DE29502541U1 - Rotor head for rotary wing aircraft - Google Patents
Rotor head for rotary wing aircraftInfo
- Publication number
- DE29502541U1 DE29502541U1 DE29502541U DE29502541U DE29502541U1 DE 29502541 U1 DE29502541 U1 DE 29502541U1 DE 29502541 U DE29502541 U DE 29502541U DE 29502541 U DE29502541 U DE 29502541U DE 29502541 U1 DE29502541 U1 DE 29502541U1
- Authority
- DE
- Germany
- Prior art keywords
- rotor
- rotor head
- wing aircraft
- rotary wing
- plane
- 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 - Lifetime
Links
- 230000000087 stabilizing effect Effects 0.000 claims description 5
- 238000011105 stabilization Methods 0.000 description 7
- 230000006641 stabilisation Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 2
- 206010038743 Restlessness Diseases 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- B64C27/625—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including rotating masses or servo rotors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Retarders (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Besch reibungDescription
Rotorkopf für DrehflüglerRotor head for rotary wing aircraft
Rotorkopfzentralstücke üblicher Bauart (Fig. 3 u. 4), z. B. bei ferngesteuerten Industriehubschraubern und Modellhubschrauber^ sind aus einem Stück gefertigt. Die Stabilisierungsebene (1) und die Rotorebe (2) sind in der Draufsicht um genau 90 Grad versetzt.Rotor head central pieces of the usual design (Fig. 3 and 4), e.g. in remote-controlled industrial helicopters and model helicopters^ are made from one piece. The stabilization plane (1) and the rotor plane (2) are offset by exactly 90 degrees in the top view.
Nach bekannter Theorie wirkt die Rotorsteuerung, aufgrund der Kreiselwirkung, in der Rotorkreisebene 90 Grad später. Bei einem von oben gesehen linksdrehenden Rotor, muß z. B. das Rotorblatt links vom Hubschrauber angestellt werden, damit der Hubschrauber nach vorne kippt, da die Wirkung 90 Grad später erfolgt.According to known theory, the rotor control, due to the gyroscopic effect, acts 90 degrees later in the rotor circle plane. For example, with a rotor that rotates to the left when viewed from above, the rotor blade must be set to the left of the helicopter so that the helicopter tilts forward, since the effect occurs 90 degrees later.
Der im Schutzanspruch angegebenen Erfindung liegt das Problem zugrunde, daß in der Praxis dieser Winkel nicht stimmt und um mehrere Grad abweicht. Der Grund dafür ist z. B. der Blattschwerpunkt. Diese Abweichung wird durch den Piloten bei der Steuerung korrigiert bzw. bei der Taumelscheibeneinstellung berücksichtigt. Wird nun eine starke Eigenstabilisierung verwendet, z. B. Stabilisierungsstange mit Gewichten oder Umlenkhebel zur Verstärkung, wird das Aussteuern fast aller äußeren Einflüsse (z. B. Windböen) durch diese Stabilisierung, ohne Zutun des Piloten vorgenommen. Hier ist diese Abweichung jedoch nicht berücksichtigt, da Stabiiisierungsstange und Rotorblätter nach üblicher Bauart um 90 Grad versetzt sind. Beim herkömmlichen System kann eine Störung auch durch die Stabilisierung nicht ganz beseitigt werden, da die Korrektur nicht genau entgegengesetzt erfolgt. Die verbleibende Unruhe muß wieder durch den Piloten ausgesteuert werden.The invention specified in the protection claim is based on the problem that in practice this angle is incorrect and deviates by several degrees. The reason for this is, for example, the center of gravity of the blade. This deviation is corrected by the pilot during control or taken into account when adjusting the swash plate. If a strong self-stabilization is used, e.g. a stabilization rod with weights or a bellcrank for reinforcement, almost all external influences (e.g. gusts of wind) are compensated for by this stabilization, without the pilot having to do anything. However, this deviation is not taken into account here, since the stabilization rod and rotor blades are offset by 90 degrees according to the usual design. In the conventional system, a disturbance cannot be completely eliminated even by stabilization, since the correction is not carried out in exactly the opposite way. The remaining unrest must again be compensated for by the pilot.
Mit der Erfindung wird erreicht, daß die Wirkrichtung der Stabilisierungsstange exakt an die Erfordernisse der Rotorkreisebene angepaßt werden kann. Dies erfolgt durch Verdrehen des Rotorzentralstücks zwischen Rotorkreisebene und Stabilisierungsebene mit anschließender Justierung in der erforderlichen Position. Für die Funktion der Erfindung ist es unerheblich, ob sich die Stabilisierungsebene oberhalb oder unterhalb (bei einigen Rotorsystemen üblich) der Rotorkreisebene befindet.The invention ensures that the direction of action of the stabilizing rod can be adapted exactly to the requirements of the rotor circle plane. This is done by rotating the rotor center piece between the rotor circle plane and the stabilizing plane and then adjusting it to the required position. For the function of the invention, it is irrelevant whether the stabilizing plane is above or below (common in some rotor systems) the rotor circle plane.
Das gleiche Ergebnis wird mit einer Ausführung nach Schutzanspruch 2 erreicht. Hier wird z. B. ein in Versuchen erflogener oder auch berechneter Winkelversatz, der nicht genau 90 Grad beträgt, bereits bei der Fertigung berücksichtigt und das Zentralstück kann aus einem Stück gefertigt werden. Dies ist z. B. sinnvoll, wenn immer die gleichen Rotorblätter verwendet werden und ein Einstellfehler durch den Anwender ausgeschlossen werden soll.The same result is achieved with a design according to claim 2. Here, for example, an angular offset that is not exactly 90 degrees and is flown in tests or calculated is already taken into account during production and the central piece can be made from one piece. This is useful, for example, if the same rotor blades are always used and setting errors by the user are to be excluded.
Ein Ausführungsbeispiel der Erfindung wird anhand der Figuren 2 und 3 erläutert.An embodiment of the invention is explained with reference to Figures 2 and 3.
Figur 2:Figure 2:
Eine Störung, z. B. Windböe, erfolgt aus Richtung C. Durch die angepaßte virtuelle Drehung der Stabilisierungsebene erfolgt die Korrektur genau entgegengesetzt zur Störung in Richtung D. Die Unruhe wird vollkommen beseitigt.A disturbance, e.g. a gust of wind, comes from direction C. Due to the adapted virtual rotation of the stabilization plane, the correction is made exactly opposite to the disturbance in direction D. The disturbance is completely eliminated.
Figur 3:Figure 3:
Beim herkömmlichen System wird die Störung in einem anderen Winkel korrigiert, also nicht in die Richtung, aus der sie gekommen ist. Das System wird nie vollkommen ruhig laufen.In the conventional system, the disturbance is corrected at a different angle, i.e. not in the direction from which it came. The system will never run completely smoothly.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE29502541U DE29502541U1 (en) | 1995-02-16 | 1995-02-16 | Rotor head for rotary wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE29502541U DE29502541U1 (en) | 1995-02-16 | 1995-02-16 | Rotor head for rotary wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE29502541U1 true DE29502541U1 (en) | 1995-04-06 |
Family
ID=8003988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DE29502541U Expired - Lifetime DE29502541U1 (en) | 1995-02-16 | 1995-02-16 | Rotor head for rotary wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE29502541U1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0727350A1 (en) * | 1995-02-15 | 1996-08-21 | Bruno Ziegler | Rotorcraft with gyroscopic rotor stabilisation |
| DE19524793A1 (en) * | 1995-02-15 | 1996-08-22 | Bruno Ziegler | Rotary wing with gyro stabilization of the rotor |
-
1995
- 1995-02-16 DE DE29502541U patent/DE29502541U1/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0727350A1 (en) * | 1995-02-15 | 1996-08-21 | Bruno Ziegler | Rotorcraft with gyroscopic rotor stabilisation |
| DE19524793A1 (en) * | 1995-02-15 | 1996-08-22 | Bruno Ziegler | Rotary wing with gyro stabilization of the rotor |
| DE19524793C2 (en) * | 1995-02-15 | 1998-07-16 | Bruno Ziegler | Control for the rotor of a rotary wing aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| R207 | Utility model specification |
Effective date: 19950518 |
|
| R156 | Lapse of ip right after 3 years |
Effective date: 19981103 |