WO2009013323A3 - Aerodynamisches profil, aktor zur verwendung darin sowie damit versehenes versuchsmodell - Google Patents

Aerodynamisches profil, aktor zur verwendung darin sowie damit versehenes versuchsmodell Download PDF

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Publication number
WO2009013323A3
WO2009013323A3 PCT/EP2008/059673 EP2008059673W WO2009013323A3 WO 2009013323 A3 WO2009013323 A3 WO 2009013323A3 EP 2008059673 W EP2008059673 W EP 2008059673W WO 2009013323 A3 WO2009013323 A3 WO 2009013323A3
Authority
WO
WIPO (PCT)
Prior art keywords
rear edge
actuator
aerodynamic profile
test model
model provided
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
PCT/EP2008/059673
Other languages
English (en)
French (fr)
Other versions
WO2009013323A2 (de
Inventor
Andreas Wildschek
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 Defence and Space GmbH
Original Assignee
EADS Deutschland 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 EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of WO2009013323A2 publication Critical patent/WO2009013323A2/de
Publication of WO2009013323A3 publication Critical patent/WO2009013323A3/de
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • B64C27/615—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including flaps mounted on blades
    • 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
    • H—ELECTRICITY
    • H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N30/00—Piezoelectric or electrostrictive devices
    • H10N30/20—Piezoelectric or electrostrictive devices with electrical input and mechanical output, e.g. functioning as actuators or vibrators
    • H10N30/204—Piezoelectric or electrostrictive devices with electrical input and mechanical output, e.g. functioning as actuators or vibrators using bending displacement, e.g. unimorph, bimorph or multimorph cantilever or membrane benders
    • H10N30/2041—Beam type
    • H10N30/2042—Cantilevers, i.e. having one fixed end
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72—Means acting on blades
    • B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
    • B64C2027/7261—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
    • B64C2027/7266—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators
    • B64C2027/7283—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators of the piezoelectric type
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

Die Erfindung betrifft ein aerodynamisches Profil (400), das an einer einer Anströmung (S) abzuwendenden Seite einen eine Hinterkante (412) bildenden Hinterkantenbereich (410) hat. Um die Hinterkante (412) auch für schnelle Regelungen bei einfachem Aufbau und extremer Miniaturisierbarkeit verlagern oder verformen zu können, wird vorgeschlagen, dass ein Aktor (418), der ein gesteuert kontrahierbares oder expandierbares Material oder Element (432) aufweist, im Inneren des Hinterkantenbereichs (410) zur zumindest teilweisen Lageveränderung und/oder Verformung der Hinterkante (412) und/oder des des Hinterkantenbereichs (410) vorgesehen ist.
PCT/EP2008/059673 2007-07-26 2008-07-23 Aerodynamisches profil, aktor zur verwendung darin sowie damit versehenes versuchsmodell Ceased WO2009013323A2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007035463.2 2007-07-26
DE102007035463A DE102007035463A1 (de) 2007-07-26 2007-07-26 Aerodynamisches Profil, Aktor zur Verwendung darin sowie damit versehenes Versuchsmodell

Publications (2)

Publication Number Publication Date
WO2009013323A2 WO2009013323A2 (de) 2009-01-29
WO2009013323A3 true WO2009013323A3 (de) 2009-04-02

Family

ID=40175657

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/059673 Ceased WO2009013323A2 (de) 2007-07-26 2008-07-23 Aerodynamisches profil, aktor zur verwendung darin sowie damit versehenes versuchsmodell

Country Status (2)

Country Link
DE (1) DE102007035463A1 (de)
WO (1) WO2009013323A2 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013107453A1 (en) * 2012-01-17 2013-07-25 Danfoss Polypower A/S Transducer activated morphing structure
CN104502056B (zh) * 2014-11-28 2017-12-05 中国航空工业空气动力研究院 飞机风洞试验模型边条翼上反角可控运动系统
CN109000911B (zh) * 2018-06-26 2024-02-02 哈尔滨电气股份有限公司 一种用于叶片热机械疲劳-蠕变的试验装置
CN114412953B (zh) * 2021-12-24 2022-11-25 南京航空航天大学 基于被动控制的直升机旋翼压电薄膜抑振结构及方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5224826A (en) * 1989-07-26 1993-07-06 Massachusetts Institute Of Technology Piezoelectric helicopter blade flap actuator
US6048622A (en) * 1994-04-19 2000-04-11 Massachusetts Institute Of Technology Composites for structural control
US6375127B1 (en) * 2000-07-07 2002-04-23 Kari Appa Active control surface modal system for aircraft buffet and gust load alleviation and flutter suppression
WO2004069651A1 (de) * 2003-02-04 2004-08-19 Eads Deutschland Gmbh Verformbares aerodynamisches profil
DE10334267A1 (de) * 2003-07-25 2005-02-24 Eurocopter Deutschland Gmbh Rotorblatt mit elastisch beweglicher Rotorblatt-Klappe sowie Drehflügelflugzeug mit einem solchen Rotorblatt
WO2007071231A1 (de) * 2005-12-21 2007-06-28 Eads Deutschland Gmbh Dreidimensionales stapelpiezoelement und piezoelektrischer aktuator mit einem solchen stapelpiezoelement

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19923087B4 (de) * 1999-05-20 2004-02-26 Eads Deutschland Gmbh Vorrichtung zur Druck-, Schall- und Vibrationsmessung, sowie Verfahren zur Strömungsanalyse an Bauteiloberflächen
WO2001031715A1 (en) * 1999-10-22 2001-05-03 The Government Of The United States As Represented By The Administrator Of The National Aeronautics And Space Administration Non-uniform thickness electroactive device
DE102004055996A1 (de) * 2004-11-19 2006-05-24 Stefan Eickenberg Biegeaktuator

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5224826A (en) * 1989-07-26 1993-07-06 Massachusetts Institute Of Technology Piezoelectric helicopter blade flap actuator
US6048622A (en) * 1994-04-19 2000-04-11 Massachusetts Institute Of Technology Composites for structural control
US6375127B1 (en) * 2000-07-07 2002-04-23 Kari Appa Active control surface modal system for aircraft buffet and gust load alleviation and flutter suppression
WO2004069651A1 (de) * 2003-02-04 2004-08-19 Eads Deutschland Gmbh Verformbares aerodynamisches profil
DE10334267A1 (de) * 2003-07-25 2005-02-24 Eurocopter Deutschland Gmbh Rotorblatt mit elastisch beweglicher Rotorblatt-Klappe sowie Drehflügelflugzeug mit einem solchen Rotorblatt
WO2007071231A1 (de) * 2005-12-21 2007-06-28 Eads Deutschland Gmbh Dreidimensionales stapelpiezoelement und piezoelektrischer aktuator mit einem solchen stapelpiezoelement

Also Published As

Publication number Publication date
WO2009013323A2 (de) 2009-01-29
DE102007035463A1 (de) 2009-02-05

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