Patent Publication Number: US-2013240163-A1

Title: Aircraft door frame lining for visually covering a door area in an aircraft

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
     This is a continuation of International Application No. PCT/EP2011/069812, filed Nov. 10, 2011, which application claims priority to U.S. Provisional Patent Application No. 61/413,112, filed on Nov. 12, 2010 and to German Patent Application No. 10 2010 051 217.6, filed on Nov. 12, 2010, which are incorporated herein by reference in their entirety. 
    
    
     TECHNICAL FIELD 
     The technical field relates to aircraft interior architecture. In particular, the technical field relates to an aircraft door frame lining for visually covering a door area in an aircraft, to an aircraft interior architecture, to a method, and to an aircraft. 
     BACKGROUND 
     The visual improvement of aircraft interior architecture increasingly forms part of the requirement of airlines, with which requirements aircraft manufacturers are confronted. Apart from, for example, maximizing the overhead space in passenger areas, visually pleasing surfaces and surface flows in the interior of an aircraft form parts of the aspects of an interior architecture, which aspects may ensure a special sense of well-being in passengers. 
     In particular on long-haul flights, where passengers have sleep phases or rest phases, a reduction in the brightness of light sources in the aircraft interior may be desirable. Thus, increasingly, attention is paid to indirect illumination in the aircraft interior architecture and to darkening or shielding bright light sources in the aircraft interior. 
     In addition, other objects, desirable features and characteristics will become apparent from the subsequent summary and detailed description, and the appended claims, taken in conjunction with the accompanying drawings and this background. 
     SUMMARY 
     Accordingly, the present disclosure provides visual enhancement of an aircraft interior architecture. 
     The exemplary embodiments described equally relate to the aircraft door frame lining, the aircraft interior architecture, the method and the aircraft. In other words, characteristics which below are described with reference to, for example, the aircraft door frame lining can also be implemented in the aircraft interior architecture and in the aircraft and vice versa. 
     According to an exemplary embodiment of the present disclosure, an aircraft door frame lining for visually covering a door area in an aircraft is stated. The aircraft door frame lining comprises an upper door frame lining, wherein the upper door frame lining comprises a first component. The first component is designed for attachment above an aircraft door, and the first component is designed for visually covering the door area. 
     The aircraft door frame lining is designed for lining a door within the fuselage of the aircraft. 
     In other words, the door to be covered is situated in the fuselage of the aircraft rather than in the interior of the aircraft. 
     In this arrangement the aircraft door frame lining is designed as a permanently installed part of the interior architecture of the aircraft. In other words, the aircraft door frame lining forms an integral part of the interior architecture. 
     In other words, an aircraft interior architecture is stated that comprises a permanently installed upper door frame lining with a first component. This first component is affixed above an aircraft door, and the first component is designed for visually covering the door area. 
     For example, the first component may comprise a length such that a width of the door area (or even a longer distance) can be spanned. In this arrangement visual covering can either take place by means of the first component itself, or by means of a medium, for example by means of a curtain or a roller blind that is additionally affixed to the first component. 
     The aircraft door frame lining is designed in such a manner that by means of a curtain or a roller blind the door area of the aircraft may be completely covered. 
     Thus, an aircraft interior architecture may be provided by means of which during the flight the door entrance area can be covered with the use of, for example, a curtain, and thus the door entrance area is visually enhanced and an inviting ambiance may be created. 
     Advantageously, the present disclosure may be simple to handle because the aircraft door frame lining forms a permanently installed part of the aircraft interior architecture, and thus no separate design space is required. 
     Hereinafter, the term “aircraft door frame lining” may be used synonymously with the term “door frame lining”. 
     According to another exemplary embodiment of the present disclosure, the first component is designed in such a manner that attachment of the first component above the door to a primary structure of the aircraft becomes possible. 
     In other words, the length of the first component is such that attachment points of the first component can be affixed to the primary structure of the aircraft. 
     In other words, this exemplary embodiment of the present disclosure differs from the merely temporary, detachable affixation of a visual barrier on the aircraft door surface in that the present disclosure states a permanently installed interior architecture with the aircraft door frame lining, wherein the aforesaid is attached to the primary structure of the aircraft. Thus, the door frame lining may carry greater loads because load introduction, for example of the weight of a roller blind above the aircraft door frame lining, takes place up to the primary structure of the aircraft. 
     Affixation of the aircraft door frame lining to the primary structure of the aircraft can take place by means of the principle of “lining-bracket-primary structure”. In this arrangement the door frame lining is screwed with the use of holders (brackets) to the primary structure, in most cases by means of screws. However, other fasteners are also possible. In this manner a high strength of the door frame lining may be obtained because it is connected to the primary structure. 
     According to another exemplary embodiment of the present disclosure, the first component is a curtain rail. 
     As is, for example, shown in  FIGS. 1 to 4 , the curtain rail is connected above a door area to the aircraft primary structure. By means of a curtain that is present in a separately provided stowage compartment of the aircraft door frame lining, at any desired point in time the door area of the aircraft can be visually covered. Apart from simple handling, this provides a stowage space for the curtain, which is in this case not in the way of the aircraft crew. This corresponds to a visually pleasing solution, and no additional stowage space, for example in the hatrack, may be required. 
     According to an exemplary embodiment of the present disclosure, the aircraft door frame lining further comprises a lateral door frame lining, wherein the lateral door frame lining comprises a first volume for the stowage of a curtain. 
     In this arrangement the lateral door frame lining as well as the upper door frame lining forms an integral part of the interior architecture of the aircraft interior. 
     According to an exemplary embodiment the aircraft door frame lining is made from a plastic material. 
     Furthermore, the lateral door frame lining can also be referred to as the “lateral lining”. For example, the first volume can be provided by means of a flap behind which there is an intermediate area between the interior architecture and the aircraft primary structure. If it is not desirable to make it possible to see the aircraft primary structure, for example the frame elements for opening the flaps, according to an exemplary embodiment of the present disclosure the design as an interior-lined compartment for providing the first volume is provided. 
     According to an exemplary embodiment of the present disclosure, the lateral door frame lining is designed as a re-closable compartment for providing the first volume. 
     In this arrangement, on the compartment a lock can be in place for the purpose of securing the compartment. By way of an articulated connection the compartment can comprise a rotatably held door behind which, for example, the curtain can be stowed. This can further increase the space saving achieved by means of an exemplary embodiment of the present disclosure. 
     According to this exemplary embodiment of the present disclosure, horizontal stowage of a curtain on the curtain rail within the re-closable compartment may be made possible. If desired, likewise, a curtain can be provided, wherein by means of a horizontal movement of the curtain complete stowage in the lateral door frame lining can take place. 
     According to an exemplary embodiment of the present disclosure, the lateral door frame lining comprises an opening. Furthermore, the curtain rail extends through the opening, and consequently, for attachment, the curtain rail is to be connected to the primary structure of the aircraft. 
     In other words, the lateral door frame lining comprises a region in which the curtain rod or curtain rail extends through the lateral door frame lining. In this arrangement the lateral door frame lining is arranged in such a manner that when the curtain rail is passed through it, said curtain rail can be made to connect the aircraft primary structure for attachment. 
     According to an exemplary embodiment of the present disclosure, the curtain rail comprises a slider for accommodating a curtain. Furthermore, the curtain rail is attached to the aircraft door frame lining in such a manner that the slider projects in horizontal direction from the curtain rail. 
     In other words, the slider is arranged between the rail and the interior or passenger compartment of the aircraft. Said slider thus does not point from the curtain rail to the floor of the aircraft, but instead it points horizontally and laterally forwards. The connecting region through which the curtain is affixed to the slider is not situated between the rail and the floor, but instead frontally or horizontally in front of the rail. 
     In other words, the curtain is guided in front of the curtain rail. In contrast to conventional curtain guides there is no gap between the curtain rail and the curtain. 
     According to an exemplary embodiment the curtain rail is completely covered by the installed curtain. This may make a further contribution to providing a visually pleasing solution for covering the door entrance area. 
     According to an exemplary embodiment of the present disclosure, the aircraft door frame lining comprises a curtain, wherein the curtain rail and the curtain are interconnected in such a manner that in its installed state the curtain covers the curtain rail. 
     According to an exemplary embodiment of the present disclosure, the curtain comprises a reinforced connecting area. 
     In this arrangement the connecting area can be designed for affixation of the curtain to the slider. 
     By means of this exemplary embodiment, due to the reinforced connecting area in the curtain, the latter can be guided horizontally in front of the curtain rail so that said curtain completely covers the curtain rail. There is thus no visual gap between the curtain and the curtain rail. 
     According to an exemplary embodiment of the present disclosure, the first component of the upper door frame lining is a second volume for the stowage of a roller blind. 
     In other words, the second volume is designed for the stowage of a roller blind. This may make it possible to visually cover the door area within the aircraft interior, for example by pulling the roller blind out of the second volume. In other words, vertical stowage of the roller blind is made possible by means of the second volume. In vertical direction it is thus possible to pull the roller blind from the second volume above the aircraft door in the direction of the floor. In this case, too, the second volume forms an integral part of the interior architecture of the aircraft. 
     In this and in any other exemplary embodiment the term “roller blind” may relate to any covering device that fulfils the task of providing a visual cover of the door area. 
     For example, the first component can additionally be designed to roll the roller blind on or off by means of a rotation mechanism. 
     According to another exemplary embodiment of the present disclosure, the first component is designed as a compartment within the aircraft door frame lining that is arranged above the aircraft door. 
     According to an exemplary embodiment of the present disclosure, the first component comprises an outlet opening, wherein the outlet opening makes it possible for a roller blind to be reversibly pulled out. 
     According to one exemplary embodiment of the present disclosure, the aircraft door frame lining comprises at least one locking point, wherein the locking point is designed to lock a roller blind. 
     As shown, for example, in  FIG. 7 , in this manner a roller blind that above the aircraft door forms an integral part of the aircraft interior can be permanently attached in the floor area. 
     According to one exemplary embodiment of the present disclosure, the locking point is situated in a floor area of the aircraft door frame lining. 
     According to one exemplary embodiment of the present disclosure, an aircraft interior architecture comprising an aircraft door frame lining according to a preceding or following exemplary embodiment is stated. 
     According to one exemplary embodiment of the present disclosure, an aircraft comprising an aircraft door frame lining according to any one of the preceding or following exemplary embodiments is stated. 
     According to one exemplary embodiment of the present disclosure, a method for visually covering a door area in an aircraft is stated, wherein the method comprises the following: providing an upper door frame lining that forms a permanent part of an aircraft interior architecture, wherein the upper door frame lining is designed for guiding a medium, for example a roller blind or a curtain; positioning the medium along the upper door frame lining, which results in visual covering of the door area in an aircraft. 
     According to one exemplary embodiment of the present disclosure, by means of the aircraft door frame lining a method for visually covering the door area of the aircraft is provided, which method comprises the following: providing a curtain of a lateral door frame lining; positioning the curtain along a curtain rod that forms part of the upper door frame lining, which results in complete visual covering of a door area in an aircraft. 
     According to an exemplary embodiment of the present disclosure, by means of the aircraft door frame lining a method for visually covering the door area of the aircraft is provided, which method comprises the following: providing an upper door frame lining that has been affixed above an aircraft door, wherein the upper door frame lining forms part of an integral permanent aircraft interior architecture; pulling a roller blind in vertical direction from the upper door frame lining, which results in complete visual covering of a door area of an aircraft door. 
     It may be considered to be a fundamental idea of the present disclosure to provide a permanently installed upper door frame lining along which a medium, for example a roller blind or a curtain, can be guided. Furthermore, for guiding along the upper door frame lining this medium is brought into position within the aircraft door frame lining so that, if desired, the curtain or the roller blind can be moved and guided along the door frame lining in such a manner that visual covering of the door area in an aircraft takes place. Since both the upper door frame lining and the roller blind or the curtain form an integral part of the aircraft interior architecture, they need not be dismantled, remounted or stowed at other locations within the aircraft. 
     A person skilled in the art can gather other characteristics and advantages of the disclosure from the following description of exemplary embodiments that refers to the attached drawings, wherein the described exemplary embodiments should not be interpreted in a restrictive sense. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The various embodiments will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and wherein: 
         FIG. 1  to  FIG. 3  show diagrammatic two-dimensional views of an aircraft door frame lining according to an exemplary embodiment of the present disclosure. 
         FIG. 4  shows a diagrammatic two-dimensional view of a curtain rail as part of an aircraft door frame lining according to an exemplary embodiment of the present disclosure. 
         FIG. 5  to  FIG. 7  show diagrammatic two-dimensional views of a door frame lining according to a further exemplary embodiment of the present disclosure. 
         FIG. 8  shows an aircraft comprising a door frame lining according to an exemplary embodiment of the present disclosure. 
         FIG. 9  shows a flow chart of a method according to a further exemplary embodiment of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
     The following detailed description is merely exemplary in nature and is not intended to limit the present disclosure or the application and uses of the present disclosure. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description. 
       FIG. 1  shows an aircraft door frame lining  100  for visually covering a door area  101 A and  101 B in an aircraft. In this arrangement the aircraft door frame lining comprises an upper door frame lining  102  with a first component  103 . In this arrangement the first component is attached above the aircraft door  104  of the aircraft interior architecture shown. Furthermore, the first component  103  is designed for visually covering the door area. In the exemplary embodiment shown in this figure the first component is designed as a curtain rail  105 . Furthermore, in  FIG. 1  a lateral door frame lining  106  is shown that provides a first volume  107  for the stowage of a curtain. The lateral door frame lining is designed as a re-closable compartment  108  for providing the first volume. 
     The lateral door frame lining further comprises an opening (not shown), wherein the curtain rail extends through the opening, which results in the curtain rail being able to be connected to the primary structure of the aircraft (not shown) for attachment. 
     In other words, the curtain rail is designed in such a manner that attachment of the curtain rail above the aircraft door  104  to the primary structure of the aircraft can take place. This can ensure that the first component bears the weight force of, for example, a roller blind or a curtain and introduces this load into the primary structure. In other words, the first component is designed for introducing the load of a roller blind or of a curtain into the primary structure of the aircraft. In this arrangement in  FIG. 1  the aircraft door frame lining is shown in a first state, in which the curtain (not drawn in the figure) is still accommodated in the lateral door frame lining  106  that extends perpendicularly to the upper door frame lining. 
       FIG. 2  shows the exemplary embodiment of  FIG. 1  in a second state, in which the curtain  200  is visible. In this arrangement the door  201  of the compartment  108  in which the curtain can be accommodated for stowage is shown in its open position. In this arrangement the upper area of the compartment  108  shows that the curtain rod  105  extends into the compartment  108  and through an opening (not shown in the drawing) leads behind the compartment to the primary structure. 
       FIG. 3  shows the aircraft door frame lining of  FIGS. 1 and 2  in a further, third, state. In this arrangement the aircraft door frame lining  100  is shown with an upper door frame lining  102  and a lateral door frame lining  106 . The illustration clearly shows that the curtain  200  visually covers the entire door area with the width  101 A and the height  101 B. In this manner it is possible to achieve a visually pleasing design of the aircraft interior architecture. Moreover, according to the exemplary embodiment of  FIGS. 1 and 3  simple handling is ensured because by means of moving the curtain in horizontal direction from a storage compartment integrally integrated in the aircraft interior architecture complete covering is possible. No stowage space, for example in a hatrack, is required for covering the door area. 
       FIG. 4  shows a curtain rail  105  with a slider  400  and a curtain  200  attached thereto, wherein the aforesaid can be integrated in an exemplary embodiment of an aircraft door frame lining according to the present disclosure. As an example, the aircraft fuselage  406  is shown in which there is an aircraft door  104  that can be opened as indicated by the arrow  405 . For visually separating this door area  101 A and  101 B an aircraft door frame lining  100  is provided that is attached to the primary structure of the aircraft (in the illustration as an example represented by the fuselage  406 ). In this arrangement  FIG. 4  shows that the slider  400  is arranged within the curtain rail  105  in such a manner that the curtain  200  extends in front of the curtain rail  105  and is thus located in horizontal direction  401  spaced apart from the curtain rail. In this manner an arrangement can be achieved in which the curtain  200  completely covers the curtain rail  105  from the view of passengers in the passenger area  404 . 
     The curtain shown in the illustration comprises a reinforced connecting area  402  so that affixation, as described above, of the curtain to the slider  400  in front of the curtain rail is made possible. 
       FIG. 5  shows a further exemplary embodiment of the present disclosure, in which an aircraft door frame lining  100  is shown which comprises a second volume  501  for the stowage of a roller blind  600  (see  FIG. 6 ). Also shown is an upper door frame lining  102 , which forms an integral part of the aircraft interior architecture shown. In this arrangement the upper door frame lining comprises a first component  103 , which is attached above the aircraft door. In conjunction with the following  FIGS. 6 and 7  it becomes clear that the first component is designed for visually covering the door area  101 A and  101 B. 
     The second volume shown in the illustration is arranged as a coffer or box above the door and comprises an outlet opening  501  that makes it possible to reversibly pull out the roller blind  600  (see  FIG. 6 ). 
       FIG. 6  shows the aircraft door frame lining  100  of  FIG. 5  in a second state, in which the roller blind  600  has already been pulled out in vertical direction. In this manner continuous covering of the surface of the door area can be achieved as desired. 
       FIG. 7  shows the exemplary embodiment of the aircraft door frame lining  100  of  FIGS. 5 and 6  in a completely closed third state. In this arrangement the roller blind  600 , which is situated in the first component, has been completely pulled out of the outlet opening  501 . Furthermore, the roller blind  600  is affixed at locking points  700  that are situated in a floor area  701  of the aircraft door frame lining. 
       FIG. 8  shows an aircraft  800  according to a further exemplary embodiment of the present disclosure, wherein the aircraft comprises two aircraft door frame linings  100 . 
       FIG. 9  shows a flow chart of a method according to a further exemplary embodiment of the present disclosure. The method comprises providing an upper door frame lining that forms an integral part of an aircraft interior architecture. This is designated S 1 . In this arrangement the upper door frame lining is designed for guiding a medium, for example a roller blind or a curtain. Positioning the medium along the upper door frame lining, which results in visually covering the door area in an aircraft, is designated S 2 . 
     While at least one exemplary embodiment has been presented in the foregoing detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the present disclosure in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the present disclosure as set forth in the appended claims and their legal equivalents.