EP2586707B1 - Sicherheitsverriegelung für die Klappe einer Flugzeugtriebwerksgondel - Google Patents

Sicherheitsverriegelung für die Klappe einer Flugzeugtriebwerksgondel 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
English (en)
French (fr)
Other versions
EP2586707A1 (de
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 ES11382332.2T priority Critical patent/ES2569127T3/es
Priority to EP11382332.2A priority patent/EP2586707B1/de
Publication of EP2586707A1 publication Critical patent/EP2586707A1/de
Application granted granted Critical
Publication of EP2586707B1 publication Critical patent/EP2586707B1/de
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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. Flugzeugtriebwerksgondel, umfassend:
    - Lüfterabdeckhaubenklappen (10, 20),
    - Lüfterabdeckungsverriegelungsmittel (30) zum Fixieren und Verriegeln der Lüfterabdeckhaubenklappen (10, 20),
    - eine Anzeigeeinrichtung zur Bereitstellung eines Warnsignals, wenn die Lüfterabdeckhaubenklappen (10, 20) nicht richtig verriegelt sind, umfassend:
    - eine Platte (41), die an einer der Lüfterabdeckhaubenklappen (10, 20) befestigt ist,
    - eine primäre Verriegelungsvorrichtung (101) zum Fixieren der Platte (41) an den Lüfterabdeckhaubenklappen (10, 20),
    - Rotationsmittel (42), die in einer der Lüfterabdeckhaubenklappen (10, 20) angeordnet sind, um die Platte (41) derart in Drehung zu versetzen, dass diese durch das Drehen der Platte (41) unter wenigstens teilweiser Bedeckung der Lüfterabdeckungsverriegelungsmittel (30) über den Lüfterabdeckhaubenklappen (10, 20) verriegelt wird,
    gekennzeichnet durch
    - eine Sicherheitsverriegelungsvorrichtung (100), umfassend Sicherheitsverriegelungsmittel (102), die einen alternativen Sicherheitsverschluss der Anzeigeeinrichtung (40) über den Lüfterabdeckhaubenklappen (10, 20) bereitstellen, wobei die Sicherheitsverriegelungsmittel (102) Eingriffsmittel (50) und Aufnahmemittel (60) umfassen, wobei die Eingriffsmittel (50) in der Anzeigeeinrichtung (40) angeordnet sind und in die Aufnahmemittel (60) eingreifen, die in den Lüfterabdeckhaubenklappen (10, 20) angeordnet sind,
    wobei die Eingriffsmittel (50) einen Drehhaken (51) und eine Feder (55) umfassen, die beide auf einem in der Platte montierten Träger angeordnet sind, wobei die Sicherheitsverriegelungsmittel (102) so ausgestaltet sind, dass sie nur durch das Schließen der Anzeigevorrichtung (40) über den Lüfterabdeckhaubenklappen (10, 20) - ohne die Notwendigkeit irgend einer weiteren Bedienung - verriegelt werden.
  2. Flugzeugtriebwerksgondel nach Anspruch 1, wobei die Sicherheitsverriegelungsvorrichtung (100) neben der primären Verriegelungsvorrichtung (101) an der Seite der Platte (41) angeordnet ist, die während des Fluges des Flugzeugs dem eintretenden Luftstrom (90) zugewandt ist.
  3. Flugzeugtriebwerksgondel nach Anspruch 1, wobei der Wert der elastischen Konstanten (K) der Feder (55) und der Trägheitswert des Hakens (51) um seine Drehachse so gewählt sind, dass sie die Resonanzfrequenzen des Flugzeugtriebwerks vermeiden.
  4. Flugzeugtriebwerksgondel nach Anspruch 3, wobei der Wert der elastischen Konstanten (K) der Feder (55) und der Trägheitswert des Hakens (51) um seine Drehachse so gewählt sind, dass sie Resonanzfrequenzen unterhalb von 60 Hz vermeiden.
  5. Flugzeugtriebwerksgondel nach Anspruch 3 oder 4, wobei die größtmögliche mechanische Drehbewegung des Hakens (51) so berechnet wird, dass sie derart begrenzt ist, dass eine zusätzliche Drehung durch das Bedienungspersonal die Eingriffsmittel (50) nicht beschädigen würde.
  6. Flugzeugtriebwerksgondel nach Anspruch 5, wobei die größtmögliche Drehbewegung des Hakens (51) 30° ist.
  7. Flugzeugtriebwerksgondel nach einem der vorhergehenden Ansprüche, wobei die Anzeigeeinrichtung (40) eine Platte (41) umfasst, die lokal, um den Bereich, wo sich die Sicherheitsverriegelungsvorrichtung (100) befindet, eine erhöhte Dicke aufweist.
  8. Flugzeugtriebwerksgondel nach einem der vorhergehenden Ansprüche, wobei die Aufnahmemittel (60) ein Fangelement (61) umfassen, über das der Haken (51) eingreift, wobei das Fangelement (61) eine Achse oder eine Befestigungsschraube ist.
  9. Flugzeug, eine Flugzeugtriebwerksgondel nach einem der Ansprüche 1 bis 8 umfassend.
EP11382332.2A 2011-10-27 2011-10-27 Sicherheitsverriegelung für die Klappe einer Flugzeugtriebwerksgondel Active EP2586707B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
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
EP11382332.2A EP2586707B1 (de) 2011-10-27 2011-10-27 Sicherheitsverriegelung für die Klappe einer Flugzeugtriebwerksgondel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11382332.2A EP2586707B1 (de) 2011-10-27 2011-10-27 Sicherheitsverriegelung für die Klappe einer Flugzeugtriebwerksgondel

Publications (2)

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

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Application Number Title Priority Date Filing Date
EP11382332.2A Active EP2586707B1 (de) 2011-10-27 2011-10-27 Sicherheitsverriegelung für die Klappe einer Flugzeugtriebwerksgondel

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EP (1) EP2586707B1 (de)
ES (1) ES2569127T3 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015010271A1 (en) * 2013-07-24 2015-01-29 Mra Systems, Inc. Engine door and latch assembly
EP3356628B1 (de) * 2015-09-30 2022-01-19 Howmet Aerospace Inc. Druckentlastungsklappe

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

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ES2569127T3 (es) 2016-05-06
EP2586707A1 (de) 2013-05-01

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