EADS Deutschland GmbH Transmission d'une force de commande
DE102011118321A1 (de) * 2011-11-11 2013-05-16 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
US20130327887A1 (en) * 2010-05-26 2013-12-12 Airbus Operations Gmbh Device for an adjustable flap of a wing
JP2015506876A (ja) * 2012-02-09 2015-03-05 ムーグ インコーポレーテッド アクチュエータ・システム及び方法
DE102010024121B4 (de) * 2010-06-17 2017-04-06 Airbus Defence and Space GmbH Stellantriebseinheit
US10753444B2 (en) 2016-01-13 2020-08-25 Moog Inc. Summing and fault tolerant rotary actuator assembly
US11104422B1 (en) * 2020-02-07 2021-08-31 The Boeing Company Compact and redundant method for powering flight control surface from within fuselage
US11235862B2 (en) * 2017-07-18 2022-02-01 Kawasaki Jukogyo Kabushiki Kaisha Aircraft flight control system including electromechanical actuator

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1935004A (en) * 1932-10-21 1933-11-14 Jr Simon Peter Winther Hydraulic aeroplane control
US2863321A (en) * 1957-11-04 1958-12-09 Boeing Co Torque transmitting mechanism
US2972898A (en) * 1959-05-26 1961-02-28 Cleveland Pneumatic Ind Inc Actuation mechanism
WO1999015403A2 (fr) * 1997-09-25 1999-04-01 Northrop Grumman Corporation Volet de bord d'attaque extensible
EP1721826A1 (fr) * 2005-05-11 2006-11-15 Honeywell International Inc. Système d'actionnement d'une surface de commande de vol avec comandes configurés avec redondance

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1935004A (en) * 1932-10-21 1933-11-14 Jr Simon Peter Winther Hydraulic aeroplane control
US2863321A (en) * 1957-11-04 1958-12-09 Boeing Co Torque transmitting mechanism
US2972898A (en) * 1959-05-26 1961-02-28 Cleveland Pneumatic Ind Inc Actuation mechanism
WO1999015403A2 (fr) * 1997-09-25 1999-04-01 Northrop Grumman Corporation Volet de bord d'attaque extensible
EP1721826A1 (fr) * 2005-05-11 2006-11-15 Honeywell International Inc. Système d'actionnement d'une surface de commande de vol avec comandes configurés avec redondance

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9573676B2 (en) * 2010-05-26 2017-02-21 Airbus Operations Gmbh Device for an adjustable flap of a wing
US20130327887A1 (en) * 2010-05-26 2013-12-12 Airbus Operations Gmbh Device for an adjustable flap of a wing
DE102010024121B4 (de) * 2010-06-17 2017-04-06 Airbus Defence and Space GmbH Stellantriebseinheit
DE102010053396B4 (de) * 2010-12-03 2014-12-24 Airbus Defence and Space GmbH Übertragung einer Steuerungskraft
EP2460721A1 (fr) * 2010-12-03 2012-06-06 EADS Deutschland GmbH Transmission d'une force de commande
DE102011118321A1 (de) * 2011-11-11 2013-05-16 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
DE102011118321B4 (de) 2011-11-11 2023-01-19 Liebherr-Aerospace Lindenberg Gmbh Hydraulischer Rotationsantrieb
JP2015506876A (ja) * 2012-02-09 2015-03-05 ムーグ インコーポレーテッド アクチュエータ・システム及び方法
KR101842235B1 (ko) * 2012-02-09 2018-03-27 무그 인코포레이티드 액츄에이터 시스템 및 방법
US10281033B2 (en) 2012-02-09 2019-05-07 Moog Inc. Multiple actuator and linkage system
US11248698B2 (en) 2012-02-09 2022-02-15 Moog Inc. Multiple actuator and linkage system
US10753444B2 (en) 2016-01-13 2020-08-25 Moog Inc. Summing and fault tolerant rotary actuator assembly
US11235862B2 (en) * 2017-07-18 2022-02-01 Kawasaki Jukogyo Kabushiki Kaisha Aircraft flight control system including electromechanical actuator
US11104422B1 (en) * 2020-02-07 2021-08-31 The Boeing Company Compact and redundant method for powering flight control surface from within fuselage

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