97results 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 fastening system for attaching a component to a fuselage structure in the interior of an aircraft is proposed, comprising several rigid retaining elements for attachment to the fuselage structure, a position compensation device on each of the retaining elements, at least one elongated base body connectable to the retaining elements, and at least one fastening element connectable to the base body and a component to be fastened, wherein the retaining elements each have at least one structural support for connection to the fuselage structure and a receiving holder for receiving the position compensation device, wherein the position compensation device has a first position compensation bushing and a second position compensation bushing, wherein the first position compensation bushing is rotatably arranged in the receiving holder and has an eccentric first bore.wherein the second position compensation bushing is rotatably arranged in the first position compensation bushing and has an eccentric second bore, wherein the base body extends through and is held in the second opening, and wherein the base body has first connecting means along at least half of its length which are complementary to second connecting means of the at least one fastening element, such that the at least one fastening element can be connected to the base body at different positions.

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.

A system and a method for measuring the loading status of various storage areas are disclosed including a camera system configured to capture video or images of a storage area, one or more processing modules configured to receive image or video data from the one or more camera of the camera system, determining unoccupied volume of the storage area based on the received image or video data, use the determined unoccupied volume of the storage area to provide output data, and use the output data to provide an optimized storage arrangement for objects, wherein the optimized storage arrangement can be displayed. The system may include a mobile device or other device with a display configured to display the output data and / or indicia based on the optimized storage arrangement.

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).

A bidirectional latching device for securing a cargo in a vehicle may have a latch catch assembly and a latch head. The latch catch assembly may selectably engage with the latch head. When engaged with the latch head, the latch catch assembly may lock the latch head in position to resist movement and the latch head may secure the cargo in the vehicle. When disengaged from the latch head, the latch catch assembly may release the latch head and the latch head may move to a stowed position. The latch catch assembly may lock the latch head to resist movement in one or more directions of movement. The latch head may be shaped to secure the cargo in the vehicle in at least two directions. Thus, cargo may be secured more efficiently by requiring a reduced number of latch devices because the disclosed latch device is bidirectional.

To provide systems and methods for determining a state of components, for example, stowage bin assemblies, within an internal cabin of a vehicle.SOLUTION: A system 100 includes one or more components 102 within an internal cabin 104 of a vehicle 106. An imaging device 108 obtains an image of the one or more components 102. A state determination control unit 112 includes a processor. The state determination control unit 112 is in communication with the imaging device 108 and receives image data 122 including the image from the imaging device 108. Further, the state determination control unit 112 determines a state of the one or more components 102 based on the image data 122.SELECTED DRAWING: Figure 1

A stowage bin lighting assembly for mounting to an internal cabin of a vehicle includes a chassis having a plate extending longitudinally between ends. The chassis supports light mount pedestals, wire standoffs, and at least one valance support above the upper surface. The stowage bin lighting assembly includes a light mounted to the light mount pedestals positioned above the plate by the light mount pedestals for providing lighting from the stowage bin assembly to the internal cabin of the vehicle. The stowage bin lighting assembly includes a wire electrically connected to the light to supply power to the light and coupled to at least one of the wire standoffs to control a position of the wire relative to the plate. The stowage bin lighting assembly includes a valance coupled to the valance mount pedestals configured to be coupled to the stowage bin assembly by the valance support.

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).

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

To provide aircraft sanitization systems and devices.SOLUTION: An aircraft sanitization system includes: a frame; and a tray operatively coupled to at least first two corners of the frame and is rotatable about a pivot axis. The tray is configured to be in one of a locked state and an unlocked state based on rotation about the pivot axis. In the unlocked state, the tray is at an angle greater than zero with respect to the frame; and, in the locked state, the tray is at an angle equal to zero with respect to the frame. The aircraft sanitization system further includes a set of ultraviolet (UV) light emitting diodes (LEDs) attached on an exposed surface of the frame, where the set of UV LEDs is configured to sanitize the tray when the tray is in the locked state.SELECTED DRAWING: Figure 1

A strongback (200) is within the internal cabin (100, 202) of an aircraft (10). A first stowage bin (204, 206) is configured to couple to the strongback (200). The first stowage bin (204, 206) has a first size and a first shape. A second stowage bin (204, 206) is also configured to couple to the strongback (200). The second stowage bin (204, 206) has a second size and a second shape. One or both of the first size differs from the second size, or the first shape differs from the second shape. The strongback (200) is configured to interchangeably receive and retain the first stowage bin (204, 206) and a second stowage bin (204, 206).

The invention relates to a hinge assembly (1; 1 '; 1001, 1002; 2001) for pivotably coupling two components in an aircraft or spacecraft cabin, in particular for pivotably attaching a door (107) of an overhead storage compartment (102). The hinge assembly comprises: a first hinge component (2; 1002, 1003; 2002) and the second hinge part (3; 1003, 1004; 2003) arranged and coupled to be pivotable relative to each other about a hinge axis (A), an elastic element (5; 1005) capable of providing an elastic torque about the hinge axis (A), and a torque adjuster (6; 6 ', 6a', 6b '; 1006, 1007; 2006). The elastic element is coupled in a torque-transmitting manner to each of the first hinge part and the torque-adjusting member. The hinge assembly comprises form-fitting engagement means (7; 7 '; 1007, 1007; 2007) configured to maintain a form-fitting engagement by elastic action in order to prevent rotation of the torque adjustment member at least in the first direction of rotation (R1), and the form-fitting engagement means are disengageable against elastic action in order to enable the torque adjustment member to overcome the torque adjustment member (200) caused by the elastic element (5; 1005) in a second direction of rotation (R2) opposite the first direction of rotation (R1) in order to apply a torsional preload to the elastic element.

To provide aircraft sanitization systems and devices.SOLUTION: An aircraft sanitization system includes: a frame; and a tray operatively coupled to at least first two corners of the frame and is rotatable about a pivot axis. The tray is configured to be in one of a locked state and an unlocked state based on rotation about the pivot axis. In the unlocked state, the tray is at an angle greater than zero with respect to the frame; and, in the locked state, the tray is at an angle equal to zero with respect to the frame. The aircraft sanitization system further includes a set of ultraviolet (UV) light emitting diodes (LEDs) attached on an exposed surface of the frame, where the set of UV LEDs is configured to sanitize the tray when the tray is in the locked state.SELECTED DRAWING: Figure 1

An aircraft stowage compartment includes a main body, a swiveling compartment swiveling relative to the main body, and a spring unit therebetween. In an active state, a spring device of the spring unit generates closing forces on the swiveling compartment prevented in a passive state. A connection unit with a connection element in biased zero position switches on the passive state and in connection position switches on the active state. The connection unit has a locking device biased towards locking, for the connection element in the connection position. The connection unit has a release element for the locking device actuatable from biased rest position into release position. In the rest position, locking of the connection element in the connection position is enabled by the locking device and prevented in the release position. An aircraft includes a basic structure, the stowage compartment and the main body fixed to the basic structure.

The invention relates to an aircraft disinfection system and apparatus, and specifically discloses an aircraft disinfection system. The aircraft disinfection system includes a frame. The aircraft disinfection system also includes a tray operatively coupled to at least the first two corners of the frame and rotatable about a pivot axis. The tray is configured to be in one of a locked state and an unlocked state based on rotation about the pivot axis. In the unlocked state, the tray is at an angle greater than zero relative to the frame, and in the locked state, the tray is at an angle equal to zero relative to the frame. The aircraft disinfection system also includes a set of ultraviolet (UV) light emitting diodes (LEDs) attached on the exposed surface of the frame, where the set of UV LEDs is configured to disinfect the tray when the tray is in the locked state.

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.

The present invention relates to a compartment (10) for charging at least one personal electronic device (11), for use onboard transportation vehicle, the compartment (10) comprising an inner space (12) suitable for receiving at least one personal electronic device (11), at least one electrical insert (13) for charging the personal electronic device (11), a waterline connection (16), the connection comprises a material (18) being configured to undergo a transformation when exposed to a temperature above a predetermined temperature threshold, the transformation releasing water into the compartment (10). The invention also relates to a monument of a transportation vehicle and to a transportation vehicle with the monument.

The invention provides an unmanned helicopter modularized external manned system, which belongs to the technical field of air transportation, and comprises a load frame, a plurality of driving and mounting modules connected to the load frame, a plurality of seat modules connected to the driving and mounting modules, a storage module arranged below the load frame, and an automatic balance module connected to the load frame. The automatic balancing module is used for adjusting the gravity center of the unmanned helicopter according to the manned system. According to the invention, after an external manned system is loaded on the unmanned helicopter and a pneumatic model is changed, the manned system can be adjusted according to real-time feedback of an external environment.

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.