FR2991294A1 - Bi-plate rotor device for aircraft i.e. rear rotor aircraft, has pitch lever with its operating rod placed on sleeve, and frequency adapter fixed in sleeve for damping drag and limiting flapping of blade - Google Patents

Bi-plate rotor device for aircraft i.e. rear rotor aircraft, has pitch lever with its operating rod placed on sleeve, and frequency adapter fixed in sleeve for damping drag and limiting flapping of blade Download PDF

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Publication number
FR2991294A1
FR2991294A1 FR1201592A FR1201592A FR2991294A1 FR 2991294 A1 FR2991294 A1 FR 2991294A1 FR 1201592 A FR1201592 A FR 1201592A FR 1201592 A FR1201592 A FR 1201592A FR 2991294 A1 FR2991294 A1 FR 2991294A1
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France
Prior art keywords
sleeve
blade
aircraft
frequency adapter
flapping
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Granted
Application number
FR1201592A
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French (fr)
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FR2991294B1 (en
Inventor
Etienne Jean Rampal
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Individual
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Individual
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Classifications

    • 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
    • B64C27/605—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
    • 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
    • B64C27/51—Damping of blade movements

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

Abstract

The device has a laminated spherical stop (5), where each blade is assembled on the abutment ball joint. The ball joint is fixed to a set of interdependent plates (1', 1'') of a bi-plate hub (1). A pitch lever (8) with its operating rod (9) is placed on a sleeve (4). A frequency adapter (6) is fixed in the sleeve for damping drag and limiting flapping of the blade. The interdependent plates are arranged in a parallel manner and are superimposed with regard to each other so as to ensure fixing of the laminated spherical stop.

Description

- 1 - La présente invention concerne un ensemble rotor bi-plateaux compact pour aéronefs dans lequel, à l'intérieur de son moyeu et pour chaque pale, sont logés le levier de pas et son manchon avec sa bielle de commande de pas correspondante, ainsi que l'adaptateur de fréquence fixé sur ce manchon pour l'amortissement en traînée de la pale. La commande de pas pour les variations en incidence des pales comprend traditionnellement sur chacune d'elles un levier de pas animé par une bielle, logés l'un et l'autre à l'extérieur du moyeu, de même que son amortisseur de traînée, constituant ainsi un ensemble rotor peu aérodynamique avec des risques d'endommagement aux chocs par des volatiles ou tirs de balles pouvant entraîner la perte de l'appareil. Le dispositif selon l'invention permet de remédier à ces 15 inconvénients. Il comporte en effet selon une première caractéristique pour chaque pale un levier de pas, solidaire de son manchon équipé d'un adaptateur de fréquence, et sa bielle de commande de pas, tous ensembles logés à l'intérieur d'un moyeu 20 bi-plateaux constitué par deux plateaux solidaires superposés sur l'arbre rotor, lesquels permettent l'assemblage de la butée sphérique lamifiée pour les articulations en pas, battement, traînée de cette pale. Selon une deuxième caractéristique ce dispositif 25 d'ensemble rotor comporte pour chaque pale son adaptateur de fréquence fixé à l'intérieur de son manchon dans lequel il fait office d'amortisseur de traînée et butée de battement, et avec lequel il peut donc tourner avec son manchon sur une fusée solidaire de l'armature externe de la butée sphérique 30 lamifiée selon les variations d'incidence de la pale. Les dessins annexés illustrent l'invention : La figure 1 représente en vue de dessus un ensemble rotor avec quatre pales selon l'invention. La figure 2 représente en coupe et en élévation 35 l'ensemble rotor selon l'invention. - 2 - En référence à ces dessins, le dispositif comporte 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), d'une part la fixation de la butée sphérique lamifiée (5) par les vis ou boulons (11), et d'autre part la liaison du manchon (4) sur l'armature (5') de celle-ci avec les boulons (10). Chaque manchon (4) de pale (3) est équipé d'un levier de pas (8) sur lequel est liée la bielle (9) reliée au coulisseau (15) par les rotules lisses (12) et boulons (13) à chacun de ses deux embouts afin d'assurer les variations d'incidence de la pale. À l'intérieur de chaque manchon (4) est logé et fixé avec les vis (14) un adaptateur de fréquence (6) pour l'amortissement en traînée et limitation en battement de la pale, lequel peut donc tourner avec son manchon, selon les variations d' incidence, grâce à son moyeu central (6') sur la frette (7), laquelle est prévue à cet effet sur la fusée (5'' ') solidaire de l'armature externe (5") de la butée sphérique lamifiée (5). Ce dispositif d'ensemble rotor, non limité en nombre de pales, est particulièrement indiqué pour tout type d'aéronefs, notamment les rotors arrières de giravions.The present invention relates to a compact twin-plate rotor assembly for aircraft in which, within its hub and for each blade, is housed the pitch lever and its sleeve with its corresponding pitch control rod, and that the frequency adapter attached to this sleeve for drag damping of the blade. The pitch control for the variations in incidence of the blades traditionally comprises on each of them a step lever driven by a connecting rod, housed one and the other outside the hub, as well as its drag damper, thus constituting a low aerodynamic rotor assembly with risks of damage to shocks by birds or bullets that can cause the loss of the device. The device according to the invention overcomes these disadvantages. It comprises in fact according to a first characteristic for each blade a pitch lever, integral with its sleeve equipped with a frequency adapter, and its pitch control rod, all together housed inside a hub 20 bi- trays consisting of two solidarity plates superimposed on the rotor shaft, which allow the assembly of the laminated spherical stop for the joints in steps, flapping, drag of this blade. According to a second characteristic, this rotor assembly device comprises for each blade its frequency adapter fixed inside its sleeve in which it serves as a drag damper and beat stop, and with which it can therefore rotate with its sleeve on a rocket integral with the outer armature of the spherical stop 30 laminated according to the variations of incidence of the blade. The attached drawings illustrate the invention: FIG. 1 represents a top view of a rotor assembly with four blades according to the invention. Figure 2 shows in section and elevation the rotor assembly according to the invention. With reference to these drawings, the device comprises on its shaft (2) a hub (1) constituted by two parallel plates and integral (1 ') and (1 ") so as to ensure, for the joints of each blade (3), on the one hand the attachment of the laminated spherical abutment (5) by the screws or bolts (11), and on the other hand the connection of the sleeve (4) to the armature (5 ') thereof. With each bolt (10), each sleeve (4) of blade (3) is equipped with a pitch lever (8) on which is connected the rod (9) connected to the slide (15) by the plain bearings (12). ) and bolts (13) to each of its two ends to ensure the variations of incidence of the blade.In each sleeve (4) is housed and fixed with the screws (14) a frequency adapter ( 6) for drag damping and beat limitation of the blade, which can therefore rotate with its sleeve, according to the variations of incidence, thanks to its central hub (6 ') on the collar (7), which is providedthis effect on the spindle (5 '' ') integral with the outer shell (5 ") of the laminated spherical stop (5). This rotor assembly device, not limited in number of blades, is particularly suitable for all types of aircraft, including rotorcraft rear rotors.

Claims (3)

REVENDICATIONS1) Dispositif d'ensemble rotor bi-plateaux pour aéronefs caractérisé en ce qu'il comporte, pour chaque pale (3) articulée en incidence, traînée et battement sur sa butée sphérique lamifiée (5), un moyeu bi-plateaux (1), dans lequel sont logés le levier de pas (8) avec sa bielle de commande (9) sur son manchon (4) à l'intérieur duquel est fixé l'adaptateur de fréquence (6) pour l'amortissement en traînée et la limitation en battement de la pale.CLAIMS1) Device for two-platter rotor assembly for aircraft characterized in that it comprises, for each blade (3) articulated in incidence, drag and beat on its laminated spherical abutment (5), a two-platter hub (1) , in which the step lever (8) with its control rod (9) is accommodated on its sleeve (4) inside which the frequency adapter (6) is fixed for drag damping and the limitation in beat of the blade. 2) Dispositif selon la revendication 1 caractérisé par un moyeu bi-plateaux (1) dont les plateaux (1') et (1") parallèles et superposés permettent d'assurer la fixation de la butée d'articulation sphérique lamifiée (5) avec les vis aux boulons (11) et le manchon correspondant (4) avec les boulons (10) sur l'armature (5') de cette butée sphérique.2) Device according to claim 1 characterized by a two-plate hub (1) whose plates (1 ') and (1 ") parallel and superimposed to ensure the fixing of the laminated spherical hinge stop (5) with the screws to the bolts (11) and the corresponding sleeve (4) with the bolts (10) on the armature (5 ') of this spherical stop. 3) Dispositif selon les revendications 1 et 2 caractérisé en ce que l'intérieur du manchon (4) pour chaque pale (3) comporte l'adaptateur de fréquence (6) fixé par les vis (14) pouvant donc ainsi tourner avec lui, selon les variations de pas, grâce à son moyeu (6') en appui sur la frette (7) dont est équipée à cet effet la fusée (5"') solidaire de l'armature externe (5") de la butée d'articulation sphérique lamifiée (5).3) Device according to claims 1 and 2 characterized in that the inside of the sleeve (4) for each blade (3) comprises the frequency adapter (6) fixed by the screws (14) can thus rotate with it, according to the variations of pitch, thanks to its hub (6 ') resting on the hoop (7) which is equipped for this purpose the rocket (5 "') integral with the outer armature (5") of the abutment laminated spherical joint (5).
FR1201592A 2012-06-04 2012-06-04 ROTOR BI-PLATFORM AIRCRAFT ASSEMBLY WITH INTERNAL HOUSING OF STEP CONTROLS AND FREQUENCY ADAPTERS Expired - Fee Related FR2991294B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1201592A FR2991294B1 (en) 2012-06-04 2012-06-04 ROTOR BI-PLATFORM AIRCRAFT ASSEMBLY WITH INTERNAL HOUSING OF STEP CONTROLS AND FREQUENCY ADAPTERS

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1201592A FR2991294B1 (en) 2012-06-04 2012-06-04 ROTOR BI-PLATFORM AIRCRAFT ASSEMBLY WITH INTERNAL HOUSING OF STEP CONTROLS AND FREQUENCY ADAPTERS

Publications (2)

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FR2991294A1 true FR2991294A1 (en) 2013-12-06
FR2991294B1 FR2991294B1 (en) 2015-02-13

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FR1201592A Expired - Fee Related FR2991294B1 (en) 2012-06-04 2012-06-04 ROTOR BI-PLATFORM AIRCRAFT ASSEMBLY WITH INTERNAL HOUSING OF STEP CONTROLS AND FREQUENCY ADAPTERS

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297078A (en) * 1978-05-17 1981-10-27 Westland Aircraft Limited Helicopter rotors
WO1993002916A1 (en) * 1991-08-02 1993-02-18 The Boeing Company Ducted fan and pitch controls for tail rotor of rotary wing aircraft
FR2764578A1 (en) * 1997-06-13 1998-12-18 Eurocopter France GIRAVION ROTOR WITH TWO-PLATE HUB AND PARTIALLY EXTERNAL STEP CONTROL

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297078A (en) * 1978-05-17 1981-10-27 Westland Aircraft Limited Helicopter rotors
WO1993002916A1 (en) * 1991-08-02 1993-02-18 The Boeing Company Ducted fan and pitch controls for tail rotor of rotary wing aircraft
FR2764578A1 (en) * 1997-06-13 1998-12-18 Eurocopter France GIRAVION ROTOR WITH TWO-PLATE HUB AND PARTIALLY EXTERNAL STEP CONTROL

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Year of fee payment: 4

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Effective date: 20170228