EP2190740A1 - Nacelle equipped with a device for detecting the locking state of a locking device - Google Patents

Nacelle equipped with a device for detecting the locking state of a locking device

Info

Publication number
EP2190740A1
EP2190740A1 EP08786951A EP08786951A EP2190740A1 EP 2190740 A1 EP2190740 A1 EP 2190740A1 EP 08786951 A EP08786951 A EP 08786951A EP 08786951 A EP08786951 A EP 08786951A EP 2190740 A1 EP2190740 A1 EP 2190740A1
Authority
EP
European Patent Office
Prior art keywords
locking
control handle
nacelle
locking member
cover
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Withdrawn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
EP08786951A
Other languages
German (de)
French (fr)
Inventor
Fabrice Provost
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 EP2190740A1 publication Critical patent/EP2190740A1/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Withdrawn legal-status Critical Current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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings

Definitions

  • the invention relates to a turbojet engine nacelle of an aircraft.
  • An aircraft is driven by several turbojets each housed in a nacelle also housing a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped.
  • These ancillary actuating devices comprise in particular a mechanical system for actuating thrust reversers.
  • a nacelle generally has a tubular structure comprising an air inlet in front of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a rear section capable of housing thrust reversal means and intended to surround the combustion chamber of the engine.
  • turbojet and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • Modern nacelles are often intended to house a turbofan engine capable of generating through the blades of the rotating fan a hot air flow (also called primary flow) from the combustion chamber of the turbojet engine.
  • a nacelle generally has an external structure, called Outer Fixed Structure (OFS), which defines, with a concentric internal structure, called Inner Fixed Structure (IFS), an annular flow channel, also called a vein, for channeling a flow of cold air, called secondary, which circulates outside the turbojet engine.
  • OFS Outer Fixed Structure
  • IFS Inner Fixed Structure
  • the primary and secondary flows are ejected from the turbojet engine from the rear of the nacelle.
  • Each propulsion unit of the aircraft is thus formed by a nacelle and a turbojet, and is suspended from a fixed structure of the aircraft, for example under a wing or on the fuselage, by means of a pylon or attached mast. to the turbojet engine or to the nacelle.
  • the rear section of the external structure of the nacelle is usually formed of a first and a second half-shell of substantially semicylindrical shape, on either side of a longitudinal vertical plane of symmetry of the nacelle, and mounted movable so as to be able to deploy between a working position and a maintenance position in order to give access to the turbojet engine.
  • the two half-shells are generally pivotally mounted about a longitudinal hinge axis at the top (at 12 o'clock) of the inverter.
  • the half-shells are maintained in closing position by means of locking devices arranged along a connecting line situated at the bottom (at 6 o'clock).
  • the two half-shells are in particular connected to one another at a front frame, which allows the attachment of the rear section to a fixed part of the middle section, via at least one locking device comprising a locking member equipping the first half-shell, a complementary locking member equipping the second half-shell, and a control handle fixed in the first half-shell and connected to the locking member through transmission means.
  • the control handle is usually designed so that it can be moved alternately from a stable open position where the locking member is open, to a stable locking position where the locking member is closed, passing through a unstable intermediate phase where the locking member is closed.
  • This control handle is equipped with a secondary locking system comprising a locking member allowing, once placed in the locking position, to lock said control handle in its locking position.
  • the control handle comprises a trigger which must be previously actuated by the operator to allow the rotation of said control handle towards its locking position. Once the latter is reached, the operator can release the trigger, which causes the translation of the locking member in the control handle and its engagement in an orifice presented by an internal part to block the control handle in its locking position.
  • the median section is traditionally formed from at least two covers mounted mobile in rotation about a longitudinal axis so as to be able to deploy each between a working position and a maintenance position. These covers are especially designed so that their rear ends are positioned around the front frame when in the working position, and are thus brought to cover the control handle of the locking device.
  • the control handle In the open position, the control handle protrudes from the connecting line located in the lower part, and is generally visible from the outside.
  • the intermediate position or when the locking member is not in its locking position, that is to say when the trigger is not engaged, it suffices for a slight lack of attention on the part of the operator so that it fails to detect that the control handle is not in its locking position.
  • hoods were folded and locked in the working position while the control handle was in the intermediate position or that the locking member was not in its locking position. Such a case is particularly worrying because, the control handle being unstable in this position, the locking member can be made to disengage from the complementary locking member under the effect of external stresses.
  • the object of the present invention is to remedy the disadvantage mentioned previously, simply and reliably, and for this purpose consists of a turbojet engine nacelle comprising a front air inlet section, a median section intended to surround a fan blower. turbojet, and a rear section formed from at least two half-shells connected to each other via at least one locking device actuated by a control handle equipped with a locking system secondary member comprising a locking member which, when placed in the locking position, blocks said control handle in its locking position, said middle section being formed from at least two covers that can be deployed between a working position and a maintenance position, characterized in that the blocking member and at least one zone of the inner face of one of the two covers are designed so as to ir abut against each other to prevent closing of said cover if the control handle is not in its locking position and / or if the locking member is not in its position of blocking.
  • the locking member comprises a rod, housed in the control handle, extended by a head.
  • this rod is caused to translate in the control handle to move alternately from a position where the head protrudes from said control handle when the latter is in the open position or in position intermediate, at a position where the head is housed in the control handle when the latter in the locking position.
  • the head comprises at least one outgrowth.
  • the latter preferably extends transversely to the rod.
  • the zone of the internal face of the cover comprises at least one shoulder oriented towards the inside.
  • the protrusion and the shoulder are designed so that said protrusion is in the path of the shoulder when the hood is folded towards its working position while the control handle is not located in its locking position and / or that the locking member is not in its locking position.
  • the shoulder is constituted by a portion of a stiffener equipping the inner face of the hood.
  • the present invention also relates to an aircraft, characterized in that it comprises at least one nacelle according to the invention.
  • Figure 1 is a schematic longitudinal sectional view of a nacelle according to the invention in the closed state
  • Figure 2 is a perspective view of the rear section of the nacelle shown in Figure 1;
  • Figure 3 is an enlarged partial view of the locking device equipping the nacelle shown in Figure 2;
  • Figure 4 is a schematic view of the control handle of the locking device of Figure 3, in the locking position;
  • Figure 5 is a schematic view of the locking device of Figure 3, when the cover is in abutment against the head of the locking member.
  • a nacelle 1 of an aircraft according to the invention as represented in FIG. 1, comprises, in a manner known per se, an external structure 2, so-called
  • OFS which defines an annular flow channel 3 with a concentric internal structure 4 surrounding the structure of the turbojet engine (not shown) proper behind a fan 5. More precisely, this external structure 2 is broken down into a front air intake section 6, a median section 7 intended to surround the fan 5, and a rear section 8 formed from at least two half-shells 9a, 9b. In the working position, the two half-shells 9a, 9b are positioned closer to the turbojet, and are conventionally held in this position using a plurality of locking devices 10, well known to man of the trade, and provided along a junction line located in the lower part (at 6 o'clock). As shown in FIG.
  • such a locking device 10 may notably be integrated in the front part of the rear section 8, and more particularly at the level of a front frame 11, the latter being the element enabling the rear section to be reattached. 8 to a fixed part of the median section 7.
  • the locking device 10, as shown in FIG. 3, schematically comprises a locking member 12 fitted to one of the two half-shells 9a, and a complementary locking member (not shown) equipping the other half-shell 9b.
  • this locking device 10 comprises a remote control handle 13 connected to the locking member 12 via transmission means comprising a connecting rod 15 having, on the one hand, a first end attached to a connecting rod 16 whose rotation is actuated by the pivoting of the control handle 13, and secondly, a second end indirectly attached to said locking member 12.
  • the locking member 12 is constituted by a hook whose pivoting is controlled in a conventional manner to the movement of the control handle 13 via a set of links 18 connecting the second end of the rod 15 to said hook 12.
  • the complementary locking member will be made in the form of a longitudinal axis about which the hook 12 can come to hang up or on the contrary deviate depending on whether the control handle 13 will be actuated for closing or opening of the locking device 10.
  • the control handle 13 of such a locking device 10 is designed to be able to be moved alternately from a stable open position in which the hook 12 is open to a position of stable locking where the hook 12 is closed, passing through an unstable intermediate phase where the hook 12 is closed.
  • this control handle 13 is equipped with a secondary locking system comprising a locking member in the form of a rod 19 allowing, once placed in the locking position, to block said control handle 13 in its locking position.
  • control handle 13 includes a trigger
  • the rod 19 is extended by a head 20 which, on the one hand, protrudes from the control handle 13 when the latter is in the open position or in the intermediate position, as shown in Figure 5, and secondly , is housed in the control handle 13 when it is in the locking position.
  • the head 20 is extended by an outgrowth 21, oriented towards the front, and extending transversely with respect to the rod 19.
  • the middle section 7 is traditionally formed from at least two covers 22a, 22b rotatably mounted around a longitudinal axis (not shown) so as to be able to deploy each between a working position and a maintenance position.
  • covers 22a, 22b are designed so as to each have a rear end which is positioned around the front frame 11 of the rear section 8 when in the working position.
  • the rear end of the cover 22a is made to cover the control handle 13 of the locking device 10 when said cover 22a is in the working position.
  • the cover 22a has, at its rear end, an inner face in which is fixed a stiffener 24 device, schematically shaped ⁇ .
  • this stiffener 24 therefore constitutes a peripheral shoulder whose part or zone abuts against the protrusion 21 when the cover 22a is folded towards its working position while the control handle 13 is not located in its locking position. In doing so, closing the cover 22a is made impossible, and the operator in charge of maintenance is immediately informed of the situation.

Abstract

The present invention relates to a nacelle comprising a mid-section and an aft- section formed from two half-shells (9a) interconnected by a locking device (10) actuated by an operating handle (13) equipped with a secondary locking system comprising a latching member (19) for latching said operating handle in its locking position, said mid-section being formed from two cowls which can be deployed between a working position and a maintenance position, characterized in that the latching member and a region of the internal face of one of the two cowls are designed so as to butt one against the other in order to prevent the closure of said cowl if the operating handle is not situated in its locking position and/or if the latching member is not in its latching position.

Description

NACELLE EQUIPEE D'UN DISPOSITIF DE DETECTION DE L'ETAT DE VERROUILLAGE NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LATCHING STATUS
D'UN DISPOSITIF DE VERROUILLAGEA LOCKING DEVICE
L'invention se rapporte à une nacelle de turboréacteur d'un aéronef.The invention relates to a turbojet engine nacelle of an aircraft.
Un aéronef est mu par plusieurs turboréacteurs logés chacun dans une nacelle abritant également un ensemble de dispositifs d'actionnement annexes liés à son fonctionnement et assurant diverses fonctions lorsque le turboréacteur est en fonctionnement ou à l'arrêt. Ces dispositifs d'actionnement annexes comprennent notamment un système mécanique d'actionnement d'inverseurs de poussée.An aircraft is driven by several turbojets each housed in a nacelle also housing a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped. These ancillary actuating devices comprise in particular a mechanical system for actuating thrust reversers.
Une nacelle présente généralement une structure tubulaire comprenant une entrée d'air en avant du turboréacteur, une section médiane destinée à entourer une soufflante du turboréacteur, une section arrière pouvant abriter des moyens d'inversion de poussée et destinée à entourer la chambre de combustion du turboréacteur, et est généralement terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur. Les nacelles modernes sont souvent destinées à abriter un turboréacteur double flux apte à générer par l'intermédiaire des pâles de la soufflante en rotation un flux d'air chaud (également appelé flux primaire) issu de la chambre de combustion du turboréacteur.A nacelle generally has a tubular structure comprising an air inlet in front of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a rear section capable of housing thrust reversal means and intended to surround the combustion chamber of the engine. turbojet, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine. Modern nacelles are often intended to house a turbofan engine capable of generating through the blades of the rotating fan a hot air flow (also called primary flow) from the combustion chamber of the turbojet engine.
Une nacelle présente généralement une structure externe, dite Outer Fixed Structure (OFS), qui définit, avec une structure interne concentrique, dite Inner Fixed Structure (IFS), un canal annulaire d'écoulement, encore appelé veine, visant à canaliser un flux d'air froid, dit secondaire, qui circule à l'extérieur du turboréacteur. Les flux primaire et secondaire sont éjectés du turboréacteur par l'arrière de la nacelle. Chaque ensemble propulsif de l'avion est ainsi formé par une nacelle et un turboréacteur, et est suspendu à une structure fixe de l'avion, par exemple sous une aile ou sur le fuselage, par l'intermédiaire d'un pylône ou mât rattaché au turboréacteur ou à la nacelle.A nacelle generally has an external structure, called Outer Fixed Structure (OFS), which defines, with a concentric internal structure, called Inner Fixed Structure (IFS), an annular flow channel, also called a vein, for channeling a flow of cold air, called secondary, which circulates outside the turbojet engine. The primary and secondary flows are ejected from the turbojet engine from the rear of the nacelle. Each propulsion unit of the aircraft is thus formed by a nacelle and a turbojet, and is suspended from a fixed structure of the aircraft, for example under a wing or on the fuselage, by means of a pylon or attached mast. to the turbojet engine or to the nacelle.
La section arrière de la structure externe de la nacelle est usuellement formée d'une première et d'une deuxième demi-coquilles de forme sensiblement hémicylindrique, de part et d'autre d'un plan vertical longitudinal de symétrie de la nacelle, et montées mobiles de manière à pouvoir se déployer entre une position de travail et une position de maintenance en vue de donner accès au turboréacteur. Les deux demi-coquilles sont généralement montées pivotantes autour d'un axe longitudinal formant charnière en partie supérieure (à 12 heures) de l'inverseur. Les demi-coquilles sont maintenues en position de fermeture au moyen de dispositifs de verrouillage disposés le long d'une ligne de jonction située en partie inférieure (à 6 heures).The rear section of the external structure of the nacelle is usually formed of a first and a second half-shell of substantially semicylindrical shape, on either side of a longitudinal vertical plane of symmetry of the nacelle, and mounted movable so as to be able to deploy between a working position and a maintenance position in order to give access to the turbojet engine. The two half-shells are generally pivotally mounted about a longitudinal hinge axis at the top (at 12 o'clock) of the inverter. The half-shells are maintained in closing position by means of locking devices arranged along a connecting line situated at the bottom (at 6 o'clock).
De façon classique, les deux demi-coquilles sont notamment reliées l'une à l'autre au niveau d'un cadre avant, qui permet le rattachement de la section arrière à une partie fixe de la section médiane, par l'intermédiaire d'au moins un dispositif de verrouillage comprenant un organe de verrouillage équipant la première demi-coquille, un organe de verrouillage complémentaire équipant la seconde demi-coquille, et une poignée de commande fixée dans la première demi-coquille et reliée à l'organe de verrouillage par l'intermédiaire de moyens de transmission.Conventionally, the two half-shells are in particular connected to one another at a front frame, which allows the attachment of the rear section to a fixed part of the middle section, via at least one locking device comprising a locking member equipping the first half-shell, a complementary locking member equipping the second half-shell, and a control handle fixed in the first half-shell and connected to the locking member through transmission means.
La poignée de commande est habituellement conçue de manière à pouvoir être déplacée alternativement d'une position d'ouverture stable où l'organe de verrouillage est ouvert, à une position de verrouillage stable où l'organe de verrouillage est fermé, en passant par une phase intermédiaire instable où l'organe de verrouillage est fermé.The control handle is usually designed so that it can be moved alternately from a stable open position where the locking member is open, to a stable locking position where the locking member is closed, passing through a unstable intermediate phase where the locking member is closed.
Cette poignée de commande est équipée d'un système de verrouillage secondaire comprenant un organe de blocage permettant, une fois placé en position de blocage, de bloquer ladite poignée de commande dans sa position de verrouillage. Pour cela, la poignée de commande comprend une gâchette qui doit être préalablement actionnée par l'opérateur pour permettre la mise en rotation de ladite poignée de commande en direction de sa position de verrouillage. Une fois cette dernière atteinte, l'opérateur peut relâcher la gâchette, ce qui provoque la translation de l'organe de blocage dans la poignée de commande et son engagement dans un orifice présenté par une pièce interne en vue de bloquer la poignée de commande dans sa position de verrouillage.This control handle is equipped with a secondary locking system comprising a locking member allowing, once placed in the locking position, to lock said control handle in its locking position. For this, the control handle comprises a trigger which must be previously actuated by the operator to allow the rotation of said control handle towards its locking position. Once the latter is reached, the operator can release the trigger, which causes the translation of the locking member in the control handle and its engagement in an orifice presented by an internal part to block the control handle in its locking position.
La section médiane est traditionnellement formée à partir d'au moins deux capots montés mobiles en rotation autour d'un axe longitudinal de manière à pouvoir se déployer chacun entre une position de travail et une position de maintenance. Ces capots sont notamment conçus pour que leurs extrémités arrières viennent se positionner autour du cadre avant lorsqu'ils sont en position de travail, et soient donc amenés à recouvrir la poignée de commande du dispositif de verrouillage.The median section is traditionally formed from at least two covers mounted mobile in rotation about a longitudinal axis so as to be able to deploy each between a working position and a maintenance position. These covers are especially designed so that their rear ends are positioned around the front frame when in the working position, and are thus brought to cover the control handle of the locking device.
En position d'ouverture, la poignée de commande fait saillie de la ligne de jonction située en partie inférieure, et est généralement visible depuis l'extérieur. En position intermédiaire, ou lorsque l'organe de blocage n'est pas dans sa position de blocage, c'est-à-dire lorsque la gâchette n'est pas engagée, il suffit d'un léger manque d'attention de la part de l'opérateur pour que celui-ci omette de détecter que la poignée de commande n'est pas dans sa position de verrouillage. L'expérience a montré que des capots ont été rabattus et verrouillés en position de travail alors que la poignée de commande était en position intermédiaire ou que l'organe de blocage n'était pas dans sa position de blocage. Un tel cas de figure est particulièrement préoccupant car, la poignée de commande étant instable dans cette position, l'organe de verrouillage peut être amené à se désengager de l'organe de verrouillage complémentaire sous l'effet de sollicitations extérieures.In the open position, the control handle protrudes from the connecting line located in the lower part, and is generally visible from the outside. In the intermediate position, or when the locking member is not in its locking position, that is to say when the trigger is not engaged, it suffices for a slight lack of attention on the part of the operator so that it fails to detect that the control handle is not in its locking position. Experience has shown that hoods were folded and locked in the working position while the control handle was in the intermediate position or that the locking member was not in its locking position. Such a case is particularly worrying because, the control handle being unstable in this position, the locking member can be made to disengage from the complementary locking member under the effect of external stresses.
La présente invention a pour but de remédier à l'inconvénient évoqué précédemment, de façon simple et fiable, et consiste pour cela en une nacelle de turboréacteur comprenant une section avant d'entrée d'air, une section médiane destinée à entourer une soufflante du turboréacteur, et une section arrière formée à partir d'au moins deux demi-coquilles reliées l'une à l'autre par l'intermédiaire d'au moins un dispositif de verrouillage actionné par une poignée de commande équipée d'un système de verrouillage secondaire comprenant un organe de blocage permettant, une fois placé en position de blocage, de bloquer ladite poignée de commande dans sa position de verrouillage, ladite section médiane étant formée à partir d'au moins deux capots pouvant se déployer entre une position de travail et une position de maintenance, caractérisée en ce que l'organe de blocage et au moins une zone de la face interne de l'un des deux capots sont conçus de manière à venir en butée l'un contre l'autre afin d'empêcher la fermeture dudit capot si la poignée de commande n'est située pas dans sa position de verrouillage et/ou si l'organe de blocage n'est pas dans sa position de blocage.The object of the present invention is to remedy the disadvantage mentioned previously, simply and reliably, and for this purpose consists of a turbojet engine nacelle comprising a front air inlet section, a median section intended to surround a fan blower. turbojet, and a rear section formed from at least two half-shells connected to each other via at least one locking device actuated by a control handle equipped with a locking system secondary member comprising a locking member which, when placed in the locking position, blocks said control handle in its locking position, said middle section being formed from at least two covers that can be deployed between a working position and a maintenance position, characterized in that the blocking member and at least one zone of the inner face of one of the two covers are designed so as to ir abut against each other to prevent closing of said cover if the control handle is not in its locking position and / or if the locking member is not in its position of blocking.
Un avantage important en termes de masse, encombrement et coût découle du fait qu'une telle nacelle est ainsi parfaitement sécurisée sans qu'il soit nécessaire de dupliquer la poignée de commande du dispositif de verrouillage, ou le dispositif de verrouillage lui-même.An important advantage in terms of weight, bulk and cost derives from the fact that such a platform is thus perfectly secure without the need to duplicate the control handle of the locking device, or the locking device itself.
Préférentiellement, l'organe de blocage comprend une tige, logée dans la poignée de commande, prolongée par une tête. De façon classique, cette tige est amenée à se translater dans la poignée de commande afin de passer alternativement d'une position où la tête fait saillie de ladite poignée de commande lorsque cette dernière est en position d'ouverture ou en position intermédiaire, à une position où la tête est logée dans la poignée de commande lorsque celle-ci en position de verrouillage.Preferably, the locking member comprises a rod, housed in the control handle, extended by a head. Conventionally, this rod is caused to translate in the control handle to move alternately from a position where the head protrudes from said control handle when the latter is in the open position or in position intermediate, at a position where the head is housed in the control handle when the latter in the locking position.
Préférentiellement encore, la tête comporte au moins une excroissance. Cette dernière s'étend de préférence transversalement à la tige. Avantageusement, la zone de la face interne du capot comprend au moins un épaulement orienté vers l'intérieur.Preferentially, the head comprises at least one outgrowth. The latter preferably extends transversely to the rod. Advantageously, the zone of the internal face of the cover comprises at least one shoulder oriented towards the inside.
Avantageusement encore, l'excroissance et l'épaulement sont conçus de manière à ce que ladite excroissance soit sur la trajectoire de l'épaulement lorsque le capot est rabattu en direction de sa position de travail alors que la poignée de commande n'est pas située dans sa position de verrouillage et/ou que l'organe de blocage n'est pas dans sa position de blocage.Advantageously, the protrusion and the shoulder are designed so that said protrusion is in the path of the shoulder when the hood is folded towards its working position while the control handle is not located in its locking position and / or that the locking member is not in its locking position.
Selon un mode de réalisation particulièrement préféré, l'épaulement est constitué par une partie d'un raidisseur équipant la face interne du capot.According to a particularly preferred embodiment, the shoulder is constituted by a portion of a stiffener equipping the inner face of the hood.
La présente invention se rapporte également à un aéronef, caractérisé en ce qu'il comprend au moins une nacelle selon l'invention.The present invention also relates to an aircraft, characterized in that it comprises at least one nacelle according to the invention.
La mise en œuvre de l'invention sera mieux comprise à l'aide de la description détaillée qui est exposée ci-dessous en regard du dessin annexé dans lequel :The implementation of the invention will be better understood with the aid of the detailed description which is set out below with reference to the appended drawing in which:
La figure 1 est une vue schématique en coupe longitudinale d'une nacelle selon l'invention à l'état de fermeture ;Figure 1 is a schematic longitudinal sectional view of a nacelle according to the invention in the closed state;
La figure 2 est une vue en perspective de la section arrière de la nacelle représentée à la figure 1 ; La figure 3 est une vue partielle agrandie du dispositif de verrouillage équipant la nacelle représentée à la figure 2 ;Figure 2 is a perspective view of the rear section of the nacelle shown in Figure 1; Figure 3 is an enlarged partial view of the locking device equipping the nacelle shown in Figure 2;
La figure 4 est une vue schématique de la poignée de commande du dispositif de verrouillage de la figure 3, en position de verrouillage ;Figure 4 is a schematic view of the control handle of the locking device of Figure 3, in the locking position;
La figure 5 est une vue schématique du dispositif de verrouillage de la figure 3, lorsque le capot est en butée contre la tête de l'organe de blocage.Figure 5 is a schematic view of the locking device of Figure 3, when the cover is in abutment against the head of the locking member.
Une nacelle 1 d'un aéronef selon l'invention, telle que représentée à la figure 1 , comprend de manière connue en soi une structure externe 2, diteA nacelle 1 of an aircraft according to the invention, as represented in FIG. 1, comprises, in a manner known per se, an external structure 2, so-called
OFS, qui définit un canal annulaire 3 d'écoulement avec une structure interne 4 concentrique entourant la structure du turboréacteur (non représenté) proprement dite en arrière d'une soufflante 5. Plus précisément, cette structure externe 2 se décompose en une section avant 6 d'entrée d'air, une section médiane 7 destinée à entourer la soufflante 5, et une section arrière 8 formée à partir d'au moins deux demi- coquilles 9a, 9b. En position de travail, les deux demi-coquilles 9a, 9b sont positionnées au plus près du turboréacteur, et sont maintenues de façon classique dans cette position à l'aide d'une pluralité de dispositifs de verrouillage 10, bien connus de l'homme du métier, et prévus le long d'une ligne de jonction située en partie inférieure (à 6 heures). Comme représenté à la figure 2, un tel dispositif de verrouillage 10 peut notamment être intégré en partie avant de la section arrière 8, et plus spécialement au niveau d'un cadre avant 11 , ce dernier étant l'élément permettant de rattacher la section arrière 8 à une partie fixe de la section médiane 7. Le dispositif de verrouillage 10, tel que représenté à la figure 3, comprend schématiquement un organe de verrouillage 12 équipant l'une des deux demi-coquilles 9a, et un organe de verrouillage complémentaire (non représenté) équipant l'autre demi-coquille 9b.OFS, which defines an annular flow channel 3 with a concentric internal structure 4 surrounding the structure of the turbojet engine (not shown) proper behind a fan 5. More precisely, this external structure 2 is broken down into a front air intake section 6, a median section 7 intended to surround the fan 5, and a rear section 8 formed from at least two half-shells 9a, 9b. In the working position, the two half-shells 9a, 9b are positioned closer to the turbojet, and are conventionally held in this position using a plurality of locking devices 10, well known to man of the trade, and provided along a junction line located in the lower part (at 6 o'clock). As shown in FIG. 2, such a locking device 10 may notably be integrated in the front part of the rear section 8, and more particularly at the level of a front frame 11, the latter being the element enabling the rear section to be reattached. 8 to a fixed part of the median section 7. The locking device 10, as shown in FIG. 3, schematically comprises a locking member 12 fitted to one of the two half-shells 9a, and a complementary locking member ( not shown) equipping the other half-shell 9b.
De façon classique, ce dispositif de verrouillage 10 comprend une poignée de commande 13 déportée reliée à l'organe de verrouillage 12 par l'intermédiaire de moyens de transmission comprenant une bielle 15 présentant, d'une part, une première extrémité rattachée à une biellette 16 dont la mise en rotation est actionnée par le pivotement de la poignée de commande 13, et d'autre part, une seconde extrémité rattachée indirectement audit organe de verrouillage 12.In a conventional manner, this locking device 10 comprises a remote control handle 13 connected to the locking member 12 via transmission means comprising a connecting rod 15 having, on the one hand, a first end attached to a connecting rod 16 whose rotation is actuated by the pivoting of the control handle 13, and secondly, a second end indirectly attached to said locking member 12.
L'organe de verrouillage 12 est constitué par un crochet dont le pivotement est asservi de façon classique au mouvement de la poignée de commande 13 par l'intermédiaire d'un jeu de biellettes 18 reliant la seconde extrémité de la tige 15 audit crochet 12. L'organe de verrouillage complémentaire sera réalisé sous la forme d'un axe longitudinal autour duquel le crochet 12 pourra venir se raccrocher ou au contraire s'écarter selon que la poignée de commande 13 sera actionnée en vue de la fermeture ou de l'ouverture du dispositif de verrouillage 10.The locking member 12 is constituted by a hook whose pivoting is controlled in a conventional manner to the movement of the control handle 13 via a set of links 18 connecting the second end of the rod 15 to said hook 12. The complementary locking member will be made in the form of a longitudinal axis about which the hook 12 can come to hang up or on the contrary deviate depending on whether the control handle 13 will be actuated for closing or opening of the locking device 10.
La poignée de commande 13 d'un tel dispositif de verrouillage 10 est conçue de manière à pouvoir être déplacée alternativement d'une position d'ouverture stable dans laquelle le crochet 12 est ouvert à une position de verrouillage stable où le crochet 12 est fermé, en passant par une phase intermédiaire instable où le crochet 12 est fermé.The control handle 13 of such a locking device 10 is designed to be able to be moved alternately from a stable open position in which the hook 12 is open to a position of stable locking where the hook 12 is closed, passing through an unstable intermediate phase where the hook 12 is closed.
De façon classique, cette poignée de commande 13 est équipée d'un système de verrouillage secondaire comprenant un organe de blocage réalisé sous la forme d'une tige 19 permettant, une fois placée en position de blocage, de bloquer ladite poignée de commande 13 dans sa position de verrouillage.In a conventional manner, this control handle 13 is equipped with a secondary locking system comprising a locking member in the form of a rod 19 allowing, once placed in the locking position, to block said control handle 13 in its locking position.
Pour cela, la poignée de commande 13 comprend une gâchetteFor this, the control handle 13 includes a trigger
(non représentée) qui doit être préalablement actionnée par l'opérateur pour permettre la mise en rotation de ladite poignée de commande 13 en direction de sa position de verrouillage. Une fois cette dernière atteinte, l'opérateur peut relâcher la gâchette, ce qui provoque la translation de la tige 19 dans la poignée de commande 13 et son engagement dans un orifice (non représenté) présenté par une pièce interne afin de bloquer la poignée de commande 13 dans sa position de verrouillage.(Not shown) which must be previously actuated by the operator to allow the rotation of said control handle 13 towards its locking position. Once this is reached, the operator can release the trigger, which causes the translation of the rod 19 in the control handle 13 and its engagement in an orifice (not shown) presented by an internal part to block the handle of control 13 in its locking position.
La tige 19 est prolongée par une tête 20 qui, d'une part, fait saillie de la poignée de commande 13 lorsque cette dernière est en position d'ouverture ou en position intermédiaire, comme représenté à la figure 5, et d'autre part, est logée dans la poignée de commande 13 lorsque celle-ci est en position de verrouillage.The rod 19 is extended by a head 20 which, on the one hand, protrudes from the control handle 13 when the latter is in the open position or in the intermediate position, as shown in Figure 5, and secondly , is housed in the control handle 13 when it is in the locking position.
Selon l'invention, la tête 20 est prolongée par une excroissance 21 , orientée vers l'avant, et s'étendant transversalement par rapport à la tige 19.According to the invention, the head 20 is extended by an outgrowth 21, oriented towards the front, and extending transversely with respect to the rod 19.
La section médiane 7 est traditionnellement formée à partir d'au moins deux capots 22a, 22b montés mobiles en rotation autour d'un axe longitudinal (non représenté) de manière à pouvoir se déployer chacun entre une position de travail et une position de maintenance.The middle section 7 is traditionally formed from at least two covers 22a, 22b rotatably mounted around a longitudinal axis (not shown) so as to be able to deploy each between a working position and a maintenance position.
Ces capots 22a, 22b sont conçus de manière à présenter chacun une extrémité arrière venant se positionner autour du cadre avant 11 de la section arrière 8 lorsqu'ils sont en position de travail. Ainsi, l'extrémité arrière du capot 22a est amené à recouvrir la poignée de commande 13 du dispositif de verrouillage 10 lorsque ledit capot 22a se retrouve en position de travail.These covers 22a, 22b are designed so as to each have a rear end which is positioned around the front frame 11 of the rear section 8 when in the working position. Thus, the rear end of the cover 22a is made to cover the control handle 13 of the locking device 10 when said cover 22a is in the working position.
De façon classique, et comme représenté à la figure 4, le capot 22a présente, au niveau de son extrémité arrière, une face interne dans laquelle est fixé un raidisseur 24 périphérique, schématiquement en forme de Ω. Comme représenté à la figure 5, ce raidisseur 24 constitue de ce fait un épaulement périphérique dont une partie ou zone vient en butée contre l'excroissance 21 lorsque le capot 22a est rabattu en direction de sa position de travail alors que la poignée de commande 13 n'est pas située dans sa position de verrouillage. Ce faisant, la fermeture du capot 22a est rendue impossible, et l'opérateur en charge de la maintenance est immédiatement informé de la situation.Conventionally, and as shown in Figure 4, the cover 22a has, at its rear end, an inner face in which is fixed a stiffener 24 device, schematically shaped Ω. As shown in FIG. 5, this stiffener 24 therefore constitutes a peripheral shoulder whose part or zone abuts against the protrusion 21 when the cover 22a is folded towards its working position while the control handle 13 is not located in its locking position. In doing so, closing the cover 22a is made impossible, and the operator in charge of maintenance is immediately informed of the situation.
Il est à noter que cette interaction entre l'excroissance 21 et le raidisseur 24 peut se produire aussi bien lorsque la poignée de commande 13 est en position d'ouverture qu'en position intermédiaire, et/ou lorsque la gâchette n'est pas engagée. Bien que l'invention ait été décrite en liaison avec des exemples particuliers de réalisation, il est bien évident qu'elle n'y est nullement limitée et qu'elle comprend tous les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention. It should be noted that this interaction between the protrusion 21 and the stiffener 24 can occur both when the control handle 13 is in the open position in the intermediate position, and / or when the trigger is not engaged . Although the invention has been described in connection with particular embodiments, it is obvious that it is not limited thereto and that it comprises all the technical equivalents of the means described and their combinations if they are within the scope of the invention.

Claims

REVENDICATIONS
1.- Nacelle (1 ) de turboréacteur comprenant une section avant (6) d'entrée d'air, une section médiane (7) destinée à entourer une soufflante (5) du turboréacteur, et une section arrière (8) formée à partir d'au moins deux demi-coquilles (9a, 9b) reliées l'une à l'autre par l'intermédiaire d'au moins un dispositif de verrouillage (10) actionné par une poignée de commande (13) équipée d'un système de verrouillage secondaire comprenant un organe de blocage (19) permettant, une fois placé en position de blocage, de bloquer ladite poignée de commande dans sa position de verrouillage, ladite section médiane étant formée à partir d'au moins deux capots (22a, 22b) pouvant se déployer entre une position de travail et une position de maintenance, caractérisée en ce que l'organe de blocage comprend une tige (19), logée dans la poignée de commande (13), prolongée par une tête (20), l'organe de blocage et au moins une zone de la face interne de l'un des deux capots (22a) étant conçus de manière à venir en butée l'un contre l'autre afin d'empêcher la fermeture dudit capot si la poignée de commande n'est située pas dans sa position de verrouillage et/ou si l'organe de blocage n'est pas dans sa position de blocage.1.- turbojet engine nacelle (1) comprising a front air inlet section (6), a median section (7) intended to surround a fan (5) of the turbojet engine, and a rear section (8) formed from at least two half-shells (9a, 9b) connected to one another by means of at least one locking device (10) actuated by a control handle (13) equipped with a system secondary locking device comprising a locking member (19) enabling, once placed in the locking position, to lock said control handle in its locking position, said middle section being formed from at least two covers (22a, 22b ) that can be deployed between a working position and a maintenance position, characterized in that the locking member comprises a rod (19) housed in the control handle (13), extended by a head (20), blocking member and at least one zone of the inner face of one of the two covers (2 2a) being designed to abut against each other to prevent closure of said cover if the control handle is not in its locking position and / or if the locking member is not in its blocking position.
2.- Nacelle (1 ) selon la revendication 1 , caractérisée en ce que la tête (20) comporte au moins une excroissance (21 ).2. Nacelle (1) according to claim 1, characterized in that the head (20) comprises at least one protrusion (21).
3.- Nacelle (1 ) selon la revendication 2, caractérisée en ce que l'excroissance (21 ) s'étend transversalement à la tige (19).3. The nacelle (1) according to claim 2, characterized in that the protrusion (21) extends transversely to the rod (19).
4.- Nacelle (1 ) selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la zone de la face interne du capot (22a) comprend au moins un épaulement (24) orienté vers l'intérieur.4. Nacelle (1) according to any one of claims 1 to 3, characterized in that the area of the inner face of the cover (22a) comprises at least one shoulder (24) facing inwards.
5.- Nacelle (1 ) selon les revendications 3 et 4, caractérisée en ce que l'excroissance (21 ) et l'épaulement (24) sont conçus de manière à ce que ladite excroissance soit sur la trajectoire de l'épaulement lorsque le capot (22a) est rabattu en direction de sa position de travail alors que la poignée de commande (13) n'est pas située dans sa position de verrouillage et/ou que l'organe de blocage n'est pas dans sa position de blocage. 5. Nacelle (1) according to claims 3 and 4, characterized in that the protrusion (21) and the shoulder (24) are designed so that said protrusion is on the path of the shoulder when the cover (22a) is folded towards its working position while the control handle (13) is not in its locking position and / or the locking member is not in its locking position .
6.- Nacelle (1 ) selon la revendication 5, caractérisée en ce que l'épaulement est constitué par une partie d'un raidisseur (24) équipant la face interne du capot (22a).6. Nacelle (1) according to claim 5, characterized in that the shoulder is constituted by a portion of a stiffener (24) fitted to the inner face of the cover (22a).
7.- Aéronef, caractérisé en ce qu'il comprend au moins une nacelle (1 ) selon l'une quelconque des revendications 1 à 6. 7. Aircraft, characterized in that it comprises at least one nacelle (1) according to any one of claims 1 to 6.
EP08786951A 2007-08-20 2008-08-06 Nacelle equipped with a device for detecting the locking state of a locking device Withdrawn EP2190740A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0705937A FR2920144B1 (en) 2007-08-20 2007-08-20 NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LATCHING STATE OF A LATCHING DEVICE
PCT/EP2008/060345 WO2009024469A1 (en) 2007-08-20 2008-08-06 Nacelle equipped with a device for detecting the locking state of a locking device

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EP2190740A1 true EP2190740A1 (en) 2010-06-02

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EP08786951A Withdrawn EP2190740A1 (en) 2007-08-20 2008-08-06 Nacelle equipped with a device for detecting the locking state of a locking device

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US (1) US9132920B2 (en)
EP (1) EP2190740A1 (en)
CN (1) CN101778766B (en)
BR (1) BRPI0814908A2 (en)
CA (1) CA2696714C (en)
FR (1) FR2920144B1 (en)
RU (1) RU2469919C2 (en)
WO (1) WO2009024469A1 (en)

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FR2920144A1 (en) 2009-02-27
CA2696714C (en) 2015-11-24
CN101778766B (en) 2014-05-07
RU2010109785A (en) 2011-09-27
CN101778766A (en) 2010-07-14
CA2696714A1 (en) 2009-02-26
US9132920B2 (en) 2015-09-15
FR2920144B1 (en) 2010-01-08
US20110182728A1 (en) 2011-07-28
BRPI0814908A2 (en) 2015-02-03
WO2009024469A1 (en) 2009-02-26
RU2469919C2 (en) 2012-12-20

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