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FR2991293A1 - Rotor device for rotor craft, has blades connected inside double-plate rotor hub, plates attached at end of rotor shaft of hub, laminated spherical stop fixed between plates by bolts, and sleeve with bolts provided on reinforcement of stop - Google Patents

Rotor device for rotor craft, has blades connected inside double-plate rotor hub, plates attached at end of rotor shaft of hub, laminated spherical stop fixed between plates by bolts, and sleeve with bolts provided on reinforcement of stop Download PDF

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Publication number
FR2991293A1
FR2991293A1 FR1201523A FR1201523A FR2991293A1 FR 2991293 A1 FR2991293 A1 FR 2991293A1 FR 1201523 A FR1201523 A FR 1201523A FR 1201523 A FR1201523 A FR 1201523A FR 2991293 A1 FR2991293 A1 FR 2991293A1
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France
Prior art keywords
rotor
bolts
hub
plates
sleeve
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
FR1201523A
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French (fr)
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FR2991293B1 (en
Inventor
Etienne Jean Rampal
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Individual
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Individual
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Publication date
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Priority to FR1201523A priority Critical patent/FR2991293B1/en
Publication of FR2991293A1 publication Critical patent/FR2991293A1/en
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Publication of FR2991293B1 publication Critical patent/FR2991293B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/51—Damping of blade movements
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Dampers (AREA)

Abstract

The device has drag shock absorbers (6), where each absorber is placed between two successive blades (3). The blades are connected inside a double-plate rotor hub (1). The hub includes a rotor shaft, and plates are attached at an end of the rotor shaft. A laminated spherical stop (5) of each blade is fixed between the plates by bolts (11). A sleeve with bolts (10) is provided on reinforcement (5') of the stop. A yoke or tenon (7) is secured at rear of the reinforcement or the sleeve and formed with holes (7') side by side.

Description

-i - La présente invention concerne un rotor d'aéronef avec un moyeu bi-plateaux et pales articulées chacune sur leur rotule sphérique lamifiée autour de laquelle leur mouvement en traînée est limité par des amortisseurs logés à l'intérieur du moyeu, entre les manchons de deux pales successives avec lesquelles ils sont liés à chacune de leurs extrémités par une rotule lisse. Les amortisseurs de traînée sont traditionnellement disposés à l'extérieur du moyeu, accrochés chacun sur celui-ci à l'une de leurs deux extrémités et à la pale à l'autre. Si l'on envisage de les lier à deux pales successives leur longueur sera donc plus grande, surtout si le nombre de celles-ci est faible. Ce type de rotor est dénommé « rotor avec amortisseurs de traînée interpales » dans le jargon aéronautique. Le dispositif selon l'invention permet de remédier à ces inconvénients. Il comporte en effet selon une première caractéristique des amortisseurs de traînée attachés chacun entre deux pales successives, mais logés à l'intérieur d'un moyeu constitué par deux plateaux solidaires et superposés sur l'arbre rotor, lequel permet l'assemblage et l'articulation de chaque pale et leur manchon sur leur butée sphérique lamifiée. Selon une deuxième caractéristique chaque butée 25 d'articulation sphérique lamifiée, ou son manchon, est équipée d'une chape ou tenon orientée vers l'axe rotor et percée par deux trous parallèles côte à côte de façon à assurer chacun l'assemblage avec rotule lisse d'un embout de deux amortisseurs de traînée successifs sur cette chape ou tenon.The present invention relates to an aircraft rotor with a dual-plate hub and blades each articulated on their laminated spherical ball around which their movement in drag is limited by dampers housed inside the hub, between the sleeves of two successive blades with which they are connected at each of their ends by a smooth ball joint. The drag dampers are traditionally arranged outside the hub, each hooked on it at one of their two ends and the blade to the other. If we plan to link them to two successive blades their length will be greater, especially if the number of them is small. This type of rotor is called "rotor with interpale drag dampers" in aeronautical jargon. The device according to the invention overcomes these disadvantages. It comprises in fact according to a first characteristic drag dampers each attached between two successive blades, but housed inside a hub consisting of two plates integral and superimposed on the rotor shaft, which allows the assembly and the articulation of each blade and their sleeve on their laminated spherical stop. According to a second characteristic each laminated spherical hinge stop 25 or its sleeve is equipped with a clevis or tongue oriented towards the rotor axis and pierced by two parallel holes side by side so as to ensure each assembly with a ball joint. smooth of a tip of two successive drag shock absorbers on this screed or tenon.

30 Les dessins annexés illustrent l'invention : La figure 1 représente en vue de dessus un ensemble rotor avec trois pales. La figure 2 représente en vue de dessus un ensemble rotor avec quatre pales.The accompanying drawings illustrate the invention: Figure 1 shows a top view of a rotor assembly with three blades. Figure 2 shows a top view of a rotor assembly with four blades.

35 La figure 3 représente en coupe et en élévation - 2 - l'ensemble rotor. En référence à ces dessins le dispositif comprend sur son arbre (2) un moyeu (1) constitué par deux plateaux parallèles et solidaires (1') et (1") de façon à assurer, pour les articulations de chaque pale (3), la fixation de leur butée sphérique lamifiée (5) par les boulons (11), et le manchon (4) avec les boulons (10) sur l'armature (5') de celle-ci. A l'arrière de cette armature (5') ou du manchon (4), c'est-à-dire sur leur face orientée vers l'axe rotor, est 10 solidarisée une chape ou un tenon (7) percés par deux trous (7') côte à côte et parallèles permettant ainsi chacun l'attache d'un amortisseur de traînée (6) successifs à l'aide d'une rotule lisse (8) et vis ou boulons (9) sur l'un de leurs deux embouts.Figure 3 shows in section and elevation the rotor assembly. With reference to these drawings, the device comprises on its shaft (2) a hub (1) consisting of two parallel and integral plates (1 ') and (1 ") so as to ensure, for the joints of each blade (3), fixing their laminated spherical abutment (5) by the bolts (11), and the sleeve (4) with the bolts (10) on the armature (5 ') thereof. 5 ') or the sleeve (4), that is to say on their side facing the rotor axis, is secured a clevis or tenon (7) pierced by two holes (7') side by side and parallel thus allowing each the attachment of a drag damper (6) successive with a smooth ball (8) and screws or bolts (9) on one of their two ends.

15 Le dispositif selon l'invention est particulièrement destiné pour tout type d'aéronef, notamment les giravions.The device according to the invention is particularly intended for any type of aircraft, in particular rotorcraft.

Claims (2)

REVENDICATIONS1°) Dispositif de rotor pour aéronefs caractérisé en ce qu'il comporte des amortisseurs de traînée (6) disposés chacun entre deux pales (3) successives, avec lesquelles ils sont liés, à l'intérieur de leur moyeu rotor bi-plateaux (1) constitué d'un mat rotor (2) en bout duquel sont solidarisés les plateaux (1') et (1") et entre lesquels la butée d'articulation sphérique lamifiée (5) de chaque pale (3) est fixée avec les vis ou boulons (11) ainsi que le manchon correspondant (4) avec les boulons (10) sur l'armature (5') de cette dernière.CLAIMS 1 °) Aircraft rotor device characterized in that it comprises drag dampers (6) each disposed between two blades (3) successive, with which they are connected, within their two-plate rotor hub ( 1) consisting of a rotor mat (2) at the end of which are secured the plates (1 ') and (1 ") and between which the laminated spherical hinge stop (5) of each blade (3) is fixed with the screws or bolts (11) and the corresponding sleeve (4) with the bolts (10) on the armature (5 ') thereof. 2°) Dispositif selon la revendication 1 caractérisé pour chaque pale (3) par sa chape ou tenon (7) percés par deux trous (7') côte à côte, parallèles, et solidaires de l'armature (5') de leur butée d'articulation sphérique lamifiée (5) ou de leur manchon (4) de façon à assurer la liaison de deux amortisseurs successifs (6) à l'aide d'une rotule lisse (8) et vis ou boulons (9) à chacun de leurs embouts.2 °) Device according to claim 1 characterized for each blade (3) by its yoke or pin (7) pierced by two holes (7 ') side by side, parallel, and integral with the armature (5') of their abutment laminated spherical joint (5) or their sleeve (4) so as to ensure the connection of two successive dampers (6) with a smooth ball (8) and screws or bolts (9) to each of their tips.
FR1201523A 2012-05-29 2012-05-29 ROTOR BI-AIRCRAFT TRAILERS WITH INTERPOREAL SHOCK ABSORBERS INSIDE THE HUB Expired - Fee Related FR2991293B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1201523A FR2991293B1 (en) 2012-05-29 2012-05-29 ROTOR BI-AIRCRAFT TRAILERS WITH INTERPOREAL SHOCK ABSORBERS INSIDE THE HUB

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1201523A FR2991293B1 (en) 2012-05-29 2012-05-29 ROTOR BI-AIRCRAFT TRAILERS WITH INTERPOREAL SHOCK ABSORBERS INSIDE THE HUB

Publications (2)

Publication Number Publication Date
FR2991293A1 true FR2991293A1 (en) 2013-12-06
FR2991293B1 FR2991293B1 (en) 2015-04-10

Family

ID=46650592

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1201523A Expired - Fee Related FR2991293B1 (en) 2012-05-29 2012-05-29 ROTOR BI-AIRCRAFT TRAILERS WITH INTERPOREAL SHOCK ABSORBERS INSIDE THE HUB

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FR (1) FR2991293B1 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1456107A1 (en) * 1964-07-04 1968-12-19 Westland Aircraft Ltd Rotary wing aircraft
EP0021901A1 (en) * 1979-06-05 1981-01-07 Aerospatiale Societe Nationale Industrielle Compact articulated rotor hub for a rotor craft
EP1767452A1 (en) * 2005-09-21 2007-03-28 Eurocopter Rotor for rotorcraft with blades articulated in flap and drag
EP2184229A1 (en) * 2008-11-11 2010-05-12 Agusta S.p.A. Helicopter rotor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1456107A1 (en) * 1964-07-04 1968-12-19 Westland Aircraft Ltd Rotary wing aircraft
EP0021901A1 (en) * 1979-06-05 1981-01-07 Aerospatiale Societe Nationale Industrielle Compact articulated rotor hub for a rotor craft
EP1767452A1 (en) * 2005-09-21 2007-03-28 Eurocopter Rotor for rotorcraft with blades articulated in flap and drag
EP2184229A1 (en) * 2008-11-11 2010-05-12 Agusta S.p.A. Helicopter rotor

Also Published As

Publication number Publication date
FR2991293B1 (en) 2015-04-10

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