Abstract: A movable or pivoting privacy barrier is provided inside the side panels of a cinema seat for selectively providing privacy to the user, with the option of allowing a user to decide whether not to use the privacy barrier. The dynamic privacy barrier system of the includes a privacy barrier that is part and provided inside of the seat support, so that the privacy barrier is pivoted inside the seat support to retract or store the component. The proposed system provides an enhanced privacy experience without affecting the aesthetic appearance of the seat or the environment where it is installed.

Abstract: A system and related method operates to receive autopilot selection and monitor aircraft systems to control which autopilot is actively flying the aircraft. During certain flight operations in which a single autopilot is in use, the system reverts to the next available autopilot should the active and selected autopilot disconnect for any reason (e.g., faults and/or failures). The system maintains a redundant ability for pilot use of each pilot selectable mode of each autopilot channel including altitude hold, speed hold, heading hold, etc. For an indication to a pilot or remote operator that the system has reverted to a second autopilot, the system commands a momentary aural warning and a visual message/lights. For failures resulting in timely but necessary maneuver requirements, the system maintains autopilot control laws, control authority and roll authority.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device separate from the compressing device and arranged in fluid communication with the ram air circuit and the at least one dehumidification system. The environmental control system receives a flow of a first medium and a flow of a second medium. The environmental control system is operable in a plurality of modes and in a first mode, a flow of the first medium is provided to the compressing device and the expansion device in series.

Abstract: An aircraft is provided and includes fuselage having a nose, a main section aft of the nose and a tail aft of the main section, an engine nacelle partially embedded in the tail and including a boundary layer ingestion (BLI) propulsor with an inlet directly adjacent to the fuselage and a nozzle element disposed upstream from the inlet and configured to accelerate boundary flows flowing toward the interior side of the engine nacelle.

Abstract: Implementations provide an aircraft synthetic vision system (“SVS”) giving passengers an exterior view. Omitting windows reduces costs, lowers weight, and simplifies hypersonic aircraft design and construction. Unlike contemporary SVSs, no lag exists between the exterior view and actual aircraft motion. Passengers experience no airsickness associated with a visual and vestibular system feedback mismatch. Lag is eliminated by predicting aircraft interior motion based on sensor feedback, and (b) displaying video camera images transformed to match the predicted aircraft orientation when the images get through the display system latency. Implementations predict aircraft orientation and pre-transform—through the use of dead reckoning to adjust a video signal based on sensed aircraft dynamics and an aircraft electronic model—an image captured from a video camera to match that orientation at the image display time.

Abstract: An adjustable monument mounting assembly is provided. The assembly comprises a saddle bracket that includes a recessed pocket section with a hole. A threaded adjustable fitting is configured at a first end to fit within the hole in the pocket and is accessible through the pocket. The opposite end of the adjustable fitting is configured to contact a structural mounting point. The adjustable fitting can be rotated within the hole and adjusted to bridge a gap between the saddle bracket and structural mounting point, eliminating the need for a shim. A bolt fits through a center through-hole in the adjustable fitting, allowing the adjustable fitting and bolt couple the saddled bracket to the structural mounting point.

Abstract: A fastening system for fastening fitments to a floor of a cabin of a vehicle has a receiving frame, a cantilever mounted on the receiving frame so as to be pivotable on a pivoting plane defined by the receiving frame, and having a mounting end and a fastening end, a first fastening element, and a multiplicity of second fastening elements. The first fastening element is arranged at the fastening end of the cantilever. The second fastening elements are positionable on the floor. The first fastening element is configured in a manner corresponding to the second fastening elements such that the first fastening element is mechanically connectable selectively to a second fastening element. A pivoting position of the cantilever is lockable relative to the receiving frame.

Abstract: A lumbar support (100) for a seat (200) defining a back plane (E) comprises a support device (10) having an upper end (O) including an upper angle of inclination (?) with the back plane (E) and a lower end (U) including a lower angle of inclination (?) with the back plane (E) and forming an crown of the curvature (S) located in an adjustable position between the upper end (O) and the lower end (U). The lumbar support (100) further comprises at least one angle adjuster (20, 25) connected to the upper end (O) or the lower end (U) and adapted to vary the upper angle of inclination (?) or the lower angle of inclination (?) in order to adjust the position of the crown of the curvature (S), and an actuator (30, 35) for adjusting the angle adjuster (20, 25).

Abstract: An oxygen delivery system provides controlled flow of oxygen-enriched gas to a patient. The system includes one or more sensors configured to measure respiration rate information and heart rate information of the patient. A computer system including one or more physical processors is operatively connected with the sensors. The physical processors are programmed with computer program instructions which, when executed cause the computer system to determine a metabolic oxygen consumption information of the patient from the respiration rate information and the heart rate information from the one or more sensors, and continuously adjust flow, volume and/or pressure of the oxygen-enriched gas delivered from an oxygen source of the oxygen delivery system to the patient based on the determined metabolic oxygen consumption information of the patient.

Abstract: A keep-out assembly for a stowage bin assembly positioned above at least a portion of one or more seats within a vehicle includes a keep-out lens and a keep-out bracket. The keep-out lens is pellucid and extends between an inner edge and an outer edge. The keep-out lens has a top surface and a bottom surface. The keep-out mounting bracket has a base configured to be mounted to the stowage bin assembly at a top of the stowage bin assembly. The keep-out mounting bracket has a support arm extending from the base. The support arm engages the keep-out lens and supports the bottom surface of the keep-out lens at an elevated position above the stowage bin assembly.

Abstract: A moveable barrier system comprising a first panel having a first vertical edge and a second vertical edge, the first vertical edge rotatably coupled to a first vertical surface along a first axis, and a second panel having a third vertical edge and a fourth vertical edge, the third vertical edge of the second panel rotatably coupled to the second vertical edge of the first panel, the fourth vertical edge of the second panel removably coupled to a second vertical surface. Each of the first and second panel have a structural layer that forms a vertical plane, spanning the first vertical edge and the second vertical edge, and a projectile resistant layer that is resistant to projectile impact. The first panel and the second panel are configured to move from a stored position into an active position when in use.

Abstract: An aircraft region comprising an aisle section extending in a longitudinal direction of the aircraft region, a bench seat oriented transversely with respect to the longitudinal direction and having a first seat adjacent to the aisle section and a second seat arranged remote from the aisle section, and an aircraft stowage bin system having a first stowage bin arranged at least in part above the first seat and a second stowage bin arranged at least in part above the second seat. The first stowage bin has a first rear side facing away from the aisle section, and the second stowage bin has a second rear side facing away from the aisle section. The second stowage bin is arranged above the second seat such that it is accessible for a person sitting on the second seat or standing in the longitudinal direction in front of the second seat.

Abstract: A system for disposing waste in a transportation system includes a collection device for collecting waste in the cabin of the transportation system, a separate receptacle device for receiving collected waste from the collection device, and a connection device for selectively connecting the collection device to the receptacle device in order to deliver collected waste from the collection device into the receptacle device. The receptacle device is arranged in a lower deck region underneath the cabin floor. The connection device extends into the receptacle device from the cabin floor and includes a closure that is arranged on or in the cabin floor. The collection device is mechanically couplable to the connection device, and includes a closable output opening aligned with the closure of the connection device in the coupled state. The closure and/or the output opening can only be opened when the collection device is coupled to the receptacle device.

Abstract: An aircraft includes a partition wall for supporting monuments such as lavatories and galleys. The partition wall may support a large majority of the weight of the monuments such that the flooring of the aircraft is relieved of the force from various monuments. Additionally, the partition wall may be used to support the fuselage of the aircraft.

Abstract: A monument arrangement for a cabin of a vehicle has a first monument, with a washroom formed therein, a second monument and an aisle. The first and second monuments enclose the aisle, wherein an access opening to the washroom is directed toward a side wall of the second monument and is adjacent to the aisle. The distance between the access opening and the relevant side wall of the second monument is at most 1 m, and the side wall of the second monument has a first, rigid side wall portion and at least one second side-wall portion, which is mounted on the first side wall portion such that it can be pivoted about a vertical axis and which can be pivoted from a neutral position, running in the direction toward the first side wall portion, into an angled position, directed away from the first monument and the aisle.

Abstract: An apparatus for controlling a rear-seat leg support for a vehicle seat includes: a rear-seat leg support disposed at a lower side of a vehicle seat and that performs an upward-downward rotational operation and a forward-rearward slide operation; a passenger seat that performs a forward-rearward slide operation and a forward-rearward reclining operation; a drive unit that operates each of the rear-seat leg support and the passenger seat; a sensor unit connected to the drive unit and that detects a rotation angle and a slide position of the rear-seat leg support or a slide position and a reclining angle of the passenger seat; an input unit that receives an inputted operation instruction to operate the rear-seat leg support or the passenger seat; and a control unit that adjusts the slide position of the rear-seat leg support.

Abstract: A safety open and closing system for an overpressure door on fuselage of an aircraft. Wherein the safety opening and closing system allows safe access through the overpressure door to the compartment. The safety open and closing system including an assembly of a hollow beam, a blocking bar in the hollow beam, a spring biasing the blocking bar with respect to the hollow beam and a lever at the end of the blocking beam which pivots between a position A that allows closure of the overpressure door and a position B preventing closure of the door.

Abstract: An emergency vision apparatus includes a housing for attachment underneath an instrument panel in a cockpit, the housing including a front opening, a front cover for the front opening, a bottom portion of the front cover being pivotably attached to the housing to allow the front cover to open and rotate downwardly; an inflatable enclosure made of airtight material and having an expanded form when deployed and a deflated form when not in use, the enclosure when in the deflated form is stored within the housing; first and second clear members disposed at respective first and second ends of the enclosure to enable a user to see through the enclosure when expanded and observe a source of visual information at a distal end of the enclosure while smoke or other particulate matter is in the environment; a first switch operably associated with the blower to activate the blower and thereby inflate the enclosure to the expanded form when the enclosure is to be deployed; and a tubular air passageway connecting the blowe

Abstract: An aircraft suite may include a passenger compartment disposed on a main deck of an aircraft. The passenger compartment may be partitioned from a main passenger cabin of the main deck by at least one bulkhead. The passenger compartment may include an aircraft seat and a hatch set within an opening in a floor of the passenger compartment. The aircraft suite may include a lower lobe rest compartment integrated in a cargo deck below the main deck. The lower lobe rest compartment may be proximate to the passenger compartment. The lower lobe rest compartment may include a passenger rest compartment and a device proximate to the hatch. The device may be configured to assist a passenger to at least one of descend into the lower lobe rest compartment from the passenger compartment, or ascend into the passenger compartment from the lower lobe rest compartment, via the hatch.

Abstract: A toilet module and a vehicle including a toilet module are provided. An exemplary toilet module includes a toilet unit and a housing. The housing includes a front wall with an access opening, a first functional wall arranged opposite the front wall and supporting the toilet unit, and a second functional wall perpendicular to the front wall and extending between the front wall and the first functional wall. Further, the toilet module includes a storage shelf attached to the housing and a swivable table attached to the housing and movable to an extended configuration. The swivable table overlaps the storage shelf when in the extended configuration.

Abstract: A bi-directional entry vestibule for a passenger aircraft provides passenger access to overhead rest cabins and lower-lobe rest cabins (e.g., on a lower cargo deck) via separate enclosed chambers incorporating ascending and descending staircases respectively. The ascent and descent chambers may be accessed from the main passenger cabin via access doors (one door or separate doors); the ascending and descending access doors may be on opposing sides of the aircraft (e.g., accessible from port-side and starboard-side aisles) or adjacent to each other and accessible via the same aisle. The ascent chamber may include a further transitional space transitioning into an overhead corridor-based cabin, the transitional space including a crew station comprising a fold-down jump seat, communications equipment, and emergency supply storage.

Abstract: Disclosed is a system and method for passenger safety. A sensing unit, remote device, and/or fob may interoperate to provide various alerts and other indications representative of aspects of a context environment proximate to a sensing unit. In this manner, passenger safety may be enhanced.

Abstract: A cabin arrangement for a vehicle includes a first lateral segment module having a first main extension axis, a second lateral segment module having a second main extension axis, and an aisle. The main extension axes run parallel to each other, wherein the first lateral segment module and the second lateral segment module are distanced from each other in a direction perpendicular to the main extension axes and enclose the aisle between each other. The aisle runs parallel to the main extension axes, and the first lateral segment module has a receiving space that receives serving trolleys. The receiving space has an opening that faces into the aisle. The receiving space is designed to receive serving trolleys arranged transverse to the first main extension axis and staggered parallel to the first main extension axis.

Abstract: In a method for the ventilation of an aircraft area, air conveyed from an aircraft environment by a conveying device into an interior space of the aircraft is supplied during ground operation of the aircraft to the aircraft area to be ventilated. During flight mode of the aircraft, air flowing from the aircraft environment via a ram air duct into the interior space of the aircraft is supplied to the aircraft area to be ventilated. During flight mode of the aircraft, in addition to the air flowing from the aircraft environment via the ram air duct into the interior space of the aircraft, air conveyed from the aircraft environment by the conveying device into the interior space of the aircraft is supplied to the aircraft area to be ventilated when a flight velocity of the aircraft falls below a flight velocity threshold value.

Abstract: A fuselage assembly for an aircraft including a stringer extending longitudinally along the fuselage. The stringer defines a fluid channel. The fluid channel is configured to form at least part of a distribution duct of a cabin air distribution system.

Abstract: There is disclosed a cooling system for a liquid cooled internal combustion aircraft power plant for an aircraft having a tail cone. The cooling system has: an air inlet defined through a wall of the tail cone and fluidly connected to an environment outside the aircraft; a heat exchanger having at least one first conduit fluidly connected to the environment via the air inlet and at least one second conduit in heat exchange relationship with the at least one first conduit and fluidly connectable to a coolant circuitry of the liquid cooled internal combustion aircraft power plant; a blower fluidly connected to the environment via the air inlet; and an air outlet fluidly connected to the blower and defined through a wall of the aircraft upstream of the air inlet relative to a direction of an airflow along the aircraft.

Abstract: An airplane is provided. The airplane includes a compressing device including a turbine and a compressor. The turbine includes first and second inlets and provides energy by expanding one or more mediums. The first inlet is receives a first medium of the one or more mediums. The second inlet receives a second medium of the one or more mediums. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode.

Abstract: An accessory drive for an engine includes a power takeoff (PTO) configured to couple power from a rotating shaft of the engine and to convey the power through an opening in a housing of the engine. A gearbox is coupled to and configured to be driven by the PTO. The gearbox is disposed external to the housing and includes a planetary gear train. At least one engine accessory is coupled to and configured to be driven by the planetary gear train.

Abstract: A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. Provision is made on at least one of the wall parts for a fixing section which is overlapped by the floor panel. Also described is an aircraft which features such a cabin monument.

Abstract: A seating system for a vehicle that comprises floor beams, which support floor panels that define a floor surface. The vehicle has a virtual longitudinal plane, perpendicular to the floor surface, and a virtual longitudinal axis, parallel to the floor surface and lying in the virtual longitudinal plane. The seating system comprises a primary pair of seat tracks, a secondary pair of seat tracks, one of which is positioned between seat tracks of the primary pair of seat tracks, and a first seat assembly. The first seat assembly comprises a first seat support and a first plurality of seats, attached to the first seat support. The first seat support is attached to the primary pair of seat tracks.

Abstract: A trash can device for an aircraft lavatory unit is provided, including: a waste container in a storage chamber of the aircraft lavatory unit; a chute, disposed above the waste container, including a trash feed opening formed at a section of the chute corresponding to a trash feed port of a panel sectioning off the storage chamber; and a waste flap that opens and closes the trash feed opening. A fire spreading prevention space is formed below the chute in a state when the waste flap is positioned in a closed position in which the trash feed opening is closed by the waste flap. The trash can device is provided with a holding/moving portion of the waste flap, the holding/moving portion holds the waste flap in an open position in which the trash feed opening is opened and moves the waste flap to the closed position when exposed to heat.

Abstract: A compressor temperature control system and method for an aircraft air cycle machine is presented. The system prevents overheating of the compressor using a low limit valve positioned between a turbine outlet and a bleed air source. The low limit valve directs the air to an air cycle machine, or bypasses the machine, in regards at least in part to the air temperature measured in the cabin supply duct.

Abstract: An aircraft cabin management system includes a control unit and at least one sensor intended to be incorporated into a seat and suitable for establishing a communication with the control unit in order to transmit, to the control unit, at least one signal relating to at least one measurement performed by the sensor.

Abstract: An airplane is provided. The airplane includes an environmental control system that provides a pressurized medium to a chamber of the airplane. The airplane also includes a bleed system. The bleed system includes a plurality of ports, each of which can provide a bleed medium from an engine of the airplane to the environmental control system. The plurality of ports includes at least a first port, a second port, and a third port. The first port is selected for an idle condition. The second port is selected for a hot day cruise condition. The third port is selected for a standard operating condition. The bleed system can operate in a first mode, a second mode, or a third mode to provide the bleed medium to the environmental control system from the first port, the second port, or the third port respectively.

Abstract: Passenger rest compartments may be incorporated into remote areas of an aircraft, either in the overhead crown region or in lower lobe cargo decks. Each passenger rest compartment includes two-way audio communication with the flight deck and non-intrusive non-visual monitoring of the compartments and surrounding environment to determine passenger presence, absence, and general well-being as well as environmental safety. Rest compartments may be integrated into rest cabins in the overhead or lower lobe areas, the rest cabins accessible from the main passenger cabin via an entry vestibule providing dedicated enclosed paths to the overhead and lower cabins. Additional deployable egress hatches may allow passengers to rapidly return to the main deck from the overhead and lower lobe cabins in the event of an emergency. Selected passenger seats (e.g., partitioned or other premium seats) may include private access to passenger rest compartments.

Abstract: A waste bin device of an aircraft lavatory unit is provided. A chute, waste flap, and waste container are formed from a material having fire resistance performance. A fire spreading prevention space that prevents fire from spreading to the outside of a waste bin device main body due to a flame occurring when inserted waste catches fire is formed inside the waste bin device main body at a storing position of the waste container positioned with regard to a lower portion of the chute. A maintaining portion maintains the waste container at a storing position. The maintaining portion includes a first maintaining portion that maintains from a vertical direction a condition where an upper portion of the waste container and lower portion of the chute are aligned, and a second maintaining portion that maintains the condition from a direction orthogonal to the vertical direction, at the storing position.

Abstract: An environmental control system of an aircraft includes a ram air circuit having a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and a plurality of compressing devices is arranged in fluid communication with the ram air circuit and the dehumidification system.

Abstract: A cockpit internal anti-sabotage system (CIASS) without compromising the cockpit security and the present anti-hijacking procedure and protocol, wherein a single cockpit crew alone in the cockpit cannot deny bonafide entry of other cockpit crew or cabin crew in an attempt to commit suicide or sabotage the aircraft, the system comprises a manual door lock system and an automated door lock system wherein both the systems comprising a mechanical system or a non-mechanical system or combination of both.

Abstract: A passenger seat system for a transport means has an elongate carrier structure to be attached, fixedly with respect to a structure, and having a main extent axis and mutually spaced-apart raster openings on the carrier structure top side, raster openings projecting into at least one lateral delimitation of the carrier structure, and a seat having a seat frame, displaceable and arrestable on the carrier structure, a bottom side lying on the carrier structure, and a top side holding a seat surface. The seat frame has an arresting device on the bottom side and has an operating unit coupled to the arresting device. The operating unit is movable into an arresting position and an unlocking position. The arresting device has an arresting lever movable into an engagement position, for lateral engagement into a raster opening, and a release position, in which the arresting lever is released from the carrier structure.

Abstract: A humidifier system for a vehicle passenger cabin includes an onboard humidifier, an onboard reservoir in fluid communication with the humidifier and adapted to collect a fluid from a vehicle heat exchanger, and a controller configured to determine at least a passenger cabin relative humidity value and a dew point value for at least one vehicle window. The controller is configured to actuate the onboard humidifier to provide a humidified airflow into the passenger cabin, and to actuate a window heating system to heat the at least one vehicle window sufficiently to prevent or remove fogging resulting from the humidified airflow. Methods for controlling the humidifier system are described.

Abstract: A gas turbine engine includes first and second electrical machines coupled to the gas turbine engine, each of the first and second electrical machines electrically coupled to both a primary electrical bus and a secondary electrical bus. The gas turbine includes a first controller configured to control operation of the gas turbine engine, and a second controller coupled to the first controller, the second controller configured to respond to control inputs from the first controller and control an electrical output of the first and second electrical machines to the primary and secondary electrical busses. A converter controller is coupled to an energy storage system, the second controller, the primary electrical bus, and the secondary electrical bus.

Abstract: A floor panel includes a first structural layer, a film heater configured to emit far-infrared radiation, and a first open cell layer disposed between the film heater and the first structural layer such that far infrared radiation from the film heater is directed toward the first open cell layer.

Abstract: A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door assembly also includes a privacy door rotatably coupleable to the first post via a set of hinges, where the privacy door comprises a decompression latch arranged to engage the latch recess when the privacy door is in a closed position within the door frame, and where the decompression latch is configured to disengage from the latch recess in response to a decompression detected on a forward side of the privacy door.

Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.

Abstract: A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door assembly also includes a privacy door rotatably coupleable to the first post via a set of hinges, where the privacy door comprises a decompression latch arranged to engage the latch recess when the privacy door is in a closed position within the door frame, and where the decompression latch is configured to disengage from the latch recess in response to a decompression detected on a forward side of the privacy door.

Abstract: A control cabinet arrangement, comprising a cooling device which is received in a control cabinet housing, wherein the cooling device can be slidably held on the control cabinet housing via a linear adjusting unit, particularly a bar system, and can be adjusted between a pull-out position and a slide-in position, wherein the cooling device in the slide-in position is completely received in the control cabinet housing, and in the pull-out position, the cooling device protrudes at least partially beyond a door side of the control cabinet housing from the control cabinet housing, and wherein a door element, which closes in its closed position the door side of the control cabinet housing, comprises at least one air passage opening which opens into an air outlet and/or an air inlet of the cooling device in the closed position of the door element, when the cooling device is in the slide-in position.

Abstract: Fuselage configurations in which window seats project into and partially occupy inter-frame spaces. In accordance with some embodiments, a frame in proximity to a window seat is equipped with a riser duct closure cover for defining a riser duct for passing a volume of air through a supply duct located below a floor of a passenger cabin through the riser duct and through a crown distribution duct located above a ceiling of the passenger cabin. In accordance with other embodiments, the frames in proximity to window seats are equipped with respective airbags. More specifically, for each pair of adjacent frames in which the forward frame of the pair is located forward of the window seat, the aft frame of the pair is located aft of the window seat, the forward frame is equipped with an airbag.

Abstract: A value for an aircraft movement limit is received where the aircraft movement limit is associated with a manned aircraft. The aircraft movement limit is automatically set to the value. A pilot instruction is received and a control signal for the aircraft is generated using the pilot instruction and the aircraft movement limit.

Abstract: An aircraft includes a passenger cabin having a floor, a cargo compartment below the floor, a first access unit for accessing the cargo compartment from the passenger cabin, the first access unit being located on the floor and a utility space module arranged in the cargo. At least one part of the cargo compartment includes a first lateral half and a second lateral half in relation to a longitudinal axis of the aircraft; the lateral halves form the part of the cargo compartment. The utility space module includes a utility space cross-section in a direction normal to the longitudinal axis, which is dimensioned such that it conforms to a cross-section of one of the lateral halves of the cargo compartment. Further, the utility space module is placed exclusively in the first lateral half or the second lateral half of the cargo compartment directly below the first access unit.

Abstract: A visual output assembly for an aircraft cabin includes at least one electronic display device, a projection screen, an image projector configured to project images onto the projection screen, and at least one illumination device.