WO1996009955A1 - Timonerie pour le deploiement d'une surface par rapport a une aile - Google Patents

Timonerie pour le deploiement d'une surface par rapport a une aile Download PDF

Info

Publication number
WO1996009955A1
WO1996009955A1 PCT/NZ1995/000096 NZ9500096W WO9609955A1 WO 1996009955 A1 WO1996009955 A1 WO 1996009955A1 NZ 9500096 W NZ9500096 W NZ 9500096W WO 9609955 A1 WO9609955 A1 WO 9609955A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
slat
flap
linkage mechanism
moveable surface
Prior art date
Application number
PCT/NZ1995/000096
Other languages
English (en)
Inventor
Michael Craig Broadbent
Original Assignee
West-Walker, Francis, Nigel
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 West-Walker, Francis, Nigel filed Critical West-Walker, Francis, Nigel
Priority to AU36216/95A priority Critical patent/AU3621695A/en
Publication of WO1996009955A1 publication Critical patent/WO1996009955A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
    • B63B1/16—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving additional lift from hydrodynamic forces
    • B63B1/24—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving additional lift from hydrodynamic forces of hydrofoil type
    • B63B1/28—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving additional lift from hydrodynamic forces of hydrofoil type with movable hydrofoils
    • B63B1/285—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving additional lift from hydrodynamic forces of hydrofoil type with movable hydrofoils changing the angle of attack or the lift of the foil
    • B63B1/286—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving additional lift from hydrodynamic forces of hydrofoil type with movable hydrofoils changing the angle of attack or the lift of the foil using flaps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing

Definitions

  • the present invention relates to a mechanical system for deploying leading edge and trailing edge lift enhancing surfaces for aircraft or marine craft wings.
  • Aerodynamics is but one discipline in the field of fluid dynamics and all technology for aerodynamic devices can be easily adapted to hydrodynamic use.
  • reference to an aircraft wing is intended to include reference to a marine craft wing.
  • a change of wing shape, varying the camber permits the optimisation in regard to aerodynamic drag, of a wing section for different flight conditions in particular cruise, takeoff and landing.
  • Early forms of variable camber devices consisted of hinged surfaces at the trailing edge of wings, flaps. Later, it was noticed that creating a slot between the main wing and the moveable surface enhanced the total lift beyond levels achieved by a simple hinged variable camber device.
  • the slot, or gap has the beneficial effect of energising the upper surface airflow, thus reducing the chance of stall at low speeds.
  • variable camber device is known as the Variable Camber Krueger flap system.
  • the aerodynamic surface deploys and unfolds from a position under and behind the D-nose of the wing to a position in front of and below the wing.
  • Various improvements on the Krueger system have been proposed but these generally require the use of multiple linkages.
  • One such improvement is discussed in US patent 5,158,252 assigned to The Boeing Company and which discloses a variable camber system having a rotatable drive arm which operates a first and second linkage subassembly.
  • US Patent 4,202,519 assigned to The Boeing Company discloses a leading edge slat apparatus which utilises a tilting arm having one end pivotally connected to the undersurface of an airfoil and the other end pivotally connected to an actuating member and a tilting link.
  • US Patent 3,941,334 assigned to The Boeing Company relates to yet another form of variable camber apparatus and describes a hinged rib member and a linkage mechanism to bend and twist the leading edge of the airfoil to contour it into a predetermined curvilinear plot.
  • variable camber leading edge systems are disclosed in US Patents 4,285,482 assigned to The Boeing Company; 4,040,579 assigned to The United States of America; US Patent 2,938,680 assigned to North American Aviation Inc and US Patent 2,406,475 to Gerrit P Rogers and Samuel H Pearls.
  • Trailing edge slotted variable camber devices rotate an airfoil about a line below and parallel to the wing trailing edge, thus causing both rotation and translation of the aerodynamic surface. This is often achieved through multiple pivot joints, located below the trailing edge of the wing, connecting an extension of the wing to an extension of the aerodynamic surface. Some devices rely on a track attached to the underside of the wing to translate and rotate the surface. Other devices use straight tracks and rotation is achieved through control linkages. Both offset hinge and track devices increase the profile of the wing in the direction of flight during cruise, thus increasing aerodynamic drag and fuel burn.
  • a disadvantage with the tracked variety of the leading edge and trailing edge systems is that the track pairs used to move the flaps and slats must be interconnected to give redundancy to actuators and to ensure balanced deployment. Considerable care must be exercised in the design of such systems to avoid asymmetric deployment which can cause locking of the mechanism.
  • the present invention comprises a linkage mechanism for varying the deployment of a moveable surface in relation to a wing, said linkage mechanism being characterised in that it comprises:
  • each swing arm has a first end connected to the wing and a second end connected to the moveable surface, whereby the said moveable surface can swing towards or away from the said wing to deploy or retract the said moveable surface, and
  • At least one control rod which acts between the said moveable surface and a base pivot point associated with the said wing, whereby the moveable surface will also rotate about a span line which is substantially parallel to and below the wing.
  • the base pivot point is located on the swing arm.
  • the base pivot point is located on the wing.
  • the base pivot point is located on a extension to the wing.
  • the pivotal connection of the first end of the swing arm to the wing comprises a rotary actuator.
  • the moveable surface comprises a slat located at the leading edge of the wing and the second end of each swing arm is connected to the slat by a ball joint.
  • the moveable surface comprises a flap located at the trailing edge of the wing and the second end of each swing arm is pivotally connected to a rotation arm which is connected to the flap.
  • Fig. 1 shows diagrammatically a plan view of a wing with four slats at the leading edge and two flaps at the trailing edge.
  • Fig. 2 is a diagrammatic cross sectional view of a retracted slat taken along the line 2 - 2 of Fig. 1.
  • Fig. 3 is a diagrammatic plan view of the retracted slat shown in Fig. 2.
  • Fig. 4 is a diagrammatic cross sectional view of a semi-deployed slat as taken along the line 4 - 4 of Figure 1.
  • Fig. 5 is a diagrammatic plan view of the semi-deployed slat shown in Fig. 4.
  • Fig. 6 is a diagrammatic cross sectional view of a fully extended slat taken along the line 6 - 6 of Figure 1.
  • Fig. 7 is a diagrammatic plan view of the fully extended slat shown in Fig. 6.
  • Fig. 8 is a diagrammatic plan view of an extended flap shown in Fig. 1 with the upper surface of the wing and part of the flap cut away to show the swing and rotation arms, and the control rods at fully deployed position.
  • Fig. 9 is a diagrammatic cross sectional view of a deployed flap taken along the line 9 - 9 of Fig. 8
  • Fig. 10 is a diagrammatic plan view of a retracted flap shown in Fig 1 with the upper surface of the wing and part of the flap cut away to show the swing and rotation and the control rods at the retracted position.
  • Fig. 1 1 is a diagrammatic cross sectional view of a retracted flap taken along line 1 1 - 11 of Fig. 10.
  • slats 10 are positioned at the leading edge of the wing 11 and the flaps 16 are positioned at the trailing edge of the wing 11.
  • Figs. 2 and 3 are respectively a diagrammatic side elevational view and a plan view of a retracted slat 10 and of a nose section for an airfoil envelope of the wing 11.
  • the slat 10 is attached to the wing 11 by two or more swing arms 12 of which one end is attached through the pivot joints 15 to the wing interface and in the form of the invention illustrated, the other end of each swing arm is attached by means of a ball joint 13 to the underside of the slat 10.
  • Pivoting of the swing arms 12 about the pivot joints 15 may be actuated by an appropriate means as is known in the art. While in the embodiment shown in the drawings the pivoting of the swing arms is preferably obtained by rotary actuation of the pivot joint 15, other methods of achieving this result can be obtained such as by utilising linear actuators either between the wing 11 and the slat 10 or between the wing 11 and the swing arm 12.
  • Control rods 14 are utilised to provide the desired rotation of the slats 10 about a span line which is both substantially parallel and below the leading edge of the wing 1 1.
  • the control rods 14 are connected between the slat 10 and a base pivot point by means of bearings 14a and 14b.
  • the base pivot point comprises the bearing 14b and is located on the swing arm 12 and the second bearing 14a is located at a high point on the slat 10.
  • the bearing 14b which forms the base pivot point may be located on the wing 11 or on an extension to the wing.
  • the slat 10 is translated forwards and downwards by the pivoting of the swing arms 12 between the positions shown in Figs. 2 to 7.
  • the restriction of the movement due to the control rods 14 will cause the slat during the translation, to rotate about a span line substantially parallel and below the leading edge of the wing 11.
  • the flaps 16 which are diagrammatically indicated in Fig. 1 as being positioned at the rear of the wing 11, are further diagrammatically illustrated in Figs. 8 through 1 1.
  • each flap 16 provides a complete tail section for the aerofoil envelope of the wing 1 1 and is pivotally attached to the wing 11 by two or more swing arms 17 and rotation arms 18.
  • one end of the swing arm 17 is attached to the wing 1 1 through a pivot joint 15 and the other end of the swing arm 17 is attached to a first end of the rotation arm 18 by a pivot joint 21.
  • the second end of the rotation arm 18 is attached to the flap 16 by a pivot joint 20. Rotation of the pivot joint 15 will thus result in the swing arm 17 pivoting so that the flap 16 can move from the fully deployed position shown in Figs. 8 and 9 to the retracted position shown in Figs. 10 and 1 1.
  • Control rods 19 are utilised to provide the desired rotation of the flaps 16 about a span line which runs substantially parallel and below the trailing edge of the wing 11.
  • the control rods 19 are connected between the flap 16 and a base pivot point by means of bearings 19a and 19b respectively.
  • the pivot point 19b is located on the swing arm 17 and the second bearing 19a is located at a high point on the flap 16.
  • the base pivot point may be located either on the wing 1 1 or on an extension of the wing 1 1.
  • the trailing edge moveable surface which is formed by the flap 16 is translated backwards and downwards by the pivoting of the swing arms 17 between the positions shown in Figs. 8 to 11.
  • the restriction of the movement due to the control rods 19 will cause the flap 16 to rotate about a span line which is substantially parallel and below the trailing edge of the wing 11.
  • Optimisation and customisation of the pivot angle rotation of the slat and flap may be achieved by varying the length and position of the control rods 14 and 19.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

Surface améliorant la sustentation pour l'aile d'un aéronef ou d'un bâtiment marin, et se trouvant au niveau du bord d'attaque (bec) et/ou du bord de fuite (volet), ladite surface étant reliée à l'aile par l'intermédiaire d'un système de timonerie. Ce système possède au moins deux bras pivotants parallèles (12) écartés l'un de l'autre, l'une des extrémités de chaque bras pivotant étant reliée pivotante (15) à l'aile tandis que l'autre extrémité (13) est reliée pivotante au bec ou au volet. (Les bras pivotants tels que représentés sont constitués chacun d'une seule pièce; cependant selon une variante de réalisation, chacun des bras pivotants est composé de deux pièces articulées au milieu du bras). Une tige de commande (14) s'étend entre le bec ou le volet et un point de pivotement de base situé sur le bras pivotant (tel que représenté) ou sur l'aile et, lors du déploiement, elle fait tourner le bec ou le volet autour d'une ligne d'envergure qui est sensiblement parallèle à l'aile et située en dessous de celle-ci.
PCT/NZ1995/000096 1994-09-29 1995-09-27 Timonerie pour le deploiement d'une surface par rapport a une aile WO1996009955A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU36216/95A AU3621695A (en) 1994-09-29 1995-09-27 Linkage to deploy a surface relative to a wing

Applications Claiming Priority (8)

Application Number Priority Date Filing Date Title
NZ26021694 1994-09-29
NZ260216 1994-09-29
NZ26490494 1994-11-11
NZ264904 1994-11-11
NZ270114 1994-12-09
NZ27011494 1994-12-09
NZ270885 1995-04-06
NZ27088595 1995-04-06

Publications (1)

Publication Number Publication Date
WO1996009955A1 true WO1996009955A1 (fr) 1996-04-04

Family

ID=27484338

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NZ1995/000096 WO1996009955A1 (fr) 1994-09-29 1995-09-27 Timonerie pour le deploiement d'une surface par rapport a une aile

Country Status (2)

Country Link
AU (1) AU3621695A (fr)
WO (1) WO1996009955A1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2311969A (en) * 1996-04-13 1997-10-15 Michael Craig Broadbent Variable camber wing mechanism
WO1997038900A1 (fr) * 1996-04-13 1997-10-23 Michael Craig Broadbent Mecanisme a cambrure variable pour aile
GB2323577A (en) * 1997-02-21 1998-09-30 Michael Craig Broadbent Interconnection system for moveable wing surfaces
EP0909705A2 (fr) * 1997-10-16 1999-04-21 Northrop Grumman Corporation Tringlerie du type à ciseaux pour mécanismes de volets à fente
GB2362363A (en) * 2000-05-20 2001-11-21 Michael Craig Broadbent System for deploying a moveable wing surface such as a slat from a main wing section
GB2380173A (en) * 2001-06-15 2003-04-02 Michael Craig Broadbent Wing with contiguous variable camber device
GB2402914A (en) * 2003-06-17 2004-12-22 Michael Craig Broadbent Deployment system for a moveable wing surface
US6974112B2 (en) 2003-06-17 2005-12-13 Michael Craig Broadbent Deployment system for a moveable wing surface
CN101646599B (zh) * 2007-01-11 2013-06-19 空中客车英国运营有限责任公司 机翼的前缘结构
US9573673B2 (en) 2012-08-08 2017-02-21 Airbus Operations Limited Slat support and deployment coupling
US10974816B2 (en) 2017-09-28 2021-04-13 The Boeing Company High-fowler flap actuation apparatus and related methods

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2246116A (en) * 1937-10-28 1941-06-17 Messerschmitt Boelkow Blohm Airplane wing structure
GB1286581A (en) * 1969-04-05 1972-08-23 Dornier A G Aircraft wing
GB1365168A (en) * 1971-01-27 1974-08-29 Hamburger Flugzeugbau Gmbh Device for extending and retracting flaps of aircraft wings
DE2354420A1 (de) * 1973-10-31 1975-05-07 Dornier Gmbh Spaltklappenbetaetigungsanordnung an tragfluegeln fuer luftfahrzeuge
US4202519A (en) * 1978-09-08 1980-05-13 The Boeing Company Airfoil leading edge slat apparatus
US4405105A (en) * 1980-04-10 1983-09-20 Vereinigte Flugtechnische Werke Gmbh Airfoil flap actuation

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2246116A (en) * 1937-10-28 1941-06-17 Messerschmitt Boelkow Blohm Airplane wing structure
GB1286581A (en) * 1969-04-05 1972-08-23 Dornier A G Aircraft wing
GB1365168A (en) * 1971-01-27 1974-08-29 Hamburger Flugzeugbau Gmbh Device for extending and retracting flaps of aircraft wings
DE2354420A1 (de) * 1973-10-31 1975-05-07 Dornier Gmbh Spaltklappenbetaetigungsanordnung an tragfluegeln fuer luftfahrzeuge
US4202519A (en) * 1978-09-08 1980-05-13 The Boeing Company Airfoil leading edge slat apparatus
US4405105A (en) * 1980-04-10 1983-09-20 Vereinigte Flugtechnische Werke Gmbh Airfoil flap actuation

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997038900A1 (fr) * 1996-04-13 1997-10-23 Michael Craig Broadbent Mecanisme a cambrure variable pour aile
GB2311969B (en) * 1996-04-13 1999-09-22 Michael Craig Broadbent Variable camber wing mechanism
US6015117A (en) * 1996-04-13 2000-01-18 Broadbent; Michael C Variable camber wing mechanism
GB2311969A (en) * 1996-04-13 1997-10-15 Michael Craig Broadbent Variable camber wing mechanism
GB2323577A (en) * 1997-02-21 1998-09-30 Michael Craig Broadbent Interconnection system for moveable wing surfaces
EP0909705A2 (fr) * 1997-10-16 1999-04-21 Northrop Grumman Corporation Tringlerie du type à ciseaux pour mécanismes de volets à fente
EP0909705A3 (fr) * 1997-10-16 2001-03-07 Northrop Grumman Corporation Tringlerie du type à ciseaux pour mécanismes de volets à fente
GB2362363B (en) * 2000-05-20 2003-09-10 Michael Craig Broadbent Deployment system for a moveable wing surface
GB2362363A (en) * 2000-05-20 2001-11-21 Michael Craig Broadbent System for deploying a moveable wing surface such as a slat from a main wing section
GB2380173A (en) * 2001-06-15 2003-04-02 Michael Craig Broadbent Wing with contiguous variable camber device
US6682023B2 (en) 2001-06-15 2004-01-27 Michael Craig Broadbent Contiguous variable camber device
GB2402914A (en) * 2003-06-17 2004-12-22 Michael Craig Broadbent Deployment system for a moveable wing surface
GB2402914B (en) * 2003-06-17 2005-08-10 Michael Craig Broadbent Deploying system for a moveable wing surface
US6974112B2 (en) 2003-06-17 2005-12-13 Michael Craig Broadbent Deployment system for a moveable wing surface
CN101646599B (zh) * 2007-01-11 2013-06-19 空中客车英国运营有限责任公司 机翼的前缘结构
US9573673B2 (en) 2012-08-08 2017-02-21 Airbus Operations Limited Slat support and deployment coupling
US10974816B2 (en) 2017-09-28 2021-04-13 The Boeing Company High-fowler flap actuation apparatus and related methods

Also Published As

Publication number Publication date
AU3621695A (en) 1996-04-19

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