DE102006042575A1 - Rotor head unit for helicopter or surface airplane, has blade holders and bearing unit movably arranged to each other, where movability between bearing unit and blade holders is enabled totally or partially by solid joints - Google Patents
Rotor head unit for helicopter or surface airplane, has blade holders and bearing unit movably arranged to each other, where movability between bearing unit and blade holders is enabled totally or partially by solid joints Download PDFInfo
- Publication number
- DE102006042575A1 DE102006042575A1 DE200610042575 DE102006042575A DE102006042575A1 DE 102006042575 A1 DE102006042575 A1 DE 102006042575A1 DE 200610042575 DE200610042575 DE 200610042575 DE 102006042575 A DE102006042575 A DE 102006042575A DE 102006042575 A1 DE102006042575 A1 DE 102006042575A1
- Authority
- DE
- Germany
- Prior art keywords
- rotor head
- rotor
- bearing unit
- head unit
- bearing
- 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.)
- Withdrawn
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
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/12—Helicopters ; Flying tops
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
Description
Die
Erfindung beschreibt eine vereinfachte Rotorkopf- und Antriebseinheit
eines Hubschraubers oder Flächenflugzeugs.
In
Er
besteht aus einem Rumpf/Chassis (
Aufgabetask
Bisherige Konstruktionen weisen einige Nachteile auf. Die Anlenkung der Blätter soll möglichst leichtgängig, steif und spielfrei sein. Durch die Summe der Gelenke und Hebel ist das nur bedingt zu erreichen. Ein weiterer Aspekt ist die Gewichtsreduzierung. Durch die Trennung in Motor, Getriebe, Lagerung, Rotorwelle und Anlenkkonstruktion und die dazu Notwendige starre Verbindung dieser Teile über ein Chassis steigt das Gewicht der Konstruktion. Das Getriebe ist mit Verschleiß behaftet und führt zu Geräuschentwicklung. Der in Folge von Unfällen auftretende Reparaturaufwand steigt ebenfalls mit dem Umfang der Konstruktion an.Previous Constructions have some disadvantages. The articulation of the leaves should preferably smooth, be stiff and play free. By the sum of the joints and levers this is only partially achievable. Another aspect is the weight reduction. Due to the separation in engine, transmission, bearing, rotor shaft and Anlenkkonstruktion and the necessary rigid connection this Parts over one Chassis increases the weight of the construction. The transmission is with Wear and leads to noise. The result of accidents occurring repair costs also increases with the extent of Construction on.
Lösungsolution
Der
Kern der Erfindung besteht im Einsatz von Festkörpergelenken als Verbindung
zwischen Blatthaltern und einer der Taumelscheibe ähnlichen Lagereinheit
(
Technische
Ausführungen
können
in vielfältigen
Variationen der Erfindung entstehen. So können über je ein Festkörpergelenk
pro Blatthalter auch Rotoren mit mehr als zwei Blättern realisiert
werden. Dabei muss der Spurlauf pro Blatthalter getrennt einstellbar
sein. Im dargestellten Beispiel können die Festkörpergelenke
Grundsätzlich kann die Erfindung auch eingesetzt werden, wenn der Antrieb des Rotors über ein Antriebsmittel, z.B. Zahnräder oder Riemen, erfolgt. So kann ein großes Spektrum von Motoren verwendet werden.Basically The invention also be used when the drive of the rotor via a Drive means, e.g. gears or belt, takes place. So can a wide range of engines used become.
Durch den Einsatz von Festkörpergelenken können viele konstruktive Vorteile erzielt werden. Die Anzahl der Bauelemente sinkt, die Steifigkeit der Anlenkung und die Spielfreiheit werden verbessert. In Verbindung mit der Übertragung der Steuerbewegung im Zentrum der Lagereinheit entsteht eine enorm einfache und robuste Konstruktion. In Folge kann die Antriebseinheit einfach integriert und dadurch zusätzlich Gewicht eingespart werden.By The use of solid joints can be many constructive advantages are achieved. The number of components decreases, the rigidity of the linkage and the backlash become improved. In connection with the transfer of the tax movement In the center of the storage unit, a tremendously simple and robust system is created Construction. As a result, the drive unit can be easily integrated and in addition To save weight.
Als weitere Anwendung kann eine solche Konstruktion auch als Antriebseinheit für Flächenflugzeuge eingesetzt werden. Zur Anpassung von Motordrehzahl und Fluggeschwindigkeit sind Verstellpropeller, teilweise mit Umkehr der Schubrichtung, bekannt. Durch die zusätzliche zyklische Verstellmöglichkeit kann der Auftriebspunkt verlagert und so die Flug- oder Schwebelage gesteuert werden.When Another application can also be such a construction as a drive unit for surface aircraft be used. To adjust the engine speed and airspeed are variable pitch propellers, partly with reversal of the thrust direction, known. By the additional cyclic adjustment The buoyancy point can shift and so the flight or Schwebelage to be controlled.
Claims (10)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200610042575 DE102006042575A1 (en) | 2006-09-11 | 2006-09-11 | Rotor head unit for helicopter or surface airplane, has blade holders and bearing unit movably arranged to each other, where movability between bearing unit and blade holders is enabled totally or partially by solid joints |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200610042575 DE102006042575A1 (en) | 2006-09-11 | 2006-09-11 | Rotor head unit for helicopter or surface airplane, has blade holders and bearing unit movably arranged to each other, where movability between bearing unit and blade holders is enabled totally or partially by solid joints |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102006042575A1 true DE102006042575A1 (en) | 2008-03-27 |
Family
ID=39104594
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200610042575 Withdrawn DE102006042575A1 (en) | 2006-09-11 | 2006-09-11 | Rotor head unit for helicopter or surface airplane, has blade holders and bearing unit movably arranged to each other, where movability between bearing unit and blade holders is enabled totally or partially by solid joints |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102006042575A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2945269A1 (en) * | 2009-05-11 | 2010-11-12 | Univ Compiegne Tech | Rotor blades controlling device for small sized revolving wing i.e. drone, of helicopter, has supports carrying portion of electronic controls of actuators and connecting actuators to controls |
FR2956589A1 (en) * | 2010-02-23 | 2011-08-26 | Rene Felix Charles Kokkelink | Rotor head for helicopter i.e. radio controlled helicopter, has axles whose ends are attached on cyclic plate that is inclined in desired direction and directs pins of blades in same direction, and bars attached directly on pins of blades |
CN101869769B (en) * | 2008-04-21 | 2012-05-23 | 上海九鹰电子科技有限公司 | Mechanical maneuvering system of single-rotor wing model helicopter |
DE102012203978A1 (en) * | 2012-03-14 | 2013-09-19 | Zf Friedrichshafen Ag | Rotor blade control device |
WO2017125533A1 (en) * | 2016-01-20 | 2017-07-27 | Prox Dynamics As | A spring system varying stiffness with applied force for use in a torque dependent rotor of a rotary wing aircraft |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2088413A (en) * | 1934-03-29 | 1937-07-27 | Hafner Raoul | Helicopter and rotating wing aircraft |
DE1130298B (en) * | 1961-03-29 | 1962-05-24 | Dornier Werke Gmbh | Device for the automatic regulation of the general blade angle adjustment in helicopter rotors |
US3132697A (en) * | 1960-12-08 | 1964-05-12 | Donald J Cheesman | Helicopter control system |
DE2150761A1 (en) * | 1970-10-15 | 1972-06-15 | Westland Aircraft Ltd | Semi-rigid rotor assembly for rotary wing aircraft |
DE2644945A1 (en) * | 1975-10-13 | 1977-04-21 | Westland Aircraft Ltd | HELICOPTER ROTOR |
DE19915085C2 (en) * | 1998-05-28 | 2002-03-14 | Eurocopter Deutschland | Rotor blade for a bearingless rotor of a helicopter |
DE10052757A1 (en) * | 2000-10-25 | 2002-05-08 | Zf Luftfahrttechnik Gmbh | Rotor blade control device |
GB2387157A (en) * | 2002-02-05 | 2003-10-08 | Nigel Howard Mckrill | A rotor pitch control system for a rotating wing aircraft |
DE102004032530A1 (en) * | 2004-03-08 | 2005-10-06 | Stefan Reich | Rotorcraft and control |
-
2006
- 2006-09-11 DE DE200610042575 patent/DE102006042575A1/en not_active Withdrawn
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2088413A (en) * | 1934-03-29 | 1937-07-27 | Hafner Raoul | Helicopter and rotating wing aircraft |
US3132697A (en) * | 1960-12-08 | 1964-05-12 | Donald J Cheesman | Helicopter control system |
DE1130298B (en) * | 1961-03-29 | 1962-05-24 | Dornier Werke Gmbh | Device for the automatic regulation of the general blade angle adjustment in helicopter rotors |
DE2150761A1 (en) * | 1970-10-15 | 1972-06-15 | Westland Aircraft Ltd | Semi-rigid rotor assembly for rotary wing aircraft |
GB1310035A (en) * | 1970-10-15 | 1973-03-14 | Westland Aircraft Ltd | Semi-rigid rotor systems for rotary wing aircraft |
DE2644945A1 (en) * | 1975-10-13 | 1977-04-21 | Westland Aircraft Ltd | HELICOPTER ROTOR |
DE19915085C2 (en) * | 1998-05-28 | 2002-03-14 | Eurocopter Deutschland | Rotor blade for a bearingless rotor of a helicopter |
DE10052757A1 (en) * | 2000-10-25 | 2002-05-08 | Zf Luftfahrttechnik Gmbh | Rotor blade control device |
GB2387157A (en) * | 2002-02-05 | 2003-10-08 | Nigel Howard Mckrill | A rotor pitch control system for a rotating wing aircraft |
DE102004032530A1 (en) * | 2004-03-08 | 2005-10-06 | Stefan Reich | Rotorcraft and control |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101869769B (en) * | 2008-04-21 | 2012-05-23 | 上海九鹰电子科技有限公司 | Mechanical maneuvering system of single-rotor wing model helicopter |
FR2945269A1 (en) * | 2009-05-11 | 2010-11-12 | Univ Compiegne Tech | Rotor blades controlling device for small sized revolving wing i.e. drone, of helicopter, has supports carrying portion of electronic controls of actuators and connecting actuators to controls |
FR2956589A1 (en) * | 2010-02-23 | 2011-08-26 | Rene Felix Charles Kokkelink | Rotor head for helicopter i.e. radio controlled helicopter, has axles whose ends are attached on cyclic plate that is inclined in desired direction and directs pins of blades in same direction, and bars attached directly on pins of blades |
DE102012203978A1 (en) * | 2012-03-14 | 2013-09-19 | Zf Friedrichshafen Ag | Rotor blade control device |
US9669923B2 (en) | 2012-03-14 | 2017-06-06 | Zf Friedrichshafen Ag | Rotor blade control device |
WO2017125533A1 (en) * | 2016-01-20 | 2017-07-27 | Prox Dynamics As | A spring system varying stiffness with applied force for use in a torque dependent rotor of a rotary wing aircraft |
WO2017125489A1 (en) * | 2016-01-20 | 2017-07-27 | Prox Dynamics As | Resonant operating rotor assembly |
US10960974B2 (en) | 2016-01-20 | 2021-03-30 | FLIR Unmanned Aerial Systems AS | Resonant operating rotor assembly |
US11267569B2 (en) | 2016-01-20 | 2022-03-08 | FLIR Unmanned Aerial Systems AS | Spring system varying stiffness with applied force for use in a torque dependent rotor of a rotary wing aircraft |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
ON | Later submitted papers | ||
OP8 | Request for examination as to paragraph 44 patent law | ||
8120 | Willingness to grant licenses paragraph 23 | ||
R120 | Application withdrawn or ip right abandoned |
Effective date: 20120123 |