EP2181038A1 - Coupling device intended to connect first and second elements which are articulated with respect to one another - Google Patents

Coupling device intended to connect first and second elements which are articulated with respect to one another

Info

Publication number
EP2181038A1
EP2181038A1 EP08786954A EP08786954A EP2181038A1 EP 2181038 A1 EP2181038 A1 EP 2181038A1 EP 08786954 A EP08786954 A EP 08786954A EP 08786954 A EP08786954 A EP 08786954A EP 2181038 A1 EP2181038 A1 EP 2181038A1
Authority
EP
European Patent Office
Prior art keywords
connecting rod
state
connecting device
another
articulated
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Withdrawn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
EP08786954A
Other languages
German (de)
French (fr)
Inventor
Pascal-Marie Paul Marcel Soulier
Aurélie DE SORBAY
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.)
Safran Nacelles SAS
Original Assignee
Aircelle 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 Aircelle SA filed Critical Aircelle SA
Publication of EP2181038A1 publication Critical patent/EP2181038A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/63—Frangible connections
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32114—Articulated members including static joint
    • Y10T403/32221—Articulate joint comprises pivoted clevis or channel bar
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32606—Pivoted
    • Y10T403/32861—T-pivot, e.g., wrist pin, etc.

Definitions

  • Connecting device for connecting a first and a second articulated element relative to each other
  • the invention relates to a connecting device for connecting a first and a second element articulated with respect to one another.
  • the invention applies more particularly to areas in which the articulated elements are subjected to external stresses, the connecting device then being subjected consecutively to compressive stresses and to tensile stresses, thus generating a fatigue phenomenon of constituent elements of the connecting device.
  • a connecting device is used in particular in the field of aeronautics, in particular to equip nacelles.
  • a nacelle is a fairing element for protecting a reactor from an aircraft.
  • a nacelle generally carries two articulated elements on the mast of the aircraft so as to allow access to the engine housed inside the nacelle.
  • Locks are arranged at junction areas between the two articulated elements arranged in the lower part, that is to say at 6 o'clock, and in the upper part, that is to say at 12 o'clock, in order to avoid opening the platform during the flight. It is known to use locks comprising a connecting device comprising a connecting rod, the latter being subjected to both compression stresses and tensile stresses, thus generating a phenomenon of fatigue.
  • the rod subjected to fatigue is greatly weakened so that, for safety reasons, it is necessary to oversize it significantly and / or to provide an additional connecting rod to overcome any breakage of the aforementioned rod.
  • Such a connecting device has a weight, a cost and a large footprint.
  • the invention aims to solve these drawbacks by proposing a connecting device, intended to connect a first and a second articulated element with respect to the other, characterized in that it comprises a compression element designed to realize the passing a compressive force from one element to another in a first state, and a traction element designed to effect the passage of a tensile force from one element to another in a second state, the element compression member further forming a substitution traction member adapted to effect the passage of a tensile force from one element to another in a third state corresponding to the breaking of the traction element.
  • a fatigue phenomenon occurs when an element is frequently subjected to tensile stresses, creating a crack that tends to propagate during repetitive tensile stresses.
  • the compression element does not support any tensile stress so that it is not subjected to fatigue.
  • connection device thus provides a path of healthy effort created by the compression element and to play the same role as the traction element in case of rupture of the latter.
  • the compression element comprises a first connecting rod, the traction element comprising a second connecting rod, each connecting rod being equipped with a first and a second end provided with articulation means, respectively on the first and the second articulated elements.
  • the second connecting rod is housed in the first connecting rod.
  • This characteristic makes it possible to increase the compactness of the connecting device.
  • each connecting rod has an oblong opening in the vicinity of at least one end, the oblong opening being intended for the passage of an articulation axis of the connecting device on the corresponding element.
  • the oblong openings allow to accept a slight movement between the connecting rods and the hinge pins connected to the corresponding articulated elements. They also make it possible to compensate for the positioning defects of one half-shell relative to the other so as to allow their locking.
  • the oblong openings are arranged so that, in the first state, the first connecting rod is in abutment against the hinge axis while the second connecting rod is set back from it and that, in the second state, the second rod is in abutment against the hinge axis while the first rod is set back from it.
  • the first link in the first state, the first link is only subjected to compressive stresses while the second link is not subject to any particular constraint and, in the second state, the second rod is subjected only to tensile stresses while the first rod is not subject to any particular constraint.
  • the invention further relates to a nacelle comprising a first and a second element articulated with respect to each other, characterized in that the articulated elements are connected by at least one connecting device according to the invention.
  • the invention also relates to an aircraft, characterized in that it comprises at least one nacelle according to the invention.
  • Figure 1 is a longitudinal sectional view in a first state
  • Figure 2 is an enlarged view of one end of the connecting device of Figure 1;
  • Figures 3 and 4 are views respectively corresponding to Figures 1 and 2, the connecting device in a second state;
  • FIG. 1 shows a connecting device 1 comprising a first connecting rod 2 of generally tubular shape and a second connecting rod 3 of generally cylindrical shape, extending inside the first connecting rod 2 along an axis A.
  • Each connecting rod 2, 3 comprises a first and a second end 4, 5, respectively connected to a first and a second clevis
  • the axis 9 is arranged perpendicular to the axis 8.
  • the second ends of the connecting rods 2, 3 are connected to a universal joint 13 of which the yoke 7 is part and having an axis articulation 14 parallel to the axis 8.
  • the first end 4 of the second connecting rod 3 comprises a yoke 10 hinged to the first hinge axis 8, the yoke 10 having two oblong holes 11 arranged facing one another.
  • the first end 4 of the first connecting rod 2 further comprises two oblong holes 12 traversed by the first hinge axis 8 and arranged facing one another.
  • the oblong holes 11, 12 have substantially the same length and are arranged staggered with respect to each other so that, in a first traction state of the connecting device, shown in FIGS. 1 and 2, the second connecting rod 3 in abutment against the first hinge pin 8, at the outer portion of the oblong holes 11, while the first rod 2 is set back from the aforementioned axis 8. In this way, in the first state of traction, only the second link 3 is subjected to tensile stresses, the first link 2 being subjected to no particular constraint.
  • Figures 3 and 4 show the connecting device 1 in a second state, corresponding to a state of compression thereof.
  • the first link 2 abuts against the first hinge axis 8, at the inner portion of the oblong holes 12, while the second link 3 is set back from the aforementioned axis 8.
  • the first connecting rod 2 can also abut against a concave bottom 15 of the yoke 6, or else come into abutment against the bottom 15 and against the axis 8.
  • first rod 2 does not abut against the axis 8
  • first connecting rod 2 is subjected to compressive stresses, the second connecting rod 3 being subjected to no particular constraint.
  • the device In normal operation, the device is subjected to one of the two aforementioned states, so that none of the connecting rods 2, 3 is subjected to both compression and traction.
  • the connecting rods 2, 3 therefore do not undergo a fatigue phenomenon, occurring during a succession of tensile stresses or by the alternation between compressive stresses and tensile stresses.
  • Figures 5 and 6 show a third state of the connecting device 1 corresponding to accidental operation.
  • This third state corresponds to a break of the second connecting rod 3.
  • the first connecting rod 2 capable of producing the passage of compressive force between the two articulated elements of the nacelle, is also capable of producing the passage of tensile force in the event of rupture. of the second connecting rod 3.
  • the first connecting rod 2 abuts against the first hinge axis 8, at the outer portion of the oblong holes 12.
  • the first connecting rod 2 thus forms a pathway for the traction forces.
  • the second connecting rod 3 able to achieve the passage of traction force between the two articulated elements of the nacelle, is also able to achieve the passage of compressive force in case of breakage of the first connecting rod 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
  • Piles And Underground Anchors (AREA)

Abstract

The invention relates to a coupling device (1) intended to connect first and second elements which are articulated with respect to one another, characterized in that it comprises a compression element (2) designed to allow a compressive force to pass from one element to another in a first state, and a tension element (3) designed to allow a tensile force to pass from one element to another in a second state, the compression element additionally forming a substitution tension element designed to allow a tensile force to pass from one element to another in a third state corresponding to the fracturing of the tension element.

Description

Dispositif de liaison, destiné à relier un premier et un second éléments articulés l'un par rapport à l'autre Connecting device for connecting a first and a second articulated element relative to each other
L'invention concerne un dispositif de liaison, destiné à relier un premier et un second éléments articulés l'un par rapport à l'autre. L'invention s'applique plus particulièrement à des domaines dans lesquels les éléments articulés sont soumis à des contraintes externes, le dispositif de liaison étant alors soumis consécutivement à des contraintes de compression et à des contraintes de traction, engendrant ainsi un phénomène de fatigue des éléments constitutifs du dispositif de liaison. Un dispositif de liaison est notamment utilisé dans le domaine de l'aéronautique, en particulier afin d'équiper des nacelles.The invention relates to a connecting device for connecting a first and a second element articulated with respect to one another. The invention applies more particularly to areas in which the articulated elements are subjected to external stresses, the connecting device then being subjected consecutively to compressive stresses and to tensile stresses, thus generating a fatigue phenomenon of constituent elements of the connecting device. A connecting device is used in particular in the field of aeronautics, in particular to equip nacelles.
Une nacelle est un élément de carénage permettant de protéger un réacteur d'un aéronef. Une nacelle co mporte généralement deux éléments articulés sur le mat de l'aéronef de manière à permettre un accès au moteur logé à l'intérieur de la nacelle.A nacelle is a fairing element for protecting a reactor from an aircraft. A nacelle generally carries two articulated elements on the mast of the aircraft so as to allow access to the engine housed inside the nacelle.
Des verrous sont disposés au niveau de zones de jonction entre les deux éléments articulés, disposées en partie inférieure, c'est-à-dire à 6 heures, et en partie supérieure, c'est-à-dire à 12 heures, afin d'éviter une ouverture de la nacelle durant le vol. II est connu d'utiliser des verrous comprenant un dispositif de liaison comportant une bielle, celle-ci étant soumise aussi bien à des contraintes de compression qu'à des contraintes de traction, engendrant alors un phénomène de fatigue.Locks are arranged at junction areas between the two articulated elements arranged in the lower part, that is to say at 6 o'clock, and in the upper part, that is to say at 12 o'clock, in order to avoid opening the platform during the flight. It is known to use locks comprising a connecting device comprising a connecting rod, the latter being subjected to both compression stresses and tensile stresses, thus generating a phenomenon of fatigue.
La bielle soumise à de la fatigue est fortement fragilisée de sorte que, pour des raisons de sécurité, il est nécessaire de la surdimensionner de manière importante et/ou de prévoir une bielle additionnelle permettant de pallier une éventuelle rupture de la bielle précitée. Un tel dispositif de liaison présente un poids, un coût et un encombrement importants.The rod subjected to fatigue is greatly weakened so that, for safety reasons, it is necessary to oversize it significantly and / or to provide an additional connecting rod to overcome any breakage of the aforementioned rod. Such a connecting device has a weight, a cost and a large footprint.
L'invention vise à résoudre ces inconvénients en proposant un dispositif de liaison, destiné à relier un premier et un second éléments articulés l'un par rapport à l'autre, caractérisé en ce qu'il comporte un élément de compression conçu pour réaliser le passage d'un effort de compression d'un élément à un autre dans un premier état, et un élément de traction conçu pour réaliser le passage d'un effort de traction d'un élément à un autre dans un second état, l'élément de compression formant en outre un élément de traction de substitution conçu pour réaliser le passage d'un effort de traction d'un élément à un autre, dans un troisième état correspondant à la rupture de l'élément de traction. Un phénomène de fatigue apparaît lorsqu'un élément est fréquemment soumis à des contraintes de traction, créant alors une crique qui a tendance à se propager lors des sollicitations répétitives en traction.The invention aims to solve these drawbacks by proposing a connecting device, intended to connect a first and a second articulated element with respect to the other, characterized in that it comprises a compression element designed to realize the passing a compressive force from one element to another in a first state, and a traction element designed to effect the passage of a tensile force from one element to another in a second state, the element compression member further forming a substitution traction member adapted to effect the passage of a tensile force from one element to another in a third state corresponding to the breaking of the traction element. A fatigue phenomenon occurs when an element is frequently subjected to tensile stresses, creating a crack that tends to propagate during repetitive tensile stresses.
L'élément de compression ne supporte aucune contrainte de traction de sorte qu'il n'est pas soumis à de la fatigue.The compression element does not support any tensile stress so that it is not subjected to fatigue.
Le dispositif de liaison selon l'invention apporte ainsi un chemin d'effort sain crée par l'élément de compression et permettant de jouer le même rôle que l'élément de traction en cas de rupture de ce dernier.The connection device according to the invention thus provides a path of healthy effort created by the compression element and to play the same role as the traction element in case of rupture of the latter.
Le dimensionnement de l'élément de traction peut ainsi être réduit. Avantageusement, l'élément de compression comporte une première bielle, l'élément de traction comportant une seconde bielle, chaque bielle étant équipée d'une première et d'une seconde extrémités équipées de moyens d'articulation, respectivement sur le premier et le second éléments articulés. Selon une caractéristique de l'invention, la seconde bielle est logée dans la première bielle.The dimensioning of the traction element can thus be reduced. Advantageously, the compression element comprises a first connecting rod, the traction element comprising a second connecting rod, each connecting rod being equipped with a first and a second end provided with articulation means, respectively on the first and the second articulated elements. According to one characteristic of the invention, the second connecting rod is housed in the first connecting rod.
Cette caractéristique permet d'augmenter la compacité du dispositif de liaison.This characteristic makes it possible to increase the compactness of the connecting device.
Préférentiellement, chaque bielle comporte une ouverture oblongue au voisinage d'au moins une extrémité, l'ouverture oblongue étant destinée au passage d'un axe d'articulation du dispositif de liaison sur l'élément correspondant.Preferably, each connecting rod has an oblong opening in the vicinity of at least one end, the oblong opening being intended for the passage of an articulation axis of the connecting device on the corresponding element.
Les ouvertures oblongues permettent d'accepter un léger débattement entre les bielles et les axes d'articulation reliés aux éléments articulés correspondants. Elles permettent en outre de compenser les défauts de positionnement d'une demi-coquille par rapport à l'autre de manière à permettre leur verrouillage.The oblong openings allow to accept a slight movement between the connecting rods and the hinge pins connected to the corresponding articulated elements. They also make it possible to compensate for the positioning defects of one half-shell relative to the other so as to allow their locking.
Selon une possibilité de l'invention, les ouvertures oblongues sont agencées de sorte que, dans le premier état, la première bielle est en butée contre l'axe d'articulation tandis que la seconde bielle est en retrait de celui-ci et que, dans le second état, la seconde bielle est en butée contre l'axe d'articulation tandis que la première bielle est en retrait de celui-ci.According to a possibility of the invention, the oblong openings are arranged so that, in the first state, the first connecting rod is in abutment against the hinge axis while the second connecting rod is set back from it and that, in the second state, the second rod is in abutment against the hinge axis while the first rod is set back from it.
De cette manière, dans le premier état, la première bielle est soumise uniquement à des contraintes de compression tandis que la seconde bielle n'est soumise à aucune contrainte particulière et, dans le second état, la seconde bielle est soumise uniquement à des contraintes de traction tandis que la première bielle n'est soumise à aucune contrainte particulière.In this way, in the first state, the first link is only subjected to compressive stresses while the second link is not subject to any particular constraint and, in the second state, the second rod is subjected only to tensile stresses while the first rod is not subject to any particular constraint.
L'invention concerne en outre une nacelle comportant un premier et un second éléments articulés l'un par rapport à l'autre, caractérisée en ce que les éléments articulés sont reliés par au moins un dispositif de liaison selon l'invention.The invention further relates to a nacelle comprising a first and a second element articulated with respect to each other, characterized in that the articulated elements are connected by at least one connecting device according to the invention.
L'invention concerne également un aéronef, caractérisé en ce qu'il comporte au moins une nacelle selon l'invention.The invention also relates to an aircraft, characterized in that it comprises at least one nacelle according to the invention.
De toute façon, l'invention sera bien comprise à l'aide de la description qui suit en référence au dessin schématique annexé représentant, à titre d'exemple, une forme de réalisation de ce dispositif de liaison.In any case, the invention will be better understood from the description which follows with reference to the attached schematic drawing showing, by way of example, an embodiment of this connecting device.
Figure 1 en est une vue en coupe longitudinale, dans un premier état;Figure 1 is a longitudinal sectional view in a first state;
Figure 2 est une vue agrandie d'une extrémité du dispositif de liaison de la figure 1 ;Figure 2 is an enlarged view of one end of the connecting device of Figure 1;
Figures 3 et 4 sont des vues correspondant respectivement aux figures 1 et 2, du dispositif de liaison dans un deuxième état ;Figures 3 and 4 are views respectively corresponding to Figures 1 and 2, the connecting device in a second state;
Figures 5 et 6 sont des vues correspondant respectivement aux figures 1 et 2, du dispositif de liaison dans un troisième état ; La figure 1 représente un dispositif de liaison 1 comportant une première bielle 2 de forme générale tubulaire et une seconde bielle 3 de forme générale cylindrique, s'étendant à l'intérieur de la première bielle 2 selon un axe A.Figures 5 and 6 are views respectively corresponding to Figures 1 and 2, the connecting device in a third state; FIG. 1 shows a connecting device 1 comprising a first connecting rod 2 of generally tubular shape and a second connecting rod 3 of generally cylindrical shape, extending inside the first connecting rod 2 along an axis A.
Chaque bielle 2, 3 comporte une première et une seconde extrémités 4, 5, reliées respectivement à une première et une seconde chapesEach connecting rod 2, 3 comprises a first and a second end 4, 5, respectively connected to a first and a second clevis
6, 7, ces dernières étant fixées à un premier et un second éléments mobiles d'une nacelle, non représentés, par l'intermédiaire d'un premier et d'un second axes d'articulation 8, 9. L'axe 9 est disposé perpendiculairement à l'axe 8.6, 7, the latter being fixed to a first and a second movable element of a nacelle, not shown, by means of a first and a second hinge axis 8, 9. The axis 9 is arranged perpendicular to the axis 8.
Plus précisément, les secondes extrémités des bielles 2, 3 sont reliées à un cardan 13 dont fait partie la chape 7 et présentant une articulation d'axe 14 parallèle à l'axe 8.More specifically, the second ends of the connecting rods 2, 3 are connected to a universal joint 13 of which the yoke 7 is part and having an axis articulation 14 parallel to the axis 8.
La première extrémité 4 de la seconde bielle 3 comporte une chape 10 articulée sur le premier axe d'articulation 8, la chape 10 comportant deux trous oblongs 11 disposés en regard l'un de l'autre. La première extrémité 4 de la première bielle 2 comporte en outre deux trous oblongs 12 traversés par le premier axe d'articulation 8 et disposés en regard l'un de l'autre.The first end 4 of the second connecting rod 3 comprises a yoke 10 hinged to the first hinge axis 8, the yoke 10 having two oblong holes 11 arranged facing one another. The first end 4 of the first connecting rod 2 further comprises two oblong holes 12 traversed by the first hinge axis 8 and arranged facing one another.
Les trous oblongs 11 , 12 présentent sensiblement la même longueur et sont agencés de manière décalés les uns par rapport aux autres de sorte que, dans un premier état de traction du dispositif de liaison, représenté aux figures 1 et 2, la seconde bielle 3 vient en butée contre le premier axe d'articulation 8, au niveau de la partie externe des trous oblongs 11 , tandis que la première bielle 2 est en retrait de l'axe 8 précité. De cette manière, dans le premier état de traction, seule la seconde bielle 3 est soumise à des contraintes de traction, la première bielle 2 n'étant soumise à aucune contrainte particulière.The oblong holes 11, 12 have substantially the same length and are arranged staggered with respect to each other so that, in a first traction state of the connecting device, shown in FIGS. 1 and 2, the second connecting rod 3 in abutment against the first hinge pin 8, at the outer portion of the oblong holes 11, while the first rod 2 is set back from the aforementioned axis 8. In this way, in the first state of traction, only the second link 3 is subjected to tensile stresses, the first link 2 being subjected to no particular constraint.
Les figures 3 et 4 représentent le dispositif de liaison 1 dans un second état, correspondant à un état de compression de celui-ci. Dans ce second état de compression, la première bielle 2 est en butée contre le premier axe d'articulation 8, au niveau de la partie interne des trous oblongs 12, tandis que la seconde bielle 3 est en retrait de l'axe 8 précité.Figures 3 and 4 show the connecting device 1 in a second state, corresponding to a state of compression thereof. In this second state of compression, the first link 2 abuts against the first hinge axis 8, at the inner portion of the oblong holes 12, while the second link 3 is set back from the aforementioned axis 8.
En fonction des dimensions des différents éléments, la première bielle 2 peut également venir en butée contre un fond concave 15 de la chape 6, ou encore venir à la fois en butée contre le fond 15 et contre l'axe 8.Depending on the dimensions of the various elements, the first connecting rod 2 can also abut against a concave bottom 15 of the yoke 6, or else come into abutment against the bottom 15 and against the axis 8.
Dans le cas où la première bielle 2 ne vient pas en butée contre l'axe 8, il est possible d'alléger celui-ci en le dimensionnant uniquement à des contraintes de traction successives plutôt qu'à des contraintes alternées de traction et de compression. Ainsi, seule la première bielle 2 est soumise à des contraintes de compression, la seconde bielle 3 n'étant soumise à aucune contrainte particulière.In the case where the first rod 2 does not abut against the axis 8, it is possible to lighten it by sizing it only to successive tensile stresses rather than alternating tensile and compressive stresses . Thus, only the first connecting rod 2 is subjected to compressive stresses, the second connecting rod 3 being subjected to no particular constraint.
En fonctionnement normal, le dispositif est soumis à l'un des deux états précités, de sorte qu'aucune des bielles 2, 3 n'est soumise à la fois à de la compression et à de la traction. Les bielles 2, 3 ne subissent donc pas de phénomène de fatigue, apparaissant lors d'une succession de contraintes de traction ou par l'alternance entre des contraintes de compression et des contraintes de traction.In normal operation, the device is subjected to one of the two aforementioned states, so that none of the connecting rods 2, 3 is subjected to both compression and traction. The connecting rods 2, 3 therefore do not undergo a fatigue phenomenon, occurring during a succession of tensile stresses or by the alternation between compressive stresses and tensile stresses.
Les figures 5 et 6 représentent un troisième état du dispositif de liaison 1 correspondant à un fonctionnement accidentel. Ce troisième état correspond en effet à une rupture de la seconde bielle 3. Comme cela est représenté plus particulièrement en figure 6, la première bielle 2, apte à réaliser le passage d'effort de compression entre les deux éléments articulés de la nacelle, est également apte à réaliser le passage d'effort de traction en cas de rupture de la seconde bielle 3. En effet, en cas de rupture et de traction sur le dispositif de liaison 1 , la première bielle 2 vient en butée contre le premier axe d'articulation 8, au niveau de la partie externe des trous oblongs 12. La première bielle 2 forme ainsi un chemin de passage pour les efforts de traction.Figures 5 and 6 show a third state of the connecting device 1 corresponding to accidental operation. This third state corresponds to a break of the second connecting rod 3. As shown more particularly in FIG. 6, the first connecting rod 2, capable of producing the passage of compressive force between the two articulated elements of the nacelle, is also capable of producing the passage of tensile force in the event of rupture. of the second connecting rod 3. Indeed, in case of breakage and traction on the connecting device 1, the first connecting rod 2 abuts against the first hinge axis 8, at the outer portion of the oblong holes 12. The first connecting rod 2 thus forms a pathway for the traction forces.
De même, selon le même principe, la seconde bielle 3, apte à réaliser le passage d'effort de traction entre les deux éléments articulés de la nacelle, est également apte à réaliser le passage d'effort de compression en cas de rupture de la première bielle 2.Similarly, according to the same principle, the second connecting rod 3, able to achieve the passage of traction force between the two articulated elements of the nacelle, is also able to achieve the passage of compressive force in case of breakage of the first connecting rod 2.
Comme il va de soi l'invention ne se limite pas à la forme de réalisation de ce dispositif de liaison, décrite ci-dessus à titre d'exemple, mais elle embrasse au contraire toutes les variantes. C'est ainsi qu'un tel dispositif pourrait être utilisé dans des domaines d'application différents de celui des nacelles. It goes without saying that the invention is not limited to the embodiment of this connecting device, described above by way of example, but it encompasses all variants. Thus such a device could be used in fields of application different from that of nacelles.

Claims

REVENDICATIONS
1. Dispositif de liaison (1 ), destiné à relier un premier et un second éléments articulés l'un par rapport à l'autre, caractérisé en ce qu'il comporte un élément de compression (2) conçu pour réaliser le passage d'un effort de compression d'un élément à un autre dans un premier état, et un élément de traction (3) conçu pour réaliser le passage d'un effort de traction d'un élément à un autre dans un second état, l'élément de compression formant en outre un élément de traction de substitution conçu pour réaliser le passage d'un effort de traction d'un élément à un autre, dans un troisième état correspondant à la rupture de l'élément de traction.1. Connecting device (1) for connecting a first and a second articulated elements relative to each other, characterized in that it comprises a compression element (2) designed to achieve the passage of a compressive force from one element to another in a first state, and a traction element (3) designed to effect the passage of a tensile force from one element to another in a second state, the element compression member further forming a substitution traction member adapted to effect the passage of a tensile force from one element to another in a third state corresponding to the breaking of the traction element.
2. Dispositif de liaison (1 ) selon la revendication 1 , caractérisé en ce que l'élément de compression comporte une première bielle (2), l'élément de traction comportant une seconde bielle (3), chaque bielle (2, 3) étant équipée d'une première et d'une seconde extrémités (4, 5) équipées de moyens d'articulation (8, 9), respectivement sur le premier et le second éléments articulés.2. Connecting device (1) according to claim 1, characterized in that the compression element comprises a first connecting rod (2), the traction element comprising a second connecting rod (3), each connecting rod (2, 3). being equipped with first and second ends (4, 5) equipped with hinge means (8, 9) respectively on the first and second articulated elements.
3. Dispositif de liaison (1 ) selon la revendication 2, caractérisé en ce que la seconde bielle (3) est logée dans la première bielle (2).3. Connecting device (1) according to claim 2, characterized in that the second connecting rod (3) is housed in the first connecting rod (2).
4. Dispositif de liaison (1 ) selon l'une des revendications 2 et 3, caractérisé en ce que chaque bielle (2, 3) comporte une ouverture oblongue (12, 11 ) au voisinage d'au moins une extrémité (4, 5), l'ouverture oblongue (12, 11 ) étant destinée au passage d'un axe d'articulation (8) du dispositif de liaison (1 ) sur l'élément correspondant.4. Connecting device (1) according to one of claims 2 and 3, characterized in that each rod (2, 3) has an oblong opening (12, 11) in the vicinity of at least one end (4, 5). ), the oblong opening (12, 11) being intended for the passage of a hinge axis (8) of the connecting device (1) on the corresponding element.
5. Dispositif de liaison (1 ) selon la revendication 4, caractérisé en ce que les ouvertures oblongues (11 , 12) sont agencées de sorte que, dans le premier état, la première bielle (2) est en butée contre l'axe d'articulation (8) tandis que la seconde bielle (3) est en retrait de celui-ci et que, dans le second état, la seconde bielle (3) est en butée contre l'axe d'articulation (8) tandis que la première bielle (2) est en retrait de celui-ci.5. Connecting device (1) according to claim 4, characterized in that the oblong openings (11, 12) are arranged so that, in the first state, the first connecting rod (2) abuts against the axis d articulation (8) while the second connecting rod (3) is set back from the latter and that, in the second state, the second connecting rod (3) abuts against the hinge axis (8) while the first rod (2) is set back from it.
6. Nacelle comportant un premier et un second éléments articulés l'un par rapport à l'autre, caractérisée en ce que les éléments articulés sont reliés par au moins un dispositif de liaison (1 ) selon l'une des revendications 1 à 5. 6. Nacelle comprising first and second elements articulated with respect to each other, characterized in that the articulated elements are connected by at least one connecting device (1) according to one of claims 1 to 5.
7. Aéronef, caractérisé en ce qu'il comporte au moins une nacelle selon la revendication 6. 7. Aircraft, characterized in that it comprises at least one nacelle according to claim 6.
EP08786954A 2007-08-20 2008-08-06 Coupling device intended to connect first and second elements which are articulated with respect to one another Withdrawn EP2181038A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0705935A FR2920178B1 (en) 2007-08-20 2007-08-20 CONNECTING DEVICE FOR CONNECTING FIRST AND SECOND ARTICULATED ELEMENTS RELATIVE TO EACH OTHER
PCT/EP2008/060348 WO2009024470A1 (en) 2007-08-20 2008-08-06 Coupling device intended to connect first and second elements which are articulated with respect to one another

Publications (1)

Publication Number Publication Date
EP2181038A1 true EP2181038A1 (en) 2010-05-05

Family

ID=39315172

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08786954A Withdrawn EP2181038A1 (en) 2007-08-20 2008-08-06 Coupling device intended to connect first and second elements which are articulated with respect to one another

Country Status (8)

Country Link
US (1) US8342770B2 (en)
EP (1) EP2181038A1 (en)
CN (1) CN101778764B (en)
BR (1) BRPI0813606A2 (en)
CA (1) CA2696716A1 (en)
FR (1) FR2920178B1 (en)
RU (1) RU2475420C2 (en)
WO (1) WO2009024470A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2920174A1 (en) * 2007-08-20 2009-02-27 Aircelle Sa CONNECTION DEVICE BETWEEN THE TWO HALF SHELLS OF AN AIRCRAFT ENGINE NACELLE, AND NACELLE EQUIPPED WITH SUCH A DEVICE
FR2962976B1 (en) * 2010-07-22 2013-07-26 Airbus Operations Sas CONNECTING DEVICE FOR CONNECTING A FIRST BODY TO A SECOND BODY, IN PARTICULAR FOR AN AIRCRAFT ENGINE ASSEMBLY
FR2963070B1 (en) * 2010-07-23 2014-02-14 Airbus Operations Sas AIRCRAFT COMPRISING A ROD COMPRISING A PART OF COMPOSITE MATERIAL
FR2965850B1 (en) * 2010-10-11 2012-12-14 Airbus Operations Sas SAFETY LINK DEVICE AND AIRCRAFT EQUIPPED WITH SUCH A SAFETY LINK DEVICE
FR2965867B1 (en) * 2010-10-12 2013-08-09 Airbus Operations Sas STRUCTURAL ROD ADAPTED TO FILTER LONGITUDINAL VIBRATIONS
FR2969578B1 (en) 2010-12-27 2013-02-08 Snecma DEVICE FOR SUSPENDING A TURBOJET ENGINE
US8632099B2 (en) * 2011-11-14 2014-01-21 Mac Trailer Manufacturing, Inc. Tank trailer having an air actuated handrail assembly
DE102014101189B4 (en) * 2014-01-31 2019-07-25 Hs Products Engineering Gmbh Power transmission device for a transmission and assembly method
DE102014105372A1 (en) * 2014-04-15 2015-10-29 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Device for protection against overload
CN108825674B (en) * 2014-11-28 2021-10-08 重庆西山科技股份有限公司 Performance testing device for operation power device
GB201503560D0 (en) 2015-03-03 2015-04-15 Rolls Royce Plc A system and method for applying a tensile load to a component
FR3037039B1 (en) 2015-06-03 2017-06-02 Aircelle Sa DEVICE FOR LOCKING PIVOTING HOODS OF A PUSH INVERTER
CN105908646A (en) * 2016-04-29 2016-08-31 闫鹏飞 Prompting device
US10612491B2 (en) * 2017-09-25 2020-04-07 Rohr, Inc. Mounting device with pin actuator

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3922104A (en) * 1974-09-20 1975-11-25 Us Navy Tension link control device
US4808023A (en) * 1985-02-12 1989-02-28 The United States Of America As Represented By The Secretary Of The Air Force Dual load path pin clevis joint
US4786202A (en) * 1985-02-12 1988-11-22 The United States Of America As Represented By The Secretary Of The Air Force Dual load path pin clevis joint
HU198649B (en) * 1986-06-17 1989-11-28 Finoszerelvenygyar Telescope arm with locked formation in ground state
US4836485A (en) * 1987-01-30 1989-06-06 Alliance Research Corporation Universally adjustable mounting device
RU2060186C1 (en) * 1990-07-02 1996-05-20 Женыс Мадыкенович Касылкасов Rail vehicle coupling
US5470118A (en) * 1992-12-02 1995-11-28 Burton; James E. Shear device for well service tools
FR2771459B1 (en) * 1997-11-27 2000-02-04 Aerospatiale TELESCOPIC ROD FOR OPENING A MOBILE HOOD, ESPECIALLY OF AN AIRCRAFT ENGINE NACELLE
FR2771710B1 (en) * 1997-12-03 2000-02-11 Aerospatiale OPENING DEVICE COMMON TO TWO ADJACENT HOODS FOR AN AIRCRAFT NACELLE
US6007267A (en) * 1998-07-16 1999-12-28 Kenneth Roberts Mechanical load fuse assembly
GB0124446D0 (en) * 2001-10-11 2001-12-05 Short Brothers Ltd Aircraft propulsive power unit
US6622963B1 (en) * 2002-04-16 2003-09-23 Honeywell International Inc. System and method for controlling the movement of an aircraft engine cowl door
US7093996B2 (en) * 2003-04-30 2006-08-22 General Electric Company Methods and apparatus for mounting a gas turbine engine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2009024470A1 *

Also Published As

Publication number Publication date
CN101778764B (en) 2013-07-17
CN101778764A (en) 2010-07-14
US20110110705A1 (en) 2011-05-12
FR2920178A1 (en) 2009-02-27
FR2920178B1 (en) 2009-10-30
RU2475420C2 (en) 2013-02-20
US8342770B2 (en) 2013-01-01
CA2696716A1 (en) 2009-02-26
BRPI0813606A2 (en) 2014-12-30
WO2009024470A1 (en) 2009-02-26
RU2010109814A (en) 2011-09-27

Similar Documents

Publication Publication Date Title
WO2009024470A1 (en) Coupling device intended to connect first and second elements which are articulated with respect to one another
EP2580120B1 (en) Fails-safe jet engine joint
EP2167384B1 (en) Pylon for coupling an engine for an aircraft having a rear engine attachment beam forming a rudder control bar
EP1858758B1 (en) Engine fastener of a mounting system interposed between an attachment strut and an aircraft engine
CA2613194C (en) Engine mount for an aircraft, to be placed between an engine and an engine mounting structure
EP2185414B1 (en) Aircraft engine attachment pylon with a four-point articulated spreader beam
FR3032180A1 (en) PROPELLANT ASSEMBLY COMPRISING A TURBOJET ENGINE AND A COUPLING MAT FOR A NEW DISTRIBUTION OF EFFORTS BETWEEN THE TURBOJET AND THE VIL
EP2137072B1 (en) Device for attaching an aircraft engine and aircraft comprising at least one such device
WO2008135366A1 (en) Aircraft engine mounting device and aircraft including at least one such device
WO2008135364A1 (en) Aircraft engine mounting structure including a rear engine anchor beam located at a distance from the structure box
WO2013128123A1 (en) Method for holding an adapter piece on a tubular housing of a turbo engine, and corresponding adapter piece and holding system
FR3058986A1 (en) REAR ATTACHMENT OF AN AIRCRAFT ENGINE COMPRISING BREAKWATER LIGHTS
EP0048191B1 (en) Airship fuselage structure resistant to longitudinal cracks of the skin
FR2963320A1 (en) Engine assembly i.e. turbofan assembly, for aircraft, has connection units ensuring passage of efforts along effort resumption directions defining effort resumption plane, where resumption plane and rod plane intercept along straight line
FR3021625A1 (en) FLEXIBLE CONNECTION BETWEEN THE FLOOR STRUCTURE AND THE HULL STRUCTURE OF AN AIRCRAFT.
EP4124575B1 (en) Propulsion assembly for aircraft comprising a turbojet, a mast and means for attaching the turbojet to the mast
FR2901241A1 (en) Door jettisoning device for military aircraft, has guiding unit with roller sliding in ramp to maintain upper element in axis of lower element during actuation of door, where upper element is disengaged from guiding unit above angle
FR3100530A1 (en) Aircraft engine assembly comprising a thrust force recovery device
WO2009027588A1 (en) Locking device
WO2019122634A1 (en) Suspension device
FR3004420A1 (en) SUSPENSION CRANK OF A TURBOPROPULSEUR
FR3081836A1 (en) PROPULSIF ASSEMBLY OF AN AIRCRAFT AND METHOD FOR VERIFYING THE INTEGRITY OF AN ENGINE FASTENER OF THE PROPULSIVE ASSEMBLY
WO2024089345A1 (en) Device for suspending an equipment item for a turbomachine on a turbomachine engine structure
FR3141440A1 (en) Device for suspending equipment for a turbomachine from a turbomachine engine structure
FR3141439A1 (en) Device for suspending equipment for a turbomachine from a turbomachine engine structure

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20100113

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN NACELLES

17Q First examination report despatched

Effective date: 20170221

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20181116