EP2328805A2 - Système d'hypersustentation pour aéronef comprenant un volet hypersustentateur et procédé de réglage de volet hypersustentateur - Google Patents

Système d'hypersustentation pour aéronef comprenant un volet hypersustentateur et procédé de réglage de volet hypersustentateur

Info

Publication number
EP2328805A2
EP2328805A2 EP09778200A EP09778200A EP2328805A2 EP 2328805 A2 EP2328805 A2 EP 2328805A2 EP 09778200 A EP09778200 A EP 09778200A EP 09778200 A EP09778200 A EP 09778200A EP 2328805 A2 EP2328805 A2 EP 2328805A2
Authority
EP
European Patent Office
Prior art keywords
flap
lift
edge flap
leading edge
aircraft
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.)
Ceased
Application number
EP09778200A
Other languages
German (de)
English (en)
Inventor
Daniel Reckzeh
Klaus Schindler
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.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
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 Operations GmbH filed Critical Airbus Operations GmbH
Publication of EP2328805A2 publication Critical patent/EP2328805A2/fr
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • B64C9/24—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap
    • 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
    • B64C9/28—Adjustable control surfaces or members, e.g. rudders forming slots by flaps at both the front and rear of the wing operating in unison
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/30—Wing lift efficiency

Definitions

  • the invention relates to a high-lift system for an aircraft having at least one high-lift flap arranged on each of the main wings of the aircraft and to a method for adjusting at least one high-lift flap arranged on each of the main wings of an aircraft.
  • the object of the invention is to provide a high-lift system and a method for adjusting at least one arranged on each of the main wing of an aircraft high-lift flap, each representing a favorable buoyancy configuration for the start.
  • a pilot input device for generating flight phase-related specifications for the at least one high-lift flap, wherein these specifications include at least one start default,
  • a control device functionally connected to the pilot input device with a conversion function, with the flight phase-related targets are converted into control commands for actuating a drive device for adjusting or adjusting the adjustment states of the at least one high-lift flap, a predetermined flight phase is the start phase.
  • the pilot input device can be used to select an automatic flight mode which automatically generates the start default.
  • the high-lift system according to the invention for an aircraft has at least one high-lift flap arranged on each of the main wings 1 of the aircraft.
  • the at least one high-lift flap can be realized by at least one leading edge flap 3 per wing and optionally at least one trailing edge flap 5 per wing.
  • the high-lift system has a pilot input device for generating flight phase-related specifications for the at least one high-lift flap.
  • the conversion function of the control device is designed such that it generates an adjusting command to the drive device to a received start specification, wherein the at least one leading edge flap 3 is arranged in an adjustment state, in which a gap between the leading edge flap 3 and the main wing 1 with a gap width between 0.1% and 0.4% based on the local chord.
  • This gap width range is maintained according to the invention over the span of the leading edge flap 3.
  • a single starting position may be provided, in which this gap width range is adjusted.
  • the leading edge flap 3 is arranged in an adjustment angle in the range between 10 and 22 degrees.
  • the conversion function of the control device generates an adjustment command for a trailing edge flap 5, on the basis of which the drive device additionally arranges the trailing edge flap 5 in an extended adjustment state.
  • the trailing edge flap 5 is arranged in an adjustment angle in the range between 10 and 30 degrees.
  • a trailing edge flap 5 is additionally arranged in an extended adjustment state.
  • the start input can be manually selected with the pilot input device or that an automatic flight mode can be selected with the pilot input device, which automatically generates the start default.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Transmission Devices (AREA)
  • Traffic Control Systems (AREA)
  • Blinds (AREA)

Abstract

L'invention concerne un système d'hypersustentation pour un aréonef comportant au moins un volet hypersustentateur installé sur chacune des ailes principales (1) de l'aéronef, ledit système comprenant un dispositif d'entrée pilote pour la génération de consignes liées à la phase de vol, pour ledit au moins un volet hypersustentateur, ces consignes incluant au moins une consigne de démarrage, et un dispositif de commande couplé fonctionnellement au dispositif d'entrée pilote, comprenant une fonction de conversion qui assure la conversion des consignes liées à la phase de vol en instructions de réglage activant un mécanisme de commande, lequel règle ou modifie les état de réglage du ou des volets hypersustentateurs, une phase de vol prédéfinissable constituant la phase de démarrage. La fonction de conversion du dispositif de commande est conçue de telle manière qu'en réponse à une consigne de démarrage, une instruction de réglage est générée à l'adresse du mécanisme de commande, selon laquelle un volet de bord d'attaque (3) du ou des volets hypersustentateurs est positionné dans un état de réglage tel que le volet de bord d'attaque (3) et l'aile principale sont séparés par une fente d'une largeur comprise entre 0,1% et 0,4% de la profondeur locale de l'aile. L'invention concerne également un procédé pour régler au moins un volet hypersustentateur installé sur chacune des ailes principales (1) d'un aéronef.
EP09778200A 2008-08-28 2009-08-28 Système d'hypersustentation pour aéronef comprenant un volet hypersustentateur et procédé de réglage de volet hypersustentateur Ceased EP2328805A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US9241108P 2008-08-28 2008-08-28
DE200810044750 DE102008044750A1 (de) 2008-08-28 2008-08-28 Hochauftriebssystem für ein Flugzeug mit einer Hochauftriebsklappe und Verfahren zur Verstellung der Hochauftriebsklappe
PCT/EP2009/006271 WO2010022978A2 (fr) 2008-08-28 2009-08-28 Système d'hypersustentation pour aéronef comprenant un volet hypersustentateur et procédé de réglage de volet hypersustentateur

Publications (1)

Publication Number Publication Date
EP2328805A2 true EP2328805A2 (fr) 2011-06-08

Family

ID=41605953

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09778200A Ceased EP2328805A2 (fr) 2008-08-28 2009-08-28 Système d'hypersustentation pour aéronef comprenant un volet hypersustentateur et procédé de réglage de volet hypersustentateur

Country Status (6)

Country Link
US (1) US9145199B2 (fr)
EP (1) EP2328805A2 (fr)
CN (1) CN102137793B (fr)
DE (1) DE102008044750A1 (fr)
RU (1) RU2011111584A (fr)
WO (1) WO2010022978A2 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008044750A1 (de) 2008-08-28 2010-03-04 Airbus Deutschland Gmbh Hochauftriebssystem für ein Flugzeug mit einer Hochauftriebsklappe und Verfahren zur Verstellung der Hochauftriebsklappe
US8534610B1 (en) * 2009-07-17 2013-09-17 The Boeing Company Method and apparatus for a leading edge slat on a wing of an aircraft
CN102642616B (zh) * 2012-05-11 2014-09-17 中国航空工业集团公司西安飞机设计研究所 一种带固定双缝襟翼的飞机增升装置
US9327826B2 (en) * 2012-10-25 2016-05-03 Textron Innovations Inc. Self-centering aircraft flap position command apparatus
CN102975849A (zh) * 2012-12-14 2013-03-20 中国航空工业空气动力研究院 一种前探式前翼前缘襟翼结构
CN103287574B (zh) * 2013-01-05 2015-07-01 中国航空工业集团公司西安飞机设计研究所 一种飞机增升装置控制方法
CN105109671B (zh) * 2015-09-25 2017-05-17 江西洪都航空工业集团有限责任公司 一种前缘襟翼控制方法
CN114320736A (zh) * 2022-01-04 2022-04-12 上海电气风电集团股份有限公司 风电叶片及其叶片动态失速控制方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1395340A (fr) * 1964-05-19 1965-04-09 British Aircraft Corp Ltd Perfectionnements aux dispositifs hyper-sustentateurs pour avions

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5056741A (en) * 1989-09-29 1991-10-15 The Boeing Company Apparatus and method for aircraft wing stall control
US5544847A (en) * 1993-11-10 1996-08-13 The Boeing Company Leading edge slat/wing combination
US5681013A (en) * 1995-12-26 1997-10-28 The Boeing Company Vortex leading edge flap assembly for supersonic airplanes
GB0127254D0 (en) 2001-11-13 2002-01-02 Lucas Industries Ltd Aircraft flight surface control system
DE102005027749B4 (de) 2005-06-16 2011-07-28 Airbus Operations GmbH, 21129 Auftriebserhöhende Klappe, insbesondere Nasenklappe, für einen aerodynamisch wirksamen Flügel
US7708231B2 (en) * 2005-11-21 2010-05-04 The Boeing Company Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods
DE102008044750A1 (de) 2008-08-28 2010-03-04 Airbus Deutschland Gmbh Hochauftriebssystem für ein Flugzeug mit einer Hochauftriebsklappe und Verfahren zur Verstellung der Hochauftriebsklappe

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1395340A (fr) * 1964-05-19 1965-04-09 British Aircraft Corp Ltd Perfectionnements aux dispositifs hyper-sustentateurs pour avions

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2010022978A2 *

Also Published As

Publication number Publication date
CN102137793B (zh) 2014-11-12
WO2010022978A3 (fr) 2010-07-22
DE102008044750A1 (de) 2010-03-04
US20110163204A1 (en) 2011-07-07
RU2011111584A (ru) 2012-10-10
CN102137793A (zh) 2011-07-27
US9145199B2 (en) 2015-09-29
WO2010022978A2 (fr) 2010-03-04

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