Abstract: A passenger seat assembly can include a seat frame; a seat back supported by the seat frame, comprising a rearward surface, and moveable between a stowed position and a deployed position; and a monitor shroud positioned proximate to the rearward surface of the seat back and fixedly coupled to a stationary surface, wherein the monitor shroud remains stationary as the seat back moves between the stowed position and the deployed position, and the monitor shroud defines an opening that provides access to the rearward surface of the seat back.

Abstract: Lateral sleep systems for aircraft are disclosed. A divider is located between a first seat and a second seat of the aircraft. The divider includes a first panel oriented toward the first seat and a second panel oriented toward the second seat. The first panel defines a first support ledge. The second panel defines a second support ledge. A first lateral sleep apparatus positioned on a first side of the divider adjacent the first seat includes a first headrest and a first cradle. The first cradle supports the first headrest and includes a first panel mounting interface coupling the first headrest to the first support ledge. A second lateral sleep apparatus positioned on a second side of the divider adjacent the second seat includes a second headrest and a second cradle. The second cradle supports the second headrest and includes a second panel mounting interface coupling the second headrest to the second support ledge.

Abstract: Provided is an Aircraft Lavatory Unit 20 that ensures lavatory user comfort while facilitating diaper changing. The Aircraft Lavatory Unit 20 includes a Diaper Changing Table 10 on which an infant can be placed and which can be selectively changed between a Housed State in which the Diaper Changing Table 10 is housed in a Wall Surface and a Pulled-Out State in which the Diaper Changing Table 10 is pulled out from the Wall Surface; and a display 25 which is disposed to face the Diaper Changing Table 10 in the Pulled-Out State and display still images or videos.

Abstract: A fastening apparatus, for a backseat bench of a motor vehicle, includes a housing installation with a fastening space for receiving a retaining section of a component to be fastened, wherein the housing installation is insertable in an assembly direction into a passage opening of a carrier component, and wherein the housing installation has an abutment section with an abutment surface extending transversely to the assembly direction at an end counter to the assembly direction for abutment on an edge of a carrier component facing counter to the assembly direction. A catching installation is provided with catching elements for connecting the fastening apparatus to a carrier component. The fastening apparatus further has a fastening installation with a catching means for releasably fixing a retaining section of a component to be fastened, wherein the fastening installation is arranged in front of the abutment section in the assembly direction.

Abstract: An escape path marking for an aircraft includes a lighting element, which luminesces in a dark environment, and which emits an emitted light which exits at an outer side of the escape path marking. A transparent protective element is arranged between the lighting element and the outer side of the escape path marking. A planar grid element, which comprises regularly alternating pure-color transparent and opaque regions, is arranged between the lighting element and the outer side of the escape path marking. A transparent pigmented element is formed and arranged between lighting element and the outer side of the escape path marking such that in an event of external illumination according to at least one predefined illumination scenario, a predefined first color tone results on the outer side of the escape path marking at the transparent regions of the grid element.

Abstract: A panel for covering a supply channel in a passenger cabin of a vehicle including a mounting surface facing the passenger cabin while the panel covers the supply channel. The panel is elongated in a longitudinal direction and adapted for mounting passenger supply units. The mounting surface includes spaced openings arranged along a longitudinal direction of the panel, wherein each opening includes a connector assembly for a passenger supply unit. The panel includes a mount securing passenger supply units. The mounting surface comprises extended areas for providing support in opposing lateral directions to passenger supply units mounted to the panel.

Abstract: A lavatory system within an internal cabin of a vehicle includes an enclosure defining an interior chamber, a first lavatory unit within the interior chamber, and a second lavatory within the interior chamber. The first lavatory unit is adjacent to the second lavatory unit. In at least one embodiment, a lavatory within an internal cabin of a vehicle includes an interior chamber defined by one or more outer walls, and a storage compartment extending outwardly from at least one of outer walls. The storage compartment defines an internal storage space that connects to the interior chamber. In at least one embodiment, a lavatory includes a first lavatory unit, a second lavatory adjacent to the first lavatory unit, and a containment compartment common to the first lavatory unit and the second lavatory unit.

Abstract: Duct stringers for aircraft wing boxes. The duct stringer comprises a base, a pair of sidewalls projecting from the base in a spaced-apart relationship, and a cap wall that extends between and interconnects the pair of sidewalls, with the cap wall being positioned spaced apart from the base by the pair of sidewalls. The duct stringer further comprises an ovaloid vent formed in the cap wall. The ovaloid vent comprises a perimeter that circumscribes an aperture and that defines a closed shape. The perimeter comprises a pair of curved end regions opposed to one another and that each arc at least substantially through 180 degrees. Each curved end region comprises a non-uniform radius of curvature.

Abstract: A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine and extracting work from a second medium provided to a second turbine operably coupled to the compressor to drive the compressor. The first medium is provided to the compressor and the turbine sequentially. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine and in a second mode of operation, at least a portion of the first medium to be provided to the downstream load bypasses the turbine.

Abstract: An assembly for an interior of a vehicle with the assembly having a monument wall configured to mount to the interior of the vehicle. A panel is configured to mount to an overhead support structure adjacent to the monument wall. The panel includes a front side configured to face into the interior of the vehicle and an opposing back side. One or more latch assemblies are configured to connect the panel to the overhead support structure adjacent to the monument wall. The latch assemblies include a latch mounted to the back side of the panel, a track with one or more rails, a follower with an arm and a head with the head sized to engage with the track, and a pull mechanism to unlock the latch.

Abstract: A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

Abstract: An aircraft seating module (20) includes a seating mount (26) having a horizontal mounting rail (28) integrally joined to a vertical mounting post (30) at an adjoining elbow (32). The rail (28) includes a mounting boss (34) longitudinally spaced from the post (30) for attachment to an aircraft cabin seat track (18). Both the rail (28) and post (30) include mounting holes (38) for attaching a passenger seat (22) and appended furniture (24) directly to the seating mount (26) and in turn indirectly to the seat track (18) in the cabin floor (12).

Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.

Abstract: Passenger seats having improved comfort emergency egress solutions for mini suites or other types of passenger seats that have a privacy screen, wall, or sliding door that divides the passenger seat from the aisle area or other common area. Specific embodiments find particular use on-board passenger transportation vehicles, such as aircraft, where comfort and privacy must be balanced with safety and federal regulations.

Abstract: An aircraft area having a textile display, aircraft passenger seat having a textile display, and aircraft including an aircraft area. An aircraft area includes an interior component, a textile display on the interior component and including at least one textile fiber capable of changing a color at at least one section of the textile fiber, and a controller operatively coupled to the textile display and configured to change color of the at least one section of the textile fiber, such that the textile display displays information. An aircraft passenger seat includes a back rest, seat pan, and textile display integrated into a seat cover covering the backrest and/or the seat pan. The textile display includes at least one textile fiber capable of changing a color at at least one section of the textile fiber. An aircraft may include one or more aircraft areas and/or one or more aircraft passenger seats.

Abstract: A user destination is identified based on received location information from a user. A first seat in a vehicle is assigned to the user based on the user destination. At least one of the first seat and a second seat in the vehicle is moved upon user entry until a distance between the first seat and the second seat is greater than a distance threshold.

Abstract: A galley system within an internal cabin of an aircraft includes one or more inboard cart compartments that are configured to removably retain one or more first galley carts, and one or more outboard cart compartments. The outboard cart compartment(s) are configured to removably retain one or more second galley carts. The inboard cart compartment(s) extend forwardly and/or rearwardly in relation to the outboard cart compartment(s).

Abstract: A restraint system for helping to protect an occupant of a vehicle having a floor and a cabin with a floor for the occupant includes an airbag. The airbag has a stored condition on the vehicle floor and is inflatable to a deployed condition aligned with the occupant in a forward-rearward direction of the vehicle. The airbag is configured to utilize the vehicle floor as a reaction surface for restraining the movement of the airbag in response to occupant penetration into the airbag.

Abstract: An aircraft including a cabin inside which a floor is installed, and at least one arranging module which is fixed solely to the floor and which includes a front wall, a rear wall, a port-side wall and a starboard-side wall which are rigidly connected to one another. The port-side and starboard-side walls each have a door, a roof and a deck fixed to each of the front, rear, port-side and starboard-side walls, and a separating system which makes it possible to separate the internal volume of the arranging module into two volumes, each being accessible through one of the doors. Such an aircraft therefore provides an arranging module which is fixed solely to the floor of the cabin, thereby facilitating the set-up thereof.

Abstract: A multirotor drone comprises a main body and an air channel embedded within the main body having an air inlet on the surface of the main body, multiple propellers that induce an air flow toward the air inlet and into the air channel, a microcontroller positioned and configured to control navigation of the drone by actuation of the plurality of propellers, an air scoop having a section positioned at the outer surface of the main body adjacent to the air inlet which is adjustable so as to capture and divert air into the air inlet and air channel or to block air flow into the air inlet, and a gas sensor positioned within the air channel. The air scoop is positioned to capture air flow from at least one of the plurality of propellers into the air channel and to the gas sensor.

Abstract: A passenger module that may be connected to an aircraft for transport, and may be detached and attach different module for carriage to a different destination. In alternative embodiments involving different aircrafts such as fixed wing and helicopter aircraft, a module may be adapted to have a transparent exterior so that passengers may have a broad range of unobstructed view of the outside surroundings. The module may have a range of free movements while still connected to the aircraft for such purposes as sightseeing.

Abstract: A sanitation assembly attaches over a surface inside a tray table of an aircraft. A source of UV radiation is mounted to the assembly and configured to direct UVC radiation to the tray table at a predetermined dosage, wherein the assembly uses for disinfection of the aircraft tray table. The embodiments may use UV light sources and/or a disinfection unit powered by a fuel cell or other external power source.

Abstract: An environmental control system that includes a first environmental control system pack, a first recirculation fan assembly, and a cabin air sensor unit. The first environmental control system pack is arranged to provide conditioned air to an aircraft cabin. The first recirculation fan assembly is arranged to recirculate a first cabin air fluid flow back to the aircraft cabin. The cabin air sensor unit is arranged to provide a first air quality signal indicative of an air quality of the first cabin air fluid flow to a controller.

Abstract: A cabin interior arrangement 1 for an aircraft is proposed that comprises a first cabin interior object and a second cabin interior object 3a, b, comprising a power transmitting device 5 for transmitting power from an aircraft electrical system 7, wherein the power transmitting device 5 is arranged on the first cabin interior object 3a, comprising a power receiving device 6 for receiving the power from the power transmitting device 5, wherein the power receiving device 6 is arranged on the second cabin interior object 3b, wherein the power transmitting device 5 and the power receiving device 6 are embodied as a power transfer arrangement 2 for supplying the power to a mobile terminal 4, wherein the power transmitting device 5 and the power receiving device 6 are designed to transfer power over a distance of several centimetres, wherein the power transmitting device 5 and the power receiving device 6 are deigned to set up a wireless and/or cordless supply connection segment 10 between the power transmitting de

Abstract: A floor assembly is provided. The floor assembly is configured to form or be positioned on a floor of an enclosed space. The floor assembly includes a grid, a pan, and a surround member. The grid has an array of openings configured to allow passage of liquid. The pan is disposed beneath the grid and defines a cavity. The pan includes a pan floor and a frame. The frame is disposed laterally outward of the pan floor and supports the grid. The surround member is supported by the frame. The surround member is disposed laterally outward of the grid, and the surround member and grid do not overlap.

Abstract: Operation of an overhead storage bin sensor used to monitor the volume consumed within the bin including a VOC sensor to monitor for material that may become overheated within the bin such as lithium ion batteries in electronics products is provided. Currently, fire or smoke detectors are not integrated into the storage bins leaving this area vulnerable to developing fires and outgassing of electronic components often stored by passengers. Early detection of such events can prevent propagation of fire on board an aircraft by rapidly reporting the event and giving the location of the event. The system described leverages other patents applied for including a wireless sensor network and storage volume sensors. The sensor monitors for outgassing of materials or smoldering material by monitoring the air quality within the bin space.

Abstract: An aircraft lavatory complex incorporating lavatories accessible to passengers of reduced mobility (PRM) is disclosed. Left-side and right-side full service lavatory units are accessible via left-side and right-side lavatory access doors opening in opposing directions. The left-side and right-side full service lavatory units are separated by a common central partition repositionable by cabin crewmembers (but protected from independent repositioning by occupants of either lavatory unit) to enlarge either of the left-side or right-side lavatory units for enhanced PRM accessibility.

Abstract: A modular aft galley and lavatory complex is disclosed. The galley complex is situated aft of an aircraft passenger cabin and incorporates left-side, right-side, and aft galley structures together partially enclosing an interior workspace, the left-side and right-side galley structures separated by a center aisle. Each galley structure includes trolley bays capable of securing trolleys therewithin. Each trolley can be removed from its trolley bay into the interior workspace or central aisle for use in catering or service operations inflight. Each galley structure includes storage bays accessible from the interior workspace. Between the upper and lower portions are flat workdecks and galley insert bays capable of accepting ovens, chillers, beverage makers, and other galley insert devices. Either the left or right galley structure includes a lavatory complex adjacent to the passenger cabin, incorporating aft lavatory units and a galley extension housing additional storage and cart space.

Abstract: An aircraft passenger compartment suite may include a first side with a first display device, a second side with a second display device, and a privacy divider separating the first side and the second side. The first display device may be configured to actuate between a first deployed position and a first stowed position via a first stowage mechanism. The second display device may be configured to actuate between a second deployed position and a second stowed position via a second stowage mechanism. The privacy divider may include one or more panels configured to actuate between a panel deployed position and a panel stowed position. The privacy divider may be open when at least one of the first display device is in the first stowed position, the second display device is in the second stowed position, or the one or more panels are in the panel stowed position.

Abstract: A system for manufacturing a kitchen arrangement for a cabin of a vehicle includes a primary module with an electrical energy supply device, a cooling device, and at least one supply connection for supplying the primary module with a requisite. The system also includes at least one auxiliary module that is couplable with the primary module. The cooling device is set up to provide a stream of cooled fluid to a fluid outlet. At least one outer boundary surface of the primary module comprises an electrical connection coupled with the electrical energy supply device and a fluid connection coupled with the fluid outlet. The at least one outer boundary surface is adjusted for coupling with an auxiliary module having a correspondingly shaped boundary surface.

Abstract: An interior space for an aircraft includes a cockpit, a cockpit wall separating the cockpit from the remaining interior space, a cabin door arranged directly behind the cockpit wall for accessing the interior space of the aircraft from outside the fuselage, a modular installation space for installation equipment, a plurality of seat rows, a longitudinal aisle extending along the interior space through the seat rows to separate adjacent groups of seats from each other, and an access path for the cabin door. The access path extends from the cabin door to the longitudinal aisle to create an intersection region between the access path and the longitudinal aisle. The modular installation space is arranged directly forward of the seat rows. The access path extends at an angle of at least 100° to the longitudinal aisle in a forward direction.

Abstract: An aircraft monument for use in a cabin of an aircraft includes a monument assembly and a seat assembly. The monument assembly includes a frame having a plurality of walls defining a compartment. The plurality of walls include a first end wall having a forward section at a forward plane of the frame. The compartment is defined rearward of the forward section. The seat assembly is forward of the frame. The seat assembly has a shell configured to at least partially surround a passenger seat. The shell has a rear rearward of the forward plane of the frame.

Abstract: In order to make available a space-saving sanitary unit having a toilet which offers improved user convenience to persons with restricted mobility, a cabin module for an aircraft is described which has a sanitary unit. The sanitary unit has a toilet cubicle with a toilet. The toilet cubicle is formed by four side walls and the toilet is arranged on a first side wall. A first access door is arranged in a second side wall, which extends transversely to the first side wall and adjoins the first side wall. A surface which is designed to at least partially accommodate a wheelchair is provided as an option within the toilet cubicle. The cabin module is configured to be installed with the second side wall transversely to a direction of flight. The first side wall 18a is aligned with an external wall in the installed state.

Abstract: A door assembly configured to be positioned between a first compartment and a second compartment that includes a main door portion having a first decompression opening defined therein, at least a first panel portion positioned in a first position within the first decompression opening, and a decompression sensor. The first panel portion is movable linearly between the first position and a second position and is pivotable between the second position and a third position. In the third position the first compartment is in fluid communication with the second compartment via the first decompression opening.

Abstract: A gas turbine engine includes a main compressor section, a combustor, and a main turbine section. A fuel pump delivers fuel to the combustor. A tap taps air compressed by the main compressor section, and is connected for delivering the tapped air through a first heat exchanger and to a boost compressor. Air downstream of the boost compressor is connected to cool a component. Driving compressed air is connected to be delivered to a power turbine. The power turbine is connected to drive both the boost compressor and the fuel pump.

Abstract: A flight deck barrier door for an aircraft, the flight deck barrier door including a door frame and a door panel in the door frame. The door panel has a plurality of vents. The door panel and door frame have a minimum total vented surface area of 1000 square inches.

Abstract: An aircraft air distribution assembly providing integrated personally controllable air flow and cabin air flow is presented. The aircraft air distribution assembly comprises a plenum and a flow restriction system. The plenum is connected to a plurality of personal air outlets configured to provide the personally controllable air flow. The flow restriction system extends through at least one wall of the plenum, the flow restriction system configured to set a pressure for the cabin air flow.

Abstract: Apparatus and method for conditioning engine-heated air onboard an aircraft including a heat exchanger (140) at least partially disposed in a pylon structure (118) for supporting an engine (134) of the aircraft. The pylon heat exchanger (140) extracts heat from a flow (156) of engine-heated air. A flow (142) of ambient air is provided to the pylon heat exchanger (140) from a ram air inlet (150).

Abstract: An aircraft fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.

Abstract: Systems and methods provide airflow to a first area from a second area within a vehicle. The system includes a fan mounted within a door separating the first area from the second area. The fan is configured to direct airflow from the second area into the first area. The fan having a shield positioned adjacent to the second area that is configured to conceal the fan.

Abstract: An aircraft seat with a voltage supply port associated only with the aircraft seat and/or a data port associated only with the aircraft seat, a voltage supply unit, associated with the aircraft seat and including a voltage input and a voltage output, each of which is connected to another of the voltage supply ports, a switching circuit associated only with the aircraft seat and hooked up between the voltage output and the voltage supply port and/or between the data port and a data network, with which each of the voltage supply port or each of the data port can be activated or deactivated.

Abstract: A cabin segment 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 arranged in the cabin segment. The main extension axes parallel to each other, and the first and second lateral segment modules are distanced from each other in a direction perpendicular to the main extension axes and enclose the aisle, which runs parallel to the main extension axes. At least one of the first lateral segment module and the second lateral segment module includes a lavatory accessible through a lavatory opening positioned outside the aisle. The first lateral segment module includes at least one receiving space to receive serving trolleys. The at least one receiving space has a receiving opening facing into the aisle.

Abstract: An insulation pack for thermally and acoustically insulating an aircraft has a mat formed from an insulation material, and a casing film which completely encases the mat. The casing film has drying openings, each closable a cover that is connected to the casing film. Each cover has a coating substance, the planar extent of which varying as a function of the relative air humidity of the air in the interior of the insulation pack such that each cover moves relative to the casing film, as a function of air humidity. The associated covers are adapted for assuming an orientation which, below a predetermined relative air humidity, closes the associated drying opening and which, at higher relative air humidity values, at least partially opens the associated drying opening.

Abstract: A floor assembly for an aircraft comprising a multiplicity of supports configured to be fastened in pairs to opposite sides of a frame of the aircraft, and a monolithic self-supporting floor element comprising at least two longitudinal members, a floor plate arranged on the longitudinal members and a respective connecting element arranged at each end of each of the longitudinal members. The floor element can be fastened to the frame by fastening of each connecting element to a corresponding support, and the floor plate can extend in the direction of the longitudinal members at least between two supports fastened in pairs. Furthermore, an aircraft region comprises such a floor assembly, an aircraft comprises such an aircraft region.

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: 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: 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.