Abstract: An aircraft monument for installation in an aircraft cabin comprising a sanitary module. The sanitary module comprises a toilet which is adapted to be used as a sanitary facility for passengers when an aircraft equipped with the aircraft monument is in cruising flight. The toilet is further adapted to be used as a flight attendant seat if necessary. The aircraft monument also comprises a door opening which is adapted, when the aircraft monument is installed in an aircraft, to give a person sitting on the toilet which is being used as a flight attendant seat an unimpeded view of an area of the aircraft cabin which is arranged in front of the aircraft monument in the direction of viewing of the person sitting on the toilet which is being used as a flight attendant seat.

Abstract: An aircraft monument for installation in an aircraft cabin comprising a first functional module, a second functional module and a side wall for delimiting the first module from at least one of a region of the aircraft cabin adjacent to the first module and a region of the aircraft monument adjacent to the first module. The side wall is movable between a first and a second operational position and comprises a first side-wall region separating the first and second functional modules and in the second operational position, the side wall is displaced in the direction of the second module relative to its position in the first operational position, so that a movement of the side wall from its first operational position into its second operational position results in an enlargement of a base area of the first module and a corresponding diminution of a base area of the second module.

Abstract: A no touch lavatory has a first sensor outside the lavatory that is operable to cause a motor assembly to open the door of the lavatory in response to a person making a motion in close proximity to the first sensor, a second sensor inside the lavatory that causes the motor assembly to close the door and causes a lock to lock the door in response to the second sensor detecting the person entering the lavatory, and a third sensor inside the lavatory that causes the lock to unlock the door and causes the motor assembly to open the door in response to the third sensor detecting a motion made by the person inside the lavatory.

Abstract: A crew bunk system may include a bunk frame assembly and at least two vertically spaced crew berths. Each one of the crew berths may have a lengthwise hinge line dividing the crew berth into a stationary panel and a foldable panel. The stationary panel may be fixedly coupled to the bunk frame assembly. The foldable panel may be hingedly coupled to the stationary panel along the hinge line. The crew bunk system may include at least one connecting member interconnecting the foldable panels such that the foldable panels pivot in unison between a deployed position and a stowed position. The crew bunk system may include a latching mechanism configured to lock the foldable panels in the stowed position.

Abstract: An aircraft power distribution architecture includes a power rail extending generally along the length of an aircraft for receiving power from a generator, and for distributing power through plug-in modules located along the length of the power rail.

Abstract: An emergency vision apparatus for providing an operator in a station visual access to information during a vision-obscuring emergency, comprises an expandable first enclosure filled with clear air, the first enclosure having front and rear transparent panels to allow an operator visual access through the first enclosure to a first source of information disposed in front of the front panel; an expandable second enclosure filled with clear air, the second enclosure having a rear panel and a transparent front panel for being disposed in proximity to a second source of information; a first camera disposed at the rear panel of the second enclosure, the camera being directed toward the front panel to image the second source of information through the second enclosure front panel; and a first display operably connected to the camera, the display being operably associated with the first enclosure to be visible to the operator through the first enclosure rear panel.

Abstract: A luggage compartment for a means of transport and a means of transport with a luggage compartment are provided. The luggage compartment comprises a housing with a pivotably attached connecting element and with a sliding element. The connecting element is adapted for being pivotably attached to a first structural element and the sliding element is adapted for moving along a rail connected to a second structural element. The luggage compartment is easy to manufacture and to maintain.

Abstract: The Invention relates to a passenger cabin emergency oxygen device for an aircraft, comprising at least one electrically driven activation device for activating the emergency oxygen device, at least one energy storage device and a source of electrical energy. Said source of electrical energy and said energy storage device are coupled together for substantially constant energy transmission from the source of electrical energy to the energy storage device at a first energy level, an activation device and a controller are coupled together for signal transmission from the controller to the activation device, said activation device and said energy storage device are coupled together for energy transmission from the energy storage device to the activation device at a second energy level which is higher than the first energy level.

Abstract: A mounting system (10) for attaching a structural monument in a desired position in an aircraft cabin comprises a support element (12) that is connectable to a base body (14) of the structural monument in a pedestal area of the structural monument. The mounting system (10) further comprises a receiving device (50) that is attachable in an area of a floor of the aircraft cabin, and a first coupling element (38) attached to the support element (12), designed for connecting the supporting element (12) to the receiving device (50) that is attachable in an area of a floor of the aircraft cabin. Finally, the mounting system (10) comprises a retaining element (76) that is connectable to the base body (14) of the structural monument in a ceiling area of the structural monument, and a second coupling element (86) attached to the retaining element (76), designed for connecting the retaining element (76) to a structurally solid component of the aircraft.

Abstract: A method and apparatus for a hierarchical access system for a compartment. The hierarchical access system comprises a moveable barrier, a locking mechanism, and a control unit. The moveable barrier is capable of preventing access to at least one of a first space and a second space in the compartment in the lavatory when the moveable barrier is in a closed position. The locking mechanism is capable of securing the moveable barrier in the closed position. The control unit is capable of unlocking the locking mechanism in a manner that provides different levels of access to the first space and the second space in the compartment in response to receiving an access request.

Abstract: The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve.

Abstract: The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.

Abstract: There is provided a hanging partition. The hanging partition comprises at least one flexible, hanging panel having a plurality of pleats, each pleat having a hemmed portion. The hanging partition further comprises a plurality of magnets positioned within two or more of the hemmed portions. The hanging partition further comprises a plurality of hanging elements for suspending the hanging panel from a longitudinal hanging device. The magnets are aligned with respect to each other to cause a magnetic attraction between adjacent magnets in order to hold the hemmed portions together when the hemmed portions overlap when the hanging partition is in a retracted position.

Abstract: A direction controlled service apparatus may include a mounting assembly, a housing assembly configured to operably connect to the mounting assembly, the housing assembly being movable with respect to the mounting assembly, and a plurality of actuators connected between the mounting assembly and the housing assembly, each actuator of the plurality of actuators being configured to contract upon a current being applied to the actuator to rotate the housing assembly with respect to the mounting assembly.

Abstract: A method and apparatus are provided for at least partially environmentally isolating a volume, such as by environmentally isolating the cargo compartment from the passenger compartment of an aircraft. In the context of an apparatus, a barrier curtain is provided that partially defines the volume. The apparatus also includes a cable extending along one or more walls that partially define the volume. The barrier curtain is supported by the cable. The apparatus may also include a cable release mechanism attached to a respective wall. The cable is carried by the cable release mechanism and the cable release mechanism is configured to fail at a predetermined load, thereby permitting the barrier curtain to drop in response to a decompression event.

Abstract: Embodiments of the invention provide a breathing mask for aircraft crewmember. The breathing mask includes an on-demand regulator with an inlet connected to a source of breathing gas and an outlet to exhaust the breathing gas. The outlet has an aperture controlled by a movable valve having an open position when the crewmember breathes out and a closed position when the crewmember breathes in. The breathing mask also has a latch member operable by a crewmember to latch the valve in the open position, the latch member including an unlocking member to release the valve when the cabin pressure is below a predetermined value.

Abstract: An aircraft including a fuselage that includes a floor extending in the longitudinal plane of the fuselage and separating a first space from a second space accommodated in the fuselage. The first space includes a fuselage portion having a length essentially equal to the width of the floor along the fuselage cross-section, and the distance between the fuselage portion and the floor is essentially constant along the width.

Abstract: A movable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end and an ingress/egress location at a second end, and a seat that travels along the predetermined path between the operational location and the ingress/egress location, wherein the seat has an operational orientation at the operational location and an ingress/egress seat orientation at the ingress/egress location; the ingress/egress seat orientation being substantially angled relative to the operational seat orientation. Another moveable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end, an ingress/egress location at a second end, and a standby location along the path there between; and a seat that travels along the predetermined path between the operational location, the standby location, and the ingress/egress location; wherein the position of the seat is adjustable at the operational location.

Abstract: The present invention relates to a removable support (10) for optional equipment (6) on an aircraft (1). The support (10) comprises an elongate beam (20) fitted with at least one attachment point for a piece of equipment and extending from a first end portion (21) to a second end portion (22), and the support (10) is provided with first fastener means (30) provided with a first fastener arm (31) connected to a first link arm (32) that is releasably fastened to the first end portion (21), and with second fastener means (40) provided with a second fastener arm (41) connected to a second link arm (42) that is releasably fastened to the second end portion (22), a first support rod (34) also connecting the first fastener arm (31) to the first link arm (32), and a second support rod (44) also connecting the second fastener arm (41) to the second link arm (42).

Abstract: Integration of supply functions is provided in a storage compartment. In particular, an integrated module is provided, which can be mounted in the overhead area of a passenger cabin, and exhibits different system components, which are automatically hooked up to the supply system of the transport (e.g., an aircraft) during the mechanical installation of the module on the load-bearing structure of the cabin.

Abstract: An aircraft having a cockpit, said cockpit including a canopy provided with transparent surfaces fastened to bars, a central console, and two seats arranged transversely on either side of the central console. The aircraft includes at least one support (31, 33) connected to the central console and at least one display unit for displaying multiple indications for assisting piloting, each display unit being carried by at least one support (31, 32, 33, 34) interposed between a bar and a theoretical position of the eye of a person sitting on one of said two seats, each support (31, 32, 33, 34) visually masking a bar at least in part, in order to optimize the visibility to the outside of the cockpit as made available to that person, the theoretical position being defined by the manufacturer.

Abstract: A space saving aircraft wheelchair accessible lavatory for a passenger aircraft interior cabin includes an exterior wall having a first portion spaced apart from an emergency exit path a sufficient distance to define a space for a crew member to assist passengers exiting the airplane in an emergency. A second portion of the exterior wall is offset relative to the first portion of the exterior wall, such as to provide a space within the lavatory for the temporary placement of a wheelchair, or for installation of an amenity. An attendant seat is also provided adjacent to the exterior wall and the emergency exit path.

Abstract: A lavatory monument assembly configured to be positioned in the interior of a vehicle. The lavatory monument assembly includes an enclosure that defines a first lavatory interior and includes at least a front wall and first and second side walls extending rearwardly from the front wall. The first lavatory interior includes a urinal positioned therein. The lavatory monument assembly also includes a first storage compartment positioned in the first lavatory interior. The first storage compartment includes a first storage door that is movable between an open position and a closed position. The front wall includes a first lavatory door that is movable between a closed and an open position and provides access to the first lavatory interior.

Abstract: A baggage compartment for an aircraft is provided. The compartment has a housing and a baggage holder swivel-mounted in the housing. The baggage holder is moveable from a closed position into an open position with a first swivel movement to open the baggage. The baggage holder is moveable from the open position into the closed position with a second swivel movement to close the baggage. The compartment also has a swiveling device for moving the baggage holder into the open or closed position by performing the first or second swivel movement.

Abstract: Sensor pod attachment assemblies are provided for attaching a sensor pod containing airborne sensor equipment to an aircraft fuselage. The sensor pod assemblies may include fore and aft pairs of attachment pylon assemblies each having a lower end attached to the aircraft fuselage and an upper end attached to the sensor pod. The fore pair of attachment pylon assemblies can include port and starboard pylon structures, and a cross-support base connected to upper ends of the port and starboard pylon structures. The aft pair of attachment pylon assemblies may include a lengthwise adjustable spar assembly.

Abstract: A multifunctional module is provided for a passenger services conduit in an aircraft. The multifunctional module includes, but is not limited to a first interface and at least one utility unit for providing a passenger with services. The first interface is for connecting the utility unit to the passenger utility conduit, the interface, for example, being designed as a mechanical interface.

Abstract: An integrated aircraft galley structure includes a service module having a plurality of galley inserts including at least one oven and at least one refrigeration unit. The service module is formed with a plurality of bays sized to receive the plurality of galley inserts, along with a human machine interface for controlling all of the galley inserts. The service module further includes a plurality of galley insert modules for controlling each galley insert, and an insert power and control unit for each galley insert for controlling power to said insert. The entire system is controlled by a galley power and control unit for controlling each of the insert galley power and control units, and an AC distribution unit for distributing power to the insert power and control units.

Abstract: An overhead luggage compartment for a vehicle cabin is provided. The compartment has a ledge pivotably held about a pivot axis in a housing half-shell. The ledge is connected to the housing half-shell through a damper for damping a pivoting movement. One end of the camper is attached to a ledge side wall. The other end of a damper is attached to a damper fastening element. The damper fastening element is rotatably attached to the ledge side wall about the pivot axis. A damper mating fastening element corresponding to the damper fastening element is fixedly attached to a housing half-shell side wall opposing the ledge side wall. With an engagement of the damper fastening element in the damper mating fastening element, a connection, which is fixed in terms of rotation, is made between the damper fastening element and the damper mating fastening element.

Abstract: An aircraft that includes a cabin that has a floor, side walls, a ceiling and an interior, a first class section positioned in the interior that includes a longitudinally extending first aisle extending therethrough, a first door positioned fore of the first class section, an economy class section positioned in the interior and aft of the first class section, and a longitudinally extending second aisle that extends parallel to the first aisle and that does not extend through the first class section. An economy class passenger that enters through the first door travels down the second aisle to enter the economy class section and never enters the first class section.

Abstract: Disclosed herein is a divider utilized to provide part of a visual separation between sections of a passenger cabin of a commercial aircraft, the divider comprising several components. One component is a support arm fixedly connected to the frame of an aircraft above a passenger seat. Another component may be a curtain attached to a lower edge of the support arm and projecting vertically below the support arm. Yet another component may be a rigid view block adjacent the face of the luggage stowage compartment and configured to move therewith such that the view block is adjacent the face of the luggage stowage compartment while the luggage stowage compartment is in a closed position, and repositions with the face of the luggage stowage compartment when the compartment is opened.

Abstract: An on-board supply system (10) for use in an aircraft comprises a fuel cell unit (20) for generating electrical energy and heat energy, and at least one consumer system (100). The fuel cell unit (20) is designed to release heat energy in the form of hot air, and the consumer system (100) is designed to absorb the electrical energy and the heat energy in the form of hot air. The fuel cell unit (20) can comprise at least one low-temperature (LT) fuel cell (30) and at least one high-temperature (HT) fuel cell (40), which can both (30, 40) be designed to be regulated to their respective operating temperature in operation by means of air cooling, and an air cooling inlet (44) of the HT fuel cell (40) can be connected in fluid communication with an air cooling outlet (36) of the LT fuel cell (30).

Abstract: An interface system for use in an aircraft galley includes a first connection element. The first connection element can be connected via a first appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a first galley appliance, and can be connected via a second appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a second galley appliance. Further, the first connection element can be connected via an aircraft galley connection apparatus to a complementary aircraft galley connection apparatus of a second connection element of the interface system. The second connection element can be fixed in a compartment in the aircraft galley, so as to connect the first connection element to an electrical system, a freshwater supply system and a wastewater disposal system.

Abstract: Disclosed herein is a divider providing part of a separation between sections of a passenger cabin of a commercial aircraft, the divider comprising several components. One component may be a support arm connected to the frame of an aircraft above a passenger seat, the support arm having an outer edge facing the aisle of the passenger cabin, and an inner edge which is adjacent the face of a luggage compartment when the bucket is in an open position. Another component may be a curtain attached to a lower edge of the support arm and projecting vertically below the support arm. Yet another component may be a rigid view block adjacent the face of the compartment and configured to reposition such that the view block is adjacent the face of the compartment while the compartment is in a closed position, and repositions when the compartment is opened.

Abstract: A cladding apparatus is provided for the interior of an aircraft that includes, but is not limited to at least one two-dimensional fabric sheet, at least one guide device, and at least one tensioning element. The guide device is configured to be attached in the interior along a direction of extension of the interior, and slidably guide the fabric sheet at least in a first section of the interior along the direction of extension. The tensioning element is, furthermore, configured to be attached in the interior, and by producing a tensile force that acts on the front edge and/or the rear edge of the fabric sheet to stretch taut the fabric sheet along the direction of extension of the interior.

Abstract: A cabin equipment component connection system for an aircraft comprises a plurality of connecting elements, which are adapted to be connected to a cabin equipment component in order to connect the cabin equipment component to a higher-level system of the aircraft. In at least one zone of the cabin equipment component connection system, a number and an arrangement of the connecting elements in the cabin of the aircraft are selected such that cabin equipment components that are provided in a first number and/or a first arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system, and that cabin equipment components that are provided in a second number and/or a second arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system.

Abstract: A combination lavatory and galley arrangement for aircraft includes a lavatory portion having adjacent inboard and outboard lavatories, and a galley portion, and can be located aft of aft aircraft aft doors, and can at least partially rearwardly extend into the aircraft's aft pressure dome. The inboard and outboard lavatories can be separated by a movable wall or partition to provide access for persons with restricted mobility, and can be provided in a modular housing to facilitate retrofit assembly within an aircraft. The movable wall can be an articulating movable lavatory partition movable between a first, linearly extended configuration and a second, folded configuration in a stowed position to provide entry for persons with restricted mobility.

Abstract: An aircraft monument for installation in an aircraft cabin comprising a sanitary module having a sanitary fitment, and a galley module arranged adjacent to the sanitary module. The galley module comprises a trolley parking place and a work surface. The trolley parking place is separated from the sanitary module by a partition wall.

Abstract: A device for mixing at least two separate streams of components which, when mixed, form a combined fluid stream. The device comprises a conduit with at least two separate passageways leading to exit openings at an end face of the conduit. Each passageway communicates with a separate component stream and is arranged to direct the separate component stream in a downstream direction. The exit openings each have a predetermined cross-sectional flow area. A separate channel is located at a downstream end of each passageway exit opening. The channels are arranged to redirect the flow from each passageway to an axial direction. A single mixing chamber communicates with all of the separate channels, the mixing chamber being arranged to receive each of the component streams at an upstream end thereof and to permit a mixing of the component streams. An outlet is arranged downstream of the mixing chamber through which the combined fluid stream is dispensed.

Abstract: A movable storage compartment for a passenger cabin comprises a housing and fixing structures on the side walls of the housing, the housing being open on one side and being able to be moved back and forth between an open and a closed position, that is to say being able to be opened and closed. The fixing structures are formed in such a way that during a movement from the open position to the closed position the housing can be moved first predominantly rotationally and then predominantly translationally upwards.

Abstract: An overhead luggage compartment for a passenger aircraft is provided. The overhead luggage compartment has a receptacle which has a base and two side walls extending from the base. The receptacle can be moved from a closed position into an open position. A device for adjusting a maximum opening width of the receptacle is provided on at least one of the side walls.

Abstract: An internal wall in an aircraft cabin separates a lavatory and a galley of the aircraft. The internal wall has an intermediate notch that increases a lateral width dimension of the lavatory above the notch and thereby improves the spatial environment of the lavatory.

Abstract: A method and apparatus for assisting movement of a bin into a closed position. An assistance system associated with the bin may be activated in response to a manipulation of a switch associated with the bin. The assistance system may comprise a biasing system and a switch. The biasing system may be configured to generate a force in a direction towards a closed position for the bin. A switch may be connected to the biasing system and configured to activate the biasing system when a selected amount of weight is present in the bin. The force in the direction towards the closed position for the bin may be generated in response to activating the assistance system.

Abstract: The invention concerns an aircraft comprising a cockpit situated outside the nose of the aircraft. The cockpit is situated in a lower part of a fin, the latter advantageously extending to a front end of the aircraft. Preferably, the aircraft has a lancet-shaped nose.

Abstract: A paneled partition assembly is disclosed that can be used to selectively separate a first space from a second space. The paneled partition assembly can cover an opening when in a closed and extended position and uncover the opening when in an opened and retracted position. The paneled partition assembly can include a first panel and a second panel configured such that rotation of a handle on the first panel causes linear movement of the second panel. The partition assembly can include a pair of mating assemblies that selectively move from open and retracted positions on opposite sides of an opening to closed and extended positions in which opposite leading edges abut one another.

Abstract: A partition configured to be positioned within an aircraft. The partition includes a first divider wall having a first wall portion and a first divider assembly. The first divider assembly includes a first lighted member and first lighting for illuminating the first lighted member. The partition also includes a second divider wall that is spaced apart from the first divider wall. The second divider wall includes a second wall portion and a second divider assembly that includes a second lighted member and second lighting for illuminating the second lighted member.

Abstract: The present invention relates to an aircraft cockpit with a double flight deck in which a central pane of a windscreen can be removed in order to at least partially clear an opening in order to constitute an emergency exit and ensure natural ventilation of the cockpit. Moreover, a central portion of a glare shield and of a flight station instrument panel are optionally moveable in order to facilitate access to the opening in the event of the need for emergency evacuation.

Abstract: The invention concerns an aircraft comprising a fuselage, a cockpit (10) and a cabin (11), characterized in that the cockpit (10) is situated below the cabin (11), outside the nose of the aircraft. the cabin (11) advantageously extends to a front end of the aircraft. Preferably, the aircraft has a lancet-shaped nose.

Abstract: An aircraft may include a cabin having a first portion, a second portion, a first ramp and a second ramp. The first portion of the cabin may include an upper deck and a lower deck. The upper deck and the lower deck may be disposed proximate to each other with vertical separation therebetween. The second portion may include an intermediate deck disposed in a plane that is substantially parallel to planes in which the upper deck and the lower deck lie. The intermediate deck may be vertically separated from both the upper deck and the lower deck. The first ramp may extend between the lower deck and the intermediate deck to provide access therebetween. The second ramp may extend between the upper deck and the intermediate deck to provide access therebetween.

Abstract: A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

Abstract: A partition configured to be positioned within an aircraft. The partition includes a first divider assembly that includes a first wall portion having a first jamb member secured to an inboard surface thereof and a first door hingedly connected to the first jamb member. The first jamb member includes first lighting that illuminates the first door, and the first door is movable between a stowed position and a deployed position. The partition also includes a second divider assembly that includes a second wall portion having a second jamb member secured to an inboard surface thereof and a second door hingedly connected to the second jamb member. The second jamb member includes second lighting that illuminates the second door, and the second door is movable between a stowed position and a deployed position. The second door is spaced apart from the first door.