EP2586707B1 - Dispositif de verrouillage de sécurité pour le capuchon d'une gondole de moteur d'avion - Google Patents

Dispositif de verrouillage de sécurité pour le capuchon d'une gondole de moteur d'avion Download PDF

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Publication number
EP2586707B1
EP2586707B1 EP11382332.2A EP11382332A EP2586707B1 EP 2586707 B1 EP2586707 B1 EP 2586707B1 EP 11382332 A EP11382332 A EP 11382332A EP 2586707 B1 EP2586707 B1 EP 2586707B1
Authority
EP
European Patent Office
Prior art keywords
fan cowl
panel
cowl doors
power unit
locking device
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.)
Active
Application number
EP11382332.2A
Other languages
German (de)
English (en)
Other versions
EP2586707A1 (fr
Inventor
Francisco José Benitez Guerrero
Ramón Ramos Gallo
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.)
Airbus Defence and Space SA
Original Assignee
Airbus Defence and Space 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 Airbus Defence and Space SA filed Critical Airbus Defence and Space SA
Priority to EP11382332.2A priority Critical patent/EP2586707B1/fr
Priority to ES11382332.2T priority patent/ES2569127T3/es
Publication of EP2586707A1 publication Critical patent/EP2586707A1/fr
Application granted granted Critical
Publication of EP2586707B1 publication Critical patent/EP2586707B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • E—FIXED CONSTRUCTIONS
    • E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
    • E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
    • E05B41/00—Locks with visible indication as to whether the lock is locked or unlocked

Definitions

  • the present invention relates to a security locking device for assuring a correct closure of the fan cowl doors of an aircraft power unit nacelle.
  • An aircraft having a power unit supported in the airframe mounted configuration comprises an engine and a nacelle structure housing said engine.
  • the nacelle structure comprises two displaceable parts called fan cowl doors or cowlings which can be opened on the ground during maintenance operations to access the various items of the power unit, the cowlings or fan cowl doors being closed and properly latched during operational conditions of the aircraft, therefore providing aerodynamic continuity for the power unit in flight.
  • the nacelle usually comprises fan cowl locking means fixing and latching the fan cowl doors during operation of the aircraft.
  • an indication device is also provided for indicating if these fan cowl locking means are not properly latched.
  • This indication device comprises a panel fixed by rotating means on one of the two fan cowlings, the panel being closed on that one fan cowling by means of several primary locking means by rotating on said rotating means, therefore covering at least partially the fan cowl locking means of the fan cowl doors, such that all the fan cowl locking means have to be properly latched for the panel being closed.
  • the present invention is oriented to the solution of the above-mentioned drawbacks.
  • the present invention relates to a security locking device for assuring a correct closure of the fan cowl doors of an aircraft power unit nacelle.
  • the fan cowl doors of the nacelle structure of an aircraft housing an engine are closed when the aircraft is in flight by means of fan cowl locking means.
  • an indication device rotating over rotating means located in one of the two fan cowl doors, is provided, such that this indication device comprises a panel fixed on one of the two fan cowl doors by means of a primary locking device, such that, by rotating the panel on the rotating means the panel is latched over the fan cowl doors, covering at least partially the fan cowl locking means.
  • a security locking device is provided, providing security alternative latching for the cited indication device.
  • the security locking device of the invention comprises security locking means providing the security alternative latch of the indication device, as these security locking means close automatically over the fan cowl locking means, without the need of further operation on the part of the maintenance personnel. Therefore, the indication device can be fixed by the primary locking device and also by security locking means such that, even if the primary locking device does not properly latch the indication device over the fan cowl doors, the security locking means assure that the indication device is latched over the fan cowl doors, as the security locking means are latched without the need of being operated.
  • the primary locking device fixes the panel of the indication device on one of the fan cowl doors by rotating on the mentioned rotating means, such that the panel, once it is closed, covers at least partially the fan cowl locking means of the fan cowl doors.
  • This primary locking device is designed having an equilibrated and aligned engaged status, also being of easy and friendly manipulation for the maintenance personnel.
  • the security locking means give a further security latch for the indication device, preventing the detachment of the panel in the indication device in the case in which the primary locking device is not actuating properly, that is, in the case in which the primary locking device is not properly latched on the fan cowl door.
  • the present invention relates to a security locking device 100 for assuring a correct closure of the fan cowl doors 10, 20 of an aircraft power unit nacelle.
  • the fan cowl doors 10, 20 are closed by means of fan cowl locking means 30.
  • an indication device 40 is provided, such that this indication device 40 comprises a panel 41 fixed by rotating means 42 on one of the two fan cowl doors 10 or 20.
  • the panel 41 is fixed on one of the fan cowl doors 10 or 20 by a primary locking device 101.
  • a security locking device 100 is provided, providing security alternative latching for the correct latch of the cited indication device 40.
  • the security locking device 100 of the invention comprises security locking means 102.
  • the primary locking device 101 engages the panel 41 of the indication device 40 on one of the fan cowl doors 10 or 20 by rotating on the mentioned rotating means 42, such that the panel 41, once it is engaged by the primary locking device 101, covers at least partially the fan cowl locking means 30.
  • the primary locking device 101 is designed having an equilibrated and aligned engaged status, also being of easy and friendly manipulation for the maintenance personnel.
  • the security locking means 102 of the invention give a further security latch, preventing the detachment of the panel 41 in the indication device 40 in the case in which primary locking device 101 is not properly latched on the fan cowl door 10 or 20.
  • the security locking means 102 of the invention act as a safety device, providing a positive lock or latch of the panel 41 over the fan cowl door 10 or 20, at the tip of the panel 41, when this panel 41 is slammed without any further operation or actuation. Therefore, the security locking device 100of the invention avoids possible failures in cases where the fan cowl locking means 30 or the primary locking device 101 are not properly latched, as the security locking means 102 are latched automatically as the panel 41 in the indication device 40 is closed, without the need of further operation on the part of the maintenance personnel.
  • the security locking means 102 comprise engaging means 50 located in the panel 41 engaging with receiving means 60 located in the fan cowl doors, 10 or 20 (see Figures 6a and 6b ).
  • the primary locking device 101 will preferably have a design based on a pressure relief latch design, comprising an opening 6, typically a slot, than can be operated by means of a screwdriver, and adjusting means 7, typically a bolt, for setting the grip of the panel 41, preferably varying from 7 mm up to 12 mm.
  • the kinematics of the primary locking device 101 is such that it ensures no contact in neither the opening nor in the closing sequences of operation of the panel 41 in the worst case of tolerances.
  • the engaging means 50 in the security locking means 102 comprise a hook 51 rotating around a pin 52 by support bushings 53 and a spring 55, located on a support 54 installed in the panel 41 (see Figures 7a , 7b and 7c ).
  • This configuration allows a maximum mechanical rotation of the hook 51 that is calculated so that it is limited in such a way that an extra rotation from the operation personnel would not damage the engaging means 50.
  • the maximum mechanical rotation of the hook 51 is of about 30°.
  • the value of the elastic constant K of the spring 55 and the hook 51 inertia are selected such that the resonance frequency has a different value than the oscillation frequency of the engine, therefore avoiding coupling in frequencies with the engine.
  • the value of the elastic constant K of the spring 55 and the value of the hook 51 inertia are selected such that they avoid resonance frequencies under about 60 Hz.
  • the receiving means 60 located in the fan cowl doors, 10 or 20, comprise a catching element 61, preferably an axis or mounting bolt, over which the hook 51 engages, this catching element 61 being fixed to a bracket 63 by bushings 62 (see Figures 8a and 8b ).
  • the cut-out of the fan cowl door 10 or 20 over which the panel 41 is engaged by means of the security locking device100 has to be increased circumferentially in order to accommodate both the primary locking device 101 and the security locking means 102 (see Figures 11 and 12 ), the surrounding parts in the fan cowl being modified accordingly, and the attaching points for the lightning protection being also consequently relocated.
  • the panel 41 comprises a new cut-out 205 for accommodating the security locking means 102.
  • a new strip 200 is preferably provided, apart from the strip parts 201 and 202 in the known prior art being redesigned consequently, in such a way that the thickness of the panel 41 is locally increased, around the area where the security locking device 100 is located, avoiding possible gaps between the panel 41 and the fan cowl doors 10, 20, therefore avoiding that air enters through these gaps, tearing off the panel 41.
  • the security locking device 100 in the indication device 40 according to the invention is located next to the primary locking device 101 on the side of the panel 41 facing incoming airflow 90 during flight of the aircraft.
  • This security locking device 100 operates when the primary locking device 101 is not working properly (that is, when the primary locking device 101 is not properly latched), so that the security locking device 100 has to ensure that the airflow 90 which enters the region between the fan cowl doors 10, 20 and the panel 41 of the indication device 40 is minimized. This is achieved by ensuring that there is no space between the panel 41 in its closed position and the fan cowl doors 10, 20 on the side facing the incoming airflow 90.
  • Figure 14a represents an indication device 40 with a panel 41 according to the known prior art, the panel 41 being closed by a primary locking device 101: this Figure shows the primary locking device 101 in its nominal closed position over the fan cowl doors 10, 20. There is no space, as it can be seen in this Figure, between the panel 41 and the fan cowl doors 10, 20 on the side facing the airflow 90.
  • the security locking device 100 of the invention is therefore designed so that it only supports the load of the panel 41 when the primary locking device 101 is not properly latching the panel 41, so the panel 41 is either supported by the primary locking device 101 or by the security locking means 102.
  • the security locking means 102 are a security measure, they are located in such a way that the hook 51 and the catching element 61 only enter into contact when the panel 41 falls from its nominal position (where it is latched to the fan cowl doors 10, 20 by the primary locking device 101) to the position where it is supported by the secondary locking means 102.
  • the security locking means 102 are preferably located, together with the primary locking device 101, close to the edge of the indication device 40 (panel 41) facing the airflow 90. The reason is that the incorrect closure of the primary locking device 101 is what causes the existence of a gap between the panel 41 and the fan cowl doors 10, 20 through which air from the airflow 90 makes the panel 41 and the indication device 40 lift up and get lost in flight.

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Lock And Its Accessories (AREA)

Claims (9)

  1. Nacelle d'unité de propulsion d'aéronef, qui comprend :
    - des portes de capot de soufflante (10, 20),
    - un moyen de verrouillage de capot de soufflante (30) destiné à fixer et à verrouiller les portes du capot de soufflante (10, 20),
    - un dispositif d'indication destiné à fournir un signal d'alarme lorsque les portes de capot de soufflante (10, 20) ne sont pas correctement verrouillées, qui comprend :
    - un panneau (41) fixé sur l'une des portes de capot de soufflante (10, 20),
    - un dispositif de verrouillage primaire (101) destiné à fixer le panneau (41) sur les portes de capot de soufflante (10, 20),
    - un moyen de rotation (42) situé dans l'une des portes de capot de soufflante (10, 20) afin de faire tourner le panneau (41) de sorte que, en tournant, le panneau (41) se verouille sur les portes de capot de soufflante (10, 20) en recouvrant partiellement le moyen de verrouillage du capot de soufflante (30),
    caractérisée par
    - un dispositif de verrouillage de sécurité (100) qui comprend un moyen de verrouillage de sécurité (102) qui assure un verrouillage alternatif du dispositif d'indication (40) sur les portes du capot de soufflante (10, 20), le moyen de verrouillage de sécurité (102) comprenant un moyen d'engagement (50) et un moyen de réception (60), le moyen d'engagement (50) se trouvant dans le dispositif d'indication (40) et s'engageant avec le moyen de réception (60) qui se trouve dans les portes du capot de soufflante (10, 20),
    dans laquelle le moyen d'engagement (50) comprend un crochet rotatif (51) et un ressort (55), qui se trouvent sur un support installé dans le panneau,
    le moyen de verrouillage de sécurité (102) étant configuré de sorte qu'il soit verrouillé uniquement en fermant le dispositif d'indication (40) sur les portes du capot de soufflante (10, 20), sans avoir besoin d'une opération supplémentaire.
  2. Nacelle d'unité de propulsion d'aéronef selon la revendication 1, dans laquelle le dispositif de verrouillage de sécurité (100) se trouve près du dispositif de verrouillage primaire (101) sur le côté du panneau (41), face au flux d'air entrant (90) pendant le vol de l'aéronef.
  3. Nacelle d'unité de propulsion d'aéronef selon la revendication 1, dans laquelle la valeur de la constante élastique (K) du ressort (55) et la valeur d'inertie du crochet (51) autour de son axe de rotation sont choisies de sorte qu'elles évitent les fréquences de résonance du moteur de l'aéronef.
  4. Nacelle d'unité de propulsion d'aéronef selon la revendication 3, dans laquelle la valeur de la constante élastique (K) du ressort (55) et la valeur d'inertie du crochet (51) autour de son axe de rotation sont choisies de sorte qu'elles évitent les fréquences de résonance inférieures à 60 Hz.
  5. Nacelle d'unité de propulsion d'aéronef selon l'une quelconque des revendications 3 et 4, dans laquelle la rotation mécanique maximale du crochet (51) est calculée de sorte qu'elle soit limitée afin que toute rotation supplémentaire par le personnel d'exploitation n'endommage pas le moyen d'engagement (50).
  6. Nacelle d'unité de propulsion d'aéronef selon la revendication 5, dans laquelle la rotation maximale du crochet (51) est de 30°.
  7. Nacelle d'unité de propulsion d'aéronef selon l'une quelconque des revendications précédentes, dans laquelle le dispositif d'indication (40) comprend un panneau (41) qui possède une épaisseur locale plus importante, autour de la zone dans laquelle se trouve le dispositif de verrouillage de sécurité (100).
  8. Nacelle d'unité de propulsion d'aéronef selon l'une quelconque des revendications précédentes, dans laquelle le moyen de réception (60) comprend un élément de saisie (61), sur lequel s'engage le crochet (51), l'élément de saisie (61) étant un axe ou un boulon de montage.
  9. Aéronef qui comprend une nacelle de propulsion selon l'une quelconque des revendications 1 à 8.
EP11382332.2A 2011-10-27 2011-10-27 Dispositif de verrouillage de sécurité pour le capuchon d'une gondole de moteur d'avion Active EP2586707B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11382332.2A EP2586707B1 (fr) 2011-10-27 2011-10-27 Dispositif de verrouillage de sécurité pour le capuchon d'une gondole de moteur d'avion
ES11382332.2T ES2569127T3 (es) 2011-10-27 2011-10-27 Cierre de seguridad para la capota de la góndola de una unidad de potencia de una aeronave

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11382332.2A EP2586707B1 (fr) 2011-10-27 2011-10-27 Dispositif de verrouillage de sécurité pour le capuchon d'une gondole de moteur d'avion

Publications (2)

Publication Number Publication Date
EP2586707A1 EP2586707A1 (fr) 2013-05-01
EP2586707B1 true EP2586707B1 (fr) 2016-01-20

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ID=45063073

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11382332.2A Active EP2586707B1 (fr) 2011-10-27 2011-10-27 Dispositif de verrouillage de sécurité pour le capuchon d'une gondole de moteur d'avion

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EP (1) EP2586707B1 (fr)
ES (1) ES2569127T3 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11060331B2 (en) 2013-07-24 2021-07-13 Mra Systems, Llc Engine door and latch assembly
WO2017058860A1 (fr) * 2015-09-30 2017-04-06 Alcoa Inc. Porte de détente de pression

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4531769A (en) 1982-08-25 1985-07-30 The Boeing Company Hook latch for an engine cowling
US5620212A (en) 1995-08-28 1997-04-15 Hartwell Corporation Low profile hook latch assembly
US6279971B1 (en) * 1999-10-05 2001-08-28 Hartwell Corporation Latch with sensor
US6755448B2 (en) * 2001-06-20 2004-06-29 Hartwell Corporation Blowout latch
FR2832752B1 (fr) * 2001-11-27 2004-08-06 Airbus France Dispositif indicateur de defaut de fermeture d'au moins un mecanisme de verrouillage interpose entre deux elements
FR2916425B1 (fr) * 2007-05-25 2009-07-03 Aircelle Sa Dispositif de verrouillage d'une partie ouvrante de nacelle de turboreacteur par rapport a une partie fixe,et nacelle equipee d'un tel dispositif
FR2955347B1 (fr) * 2010-01-21 2012-01-27 Eurocopter France Dispositif de verrouillage d'un element contre une structure adjacente, aeronef muni dudit dispositif et procede d'extraction mis en oeuvre par ledit dispositif

Also Published As

Publication number Publication date
ES2569127T3 (es) 2016-05-06
EP2586707A1 (fr) 2013-05-01

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