DE102004049893B4 - Joint cover in aircraft - Google Patents

Joint cover in aircraft

Info

Publication number
DE102004049893B4
DE102004049893B4 DE200410049893 DE102004049893A DE102004049893B4 DE 102004049893 B4 DE102004049893 B4 DE 102004049893B4 DE 200410049893 DE200410049893 DE 200410049893 DE 102004049893 A DE102004049893 A DE 102004049893A DE 102004049893 B4 DE102004049893 B4 DE 102004049893B4
Authority
DE
Germany
Prior art keywords
cover
joint
joint cover
clamping
aircraft
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.)
Expired - Fee Related
Application number
DE200410049893
Other languages
German (de)
Other versions
DE102004049893A1 (en
Inventor
Werner Granzeier
Jan Schröder
Andreas Wietzke
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
Priority to DE200410049893 priority Critical patent/DE102004049893B4/en
Priority claimed from EP05022132A external-priority patent/EP1647480B1/en
Publication of DE102004049893A1 publication Critical patent/DE102004049893A1/en
Application granted granted Critical
Publication of DE102004049893B4 publication Critical patent/DE102004049893B4/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/066Interior liners

Abstract

A joint cover for covering a joint (5) between a first element (3) and a second element (4) in an aircraft, comprising:
a clamping portion (6, 7); and
a cover portion (2);
wherein the cover portion (2) for covering a joint (5) between a first element (3) and a second element (4) is executed;
wherein the clamping portion (6, 7) for fixing the joint cover is made such that the first and second members (3, 4) are movable relative to each other so that the joint can contract;
wherein the first element (3) is a first interior of an aircraft and the second element is a second interior of an aircraft, the first and second interior devices being wall or ceiling trim elements of the aircraft; and
wherein the clamping portion (6,7) has a rear portion (6) which rests after mounting the joint cover in the joint back and surface on the first element (3) and the second element (4), ...

Description

  • The The invention relates to joint covers for aircraft. In particular, it concerns the invention a joint cover for covering a joint in one Airplane, the use of a joint cover in an airplane and an aircraft comprising a corresponding joint cover.
  • In Aircraft are used for interior fittings, such as ceilings. or wall coverings, with appropriately stored holder or Fasteners on the primary structure or other supporting Aircraft elements attached. While In flight, the fuselage of the aircraft deforms, for example due to pressure differences, significant. Thus act on the Fasteners or cladding partially considerable stresses, which leads to deformation or displacement of the panels and to visual change the gap or joint dimensions relative to each other.
  • aircraft cabins All are manufactured using the same technological process. All components, such. B. wall cladding elements (window panels, Window front panels, ceiling panels) receive elaborate edge radii and are partly suspended three-dimensionally in the room. A fixed camp and a Floating bearings ensure the flexibility of hull deformations. in this connection be great Movements or deformations of the hull are immediately visible to the passenger.
  • elastic Visual covers inside or behind the joints, such as Kederbänder, are a permanent disruptive part in daily operation and require regular repair.
  • Farther are the necessary removal, installation, maintenance and upkeep the window panels or window front panels time consuming and costly Factors in the daily Business.
  • Especially the components and joints in the spherical areas of a cabin are subject to special requirements.
  • US 2004/0021039 A1 describes a side wall assembly which can be assembled via a click connection. The two walls are firmly fixed by a connecting element.
  • US 5,695,154 A describes a joint cover for an aircraft outer skin, which is made of metal, has two legs which are pushed into the joint and is held by frictional forces in the joint.
  • It It is an object of the invention to provide a joint cover in particular for airplanes provide a simple and secure cover of Joints allowed.
  • These The object is achieved with the features of the independent claims.
  • According to one embodiment Invention as stated in claim 1, the above object is achieved by means of a joint cover to cover a joint between a first Element and a second element solved in an airplane, comprising a clamping portion and a cover portion, wherein the cover portion to the Cover a joint between a first element and a second Element executed is, wherein the clamping portion for securing the joint cover executed in such a way in that the first and the second element are movable relative to each other.
  • The Joint cover according to the invention shields thus the gap, which between two (possibly movably mounted) Wall or ceiling cladding elements exist, visually and mechanically from. Here, the joint cover, for example, on the primary structure be mounted on the aircraft or on one of the wall paneling elements. This ensures that that the passengers on the one hand deformations of the trunk no longer directly about changes can perceive the joint width and that on the other hand, no more objects squeezed in the joint can be because the cover portion not only visually, but also the joint mechanically covering.
  • According to one another embodiment of the Invention, the first element is a first interior of a Aircraft and the second element, a second interior of a Aircraft.
  • Consequently can Joints between aircraft interiors simply and safely concealed and protected become.
  • According to one another embodiment of the Invention, the cover portion consists essentially of a elastic material, wherein the cover portion in the relaxed Condition a curvature and wherein the cover portion after mounting the joint cover in the joint under tension on the front sides of the first element and the second element is created.
  • Thus, after installation of the joint cover, the cover portion can exert mechanical tension on the clamping section located behind it and continue to be in a tight position relative to the clamping section occupy first element and the second element, so that no objects between the joint cover and the elements can be pushed.
  • According to one further exemplary embodiment According to the invention, the clamping portion has a first portion which can be pushed through the joint when mounting the joint cover is, with the rear area after mounting the joint cover in the fugue on the back is applied to the first element and the second element, so that a dissolution the joint cover from the joint is avoidable.
  • On This way, the joint cover can easily and quickly in the joint to be assembled. This is done for example by simply pressing in the Joint cover in the joint. The rear area of the clamping section is for this for example compressed and then expands accordingly after being pushed in, so he's a later one Pulling out the joint cover from the joint prevents.
  • According to one another embodiment of the Invention is the first element and the second Element around fairings, their position or shape relative to their Environment during of flight operations can, wherein the joint cover the movements of the first element largely follows and wherein the cover portion always on the first element and the second element is applied.
  • advantageously, Thus, a joint cover is given, which in a simple way and manner can be connected to the first element and, for example due to spring forces, a close contact of the cover section to the two elements guaranteed.
  • According to one another embodiment of the Invention, the clamping portion has a second portion, which is fixedly connected to the cover portion, wherein the second portion or the first portion of the clamping portion on the first element is fastened and being fastened by Gluing, clipping, ultrasonic welding, screwing, riveting or by adhesion.
  • advantageously, is thus a joint coverage specified, which in a multifunctional manner on a variety of surfaces is mountable in the aircraft.
  • According to one another embodiment of the Invention, the joint cover further comprises a component selected from the group consisting of illumination device, sensor device, Speaker, and display device.
  • According to one another embodiment of the Invention, the cover portion comprises a translucent material on, so that the joint cover is durchleuchtbar.
  • Consequently can design the joint cover and thus the entire aircraft cabin the individual customer wishes be adjusted. According to the embodiments the claims 8 and 9 is the joint cover according to the invention as an information carrier usable.
  • According to one another embodiment of the Invention, the joint cover is designed as an extruded profile. An extruded profile or extruder profile made of plastic offers the advantage of the cost-effective Production as an endless component. Sealing elements and undercuts can be reconstructed with. Cutting to the required component length offers especially the possibility these parts in the retrofit area to use in existing cabins. With a suitable choice of material the installation of these parts in curved Position is no problem. Flexible materials can adapt the profile to the component geometry and to the shifting surfaces. Appropriate surfaces and color schemes can for the Customers are used corporate.
  • According to one another embodiment of the Invention, the joint cover is formed as an injection molded part. As an injection molding, all the advantages of a three-dimensional Make use of shape. Especially the installation preparation for lighting, sound elements (loudspeakers) and leave sensors or display devices make sense to implement in an injection molded part. Through the installation variants and combination of transparent and opaque materials with numerous variants of the surface shaping can be manufacture and install innovative design elements in the cabin. The elaborate edge processing hidden in this area Components can be omitted.
  • Further embodiments The invention results from the use claim and the additional independent Apparatus claim.
  • in the The following will be preferred embodiments with reference to the figures of the invention.
  • 1 shows a schematic representation of a window area in an aircraft cabin.
  • 2 shows a schematic representation of a joint cover according to an embodiment of the invention.1
  • 3 shows a schematic cross-sectional view of the joint cover of 2 ,
  • 4 shows a schematic representation of another joint cover according to another embodiment of the invention.
  • 5 shows a schematic cross-sectional view of the joint cover of 4 ,
  • 6 shows a schematic representation of another joint cover according to another embodiment of the invention.
  • 7 shows a schematic representation of another joint cover according to an embodiment of the invention.
  • 8th shows a schematic cross-sectional view of the joint cover of 7 ,
  • 9 shows a schematic cross-sectional view of the joint cover of 2 in three different phases of assembly.
  • 10 shows a schematic cross-sectional view of another joint cover according to an embodiment of the invention.
  • In The following figure description will be for the same or similar Elements use the same reference numbers.
  • 1 shows a schematic representation of a window area in an aircraft cabin. As in 1 To recognize the window area, various wall panels or window panels or window front panels 3 . 4 on which the windows 8th . 9 take up. Due to the deformation of the aircraft fuselage during flight, which can be caused for example because of the enormous pressure differences, it can lead to deformation and relative displacement of the window panels 3 . 4 come relative to each other. That's why the side panels are 3 . 4 fixed at a distance from each other to the primary structure of the aircraft or other supporting parts. The between the side panels 3 . 4 lying gap expands during flight or contracts.
  • The joints are an essential aesthetic, constructive and functional element in the interior component equipment of a means of transport (here not only aircraft are addressed, but can also be other means of transport, such as bus, train, ship or the like). Through the joint cover according to the invention with its cover portion 2 Located in the passenger's immediate visual field of view, a high degree of visible design quality, product information, passenger impact and confidence can be achieved.
  • For example, this can be Information media, such as light-emitting diode arrays, loudspeakers, fragrance Screens or information screens in the joint cover according to the invention to get integrated. Furthermore you can Sensor systems for contactless Function to be installed in the joint cover, which the passenger an elevated one Allow comfort.
  • 2 shows a schematic representation of a joint cover according to an embodiment of the invention. As in 2 to recognize, the joint cover, which is a cover portion 2 between the interior fittings 3 . 4 assembled. This is the fugue 5 which is located between the two interiors 3 . 4 located completely off the cover portion 2 covered.
  • by virtue of the construction of the custom joint cover can this component for every Window panel joint to be used. By clamping, clipping, plugging, Ultrasonic welding, Screwing, riveting or even by an adhesive or clamping force can All variants of the joint cover simply attached and installed and thus effectively cover the joint.
  • Since the joints are covered by the joint cover according to the invention, no complex edge radii in the manufacture of the window panels are required, which production costs can be saved. All tolerances are covered and, in particular, a covering of the joint is provided, which also has an injury-reducing function in the case of an accident, since the edges of the side parts 3 . 4 be hidden by the joint cover and continue the open joint cover can provide additional fixation of the side panels relative to each other. Cedar bands or so-called "filler strips" can be omitted here.
  • 3 shows a schematic cross-sectional view of the joint cover of 2 , As 3 can be seen, the joint cover, which consists essentially of the cover portion 2 and the clamping portion 6 . 7 exists between the two interiors 3 . 4 positioned. The cover section 2 consists here of an elastic material, which in the relaxed To has a curved shape. In the assembled state of the cover portion lies 2 , as in 3 to recognize, close to the first 3 and the second interior 4 at. Here, the cover portion 2 are under tension, leaving a tight fit of the cover section 2 to the surfaces of the interior fittings 3 . 4 even with a relative movement of the interior fittings 3 . 4 is guaranteed to each other.
  • The cover section 2 Here, in its dimensioning is kept larger than the width of the joint 5 , Thus, an always complete coverage of the joint is guaranteed even with deformation of the fuselage.
  • The clamping section 6 . 7 consists of a rear area 6 and from a front area 7 which is fixed to the cover section 2 connected is. The back area 6 serves to prevent slipping out of the cover from the joint. To hold the joint cover sufficiently firmly in the joint, for example, adhesive forces, which by the spring force of the cover portion 2 be exploited. This pushes the cover 2 with their outer edges to the surfaces of the interior fittings 3 . 4 and thus generates a force which is the rear area 6 of the clamping section 6 . 7 against the backs of the interior fittings 3 . 4 pulls, leaving the joint cover to the interior fittings 3 . 4 is clamped.
  • Of course, other fixings are possible. For example, the front area 7 or the back area 6 of the clamping section 6 . 7 to the first interior 3 glued, clipped, welded, screwed or riveted, so that here a rigid connection is ensured and the joint cover the movements of the first interior 3 thus largely follows. interior 4 however, can move relative to the joint cover, due to the dimensions of the cover 2 always a complete cover of the joint 5 is guaranteed.
  • 4 shows a schematic representation of another joint cover according to another embodiment of the invention. The cover section 2 which the fugue 5 obscured, this has a monitor 10 on which information can be given to the passenger. Instead of a monitor 10 It is also possible to integrate a light-emitting diode display or another type of information screen into the joint cover. This integration takes place, for example, in the production process of the joint cover, whereby the final assembly of the unit is facilitated.
  • 5 shows a schematic cross-sectional view of the joint cover of 4 , The cover section 2 is here designed as a volume component whose back flat to the interior fittings 3 . 4 is applied. The back area 6 of the clamping section 6 . 7 guaranteed in interaction with the cover section 2 a tight fit of the joint cover in the joint 5 ,
  • 6 shows a schematic representation of another joint cover according to another embodiment of the invention. Here, the upper portion of the cover portion 2 a translucent material. This translucent material 11 For example, it can be backlit by a light source integrated behind the joint cover or in the joint cover. Here it is possible to achieve various color effects or lighting effects, which can affect the sensory organs of the passengers in a pleasant or soothing or informative way.
  • The translucent material 11 may for example be in the form of a translucent polyester film with a special coating. The polyester film 11 For example, it can be designed in the form of a plotter foil, which is suitable for illuminated advertising.
  • 7 shows a schematic representation of another joint cover according to an embodiment of the invention. The cover section 2 has sensor systems 12 on, which are designed for non-contact measurement of physical parameters. For example, these may be temperature sensors, humidity sensors, odor sensors, light sensors or sound sensors. This sensor is essentially used to obtain data on the physical conditions in the passenger and this data then pass on to a corresponding processor, which can make an evaluation and then based on a regulation.
  • Also, in the field of sensor systems 12 an LED light row integrated (or in another area), which can emit light signals or light signals. These may be, for example, seat numbers, emergency signs or prohibition or mandatory signs.
  • Such a LED light row or even a monitor 10 can be used to represent a particular information in the aircraft cabin, which reflects the information as a font or icon. These are, for example, the reproduction of commands or warnings, such as "No smoking" or "fast seat belt".
  • The information presented here can be quite different. For example, it is possible to map static information, for example in the form of no smoking signs or requests for buckling or the like. Also, information regarding the corresponding row of seats or the corresponding seat or even escape route information can be displayed here. In the escape route information, for example, arrows are displayed, which point in the direction of the next possible emergency exit. Of course, but also dynamic information can be displayed, such as entertainment films or well-being enhancing visual stimuli. Of course, however, information concerning technical matters can also be displayed individually. This may be, for example, the current airspeed, the current altitude, the distance to the destination, the outside temperature or else the current temperature at the destination. Here it is z. B. possible that a control unit is provided (not shown in FIG 7 ), which is also integrated in the joint cover or in the passenger seat, and which has a corresponding data memory, so that the passenger can select all the information he needs individually.
  • In the upper part of the cover 2 is an arrangement of slots 13 integrated, which for the sound of a built-behind or inside the joint cover speaker (not shown in 7 ) is executed.
  • 8th shows a schematic cross-sectional view of the joint cover of 7 , Here it can be seen that the cover section 2 Angle at its sides 14 . 15 which is flat on the surfaces of the interior linings 3 . 4 issue.
  • 9 shows a schematic cross-sectional view of the joint cover of 2 in three different phases of assembly.
  • As 9A to remove, the rear section 6 of the clamping section 6 . 7 when pushing in the joint cover into the joint 5 angled or compressed. This bending is made possible for example by the fact that the rear area 6 is made of a material that can be bent (elastically) in the appropriate direction. This may be, for example, a suitably shaped rubber element. But also joints can be at the transitions between front 6 and rear areas 7 of the clamping section 6 . 7 be provided, which is a kinking of the rear area 6 allow so that the joint cover in the joint 5 push in, although the cross-section of the clamp 6 . 7 in the tensioned state is greater than the width of the joint 5 , The pushing in takes place in the direction of the arrow 14 ,
  • 9B shows the second phase of assembly of the joint cover. The back area 6 of the clamping section 6 . 7 is now completely through the fugue 5 pushed through and is in a deployed or relaxed state. The cover section 2 , which consists of an elastic material and has a curvature in the relaxed state, is to the interior fittings 3 . 4 pressed down and thus exerts a strong pressure on the interior fittings via its spring force 3 . 4 out, causing the clamping section 6 . 7 in the direction of the arrow 16 is pulled.
  • 9C shows the third and final phase of joint cover assembly. The back area 6 of the clamping section 6 . 7 is now firmly on the surfaces of the interiors 3 . 4 on and thus stuck in conjunction with the (still stretched) cover section 2 at the interiors 3 . 4 firmly. Of course, for further retention of the joint cover on the interior 3 Adhesive in the area 17 be provided, whereby the joint cover with the interior 3 can be firmly connected.
  • The customized joint cover is a cost-effective way different Cabin design variants to realize. By the change of the visually important area in the perceptual zone of the passengers can novel cabin effects with a serially produced additional part (Joint cover) can be achieved.
  • The formal conception of a standard cabin can be adapted to individual customer wishes become. With additional Components such as lighting, speakers, screens, scenting devices or translucent materials can change the overall impression of the cabin customized become. The adaptation of the cabin layout to the customer needs can thus be carried out quickly and cost-efficiently.
  • Within this conception can for leasing products or second-hand means of transport in the event of a change of operator the cabins without big tags and corresponding recertification adapted to the customer's request become.
  • It can All joints are to be provided with the joint cover (also later!). Farther Is it possible, to buy the joint cover with customized decorative foil or to be provided with an appropriate textured finish.
  • Before the component is glued or otherwise mounted, additional assemblies, such as light functions, scent units, speakers or mini-screens, to be assembled. Furthermore, the custom cover part also have special functions, such as LED lighting effects.
  • 10 shows a schematic cross-sectional view of another joint cover according to an embodiment of the invention. As in 10 can recognize the connection of the joint cover parallel to the window panels directly to the aircraft structure, such as aircraft bulkhead 19 , respectively. The two panels 3 . 4 In this way, they can move independently of the joint cover. The attachment of the panels and the joint cover can over standard clips 18 done on a mounting plate 20 can be mounted.
  • The Restricted invention in their execution not to the preferred embodiment shown in the figure. Rather, a variety of variants is conceivable, which of the illustrated solution and the principle of the invention also in principle different types of embodiments Use.

Claims (12)

  1. Joint cover for covering a joint ( 5 ) between a first element ( 3 ) and a second element ( 4 ) in an aircraft, comprising: a clamping section ( 6 . 7 ); and a cover portion ( 2 ); the cover section ( 2 ) to cover a joint ( 5 ) between a first element ( 3 ) and a second element ( 4 ) is executed; wherein the clamping section ( 6 . 7 ) is carried out for fixing the joint cover such that the first and the second element ( 3 . 4 ) are movable relative to each other, so that the joint can contract; the first element ( 3 ) a first interior of an aircraft and the second element is a second interior of an aircraft, wherein the first and second interior furnishings are wall or ceiling trim elements of the aircraft; and wherein the clamping portion ( 6 . 7 ) a rear area ( 6 ), which after mounting the joint cover in the joint on the back and flat on the first element ( 3 ) and the second element ( 4 ), so that a detachment of the joint cover from the joint ( 5 ) is avoidable.
  2. Joint cover according to claim 1, wherein the cover portion ( 2 ) consists essentially of an elastic material; the cover section ( 2 ) has a curvature in the relaxed state; and wherein the cover portion ( 2 ) after mounting the joint cover in the joint ( 5 ) under tension on the front side of the first element ( 3 ) and the second element ( 4 ) is created.
  3. Joint cover according to one of claims 1 or 2, wherein a first portion ( 6 ) of the clamping section ( 6 . 7 ) when mounting the joint cover through the joint ( 5 ) is pushed through.
  4. Joint cover according to one of the preceding claims, wherein the first element ( 3 ) and the second element ( 4 ) are panels that can change their position or shape relative to their surroundings during flight operations; wherein the joint cover the movements of the first element ( 3 ) largely follows; and wherein the cover portion ( 2 ) always on the first element ( 3 ) and the second element ( 4 ) is created.
  5. Joint cover according to one of the preceding claims, wherein the clamping portion ( 6 . 7 ) a second subregion ( 7 ), which is connected to the cover portion ( 2 ) is firmly connected; and wherein the second subregion ( 7 ) or the first subarea ( 6 ) of the clamping section ( 6 . 7 ) on the first element ( 3 ) is attachable.
  6. Joint cover according to claim 5, wherein the attachment by gluing, clipping, ultrasonic welding, screwing, riveting or by adhesion.
  7. Joint cover according to one of the preceding claims, further comprising a component selected from the group consisting of: Lighting device, sensor device, Speaker, and display device.
  8. Joint cover according to one of the preceding claims, wherein the cover portion ( 2 ) has a translucent material, so that the joint cover is durchleuchtbar.
  9. Joint cover according to one of the preceding claims, wherein the joint cover is designed as an extruded profile.
  10. Joint cover according to one of claims 1 to 8, wherein the joint cover is designed as an injection molded part.
  11. Use of a joint cover according to one of claims 1 to 10 in an airplane.
  12. Airplane comprising a joint cover according to one of claims 1 to 10.
DE200410049893 2004-10-13 2004-10-13 Joint cover in aircraft Expired - Fee Related DE102004049893B4 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE200410049893 DE102004049893B4 (en) 2004-10-13 2004-10-13 Joint cover in aircraft

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE200410049893 DE102004049893B4 (en) 2004-10-13 2004-10-13 Joint cover in aircraft
DE200550010646 DE502005010646D1 (en) 2004-10-13 2005-10-11 Joint cover in aircraft
AT05022132T AT490908T (en) 2004-10-13 2005-10-11 Joint cover in planes
EP05022132A EP1647480B1 (en) 2004-10-13 2005-10-11 Joint covering for aircraft
US11/249,550 US7478781B2 (en) 2004-10-13 2005-10-13 Joint cover in aircraft

Publications (2)

Publication Number Publication Date
DE102004049893A1 DE102004049893A1 (en) 2006-04-27
DE102004049893B4 true DE102004049893B4 (en) 2010-07-01

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DE200410049893 Expired - Fee Related DE102004049893B4 (en) 2004-10-13 2004-10-13 Joint cover in aircraft
DE200550010646 Active DE502005010646D1 (en) 2004-10-13 2005-10-11 Joint cover in aircraft

Family Applications After (1)

Application Number Title Priority Date Filing Date
DE200550010646 Active DE502005010646D1 (en) 2004-10-13 2005-10-11 Joint cover in aircraft

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AT (1) AT490908T (en)
DE (2) DE102004049893B4 (en)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
EP2602188A2 (en) 2011-12-09 2013-06-12 Airbus Operations GmbH Covering device and aircraft area comprising covering device

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Publication number Priority date Publication date Assignee Title
DE102006017241B4 (en) * 2006-04-12 2017-11-23 Airbus Operations Gmbh Level gap cover for cabin linings
DE102007013904A1 (en) 2007-03-22 2008-09-25 Airbus Deutschland Gmbh Spaltabdeckvorrichtung
US7578453B1 (en) 2008-02-15 2009-08-25 Kohler Co. Handshower assembly
DE102008061381A1 (en) * 2008-12-10 2010-06-24 Siemens Aktiengesellschaft Interior trim of a vehicle
US9180823B2 (en) * 2013-05-15 2015-11-10 Embraer S.A. Adaptive decorative trim assemblies for vehicle cabin interiors
FR3023536B1 (en) * 2014-07-10 2018-01-19 Airbus Corp Jet Centre Aircraft fuselage with amenity equipment
DE102017125299A1 (en) 2017-10-27 2019-05-02 Airbus Operations Gmbh Gap cover between cabin monuments, in particular for a passenger cabin of an aircraft

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Publication number Priority date Publication date Assignee Title
US4067155A (en) * 1975-08-28 1978-01-10 Grefco, Inc. Sealing system
US5014934A (en) * 1989-06-30 1991-05-14 The Boeing Company Removable seal for discontinuities in aircraft skin
US5065960A (en) * 1990-02-05 1991-11-19 Northrop Corporation Gap filler for advanced aircraft to reduce radar detectability
DE9406302U1 (en) * 1994-04-18 1995-05-18 Geta Gmbh Trim part for vehicles or airplanes
GB2287517A (en) * 1994-03-14 1995-09-20 Kenneth Barry Wilson Panel assembly system
US5695154A (en) * 1995-08-21 1997-12-09 Northrop Grumman Corporation Gap filler device
DE19709374A1 (en) * 1997-03-07 1998-09-17 Daimler Benz Aerospace Airbus Aircraft cabin ceiling section mounting
US20040021039A1 (en) * 2002-08-01 2004-02-05 Jones Gary E. Snap-on sidewall assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4067155A (en) * 1975-08-28 1978-01-10 Grefco, Inc. Sealing system
US5014934A (en) * 1989-06-30 1991-05-14 The Boeing Company Removable seal for discontinuities in aircraft skin
US5065960A (en) * 1990-02-05 1991-11-19 Northrop Corporation Gap filler for advanced aircraft to reduce radar detectability
GB2287517A (en) * 1994-03-14 1995-09-20 Kenneth Barry Wilson Panel assembly system
DE9406302U1 (en) * 1994-04-18 1995-05-18 Geta Gmbh Trim part for vehicles or airplanes
US5695154A (en) * 1995-08-21 1997-12-09 Northrop Grumman Corporation Gap filler device
DE19709374A1 (en) * 1997-03-07 1998-09-17 Daimler Benz Aerospace Airbus Aircraft cabin ceiling section mounting
US20040021039A1 (en) * 2002-08-01 2004-02-05 Jones Gary E. Snap-on sidewall assembly

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2602188A2 (en) 2011-12-09 2013-06-12 Airbus Operations GmbH Covering device and aircraft area comprising covering device
DE102011120762A1 (en) 2011-12-09 2013-06-13 Airbus Operations Gmbh Cover device and aircraft area with cover device

Also Published As

Publication number Publication date
DE102004049893A1 (en) 2006-04-27
DE502005010646D1 (en) 2011-01-20
AT490908T (en) 2010-12-15

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