Abstract: A modular aircraft closet including a structural frame having a top, a bottom, an inboard sidewall, an outboard sidewall, an open forward face and an open aft face. A forward panel attaches to the structural frame to cover the open forward face and an aft panel attaches to the structural frame to cover the open aft face. The forward and aft panels can be equipped with an exterior panel feature to customize, brand, reconfigure or retrofit the closet.

Abstract: A flight deck door assembly for an aircraft includes a flight deck bulkhead defining an access opening from a passenger deck area to a flight deck area of the aircraft, a lavatory bulkhead spaced apart from the flight deck bulkhead and defining a lavatory monument, a first lock containment arranged in a first portion of the flight deck bulkhead opposite to a door jamb formed by a second portion of the flight deck bulkhead, a second lock containment arranged in the lavatory bulkhead, and a flight deck door having a door blade hingedly coupled to the door jamb. The flight deck door is configured to latch to the first lock containment in a first closing position and to latch to the second lock containment in a second closing position.

Abstract: Embodiments of the present invention provide systems and methods for disposal of liquid and food into a sink basin. The disclosed system cooperates with and delivers the received waste material to the main waste system on-board the vehicle. This is typically an aircraft waste tank. The system does not require a manual flush, but includes a sensor system that activates drainage of the holding line when the liquid and/or other waste material reaches a certain level therein. The disclosed system combines the functionalities of a common galley sink and a galley waste disposal unit, but occupies only the space envelope of an existing galley sink. The use of an existing galley sink means that no additional space on the countertop is required.

Abstract: An aircraft galley including a trolley stowage provided in a main body of the aircraft galley. A wall of the main body includes a first section delimiting the trolley stowage and a second section. The trolley stowage is convertible between a first operational state, wherein the trolley stowage is adapted to accommodate a first number of trolleys, and a second operational state, wherein the trolley stowage is adapted to accommodate a second number of trolleys. The second number of trolleys is greater than the first number of trolleys.

Abstract: A hand-held emergency vision apparatus comprises an enclosed tubular structure having opposite first and second ends; first and second clear members disposed at respective the first and second ends; the structure including a plurality of tubular members retractable to a shorter length and extendable to one of several lengths, the tubular members are rigid and sealed from the outside air; and a filter operably associated with the tubular structure to filter the outside air such that when the tubular structure is extended from the compact form air the outside air is forced through the filter and clean air enters the tubular structure.

Abstract: Disclosed herein is an overhead passenger service unit (PSU) for a vehicle, comprising: a mounting mechanism for mounting the PSU above at least one vehicle seat; a dynamic seat row marker that provides an indication of a seat position and a status portion indicating a status of a passenger or trip aspect that is readily viewable from a vehicle aisle and is changeable during a trip; and a programmable active display that is readily viewable from a passenger seat and provides trip changeable information about the trip to the passenger.

Abstract: A method of installing an aircraft overhead stowage system includes installing a plurality of bin support rail fittings onto a plurality of bin support rails disposed above a ceiling of a cross-aisle galley complex; positioning a stowage compartment housing supported by a stowage support structure above the ceiling of the galley complex, the stowage compartment housing including a first stowage compartment and a second stowage compartment each movably engaged with and disposed inside the stowage compartment housing; aligning the stowage compartment housing and the stowage support structure with the bin support rails; and fastening the stowage support structure to the bin support rails using the bin support rail fittings such that the stowage compartment housing is structurally supported above the ceiling of the galley complex.

Abstract: An aviation mask is disclosed which includes an augmented reality visor, sensors, and a display computational unit. The sensors are communicatively connected to the augmented reality visor. The sensors detect a portion of a cockpit area of an aircraft that is viewed by an aircraft crew member wearing the augmented reality visor during a vision obscured emergency. The display computational unit is communicatively connected to the augmented reality visor and the sensors. The display computational unit projects a prestored image associated with the portion of the cockpit area in front of the augmented reality visor. Further, the display computational unit superimposes the prestored image over the portion of the cockpit area viewed by the aircraft crew member. The superimposed prestored image being viewed by the aircraft crew member through the augmented reality visor to identify objects in the portion of the cockpit area during the vision obscured emergency.

Abstract: A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

Abstract: An example device includes a processor and a computer-readable medium storing instructions which, when executed by the processor, cause the processor to perform operations for processing non-flight performance related sensor data from a sensor of an aircraft. The operations may include receiving non-flight performance related sensor data from a sensor of an aircraft, determining a condition based upon the non-flight performance related sensor data, selecting a recommended action based upon the condition that is determined based upon the non-flight performance related sensor data, and sending the recommended action to a device of a flight crew member of the aircraft.

Abstract: A controller of an airflow control system is configured to determine a target position of a door of an airflow control assembly, a first flow rate of a first airflow from a recirculated air blower, and a second flow rate of a second airflow from a fresh air blower based at least in part on a target total airflow rate into an interior of a and a target fresh airflow rate into the interior of the cab. The fresh air blower receives a mixture of fresh air and recirculated air based on a position of the door. The controller is further configured to instruct the airflow control assembly to move the door to the target position, instruct the recirculated air blower to output the first airflow at the first flow rate, and instruct the fresh air blower to output the second airflow at the second flow rate.

Abstract: Described are arrangements of seats, which include at least one column having rows of pairs of seats (12A,12B), each seat having a chair position and a bed position. A pair of foot wells (34A,34B) are positioned within an aft side of each row and configured to vertically align with the pair of seats in a next-aft row when the pair of seats are positioned in the bed position. The bed position of a first seat (12A) of the pair of seats is vertically offset from the bed position of a second seat (12B) of the pair of seats so that the first seat has a high bed position and the second seat has a low bed position.

Abstract: An aircraft lighting system includes quantum dot light-emitting diodes (“QLEDs”), including a first QLED of a first color and a second QLED of a second color. The system also includes logic circuitry configured to control the QLEDs to emit light in a first brightness ratio to create a light of a first metamer of a color and control the QLEDs to emit light in a second brightness ratio to create a light of a second metamer of the color.

Abstract: Lavatories on-board a vehicle, and in particular to a lavatory unit for use by persons with reduced mobility on-board a vehicle are described. The lavatory unit includes a lavatory housing structure enclosing a lavatory interior space, a door opening in the lavatory housing structure, a toilet assembly inside the lavatory interior space, and a transition seating support for a user. The transition seating support provides a first transfer position and a second transfer position. In the first transfer position, in an open door state the transition seating support is directly accessible for a person sitting in a wheelchair that is located at least partly outside the lavatory unit such that the person can transfer to the transition seating support and vice versa, and in the second transfer position, a person sitting on the transition seating support can transfer to the toilet assembly and vice versa.

Abstract: An aircraft comprising an air conditioning system for a cabin of the aircraft. The system comprises a mixer unit capable of mixing air that has already circulated in the cabin and fresh air from the engines of the aircraft. The air mixed in this way is then channeled towards the cabin to ventilate it. The aircraft has an airtight bulkhead allowing the cabin to be separated from a rear compartment, in such a manner as to prevent any direct exchange of air between said cabin and said compartment. This airtight bulkhead constitutes a wall delimiting the mixer unit, at least in part.

Abstract: Apparatus and methods provide for a dual pass air flow configuration in an air conditioning system to improve efficiency and performance of the air conditioning system. An air conditioning device includes a pre-conditioned air passage chamber separated from a post-conditioned air passage chamber by an impermeable partition. A coil system separates the pre-conditioned air passage chamber and the post-conditioned air passage chamber from a partially-conditioned air passage chamber. The coil system is configured to receive air from the pre-conditioned air passage chamber and to condition the air passing through the coil system into the partially-conditioned air passage chamber. The coil system is also configured to receive the air from the partially-conditioned air and further condition the air as it passes through the coil system into the post-conditioned air passage chamber.

Abstract: A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor.

Abstract: An environmental control power generation system is provided. The system may include a turbine and a generator. The system may be configured to provide air form a high pressure bleed port and/or a low pressure bleed port to the turbine. The turbine may be configured to reduce the pressure of the supplied air and generate power through the generator. The power may be supplied to an aircraft power distribution system.

Abstract: An environmental control system for an aircraft includes a bleed air system. Also included is a ram air system. Further included is an air pressure and temperature conditioning system, wherein bleed air and ram air are mixed to satisfy a cabin fresh air requirement.

Abstract: The present disclosure includes an electronic circuit breaker for an electrical load in and on-board electrical system of a motor vehicle. The electronic circuit breaker includes a shunt resistor connected at its input side to an input (E) of the electronic circuit breaker, a controllable switching element coupled at its input side to an output of the shunt resistor and at its output side to an output (A) of the electronic circuit breaker, the output being connectable to the electrical load, and a control input (gate). The electronic circuit breaker also includes a voltage detector and a hold element coupled to the voltage detector and configured to hold the control signal in a switched off (out) state when the controllable switching element has switched off the electrical load.

Abstract: An aircraft including a fuselage defining an upper lobe and a lower lobe, the fuselage including a wall structure that includes an outboard boundary and an inboard boundary spaced from the outboard boundary, wherein the outboard boundary and the inboard boundary define a wall volume therebetween, and a barrier sheeting member extending into the wall volume.

Abstract: An Environmental Control System (ECS) which includes a heat exchanger (HX) and an air conditioning unit (ACU) upstream of the heat exchanger. The heat exchanger receives flows of hot air bled from a plurality of aircraft engines and flows of cold ambient air drawn from the aircraft exterior for use by the heat exchanger and the air conditioning unit for heating and cooling the interior cabin of the aircraft. The environmental control system may operate in one of several modes, whether the heat exchanger and air conditioning unit are operating normally or have failed. In a normal mode, the air conditioning unit and heat exchanger operate in series. In an “ACU only” mode, the air conditioning unit operates without the heat exchanger. In an “HX only” mode, the heat exchanger operates without the air conditioning unit. In an “ECS off” mode, both the heat exchanger and air conditioning unit are bypassed.

Abstract: A method of opening a door of a household appliance having a cabinet with an open face providing access to a treating chamber where an article is received for treatment according to a useful cycle of operation is provided. The method includes: sensing a presence of at least a portion of a person, visually indicating and automatically opening the door in response to the sensed presence.

Abstract: A laterally and recline adjustable aircraft passenger seat assembly including a seat, spaced forward and rear rails, a seat recline motion assembly attached to the seat and slidable along the length of the spaced forward and rear rails and including a first actuator dedicated for seat recline motion, and a lateral seat motion assembly disposed between the spaced forward and rear rails and including a second linear actuator dedicated for driving lateral motion of the seat recline motion assembly.

Abstract: A cooling device applicable to an airplane having a pressurized cabin and a ram air channel for cooling an electronic device arranged in the pressurized cabin, is comprised of a partition wall separating the pressurized cabin from the ram air channel; and a heat exchanger thermally in contact with the electronic device and exposed to the ram air channel so as to radiate heat to a ram air.

Abstract: An aviation mask is disclosed which includes a first set of sensors that monitors cockpit ambient air and health of an aircraft crew member for detecting parameters that cause respiratory disorder to the aircraft crew member an oxygen regulator that switches between a dilution mode, an emergency mode, and a recirculation mode to supply respiratory gas to the aircraft crew member, an augmented reality visor, a second set of sensors that detects a portion of a cockpit area that is viewed by the aircraft crew member, and a display computational unit that projects a prestored image associated with the portion onto the augmented reality visor which is superimposed over the portion of the cockpit area. The first set of sensors also monitors aircraft cockpit area for detecting vision obscured emergencies. The superimposed prestored image is used to identify objects in the portion during the vision obscured emergency.

Abstract: An aircraft air-conditioning system including an air-conditioning unit which is designed to provide cooled process air. A process air line conducts cooled process air provided by the air-conditioning unit into a working area of an aircraft cabin. A cooler supplies cooling energy to a device to be cooled which is provided in the working area of the aircraft cabin. Finally, the aircraft air-conditioning system includes a heat transfer arrangement which transfers waste heat generated by the cooler to process air flowing through the process air line.

Abstract: A container for an oxygen supply unit is described. The container may have a container well, wherein a container door can be pivotably joined at a container well's edge, wherein the container is provided with a sensor system, adapted to indicate a status and/or change of status of the door, in particular relative to the well. A system of an arrangement of a number of oxygen supply devices in a ceiling-panel along an aircraft cabin, in particular along an aircraft cabin alley of seats, also is described, wherein each oxygen supply unit is stored in a container.

Abstract: A lavatory monument assembly configured to be positioned in the interior of an aircraft. The modular lavatory monument assembly includes first, second, third and fourth walls that cooperate to form an enclosure that defines a lavatory interior, a door positioned on one of the first, second, third, or fourth walls, and an opening on the fourth side that is open to an exterior of the enclosure. A seat is at least partially positioned in the opening. The seat includes a seat back and a seat portion that is pivotal between a storage position and a deployed position. In the deployed position the seat portion extends outside of the opening.

Abstract: A passenger aircraft (10) comprising a pressurized cabin, which comprises a top volume (13) and a passenger deck (12), the passenger deck (12) comprising at least one passenger compartment (14) separated from the rest of the passenger volume (16) by walls (15), is characterized in that a burstable wall (22) that extends below the ceiling (19) of the passenger volume and defines the passenger compartment (14) is arranged so as to be adjacent to the side wall (20), the space (23) between the burstable wall (22) and the side wall (20) being open towards the top volume (13) and forming a common pressure chamber therewith.

Abstract: An access device enables controlled or secure communication between different areas of an enclosure and, in the example illustrated in the present application of an aircraft, while providing reduced size. The access device includes at least three mobile walls able to move, independently from one another, to form a closed cylinder, the walls thus being in a so-called security vestibule position, and to overlap at least in twos in order to close off access to one or more areas while concealing the security vestibule, the walls thus being in a so-called retracted position. By overlapping at the access level of said areas that the walls allow to close, the device frees up the adjoining cabin space.

Abstract: An emergency vision apparatus for providing an operator visual access to information during a smoke emergency, comprises an enclosure made of airtight material having spaced apart front and rear panels, the front panel being transparent, the front panel including fasteners for attachment to an instrument panel; an image capture device attached to said rear panel, the image capture device being oriented to view the instrument panel through the transparent front panel; an image viewing device for being disposed in front of one of the operator's eyes, the image viewing device being operably associated with the image capture device; and a support structure to support said viewing lens in front of one of the operator's eyes.

Abstract: A sanitary unit for a cabin region on board a vehicle is provided with a first lavatory facility and a second lavatory facility. The first and the second lavatory facilities in each case form a longitudinally-directed interior space comprising two longitudinal sides and two narrow sides. In each case a narrow side comprises an access door. The first and the second lavatory facilities adjoin each other by their longitudinal sides and are separated from each other by a shared middle wall. The shared middle wall extends between lateral connection regions on the narrow sides and comprises at least one offset at least in a middle region between the two lateral connection regions in the horizontal direction.

Abstract: Described are personal electronics device mounting structures including a base (12) with an aft surface, wherein the base is configured to fit substantially within a recess (42) so that the aft surface of the base (12) is substantially flush with an aft surface surrounding the recess (42) in a stowed position, and wherein at least a first portion of the base (12) is positioned aft of the recess and at least a second portion of the base (12) is positioned within the recess (42) in a deployed position, and a cradle (14) coupled to the base, wherein the cradle (14) comprises a pair of arms (22) configured to hold a personal electronics device securely in place adjacent a passenger seat back when the base (12) is in the deployed position.

Abstract: A monument configured to be positioned in the interior of an aircraft that includes first, second, third and fourth sides and first and second lavatories spaced apart from one another by at least a portion of a galley storage section that is open to the first side. The first and second sides are opposite to one another and the third and fourth sides are opposite to one another. The first lavatory defines a first lavatory interior and includes a first toilet therein and the second lavatory defines a second lavatory interior and includes a second toilet therein.

Abstract: Structure mounted airbag assemblies and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present disclosure can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag assembly within the cavity, and an inflator operably coupled to the airbag assembly. The airbag assembly can include an airbag configured to deploy through the opening of the housing during a crash event. The airbag system can further include a door removably positioned across the opening and configured to move away from the opening during airbag deployment. The housing can be affixed to an interior portion of an aircraft, forward of and offset from an aircraft seat.

Abstract: An environmental control system includes an air supply system coupled to an aircraft. The air supply system includes an external air supply device coupled to the aircraft and a supply duct coupled in flow communication to the external air supply device. An air supply outlet is coupled in flow communication to the supply duct and in flow communication with an occupancy zone and/or a floor distribution section. An air recirculation system is coupled to the floor distribution section. The air recirculation system includes a recirculation supply device coupled to the aircraft and a recirculation duct coupled in flow communication to the recirculated supply device and coupled to the floor distribution section. A recirculation outlet is coupled in flow communication to the recirculation duct and in flow communication with the recirculation zone and/or the floor distribution section.

Abstract: A low voltage DC distribution system to provide power to power or charge passenger electronic devices. Cable assemblies pass high voltage power down in daisy chain fashion to various seat groups. Connector elements contain current limiting circuitry which provides low voltage power for distribution to seat electronic components via small gauge wire. Compared to previous systems, embodiments may have a marked reduction in installed weight, encroachment on passenger space, easier installation and reduced impact on seat structures.

Abstract: A gas turbine engine has a fan drive turbine for selectively driving a fan rotor. A drive shaft between the fan drive turbine and the fan rotor includes a clutch, and an electric motor. The electric motor is positioned such that it is not downstream of a flow path relative to the fan drive turbine. A method of operating a gas turbine engine is also disclosed.

Abstract: A vehicle seat includes a seat frame; and a holding member including a mounting portion that is attached to the seat frame. The holding member is attached to the seat frame via the mounting portion and is disposed and configured to hold a held member; the mounting portion is a tubular part projecting from the holding member toward the seat frame; a fastening member projects from one of the seat frame and the mounting portion and is inserted into the other of the seat frame and the mounting portion such that the holding member is fastened and attached to the seat frame; and the holding member includes five or more flat plate-shaped reinforcing portions projecting from the holding member toward the seat frame, and the five or more reinforcing portions are connected to the mounting portion, and are disposed radially around the mounting portion.

Abstract: A nacelle inlet is provided for an aircraft propulsion system. This nacelle inlet includes an outer barrel, a bulkhead and a plurality of supports. The outer barrel extends around an axis and along the axis to an aft end. The bulkhead is within and connected to the outer barrel. An aft portion of the outer barrel projects axially aftward from the bulkhead to the aft end. The supports are disposed around the axis and next to the bulkhead. The supports are configured to support the aft portion of the outer barrel.

Abstract: The disclosure relates to a lighting unit for an aircraft interior having a floor with a baseplate fastenable to structure of the aircraft, and having a receiving region that faces away from the structure in a fastened state. An OLED light source having one or more OLEDs is arranged in the receiving region. The lighting unit also has a lens arranged on a side of the OLED light source facing away from the baseplate, and a frame mechanically retained in the receiving region by plug contacts such that the OLED light source and the lens are fastened in the receiving region. The plug contacts include electrical and mechanical contacts, wherein the OLEDs are supplied with electricity by at least one controllable driver, and wherein the contacts supply electricity to the OLED light source.

Abstract: A method of allocating objects within a plurality of storage bins including monitoring motion within the plurality of storage bins, wherein each storage bin of the plurality of storage bins includes a profile sensor coupled therein, and activating the profile sensor coupled within a first storage bin. The profile sensor activated based on detection of motion within the first storage bin. The method also includes determining, with the profile sensor, an available capacity within the first storage bin, and transmitting an indication of the available capacity within the first storage bin.

Abstract: An aircraft lavatory unit that includes a diaper changing platform has a first side wall and a second side wall located on both sides of a toilet bowl, and a rear surface wall located to the rear of the toilet bowl. Handrails are provided on the first side wall and the second side wall. The diaper changing platform can be pivoted between a stowage position in which it is stowed in a stowage recess in the rear surface wall, and a usage position in which the diaper changing platform is lowered above the toilet bowl. The diaper changing platform is configured so that in the usage position it is supported by placing both sides of the bottom surface on the handrails of the first side wall and the second side wall.

Abstract: A toilet module for a vehicle is provided. The toilet module comprises a housing having a front wall, a first functional wall and at least one second functional wall, which enclose a floor surface on the underside of the housing, and a toilet unit. The front wall comprises an access opening. The first functional wall is arranged opposite the front wall and accommodates the toilet unit. The at least one second functional wall extends between the first functional wall and the front wall and is perpendicular to the front wall. The toilet unit has a longitudinal extension axis which forms an angle which is greater than 0° with the at least one second functional wall. In this way, a particularly narrow and compact toilet module can be provided.

Abstract: A seat system may include a door and a locking mechanism. The door may be movable between an open position and a closed position. The seat system may include a seat mounted to the door and including a seat bottom that may be movable between a stowed position and a deployed position. The seat system may further include a locking mechanism operatively coupled to the seat bottom and configured such that movement of the seat bottom from the stowed position to the deployed position when the door is in the closed position causes the locking mechanism to engage fixed door-frame structure located adjacent the door and to immobilize the door against movement from the closed position. Movement of the seat bottom from the deployed position to the stowed position may cause the locking mechanism to disengage from the fixed door-frame structure and to allow the door to be moved from the closed position.

Abstract: A monument mounted airbag system includes an airbag assembly including at least an airbag mounted directly forward of a passenger, and configured to deploy away from the passenger along an intercepting course with a predetermined path of travel of the passenger. Additionally, the airbag may be configured to substantially conform to a monument disposed in proximity thereto, and may include side support, lower support, and active vents.

Abstract: A passenger supply system installed in a passenger supply channel (PSC) on board a vehicle, such as an aircraft. The supply system comprises a rail track configured to be mounted along the PSC. The supply system further comprises an indiv panel mounted on the rail track and connectable to the PSC for supplying a passenger with conditioned air, medical outlet and/or oxygen. The indiv panel comprises a crossover area. The supply system further comprises a passenger supply unit mounted on the rail track and connectable to the PSC for supplying the passenger with light, visual information and/or sound information. The supply unit comprises an overlapping area. The supply unit and the indiv panel are configured such that in a mounted state of the supply unit and of the indiv panel the overlapping area of the supply unit at least partially overlaps with the crossover area of the indiv panel.

Abstract: A service module for supplying passengers in a passenger space of a means of transport, in particular of an aircraft, and to a service system having a service channel and a plurality of such service modules. The service module comprises at least one service component arrangement having one or more service components for individually supplying one or more passengers, and a cabin lighting unit for illuminating the passenger space of the means of transport, in particular of the aircraft.

Abstract: A high efficiency multifunction power system for an aircraft is provided. The system includes an AC generator and a multifunction power converter-controller module including at least one multifunction power converter-controller. The at least one multifunction power converter-controller is configured to function as a power converter and a controller to perform multiple operation modes.