WO2004085248A1 - Drillelement für einen lagerlosen rotor - Google Patents
Drillelement für einen lagerlosen rotor Download PDFInfo
- Publication number
- WO2004085248A1 WO2004085248A1 PCT/EP2003/014215 EP0314215W WO2004085248A1 WO 2004085248 A1 WO2004085248 A1 WO 2004085248A1 EP 0314215 W EP0314215 W EP 0314215W WO 2004085248 A1 WO2004085248 A1 WO 2004085248A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- drill element
- cross
- drill
- webs
- rotor
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/33—Rotors having flexing arms
Definitions
- the present invention relates to a drilling element for a bearingless rotor.
- the invention further relates to a bearingless rotor with such a drilling element and a rotary wing aircraft, in particular a helicopter, with such a rotor.
- EP 0 323 857 B1 discloses a bending plate to be attached to a rotor mast, comprising a rotor mast fastening section, a rotor blade fastening section in the form of two bushes arranged at a free end of the bending plate, and one between the rotor mast fastening section and the rotor blade fastening section located swiveling and torsionally soft intermediate area, which forms a drilling element.
- the drilling element has an approximately H-shaped cross section, which is formed from a central, strip-shaped element and two elements arranged laterally thereto, each of which has a cross-sectional shape in the shape of a lying Y. The legs of the Y-shaped cross-sectional area are spread apart.
- the H-shaped cross section or its composite individual elements have an essentially constant material thickness.
- the bending plate is largely made of fiber composite material. Due to the H-shaped cross-sectional design and the strong spreading of the legs of the Y-shaped cross-sectional area, the cross-sectional profile may be warped in an unfavorable manner if the twist element is twisted.
- a yoke to be attached to a rotor mast comprising a rotor mast fastening section, an adjoining plate-shaped, impact-resistant region, a rotor blade fastening section in the form of two bushes arranged at a free end of the yoke, and one between the impact-free area and the rotor blade fastening section, the swiveling and torsion-soft intermediate area, which forms a drill element.
- the drilling element has a star-shaped cross-section with six webs or arms (referred to as "flanges" there).
- the webs which have an essentially constant material thickness, are arranged so that they are spread apart relatively to one another.
- the yoke is largely made of fiber composite material.
- the individual webs have An outer layer made of a fiber fabric Due to the explained cross-sectional design and the strong spreading of the webs or arms, the cross-sectional profile can be warped in an unfavorable manner if the twist element is twisted.
- DE-OS-2917301 discloses a bearingless rotor with a structure element which is soft in terms of impact, swivel and torsion.
- the torsional softness gives the structural element, in addition to the impact and swivel-soft properties, the property of a drill element.
- This drill element has an essentially T-shaped or cruciform cross-sectional shape.
- the individual webs or arms of the T-shaped or cross-shaped cross section, which have a substantially constant thickness, are slotted.
- the drilling elements are designed to be sufficiently pivot-resistant and stable, the drilling elements would no longer be sufficiently rotatable due to the resulting excessive torsional or drilling rigidity, which can have a disadvantageous effect, in particular, on the controllability of a rotor equipped with such a drilling element.
- such drill elements have a very high weight and a very large overall cross section, which is not desirable both for aerodynamic reasons and in view of the lowest possible empty weight of a rotary wing aircraft.
- the object of the invention is to provide a compact drill element with a high swivel rigidity with low torsional or drill rigidity and at the same time high torsion or drill strength. Furthermore, a bearingless rotor and a rotary wing aircraft with such a drilling element are to be provided.
- a drilling element according to the invention having the features of claim 1.
- This drill element for a bearingless rotor which is largely made of fiber composite material, has an essentially symmetrical, flattened drill element cross-sectional shape, which has approximately the outline shape of a lying, central double conical section.
- the outline has a shape similar to a "fly” or a lying hourglass, or the shape of two narrow, lying, essentially isosceles triangles, which are connected to each other in the area of their facing tips.
- the outline shape as X-shaped, but the areas between two adjacent legs of the "X" are largely filled with fiber composite material.
- the drill element according to the invention has a very high swivel rigidity with low torsional or drill rigidity and a high torsion or drill strength. It is largely free from warping when twisted. At the same time, the drill element according to the invention has a comparatively compact overall cross section with high strength. The drill element according to the invention is therefore particularly suitable for tilt rotor applications. Because the twist element according to the invention, as mentioned above, is very easy to twist, it can also be considerably shorter than previously known for a given twist angle range Drill elements are designed. The length of the drilling element according to the invention can be reduced to approximately one third of the length of a conventional, previously known drilling element.
- the above-mentioned object is achieved by a bearingless rotor with the features of claim 14. Furthermore, the above-mentioned object is achieved according to a third aspect by an inventive rotary-wing aircraft with the features of claim 15.
- the figure shows a schematic cross-sectional representation of a drilling element according to the invention.
- the figure shows a schematic cross-sectional illustration of a drilling element 2 according to the invention for a bearingless rotor.
- the drilling element 2 is largely made of fiber composite material. As can be clearly seen in the drawing, it has a symmetrical, flattened drill element cross-sectional shape, which has approximately the outline shape of a lying, central double conic section.
- the horizontal central axis of the drill element cross section is identified by the reference symbol H and the vertical central axis by the reference symbol V.
- the outline of the drill element cross-section has approximately the shape of two relatively narrow, lying, essentially isosceles triangles, which are aligned symmetrically to the horizontal and vertical central axis H, V and are connected to one another in the region of their mutually facing tips.
- the longitudinal direction or longitudinal axis of the drilling element is indicated by the reference symbol A.
- the longitudinal axis A preferably runs radially to the rotor circle of the rotor or extends essentially parallel to the longitudinal direction of a rotor blade of the rotor.
- the previously described drill element cross-sectional shape is formed by two similar groups (s1 to S3 and S4 to S6) of webs S1 to S6 which are laterally opposite one another in mirror symmetry about the vertical central axis V.
- the webs S1 to S6 have a common, thin, flattened root region 4, which extends in a region around the longitudinal axis A and represents a central section of the drill element cross-sectional shape.
- the webs S1 to S6 open into this root area 4 or proceed from this.
- the webs S1 to S6 of a respective group (S1 to S3 and S4 to S6) are arranged on each side of the vertical axis V separated from one another by narrow intermediate gaps 6.
- the thickness of the respective webs S1 to S6 increases from the root area 4 outwards to the free lateral side edges of the drilling element 2.
- the webs S1 to S6 have a very small spread relative to each other.
- the webs S1 to S6 themselves each have a wedge-shaped cross-sectional shape in the manner of a lying or slightly inclined narrow triangle, the tip of which opens into the root region 4.
- the webs S1 to S6 in this exemplary embodiment not only have unidirectional, highly stretchable reinforcing fiber packages 8, which are arranged in a suitable matrix, e.g., in the area of the lateral sides of the drill element cross-sectional shape, but essentially over their almost entire wedge-shaped cross-sectional shape. an epoxy resin, are embedded and also have a largely wedge-shaped cross-sectional shape with an outwardly increasing thickness.
- the fibers of the unidirectional reinforcement fiber packs 8 run in the longitudinal direction A of the twist element 2 and thus in the direction of the centrifugal force of a rotor blade (not shown) associated with the twist element 2 of the rotor.
- the unidirectional reinforcement fiber packs 8 extend to the outer contour of the drill element cross section.
- the unidirectional reinforcing fiber packages 8 on the outer contour of the drill element cross section are therefore not covered or overlaminated by a fiber fabric cover layer or the like which has a multidirectional fiber arrangement.
- the fibers of the unidirectional reinforcement fiber bundles 8 are preferred
- the reinforcing fiber packs 8 can additionally contain a small proportion of other types of fiber or even be made from other types of fiber.
- the fibers of the unidirectional reinforcing fiber bundles 8 lie in the cross-sectional areas of the twist element 2 that are most stretched during rotor operation due to pivoting movements of the rotor blade and can absorb very high loads here.
- the previously mentioned embodiment of the drill element cross section and in particular its webs S1 to S6 and unidirectional reinforcing fiber packages 8 thus ensures that a high pivoting stiffness can be achieved despite a comparatively small width of the drill element cross section.
- the webs S1 to S6 are each slotted in the longitudinal direction of the drilling element 2.
- a slot 10 is provided in this embodiment.
- the respective slot 10 extends from a free lateral side edge of the drill element cross-sectional shape in the direction of the root region 4 and ends shortly before this.
- the slots 10 of the upper and lower webs S1, S3 and S4, S6 have the same depth, while the slots 10 of the respective middle webs S2 and S5 have a smaller depth.
- the slots 10 are essentially rectilinear.
- the respective slot longitudinal axes or their extensions preferably intersect at the center (here: longitudinal axis A) of the overall cross-sectional shape of the drill element, as in the present exemplary embodiment, in the immediate vicinity of the center through the root region 4.
- the slot 10 of a respective web S1 to S6 runs between (at least) two adjacent unidirectional reinforcing fiber packs 8.
- a respective web S1 to S6 has at least one reinforcing fiber fabric layer 12 which, starting from a lateral slot opening, is U-shaped or loop-shaped around a slot floor 10a and the slot contour located within the web S1 to S ⁇ .
- This U-shaped or loop-shaped reinforcing fiber fabric layer 12 is thus located between two adjacent unidirectional reinforcing fiber packs 8 and is glued or laminated to them.
- two webs S1, S6 and S3, S4, which face each other in pairs on the top and bottom of the drill element cross-sectional shape, are equipped with at least one reinforcing fiber layer 14 that extends across the width of the respective web S1, S3 and extends continuously over the root area 4 to the other, opposite web S6, S4 and across its width.
- the reinforcing fiber layer 14 is preferably a fiber fabric. It can be seen from the drawing that the respective reinforcing fiber layer 14 (top and bottom) in the root area 4 extends to the outer contour of the drill element cross section.
- the lateral side surfaces of the webs S1 to S6 are chamfered above and below the horizontal central axis H towards the vertical central axis V or slightly inclined by an angle ⁇ .
- the number of webs can vary and assume a lower or higher number than the six webs S1 to S6 described above.
- the drill element 2 is preferably an integral part of a rotor blade, a rotor blade connecting element, a rotor blade connecting element or a rotor head element (e.g. a rotor head plate or a rotor head yoke). However, it can also be designed as a separate component.
- the drill element 2 can have connection elements at its end regions for connecting adjacent components (e.g. for a rotor blade if the drill element is designed as a separate component or as an integral component of a rotor head element).
- the drill element 2 according to the invention is particularly suitable as a component of a bearingless rotor.
- a rotary wing aircraft in particular a helicopter, in particular a tilt rotor helicopter, is equipped with at least one bearingless rotor and with at least one such drilling element 2.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03789273A EP1606162B1 (de) | 2003-03-27 | 2003-12-13 | Drillelement für einen lagerlosen rotor |
AU2003293878A AU2003293878A1 (en) | 2003-03-27 | 2003-12-13 | Drilling element for a bearingless rotor |
DE50307496T DE50307496D1 (de) | 2003-03-27 | 2003-12-13 | Drillelement für einen lagerlosen rotor |
US10/551,007 US7296975B2 (en) | 2003-03-27 | 2003-12-13 | Twist element for a bearingless rotor |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10313982.6 | 2003-03-27 | ||
DE10313982A DE10313982B4 (de) | 2003-03-27 | 2003-03-27 | Drillelement für einen lagerlosen Rotor |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004085248A1 true WO2004085248A1 (de) | 2004-10-07 |
Family
ID=33038789
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2003/014215 WO2004085248A1 (de) | 2003-03-27 | 2003-12-13 | Drillelement für einen lagerlosen rotor |
Country Status (5)
Country | Link |
---|---|
US (1) | US7296975B2 (de) |
EP (1) | EP1606162B1 (de) |
AU (1) | AU2003293878A1 (de) |
DE (2) | DE10313982B4 (de) |
WO (1) | WO2004085248A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2899121A1 (de) | 2014-01-22 | 2015-07-29 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Flexbeam-Einheit für einen lagerlosen oder scharnierlosen und lagerlosen mehrflügeligen Rotor eines Drehflüglers |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2246256B1 (de) * | 2009-04-29 | 2012-10-24 | Eurocopter Deutschland GmbH | Element zur Übertragung des Spannungsdrehmoments für eine Fenestronschaufel und Herstellungsverfahren dafür |
DE102017124598A1 (de) * | 2017-10-20 | 2019-04-25 | Wobben Properties Gmbh | Rotorblatt und Rotor für eine Windenergieanlage, mit einer lagerlosen Pitchverstellung und Windenergieanlage |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2917301A1 (de) | 1979-04-28 | 1980-10-30 | Messerschmitt Boelkow Blohm | Lagerloser rotor |
US4650401A (en) * | 1983-04-07 | 1987-03-17 | Mcdonnell Douglas Helicopter Company | Flat strap cruciform flexure for helicopter rotor systems |
FR2608554A1 (fr) * | 1986-12-19 | 1988-06-24 | Messerschmitt Boelkow Blohm | Rotor, notamment pour aeronefs a voilure tournante |
EP0323857A2 (de) | 1988-01-08 | 1989-07-12 | Fuji Jukogyo Kabushiki Kaisha | Biegeplatte eines Hubschrauberrotorblattes und deren Fertigungsverfahren |
US5358381A (en) | 1993-03-19 | 1994-10-25 | Bell Helicopter Textron Inc. | Yoke for helicopter rotor systems |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4191463B2 (ja) * | 2002-12-03 | 2008-12-03 | 富士重工業株式会社 | フレックスビーム |
-
2003
- 2003-03-27 DE DE10313982A patent/DE10313982B4/de not_active Expired - Fee Related
- 2003-12-13 EP EP03789273A patent/EP1606162B1/de not_active Expired - Fee Related
- 2003-12-13 DE DE50307496T patent/DE50307496D1/de not_active Expired - Lifetime
- 2003-12-13 WO PCT/EP2003/014215 patent/WO2004085248A1/de active IP Right Grant
- 2003-12-13 US US10/551,007 patent/US7296975B2/en not_active Expired - Fee Related
- 2003-12-13 AU AU2003293878A patent/AU2003293878A1/en not_active Abandoned
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2917301A1 (de) | 1979-04-28 | 1980-10-30 | Messerschmitt Boelkow Blohm | Lagerloser rotor |
US4650401A (en) * | 1983-04-07 | 1987-03-17 | Mcdonnell Douglas Helicopter Company | Flat strap cruciform flexure for helicopter rotor systems |
FR2608554A1 (fr) * | 1986-12-19 | 1988-06-24 | Messerschmitt Boelkow Blohm | Rotor, notamment pour aeronefs a voilure tournante |
EP0323857A2 (de) | 1988-01-08 | 1989-07-12 | Fuji Jukogyo Kabushiki Kaisha | Biegeplatte eines Hubschrauberrotorblattes und deren Fertigungsverfahren |
US5358381A (en) | 1993-03-19 | 1994-10-25 | Bell Helicopter Textron Inc. | Yoke for helicopter rotor systems |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2899121A1 (de) | 2014-01-22 | 2015-07-29 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Flexbeam-Einheit für einen lagerlosen oder scharnierlosen und lagerlosen mehrflügeligen Rotor eines Drehflüglers |
US10029784B2 (en) | 2014-01-22 | 2018-07-24 | Airbus Helicopters Deutschland GmbH | Flexbeam unit for a bearingless or a hinge- and bearingless multi-blade rotor of a rotary wing aircraft |
Also Published As
Publication number | Publication date |
---|---|
DE10313982B4 (de) | 2009-04-09 |
DE50307496D1 (de) | 2007-07-26 |
AU2003293878A1 (en) | 2004-10-18 |
US20060193727A1 (en) | 2006-08-31 |
EP1606162B1 (de) | 2007-06-13 |
US7296975B2 (en) | 2007-11-20 |
DE10313982A1 (de) | 2004-10-28 |
EP1606162A1 (de) | 2005-12-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE2451860C3 (de) | Rotorblatt für Drehflügelflugzeuge | |
EP0019041B1 (de) | Gelenkeloser Rotor | |
DE2942519A1 (de) | Gabelkopf zur befestigung von rotorblaettern an einem hubschrauber-rotormast | |
DE2421764A1 (de) | Rotor fuer drehfluegel-flugzeuge | |
DE2829605A1 (de) | Rotornabe | |
DE2645174C2 (de) | Rotorkopf für einen schlag- und schwenkgelenklosen Rotor | |
EP0019047B1 (de) | Schlag-, schwenk- und blattverstellgelenkloser Mehrblattrotor für ein Drehflügelflugzeug | |
EP1613534B1 (de) | Rotor sowie drehflügelflugzeug mit einem derartigen rotor | |
DE60204787T2 (de) | Konstruktionsteile für flugzeug | |
DE2611245C2 (de) | Rotor für Drehflügelflugzeuge | |
DE2733101C3 (de) | Schlag- und schwenkgelenklose Rotorblattlagerung | |
EP1606162B1 (de) | Drillelement für einen lagerlosen rotor | |
EP0165394B1 (de) | Bauelement zur Übertragung von Drehmomenten | |
EP1613533B1 (de) | Gelenkloser rotor sowie drehfl gelflugzeug mit einem solchen rotor | |
DE2541998A1 (de) | Blattanschluss an eine rotornabe | |
DE10316092B4 (de) | Gelenkloser Rotor mit plattenförmigem Rotorkopfelement | |
DE10316093B4 (de) | Rotor für ein Drehflügelflugzeug sowie Verfahren zur Blattwinkelverstellung eines Rotors | |
DE2945195A1 (de) | Hubschrauberrotor | |
DE202019101994U1 (de) | Rotoranordnung | |
DE1478107A1 (de) | Schi | |
DE7928619U1 (de) | Knotenblech fuer holzgitterkonstruktionen zur herstellung von hallenartigen bauten |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ OM PH PL PT RO RU SC SD SE SG SK SL TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
DFPE | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101) | ||
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
WWE | Wipo information: entry into national phase |
Ref document number: 2003789273 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2006193727 Country of ref document: US Ref document number: 10551007 Country of ref document: US |
|
WWP | Wipo information: published in national office |
Ref document number: 2003789273 Country of ref document: EP |
|
WWP | Wipo information: published in national office |
Ref document number: 10551007 Country of ref document: US |
|
NENP | Non-entry into the national phase |
Ref country code: JP |
|
WWW | Wipo information: withdrawn in national office |
Country of ref document: JP |
|
WWG | Wipo information: grant in national office |
Ref document number: 2003789273 Country of ref document: EP |