Patent ID: 12187410

Corresponding reference numerals indicate corresponding parts throughout the several views of the drawings.

DETAILED DESCRIPTION

Example embodiments will now be described more fully with reference to the accompanying drawings.FIGS.1and2respectively show an aircraft10including a fuselage100with a window display12and an associated inner passenger compartment panel11according to the present teachings. The window display12is configured to be placed between an outer window member14of an aircraft passenger compartment16and an inner passenger compartment window18. The window display12is configured to provide textual or graphical information to a passenger within the passenger compartment16. As described below, the display12can be releasably fixed to the inner compartment window18for ease of repair or replacement. The inner passenger compartment panel11can include switches or capacitive sensors (not shown) which allow for the interface by the passenger with the contents of the display12.

The display12includes a transparent (e.g. translucent) display member20(seeFIG.3) for transmitting information to the passenger. This transparent display member20can be an thin film transparent display member such as LCD display or a transparent thin film having associated OLEDs. Additionally, the display member20can be a projection display associated along the frame of the display member The thin film transparent display20has a controllable data transmission circuit22for varying the light transmission through or from the pixels24defined in the thin film transparent display member20(seeFIG.3).

As best seen inFIG.3, the controllable data transmission circuit22has a plurality of associated sensors (26,28,30) which can be used to vary the color or amount of light transmitted through each pixel associated with an image32. Alternatively, changes the amount or color of or amount of light associated with the background34of the display member20can be automated to maximize visibility. Because of differences in altitude and positioning of the sun about the earth, there will be large variations in the amount of backlight passing through the outer window member14at any given time. Because of the changes in environmental conditions, the associated sensor30can be a temperature measuring sensor which will allow the circuit22to change currents to the display member as is needed to maintain visual quality or to protect the thin film display.

Additionally, as the internal cabin lighting may be changed during a flight, the visibility of information transmitted by the display member20for the passenger can be obscured. As such, the circuit22can include a pair of light receiving sensors26,28which determine the amount of light passing through the window assembly and the inner passenger compartment. Both sensors26,28provide a signal indicative of these light values. The controllable data transmission circuit22then will calculate a difference in the amount of light between the outside and inside of the cabin and adjust either the darkness or color of pixels sending transmitting information, or the amount of light transmitted through a background.

In the case of an OLED display, the amount of light transmitted by the OLEDS can be adjusted to adjust current or voltage to the OLED to change the visibility of pixels transmitting information or the temperature of the thin film display. Additionally, the display member20can incorporate capacitive touch sensors which will allow the passenger to interact with the window display12to change the image on the display12. These touch sensors can use the electrodes of the OLEDS to convert the display member into a capacitive touch pad.

Optionally, the thin display member20can include a second layer of LCD or polarizable material (not shown) that can change the overall amount of light transmitted through the inner compartment window18. It is envisioned that the display member20can be used to communicate safety information to the passengers such as a need to remain seated or fasten seat belts. Additional, as shown inFIG.3, information related to the location of the aircraft along a flight path, viewable items in the ground or sky of interest, or movies can be shown.

FIG.4represents an exploded view of the window according to the present teachings. Shown is the associated inner passenger compartment panel11which can be of the form of a wall panel or a window frame. As shown, the window display12is positioned between an outer window member14of an aircraft passenger compartment16and an inner passenger compartment window18. To facilitate repair, the display12can be releasably fixed to the inner compartment window18for ease of access.

FIG.5shows a cross section through an aircraft window with the display member20. The outer window member14and an inner passenger compartment window18can have a curved or flat configuration (i.e. planar or substantially planar cross-sectional shape). The outer surface40of the inner passenger compartment window18is spaced from or offset from the outer window member14and the defined fuselage contour. Disposed on the outer surface40is the display member20which is functionally positioned between the inner and outer window members (18,16). By coupling the display member20to the outer surface40of the inner passenger compartment window18, the display member20can be protected from passenger contact. This additionally allows for a frame42to be used as a support for the display member20and an electrical connector (not shown) for data and power transmission.

Examples of suitable materials for the outer14and inner window panels18can include, but are not limited to, plastic materials (such as acrylic polymers). Such as polyacrylates; polyalkylmethacrylates, such as polymethylmethacrylates, polyethylmethacrylates, polypropylmethacrylates, stretched acrylic, and the like; polyurethanes; polycarbonates; polyalkylterephthalates, such as polyethyleneterephthalate (PET), polypropyleneterephthalates, polybutylene terephthalates, and the like; polysiloxane-containing polymers; or copolymers of any monomers for preparing these, or any mixtures thereof); glass, such as conventional soda-lime-silicate glass (the glass can be annealed, heat treated, or chemically tempered glass); or combinations of any of the above.

The inner window18and outer window14are preferably transparent to visible light. By “transparent” is meant having visible light transmission of greater than 0% up to 100%. Alternatively, one or both of the panels12,18can be translucent. The display member or inner or outer window members (14,18) can include for instance a film which acts a polarizer or light filter which filters out certain incident light frequencies.

FIGS.6-14illustrate another embodiment for providing a display for the aircraft10. Referring toFIGS.1,6-9, and14, as discussed above, the aircraft10includes a fuselage100that surrounds an aircraft interior102. Incorporated into the fuselage100is a sidewall assembly104. The sidewall assembly104includes a sidewall portion106of the fuselage100that includes an inner-facing side108disposed adjacent to the aircraft interior102and an outer-facing side110disposed opposite the inner-facing side108adjacent to the outside of the aircraft10.

Referring toFIGS.6-9and14, in an exemplary embodiment, the sidewall assembly104includes a plurality of windows112and114that are spaced apart and that are partially or fully surrounded by the sidewall portion106. As illustrated, a transparent display panel116is coupled to the sidewall portion106covering the inner-facing side108of the sidewall portion106including the windows112and114. In an exemplary embodiment, the transparent display panel116includes one or more display screens118a-bthat independently display information (e.g., different information) to a passenger(s)120in the aircraft interior102. In an exemplary embodiment, the transparent display panel116is a transparent OLED panel and the display screens118a-bare OLED display screens. In an exemplary embodiment, the transparent display panel116has a relatively large screen size of about 55 to about 90 inches for advantageous viewing.

Referring also toFIG.14, in an exemplary embodiment, a display controller122is in communication with the transparent display panel116to communicate video/audio signals124and126providing corresponding information to the display screens118aand118b. As illustrated, the display controller122may be controlled by the passenger120or other occupant of the aircraft10via a user input device121(e.g., hand-held controller, personal computing device or the like) to direct the display controller122to communicate the video/audio signals124and126to the various display screens118aand118b.

In an exemplary embodiment, the display controller122is in communication with a cabin management system (CMS)128. Among various functions, the CMS128is configured to control various cabin environmental functions such as temperature, lighting, galley services, and in-flight entertainment which includes audio, video, interfaces to personal electronic devices, access to media content storage (audio & video files), satellite TV, and moving map equipment as well as access to long-range satellite communications and internet connectivity. As illustrated, the CMS128is in communication with an avionics system130, an internet gateway132, and an audio-video database134, which contains a plurality of audio-video information and/or a plurality of movies, and provides information to the display controller122corresponding to temperature information, safety information, audio/video information, movies, financial market information, internet accessed information, flight information, and/or viewable items outside the aircraft. Independently, the display controller122may be in direct communication with the audio-video database134to access the audio-video information and/or movies for communication to one or more of the display screens118aand/or118b. In one example, the display controller122accesses the audio/video database134(e.g. directly or through the CMS128) to communicate video/audio signals124to the transparent display panel116for display of a movie (e.g., audio/video information) on the display screen118a, and independently accesses the avionics system130(e.g., through the CMS128) to communicate video/audio signals126for display of flight information on the display screen118b.

In an exemplary embodiment, the user input device121is used to switch the transparent display panel116on and/or off. In one example and as illustratedFIGS.6and14, the transparent display panel116is turned to an “on condition” that enables or otherwise powers the display screens118aand/or118bto display corresponding information as discussed above. In another example and as illustrated inFIGS.7-8, the transparent display panel116is turned to an “off condition” where the transparent display panel116is transparent to allow the inner-facing side108of the sidewall portion106including the windows112and114to be visible through the transparent display panel116to the passenger120. As such, the passenger120can view clearly through the transparent display panel116and the windows112and114to outside the aircraft10when the transparent display panel116is in the “off condition.”

Referring toFIGS.7-14, in an exemplary embodiment, the sidewall assembly104includes a window shade136for each of the windows112and114. The window shade136is disposed between the window112or114and the transparent display panel116. Each of the window shades136are movable between an open position (as illustrated onFIGS.7-9) to allow light to pass between the windows112and114and the transparent display panel116when the transparent display panel116is in the “off condition” and a closed position (as illustrated inFIGS.10and12) to obstruct light from passing between the windows112and114and the transparent display panel116when the transparent display panel116is in the “on condition,” for example to enhance viewing of the display screens118a-b.

To further enhance viewing of the display screens118a-b, in an exemplary embodiment, the sidewall assembly104includes a movable blackout panel138(e.g. black opaque panel) for each of the windows112and114. The movable blackout panel138is disposed between the corresponding window shade136and the transparent display panel116. In an exemplary embodiment, the display controller122is in communication with a blackout control device140that is operable coupled to the movable blackout panels138to move the panels138between a retracted position (as illustrated onFIGS.7-9) that allows light to pass between the windows112and114and the transparent display panel116when the transparent display panel116is in the “off condition” and an extended position (as illustrated inFIGS.10and12) that obstructs light from passing between the windows112and114and the transparent display panel116when the transparent display panel116is in the “on condition.” As such, with the movable blackout panels138and the window shades136in the retracted/open positions, the passenger120can see clearly through the transparent display panel116and the windows112and114to outside of the aircraft10. Likewise, with the movable blackout panels138and the window shades136in the extended/closed positions, enhance viewing of the display screens118a-bto the passenger120is provided because the area behind the transparent display panel116is blacked out by obstructing outside light from passing through the windows112and114into the area behind the display screens118a-b.

In an exemplary embodiment, the blackout control device140is further configured to move the window shades136between the open position and the closed position. In one example, the display controller122communicates command signals to the blackout control device142move the window shades136independently or together with movable blackout panels138between the open/retracted positions and the closed/extended positions.

Referring toFIGS.7-8and10-13, in an exemplary embodiment, the sidewall assembly104includes a transparent covering142that is disposed adjacent to and covers the transparent display panel116. For example, the transparent covering142is a plastic sheet formed of a transparent or amorphous polymeric material, such as, for example polymethylmethacrylate (PMMA), polycarbonate (e.g., Lexan®), or the like.

As illustrated, a ledge144is disposed adjacent to the inner-facing side108of the sidewall portion106extending under the transparent display panel116and the transparent covering142towards the aircraft interior102. In an exemplary embodiment, the ledge144is both a functional and aesthetical trim piece that provides an understructure for supporting the transparent display panel116. Additionally, the transparent display panel116is secured to the sidewall portion106via fasteners146.

The foregoing description of the embodiments has been provided for purposes of illustration and description. It is not intended to be exhaustive or to limit the disclosure. Individual elements or features of a particular embodiment are generally not limited to that particular embodiment, but, where applicable, are interchangeable and can be used in a selected embodiment, even if not specifically shown or described. The same may also be varied in many ways. Such variations are not to be regarded as a departure from the disclosure, and all such modifications are intended to be included within the scope of the disclosure.

Example embodiments are provided so that this disclosure will be thorough, and will fully convey the scope to those who are skilled in the art. Numerous specific details are set forth such as examples of specific components, devices, and methods, to provide a thorough understanding of embodiments of the present disclosure. It will be apparent to those skilled in the art that specific details need not be employed, that example embodiments may be embodied in many different forms and that neither should be construed to limit the scope of the disclosure. In some example embodiments, well-known processes, well-known device structures, and well-known technologies are not described in detail.

The terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting. As used herein, the singular forms “a”, “an” and “the” may be intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms “comprises,” “comprising,” “including,” and “having,” are inclusive and therefore specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring their performance in the particular order discussed or illustrated, unless specifically identified as an order of performance. It is also to be understood that additional or alternative steps may be employed.

When an element or layer is referred to as being “on”, “engaged to”, “connected to” or “coupled to” another element or layer, it may be directly on, engaged, connected or coupled to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as being “directly on,” “directly engaged to”, “directly connected to” or “directly coupled to” another element or layer, there may be no intervening elements or layers present. Other words used to describe the relationship between elements should be interpreted in a like fashion (e.g., “between” versus “directly between,” “adjacent” versus “directly adjacent,” etc.). As used herein, the term “and/or” includes any and all combinations of one or more of the associated listed items.

Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as “first,” “second,” and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.

Spatially relative terms, such as “inner,” “outer,” “beneath”, “below”, “lower”, “above”, “upper” and the like, may be used herein for ease of description to describe one element or feature's relationship to another element(s) or feature(s) as illustrated in the figures. Spatially relative terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as “below” or “beneath” other elements or features would then be oriented “above” the other elements or features. Thus, the example term “below” can encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.