DE3510073A1 - Rotor having rotor-hub arms in the form of forks - Google Patents

Rotor having rotor-hub arms in the form of forks

Info

Publication number
DE3510073A1
DE3510073A1 DE19853510073 DE3510073A DE3510073A1 DE 3510073 A1 DE3510073 A1 DE 3510073A1 DE 19853510073 DE19853510073 DE 19853510073 DE 3510073 A DE3510073 A DE 3510073A DE 3510073 A1 DE3510073 A1 DE 3510073A1
Authority
DE
Germany
Prior art keywords
rotor
hub
plates
base body
blade
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
DE19853510073
Other languages
German (de)
Other versions
DE3510073C2 (en
Inventor
Karlheinz 8012 Ottobrunn Mautz
Alois 8011 Putzbrunn Schwarz
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 Helicopters Deutschland 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 DE19853510073 priority Critical patent/DE3510073A1/en
Publication of DE3510073A1 publication Critical patent/DE3510073A1/en
Application granted granted Critical
Publication of DE3510073C2 publication Critical patent/DE3510073C2/de
Granted legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors
    • B64C27/35Rotors having elastomeric joints
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors

Abstract

In the case of a rotor, especially of a rotary-wing aircraft, having a rotor hub with blade holders in each case in the form of a radially outwardly pointing rotor arm (2) in the form of a fork, whose fork limbs are components of two plates (6) which are held at a distance in a coaxial arrangement above a hub base body (5) and consist of fibre-composite synthetic material, in order to connect said plates (6), the hub base body (5) which consists of a material having a greater modulus of elasticity and greater shear modulus than the fibre-composite synthetic material is provided with two fixed flanges (5.1, 5.2), it being hollow and being expanded to form a housing jacket (for blade control means) which is only interposed between the plates (6), and the two fixed flanges (5.1, 5.2) forming the jacket edges. <IMAGE>

Description

Beschreibung description

Die Erfindung betrifft einen Rotor gemäß dem Oberbegriff des Patentanspruchs. The invention relates to a rotor according to the preamble of the patent claim.

Ein derartiger Rotor hat in einer Ausführungsform gemäß der nicht veröffentlichten DE-Patentanmeldung P 34 39 257.2 im Vergleich zu Ausführungsformen mit einer ganz oder überwiegend aus Metall bestehenden Rotornabe vor allem den Vorteil eines erheblich geringeren Gewichts bei ausreichend hoher Rahmensteifigkeit der Rotornabe. Jedoch ist diese gegenüber einer Rotornabe gemäß der DE-OS 30 37 824 nicht ohne weiteres als Gehäuse für Blattsteuermittel nutzbar. Such a rotor does not have in an embodiment according to FIG published DE patent application P 34 39 257.2 in comparison to embodiments with a rotor hub consisting entirely or predominantly of metal, the main advantage a significantly lower weight with a sufficiently high frame stiffness of the Rotor hub. However, this is compared to a rotor hub according to DE-OS 30 37 824 not readily usable as a housing for blade control means.

Der Erfindung liegt daher bei einem Rotor der eingangs genannten Art die Aufgabe zugrunde, diese Nutzungsmöglichkeit der Rotornabe ohne Minderung ihrer Rahmensteifigkeit zu schaffen. The invention therefore resides in a rotor of the type mentioned at the beginning Kind of based on the task, this possibility of using the rotor hub without reduction to create their frame stiffness.

Diese Aufgabe ist gemäß dem Kennzeichen des Patentanspruchs 1 gelöst in der Erkenntnis, daß auf den für eine Fassung der Platten (gemäß der vorgenannten De-Patentanmeldung) zwingenden schubstützenden Sitz derselben auf dem Nabengrundkörper bei größerer Stütz- bzw. Einspannweite desselben für die Platten verzichtet werden kann, daß also dann deren Schubstützung über einen Nabengrundkörper der erfindungsgemäßen Ausführungsform ausreichend gesichert ist. Zugleich hat der Verzicht auf diesen Plattensitz auf dem Nabengrundkörper zwangsläufig den Vorteil einer verminderten Schwächung der Platten hinsichtlich ihrer Funktion der Rotorantriebs-Momentenübertragung. This object is achieved according to the characterizing part of claim 1 Knowing that on the basis for a version of the plates (according to the aforementioned De-patent application) compulsory thrust-supporting seat of the same on the hub body in the case of a larger support or clamping width, the same for the plates can be dispensed with can, so that then their thrust support via a hub body of the invention Embodiment is sufficiently secured. At the same time, the waiver has to do this Insert seat on the hub body inevitably has the advantage of a reduced Weakening of the plates with regard to their function of the rotor drive torque transmission.

Die Erfindung wird nachfolgend anhand eines Ausführungsbeispiels näher erläutert. Hierzu zeigt die Zeichnung in einem vertikalen Längsschnitt einen Abschnitt der Rotornabe (auch sog. Rotorkopf) beispielsweise eines Vierblattrotors eines Drehflügelflugzeugs, bei dem die Halterung des einzelnen Rotorblattes 1 an der Rotornabe über je einen hieran radial auswärts gerichteten gabelförmigen Rotorarm 2 mittels eines in einer Ausnehmung der Blattwurzel zwischen dessen beiden Gabelschenkeln angeordneten Axial-Radial-Elastomerlagers 3 und die Abstützung des hierüber hinausgehenden Blattwurzelendes an der Rotornabe in Blattschlag- und Blattschwenkrichtung mittels eines Radial-Elastomerlagers 4 hergestellt ist. Eine derartige Blatthalterung ist z.B. durch die DE- PS 27 12 706 bekannt. The invention is explained below on the basis of an exemplary embodiment explained in more detail. For this purpose, the drawing shows a vertical longitudinal section Section of the rotor hub (also known as the rotor head), for example of a four-blade rotor a rotary wing aircraft, in which the holder of the individual rotor blade 1 on the rotor hub via a fork-shaped rotor arm directed radially outward therefrom 2 by means of a blade root in a recess between its two fork legs arranged axial-radial elastomer bearing 3 and the support of the beyond Blade root end on the rotor hub in blade flapping and blade pivoting direction by means of a radial elastomer bearing 4 is made. One such blade holder is e.g. from DE-PS 27 12 706 known.

Die Gabelschenkel sämtlicher Rotorarme 2 sind Bestandteile zweier in koaxialer Anordnung über einen Nabengrundkörper 5 auf Distanz gehaltenen Platten 6 aus Faserverbundkunststoff beispielsweise der in der eingangs genannten DE-OS beschriebenen Art. Für den Nabengrundkörper 5 ist ein Werkstoff gewählt, dessen Elastizitäts- und Schubmodul größer sind als diejenigen des Faserverbundkunststoffs beispielsweise besteht er aus Titan. The fork legs of all rotor arms 2 are components of two plates held at a distance in a coaxial arrangement via a hub base body 5 6th made of fiber-reinforced plastic, for example that described in the DE-OS mentioned at the beginning Art. For the hub body 5, a material is selected whose elasticity and shear modulus are greater than those of the fiber-reinforced plastic, for example it is made of titanium.

Um bei dieser zusammengesetzten Rotornabe die Blatteinstellwinkelsteuerung vom Nabenzentrum aus zu ermöglichen, ist der Nabengrundkörper 5 ein den Platten 6 nur zwischengefügter Gehäusemantel, dessen beide Ränder zu je einem Festflansch 5.1 und 5.2 geformt sind, Hierüber sind mittels Schraubenbolzen 7 der Nabengrundkörper 5 und die Platten 6 verbunden, wobei zugleich deren Verbindung mit einer Rotorantriebs-Hohlwelle 8 über den gegenüberliegenden Festflansch 5.1 bzw. die zugehörigen Schraubenbolzen 7 hergestellt ist. Aufgrund dieser Konfiguration ist bei der Rotornabe, deren Platten 6 zugleich die Funktion von Gehäusedeckeln erfüllen, die größtmögliche Rahmensteifigkeit erreicht. Zumal (außer für die Schraubenbolzen) lediglich für die an den Blattsteuerhebeln 9 angelenkten Steuerstangen 10( zu einer nicht dargestellten Taumelscheibe) Durchgangsbohrungen nur in einer der Platten 6 vorzusehen sind. In order to control the pitch angle of this assembled rotor hub To enable the hub center from, the hub body 5 is the plates 6 only interposed housing jacket, both edges of which each have a fixed flange 5.1 and 5.2 are shaped, the hub base body is over this by means of screw bolts 7 5 and the plates 6 connected, at the same time their connection to a rotor drive hollow shaft 8 via the opposite fixed flange 5.1 or the associated screw bolts 7 is established. Because of this configuration, the rotor hub has its plates 6 at the same time fulfill the function of housing covers, the greatest possible frame rigidity achieved. Especially since (except for the screw bolts) only for those on the blade control levers 9 articulated control rods 10 (to a swash plate, not shown) through holes are only to be provided in one of the plates 6.

- Leereite -- void -

Claims (1)

Patentanspruch Rotor. insbesondere eines Drehflügelflugzeugs, mit einer Rotornabe mit Blatthalterungen jeweils in Form eines radial auswärts gerichteten gabelförmigen Rotorarmes, dessen Gabelschenkel Bestandteile zweier in koaxialer Anordnung über einen Nabengrundkörper auf Distanz gehaltenen Platten aus Faserverbundkunststoff sind, wobei zu deren Verbindung der aus einem dem Faserverbundkunststoff gegenüber einen größeren Elastizitäts-und größeren Schubmodul aufweisenden Werkstoff bestehende Nabengrundkörper hohl und mit zwei Festflanschen versehen ist, dadurch gekennzeichnet, daß der Nabengrundkörper (5) zu einem den Platten (6) nur zwischengefügten Gehäusemantel (für Blattsteuermittel) erweitert ist, wobei die beiden Festflansche (5.1, 5.2) die Mantelränder bilden.Claim rotor. in particular a rotary wing aircraft, with a rotor hub with blade holders each in the form of a radially outwardly directed fork-shaped rotor arm, the fork legs components of two in coaxial Arrangement via a hub base body held at a distance from plates made of fiber composite plastic are, with the connection of one of the fiber-reinforced plastic opposite a material having a greater elasticity and greater shear modulus The hub body is hollow and provided with two fixed flanges, characterized in that that the hub base body (5) to a housing jacket which is only inserted between the plates (6) (for blade control means) is extended, whereby the two fixed flanges (5.1, 5.2) form the edges of the jacket.
DE19853510073 1985-03-20 1985-03-20 Rotor having rotor-hub arms in the form of forks Granted DE3510073A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19853510073 DE3510073A1 (en) 1985-03-20 1985-03-20 Rotor having rotor-hub arms in the form of forks

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19853510073 DE3510073A1 (en) 1985-03-20 1985-03-20 Rotor having rotor-hub arms in the form of forks

Publications (2)

Publication Number Publication Date
DE3510073A1 true DE3510073A1 (en) 1986-09-25
DE3510073C2 DE3510073C2 (en) 1988-06-09

Family

ID=6265809

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19853510073 Granted DE3510073A1 (en) 1985-03-20 1985-03-20 Rotor having rotor-hub arms in the form of forks

Country Status (1)

Country Link
DE (1) DE3510073A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2760425A1 (en) * 1997-03-06 1998-09-11 Rene Mouille HUB FOR AN AIRCRAFT ROTOR HEAD WITH A TURNING WING AND ROTOR HEAD COMPRISING SUCH A HUB
DE19837802C1 (en) * 1998-08-20 1999-10-28 Eurocopter Deutschland Blade hub for rotor of helicopter

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE702159C (en) * 1938-01-19 1941-01-31 E H Henrich Focke Dr Ing Adjustment gear for screwdriver rotors
FR2402578A1 (en) * 1977-09-07 1979-04-06 Westland Aircraft Ltd HELICOPTER ROTOR, AND HELICOPTER WITH SUCH ROTOR
GB2040850A (en) * 1978-05-17 1980-09-03 Westland Aircraft Ltd Helicopter rotor
DE2919595A1 (en) * 1978-05-17 1981-04-30 Westland Aircraft Ltd., Yeovil, Somerset HELICOPTER ROTOR
DE3037824A1 (en) * 1977-03-23 1982-05-19 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Reinforced rotor blade head - has elastic loops around opposing pairs of blade mountings
DE2712706C2 (en) * 1977-03-23 1983-06-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Rotor of a rotary wing aircraft
DE3439257C2 (en) * 1984-10-26 1986-10-23 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Rotor, especially for a rotary wing aircraft

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE702159C (en) * 1938-01-19 1941-01-31 E H Henrich Focke Dr Ing Adjustment gear for screwdriver rotors
DE3037824A1 (en) * 1977-03-23 1982-05-19 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Reinforced rotor blade head - has elastic loops around opposing pairs of blade mountings
DE2712706C2 (en) * 1977-03-23 1983-06-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Rotor of a rotary wing aircraft
FR2402578A1 (en) * 1977-09-07 1979-04-06 Westland Aircraft Ltd HELICOPTER ROTOR, AND HELICOPTER WITH SUCH ROTOR
GB2040850A (en) * 1978-05-17 1980-09-03 Westland Aircraft Ltd Helicopter rotor
DE2919595A1 (en) * 1978-05-17 1981-04-30 Westland Aircraft Ltd., Yeovil, Somerset HELICOPTER ROTOR
US4297078A (en) * 1978-05-17 1981-10-27 Westland Aircraft Limited Helicopter rotors
DE3439257C2 (en) * 1984-10-26 1986-10-23 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Rotor, especially for a rotary wing aircraft

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2760425A1 (en) * 1997-03-06 1998-09-11 Rene Mouille HUB FOR AN AIRCRAFT ROTOR HEAD WITH A TURNING WING AND ROTOR HEAD COMPRISING SUCH A HUB
WO1998039206A1 (en) * 1997-03-06 1998-09-11 Mouille Rene Hub for rotor head of rotary wing aircraft and rotor head with such hub
US6200097B1 (en) 1997-03-06 2001-03-13 MOUILLE RENé Hub for rotor head of rotary-wing aircraft and rotor head with such hub
DE19837802C1 (en) * 1998-08-20 1999-10-28 Eurocopter Deutschland Blade hub for rotor of helicopter
EP0980824A3 (en) * 1998-08-20 2001-05-16 Eurocopter Deutschland GmbH Rotorblade for a bearingless helicopter rotor

Also Published As

Publication number Publication date
DE3510073C2 (en) 1988-06-09

Similar Documents

Publication Publication Date Title
DE2922469C2 (en) Rotor for a rotary wing aircraft
DE2829605C2 (en) Rotor hub
DE3001207C2 (en) Articulated rotor for helicopters
DE2328149C2 (en) Helicopter rotor
DE2755557C2 (en) Rotor head for a helicopter rotor
DE2800075A1 (en) HELICOPTER CROSS HOLDER ROTOR
DE2903524C2 (en) Flapping and swivel jointless connection of rotor blades of a rotary wing aircraft
DE1556414B2 (en) ROTOR FOR ROTARY WING AIRPLANES
DE3241754A1 (en) ROTOR, ESPECIALLY A ROTATING PLANE
DE2645174C2 (en) Rotor head for a non-flapping and swivel-jointless rotor
DE2838792A1 (en) HELICOPTER
DE2712706C2 (en) Rotor of a rotary wing aircraft
DE2919684B2 (en) Flapping, swiveling and blade adjustment jointless rotor
DE3244725C1 (en) Rotor blade made of fiber composite plastic
DE60201762T2 (en) Gear arrangement for a aircraft rotor with constant speed
DE3926878C2 (en)
DE3620794A1 (en) Control device for rotor blade adjustment, especially of a rotary wing aircraft
DE3510073A1 (en) Rotor having rotor-hub arms in the form of forks
DE2932441C2 (en) Damping device for a rotor blade
EP0695245B1 (en) Wiper arrangement with a rotatable wiper arm in addition to the reciprocating movement
DE3639168A1 (en) HELICOPTER MAIN ROTOR
DE2945195A1 (en) HELICOPTER ROTOR
DE2538304A1 (en) SEMI-RIGID ROTOR ARRANGEMENT FOR ROTARY-WING AIRCRAFT
DE3021280C2 (en)
DE10037539B4 (en) Adjustable swivel rotor down stop with low height

Legal Events

Date Code Title Description
8110 Request for examination paragraph 44
D2 Grant after examination
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: EUROCOPTER DEUTSCHLAND GMBH, 8012 OTTOBRUNN, DE

8339 Ceased/non-payment of the annual fee