48results about "Stowage devices" patented technology

A connecting rod coupling device for attaching a component to an aircraft fuselage and / or stiffening the fuselage has a first coupler, and a second coupler couplable to the first coupler. The first coupler has an elongate body with a first channel on a lateral surface along a first longitudinal axis. The second coupler has a hollow-cylindrical portion, which, on an inner face along a second longitudinal axis, has a second channel complementing the first channel. The hollow-cylindrical portion has a radial cutout through which the elongate body is radially insertable into the second channel from outside the hollow-cylindrical portion. The second coupler has a closure body, which closes the radial cutout, and can be positioned removably in the cutout to complete the second channel on a radially internal face. The second coupler also has an element, pushable onto the hollow-cylindrical portion to secure the closure body on the hollow-cylindrical portion.

A locking device (1) for locking a pivotably mounted door (21) of a container (20) in the closed position, with a housing (2), at least one hook (3) for hooking into a holder shaft (26), and an actuating handle (4) for unlocking the hook (3), wherein the at least one hook (3) can be actuated by the actuating handle (4) via at least one driver (6) in such a way that, upon movement of the actuating handle (4), the at least one hook (3) is movable out of the closed position, wherein the actuating handle (4) is freely movable about a predefined angular range (Δα), before the at least one hook (3) can be unlocked, and with at least one display (5) for identifying an incompletely locked state of the door (21), and an overhead luggage compartment (22) with a locking device (1) of this type. The at least one display (5) is arranged on at least one lateral outer surface (15) of the actuating handle (4) and substantially perpendicularly with respect to the second rotational axis (D2) for the actuating handle (4).

A latch system and method are configured to adjustably secure a first component to a second component. The latch system includes a mounting base. A slide plate is moveably coupled to the mounting base. The slide plate is configured to be slidably adjusted relative to the mounting base. A housing is secured to the slide plate. The housing includes an arm channel configured to receive a latch arm. A bumper is coupled to the housing. The bumper is configured to restrain motion of the latch arm within the arm channel.

The invention relates to a storage compartment (2), preferably for an aircraft (1), having: a storage space (3), a storage space flap (9), a flap drive (14), in particular a servomotor, by way of which the storage space flap (9) can be transferred between a closed position, closing a loading opening (8) of the storage space (3), and an open position, releasing the loading opening (8), a gear mechanism (24) with a drive element, in particular with a drive gearwheel (25), which is connected to the flap drive, and with an output element, in particular with an output gearwheel (26), which is connected to the storage space flap (9), wherein the gear mechanism (24) has a blocking means (29), wherein, in the closed position of the flap, the blocking means (29) blocks the rotation of the storage space flap (9) in the direction of the open position, and / or wherein, in the open position of the storage space flap (9), the blocking means (29) blocks the rotation of the storage space flap (9) in the direction of the closed position.

An assembly for an aircraft cabin includes at least one seat unit including a seat and a privacy shell extending at least partially around the seat, a compartment, such as a luggage compartment, at least one isolating curtain added to the compartment, and a removable device for holding the isolating curtain. The removable device being configured to hold the isolating curtain suspended from the compartment, so as to at least partially define a closed rest space around the seat unit and to permit manual detachment of the isolating curtain from the compartment without requiring a tool.

A system 100 for assisting boarding of a passenger aircraft is provided. The system comprises a sensor device 102 arranged to capture sensor data relating to one or more passengers 4 boarding the aircraft and a processing device 104. The processing device is arranged to obtain information relating to the aircraft, use the sensor data to identify one or more luggage items 6 carried by the one or more passengers and estimate a size of each of the one or more luggage items, process the estimated sizes of the one or more luggage items and the information relating to the aircraft using a machine learning algorithm to determine a prediction of whether the luggage capacity in a cabin of the aircraft will be exceeded when all passengers have boarded, and trigger the performance of one or more actions which influence the boarding of the aircraft based on said prediction.

The invention relates to an overhead cabin fitting (1) for an aircraft, comprising: an overhead luggage compartment (3) for luggage; a ventilation device (4) having a housing (5), an air inlet (6), an air channel (7) and an air outlet (8); and a lighting device (9) having lighting elements (10); wherein the ventilation device (4) and the lighting device (9) are each arranged above the overhead luggage compartment (3), and a support (11) on which the lighting elements (10) are arranged is provided at the air outlet (8) of the ventilation device (4).

The present disclosure relates to a cubicle having an attachment system with corner bracket fittings. The cubicle includes a floor, a left panel perpendicular to the floor, a right panel perpendicular to the floor, and an attachment system connecting the floor, the left panel, and the right panel. The attachment system includes a right corner bracket fitting connecting the right panel to the floor, a left corner bracket fitting connecting the left panel to the floor, and a filler panel connected to and extending between the right corner bracket fitting and the left corner bracket fitting.

An arrangement for a tapering rear section of an aircraft passenger cabin (200) including a seat row (204) positioned between an aisle (202) and an exterior wall, and a closet (212) positioned behind the seat row (204). A first portion (214) of the closet extends behind the seat row (204) and a second portion (216) of the closet extends into gap space (210) formed between an outboard side of the seat row (204) and the exterior wall. The closet (212) forms interior space (218) dimensioned to accommodate a folded wheelchair positioned along the exterior wall, and interior space behind the seat row (204). The second portion (216) forms an exterior surface for use by a passenger in the seat row (204), for instance a horizontal surface (230) including a provision for mounting a bassinet (228). The interior space (218) is accessible from the rear facing side of the closet to facilitate stowing and retrieving items from the interior space.

The invention relates to an aircraft seat system with an aircraft seat region (14) which has an aircraft seat (16a; 16b; 16c), which can be adjusted between a seated position and a reclined position, and a console (28a; 28b; 28c) arranged in front of the aircraft seat (16a; 16b; 16c), wherein the console (28a; 28b; 28c) forms an elevated footrest surface (34a; 34b; 34c) which is provided to form part of a reclining surface, wherein the console (28a; 28b; 28c) has a stowage module (46a; 46b; 46c) which has a stowage compartment (48a; 48b; 48c) arranged below the footrest surface (34a; 34b; 34c). According to the invention, the stowage compartment (48a; 48b; 48c) is arranged in a region behind the footrest surface (34a; 34b; 34c) and the stowage module (46a; 46b; 46c) has a cover wall (50a; 50b; 50c) which at least partially delimits the stowage compartment (48a; 48b; 48c) in the region behind the footrest surface (34a; 34b; 34c).

An example method for determining space availability in an aircraft includes receiving outputs from a plurality of laser sensors positioned in a baggage container at a first wall and a second wall, and the first wall and the second wall face each other. The plurality of laser sensors emit signals within the baggage container and detect reflected responses to generate the outputs. The example method also includes receiving images from a camera positioned on a third wall of the baggage container, wherein the third wall differs from the first wall and the second wall, mapping contents of the baggage container based on the outputs from the plurality of laser sensors, based on said mapping, outputting data indicative of occupied space in the baggage container, and associating the images from the camera with the contents of the baggage container.

Described are passenger partitioning systems having multiple divider partitions arranged. A first divider partition is arranged along an longitudinal axis of an passenger aircraft. A second divider partition is arranged along a lateral axis of the aircraft. The passenger partition systems may be used to partition off two or more seats within the passenger aircraft (e.g., to quarantine sick passengers).

A pilot storage system positionable between forward-facing cockpit seats and aft-facing passenger seats in an aircraft cabin. The pilot storage system includes a central cabinet having first and second open sides and an interior storage compartment. A first side cabinet has a first upper storage compartment, a first lower inboard storage compartment with an open side and a first lower outboard storage compartment. A second side cabinet has a second upper storage compartment, a second lower inboard storage compartment with an open side and a second lower outboard storage compartment. The open sides of the first and second lower inboard storage compartments are respectively aligned with the first and second open sides of the central cabinet such that the first and second lower inboard storage compartments and the interior storage compartment form a unified storage compartment that is accessible from the central cabinet.

A repositionable pocket for an aircraft having a rigid pocket wall pivotally attached to the aircraft sidewall and at least one strap assembly connecting the pocket to the sidewall. The strap assembly has a first end fixable to the sidewall and a second end repositionably fastened to the pocket. The strap is preferably made to be elastic and urges the attached pocket into a closed orientation thereby securing any stowed items between the pocket and the aircraft sidewall. Strap adjustability accommodates different sized objects for stowage.

The present invention relates to a removable closure device for closing off a space, in particular for an aircraft cabin, comprising: - a frame (25) comprising a housing (26), and - a movable door (27) able to move translationally with respect to the frame (25), - the removable closure device (21) further comprising a return system (38) comprising a cable reel around which a cable is wound, the cable being connected by one of its ends to the movable door (27), and - a spring system configured to store mechanical energy when the cable is in an unwound state subsequent to a movement of the door (27) towards the deployed position, and to release this mechanical energy so as to automatically return the movable door (27) from the deployed position to the stored position subsequent to the movable door (27) being released.

To provide an air distribution system for use in an aircraft for limiting cross-circulation between passengers.SOLUTION: An aircraft includes a fuselage having a side wall at least partially defining a passenger cabin and a crown section of the aircraft. The passenger cabin includes an overhead zone, a passenger zone, and a floor zone. An air supply duct is positioned within the crown section, and the air supply duct is configured to pressurize the crown section with air. At least one return air outlet is defined in the floor zone. An interior structure is coupled to the side wall and extends between the passenger cabin and the crown section. The interior structure includes a plurality of nozzles oriented to discharge the pressurized air from the crown section along an airflow path that extends downward through the overhead zone, downward through the passenger zone, and then towards the at least one return air outlet.SELECTED DRAWING: Figure 1

In order to allow length tolerance compensation, the invention proposes a coupling system (30) for connecting a first component and a second component is provided. The coupling system comprises a longitudinal axis (L), a first part (31) for the first component, wherein the first part comprises first interlocking means (34) and a second part (32) for the second component, wherein the second part comprises second interlocking means (36). The first part and second part are slidably engageable along the longitudinal axis to provide length compensation. The first interlocking means comprises a plurality of first members (38) that are spaced apart in the direction of the longitudinal axis and the second interlocking means comprises a plurality of second members (42) that are spaced apart in the direction of the longitudinal axis. Upon relative rotational movement about the longitudinal axis the first members frictionally engage with the second members to couple the first part and the second part.

A storage compartment (4) for an aircraft (2) comprises a base body (8) and a pivotable swivel compartment (10) therein, and a spring unit (14) coupled between them, wherein in an active state (AZ) a spring element (16) generates a closing force on the swivel compartment (10) by relaxing its spring unit (14), which is prevented in a passive state (PZ), and an activation unit (30) with an activation element (34) which activates the passive state (PZ) in a pre-tensioned zero position (NP) and the active state (AZ) in an activation position (ZP), wherein the activation unit (30) has a locking element (50) for the activation element (34) that is pre-tensioned to a locking position in the activation position (ZP), and wherein the activation unit (30) has a release element (60) for the locking element that can be actuated from a pre-tensioned rest position (RS) to a release position (LS). (50) exhibitswherein in the rest position (RS) locking of the switching element (34) in the switching position (ZP) by the locking means (50) is enabled and prevented in the release position (LS). An aircraft (2) with a base structure (6) contains the storage compartment (4), wherein the base body (8) is fixed to the base structure (6).

The present invention mainly relates to an assembly for an aircraft cabin (10), comprising: - at least one seat unit (11) comprising a seat (12) and a privacy shell (13) extending at least partially around the seat (12), - a compartment (18), such as a luggage compartment, and - at least one isolating curtain (21) added to the compartment (18), - a removable device (20) for holding the isolating curtain (21) being configured so as to hold the isolating curtain (21) suspended from the compartment (18), so as to at least partially define a closed rest space around the seat unit (11) and to permit manual detachment of the isolating curtain (21) from the compartment (18) without requiring a tool.

Systems, methods, and devices for configuring and using on-board luggage space availability indicators are provided. An example method includes initializing multiple sensors, each of which includes a receiver, in an interior space of an overhead bin, using the receiver in each of the multiple sensors to acquire a signal, and determining, based on the received signals, an amount of empty space corresponding to a respective sensor of the multiple sensors. Based on the amount of empty space indicated by each of the multiple sensors, one of multiple visual indicators is selected. Herein, each of the multiple visual indicators is indicative of a different available capacity of the overhead bin, e.g., a first visual indicator indicates the overhead bin is empty, whereas a last visual indicator indicates the overhead bin has no more space for additional luggage. The overhead bin visual indicator is then displayed using a light-emitting means.

A fastening system for securing a component in a cabin is proposed, comprising a first longitudinal beam (12), at least two pairs (14, 16) of two support elements (20), and several structural connectors (18), wherein the pairs of support elements can be connected to the longitudinal beam and the structure such that they extend triangularly between the first longitudinal beam and the structure, wherein two ends (22) of the support elements of each pair are spaced apart from each other and the support elements converge from these ends, wherein the longitudinal beam has at least one first fastening unit for connecting each support element to the longitudinal beam, wherein the support elements of each pair can be connected to the structure by means of at least one of the structural connectors.and wherein the length of at least one of the support elements of each pair is adjustable and / or at least one first fastening element is arranged on the longitudinal beam at an adjustable fastening position, such that the pair of support elements in question can assume an adjustable triangular shape to bridge a tolerance gap formed between the longitudinal beam in question and the structure.

The invention relates to a seat (22) of a vehicle (10) comprising a seat bottom (26), a backrest (28) fixed to the seat bottom (26), and at least one leg (32) supporting the seat bottom (26), the leg (32) comprising at least three segments (44, 46, 48) comprising a first segment (44) fastened to a lower surface (40) of the seat bottom (26), a second segment (46) fastened to a floor (20, 21) of the vehicle (10), and a third segment (48) connecting the first segment (44) and the second segment (46), the third segment (48) being arranged such that the leg (32) can define a housing (50) between the seat bottom (26) and the floor (20, 21), the housing (50) being able to accommodate at least one piece of hand luggage (52) such that it projects by no more than 100 mm relative to a front edge (34) or a rear edge (36) of the seat bottom (26).

To provide a system and a method for determining and displaying a used capacity in an overhead storage shelf.SOLUTION: Provided is a system used for determining a capacity of a storage shelf 104. The system includes a plurality of sensors 112 positioned within the storage shelf. Each sensor is configured to determine a used capacity within a portion of the storage shelf, and generate a voltage output value based on the determined used capacity, where the plurality of sensors is configured to generate a total voltage output value based on the voltage output value of each sensor. A controller is in communication with the plurality of sensors. The controller is configured to receive the total voltage output value from the plurality of sensors, determine a minimum voltage output value and a maximum voltage output value of the plurality of sensors, and determine a total used capacity of the storage shelf as a function of the total voltage output value, the minimum voltage output value, and the maximum voltage output value.SELECTED DRAWING: Figure 3

A passenger supply system for an aircraft. The passenger supply system has a passenger supply channel, a passenger service unit having a main body, and an infill panel. A portion of the main body of the passenger service unit overlaps an end of the infill panel. Also an aircraft with such a passenger supply system.

The present disclosure relates to a lightweight overhead stowage compartment (OHSC, 100) comprising a self-supporting hull (110) having an open cross-section forming a stowage space and an opening (105) to the stowage space, wherein in a longitudinal direction of the self-supporting hull (110) any section of the self-supporting hull (110) has an open end in the front and rear. The OHSC includes a vertical connector (137) configured to be placed into the stowage space, wherein the vertical connector (137) is mounted to the self-supporting hull (110) at vertical sides of the vertical connector (137) in a force transferring manner. At least one lid (150) is mounted at an arbitrary section of the self-supporting hull (100) and configured to close the opening (105) to the stowage space.

A latch mechanism for a lid of an overhead stowage compartment. The latch mechanism comprises a plurality of locking members, and a plurality of latches. Each latch is configured to engage one of the locking members, wherein the plurality of latches is configured to be mounted into a bottom of the overhead stowage compartment, and wherein the plurality of locking members is associated with a single lid of the overhead stowage compartment.