Virtual window for aircraft fuselage

Abstract

To provide a projection based virtual window system for an aircraft.SOLUTION: A projection based virtual window system of an aircraft includes a hull, a transparent lens, a projection system, and a controller. The hull is mounted to an interior wall of a passenger cabin of the aircraft. The hull is positioned so as to cover a hole in the interior wall. The transparent lens is secured between the hull and the interior wall and includes a touch sensing layer embedded within. The projection system displays an image on a projection surface of the hull. The controller receives instructions from the touch sensing layer and is further operable to provide the image to the projection system.SELECTED DRAWING: Figure 3

Description

Technical Field

[0001] The present disclosure generally relates to aircraft windows. More specifically, the present disclosure relates to virtual windows based on projections for the fuselage structure of commercial aircraft.

Background Art

[0002] The spread of composite materials used in the manufacture of aircraft fuselage structures is progressing, and since it is desired that aircraft manufacturing be faster and less expensive, the inherent physical properties of conventional physical windows have become an issue.

[0003] Physical windows occupy holes cut out in the aircraft fuselage structure, enabling the aircraft passengers to visually look outside the aircraft through the windows. Forming holes for windows in the fuselage structure during manufacturing is time-consuming and costly. Furthermore, the holes in the fuselage structure compromise the structural integrity of the fuselage, and thus additional, expensive, time-consuming, and weight-increasing reinforcement materials need to be added. Windows are typically made of transparent materials and are permanently attached to the aircraft fuselage. Physical windows need to be reinforced with additional materials to avoid structural fatigue failure. The weight of each window for an aircraft can vary greatly depending on the size of the window and the type of aircraft, and larger windows on wide-body aircraft are heavier. Since it is customary for each row of seats to be aligned with a window, conventional physical windows cannot accommodate various seat layouts due to their fixed positions.

Summary of the Invention

Problems to be Solved by the Invention

[0004] Therefore, it is desirable to have methods and apparatuses that take into account at least some of the problems described above and other possible problems.

Means for Solving the Problems

[0005] Exemplary examples of the present disclosure provide a virtual window for an aircraft, comprising an inner wall of the aircraft, a hull, a transparent lens, and a projector. The hull is attached to the inner wall of the aircraft. The transparent lens is fixed between the hull and the inner wall. The projector is disposed between the transparent lens and the hull. Further, the projector is configured to display an image on the hull.

[0006] Another exemplary example of the present disclosure provides a projection-type virtual window system for an aircraft, comprising a hull, a transparent lens, a projection system, a projection surface of the hull, and a controller. The hull is attached to the inner wall of the passenger cabin of the aircraft. The hull is disposed to cover a hole in the inner wall. The transparent lens is fixed between the hull and the inner wall. The projection system is configured to display an image on the projection surface of the hull. The controller is operable to provide an image to the projection system.

[0007] A further exemplary example of the present disclosure provides a method for projecting a virtual window of an aircraft. The method includes attaching a virtual window system to the inner wall of the aircraft. The virtual window system is disposed to cover a hole in the inner wall. The virtual window system includes a transparent lens fixed to the hull, a projection system connected to the hull and disposed between the transparent lens and the hull, and a touch sensing layer embedded in the transparent lens. The method further includes another step of providing an image from a controller in the computer system of the aircraft to the projection system. The method further includes projecting an image on the projection surface of the hull, and the image can be viewed through the hole in the inner wall and the transparent lens.

[0008] Features and functions can be achieved independently in various examples of the present disclosure or may be combined in further examples, and further details can be understood with reference to the following description and drawings.

[0009] The characteristics of the exemplary examples and the novel features considered to be are set forth in the appended claims. However, the exemplary examples, as well as their preferred modes of use, further objects and features, will be best understood by reference to the following detailed description of the exemplary examples of the present disclosure when read in conjunction with the accompanying drawings.

Brief Description of the Drawings

[0010]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Figure 9

Figure 10

Modes for Carrying Out the Invention

[0011] The exemplary example recognizes and takes into account one or more different considerations. For example, in the exemplary example, it is recognized and taken into account that during the manufacture of the fuselage structure of an aircraft, it is necessary to cut out an opening in the external skin to accommodate a conventional physical window.

[0012] In an exemplary example, it is recognized and taken into account that in a conventional physical window, due to the opening in the aircraft skin, it is fixed in a predetermined position and thus cannot accommodate an alternative design or seat arrangement in the aircraft cabin.

[0013] In an exemplary example, it is recognized and taken into account that incorporating a conventional window during the manufacture of the aircraft fuselage structure compromises the structural integrity of the fuselage structure, is costly, time-consuming, and requires additional strengthening means to increase the weight of the aircraft.

[0014] Accordingly, the exemplary example provides a projection-type virtual window system. Exemplary examples of the virtual window system can be designed as a plug-and-play unit to replace a conventional window or can be incorporated during initial manufacture. Advantages of the exemplary example include weight reduction of the aircraft due to the absence of a conventional glass window and simplification of manufacture by eliminating cut-out window openings in a composite airframe, particularly due to post-manufacture complexity. An airframe without windows can also improve the fuselage strength, for example, at the wing-body joint, and enable improvements in wing design and wing performance.

[0015] Referring now to the figures, and particularly to FIG. 1, an explanatory view of an aircraft according to an exemplary example is shown. In this exemplary example, the aircraft 100 has wings 102 and 104 attached to a fuselage 106. The aircraft 100 includes an engine 108 attached to the wing 102 and an engine 110 attached to the wing 104.

[0016] The fuselage 106 has a tail section 112. The horizontal stabilizers 114, 116 and the vertical tail stabilizer 118 are attached to the tail section 112 of the fuselage 106.

[0017] Aircraft 100 is an example of an aircraft having a conventional physical window. Window set 120 includes window 122. Window 122 is a conventional physical window. Window 122 is permanently attached to fuselage 106 within an opening formed in fuselage 106. A virtual window based on a projection as disclosed herein may be retrofitted to fuselage 106 in place of window 122, or aircraft 100 including fuselage 106 may be assembled from the start without having an opening cut out in fuselage 106 and instead may be assembled having a plurality of virtual windows based on projections. A fuselage assembled without an opening for a conventional window is more structurally sound, easier and quicker to manufacture, and less expensive to produce.

[0018] As used herein, "~set", when used with respect to items, means one or more items. For example, "window set" refers to one or more windows.

[0019] As used herein, the phrase "at least one of" when used with a list of items means that one or more different combinations of the listed items may be used and only one of each item in the list may be required. In other words, "at least one of" means that any combination of items and the number of items may be used from the list, but not all of the items in the list are necessarily required. An item can be a particular object, thing, or category.

[0020] For example, without limitation, "at least one of item A, item B, or item C" may include item A, item A and item B, or item B. This example may also include item A, item B, and item C, or item B and item C. Of course, any combination of these items can exist. In some exemplary examples, "at least one of" can be, for example, but not limited to, two item As, one item B, and ten item Cs, four item Bs and seven item Cs, or other suitable combinations.

[0021] The figure of the aircraft 100 in FIG. 1 does not imply physical or structural limitations on the embodiments that can implement the exemplary examples. For example, although the aircraft 100 is a commercial aircraft, the aircraft 100 may be a military aircraft, a rotary-wing aircraft, a helicopter, a drone, or any other suitable aircraft.

[0022] Although the exemplary examples are described with respect to aircraft, the exemplary examples may be applied to other types of platforms. The platform may be, for example, a moving platform, a stationary platform, a terrestrial structure, an underwater structure, or a space structure. More specifically, the platform may be an aircraft, a watercraft, a tank, a troop carrier, a train, a spacecraft, a space station, a satellite, a submarine, an automobile, a power plant, a bridge, a dam, a house, a manufacturing facility, a building, a tool, a mechanical structure, or any other suitable platform or structure where the installation of a projection-based virtual window is desirable.

[0023] Referring now to FIG. 2, a block diagram of an aircraft manufacturing environment according to an exemplary example is shown. The aircraft manufacturing environment 200 includes a projection-type virtual window system 202 and an aircraft 204.

[0024] In this exemplary example, the aircraft 204 includes a fuselage structure 206. The fuselage structure 206 has a skin 208. The skin 208 has no openings that were conventionally cut out and dimensioned for installing conventional windows. The fuselage structure 206 defines a passenger cabin 210. The passenger cabin 210 is the area of the aircraft 204 where passengers sit in multiple rows of seats during flight of the aircraft 204. The passenger cabin 210 includes an inner wall 212. The inner wall includes holes 262. The inner wall 212 is exposed to passengers sitting in the passenger cabin 210. The virtual window connected to the inner wall 212 is visible to passengers sitting in the passenger cabin 210 through the holes 262. Passengers sitting in the passenger cabin 210 can interact with the virtual window connected to the inner wall 212 through the holes 262. The inner wall 212 is spaced apart from the skin 208. A structural framework including, but not limited to, frames, beams, and stringers exists in the space between the inner wall 212 and the skin 208.

[0025] In this exemplary example, the projection-type virtual window system 202 includes a virtual window 220 and a computer system 222.

[0026] In this exemplary example, the virtual window 220 includes a housing 224, a transparent lens 226, a base 228, a frame 230, and a projection system 232.

[0027] The housing 224 is generally of a hollow shell shape. The housing defines a volume having at least one open side. A flange 234 is disposed at the periphery of the open side. The flange 234 defines a periphery having a contour 236. The flange 234 includes an inset portion 238. The flange 234 is shaped and dimensioned to engage with the frame 230. The frame 230 defines a contour 240. The contour 240 coincides with the contour 236.

[0028] The housing 224 includes a projection surface 242. The projection surface 242 is disposed on the inner surface of the housing 224. The projection surface 242 is on the inner surface opposite to the open side of the volume defined by the housing 224. The projection surface 242 may be simply the inner surface of the housing 224, a layer of projection paint applied to the inner surface of the housing 224, a plurality of optical layers coated on a flexible thin substrate adhered to the inner surface of the housing 224, etc. As a non-limiting example, projection paints / coatings from Smarter Surfaces are available. Further, although not limited to this, as an example, an ultra-thin flexible Fresnel screen manufactured by Formovie is available. The characteristics of the projection surface 242 enhance the image quality, brightness, contrast, etc. of the projection-type virtual window system 202.

[0029] The housing 224 may include louvers 244. The louvers 244 provide a path for air flow between the internal space and the external space of the housing 224. The air flow path provided by the louvers 244 may be required to dissipate any unwanted heat generated by the projector of the projection-type virtual window system 202.

[0030] The transparent lens 226 is connected to the base 228. The base 228 holds the transparent lens 226 in a hole 258 formed in the base 228. The hole 258 is dimensioned to securely hold the transparent lens 226 relative to the base 228. The base 228 holds the transparent lens 226 relative to the outer shell 224 when the base 228 is connected to the outer shell 224 at the inset portion 238. The transparent lens 226 includes a touch sensing layer 246. The touch sensing layer 246 may be embedded within the transparent lens 226. The touch sensing layer 246 may be a laminate layer adhered to the transparent lens 226. Examples of the touch sensing layer 246 or touch screen, such as duraTOUCH (registered trademark) made by UICO (registered trademark), are widely available. The transparent lens 226 may include an electrochromic layer integrated with or adhered to the transparent lens 226. The electrochromic layer can create a window blind effect, in which case, when the virtual window 220 is retrofitted to a fuselage structure that already has an opening for a conventional window, the electrochromic layer can shield the interior of the aircraft from the sun when the system is off. The outer shell 224 or the transparent lens 226 or both may include one or more small pinholes that operate to relieve the pressure difference between the interior of the aircraft and the space where the virtual window 220 is installed during operation of the aircraft.

[0031] The projection system 232 includes a projector set 250. The projector set 250 includes at least one projector, and may include a first projector 252 and a second projector 254. The first projector 252 projects an image 253 onto a projection surface 242. The second projector 254 projects an image 255 onto the projection surface 242. The image 253 and the image 255 may be the same image. The image 253 and the image 255 may be different images that are superimposed on each other, or may be different images that are projected side by side on the projection surface 242. When the image 253 and the image 255 are the same image, redundancy can be provided for one with respect to the other when a failure occurs. When there are multiple projectors, a cable 256 connects the first projector 252 to the second projector 254. The cable 256 can also provide a communication link between the projector and the controller 260. The image 253 and / or the image 255 can show a view from an external camera to reproduce a view of a conventional window for passengers in the passenger compartment. The first projector 252 and the second projector 254 may be regarded as "micro" or "ultra-short focus" projectors. The first projector 252 and the second projector 254 may have a projection ratio (distance / width) of about 0.250 to about 0.270. Because the projection distance between each projector and the projection surface of the virtual window 220 is limited, an ultra-short focus optical engine projector is preferred. As a non-limiting example, projectors equipped with an ultra-short focus optical engine manufactured by Ongine are available.

[0032] In this exemplary example, the operation of the projection-type virtual window system 202 can be controlled by a controller 260 within a computer system 222.

[0033] The controller 260 can be implemented in software, hardware, firmware, or a combination thereof. When software is used, the operations performed by the controller 260 can be implemented by program code configured to operate on hardware such as a processor unit. When firmware is used, the operations performed by the controller 260 can be implemented by program code and data and stored in a persistent memory that operates on the processor unit. When hardware is employed, the hardware can include a circuit that operates to execute the operations in the controller 260.

[0034] In an exemplary example, the hardware may take a form selected from at least one of a circuit system, an integrated circuit, an application specific integrated circuit (ASIC), a programmable logic device, or other suitable types of hardware configured to perform multiple operations. When using a programmable logic device, the device can be configured to perform multiple operations. The device may be reconfigured later or permanently configured to perform multiple operations. Examples of programmable logic devices include, for example, programmable logic arrays, programmable array logic, field programmable logic arrays, field programmable gate arrays, and other suitable hardware devices. Further, the process can be implemented in organic components integrated with inorganic components and can be composed of only organic components excluding humans. For example, the process may be implemented as a circuit of an organic semiconductor.

[0035] The computer system 222 is a physical hardware system and includes one or more data processing systems. When there are multiple data processing systems in the computer system 222, those data processing systems communicate with each other using a communication medium. The communication medium can be a network. The data processing system can be selected from at least one of a computer, a server computer, a tablet computer, or other suitable data processing systems.

[0036] In an exemplary example, the controller 260 can control the projection system 232 to project the image 253 and / or the image 255 onto the projection surface 242. Further, the controller 260 can receive an input from the touch sensing layer 246 and change the image 253 or the image 255. A passenger interacting with the touch sensing layer 246 generates a signal that is transmitted from the touch sensing layer 246 and received by the computer system 222. The controller 260 controls the image projected by the projection system 232 based on inputs received from the passenger as well as messages and images programmed into the computer system 222. The controller 260 operates to provide an image to the projection system 232.

[0037] In use, the frame 230 is connected to the inner wall 212 of the aircraft 204 and surrounds the hole 262. A projection system 232 including the first projector 252 and / or the second projector 254 is connected to the outer shell 224. The projection system 232 communicates with the computer system 222 and the controller 260. The communication between the projection system 232 and the computer system 222 may be wired or wireless. The transparent lens 226 is connected to the base 228. The base 228 is connected to the outer shell 224 at the inset portion 238. The outer shell 224 is connected to the frame 230 such that the hole 258 in the base 228 and the transparent lens 226 mounted therein are aligned with the hole 262 in the inner wall 212.

[0038] The virtual window 220 including the outer shell 224, the base 228, the transparent lens 226, and the projection system 232 is assembled as a plug-and-play unit that can be removably attached to the inner wall of the aircraft cabin using the frame 230. The virtual window 220 may be connected to the frame 230 using conventional fasteners, or the virtual window 220 may be connected to the frame 230 using a friction fit having a snap-on structure.

[0039] As used herein, when a first component is "connected to" or "coupled to" or "associated with" a second component, it means that the first component can be directly or indirectly connected to the second component. The connection is a physical coupling. In other words, there may be another component between the first component and the second component. If there is one or more other components between two components, the first component is considered to be indirectly connected to the second component. When the first component is directly connected to the second component, there is no other component between the two components.

[0040] For example, the first component may be considered to be physically connected to the second component by at least one of being fixed to the second component, being joined to the second component, being attached to the second component, being welded to the second component, being fastened to the second component, or being connected to the second component in any other suitable way. The first component may also be connected to the second component using a third component. The first component may be considered to be physically connected to the second component by being formed as part of the second component, an extension of the second component, or both.

[0041] Referring now to FIGS. 3-7, there are shown diagrams of a projection type virtual window system according to an exemplary example. In the exemplary example, the same reference numerals may be used in multiple diagrams. This reuse of reference numerals in different diagrams represents the same element in different diagrams. The components shown in FIGS. 3-7 are physical implementation examples of the virtual window 220 shown in block form in FIG. 2.

[0042] As shown, the virtual window 300 includes an outer shell 302, a base 304, a transparent lens 306, a projection system 308, and a frame 310.

[0043] Shell 302 defines a volume having at least one open side 312. A flange 314 is disposed about the periphery of open side 312. Flange 314 includes an inset portion 316. Flange 314 is shaped and dimensioned to engage a frame 310 attached to an interior wall 320.

[0044] Shell 302 includes projection surface 322. Projection surface 322 is disposed on the inner surface of shell 302. Projection surface 322 faces open side 312. Shell 302 includes louvers 324. Louvers 324 provide a path for airflow between the interior of shell 302 and a space external to shell 302.

[0045] Transparent lens 306 is connected to base 304. Base 304 securely holds transparent lens 306 in hole 326 formed in base 304. Transparent lens 306 includes a touch-sensitive layer. The touch-sensitive layer may be embedded within transparent lens 306 or may be a laminate layer adhered to transparent lens 306. Transparent lens 306 may also include an electrochromic layer.

[0046] Projection system 308 includes first projector 330 and second projector 331. First projector 330 projects image 334 onto projection surface 322. Second projector 331 may project image 334 or a different image onto projection surface 322. The images projected by each projector cooperate to provide images and messages to passengers in the cabin. Cable 332 connects first projector 330 to second projector 331.

[0047] Frame 310 is connected to inner wall 320 and surrounds hole 340 formed in inner wall 320. A projection system 308 including a first projector 330 and a second projector 331 is connected to outer shell 302. Transparent lens 306 is connected to base 304 at hole 326 formed in base 304. Base 304 is connected to outer shell 302 at inset portion 316. Outer shell 302 is connected to frame 310 such that hole 326 in base 304 and transparent lens 306 mounted therein are aligned with hole 340 in inner wall 320. Hole 262 is aligned with transparent lens 306 such that an image 334 can be viewed from an aircraft cabin through hole 262 and transparent lens 306.

[0048] The virtual window 300 including outer shell 302, base 304, transparent lens 306 and projection system 308 is assembled as a plug-and-play unit that can be removably attached to inner wall 320 at a desired position using frame 310. The virtual window 300 may be connected to frame 310 by conventional fasteners or the virtual window 300 may be connected to frame 310 by friction fitting.

[0049] Referring now to FIG. 8, a flowchart of a process 800 for projecting a virtual window according to an exemplary example is shown. The method shown in FIG. 8 may be used with the projection-type virtual window system 202 shown in FIGS. 1-7.

[0050] The process starts by attaching a virtual window system to the inner wall of an aircraft (step 802). The virtual window system is arranged to cover a hole in the inner wall. The virtual window system includes a transparent lens fixed to an outer shell, a projection system connected to the outer shell and arranged between the transparent lens and the outer shell, and a touch sensing layer embedded in the transparent lens. The process provides an image from a controller within the aircraft's computer system to the projection system (step 804). The process then projects the image onto a projection surface of the outer shell (step 806). The image can be seen through the hole in the inner wall and through the transparent lens. The process may receive an input from the virtual window to determine the image to be projected (step 808). In step 810, the process may project both a first image and a second image onto the projection surface of the outer shell. The process may change the image to be projected based on an input received from the touch sensing layer of the transparent lens (step 812). A passenger in the passenger cabin can interact with the touch sensing layer of the transparent lens, input to the virtual window system, and determine which image should be projected.

[0051] In some alternative embodiments of the exemplary examples, one or more of the functions described in the blocks may be performed in an order different from the order shown in the figures. For example, in some cases, two blocks shown consecutively may be performed substantially simultaneously, or the two blocks may be performed in the reverse order depending on the related functions. Also, in addition to the blocks shown in the flowchart or block diagram, other blocks may be added.

[0052] Exemplary embodiments of the present disclosure can be further described in connection with the aircraft manufacturing and maintenance inspection method 900 shown in FIG. 9 and the aircraft 1000 shown in FIG. 10. Referring first to FIG. 9, a block diagram of an aircraft manufacturing and maintenance inspection method according to an exemplary embodiment is shown. In the pre-manufacturing stage, the aircraft manufacturing and maintenance inspection method 900 may include the specifications and design 902 of the aircraft 1000 of FIG. 10 and the material procurement 904.

[0053] During manufacturing, the components and subassemblies of the aircraft 1000 in FIG. 10 are manufactured 906, and system integration 908 is performed. Thereafter, the aircraft 1000 in FIG. 10 can be made airworthy 912 through certification and transportation 910. During airworthiness 912 by the customer, the aircraft 1000 in FIG. 10 is scheduled for periodic maintenance and inspection 914, which may include modifications, reconfigurations, repairs, and other servicing, maintenance checks, or inspections.

[0054] The device of the present disclosure may be installed on the aircraft during the manufacture of components and subassemblies 906. Additionally, the device of the present disclosure may be retrofitted to the aircraft 1000 in FIG. 10 during periodic maintenance and inspection 914 as part of a modification, reconfiguration, or repair of the aircraft 1000 in FIG. 10.

[0055] Each of the processes of the aircraft manufacturing and inspection method 900 may be performed or implemented by a system integrator, third party, operator, or some combination thereof. In these examples, the operator may be the customer. For the purposes of this description, a system integrator may include, but is not limited to, any number of aircraft manufacturers and subcontractors of major systems, a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers, and the operator may be an airline, leasing company, military organization, airworthiness service organization, etc.

[0056] Referring now to FIG. 10, a block diagram of an aircraft in which an exemplary embodiment can be implemented is shown. In this example, the aircraft 1000 may include a fuselage 1002 manufactured by the aircraft manufacturing and inspection method 900 of FIG. 9 and having a plurality of systems 1004 and an interior 1006. Examples of the systems 1004 may include one or more of a propulsion system 1008, an electrical system 1010, a hydraulic system 1012, and an environmental system 1014. Any number of other systems may be included. Although an example in aerospace is shown, various exemplary embodiments may be applied to other industries such as the automotive industry.

[0057] The devices and methods embodied herein can be employed in at least one stage of the aircraft manufacturing and maintenance inspection method 900 of FIG. 9. In one exemplary example, the components or sub-assemblies fabricated in the manufacture 906 of the components and sub-assemblies of FIG. 9 may be assembled or fabricated in a manner similar to the components or sub-assemblies fabricated when the aircraft 1000 is in the in-flight state 912 of FIG. 9. As yet another example, one or more device embodiments, method embodiments, or combinations thereof may be utilized in manufacturing stages such as the manufacture 906 of the components and sub-assemblies of FIG. 9 and the system integration 908. One or more device embodiments, method embodiments, or combinations thereof may be utilized when the aircraft 1000 is in the in-flight state 912, during the servicing and maintenance inspection 914 of FIG. 9, or both. The use of several different exemplary embodiments can significantly facilitate the assembly of the aircraft 1000, significantly reduce the cost of the aircraft 1000, or both significantly facilitate the assembly of the aircraft 1000 and significantly reduce the cost of the aircraft 1000.

[0058] The disclosed virtual window system is designed to replace physical windows with digital feature configurations. The disclosed virtual window system obviates the need for heavy and costly physical windows. Physical windows need to be reinforced with more materials to avoid structural fatigue failure. The disclosed virtual window system provides a digital display for enhancing the passenger experience. In-flight information can be shared with passengers via the display. The disclosed virtual window system is not limited to pre-determined fixed positions by cutouts within the fuselage structure and can thus accommodate different seat layouts. The disclosed system is infinitely variable.

[0059] The disclosed virtual window system provides a weight reduction of approximately 70% per window. The disclosed virtual window system reduces the manufacturing time and labor of the fuselage. The disclosed virtual window system is a plug-and-play unit that enables various cabin configurations.

[0060] The descriptions of the various illustrative examples are presented for purposes of illustration and description, and are not intended to be exhaustive or to limit the examples to the forms disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different illustrative examples may provide different features compared to other desired examples. One or more of the selected examples are selected and described in order to best explain the principles of the examples, the practical application, and to enable other ordinary skill in the art to understand the disclosure of the various examples with various modifications that are suitable for the particular use contemplated.

Explanation of Signs

[0061] 100 Aircraft, 102 Wing, 104 Wing, 106 Fuselage, 108 Engine, 110 Engine, 112 Tail, 114 Horizontal Stabilizer, 116 Horizontal Stabilizer, 118 Vertical Tail Stabilizer, 120 Window Set, 122 Window, 200 Aircraft Manufacturing Environment, 202 Virtual Window System, 204 Aircraft, 206 Fuselage Structure, 208 Skin, 210 Passenger Compartment, 212 Inner Wall, 220 Virtual Window, 222 Computer System, 224 Outer Shell, 226 Transparent Lens, 228 Base, 230 Frame, 232 Projection System, 234 Flange, 236 Contour, 238 Inset Portion, 240 Contour, 242 Projection Surface, 244 Louver, 246 Touch Sensing Layer, 250 Projector Set, 252 First Projector, 253 Image, 254 Second Projector, 255 Image, 256 Cable, 258 Hole Portion, 260 Controller, 262 Hole Portion, 300 Virtual Window, 302 Outer Shell, 304 Base, 306 Transparent Lens, 308 Projection System, 310 Frame, 312 Open Side, 314 Flange, 316 Inset Portion, 320 Inner Wall, 322 Projection Surface, 324 Louver, 326 Hole Portion, 330 First Projector, 331 Second Projector, 332 Cable, 334 Image, 340 Hole Portion, 800 Process, 802 Step, 804 Step, 806 Step, 808 Step, 810 Step, 812 Step, 900 Manufacturing and Maintenance Inspection Method, 902 Specifications and Design, 904 Material Procurement, 906 Manufacturing of Components and Sub-Assemblies, 908 System Integration, 910 Certification and Transportation, 912 In Flight, 914 Maintenance and Inspection, 1000 Aircraft, 1002 Airframe, 1004 System, 1006 Interior, 1008 Propulsion System, 1010 Electrical System, 1012 Hydraulic System, 1014 Environmental System

Claims

1. A virtual window (220) for an aircraft (204), an inner wall (212) of the aircraft (204), an outer shell (224) attached to the inner wall (212), a transparent lens (226) fixed between the outer shell (224) and the inner wall (212), a projector (252) disposed between the transparent lens (226) and the outer shell (224) and displaying an image (253) on the outer shell (224), A virtual window comprising:

2. The virtual window according to claim 1, further comprising a touch sensing layer (246) embedded in the transparent lens (226), the touch sensing layer (246) being operable from inside the aircraft (204).

3. The virtual window according to claim 1, further comprising a controller (260) in a computer system (222) of the aircraft (204), the controller (260) operating to provide the image (253) to the projector (252).

4. The inner wall (212) comprises a hole (262) aligned with the transparent lens (226), whereby the image (253) is visible from inside the aircraft (204) through the hole (262) and the transparent lens (226). The virtual window according to claim 1.

5. The virtual window according to claim 1, further comprising a frame (230) connected to the inner wall (212), the frame (230) being disposed between the inner wall (212) and the outer shell (224).

6. The virtual window according to claim 5, wherein the outer shell (224) is connected to the frame (230).

7. The virtual window according to claim 1, further comprising a base (228) fixed between the outer shell (224) and the inner wall (212), the base (228) being connected to the transparent lens (226).

8. The projector (252) is a first projector (252) projecting a first image (253) on the outer shell (224), and the virtual window (220) further comprises a second projector (254) projecting a second image (255) on the outer shell (224). The virtual window according to claim 1.

9. The virtual window according to claim 8, wherein the first image (253) is different from the second image (255).

10. The outer shell (224), the transparent lens (226), and the projector (252) are assembled as a plug-and-play unit, and the plug-and-play unit is disposed between the inner wall (212) of the aircraft (204) and the outer skin (208) of the aircraft (204). The virtual window according to claim 1.

11. A projection-type virtual window system (202) for an aircraft (204), An outer shell (224) attached to the inner wall (212) of the passenger compartment (210) of the aircraft (204), the outer shell (224) being disposed to cover the hole (262) in the inner wall (212); A transparent lens (226) fixed between the outer shell (224) and the inner wall (212); A projection system (232) for displaying an image (253) on a projection surface (242) of the outer shell (224); A controller (260) operable to provide the image (253) to the projection system (232); A virtual window system comprising:

12. Further comprising a touch sensing layer (246) embedded in the transparent lens (226), the touch sensing layer (246) being operable from the passenger compartment (210) of the aircraft (204) and communicating with the controller (260). The virtual window system according to claim 11.

13. The hole (262) is aligned with the transparent lens (226) such that the image (253) can be viewed from the passenger compartment (210) of the aircraft (204) through the hole (262) and the transparent lens (226). The virtual window system according to claim 11.

14. Further comprising a frame (230) connected to the inner wall (212), the outer shell (224) being connected to the frame (230). The virtual window system according to claim 11.

15. The projection system A first projector (252) for projecting a first image (253) onto the projection surface (242); A second projector (254) for projecting a second image (255) onto the projection surface (242); A cable (256) connecting the first projector (252) to the second projector (254); A virtual window system according to claim 11, comprising:

16. The virtual window system according to claim 11, wherein the outer shell (224), the transparent lens (226), and the projection system (232) are assembled as a plug-and-play unit attached to the outer surface of the inner wall (212).

17. A method of projecting a virtual window of an aircraft, comprising: - A step (802) of attaching a virtual window system (202) to an inner wall (212) of the aircraft (204), wherein the virtual window system (202) is arranged to cover a hole (262) in the inner wall (212), and the virtual window system (202) includes: A transparent lens (226) fixed to an outer shell (224); A projection system (232) connected to the outer shell (224) and arranged between the transparent lens (226) and the outer shell (224); A touch sensing layer (246) embedded in the transparent lens (226); The step (802) comprising; - A step (804) of providing an image (253) from a controller (260) in a computer system (222) of the aircraft (204) to the projection system (232); - A step (806) of projecting the image (253) onto a projection surface (242) of the outer shell (224), wherein the image (253) can be viewed through the hole (262) in the inner wall (212) and the transparent lens (226); The method comprising.

18. The method according to claim 17, further comprising a step (808) of receiving an input from the touch sensing layer (246) to determine the image (253) to be provided to the projection system (232).

19. The projection system (232) includes a first projector (252) for projecting a first image (253) onto the projection surface (242) and a second projector (254) for projecting a second image (255) onto the projection surface (242). The method according to claim 17, further comprising a step (810) of simultaneously projecting the first image (253) and the second image (255).

20. The method according to claim 17, further comprising a step (812) of changing the projected image (253) based on an input received from the touch sensing layer (246).

Images