DE3935925A1 - Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force - Google Patents

Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force

Info

Publication number
DE3935925A1
DE3935925A1 DE19893935925 DE3935925A DE3935925A1 DE 3935925 A1 DE3935925 A1 DE 3935925A1 DE 19893935925 DE19893935925 DE 19893935925 DE 3935925 A DE3935925 A DE 3935925A DE 3935925 A1 DE3935925 A1 DE 3935925A1
Authority
DE
Germany
Prior art keywords
wing
flutter
damper
mass
inertia
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.)
Granted
Application number
DE19893935925
Other languages
German (de)
Other versions
DE3935925C2 (en
Inventor
Gerhard Dipl Ing Dr Loebert
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
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Priority to DE19893935925 priority Critical patent/DE3935925A1/en
Publication of DE3935925A1 publication Critical patent/DE3935925A1/en
Application granted granted Critical
Publication of DE3935925C2 publication Critical patent/DE3935925C2/de
Granted legal-status Critical Current

Links

Classifications

    • 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
    • B64C13/02—Initiating means
    • B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/30—Balancing hinged surfaces, e.g. dynamically
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
    • F16F7/1022—Vibration-dampers; Shock-absorbers using inertia effect the linear oscillation movement being converted into a rotational movement of the inertia member, e.g. using a pivoted mass
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
    • F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Toys (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

The passive flutter damper for an aircraft wing is formed by a winglet (6) attached to the tip of the main wing (1) by a shaft. A mass (2) is attached to the outer end of the main arm of a T-shaped lever (3). This lever is mounted on a shaft. A spring (7) is attached to the outer end of one of the shorter arms, whilst the other short arm is attached to a damper (8). In the event of an upward movement of the wing the inertia of the mass exerts a torsional force on the shaft so that the winglet (6) is rotated so that it slopes downwards to the leading edge. The air (5) flowing over the winglet then exerts a downward force tending to correct the initial upward movement of the wing. USE - Damping of aircraft wing flutter.

Description

Die Erfindung betrifft einen passiven Flatterdämpfer für einen aerodyna­ mischen Flügel.The invention relates to a passive flutter damper for an aerodyne mix wings.

Ein typisches Merkmal für den Mechanismus einer dynamischen Instabili­ tät, wie das sogenannte Flattern eines aerodynamischen Flügels, ist das Vorhandensein mindestens zweier gekoppelter Schwingungsformen benachbar­ ter Frequenz, bei denen z. B. Strömungsenergie so in Schwingungsenergie umgesetzt wird, daß mindestens eine am Flattermechanismus beteiligte Schwingungsform angefacht wird. Derartige dynamische Instabilitäten sind gefährliche Phänomene, die innerhalb kürzester Zeit zum Bruch der Flü­ gelstruktur führen können.A typical feature of the mechanism of a dynamic instability act like the so-called flutter of an aerodynamic wing, that is The presence of at least two coupled waveforms adjacent ter frequency at which z. B. flow energy so in vibration energy implemented that at least one involved in the flutter mechanism Wave form is fanned. Such dynamic instabilities are dangerous phenomena that quickly break the flue can lead gel structure.

Zur Beseitigung einer derartigen dynamischen Instabilität von umströmten elastischen Strukturen, wie z. B. das Flügelflattern, werden im allgemei­ nen entweder Versteifungen der Struktur oder ein Massenausgleich oder eine Dämpfung beweglicher Teile vorgenommen. Die vorgenannten Maßnahmen sind mit erheblichem Gewichtszuwachs verbunden.To eliminate such dynamic instability from flow around elastic structures, such as B. the wing flutter, in general Neither stiffening of the structure or a mass balance or damping moving parts. The above measures are associated with considerable weight gain.

Es ist daher Aufgabe der Erfindung, eine Maßnahme zur Unterdrückung von dynamischen Instabilitäten, insbesondere einen Flatterdämpfer zu schaf­ fen, welcher leichter, möglichst wartungsarm und auch nachträglich mon­ tierbar ist.It is therefore an object of the invention to provide a measure to suppress dynamic instabilities, in particular to create a flutter damper fen, which is lighter, as low maintenance as possible and also retrofitted is animal.

Diese Aufgabe wird durch einen nach den kennzeichnenden Merkmalen des Patentanspruchs 1 ausgebildeten passiven Flatterdämpfer gelöst.This task is performed according to the characteristics of the Claim 1 trained passive flutter damper solved.

Ein derartiger Flatterdämpfer wirkt wie ein Servosystem, jedoch rein passiv und nutzt die aerodynamischen Kräfte eines entsprechend aerodyna­ misch wirksamen Elementes, z. B. eines Winglets, dessen Anstellwinkel mit geeigneter Phase und Amplitude derart verändert wird, daß die derart entstehenden aerodynamischen Kräfte der Flatterbewegung des gesamten Flügels entgegenwirken. Die Steuerung dieses aerodynamisch wirksamen Elementes geschieht dabei durch eine im Flügel angeordnete träge Masse, deren relative Lageveränderung zum Flügel bei einer Flatterbewegung die jeweilige Stellung des aerodynamisch wirksamen Elementes verändert. Da­ durch wird vermieden, daß sich eine periodische Flatterbewegung aufbaut.Such a flutter damper acts like a servo system, but purely passive and uses the aerodynamic forces of a corresponding aerodyna mixed active element, e.g. B. a winglet whose angle of attack with suitable phase and amplitude is changed such that the such arising aerodynamic forces of the flutter movement of the whole Counteract wing. The control of this aerodynamically effective Element is done by an inertial mass arranged in the wing,  whose relative change in position to the wing with a flutter movement changed position of the aerodynamically effective element. There through it is avoided that a periodic flutter movement builds up.

Die Erfindung wird im folgenden anhand des in der Figur schematisch dar­ gestellten Ausführungsbeispieles näher erläutert.The invention is illustrated below with reference to that in the figure presented embodiment explained in more detail.

An der Spitze eines Flügels 1 ist innerhalb eines aerodynamisch verklei­ deten Gehäuses 1.2 ein Pendel 3 so angebracht, daß die Pendelachse 4 pa­ rallel zur Flügellängsachse 1.1 verläuft. Das Pendel 3 trägt am Ende ei­ ne träge Masse 2 und wird über Seitenschenkel 3.1. und 3.2 zum einen durch eine Feder 7 in einer mittleren Ruhelage gehalten und bei Bewegung durch einen Dämpfer 8 gedämpft. Die Feder 7 und der Dämpfer 8 stützen sich dabei jeweils am Gehäuse 1.2 ab.At the top of a wing 1 , a pendulum 3 is attached within an aerodynamically disguised housing 1.2 so that the pendulum axis 4 runs parallel to the longitudinal axis 1.1 of the wing. The pendulum 3 carries ei ne inert mass 2 at the end and is over side legs 3.1 . and 3.2 held by a spring 7 in a middle rest position and damped by a damper 8 when moving. The spring 7 and the damper 8 are each supported on the housing 1.2 .

An der im Flügel 1 und im Gehäuse 1.2 drehbar gelagerten Achse 4 ist in Verlängerung zum Flügel 1 ein Winglet 6 fest verbunden, derart, daß des­ sen Anstellwinkel im Ruhezustand etwa demjenigen des Flügels 1 ent­ spricht und bei Bewegungen des Pendels senkrecht zur Flügellängsachse relativ zum Flügel 1 in positive oder negative Anstellung verdreht wird.On the wing 1 and in the housing 1.2 rotatably mounted axis 4 , a winglet 6 is firmly connected in extension to the wing 1 , such that the angle of attack at rest speaks approximately to that of the wing 1 and corresponds to movements of the pendulum perpendicular to the wing longitudinal axis relative to Wing 1 is turned into positive or negative position.

Das Pendel 3 bildet zusammen mit der trägen Masse 2 sowie der Feder 7 und dem Dämpfer 8 ein gedämpftes schwingungsfähiges System, dessen Ei­ genschwingungsverhalten möglichst breitbandig und auf den Flatterfre­ quenzbereich des Flügels abgestimmt ist.The pendulum 3 forms together with the inertial mass 2 and the spring 7 and the damper 8 a damped vibratory system, the egg gene vibration behavior is as broadband and tuned to the Flatterfre frequency range of the wing.

Die Wirkungsweise dieses Flatterdämpfers ergibt sich wie folgt: Bei einer störungsbedingten Aufwärtsbewegung des Flügels 1 verursacht die Trägheit der Masse 2 am Pendel 3 eine Verdrehung des Winglets 6 der­ art, daß die durch die Pfeile 5 angedeutete Luftströmung 5 eine nach un­ ten gerichtete Kraft auf das Winglet 6 ausübt. Diese wird über die Achse 4 und das Gehäuse 1.2 an den starr mit diesem verbundenen Flügel 1 über­ tragen und somit die Aufwärtsbewegung des Flügels kompensiert. Entspre­ chend gegenläufig wirkt der Flatterdämpfer bei einer Abwärtsbewegung des Flügels 1. The operation of this flap damper results as follows: In the event of a fault-related upward movement of the wing 1 , the inertia of the mass 2 on the pendulum 3 causes the winglet 6 to rotate in such a way that the air flow 5 indicated by the arrows 5 exerts a force directed towards the un th Winglet 6 exercises. This is transmitted via the axis 4 and the housing 1.2 to the rigidly connected wing 1 and thus compensates for the upward movement of the wing. Correspondingly, the flap damper acts in a downward movement of the wing 1 .

Der Flatterdämpfer benötigt keine zusätzlichen Energien und läßt sich somit problemlos an einen aerodynamischen Flügel oder an eine andere in einer Strömung befindliche Struktur, die zu dynamischen Instabilitäten neigt, anbringen.The flutter damper requires no additional energy and can be thus easily to an aerodynamic wing or to another in a current structure leading to dynamic instabilities tends to attach.

Claims (6)

1. Passiver Flatterdämpfer für einen aerodynamischen Flügel, ge­ kennzeichnet durch eine im Bereich der Flügelspitze angeordnete, in Richtung der Flatterbewegung des Flügels (1) bewegliche träge Masse (2), welche aufgrund seiner Trägheit ein aerodynamisch wirksames Element (6) derart steuert, daß eine Flatterbewegung des Flügels (1) durch eine ent­ gegengerichtete aerodymamische Kraft des Elementes (6) kompensiert wird.1. Passive flap damper for an aerodynamic wing, characterized by an arranged in the area of the wing tip, in the direction of the flutter movement of the wing ( 1 ) movable inertial mass ( 2 ), which due to its inertia controls an aerodynamically effective element ( 6 ) in such a way that a flutter movement of the wing ( 1 ) is compensated for by an opposing aerodymatic force of the element ( 6 ). 2. Flatterdämpfer nach Anspruch 1, dadurch gekennzeichnet, daß die träge Masse (2) durch ein Feder-Dämpfer-System (7, 8) in einer Ruheposi­ tion gehalten wird.2. flutter damper according to claim 1, characterized in that the inertial mass ( 2 ) by a spring-damper system ( 7 , 8 ) is held in a rest position. 3. Flatterdämpfer nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die träge Masse (2) als Pendel (3) ausgebildet ist, welches in einer senkrecht zur Flügellängsachse (1.1) verlaufenden Richtung auslenkbar ist.3. flap damper according to claim 1 or 2, characterized in that the inertial mass ( 2 ) is designed as a pendulum ( 3 ) which can be deflected in a direction perpendicular to the longitudinal axis of the wing ( 1.1 ). 4. Flatterdämpfer nach Anspruch 3, dadurch gekennzeichnet, daß das Pendel (3) um eine in Flügellängsrichtung (1.1) verlaufende Achse (4) drehbar ist, wobei die Achse (4) mit dem aerodynamisch wirksamen Element (6) und dem Pendel (3) fest verbunden ist.4. flutter damper according to claim 3, characterized in that the pendulum ( 3 ) about an in the longitudinal direction ( 1.1 ) extending axis ( 4 ) is rotatable, the axis ( 4 ) with the aerodynamically active element ( 6 ) and the pendulum ( 3rd ) is firmly connected. 5. Flatterdämpfer nach einem der Ansprüche 1 bis 4, dadurch gekenn­ zeichnet, daß das aerodynamische Element als Winglet (6) ausgebildet ist.5. flutter damper according to one of claims 1 to 4, characterized in that the aerodynamic element is designed as a winglet ( 6 ). 6. Flatterdämpfer nach einem der Ansprüche 1 bis 5, dadurch gekenn­ zeichnet, daß die Resonanzfrequenz des Feder-Dämpfer-Systems (7, 8) in Verbindung mit der trägen Masse (2) auf die Flatterfrequenz des Flügels (1) abgestimmt ist.6. flap damper according to one of claims 1 to 5, characterized in that the resonance frequency of the spring-damper system ( 7 , 8 ) in conjunction with the inertial mass ( 2 ) is matched to the flutter frequency of the wing ( 1 ).
DE19893935925 1989-10-27 1989-10-27 Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force Granted DE3935925A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19893935925 DE3935925A1 (en) 1989-10-27 1989-10-27 Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19893935925 DE3935925A1 (en) 1989-10-27 1989-10-27 Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force

Publications (2)

Publication Number Publication Date
DE3935925A1 true DE3935925A1 (en) 1991-05-16
DE3935925C2 DE3935925C2 (en) 1993-02-11

Family

ID=6392421

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19893935925 Granted DE3935925A1 (en) 1989-10-27 1989-10-27 Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force

Country Status (1)

Country Link
DE (1) DE3935925A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6607161B1 (en) * 1999-09-14 2003-08-19 Eurocopter Convertible aircraft with tilting rotors
FR2902163A1 (en) * 2006-06-13 2007-12-14 Peugeot Citroen Automobiles Sa Open top type motor vehicle e.g. drop head type motor vehicle, has cylinder arranged inside hollow cross beam of vehicle structure, and adapted such that proper oscillation frequency of cylinder is equal to vibration frequency of vehicle
FR2951794A1 (en) * 2009-10-22 2011-04-29 Peugeot Citroen Automobiles Sa Bodyshell vibration absorbing system for e.g. drophead, has elastically deformable element arranged for being fixed to body shell by working only in extension during oscillations of beater from rest position

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11814162B2 (en) * 2020-06-18 2023-11-14 Textron Innovations Inc. Rotatable winglets for a rotary wing aircraft

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2056730B2 (en) * 1969-11-27 1978-11-30 Societe Nationale Industrielle Aerospatiale S.A., Paris Device for improving the longitudinal stability of a helicopter

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2056730B2 (en) * 1969-11-27 1978-11-30 Societe Nationale Industrielle Aerospatiale S.A., Paris Device for improving the longitudinal stability of a helicopter

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6607161B1 (en) * 1999-09-14 2003-08-19 Eurocopter Convertible aircraft with tilting rotors
FR2902163A1 (en) * 2006-06-13 2007-12-14 Peugeot Citroen Automobiles Sa Open top type motor vehicle e.g. drop head type motor vehicle, has cylinder arranged inside hollow cross beam of vehicle structure, and adapted such that proper oscillation frequency of cylinder is equal to vibration frequency of vehicle
FR2951794A1 (en) * 2009-10-22 2011-04-29 Peugeot Citroen Automobiles Sa Bodyshell vibration absorbing system for e.g. drophead, has elastically deformable element arranged for being fixed to body shell by working only in extension during oscillations of beater from rest position

Also Published As

Publication number Publication date
DE3935925C2 (en) 1993-02-11

Similar Documents

Publication Publication Date Title
DE60200897T2 (en) Coupled aircraft rotor system
DE69925601T2 (en) WIND TURBINE WING WITH U-SHAPED VIBRATION DAMPER
EP0074554A2 (en) Process and apparatus to reduce the flutter of an outside load wing unit of an aircraft
DE2214048A1 (en) Device for increasing the stability of a vehicle moving in a fluid medium
DE3126677A1 (en) Rotor blade design for high-speed rotors
WO2009013318A2 (en) Test arrangement comprising a test model that has at least one control element, and an associated method
DE1267096B (en) Device for the longitudinal stabilization of rotary wing aircraft in high-speed flight
DE3935925C2 (en)
WO2009013325A1 (en) Test arrangement having a test model and a fastening apparatus, wind tunnel arrangement, and such a fastening apparatus
EP2706034B1 (en) Active damper for low frequency oscillating structures
DD154282A1 (en) EQUIPMENT FOR WEIGHT COMPENSATION FOR HANDLING MACHINES WITH SWIVELS
DE102004032530B4 (en) Rotorcraft and control
EP0727350B1 (en) Rotorcraft with gyroscopic rotor stabilisation
DE2056730B2 (en) Device for improving the longitudinal stability of a helicopter
EP1756369B1 (en) Supporting structure with a device for damping oscillations
DE4241631C2 (en) Wind turbine
DE1481548A1 (en) Propulsion regulator
DE3221422C2 (en)
DE3935893C2 (en)
DE102015203048A1 (en) torsional vibration dampers
DE1756326C3 (en)
DE19524793C2 (en) Control for the rotor of a rotary wing aircraft
DE924123C (en) Helicopter with a hub that can be tilted on all sides and a flywheel
DE102007035461B4 (en) Method of measuring angle of attack and gust velocity on an aircraft or missile
DE1039846B (en) Swiveling arrangement of a jet engine at the tip of an aircraft wing

Legal Events

Date Code Title Description
OP8 Request for examination as to paragraph 44 patent law
D2 Grant after examination
8327 Change in the person/name/address of the patent owner

Owner name: DEUTSCHE AEROSPACE AG, 8000 MUENCHEN, DE

8364 No opposition during term of opposition
8320 Willingness to grant licenses declared (paragraph 23)
8327 Change in the person/name/address of the patent owner

Owner name: DAIMLER-BENZ AEROSPACE AKTIENGESELLSCHAFT, 80804 M

8339 Ceased/non-payment of the annual fee