DE3817978A1 - Helicopter having a tail rotor which can pivot - Google Patents

Helicopter having a tail rotor which can pivot

Info

Publication number
DE3817978A1
DE3817978A1 DE19883817978 DE3817978A DE3817978A1 DE 3817978 A1 DE3817978 A1 DE 3817978A1 DE 19883817978 DE19883817978 DE 19883817978 DE 3817978 A DE3817978 A DE 3817978A DE 3817978 A1 DE3817978 A1 DE 3817978A1
Authority
DE
Germany
Prior art keywords
helicopter
tail rotor
rotor
tail
pivot
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Withdrawn
Application number
DE19883817978
Other languages
German (de)
Inventor
Herbert Zemann
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to DE19883817978 priority Critical patent/DE3817978A1/en
Publication of DE3817978A1 publication Critical patent/DE3817978A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8218—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft wherein the rotor or the jet axis is inclined with respect to the longitudinal horizontal or vertical plane of the helicopter

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

Helicopters must be tilted forwards for horizontal flight. In the invention, this task is taken over by the tail rotor, which can pivot. The tail rotor is normally used to compensate for the contrarotation. If it is now pivoted, its force acts in two directions. On the one hand, the contrarotation is compensated for, while on the other hand the helicopter is raised at the rear and tilted forwards. The resultant greater energy requirement for the tail rotor is compensated for again by other factors which are explained in more detail in the description. Advantages of the invention are the reduced technical complexity both in production and maintenance of such a helicopter.

Description

Die Erfindung betrifft einen Hubschrauber mit schwenk­ barem Heckrotor für den Horizontalflug.The invention relates to a helicopter with swivel stable tail rotor for level flight.

Bei herkömmlichen Hubschraubern wird der Horizontalflug dadurch erreicht, daß dem Rotorblatt, daß gerade über das Heck des Hubschrau­ bers streicht, ein größerer Anstellwinkel gegeben wird, wodurch der Hubschrauber nach vorn kippt, und der Haupt­ rotor auch den Vortrieb übernehmen kann. Dazu ist eine komplizierte, und daher teure und wartungsaufwendige Technik am Rotorkopf notwendig.With conventional Helicopters achieve level flight by that the rotor blade that just above the stern of the helicopter bers strokes, a larger angle of attack is given, causing the helicopter to tip forward and the head rotor can also take over the propulsion. There is one complicated, and therefore expensive and maintenance-intensive Technology at the rotor head necessary.

Die Erfindung macht es sich zur Aufgabe, den Vortrieb eines Hubschraubers auf weniger aufwendige Weise zu erreichen. Diese Aufgabe wird erfindungsmäßig dadurch gelöst, daß der Hubschrauber mit einem schwenkbarem Heckrotor ausgerüstet wird, der nicht nur, wie bisher üblich, die Gegenrotation ausgleicht, sondern gleichzeitig den Hubschrauber am Heck hochzieht, und ihn nach vorn kippt, so daß der Hauptrotor den Vor­ trieb übernehmen kann. Dies kann erreicht werden, indem man die Rotorachse schwenkbar macht, oder das Schwanzende des Hubschraubers, an dem sich der Heckrotor befindet, um seine Achse drehbar macht. The invention does it set itself the task of propelling a helicopter less expensive to achieve. This task is solved according to the invention in that the helicopter is equipped with a swiveling tail rotor that not only compensates for the counter-rotation, as was previously the case, but at the same time pulling up the helicopter at the stern, and tilts it forward so that the main rotor moves forward drive can take over. This can be done by to make the rotor axis pivotable, or the tail end the helicopter on which the tail rotor is located, rotates around its axis.  

Wird der Heckrotor zum Horizontalflug geschwenkt, wird die Heckrotordrehzahl automatisch gesteigert, um beiden Aufgaben, sowohl dem Ausgleich der Gegenrotation als auch dem Vorkippen des Hubschraubers, gerecht zu werden. Der Vorteil der Erfindung besteht hauptsächlich im Wegfall des komplizierten Steuermechanismus der Rotorblätter für den Vortrieb. Der schwenkbare Heckrotor ist technisch wesentlich einfacher. Das Mehr an Energie, daß er benötigt, wird mit Sicherheit ausgeglichen. Einmal durch einen kleineren und leichteren Rotorkopf mit geringerem Luft­ widerstand, außerdem dadurch, daß der Heckrotor im gekippten Zustand des Hubschraubers, auch etwas Vortrieb leistet, und letztlich entfällt der Energieaufwand, der zum Anstellen der Rotorblätter notwendig ist. Durch den Wegfall des abrupten Anstellens der Rotorblätter, werden diese nicht mehr so stark beansprucht, und können einfacher hergestellt werden. Der Hubschrauber wird insgesamt billiger, und könnte auch dort eingesetzt werden, wo bisher aus Kostengründen leichte bis mittlere Propellerflugzeuge verwendet werden. Fig. 1 und Ansicht X zeigen den Hubschrau­ ber im Schwebeflug. Der Heckrotor steht senkrecht, seine Kraft wirkt in Pfeilrichtung A, und gleicht nur die Gegen­ rotation aus. Fig. 2, Ansicht Y zeigen den Heckrotor geschwenkt. Seine Kraft wirkt nun in Pfeilrichtung A und B gleichzeitig. Der Hubschrauber wird um den Winkel C nach vorn gekippt, und geht in den Horizontalflug über.If the tail rotor is swiveled for horizontal flight, the tail rotor speed is automatically increased in order to do both tasks, both to compensate for the counter-rotation and to tip the helicopter forward. The advantage of the invention consists mainly in the elimination of the complicated control mechanism of the rotor blades for propulsion. The swiveling tail rotor is technically much easier. The extra energy that he needs is surely offset. Resisting once with a smaller and lighter rotor head with less air, also in that the tail rotor in the tilted state of the helicopter also provides some propulsion, and ultimately there is no need for energy which is necessary to turn the rotor blades on. By eliminating the abrupt turning of the rotor blades, they are no longer stressed and can be manufactured more easily. The helicopter is cheaper overall and could also be used where light to medium propeller aircraft have been used for cost reasons. Fig. 1 and view X show the helicopter in hover. The tail rotor is vertical, its force acts in the direction of arrow A and only compensates for the counter rotation. Fig. 2, view Y show the tail rotor pivoted. Its force now acts simultaneously in the direction of arrows A and B. The helicopter is tilted forward by the angle C and goes into horizontal flight.

Claims (3)

1. Hubschrauber mit schwenkbarem Heckrotor für den Horizontalflug, dadurch gekennzeichnet, daß der Hub­ schrauber mit einem schwenkbarem Heckrotor ausgerüstet wird, der nicht nur, wie bisher üblich, die Gegenrotation ausgleicht, sondern gleichzeitig den Hubschrauber am Heck hochzieht, und ihn nach vorn kippt, so daß der Hauptrotor den Vortrieb übernehmen kann.1. Helicopter with a swiveling tail rotor for horizontal flight, characterized in that the helicopter is equipped with a swiveling tail rotor which not only compensates for the counter-rotation, as was customary hitherto, but at the same time pulls the helicopter up at the stern and tilts it forward. so that the main rotor can take over the propulsion. 2. Hubschrauber mit schwenkbarem Heckrotor nach Anspruch 1, dadurch gekennzeichnet, daß dies durch eine schwenkbare Heckrotorachse erreicht werden kann, oder durch ein drehbares Hubschrauberschwanzende, an dem sich der Heckrotor befindet.2. helicopter with pivotable tail rotor according to claim 1, characterized in that this is by a pivotable Tail rotor axis can be reached, or by a rotatable helicopter tail end, on which the Tail rotor is located. 3. Hubschrauber mit schwenkbarem Heckrotor nach Anspruch 1, dadurch gekennzeichnet, daß die notwendige Leistungs­ steigerung des Heckrotors, durch automatisches Ansteigen der Heckrotordrehzahl beim Schwenken erreicht wird.3. helicopter with pivotable tail rotor according to claim 1, characterized in that the necessary performance increase of the tail rotor by automatic rise the tail rotor speed is reached when swiveling.
DE19883817978 1988-05-27 1988-05-27 Helicopter having a tail rotor which can pivot Withdrawn DE3817978A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19883817978 DE3817978A1 (en) 1988-05-27 1988-05-27 Helicopter having a tail rotor which can pivot

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19883817978 DE3817978A1 (en) 1988-05-27 1988-05-27 Helicopter having a tail rotor which can pivot

Publications (1)

Publication Number Publication Date
DE3817978A1 true DE3817978A1 (en) 1989-12-07

Family

ID=6355206

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19883817978 Withdrawn DE3817978A1 (en) 1988-05-27 1988-05-27 Helicopter having a tail rotor which can pivot

Country Status (1)

Country Link
DE (1) DE3817978A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5102067A (en) * 1991-04-11 1992-04-07 United Technologies Corporation Integrated helicopter empennage structure
RU172022U1 (en) * 2017-02-08 2017-06-26 Закрытое акционерное общество "Авиастроительная корпорация "Русич" TAIL SCREW INSTALLATION DEVICE ON A SINGLE-SCREW HELICOPTER

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1615002A (en) * 1925-03-24 1927-01-18 Harold T Avery Airship
DE695917C (en) * 1938-12-04 1940-09-05 E H Henrich Focke Dipl Ing Dr Elevator and vertical stabilizer for helicopters consisting of adjustable propellers
US2702084A (en) * 1952-05-20 1955-02-15 Ministerio Da Aeronautica Aircraft of the helicopter type having dual tail rotors
DE953934C (en) * 1955-03-08 1956-12-06 Hans Harald Graf Von Saurma Helicopter with a new type of rudder control
US2959373A (en) * 1954-12-10 1960-11-08 Daniel R Zuck Convertiplane
FR1298518A (en) * 1961-06-02 1962-07-13 Sud Aviation Helicopter orientation control device
US3047254A (en) * 1960-03-14 1962-07-31 Lockheed Aircraft Corp Control means for vehicle
CH422530A (en) * 1965-07-07 1966-10-15 Aero Consultor Ag VTOL aircraft
US3540680A (en) * 1968-05-24 1970-11-17 Lockheed Aircraft Corp Dual rotor system for helicopters
DE1756894B (en) * 1972-04-13 Vereinigte Flugtechnische Werke-Fokker GmbH, 2800 Bremen/DE Aircraft with propellers in front of and behind the aircraft's center of gravity and pivotable in the lift position
DE2640433A1 (en) * 1975-09-09 1977-04-14 Piasecki Aircraft Corp VECTOR PUSH AIRSHIP
DE3328417A1 (en) * 1982-08-24 1984-03-01 Technische Geräte- u. Entwicklungsgesellschaft mbH, 9020 Klagenfurt, Kärnten TURNING WING BODY
DE3446075A1 (en) * 1984-12-18 1986-06-19 Horst Dipl.-Ing. 5400 Koblenz Eichler Tail rotor for pivoting a helicopter about its vertical and lateral axes
DE3537773C2 (en) * 1984-11-28 1987-05-21 Karl Wien At Morawetz
DE3010903C2 (en) * 1979-03-23 1987-12-17 Westland Aircraft Ltd., Yeovil, Somerset, Gb

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1756894B (en) * 1972-04-13 Vereinigte Flugtechnische Werke-Fokker GmbH, 2800 Bremen/DE Aircraft with propellers in front of and behind the aircraft's center of gravity and pivotable in the lift position
US1615002A (en) * 1925-03-24 1927-01-18 Harold T Avery Airship
DE695917C (en) * 1938-12-04 1940-09-05 E H Henrich Focke Dipl Ing Dr Elevator and vertical stabilizer for helicopters consisting of adjustable propellers
US2702084A (en) * 1952-05-20 1955-02-15 Ministerio Da Aeronautica Aircraft of the helicopter type having dual tail rotors
US2959373A (en) * 1954-12-10 1960-11-08 Daniel R Zuck Convertiplane
DE953934C (en) * 1955-03-08 1956-12-06 Hans Harald Graf Von Saurma Helicopter with a new type of rudder control
US3047254A (en) * 1960-03-14 1962-07-31 Lockheed Aircraft Corp Control means for vehicle
FR1298518A (en) * 1961-06-02 1962-07-13 Sud Aviation Helicopter orientation control device
CH422530A (en) * 1965-07-07 1966-10-15 Aero Consultor Ag VTOL aircraft
US3540680A (en) * 1968-05-24 1970-11-17 Lockheed Aircraft Corp Dual rotor system for helicopters
DE2640433A1 (en) * 1975-09-09 1977-04-14 Piasecki Aircraft Corp VECTOR PUSH AIRSHIP
DE3010903C2 (en) * 1979-03-23 1987-12-17 Westland Aircraft Ltd., Yeovil, Somerset, Gb
DE3328417A1 (en) * 1982-08-24 1984-03-01 Technische Geräte- u. Entwicklungsgesellschaft mbH, 9020 Klagenfurt, Kärnten TURNING WING BODY
DE3537773C2 (en) * 1984-11-28 1987-05-21 Karl Wien At Morawetz
DE3446075A1 (en) * 1984-12-18 1986-06-19 Horst Dipl.-Ing. 5400 Koblenz Eichler Tail rotor for pivoting a helicopter about its vertical and lateral axes

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5102067A (en) * 1991-04-11 1992-04-07 United Technologies Corporation Integrated helicopter empennage structure
RU172022U1 (en) * 2017-02-08 2017-06-26 Закрытое акционерное общество "Авиастроительная корпорация "Русич" TAIL SCREW INSTALLATION DEVICE ON A SINGLE-SCREW HELICOPTER

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