DE102007024372B4 - Noise reduction device on a high lift system on the wing of an aircraft - Google Patents
Noise reduction device on a high lift system on the wing of an aircraft Download PDFInfo
- Publication number
- DE102007024372B4 DE102007024372B4 DE102007024372.5A DE102007024372A DE102007024372B4 DE 102007024372 B4 DE102007024372 B4 DE 102007024372B4 DE 102007024372 A DE102007024372 A DE 102007024372A DE 102007024372 B4 DE102007024372 B4 DE 102007024372B4
- Authority
- DE
- Germany
- Prior art keywords
- movable element
- gap
- oscillatory movement
- wing
- profile body
- 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.)
- Expired - Fee Related
Links
Images
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
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Einrichtung zur Lärmreduzierung an einem Hochauftriebssystem am Tragflügel eines Flugzeugs, das einen Hauptprofilkörper (1) und mindestens eine an dem Hauptprofilkörper (1) angeordnete Nasenklappe (2) umfasst, die unter Vergrößerung der Profilwölbung und Freigabe eines Luft von der Unterseite zur Oberseite des Tragflügels (1) führenden Spaltes (22) ausfahrbar ist, wobei der Spalt (22) durch einen Hinterkantenbereich (21) der Nasenklappe (2) und einen Nasenbereich (13) des anderen, in Strömungsrichtung dahinter befindlichen stromabwärtigen Hauptprofilkörpers (1) begrenzt ist, wobei mindestens ein flächiges bewegliches Element (27) im Bereich der Nasenklappe (2) vorgesehenen ist, und ein piezoelektrischer Aktuator (27b) vorgesehen ist, durch welchen das bewegliche Element (27) eine oszillatorische Bewegung zur Schwingungsanregung der durch den Spalt (22) geführten Luft erfährt. Erfindungsgemäß ist der piezoelektrische Aktuator (27b) von der Innenseite des beweglichen Elements (27) beabstandet angeordnet und über ein Kopplungselement (27c) mit dem beweglichen Element (27) gekoppelt.A device for noise reduction on a high-lift system on the wing of an aircraft, comprising a main profile body (1) and at least one on the main profile body (1) arranged nose flap (2), the enlargement of the profile curvature and release of air from the bottom to the top of the wing ( 1) leading gap (22) is extendable, wherein the gap (22) by a trailing edge region (21) of the nose flap (2) and a nose region (13) of the other, located in the downstream direction downstream main profile body (1) is limited, wherein at least a planar movable element (27) is provided in the region of the nose flap (2), and a piezoelectric actuator (27b) is provided, through which the movable element (27) undergoes an oscillatory movement for vibrational excitation of the air guided through the gap (22) , According to the invention, the piezoelectric actuator (27b) is arranged at a distance from the inside of the movable element (27) and coupled to the movable element (27) via a coupling element (27c).
Description
Die Erfindung betrifft eine Einrichtung zur Lärmreduzierung an einem Hochauftriebssystem am Tragflügel eines Flugzeugs nach dem Oberbegriff des Anspruchs 1. The invention relates to a device for noise reduction on a high-lift system on the wing of an aircraft according to the preamble of
Hochauftriebssysteme am Tragflügel eines Flugzeugs umfassen typischerweise eine oder mehrere Nasenklappen, die an der in Strömungsrichtung vorderen Seite des Tragflügels angeordnet sind und eine oder mehrere Hochauftriebsklappen, die an der in Strömungsrichtung hinteren Seite des Tragflügels angeordnet sind. Die Klappen sind jeweils mit einem Hauptprofilkörper des Tragflügels in einer solchen Weise verbunden, dass die Klappen unter Vergrößerung der Profilwölbung und effektiver Verlängerung der Profilsehne unter zusätzlicher Freigabe eines Spaltes ausfahrbar sind, durch den energiereiche Luft von der Unterseite zur Oberseite des Tragflügels geführt wird. Dieser Spalt liegt dementsprechend entweder zwischen Nasenklappe oder Vorflügel einerseits und Hauptprofilkörper andererseits oder zwischen dem Hauptprofilkörper einerseits und der dahinter befindlichen Hochauftriebsklappe andererseits, je nach betrachteter Hochauftriebsklappe. Bei ausgefahrenen Klappen ist mit den Spaltströmungen eine deutliche Erzeugung von aerodynamischem Lärm verbunden, der insbesondere beim Landeanflug über bewohntem Gebiet als lästig empfunden wird, und durch Wirbel und Turbulenzen in der Spaltströmung erklärt werden kann. High lift systems on the wing of an aircraft typically include one or more nose flaps disposed on the upstream side of the wing and one or more high lift flaps disposed on the downstream side of the wing. The flaps are each connected to a main profile body of the wing in such a way that the flaps are extended by increasing the profile curvature and effective extension of the chord, with additional release of a gap is passed through the high-energy air from the bottom to the top of the wing. This gap is accordingly either between the nose flap or slats on the one hand and main profile body on the other hand or between the main profile body on the one hand and the high-lift flap behind it, depending on the considered high-lift flap. When the flaps are extended, there is a significant generation of aerodynamic noise associated with the crevices, which is particularly troublesome when landing over inhabited areas, and can be explained by eddies and turbulence in the crevice flow.
Aus der
Weiterer bekannter Stand der Technik ergibt sich aus folgenden Dokumenten. Aus der
Die Aufgabe der Erfindung ist es, eine verbesserte Einrichtung zur Lärmreduzierung an einem Hochauftriebssystem am Tragflügel eines Flugzeugs zu schaffen, insbesondere zum Schutz vor Verschleiß. The object of the invention is to provide an improved device for noise reduction on a high-lift system on the wing of an aircraft, in particular for protection against wear.
Die Aufgabe wird durch eine Einrichtung mit den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Ausführungsformen und Weiterbildungen der Einrichtung sind in den Unteransprüchen angegeben.The object is achieved by a device having the features of
Ein Vorteil der Erfindung ist es, dass die Lärmreduzierung am Hochauftriebssystem im Falle eines Fehlers keine Auswirkung auf die Funktionsfähigkeit des Hochauftriebssystems hat, insbesondere wird der Verschleiß des Hochauftriebssystems, insbesondere des Aktuators zur Anregung von Oszillationen im Strömungsmedium des Spaltes zwischen Nasenklappe und Hauptprofilkörper, verringert. An advantage of the invention is that the noise reduction on the high-lift system in the event of failure has no effect on the functioning of the high-lift system, in particular the wear of the high-lift system, in particular the actuator for excitation of oscillations in the flow medium of the gap between the nose flap and main profile body is reduced.
Im Folgenden werden Ausführungsbeispiele der Erfindung anhand der Zeichnung erläutert. In the following, embodiments of the invention will be explained with reference to the drawing.
Es zeigen: Show it:
Bezüglich der Strömungsrichtung vor dem Hauptprofilkörper
In
In konventionellen Konfigurationen ist der Slat Hook notwendig, um die „Delle“ auf der Unterseite im eingefahrenen Zustand zu überdecken. Im ausgefahrenen Zustand steht der Slat Hook im Wind und stört die glatte Kontur des Vorflügels, indem er eine Art Abrisskante darstellt. Dadurch entstehen Wirbel in der Hohlkehle, was zu Lärm führt. Abhilfe bietet ein aktiver Slat Hook. In conventional configurations, the slat hook is necessary to cover the "dent" on the bottom when retracted. When extended, the Slat Hook stands in the wind and disturbs the slippery contour of the slat, forming a kind of spoiler lip. This creates whirls in the groove, causing noise. The remedy is provided by an active slat hook.
Das in
In
Der mit dem beweglichen Element
Anstelle der beispielhaft im Zusammenhang mit
Es können mehrere in Spannweitenrichtung nebeneinander befindliche Teile des beweglichen Elements
Bei dem dargestellten Ausführungsbeispiel ist das beweglichen Element
Das bewegliche Element
BezugszeichenlisteLIST OF REFERENCE NUMBERS
- 1 1
- Hauptprofilkörper; Profilkörper Main profile body; profile body
- 2 2
- Nasenklappe; Profilkörper; Hochauftriebsklappe; Vorflügel Nasal valve; Profile body; High lift flap; vane
- 3 3
- Hinterkantenklappe; Hochauftriebsklappe; Profilkörper Trailing edge flap; High lift flap; profile body
- 11; 21 11; 21
- Hinterkantenbereich Trailing edge region
- 17; 27 17; 27
- bewegliches Element movable element
- 27c 27c
- Kopplungselement coupling element
- 12; 22 12; 22
- durchströmter Spalt flowed through gap
- 13; 23; 33 13; 23; 33
- Nasenbereich nasal area
- 14 14
- obere Beplankung upper planking
- 15 15
- untere Beplankung lower planking
- 26 26
- Hinterkantenbereich Trailing edge region
- 27b 27b
- Aktuator actuator
- 28 28
- Drucksensor; Sensor Pressure sensor; sensor
- 29 29
- Regelverstärker control amplifier
Claims (14)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007024372.5A DE102007024372B4 (en) | 2007-05-23 | 2007-05-23 | Noise reduction device on a high lift system on the wing of an aircraft |
PCT/DE2008/000828 WO2008141618A2 (en) | 2007-05-23 | 2008-05-16 | Method and device for reducing noise on a high lift system on the airfoil of an aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007024372.5A DE102007024372B4 (en) | 2007-05-23 | 2007-05-23 | Noise reduction device on a high lift system on the wing of an aircraft |
Publications (2)
Publication Number | Publication Date |
---|---|
DE102007024372A1 DE102007024372A1 (en) | 2008-11-27 |
DE102007024372B4 true DE102007024372B4 (en) | 2016-02-18 |
Family
ID=39874877
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102007024372.5A Expired - Fee Related DE102007024372B4 (en) | 2007-05-23 | 2007-05-23 | Noise reduction device on a high lift system on the wing of an aircraft |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE102007024372B4 (en) |
WO (1) | WO2008141618A2 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4699487B2 (en) * | 2007-05-25 | 2011-06-08 | 三菱重工業株式会社 | Noise reduction structure of high lift generator, wing and high lift generator |
DE102009057340A1 (en) | 2009-12-07 | 2011-06-09 | Airbus Operations Gmbh | High lift system for an aircraft, method of moving a lift flap, and aircraft with a high lift system |
CN113859515A (en) * | 2021-11-08 | 2021-12-31 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft wing flap |
CN114320735A (en) * | 2022-01-04 | 2022-04-12 | 上海电气风电集团股份有限公司 | Novel fan blade and stall control method thereof |
CN114320736A (en) * | 2022-01-04 | 2022-04-12 | 上海电气风电集团股份有限公司 | Wind power blade and blade dynamic stall control method thereof |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5798465A (en) * | 1995-03-14 | 1998-08-25 | Sulzer Innotec Ag | Method for actively damping global flow oscillations in separated unstable flows and an apparatus for performing the method |
US6247670B1 (en) * | 1999-09-07 | 2001-06-19 | Ramot University Authority For Applied Research And Industrial Development Ltd | Active flaperon assembly |
EP1314642A2 (en) * | 2001-11-24 | 2003-05-28 | Airbus Deutschland GmbH | Arrangement to reduce the noise generated by aircraft leading edge flaps |
DE102004056537A1 (en) * | 2004-11-23 | 2006-06-01 | Eads Deutschland Gmbh | Arrangement for reducing the aerodynamic noise on an additional wing of an aircraft |
US7150434B1 (en) * | 2005-02-25 | 2006-12-19 | The United States Of America As Represented By The Secretary Of The Navy | Vehicle wake vortex modifier |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IL52613A (en) * | 1977-07-28 | 1980-11-30 | Univ Ramot | Method and apparatus for controlling the mixing of two fluids |
US4845357A (en) * | 1988-02-11 | 1989-07-04 | Simmonds Precision Products, Inc. | Method of actuation and flight control |
GB8829836D0 (en) * | 1988-12-21 | 1989-02-15 | British Aerospace | Wing flap hoot suppression |
DE19925560B4 (en) * | 1999-06-04 | 2004-04-22 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Additional wing for main wing of aircraft |
-
2007
- 2007-05-23 DE DE102007024372.5A patent/DE102007024372B4/en not_active Expired - Fee Related
-
2008
- 2008-05-16 WO PCT/DE2008/000828 patent/WO2008141618A2/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5798465A (en) * | 1995-03-14 | 1998-08-25 | Sulzer Innotec Ag | Method for actively damping global flow oscillations in separated unstable flows and an apparatus for performing the method |
US6247670B1 (en) * | 1999-09-07 | 2001-06-19 | Ramot University Authority For Applied Research And Industrial Development Ltd | Active flaperon assembly |
EP1314642A2 (en) * | 2001-11-24 | 2003-05-28 | Airbus Deutschland GmbH | Arrangement to reduce the noise generated by aircraft leading edge flaps |
DE102004056537A1 (en) * | 2004-11-23 | 2006-06-01 | Eads Deutschland Gmbh | Arrangement for reducing the aerodynamic noise on an additional wing of an aircraft |
US7150434B1 (en) * | 2005-02-25 | 2006-12-19 | The United States Of America As Represented By The Secretary Of The Navy | Vehicle wake vortex modifier |
Also Published As
Publication number | Publication date |
---|---|
WO2008141618A3 (en) | 2009-02-12 |
DE102007024372A1 (en) | 2008-11-27 |
WO2008141618A2 (en) | 2008-11-27 |
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Legal Events
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OP8 | Request for examination as to paragraph 44 patent law | ||
R016 | Response to examination communication | ||
R082 | Change of representative |
Representative=s name: ROESLER RASCH & PARTNER PATENT- UND RECHTSANWA, DE |
|
R081 | Change of applicant/patentee |
Owner name: AIRBUS DEFENCE AND SPACE GMBH, DE Free format text: FORMER OWNER: EADS DEUTSCHLAND GMBH, 85521 OTTOBRUNN, DE Effective date: 20140814 |
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R082 | Change of representative |
Representative=s name: ROESLER - RASCH - VAN DER HEIDE & PARTNER PATE, DE Effective date: 20140814 Representative=s name: ISARPATENT - PATENTANWAELTE- UND RECHTSANWAELT, DE Effective date: 20140814 Representative=s name: ROESLER RASCH & PARTNER PATENT- UND RECHTSANWA, DE Effective date: 20140814 |
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R016 | Response to examination communication | ||
R018 | Grant decision by examination section/examining division | ||
R082 | Change of representative |
Representative=s name: ISARPATENT - PATENT- UND RECHTSANWAELTE BEHNIS, DE Representative=s name: ISARPATENT - PATENT- UND RECHTSANWAELTE BARTH , DE Representative=s name: ISARPATENT - PATENTANWAELTE- UND RECHTSANWAELT, DE |
|
R020 | Patent grant now final | ||
R119 | Application deemed withdrawn, or ip right lapsed, due to non-payment of renewal fee |