CA2714815A1 - Anti-torque system for rotorcraft - Google Patents

Anti-torque system for rotorcraft Download PDF

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Publication number
CA2714815A1
CA2714815A1 CA 2714815 CA2714815A CA2714815A1 CA 2714815 A1 CA2714815 A1 CA 2714815A1 CA 2714815 CA2714815 CA 2714815 CA 2714815 A CA2714815 A CA 2714815A CA 2714815 A1 CA2714815 A1 CA 2714815A1
Authority
CA
Canada
Prior art keywords
drift
blade
plane
rotor
distal end
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
CA 2714815
Other languages
French (fr)
Other versions
CA2714815C (en
Inventor
Gilles Herpin
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 SAS
Original Assignee
Eurocopter SA
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 Eurocopter SA filed Critical Eurocopter SA
Publication of CA2714815A1 publication Critical patent/CA2714815A1/en
Application granted granted Critical
Publication of CA2714815C publication Critical patent/CA2714815C/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • B64C2027/8236—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 including pusher propellers

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Tires In General (AREA)

Abstract

La présente invention concerne un dispositif anticouple d'un giravion muni d'une dérive. La dérive ayant un corps s'étendant dans un plan antéropostérieur (P1) d'une première extrémité distale à une deuxième extrémité distale, ledit dispositif anticouple est pourvu d'un rotor arrière comportant une pluralité de pales et d'un moyen de fixation fixant ledit rotor arrière auxdites première et deuxième extrémités distales, une ailerette étant fixement agencé à une extrémité libre de chaque pale.The present invention relates to an anti-torque device for a rotorcraft provided with a fin. The fin having a body extending in an anteroposterior plane (P1) from a first distal end to a second distal end, said anti-torque device is provided with a tail rotor comprising a plurality of blades and a fixing means fixing said tail rotor at said first and second distal ends, a fin being fixedly arranged at a free end of each blade.

Claims (9)

1. Dispositif anticouple d'un giravion muni d'une dérive, caractérisé en ce que, ladite dérive ayant un corps s'étendant dans un plan antéropostérieur d'une première extrémité distale à une deuxième extrémité distale, ledit dispositif anticouple est pourvu d'un rotor arrière comportant une pluralité de pales et d'un moyen de fixation fixant ledit rotor arrière auxdites première et deuxième extrémités distales, une ailerette étant fixement agencée à une extrémité libre de chaque pale. 1. Anti-torque device of a rotorcraft equipped with a drift, characterized in that said drift having a body extending into an anteroposterior plane from a first distal end to a second distal end, said anti-torque device is provided with a rear rotor having a plurality of blades and a fixing means fixing said rear rotor to said first and second distal ends, a fin being fixedly arranged at a free end of each blade. 2. Dispositif selon la revendication 1, caractérisé en ce que ladite dérive comporte une première branche munie de ladite première extrémité distale, une deuxième branche munie ladite deuxième extrémité distale, une branche commune munie d'une première et d'une deuxième surfaces, lesdites première et deuxième branches étant solidarisées à ladite première surface et ladite deuxième surface étant apte à être reliée à une poutre de queue. 2. Device according to claim 1, characterized in that said drift comprises a first branch provided with said first distal end, a second branch provided with said second distal end, a common branch provided with a first and second surfaces, the said first and second branches being secured to said first surface and said second surface being able to be connected to a beam of tail. 3. Dispositif selon la revendication 2, caractérisé en ce que lesdites première et deuxième branches étant agencées contre la branche commune de part et d'autre d'un plan horizontal de la dérive parallèle à un sol lorsque le giravion est posé sur ledit sol, ledit plan antéropostérieur présente un angle aigu (.phi.) avec ledit plan horizontal. 3. Device according to claim 2, characterized in that said first and second branches being arranged against the common branch on either side of a horizontal plane of the drift parallel to a ground when the rotorcraft is placed on the ground, said anteroposterior plane has an acute angle (.phi.) with said horizontal plane. 4. Dispositif selon l'une quelconque des revendications 1 à 3, caractérisé en ce que ladite dérive a une forme d'étau ayant une première et une deuxième mâchoires fixes munies respectivement desdites première et deuxièmes extrémités distales. 4. Device according to any one of claims 1 to 3, characterized in that said fin has a vise shape having a first and second fixed jaws respectively provided said first and second distal ends. 5. Dispositif selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'il comporte un moyen de basculement dudit rotor arrière autour d'un premier axe (AX1) reliant lesdites première et deuxième extrémités distales pour basculer le rotor arrière d'une première position pour laquelle le rotor arrière et la dérive se trouvent dans un même premier plan antéropostérieur à
une deuxième position pour laquelle le rotor arrière est contenu dans un deuxième plan transversal présentant une angulation avec le plan antéropostérieur de la dérive . 5. Device according to any one of claims 1 to 4, characterized in that it comprises means for tilting said rear rotor around a first axis (AX1) connecting said first and second distal ends to tilt the rotor rear of a first position for which the tail rotor and the drift are in the same foreground anteroposterior to a second position for which the tail rotor is contained in a second transverse plane presenting an angulation with the anteroposterior plane of the drift. 6. Dispositif selon l'une quelconque des revendications 1 à 5, caractérisé en ce que ladite ailerette d'une pale comprend une surface additionnelle en dièdre positif. 6. Device according to any one of claims 1 to 5, characterized in that said blade wing comprises a additional surface in positive dihedron. 7. Dispositif selon l'une quelconque des revendications 1 à 6, caractérisé en ce que ladite ailerette d'une pale comprend une surface additionnelle en dièdre négatif. 7. Device according to any one of claims 1 to 6, characterized in that said blade wing comprises a additional surface in negative dihedral. 8. Dispositif selon l'une quelconque des revendications 1 à 7, caractérisé en ce que ladite ailerette d'une pale comprenant une surface additionnelle en dièdre positif et une surface additionnelle en dièdre négatif, lesdites surfaces additionnelles en dièdre positif et négatif sont symétriques par rapport à un plan médian de ladite pale. 8. Device according to any one of claims 1 to 7, characterized in that said paddle of a blade comprising a additional dihedral surface area and additional area in negative dihedron, said additional dihedral surfaces and negative are symmetrical with respect to a median plane of said blade. 9. Giravion muni d'une voilure tournante et d'un fuselage comportant une poutre de queue, une dérive étant agencée sur ladite poutre de queue, caractérisé en ce que, ladite dérive s'étendant dans un plan antéropostérieur d'une première extrémité
distale à une deuxième extrémité distaie, ledit giravion comporte un dispositif anticouple selon l'une quelconque des revendications 1 à 8 pourvu d'un rotor arrière comportant une pluralité de pales et d'un moyen de fixation fixant ledit rotor arrière auxdites première et deuxième extrémités distales, une ailerette étant fixement agencée à une extrémité libre de chaque pale . 9. Giravion with rotary wing and fuselage having a tail boom, a drift being arranged on said tail boom, characterized in that, said drift extending in an anteroposterior plane of a first end distal at a second distal end, said rotorcraft comprises an anti-torque device according to one of the claims 1 to 8 provided with a rear rotor having a plurality of blades and a fixing means fixing said rear rotor to said first and second distal ends, a fin being fixedly arranged at a free end of each blade.
CA2714815A 2009-10-13 2010-09-15 Anti-torque system for rotorcraft Active CA2714815C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0904898 2009-10-13
FR0904898A FR2951137B1 (en) 2009-10-13 2009-10-13 ANTICOUPLE DEVICE OF A GIRAVION

Publications (2)

Publication Number Publication Date
CA2714815A1 true CA2714815A1 (en) 2011-04-13
CA2714815C CA2714815C (en) 2012-12-04

Family

ID=42115443

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2714815A Active CA2714815C (en) 2009-10-13 2010-09-15 Anti-torque system for rotorcraft

Country Status (2)

Country Link
CA (1) CA2714815C (en)
FR (1) FR2951137B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10377479B2 (en) 2016-06-03 2019-08-13 Bell Helicopter Textron Inc. Variable directional thrust for helicopter tail anti-torque system
US10526085B2 (en) 2016-06-03 2020-01-07 Bell Textron Inc. Electric distributed propulsion anti-torque redundant power and control system
US10703471B2 (en) 2016-06-03 2020-07-07 Bell Helicopter Textron Inc. Anti-torque control using matrix of fixed blade pitch motor modules
US11186185B2 (en) 2017-05-31 2021-11-30 Textron Innovations Inc. Rotor brake effect by using electric distributed anti-torque generators and opposing electric motor thrust to slow a main rotor

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB572417A (en) * 1943-05-24 1945-10-08 G & J Weir Ltd Improvements in helicopters
DE1581060B1 (en) * 1966-04-02 1969-09-18 Messerschmitt Boelkow Blohm Helicopter with a swiveling tail rotor
EP0018114A1 (en) * 1979-04-03 1980-10-29 The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Thrust devices
GB8507875D0 (en) * 1985-03-26 1985-05-01 Univ Open Aerodynamic/hydrodynamic control device

Also Published As

Publication number Publication date
FR2951137A1 (en) 2011-04-15
CA2714815C (en) 2012-12-04
FR2951137B1 (en) 2012-03-09

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