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EP2238653A1 - Device for fastening an aircraft cabin module - Google Patents
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EP2238653A1 - Device for fastening an aircraft cabin module - Google Patents

Device for fastening an aircraft cabin module

Info

Publication number
EP2238653A1
EP2238653A1 EP09705325.0A EP09705325A EP2238653A1 EP 2238653 A1 EP2238653 A1 EP 2238653A1 EP 09705325 A EP09705325 A EP 09705325A EP 2238653 A1 EP2238653 A1 EP 2238653A1
Authority
EP
European Patent Office
Prior art keywords
aircraft cabin
cabin module
contacts
data
plug
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.)
Granted
Application number
EP09705325.0A
Other languages
German (de)
French (fr)
Other versions
EP2238653B1 (en
Inventor
Christian Riedel
Michael Weidel
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 Operations GmbH
Original Assignee
Airbus Operations GmbH
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 Operations GmbH filed Critical Airbus Operations GmbH
Publication of EP2238653A1 publication Critical patent/EP2238653A1/en
Application granted granted Critical
Publication of EP2238653B1 publication Critical patent/EP2238653B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/627—Snap or like fastening
    • H01R13/6275—Latching arms not integral with the housing
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R25/00—Coupling parts adapted for simultaneous co-operation with two or more identical counterparts, e.g. for distributing energy to two or more circuits
    • H01R25/14—Rails or bus-bars constructed so that the counterparts can be connected thereto at any point along their length

Definitions

  • the invention relates to a device for fastening an aircraft cabin module, which additionally provides the power supply for the aircraft cabin module and allows data exchange between the aircraft cabin module and an aircraft cabin server.
  • DE 10 2006 012 730 B3 describes a fastening system for fastening a cabin equipment element to a support structure of an aircraft.
  • a device is provided for fastening an aircraft cabin module, wherein the device has a component with legs for the releasable locking of a plug attached to the aircraft cabin module and a plurality of electrical contacts.
  • the electrical connection structure comprises two half-shells, each half-shell including at least two openings leading from an inner cavity of the half-shell to an outer periphery of the half-shell.
  • Each half-shell includes a recessed channel along an inner surface, with a retaining clip attached to the half-shell that includes at least two pre-bent lugs that pass through the at least two apertures. In this case, the retaining clip is pressed over a snap connection to abut against the inner surface of the half-shell.
  • a major surface of the retaining clip rests on the surface of the recessed channel, and prior to connection, the retaining clip in each half shell thereof is supported by a minimum of three contact points is attached, wherein at least two of the contact points are Schnapprivsanbringonne.
  • aircraft cabin modules In the cabin of an aircraft, in particular a passenger plane, a plurality of aircraft cabin modules are mounted.
  • aircraft cabin modules include, for example, passenger supply units PSU (Passenger Supply Unit), emergency oxygen supply units for decentralized oxygen supply of the passengers in emergency, cabin lighting units, air nozzle units, passenger audio units, for example loudspeakers, or passenger video units, for example display monitors.
  • PSU Passenger Supply Unit
  • emergency oxygen supply units for decentralized oxygen supply of the passengers in emergency
  • cabin lighting units for example, air nozzle units
  • passenger audio units for example loudspeakers
  • passenger video units for example display monitors.
  • Some of these aircraft cabin modules must be supplied with a DC supply voltage of, for example, 28 volts DC, while others, for example the emergency oxygen supply units, must be supplied with an AC voltage of, for example, 115 volts AC.
  • the aircraft cabin modules are supplied with electrical power via power supply lines which are laid separately from data lines which serve to exchange data between the aircraft cabin modules and a central computer.
  • the attachment of the aircraft cabin modules takes place via mechanical brackets, which are mounted in a profile component, which is provided in a cabin supply channel.
  • the invention provides a device for fastening at least one aircraft cabin module with the features of patent claim 1.
  • the electrical contacts are formed by contact grooves in which contact pins of the plug attached to the aircraft cabin module can be displaced in a longitudinal direction of the rail component prior to the locking of the plug.
  • the rail component consists of a stable, lightweight and electrically insulating material, for example made of aluminum, CFRP and / or
  • the electrical contacts with a protective cap to protect against corrosion can be covered.
  • the protective cap consists for example of a rubber lip.
  • these protective contacts also provide protection against inadvertent contact with the electrically conductive contacts by a fitter or a passenger.
  • the electrically conductive contacts comprise contact groups, for example a group of DC contacts for applying a DC voltage, a group of AC contacts for applying an AC voltage and a group of data contacts for exchanging data between the aircraft cabin modules and an aircraft cabin server.
  • the data contacts preferably each have a predetermined characteristic impedance of, for example, 100 ohms / meter.
  • spring-mounted locking projections are attached to the plugs, which engage in Arretleitersauslangache.
  • this acceleration force is a multiple of the gravitational acceleration force, for example 16 G.
  • FIG. 1 shows an embodiment of a fastening device according to the invention
  • FIG. 2 shows the attachment of a passenger supply unit PSU to the exemplary embodiment of the fastening device according to the invention shown in FIG. 1;
  • FIG. 3 shows the attachment of an emergency oxygen supply unit to the embodiment of the fastening device according to the invention shown in FIG.
  • the fastening device 1 has a U-shaped rail component 2, which preferably consists of a light, stable and insulating material.
  • the U-shaped rail component 2 has two opposite legs 2A, 2B, which are connected via a centrally located middle section 2C.
  • the two opposite legs 2A, 2B are preferably formed on the central portion 2C.
  • the rail component 2 forms a rail profile whose legs form, for example, an angle of about 90 ° to the central portion 2C.
  • the light, stable, insulating material from which the rail component 2 is made is, for example, aluminum, CFRP or Teflon.
  • the rail component 2 consists for example of a shielding
  • each locking points 3A, 3B are provided on the inner sides of the two opposite legs 2A, 2B.
  • the locking points 3A, 3B are preferably opposite each other.
  • the locking points 3A, 3B become, for example
  • the middle section 2C connecting the two legs 2A, 2B has several electrical contacts 4-1 to 4-11, which are provided on the one hand for supplying power to an aircraft cabin module and, on the other hand, allow data to be exchanged between data from an aircraft cabin module to a cabin server.
  • the electrical contacts 4-1, 4-2 are provided for applying a DC supply voltage, for example a DC supply voltage of 28 V DC for a normal voltage supply of the aircraft cabin module attached to the fastening device 1.
  • a DC supply voltage for example a DC supply voltage of 28 V DC for a normal voltage supply of the aircraft cabin module attached to the fastening device 1.
  • the contacts 4-3, 4-4 are provided for an emergency supply DC voltage, for example in the amount of 28 volts DC, in the example illustrated in FIG. 1, the electrical contacts 4-5 to 4-8 also form data contacts Serve exchange of data between the fixed aircraft cabin module and an aircraft cabin server.
  • these data contacts each have a given characteristic impedance of, for example, 100 ohms / meter.
  • the electrical contacts 4-9 to 4-11 serve to apply an alternating supply voltage of, for example, 115
  • the fastening device 1 shown in FIG. 1 can be laid in a supply channel of an aircraft cabin.
  • the electrical contacts 4-i are each provided with an associated protective cap for protection
  • This protective cap consists for example of a rubber lip.
  • the protective cap also protects against inadvertent touching of the contacts by a fitter or by a passenger.
  • the electrical contacts 4-1 to 4-11 are designed as contact grooves. In these contact grooves, contact pins of a plug attached to the aircraft cabin module can be displaced in the longitudinal direction of the rail component before the plug is locked. As a result, a great flexibility in the assembly of the aircraft cabin modules within the passenger cabin is achieved. In addition, the installation of the aircraft cabin module for the fitter is significantly facilitated.
  • the electrical contacts 4-1 to 4-11 shown in FIG. 1 not only serve to make electrical contact, but additionally perform a holding function. This ensures that the aircraft cabin modules are securely attached to the fastening device 1 even with vibrations. In addition, it is easier for the fitter to move the aircraft cabin modules in front of the final locking in the longitudinal direction, without having to exert a holding force.
  • FIG. 2 shows the mounting of a passenger supply unit 5 on the fastening device 1, as shown in FIG. 1.
  • the passenger supply unit 5 has a plug 7 attached via a joint 6, the contact pins 8-1 to 8-8
  • the distance between the contact pins 8-i corresponds to the distance of the electrical contact 4-i within the rail component 2. Moreover, the height of the protruding contact pins 8-i substantially corresponds to the tie
  • the electrical contact 4-i within the rail component 2. Since the passenger control unit 5 no Senpanel Required power supply, the plug 7 of the passenger supply unit 5 no contact pins for the Kirspan- nung ⁇ mentss giftede 4-9, 4-10, 4-11.
  • the electrical contacts 4-i and the contact pins 8 ⁇ i are each gold-plated.
  • the plug 7 has two opposing spring-loaded Arret michsvorsprünge 9 A, 9 B, which can engage in the Arret réellesausEnglishungen 3 A, 3 B of the rail component 2 at locking points.
  • the locking projections 9A, 9B are retractable in a housing of the plug 7 against the spring force of a respectively associated spring, wherein the spring force of the attached spring according to the installation specifications is adjustable.
  • the spring force of the springs is so high that the locking is triggered only at a very high acceleration force, which is a multiple of the gravitational force.
  • the locking is released only at an acceleration of more than sixteen times the gravitational force G.
  • the aircraft cabin module 5 can be attached to the fastening device 1 in a very simple manner. Before the locking, ie the engagement of the locking projections 9A, 9B in corresponding locking recesses 3A 7 3B, the aircraft cabin module 5 to be mounted can be displaced in the longitudinal direction of the rail component 2 by the installer, for example, to carry out a fine adjustment.
  • the DC power supply contacts 4-1, 4-2 are connected to a DC power source for normal operation.
  • the data contacts 4-5, 4-6, 4-7, 4-8 are connected to a server for data exchange with the respective flight cabin modules connected.
  • the electrical contacts 4-9, 4-10, 4-11 are connected to an AC voltage source which provides, for example, an AC voltage with an amplitude of 115 volts.
  • FIG. 3 shows the attachment of an emergency oxygen supply unit 10 to the fastening device 1.
  • the emergency oxygen supply unit 10 has a plug 7 which is connected to the emergency oxygen supply unit 10 via a joint 6.
  • the emergency oxygen supply unit 10 serves for decentralized oxygen supply to the passengers in an emergency, with oxygen masks falling from the emergency oxygen supply unit 10.
  • an AC voltage of, for example, 115 volts AC is needed. Therefore, the electrical connector 7, as shown in Fig. 3, two contact pins 8-9, 8-11, which engage in corresponding electrical contacts 4-9, 4-11 of the rail component 2.
  • the device 1 serves not only for fastening the aircraft cabin modules, but also for their electrical energy supply and the data exchange between the aircraft cabin modules and a central processing unit, for example a server.
  • the fastening device 1 is suitable for any aircraft cabin modules, for example for passenger supply units, emergency oxygen supply units, cabin lighting units, passenger audio units, passenger video units or air nozzle units.

Landscapes

  • Connector Housings Or Holding Contact Members (AREA)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)

Abstract

The invention relates to a device for fastening an aircraft cabin module, comprising a component with limbs for releasably immobilizing a plug attached to an aircraft cabin module, and a plurality of electrical contacts. The component is designed as a U-shaped rail component (2), the limbs (2A, 2B) having immobilization points (3A, 3B) for releasably immobilizing the plug (7) attached to the aircraft cabin module (5, 10) and the center portion (2) connecting the two limbs (2A, 2B) comprising the electrical contacts (4-i) for the voltage supply and for the exchange of data with the aircraft cabin module (5, 10).

Description

Vorrichtung zur Befestigung eines Flugzeugkabinenmoduls Device for fastening an aircraft cabin module
Die Erfindung betrifft eine Vorrichtung zur Befestigung eines Flugzeugkabinenmoduls, welches zusätzlich die Spannungsversorgung für das Flugzeugkabinenmodul bereitstellt und einen Datenaustausch zwischen dem Flugzeugkabinenmodul und einem Flugzeugkabinenserver erlaubt.The invention relates to a device for fastening an aircraft cabin module, which additionally provides the power supply for the aircraft cabin module and allows data exchange between the aircraft cabin module and an aircraft cabin server.
Die DE 10 2006 012 730 B3 beschreibt ein BefestigungsSystem zum Befestigen eines Kabinenausstattungselements an einer Trägerstruktur eines Flugzeuges. Es ist eine Vorrichtung zur Befestigung eines Flugzeugkabinenmoduls vorgesehen, wobei die Vorrichtung ein Bauelement mit Schenkeln zur lösbaren Arretierung eines an dem Flugzeugkabinenmodul angebrachten Steckers und mehrere elektrische Kontakte aufweist.DE 10 2006 012 730 B3 describes a fastening system for fastening a cabin equipment element to a support structure of an aircraft. A device is provided for fastening an aircraft cabin module, wherein the device has a component with legs for the releasable locking of a plug attached to the aircraft cabin module and a plurality of electrical contacts.
Die DE 699 36 580 T2 beschreibt einen elektrischen Verbinder mit zweiteiligem Gehäuse und Klemme. Der elektrische Verbindungsaufbau umfasst zwei Halbschalen, wobei jede Halbschale wenigstens zwei Öffnungen einschließt, die von einem Innen- räum der Halbschale zu einer äußeren Umgebung der Halbschale führen. Jede Halbschale schließt einen ausgesparten Kanal entlang einer inneren Oberfläche ein, wobei an der Halbschale ein Halteklip angebracht ist, der wenigstens zwei vorgebogene Ansätze einschließt, die durch die mindestens zwei Öffnungen gehen. Dabei ist der Halteklip über eine Schnappverbindung eingepresst, um an der inneren Oberfläche der Halbschale anzuliegen. Eine Hauptoberfläche des Halteklips ruht auf der Oberfläche des ausgesparten Kanals, wobei vor der Verbindung der Halteklip in jeder Halbschale daran durch ein Minimum von drei Kontaktpunkten angebracht ist, wobei wenigstens zwei der Kontaktpunkte Schnappverbindungsanbringungen sind.DE 699 36 580 T2 describes an electrical connector with two-part housing and clamp. The electrical connection structure comprises two half-shells, each half-shell including at least two openings leading from an inner cavity of the half-shell to an outer periphery of the half-shell. Each half-shell includes a recessed channel along an inner surface, with a retaining clip attached to the half-shell that includes at least two pre-bent lugs that pass through the at least two apertures. In this case, the retaining clip is pressed over a snap connection to abut against the inner surface of the half-shell. A major surface of the retaining clip rests on the surface of the recessed channel, and prior to connection, the retaining clip in each half shell thereof is supported by a minimum of three contact points is attached, wherein at least two of the contact points are Schnappverbindungsanbringungen.
In der Kabine eines Flugzeuges, insbesondere eines Passagier- flugzeuges, sind eine Vielzahl von Flugzeugkabinenmodulen montiert. Diese Flugzeugkabinenmodule umfassen beispielsweise Passagierversorgungseinheiten PSU (Passenger Supply Unit) , Notsauerstoffversorgungseinheiten zur dezentralen Sauerstoffversorgung der Passagiere im Notfall, Kabinenbeleuchtungsein- heiten, Luftdüseneinheiten, Passagieraudioeinheiten, beispielsweise Lautsprecher, oder Passagiervideoeinheiten, beispielsweise Anzeigemonitore. Einige dieser Flugzeugkabinenmodule müssen mit einer Versorgungsgleichspannung von beispielsweise 28 Volt DC versorgt werden, während andere, bei- spielsweise die Notsauerstoffversorgungseinheiten, mit einer WechselSpannung von beispielsweise 115- Volt AC versorgt werden müssen.In the cabin of an aircraft, in particular a passenger plane, a plurality of aircraft cabin modules are mounted. These aircraft cabin modules include, for example, passenger supply units PSU (Passenger Supply Unit), emergency oxygen supply units for decentralized oxygen supply of the passengers in emergency, cabin lighting units, air nozzle units, passenger audio units, for example loudspeakers, or passenger video units, for example display monitors. Some of these aircraft cabin modules must be supplied with a DC supply voltage of, for example, 28 volts DC, while others, for example the emergency oxygen supply units, must be supplied with an AC voltage of, for example, 115 volts AC.
Bei herkömmlichen Flugzeugen werden die Flugzeugkabinenmodule über Spannungsversorgungsleitungen mit elektrischer Energie versorgt, die von Datenleitungen, welche zum Austausch von Daten zwischen den Flugzeugkabinenmodulen und einem zentralen Rechner dienen, getrennt verlegt werden.In conventional aircraft, the aircraft cabin modules are supplied with electrical power via power supply lines which are laid separately from data lines which serve to exchange data between the aircraft cabin modules and a central computer.
Die Befestigung der Flugzeugkabinenmodule erfolgt dabei über mechanische Halterungen, die in einem Profilbauelement angebracht sind, das in einem Kabinenversorgungskanal vorgesehen ist.The attachment of the aircraft cabin modules takes place via mechanical brackets, which are mounted in a profile component, which is provided in a cabin supply channel.
Aufgrund der getrennten Verkabelung von Datenleitungen und Spannungsversorgungsleitungen ist der Aufwand bei der Montage der Flugzeugkabinenmodule innerhalb des Passagierraumes eines Flugzeuges hoch.Due to the separate wiring of data lines and power supply lines, the cost of assembling the aircraft cabin modules within the passenger compartment of an aircraft is high.
Es ist daher eine Aufgabe der vorliegenden Erfindung, eine Vorrichtung zur Befestigung von Flugzeugkabinenmodulen zu schaffen, bei der der Montageaufwand minimiert wird und die robust gegenüber Erschütterungen und Beschleunigungskräften ist .It is therefore an object of the present invention to provide a device for fastening aircraft cabin modules, in which the assembly effort is minimized and the robust against shocks and acceleration forces.
Die Erfindung schafft eine Vorrichtung zur Befestigung min- destens eines Flugzeugkabinenmoduls mit den Merkmalen des Patentanspruchs 1.The invention provides a device for fastening at least one aircraft cabin module with the features of patent claim 1.
Bei einer Ausführungsform der Vorrichtung werden die elektrischen Kontakte durch Kontaktnuten gebildet, in denen Kontakt- stifte des an dem Flugzeugkabinenmodul angebrachten Steckers in einer Längsrichtung des Schienenbauelements vor der Arretierung des Steckers verschiebbar sind.In one embodiment of the device, the electrical contacts are formed by contact grooves in which contact pins of the plug attached to the aircraft cabin module can be displaced in a longitudinal direction of the rail component prior to the locking of the plug.
Hierdurch wird eine hohe Flexibilität bei der Montage der Flugzeugkabinenmodule erreicht, da ein Monteur vor der Arretierung des Flugzeugkabinenmoduls dieses in Längsrichtung in eine gewünschte Position verschieben kann. Dies ist umso hilfreicher, da die örtliche Verteilung bzw. Positionierung der Flugzeugkabinenmodule in einem Flugzeug entsprechend den Kundenwünschen stark variieren kann. Weiterhin wird es hierdurch einfacher, Plätze für mögliche spätere Einbauten freizuhalten, wenn die Flugzeugkabine beispielsweise ein anderes Bestuhlungs- bzw. Klassen-Layout erhält.As a result, a high degree of flexibility in the assembly of the aircraft cabin modules is achieved, since a fitter can move this in the longitudinal direction to a desired position before locking the aircraft cabin module. This is all the more helpful since the local distribution or positioning of the aircraft cabin modules in an aircraft can vary widely according to the customer's wishes. Furthermore, this makes it easier to keep free places for possible future installations, if the aircraft cabin, for example, receives a different seating or class layout.
Bei einer möglichen Ausführungsform besteht das Schienenbauelement aus einem stabilen, leichten und elektrisch isolierenden Material, beispielsweise aus Aluminium, CFK und/oderIn one possible embodiment, the rail component consists of a stable, lightweight and electrically insulating material, for example made of aluminum, CFRP and / or
Teflon. In dieses elektrisch isolierende Material werden die elektrisch leitenden Kontakte eingefügt.Teflon. In this electrically insulating material, the electrically conductive contacts are inserted.
Bei einer Ausführungsform der erfindungsgemäßen Befestigungsvorrichtung sind die elektrischen Kontakte mit einer Schutzkappe zum Schutz gegen Korrosion abdeckbar. Die Schutzkappe besteht dabei beispielsweise aus einer Gummilippe. Neben dem Schutz vor Korrosion bieten diese Schutzkontakte zudem einen Schutz gegen ein unbeabsichtigtes Berühren der elektrisch leitenden Kontakte durch einen Monteur bzw. einen Passagier.In one embodiment of the fastening device according to the invention, the electrical contacts with a protective cap to protect against corrosion can be covered. The protective cap consists for example of a rubber lip. Next to the Protection against corrosion, these protective contacts also provide protection against inadvertent contact with the electrically conductive contacts by a fitter or a passenger.
Die elektrisch leitenden Kontakte weisen bei einer Ausführungsform Kontaktgruppen auf, beispielsweise eine Gruppe von Gleichspannungskontakten zum Anlegen einer Gleichspannung, eine Gruppe von Wechselspannungskontakten zum Anlegen einer WechselSpannung und eine Gruppe von Datenkontakten zum Aus- tausch von Daten zwischen den Flugzeugkabinenmodulen und einem Flugzeugkabinenserver.In one embodiment, the electrically conductive contacts comprise contact groups, for example a group of DC contacts for applying a DC voltage, a group of AC contacts for applying an AC voltage and a group of data contacts for exchanging data between the aircraft cabin modules and an aircraft cabin server.
Dabei weisen die Datenkontakte vorzugsweise jeweils einen vorgegebenen Wellenwiderstand von beispielsweise 100 Ohm / Meter auf.In this case, the data contacts preferably each have a predetermined characteristic impedance of, for example, 100 ohms / meter.
In einer möglichen Ausführungsform der Befestigungsvorrichtung sind an den Steckern gefederte Arretierungsvorsprünge angebracht, die in Arretierungsausnehmungen einrasten.In a possible embodiment of the fastening device spring-mounted locking projections are attached to the plugs, which engage in Arretierungsausnehmungen.
In Abhängigkeit von der Federstärke der an den Arretierungsvorsprüngen angebrachten Feder ist es möglich, die Beschleunigungskräfte abzufangen, bei welcher sich erst Arretierungen im Flugbetrieb lösen können. In einer möglichen Ausführungs- form der erfindungsgemäßen Befestigungsvorrichtung beträgt diese Beschleunigungskraft ein Vielfaches der Erdbeschleunigungskraft, beispielsweise 16 G.Depending on the spring strength of the attached to the locking projections spring, it is possible to absorb the acceleration forces at which only locks can solve in flight. In one possible embodiment of the fastening device according to the invention, this acceleration force is a multiple of the gravitational acceleration force, for example 16 G.
Im Weiteren werden bevorzugte Ausführungsformen der erfin- dungsgemäßen Befestigungsvorrichtung zur Befestigung eines Flugzeugkabinenmoduls unter Bezugnahme auf die beigefügten Figuren zur Erläuterung erfindungswesentlicher Merkmale beschrieben .In the following, preferred embodiments of the fastening device according to the invention for fastening an aircraft cabin module will be described with reference to the attached figures to explain features essential to the invention.
Es zeigen: Fig. 1 ein Ausführungsbeispiel für eine Befestigungsvorrichtung gemäß der Erfindung;Show it: Fig. 1 shows an embodiment of a fastening device according to the invention;
Fig. 2 das Anbringen einer Passagierversorgungseinheit PSU an dem in Fig. 1 dargestellten Ausführungsbeispiel der Befestigungsvorrichtung gemäß der Erfindung;FIG. 2 shows the attachment of a passenger supply unit PSU to the exemplary embodiment of the fastening device according to the invention shown in FIG. 1; FIG.
Fig. 3 das Anbringen einer Notsauerstoffversorgungsein- heit an der in Fig. 1 dargestellten Ausführungsbeispiel der Befestigungsvorrichtung gemäß der Erfindung.3 shows the attachment of an emergency oxygen supply unit to the embodiment of the fastening device according to the invention shown in FIG.
Wie man aus Fig. 1 erkennen kann, weist die Befestigungsvor- richtung 1 ein U-förmig ausgebildetes Schienenbauelement 2 auf, das vorzugsweise aus einem leichten, stabilen und isolierenden Material besteht. Das U-förmig ausgebildete Schienenbauelement 2 weist zwei gegenüberliegende Schenkel 2A, 2B auf, die über einen mittig gelegenen Mittelabschnitt 2C ver- bunden sind. Die beiden gegenüberliegenden Schenkel 2A, 2B sind an den Mittelabschnitt 2C vorzugsweise angeformt. Das Schienenbauelement 2 bildet ein Schienenprofil, dessen Schenkel beispielsweise einen Winkel von etwa 90° zu dem Mittelabschnitt 2C bilden. Das leichte, stabile, isolierende Materi- al, aus dem das Schienenbauelement 2 besteht, ist beispielsweise Aluminium, CFK oder Teflon. Das Schienenbauelement 2 besteht beispielsweise aus einem abschirmendenAs can be seen from FIG. 1, the fastening device 1 has a U-shaped rail component 2, which preferably consists of a light, stable and insulating material. The U-shaped rail component 2 has two opposite legs 2A, 2B, which are connected via a centrally located middle section 2C. The two opposite legs 2A, 2B are preferably formed on the central portion 2C. The rail component 2 forms a rail profile whose legs form, for example, an angle of about 90 ° to the central portion 2C. The light, stable, insulating material from which the rail component 2 is made is, for example, aluminum, CFRP or Teflon. The rail component 2 consists for example of a shielding
dünnen Aluminiumprofil. Wie man aus Fig. 1 erkennen kann, sind an den Innenseiten der beiden gegenüberliegenden Schenkel 2A, 2B jeweils Arretierungspunkte 3A, 3B vorgesehen. Die Arretierungspunkte 3A, 3B liegen vorzugsweise einander gegenüber. Die Arretierungspunkte 3A, 3B werden beispielsweisethin aluminum profile. As can be seen from Fig. 1, each locking points 3A, 3B are provided on the inner sides of the two opposite legs 2A, 2B. The locking points 3A, 3B are preferably opposite each other. The locking points 3A, 3B become, for example
durch halbkugelförmige Ausnehmungen gebildet. Der die beiden Schenkel 2A, 2B verbindende Mittelabschnitt 2C weist mehrere elektrische Kontakte 4-1 bis 4-11 auf, die einerseits zur SpannungsVersorgung eines Flugzeugkabinenmoduls vorgesehen sind und zum anderen einen Datenaustausch von Daten zwischen einem Flugzeugkabinenmodul und einem Flugkabinenserver ermög- liehen.formed by hemispherical recesses. The middle section 2C connecting the two legs 2A, 2B has several electrical contacts 4-1 to 4-11, which are provided on the one hand for supplying power to an aircraft cabin module and, on the other hand, allow data to be exchanged between data from an aircraft cabin module to a cabin server.
In dem in Fig. 1 dargestellten Beispiel sind die elektrischen Kontakte 4-1, 4-2 zum Anlegen einer Versorgungsgleichspannung vorgesehen, beispielsweise einer Versorgungsgleichspannung von 28 Volt DC für eine normale SpannungsVersorgung des an der Befestigungsvorrichtung 1 angebrachten Flugzeugkabinenmoduls .In the example shown in FIG. 1, the electrical contacts 4-1, 4-2 are provided for applying a DC supply voltage, for example a DC supply voltage of 28 V DC for a normal voltage supply of the aircraft cabin module attached to the fastening device 1.
Weiterhin sind die Kontakte 4-3, 4-4 für eine Notfallversor- gungsgleichspannung, beispielsweise in Höhe von 28 Volt DC vorgesehen, in dem in Fig. 1 dargestellt Beispiel bilden ferner die elektrischen Kontakte 4-5 bis 4-8 Datenkontakte, die zum Austausch von Daten zwischen dem befestigten Flugzeugkabinenmodul und einem Flugzeugkabinenserver dienen. Diese Da- tenkontakte weisen bei einer möglichen Ausführungsform jeweils einen vorgegebenen Wellenwiderstand von beispielsweise 100 Ohm/Meter auf.Furthermore, the contacts 4-3, 4-4 are provided for an emergency supply DC voltage, for example in the amount of 28 volts DC, in the example illustrated in FIG. 1, the electrical contacts 4-5 to 4-8 also form data contacts Serve exchange of data between the fixed aircraft cabin module and an aircraft cabin server. In one possible embodiment, these data contacts each have a given characteristic impedance of, for example, 100 ohms / meter.
Die elektrischen Kontakt 4-9 bis 4-11 dienen zum Anlegen ei- ner Versorgungswechselspannung in Höhe von beispielsweise 115The electrical contacts 4-9 to 4-11 serve to apply an alternating supply voltage of, for example, 115
Volt AC, die zur Auslösung einer NotsauerstoffVersorgung für die Flugzeugkabine benötigt wird.Voltage AC needed to trigger an emergency oxygen supply to the aircraft cabin.
Die in Fig. 1 dargestellte Befestigungsvorrichtung 1 kann in einem Versorgungskanal einer Flugzeugkabine verlegt werden. Um Einflüssen durch Feuchtigkeit vorzubeugen, werden bei einer möglichen Ausführungsform die elektrischen Kontakte 4-i jeweils mit einer zugehörigen Schutzkappe zum Schutz gegenThe fastening device 1 shown in FIG. 1 can be laid in a supply channel of an aircraft cabin. In order to prevent influences due to moisture, in one possible embodiment, the electrical contacts 4-i are each provided with an associated protective cap for protection
Korrosion abgedeckt. Diese Schutzkappe besteht beispielsweise aus einer Gummilippe. Zusätzlich schützt die Schutzkappe auch gegen ein unbeabsichtigtes Berühren der Kontakte durch einen Monteur oder durch einen Passagier.Covered by corrosion. This protective cap consists for example of a rubber lip. In addition, the protective cap also protects against inadvertent touching of the contacts by a fitter or by a passenger.
Bei einer möglichen Ausführungsform der erfindungsgemäßen Be- festigungsvorrichtung sind die elektrischen Kontakte 4-1 bis 4-11, wie sie in Fig. 1 dargestellt sind, als Kontaktnuten ausgebildet. In diesen Kontaktnuten sind Kontaktstifte eines an dem Flugzeugkabinenmodul angebrachten Steckers in Längsrichtung des Schienenbauelements vor der Arretierung des Ste- ckers verschiebbar. Hierdurch wird eine große Flexibilität bei der Montage der Flugzeugkabinenmodule innerhalb der Passagierkabine erreicht. Zudem wird die Montage des Flugzeugkabinenmoduls für den Monteur entscheidend erleichtert. Die in Fig. 1 dargestellten elektrischen Kontakte 4-1 bis 4-11 die- nen bei einer möglichen Ausführungsform nicht nur der elektrischen Kontaktierung, sondern üben zusätzlich eine Haltefunktion aus. Dadurch wird erreicht, dass die Flugzeugkabinenmodule auch bei Vibrationen sicher an der Befestigungsvorrichtung 1 angebracht sind. Zudem wird es für den Monteur leichter, die Flugzeugkabinenmodule vor der letztendlichen Arretierung in Längsrichtung zu verschieben, ohne eine Haltekraft ausüben zu müssen.In one possible embodiment of the fastening device according to the invention, the electrical contacts 4-1 to 4-11, as shown in FIG. 1, are designed as contact grooves. In these contact grooves, contact pins of a plug attached to the aircraft cabin module can be displaced in the longitudinal direction of the rail component before the plug is locked. As a result, a great flexibility in the assembly of the aircraft cabin modules within the passenger cabin is achieved. In addition, the installation of the aircraft cabin module for the fitter is significantly facilitated. In one possible embodiment, the electrical contacts 4-1 to 4-11 shown in FIG. 1 not only serve to make electrical contact, but additionally perform a holding function. This ensures that the aircraft cabin modules are securely attached to the fastening device 1 even with vibrations. In addition, it is easier for the fitter to move the aircraft cabin modules in front of the final locking in the longitudinal direction, without having to exert a holding force.
Fig. 2 zeigt die Montage einer Passagierversorgungseinheit 5 an der Befestigungsvorrichtung 1, wie sie in Fig. 1 dargestellt ist. In einer möglichen Ausführungsform weist die Passagierversorgungseinheit 5 einen über ein Gelenk 6 angebrachten Stecker 7 auf, der Kontaktstifte 8-1 bis 8-8FIG. 2 shows the mounting of a passenger supply unit 5 on the fastening device 1, as shown in FIG. 1. In one possible embodiment, the passenger supply unit 5 has a plug 7 attached via a joint 6, the contact pins 8-1 to 8-8
besitzt. Der Abstand zwischen den Kontaktstiften 8-i entspricht dem Abstand der elektrischen Kontakt 4-i innerhalb des Schienenbauelements 2. Darüber hinaus entspricht die Höhe der hervorragenden Kontaktstifte 8-i im Wesentlichen der Tiehas. The distance between the contact pins 8-i corresponds to the distance of the electrical contact 4-i within the rail component 2. Moreover, the height of the protruding contact pins 8-i substantially corresponds to the tie
fe der elektrischen Kontakt 4-i innerhalb des Schienenbauelements 2. Da die Passagierbedieneinheit 5 keine Wechselspan- nungsversorgung benötigt, weist der Stecker 7 der Passagierversorgungseinheit 5 keine Kontaktstifte für die Wechselspan- nungεversorgungskontakte 4-9, 4-10, 4-11 auf. In einer möglichen Ausführungsform sind die elektrischen Kontakte 4-i und die Kontaktstifte 8~i jeweils vergoldet.fe the electrical contact 4-i within the rail component 2. Since the passenger control unit 5 no Wechselpanel Required power supply, the plug 7 of the passenger supply unit 5 no contact pins for the Wechselspan- nungεversorgungskontakte 4-9, 4-10, 4-11. In one possible embodiment, the electrical contacts 4-i and the contact pins 8~i are each gold-plated.
Wie man aus Fig. 2 erkennen kann, weist der Stecker 7 zwei einander gegenüberliegende gefederte Arretierungsvorsprünge 9A, 9B auf, welche in die Arretierungsausnehmungen 3A, 3B des Schienenbauelements 2 an Arretierungspunkten einrasten können. Die Arretierungsvorsprünge 9A, 9B sind in einem Gehäuse des Steckers 7 entgegen der Federkraft einer jeweils zugehörigen Feder versenkbar, wobei die Federkraft der angebrachten Feder entsprechend den Montagevorgaben einstellbar ist. Bei einer möglichen Ausführungsform ist die Federkraft der Federn derart hoch, dass die Arretierung erst bei einer sehr hohen Beschleunigungskraft ausgelöst wird, die ein Vielfaches der Erdbeschleunigungskraft beträgt. Bei einer möglichen Ausführungsform wird die Arretierung erst bei einer Beschleunigung von mehr als dem Sechzehnfachen der Erdbeschleunigungskraft G gelöst.As can be seen from Fig. 2, the plug 7 has two opposing spring-loaded Arretierungsvorsprünge 9 A, 9 B, which can engage in the Arretierungsausnehmungen 3 A, 3 B of the rail component 2 at locking points. The locking projections 9A, 9B are retractable in a housing of the plug 7 against the spring force of a respectively associated spring, wherein the spring force of the attached spring according to the installation specifications is adjustable. In one possible embodiment, the spring force of the springs is so high that the locking is triggered only at a very high acceleration force, which is a multiple of the gravitational force. In one possible embodiment, the locking is released only at an acceleration of more than sixteen times the gravitational force G.
Wie man aus Fig. 2 erkennen kann, ist das Flugzeugkabinenmo- dul 5 in sehr einfacher Weise an der Befestigungsvorrichtung 1 anbringbar. Vor der Arretierung, d. h. dem Einrasten der Arretierungsvorsprünge 9A, 9B in entsprechende Arretierungsausnehmungen 3A7 3B kann das zu montierende Flugzeugkabinen- modul 5 in Längsrichtung des Schienenbauelements 2 durch den Monteur verschoben werden, beispielsweise, um eine Feinjus- tierung vorzunehmen. Die Gleichspannungsversorgungskontakte 4-1, 4-2 sind mit einer Gleichspannungsversorgungsquelle für einen Normalbetrieb verbunden. Die elektrischen Kontakt 4-3,As can be seen from FIG. 2, the aircraft cabin module 5 can be attached to the fastening device 1 in a very simple manner. Before the locking, ie the engagement of the locking projections 9A, 9B in corresponding locking recesses 3A 7 3B, the aircraft cabin module 5 to be mounted can be displaced in the longitudinal direction of the rail component 2 by the installer, for example, to carry out a fine adjustment. The DC power supply contacts 4-1, 4-2 are connected to a DC power source for normal operation. The electrical contact 4-3,
4-4 sind mit einer Gleichspannungsquelle für den Notfallbe- trieb verbunden. Die Datenkontakte 4-5, 4-6, 4-7, 4-8 sind mit einem Server zum Datenaustausch mit den jeweiligen Flug- zeugkabinenmodulen verbunden. Die elektrischen Kontakte 4-9, 4-10, 4-11 sind mit einer WechselSpannungsquelle verbunden, die beispielsweise eine WechselSpannung mit einer Amplitude von 115 Volt liefert.4-4 are connected to a DC source for emergency operation. The data contacts 4-5, 4-6, 4-7, 4-8 are connected to a server for data exchange with the respective flight cabin modules connected. The electrical contacts 4-9, 4-10, 4-11 are connected to an AC voltage source which provides, for example, an AC voltage with an amplitude of 115 volts.
Fig. 3 zeigt das Anbringen einer Notsauerstoffversorgungsein- heit 10 an der Befestigungsvorrichtung 1. Die Notsauerstof£- versorgungseinheit 10 weist wie die Passagierversorgungseinheit 5 einen Stecker 7 auf, der über ein Gelenk 6 mit der Notsauerstoffversorgungseinheit 10 verbunden ist. Die Notsauerstoffversorgungseinheit 10 dient zur dezentralen Sauer- stoffversorgung der Passagiere im Notfall, wobei Sauerstoff- masken aus der Notsauerstoffversorgungseinheit 10 fallen. Zur Spannungsversorgung der Notsauerstoffversorgungseinheit 10 wird eine Wechselspannung von beispielsweise 115 Volt AC benötigt. Daher weist der elektrische Stecker 7, wie in Fig. 3 dargestellt, zwei Kontaktstifte 8-9, 8-11 auf, die in entsprechende elektrische Kontakte 4-9, 4-11 des Schienenbauelements 2 eingreifen.FIG. 3 shows the attachment of an emergency oxygen supply unit 10 to the fastening device 1. Like the passenger supply unit 5, the emergency oxygen supply unit 10 has a plug 7 which is connected to the emergency oxygen supply unit 10 via a joint 6. The emergency oxygen supply unit 10 serves for decentralized oxygen supply to the passengers in an emergency, with oxygen masks falling from the emergency oxygen supply unit 10. To supply power to the emergency oxygen supply unit 10, an AC voltage of, for example, 115 volts AC is needed. Therefore, the electrical connector 7, as shown in Fig. 3, two contact pins 8-9, 8-11, which engage in corresponding electrical contacts 4-9, 4-11 of the rail component 2.
Wie man aus den Fig. 1 bis 3 erkennen kann, dient die Vorrichtung 1 nicht nur zur Befestigung der Flugzeugkabinenmodule, sondern auch zu deren elektrischer Energieversorgung sowie dem Datenaustausch zwischen den Flugzeugkabinenmodulen und einer zentralen Recheneinheit, beispielsweise einem Server. Die Befestigungsvorrichtung 1 eignet sich für beliebige Flugzeugkabinenmodule, beispielsweise für Passagierversorgungseinheiten, Notsauerstoffversorgungseinheiten, Kabinenbeleuchtungseinheiten, Passagieraudioeinheiten, Passagiervideo- einheiten oder Luftdüseneinheiten. Mittels der Befestigungsvorrichtung 1 kann derAs can be seen from FIGS. 1 to 3, the device 1 serves not only for fastening the aircraft cabin modules, but also for their electrical energy supply and the data exchange between the aircraft cabin modules and a central processing unit, for example a server. The fastening device 1 is suitable for any aircraft cabin modules, for example for passenger supply units, emergency oxygen supply units, cabin lighting units, passenger audio units, passenger video units or air nozzle units. By means of the fastening device 1, the
Aufwand hinsichtlich der Verkabelung erheblich vermindert werden. Eine separate Verkabelung für die Energie- und Daten- Übertragung entfällt. Weiterhin wird die Montage der Flugzeugkabinenmodule für die Monteure erheblich erleichtert. Es wird eine wesentliche Verbesserung hinsichtlich der Flexibilität beim Einbau der Flugzeugkabinenmodule erreicht. Darüber hinaus wird die Wartbarkeit der Flugzeugkabinenmodule erleichtert. Durch den Einsatz der Befestigungsvorrichtung 1 als standardisierte Schnittstelle ist es zudem möglich, neuartige Flugzeugkabinenmodule schnell und einfach in das System zu integrieren. Weiterhin wird der Einbau von Flugzeugkabinenmodulen entsprechend den Kundenwünschen vereinfacht. Costs are significantly reduced with regard to the wiring. A separate cabling for the energy and data transmission is eliminated. Furthermore, the installation of aircraft cabin modules for technicians is greatly facilitated. It a significant improvement in the flexibility in installation of the aircraft cabin modules is achieved. In addition, the maintainability of the aircraft cabin modules is facilitated. By using the fastening device 1 as a standardized interface, it is also possible to integrate novel aircraft cabin modules quickly and easily into the system. Furthermore, the installation of aircraft cabin modules is simplified according to customer requirements.

Claims

P a t e n t a n s p r ü c h e Patent claims
1. Vorrichtung zur Befestigung mindestens eines Flugzeugka- binenmoduls, die ein Bauelement mit Schenkeln zur lösbaren Arretierung eines an dem Flugzeugkabinenmodul angebrachten Steckers und mehrere elektrische Kontakte aufweist, dadurch gekennzeichnet , dass das Bauelement als Schienenbauelement (2) U-förmig ausgebildet ist, wobei dessen Schenkel (2A, 2B) Arretierungspunkte (3A, 3B) zur lösbaren Arretierung des an dem Flugzeugskabinenmodul {5, 10} angebrachten Steckers (7) aufweisen und dessen die beiden Schenkel (2A, 2B) ver- bindender Mittelabschnitt (2) die elektrische Kontakte (4-i) zur Spannungsversorgung und zum Datenaustausch von Daten mit dem Flugzeugkabinenmodul (5, 10) aufweist.1. A device for attaching at least one aircraft cabin module, which has a component with legs for releasably locking a plug attached to the aircraft cabin module connector and a plurality of electrical contacts, characterized in that the component as a rail component (2) is U-shaped, wherein the Leg (2A, 2B) locking points (3A, 3B) for releasably locking the attached to the aircraft cabin module {5, 10} plug (7) and its two legs (2A, 2B) connecting the middle section (2) the electrical contacts (4-i) for power supply and data exchange of data with the aircraft cabin module (5, 10).
2. Vorrichtung zur Befestigung mindestens eines Flugzeugka- binenmoduls nach Anspruch 1, dadurch gekennzeichnet , dass die elektrischen Kontakte (4-i) durch Kontaktnuten gebildet werden, in denen Kontaktstifte (8-i) des an dem Flugzeugkabinenmoduls (5; 10) angebrachten Steckers (7) in einer Längsrichtung des Schienenbauelements (2) vor der Arretierung des Steckers (7) verschiebbar sind.2. Device for fastening at least one aircraft cabin module according to claim 1, characterized in that the electrical contacts (4-i) are formed by contact grooves in which contact pins (8-i) of the plug attached to the aircraft cabin module (5; (7) in a longitudinal direction of the rail component (2) before the locking of the plug (7) are displaceable.
3. Vorrichtung nach Anspruch 1 oder 2, dadurch gekennzei chnet , dass das Schienenbauelement (2) aus einem elektrisch isolierenden Material besteht, in dem die elektrisch leitenden Kontakte eingefügt sind.3. Apparatus according to claim 1 or 2, characterized gekennzei chnet that the rail component (2) consists of an electrically insulating material in which the electrically conductive contacts are inserted.
4. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet , dass das elektrisch isolierende Material Aluminium, CFK oder Teflon aufweist.4. Apparatus according to claim 3, characterized in that the electrically insulating material comprises aluminum, CFRP or Teflon.
5. Vorrichtung nach Anspruch 1-4, dadurch gekennzeichnet , dass die elektrischen Kontakte (4-i) jeweils mit einer Schutzkappe zum Schutz gegen Korrosion abdeckbar sind.5. Apparatus according to claim 1-4, characterized in that the electrical contacts (4-i) are each covered with a protective cap to protect against corrosion.
6. Vorrichtung nach Anspruch 5, dadurch gekennzei chnet , das s die Schutzkappe eine Gummilippe ist.6. Apparatus according to claim 5, characterized gekennzei chnet, s the protective cap is a rubber lip.
7. Vorrichtung nach Anspruch 1-5, dadurch gekennzeichnet , dass die elektrischen Kontakte (4-i)7. Apparatus according to claim 1-5, characterized in that the electrical contacts (4-i)
Gleichspannungskontakte (4-1, 4-2, 4-3, 4-4) zum Anlegen einer Gleichspannung,DC voltage contacts (4-1, 4-2, 4-3, 4-4) for applying a DC voltage,
Wechselspannungskontakte (4-9, 4-10, 4-11) zum Anlegen einer WechselSpannung und Datenkontakte (4-5, 4-6, 4-7, 4-8) zum Austausch von Daten zwischen dem Flugzeugkabinenmodul (5, 10) und einem Flugzeugkabinenserver aufweisen.AC voltage contacts (4-9, 4-10, 4-11) for applying an AC voltage and data contacts (4-5, 4-6, 4-7, 4-8) for exchanging data between the aircraft cabin module (5, 10) and have an aircraft cabin server.
8. Vorrichtung nach Anspruch 1-7, dadurch gekennzeichnet , dass das Flugzeugkabinenmodul (5, 10) eine Passagierversorgungseinheit , eine Ausgleichseinheit, eine NotsauerstoffVersorgungseinheit, eine Kabinenbeleuchtungseinheit, eine Passagieraudioeinheit, eine Passagiervideoeinheit oder eine Luftdüseneinheit aufweist.8. The device according to claim 1-7, characterized in that the aircraft cabin module (5, 10) comprises a passenger supply unit, a compensation unit, an emergency oxygen supply unit, a cabin lighting unit, a passenger audio unit, a passenger video unit or an air nozzle unit.
9. Vorrichtung nach Anspruch I1 dadurch gekennzeichnet , dass die Datenkontakte (4-5, 4-6, 4-7, 4-8) jeweils einen vorgegebenen Wellenwiderstand aufweisen, derlOO Ohm /Meter beträgt oder dem Wellenwiderstand des Verwendeten Datenbusses entspricht .9. Apparatus according to claim I 1, characterized in that the data contacts (4-5, 4-6, 4-7, 4-8) each have a given characteristic impedance which is 100 ohms / meter or corresponds to the characteristic impedance of the data bus used.
10. Vorrichtung nach Anspruch 1-8, dadurch gekennz e i chne t , das s an dem Stecker (7) gefederte Arretierungsvorsprünge (9A, 9B) angebracht sind, die in Arretierungsausnehmungen (3A, 3B) der Schenkel (2A, 2B) einrasten.Device according to claims 1-8, characterized in that there are mounted on the plug (7) spring-loaded detent projections (9A, 9B) which engage in detent recesses (3A, 3B) of the legs (2A, 2B).
11. Vorrichtung nach Anspruch 9, dadurch gekenn ze i chnet , das s sich die Arretierung des Flugzeugkabinenmoduls {5; 10) erst bei einer hohen Beschleunigungskraft löst, die mehr als ein Sechzehnfaches der Erdbeschleunigungskraft beträgt . 11. The device according to claim 9, characterized ze zechnet, the s is the locking of the aircraft cabin module {5; 10) only at a high acceleration force, which is more than sixteen times the gravitational force.
EP09705325.0A 2008-01-28 2009-01-28 Device for fastening an aircraft cabin module Not-in-force EP2238653B1 (en)

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PCT/EP2009/050954 WO2009095414A1 (en) 2008-01-28 2009-01-28 Device for fastening an aircraft cabin module

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Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8094436B2 (en) * 2010-03-29 2012-01-10 Eaton Corporation Plug-in circuit breaker assembly
US8488302B2 (en) 2011-04-14 2013-07-16 Eaton Corporation Circuit breaker panel
US8776145B2 (en) 2011-09-16 2014-07-08 Elwha Llc In-transit electronic media with location-based content
US9158908B2 (en) 2011-09-16 2015-10-13 Elwha Llc Power source for in-transit electronic media
US8649160B2 (en) 2012-02-07 2014-02-11 Eaton Corporation Plug-in circuit breaker assembly including insulative retainers
CN103523216B (en) * 2013-07-10 2016-02-03 西安航空制动科技有限公司 carbon-carbon composite material guide rail and preparation method thereof
US10135206B2 (en) * 2014-06-13 2018-11-20 3M Innovative Properties Company Electrical connector having a base with an inverted T-shaped channel
EP3410143B1 (en) * 2017-05-31 2019-07-10 Siemens Healthcare GmbH Connector for use in a magnetic resonance device
US12266893B2 (en) * 2022-04-19 2025-04-01 Dell Products L.P. Connection assembly for use in an information handling system
DE102022124324A1 (en) * 2022-09-22 2024-03-28 Te Connectivity Germany Gmbh Housing arrangement for an electrical plug and electrical plug and plug arrangement
US12431666B2 (en) * 2022-12-30 2025-09-30 Roku, Inc. Expandable accordion-style cable overmold for secure connection

Family Cites Families (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3566336A (en) * 1968-08-30 1971-02-23 Itt Connector assembly
IT1033395B (en) * 1975-03-04 1979-07-10 Gc Illumination Spa ELECTRIFIED CHANNEL WITH SNAP CONNECTOR
US4458973A (en) * 1983-01-28 1984-07-10 Amp Incorporated Connector assembly having improved internal latching system
DE3416143A1 (en) * 1984-05-02 1985-11-07 Sidler GmbH & Co, 7400 Tübingen Omnibus wiring busbar
US4572602A (en) * 1984-10-31 1986-02-25 Amp Incorporated Electrical connector assembly with guide member
US4761144A (en) * 1986-12-22 1988-08-02 Amp Incorporated Mounting means for rack and panel connector
NL9000967A (en) * 1990-04-23 1991-11-18 Du Pont Nederland DEVICE FOR ELECTRO-OPTICAL SIGNAL CONVERSION.
US5486117A (en) * 1994-08-09 1996-01-23 Molex Incorporated Locking system for an electrical connector assembly
US5575690A (en) * 1994-10-28 1996-11-19 Tvm, Inc. Hybrid modular electrical connector system
JP3000336B2 (en) * 1995-06-02 2000-01-17 日本航空電子工業株式会社 Connector device
JP3232240B2 (en) * 1996-04-26 2001-11-26 ヒロセ電機株式会社 Electrical connector
JP3143739B2 (en) * 1997-10-06 2001-03-07 日本航空電子工業株式会社 Connector device with floating function
US6244889B1 (en) * 1998-01-20 2001-06-12 Intel Corporation Method and apparatus for an electromechanically controlled electronic interface plug
KR100413026B1 (en) * 1998-04-30 2004-03-22 삼성전자주식회사 A connector assembly
WO1999062145A1 (en) * 1998-05-27 1999-12-02 Tyco Electronics Corporation Electrical connector with split shells and retention clip and method of assembling the connector
SG109416A1 (en) * 1999-01-26 2005-03-30 Molex Inc Electrical connector with locking mechanism and metal spring
DE29904381U1 (en) * 1999-03-10 2000-08-10 Robert Bosch Gmbh, 70469 Stuttgart Electrical plug device with a fixing device
US6123575A (en) * 1999-07-30 2000-09-26 Huang; Wayne Electrical card connector with mixed latching means
US6687780B1 (en) * 2000-11-02 2004-02-03 Rambus Inc. Expandable slave device system
JP2003303634A (en) * 2002-04-11 2003-10-24 Tyco Electronics Amp Kk Electric connector assembly and cap connector
US6945666B2 (en) * 2003-06-30 2005-09-20 Monarch Instrument Illumination device with removable power pack
CN2652608Y (en) * 2003-11-06 2004-11-03 韩金龙 Locking type knife store house
JP4193723B2 (en) * 2004-02-13 2008-12-10 住友電装株式会社 connector
US7188805B2 (en) * 2004-03-27 2007-03-13 The Boeing Company Continuous power bus for seat power
US7060910B2 (en) * 2004-08-18 2006-06-13 Airbus Deutschland Gmbh Attachment system for an electrical device for installation in aircraft cabins
US7217146B2 (en) * 2004-12-17 2007-05-15 Scientific-Atlanta, Inc. Connector insert for preventing contamination
FR2881278A1 (en) * 2005-01-21 2006-07-28 Fci Sa ELECTRICAL CONNECTOR WITH A REVERSIBLE CABLE GUIDE COVER, AND METHOD OF ASSEMBLING SUCH A CONNECTOR
CN2850045Y (en) * 2005-04-08 2006-12-20 富士康(昆山)电脑接插件有限公司 Electric connector assembly
JP2007122886A (en) * 2005-10-25 2007-05-17 Fujitsu Component Ltd Connector protective cover
DE102006012730B3 (en) * 2006-03-17 2007-11-08 Airbus Deutschland Gmbh An attachment system for attaching a cabin trim element to a support structure of an aircraft
US7431605B2 (en) * 2006-12-06 2008-10-07 J.S.T. Corporation Connector position assurance apparatus
AU314482S (en) * 2007-03-14 2007-06-08 Tyco Electronics Services Gmbh Dust cover for an electrical connector
CN101677168B (en) * 2008-09-16 2011-09-07 富士康(昆山)电脑接插件有限公司 Electric connector assembly and its socket electric connector and plug electric connector

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009095414A1 *

Also Published As

Publication number Publication date
RU2485648C2 (en) 2013-06-20
CN101926063A (en) 2010-12-22
JP2011513891A (en) 2011-04-28
WO2009095414A1 (en) 2009-08-06
JP5232249B2 (en) 2013-07-10
BRPI0906664A2 (en) 2015-07-14
US9252532B2 (en) 2016-02-02
EP2238653B1 (en) 2017-08-02
US20110034058A1 (en) 2011-02-10
DE102008006433A1 (en) 2009-08-27
DE102008006433B4 (en) 2011-07-28
RU2010133887A (en) 2012-03-10
CA2711246A1 (en) 2009-08-06

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