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FR3067002A1 - AIRCRAFT ROTOR HUB DEVICE WITH ARTICULATED SHAFT ON TWO SPHERICAL SPHERES LAMINATED ON ROD - Google Patents

AIRCRAFT ROTOR HUB DEVICE WITH ARTICULATED SHAFT ON TWO SPHERICAL SPHERES LAMINATED ON ROD Download PDF

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Publication number
FR3067002A1
FR3067002A1 FR1700594A FR1700594A FR3067002A1 FR 3067002 A1 FR3067002 A1 FR 3067002A1 FR 1700594 A FR1700594 A FR 1700594A FR 1700594 A FR1700594 A FR 1700594A FR 3067002 A1 FR3067002 A1 FR 3067002A1
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France
Prior art keywords
rotor hub
laminated
screws
hub device
spherical
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Granted
Application number
FR1700594A
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French (fr)
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FR3067002B1 (en
Inventor
Etienne Jean Rampal
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Individual
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Individual
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Priority to FR1700594A priority Critical patent/FR3067002B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/35—Rotors having elastomeric joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pivots And Pivotal Connections (AREA)

Abstract

L'invention concerne un dispositif de moyeu rotor avec pales (4) articulées chacune sur une rotule en forme de deux secteurs sphériques lamifiés distincts (5) et (6) assemblés chacun concentriquement et en opposition sur leur fusée correspondante (1') du moyeu (1) par leur armature interne respective (5''') et (6'''), et sur le manchon (3) en forme de chape par leur armature externe (5') pour l'un et (6') pour l'autre. Ce dispositif selon l'invention est particulièrement destiné pour la suppression d'assemblage en « porte à faux » des pales d'aéronef sur leur rotule sphérique lamifiée solidaire du moyeu rotor.The invention relates to a rotor hub device with blades (4) each hinged on a ball-shaped two separate laminated spherical sectors (5) and (6) each assembled concentrically and in opposition on their corresponding spindle (1 ') of the hub (1) by their respective internal armature (5 '' ') and (6' ''), and on the sleeve (3) in the form of clevis by their outer armature (5 ') for one and (6') for the other. This device according to the invention is particularly intended for the suppression of assembly "overhang" of the aircraft blades on their laminated spherical ball joint with the rotor hub.

Description

La présente invention concerne un dispositif de moyeu rotor pour tout type d'aéronef avec pales articulées sur rotule en forme de deux secteurs sphériques lamifiés assemblés sur fusée.The present invention relates to a rotor hub device for any type of aircraft with blades articulated on a ball joint in the form of two laminated spherical sectors assembled on a rocket.

Ce type d'articulations de pales s'effectue sur une rotule en forme d'un seul secteur sphérique lamifié pour chacune, lequel est traditionnellement logé et assemblé dans une alvéole du moyeu rotor par son armature interne et sur le manchon de pale par son armature externe. Entre ces deux -10 armatures sont moulées des couches alternées d'élastomère sur coupelles métalliques. En fonctionnement celles-ci sont sollicitées en compression due à la force centrifuge de leur pale, en torsion due aux variations de pas de celle-ci, mais aussi soumises aux efforts tranchants générés par la portance, battement, traînée de cette même pale assemblée en « porte à faux ». D'où les contraintes élevées en cisaillement radiaux et décentrage importants sur ces couches d'élastomères avec leurs coupelles métalliques.This type of blade articulation is carried out on a ball joint in the form of a single laminated spherical sector for each, which is traditionally housed and assembled in a cell of the rotor hub by its internal frame and on the blade sleeve by its frame. external. Between these two -10 frames are molded alternating layers of elastomer on metal cups. In operation these are stressed in compression due to the centrifugal force of their blade, in torsion due to variations in pitch thereof, but also subjected to the shear forces generated by the lift, beat, drag of this same blade assembled in " cantilevered ". Hence the high radial shear stresses and significant off-center on these layers of elastomers with their metal cups.

Le dispositif selon l'invention permet de remédier à ces inconvénients.The device according to the invention overcomes these drawbacks.

Il se caractérise en ce qu'il comporte sur le moyeu et pour les articulations de ses pales une rotule, pour chacune, en forme de deux secteurs sphériques lamifiés distincts, assemblés concentriquement, en opposition, leur axe- confondu avec celui de leur fusée. Pour chacun de ceux-ci l'armature interne est fixée par un écrou sur la fusée, et l'armature externe sur le manchon en forme de chape par des vis ou boulons. Le blocage en rotation des armatures internes sur la fusée peut s'effectuer par assemblage carré, cannelures, clavettes, pions au tout autre moyen.It is characterized in that it comprises on the hub and for the articulations of its blades a ball joint, for each, in the form of two distinct laminated spherical sectors, assembled concentrically, in opposition, their axis - coincident with that of their rocket. For each of these, the internal frame is fixed by a nut on the rocket, and the external frame on the sleeve in the form of a yoke by screws or bolts. The internal armatures on the rocket can be locked in rotation by square assembly, splines, keys, pins in any other way.

Selon ce dispositif, les couches d'élastomère de ces deux secteurs sphériques sont donc toujours comprimées sous l'action de la force centrifuge de leur pale correspondante.According to this device, the elastomer layers of these two spherical sectors are therefore always compressed under the action of the centrifugal force of their corresponding blade.

Les dessins annexés illustrent l'invention :The accompanying drawings illustrate the invention:

- La figure 1 représente l'ensemble moyeu en élévation,- Figure 1 shows the hub assembly in elevation,

- La figure 2 représente en coupe partielle la vue de dessus,- Figure 2 shows in partial section the top view,

- La figure 3 représente un exemple de blocage en rotation des armatures internes sur la fusée.- Figure 3 shows an example of locking in rotation of the internal reinforcements on the rocket.

En référence à ces dessins, le dispositif comprend sur son un moyeu (1) comportant les fusées (1') sur lesquelles sont assemblées en opposition, concentrique,With reference to these drawings, the device comprises on its hub (1) comprising the spindles (1 ') on which are assembled in opposition, concentric,

J 10 avec pour axe celui de celles-ci, les secteurs sphériques lamifiés (5) et avec leur armature interne respective (6' 'J 10 with the axis of these, the laminated spherical sectors (5) and with their respective internal reinforcement (6 ''

') qrâce à l'écrou (7) pour l'une et') q thanks to the nut (7) for one and

1'entretoise1'entretoise

La liaison avec le manchon (3) en forme de chape avec les épaulements d'appui (3') et (3'') et sa pale (4) s'effectue pour le secteur sphérique (5) et son armature externe (5') par les boulons ou vis (11) et pour le secteur sphérique (6) et son armature externe (6') par les boulons ou vis (12).The connection with the sleeve (3) in the form of a yoke with the support shoulders (3 ') and (3' ') and its blade (4) takes place for the spherical sector (5) and its external frame (5 ') by bolts or screws (11) and for the spherical sector (6) and its external frame (6') by bolts or screws (12).

Le blocaqe en rotation de l'armature interne (5''') sur la fusée 2Q (1') peut s'effectuer par assemblage carré (1'') ou cannelures, clavette, pion ou tout autre moyen. Même principe de blocage prévu pour l'entretoise (9) sur la fusée.The rotation rotation of the internal frame (5 '') on the 2Q rocket (1 ') can be done by square assembly (1' ') or splines, key, pin or any other means. Same blocking principle provided for the spacer (9) on the rocket.

Les secteurs sphériques (5) et (6) comprennent entre leurs armatures respectives un lamifié formé par des couches 25 alternées en élastomère, (5'') pour l'un et (6'') pour 1'autre.The spherical sectors (5) and (6) comprise between their respective reinforcements a laminate formed by alternating layers of elastomer, (5 '') for one and (6 '') for the other.

Ce dispositif selon 1'invention est particulièrement destiné pour la suppression d'assemblage en « porte à faux » des pales d'aéronef sur leur butée sphérique lamifiée 30 respective dans leur moyeu rotor.This device according to the invention is particularly intended for suppressing the “cantilevered” assembly of aircraft blades on their respective laminated spherical abutment in their rotor hub.

Claims (2)

REVENDICATIONS 1/ Dispositif de moyeu rotor d'aéronef caractérisé en ce qu'il comporte pour les articulations de ses pales (4) une rotule, pour chacune, en forme de deux secteurs sphériques distincts (5) et (6) assemblés concentriquement, en 5 opposition, leur axe confondu avec celui de leur fusée respective (1') du moyeu (1) et fixés sur celle-ci, pour l'un, par l'écrou (7) de l'armature interne (5'''), et pour l'autre avec l'entretoise (9) et vis (13) plus l'écrou (8), leur liaison avec le manchon (3) en forme de chape et ses1 / Aircraft rotor hub device characterized in that it comprises for the articulations of its blades (4) a ball joint, for each, in the form of two distinct spherical sectors (5) and (6) assembled concentrically, in 5 opposition, their axis coincident with that of their respective stub axle (1 ') of the hub (1) and fixed thereon, for one, by the nut (7) of the internal frame (5' '') , and for the other with the spacer (9) and screws (13) plus the nut (8), their connection with the sleeve (3) in the form of a yoke and its 10 épaulements d'appui (3') et (3'') se faisant alors pour le secteur sphérique (5) et son armature externe (5') à l'aide des boulons ou vis (11) et pour le secteur sphérique (6) et son armature externe (6') avec les boulons ou vis (12).10 support shoulders (3 ') and (3' ') then being made for the spherical sector (5) and its external frame (5') using bolts or screws (11) and for the spherical sector ( 6) and its external frame (6 ') with bolts or screws (12). 2/ Dispositif selon la revendication 1 caractérisé en ce2 / Device according to claim 1 characterized in that 45 Que les couches d'élastomère (5'') et (6'') de leurs secteurs respectifs (5) et (6) sont toujours comprimées sous l'action de la force centrifuge de leur pale correspondante.45 That the elastomer layers (5 '') and (6 '') of their respective sectors (5) and (6) are always compressed under the action of the centrifugal force of their corresponding blade.
FR1700594A 2017-06-02 2017-06-02 AIRCRAFT ROTOR HUB DEVICE WITH ARTICULATED BLADES ON BALL JOINT SHAPE OF TWO SPHERICAL SECTORS LAMIFIED ON ROCKET Expired - Fee Related FR3067002B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1700594A FR3067002B1 (en) 2017-06-02 2017-06-02 AIRCRAFT ROTOR HUB DEVICE WITH ARTICULATED BLADES ON BALL JOINT SHAPE OF TWO SPHERICAL SECTORS LAMIFIED ON ROCKET

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1700594 2017-06-02
FR1700594A FR3067002B1 (en) 2017-06-02 2017-06-02 AIRCRAFT ROTOR HUB DEVICE WITH ARTICULATED BLADES ON BALL JOINT SHAPE OF TWO SPHERICAL SECTORS LAMIFIED ON ROCKET

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FR3067002A1 true FR3067002A1 (en) 2018-12-07
FR3067002B1 FR3067002B1 (en) 2020-08-07

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FR1700594A Expired - Fee Related FR3067002B1 (en) 2017-06-02 2017-06-02 AIRCRAFT ROTOR HUB DEVICE WITH ARTICULATED BLADES ON BALL JOINT SHAPE OF TWO SPHERICAL SECTORS LAMIFIED ON ROCKET

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FR (1) FR3067002B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113501128A (en) * 2021-09-10 2021-10-15 北京中航智科技有限公司 Unmanned helicopter main rotor hub and unmanned helicopter

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1475326A (en) * 1966-04-08 1967-03-31 Lord Corp Rotor head, especially for helicopters
US3862812A (en) * 1973-07-18 1975-01-28 Lord Corp Rotor blade retention system
US4028002A (en) * 1976-03-01 1977-06-07 Lord Corporation Rotor blade retention system
FR2457804A1 (en) * 1978-05-17 1980-12-26 Westland Aircraft Ltd HELICOPTER ROTORS

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1475326A (en) * 1966-04-08 1967-03-31 Lord Corp Rotor head, especially for helicopters
US3862812A (en) * 1973-07-18 1975-01-28 Lord Corp Rotor blade retention system
US4028002A (en) * 1976-03-01 1977-06-07 Lord Corporation Rotor blade retention system
FR2457804A1 (en) * 1978-05-17 1980-12-26 Westland Aircraft Ltd HELICOPTER ROTORS

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113501128A (en) * 2021-09-10 2021-10-15 北京中航智科技有限公司 Unmanned helicopter main rotor hub and unmanned helicopter
CN113501128B (en) * 2021-09-10 2022-02-25 北京中航智科技有限公司 Unmanned helicopter main rotor hub and unmanned helicopter

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Publication number Publication date
FR3067002B1 (en) 2020-08-07

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