Abstract: An overhead bin for an aircraft comprises a base unit that is designed to fasten the overhead bin to a retaining structure of the aircraft, and a mounting unit that is connected to the base unit. By way of the mounting unit, a stowage space of the overhead bin can be accessed. The base unit provides a first stowage space region, and the mounting unit provides a second stowage space region that together with the first stowage space region forms the stowage space of the overhead bin.

Abstract: The present disclosure relates to an information gathering method. The information gathering method includes identifying a location of a package, the location associated with one or more location-based restrictions on collecting data. The information gathering method also includes restricting access to sensor-collectable data associated with the package in accordance with the one or more location-based restrictions.

Abstract: A switched reluctance machine has a stator core salient with stator poles disposed concentrically with a rotor that is salient with rotor poles. A plurality of coil windings are wound about the stator core so that a pair of windings are adjacent each of the stator poles. The pair of coil windings induces magnetic flux in the adjacent stator poles and the rotor rotates to align the rotor poles with the stator poles having the induced magnetic flux. The rotor is rotatable at high speeds of up to 50,000 RPM and the coil windings can be directly cooled.

Abstract: A system for mounting an aircraft monument partition to an aircraft cabin surface such as a floor may include a mounting structure fitted within and attached to a floor-abutting edge of the monument partition, the mounting structure including a mounting opening. A securement apparatus for securing the monument partition to cabin surface via the mounting structure may include a threaded fastener for extending through the mounting opening of the mounting structure and through a corresponding opening in a track mounted to the cabin surface, and a bridging washer for mating with the mounting opening; where, to secure the monument partition to the floor of the cabin area, the threaded fastener is provided through the mounting opening of the mounting structure and threaded to a mating fixture on a bottom side of the track.

Abstract: The Aircraft Secondary Barrier Cart includes a main housing, with at least two retractable cables with metallic safety-hooks at the ends that connect to the two female loops behind each bulk-head. When deployed, the two cables hold the barrier cart in place. The two retractable cables are connected to a ratcheting system to stabilize and strengthen the barrier cart's stability after deployment. The ratcheting system includes a release lever to disengage the two main-housing cables before stowage. The barrier cart includes a folding-barrier with elastic and polymer safety-hooks sewn in. When the curtain or net gets expanded, its safety-hooks attach to several female loops riveted into the upper portion of the forward galley entrance.

Abstract: A tray mounted lateral guide for use between trays of a cargo bay having a bay floor includes a main body defining a roller slot. The tray mounted lateral guide further includes a roller configured to be at least partially positioned in the roller slot and to facilitate conveyance of a pallet through the cargo bay. The tray mounted lateral guide further includes a lifter coupled to the main body and configured to be coupled to a tray and to maintain the main body in at least one of a lowered position or a raised position, the main body being further from the bay floor when in the raised position than when in the lowered position.

Abstract: An aircraft interior fitting component system comprising an aircraft interior fitting component, a support element attached to the aircraft interior fitting component, and an aircraft primary structure component. The support element is dimensioned in such a way and is attached to the aircraft interior fitting component in such a position that, in an assembled state of the aircraft interior fitting component in an aircraft, it is supported on the aircraft primary structure component at least when a predetermined load acts on the aircraft interior fitting component along the x-axis of the aircraft in flight direction.

Abstract: A modular lavatory assembly for a vehicle cabin includes a lavatory module having a housing and a toilet system having a toilet arranged in an inner space of the lavatory module and at least one service module having at least one service unit for personal use by a passenger. The at least one service module is attached to an outside of the housing. The housing encloses an inner space, which is free from additional service modules and includes at least one recess for accessing the at least one service unit of the at least one service module from an inside of the housing with the at least one service module being configured for providing access through the at least one recess. The at least one service module includes at least one additional access for accessing the at least one service unit from outside the housing.

Abstract: Described herein are methods and systems to dampen oscillations of a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the UAV's control system may dampen the oscillations by causing the UAV to switch to a forward flight mode in which movement of the UAV results in drag on the payload, thereby damping the oscillations. In another example, the control system may cause the UAV to reduce an extent flight stabilization along at least one dimension, thereby resulting in damping of the detected oscillations due to energy dissipation during movement of the UAV along the dimension. In this way, the control system could select and carry out one or more such techniques, and could do so during retraction and/or deployment of the tether.

Abstract: In a preferred embodiment, a vertically stowable aircraft storage unit for providing additional storage in a cabin area of an aircraft can include a storage compartment and a vacuum lift mechanism for lifting and lowering the storage compartment between a stowed position and a deployed position. The vacuum lift mechanism can include at least one vacuum actuator in fluid communication with a vacuum source. The aircraft storage unit can further include an overhead mounting frame for mounting the vacuum lift mechanism to an upper structure of an interior of the aircraft, and a storage compartment frame configured to releasably receive the storage compartment. The vacuum lift mechanism may be releasably attached, at an upper end, to the overhead mounting frame, and at a lower end, to the storage compartment frame. The upper structure of the interior of the aircraft can be above a ceiling of the cabin area.

Abstract: A lift apparatus for transporting objects between compartments of an aircraft through an aperture in a floor structure separating the compartments and an aircraft in which such lift apparatus is mounted. The lift apparatus includes a conveyor with a retaining portion to selectively retain and release objects to be transported, a guide to which the conveyor is mounted to be linearly movable along a predetermined path of motion defined by the guide, and a moving mechanism for driving the conveyor to linearly move along the predetermined path of motion. The retaining portion and a closing portion of the conveyor are along the path of motion, and the lift apparatus mounts in an aircraft with the path of motion extending through the aperture. The conveyor is selectively movable along the predetermined path of motion between positions.

Abstract: In an illustrative embodiment, a vertically stowable aircraft storage unit for providing additional storage in a cabin area of an aircraft includes a storage compartment, a vacuum lift mechanism, and a stowage container housing. The vacuum lift mechanism may include at least one vacuum actuator, and an air manifold in fluid communication with a vacuum source, the air manifold configured to provide vacuum and venting to the at least one vacuum actuator. The stowage container housing may be configured to receive the storage compartment in the stowed position and may be configured for mounting above a ceiling of the cabin area.

Abstract: A method for installing an item of equipment in a cabin, includes: determining the actual position of each anchoring location provided for the equipment in a first reference system and of each fixing location of the equipment in a second reference system, positioning the second reference system relative to the first reference system, prior to the installation of the equipment in the cabin, adjusting each adjustable connection in accordance with at least one characteristic determined from the actual position determined for each anchoring location and for each fixing location, positioning the adjusted adjustable connections which connect the equipment to the cabin.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A lighting system includes a substrate, an array of light-emitting diodes (LEDs), and a light cover. The array of LEDs is disposed on the substrate and is arranged in a plurality of LED rows and a plurality of LED columns. The light cover is positioned over the array of LEDs and includes an array of optical elements. Each optical element is substantially aligned with a LED.

Abstract: The present invention relates to a 3-dimensional airborne magnetic survey system that includes an unmanned aerial vehicle for magnetic survey moving along coordinate areas desired to survey while varying altitudes for each of the coordinate areas, a magnetic survey unit mounted on the unmanned aerial vehicle for magnetic survey and surveying 3D magnetic data of the earth or strata according to the altitudes, a 3-dimensional magnetic data processing unit processing a inversion on the 3-dimensional magnetic data of the earth or the strata according to the altitude for each coordinate area, a VSAT interface, a wireless controller interacting with the VSAT interface, a flight control signal for controlling the unmanned aerial vehicle of magnetic survey, and a magnetic survey signal through an internal navigation program.

Abstract: A system for determining load distribution of pieces of cargo in a cargo hold of a vehicle may include a plurality of tags, each of the plurality of tags mounted on a different piece of the pieces of cargo in the cargo hold and carrying information indicative of a weight of the different piece of cargo on which it is mounted; a plurality of sensors mounted in a spaced array along a length of the cargo hold, each of the sensors capable of reading from the tags the information indicative of the weights of the pieces of cargo; and a computer connected to receive from the plurality of sensors the information indicative of the weights and information indicative of the locations of the pieces of cargo in the cargo hold, the computer programmed to calculate therefrom a weight and/or center of gravity of the plurality of the pieces of cargo.

Abstract: A monument for a cabin of a vehicle, in particular of an aircraft or spacecraft, having an outer housing side and a fastening rail for fastening connection elements in a longitudinal direction of the fastening rail in order to fix the monument in position inside the cabin, wherein the fastening rail has a receiving space extending in the longitudinal direction of the fastening rail, which space is designed to receive and fasten mounting feet of the connection elements to the fastening rail, and wherein the fastening rail is integrated in the outer housing side.

Abstract: Disclosed is an unmanned aerial vehicle (UAV) with a pre-defined shape to deploy one or more items. The unmanned aerial vehicle (UAV) includes an upper housing, a lower housing, and a power unit. The upper housing includes plurality of rotors to lift and propel the unmanned aerial vehicle (UAV). Further the unmanned aerial vehicle (UAV) includes various electronic components such as plurality of electronic cards, a processing unit, a Global Positioning System (GPS), a communication unit, an electronic gyroscope, a barometer, engines and flight control system, video camera, a forward looking infrared (FLIR) device, a microphone, and a laser telemeter/designator/range finder. The power unit powers the aforementioned electronic components. The lower housing includes plurality of storage units to stores one or more items. The lower housing is removably attached with the upper housing in a way to deploy the items at a predetermined location through plurality of openings.

Abstract: An aircraft that includes an outer skin having an opening formed therein, and a cargo compartment including a plurality of side walls that define an interior of the cargo compartment. The plurality of side walls are positioned such that the interior is in flow communication with the opening. The aircraft further includes a hinged panel coupled to the outer skin. The hinged panel is operable between a closed position for covering the opening and an open position for exposing the interior to an ambient environment outside the aircraft. A release device is configured to retain the hinged panel in the closed position, and configured to release the hinged panel for movement into the open position when an unexpected combustion event forms in the interior.

Abstract: Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.

Abstract: Confirming compliance with a configuration includes: receiving information about a fixture, where the information includes a specified configuration of items to be displayed on the fixture; generating a display using the information, where the display depicts the specified configuration; presenting the display using a graphics system of a computing device; receiving an image depicting an actual configuration of the fixture; associating metadata with the image, where the metadata includes searchable data that distinguishes the fixture from at least some other fixtures of like type; sending the image, along with the metadata, over a network to a server that is remote from the computing device; and in a case that the specified configuration substantially matches the actual configuration, sending, along with the image and the metadata, a message indicating that the fixture is in compliance with the specified configuration.

Abstract: A device and process for a vehicle accessory lock are disclosed. The vehicle accessory lock includes a plunger housing defining a plunger bore and mountable through a door jamb. A security plunger, being spring-loaded, is received by the plunger housing. The security plunger, responsive to a closing force imparted by a hinged door surface against the security plunger, being operable to extend and engage a plunger receiver defined by a vehicle accessory to produce a locked vehicle accessory state.

Abstract: A method, apparatus, and aircraft tracker system for reporting state information for an aircraft. A state of the aircraft is identified using sensor data received from an aircraft sensor system in the aircraft. The state information is transmitted at a reporting rate set using the state of the aircraft identified from the sensor data, at least one of a crew command or a ground command when at least one of the crew command is received from a crew interface or the ground command is received from a ground source, and a policy defining priorities for reporting that are based on at least one of the crew command, the ground command, or the state of the aircraft identified from the sensor data.

Abstract: An autonomous cargo handling system is provided. The autonomous cargo handling system may comprise one or more sensing agents in electronic communication with each other. One or more of the sensing agents may be configured to monitor a sensing zone in a cargo deck to detect objects traveling through the sensing zone. In response to detecting an object, one or more sensing agents may determine an object property based on the detected object. One or more sensing agents may generate an object model based on the determined object properties. The sensing agents may also determine whether the detected object is a unit load device (ULD) or a non-ULD object based on the object property and/or the object model.

Abstract: An aircraft overhead stowage system for a cross-aisle galley complex. The aircraft overhead stowage system includes a stowage compartment housing disposed above a ceiling of the galley complex that is supported above the ceiling by a stowage support structure. A first stowage compartment and a second stowage compartment are each movably engaged with and disposed inside the stowage compartment housing, and each stowage compartment is movable between a stowed position and a deployed position relative to the stowage compartment housing using a vacuum system. A vacuum generator that creates a vacuum force is mounted on the stowage compartment housing, and a plurality of vacuum bellows connected to each stowage compartment are in fluid communication with the vacuum generator. The vacuum system causes the stowage compartments to move between the stowed position and the deployed position. Vacuum-driven and manually-driven latching assemblies and removable extensions for each stowage compartment are also provided.

Abstract: An aircraft comprising a fuselage; a main wing provided on a fuselage lower side and including a center wing and an outer wing; and a fairing covering at least a lower surface of the center wing, and a seal interposed between an end edge in a right-left direction of the fairing and an outer wing lower surface. In the aircraft, a most outboard fitting located on a most outboard side out of fittings respectively provided at a plurality of positions in the right-left direction of the fairing, and an outer wing fitting provided on the outer wing are pin-coupled via a pin or pins extending along a front-rear direction. The outer wing fitting is coupled to the outer wing at a position on an inboard side with respect to the end edge and other than a position of a joining structure for joining the center wing and the outer wing.

Abstract: A rotary shaft assembly includes a first supporting arm, a second supporting arm, a connecting arm connecting the first supporting arm and the second supporting arm and a driving device coupled to the second supporting arm. The driving device includes a rotor assembly and a stator assembly. The first supporting arm, the second supporting arm, and the connecting arm are integrally formed. The first supporting arm and the second supporting arm are arranged symmetrically with respect to a central point of the connecting arm. The second supporting arm comprises a connecting base arranged at an end distal from the connecting arm. The connecting base includes a receiving groove, and the rotor assembly is directly received in the receiving groove.

Abstract: Method of device for installation of avionics cabinets, electrical master boxes and IFE bays includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, systems cabinets are used which incorporate a structural function. The use of such system cabinet designs thus allows a reduction in the aerodynamic drag and mass of the aircraft, thereby positively impacting fuel consumption and performance of the aircraft.

Abstract: An overhead luggage compartment for aircraft can be constructed as a fixed luggage compartment with a stationary housing and a pivotable flap, or as a lowerable luggage compartment with a lowerable tray, a stationary part having side walls and a movable part which is pivotable between a closed and an open position and has a closure element for retaining the movable part in the closed position. Those parts define a luggage-receiving space. Two fastening devices for fastening to a supporting structure of the aircraft on the side walls of the stationary part are disposed on the stationary part. At least one further fastening device is disposed in the region of the lower side of the rear side of the stationary part. The fastening devices are the same for the fixed luggage compartment and for the lowerable luggage compartment.

Abstract: Provided are stowage bin systems for use on aircrafts and other like vehicles. A stowage bin system may include two disjoint supporting panels and a stowage bin bucket disposed between and pivotally supported by these panels after installation. The supporting panels may be attached to vertical frame members and, in some embodiments, to other frame members, such as adjacent vertical frame members or to horizontal frame members. In some embodiments, a supporting panel may include a gusset extending substantially normal to the main surfaces of the panel. The gusset may provide additional rigidity to the panel and, in some embodiments, include one or more open channels for attaching to a horizontal frame member. The supporting panels transfer all loads generated during operation of the aircraft from the stowage bin bucket and to the fuselage or, more specifically, to vertical and other frame members.

Abstract: A trolley arrangement for a galley of an aircraft has a trolley container in which at least two trolleys can be arranged in a longitudinal direction and a trolley-handling device for pulling and pushing a trolley longitudinally into the trolley container. This device has a linear guide with a stationary guiding bar and a slide movable along the guiding bar longitudinally, a pulling and pushing bar extending along a longitudinal axis, axially fixed on the slide, but rotatable about the longitudinal axis, a hook at a distal end of the pulling and pushing bar remote from the slide, a handling bar axially fixed on the slide or on the pulling and pushing bar, and a joint between the handling bar and the slide or the pulling and pushing bar, so that the handling bar and the pulling and pushing bar are axially connected and are rotationally coupled.

Abstract: An aircraft storage bin that includes an upper housing, and a bucket pivotally connected to the upper housing that cooperates with the upper housing to define a bin interior. The bucket includes a bottom, a front edge, first and second opposing side walls extending upwardly from the bottom and a center of gravity. The bucket pivots about a pivot axis with respect to the upper housing between an open position and a closed position. The center of gravity of the bucket is positioned below the pivot axis when the bucket is in the closed position.

Abstract: An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using an assembly that secures the payload during descent and releases the payload upon reaching the ground. The assembly can also include a bystander communication module for generating cues for bystander perception. While the assembly securing the payload is being lowered from the UAV, the bystander communication module can generate an avoidance cue indicating that bystanders should avoid interference with the assembly. The assembly also includes sensors that generate data used, at least in part, to determine when the descending assembly is at or near the ground, at which point the assembly releases the payload. The bystander communication module can then cease the avoidance cue and the UAV can retract the assembly.

Abstract: An aircraft system component carrier module includes a carrier element which is arc-shaped at least in sections and is configured, when the module is mounted in an aircraft, to extend at least in some sections substantially in the direction of the ribs of an aircraft structure over at least a section of a crown area of an aircraft cabin. The module includes a transverse carrier element which is configured, when the module is mounted in an aircraft, to extend in the crown area of an aircraft cabin substantially perpendicularly to a longitudinal axis of the cabin. The module further includes a structure holder for fastening the module to the aircraft structure, an aircraft system component holder for fastening at least one of the aircraft system components to the module and an attaching device, connected to the transverse carrier element, for attaching an aircraft luggage compartment to the module.

Abstract: An integrated avionics bay in a floor area can be provided with adequate ventilation. The structure of an aircraft cockpit floor is able to integrate at least one bay, with a walking floor in the cockpit, a structural volume and a bay integrated in a space of the liberated structural volume. The bay as integrated in a horizontal position in this space includes a peripheral frame with at least one protective cover with a direct access to the bay at the floor level and a lower wall with a rear face access. Side openings formed in the frame can couple with vertical walls to allow fresh air blowing from the rear wall of the bay via a flow from rearwards to upwards to reach the top cover and an air extraction by an upper surface extractor.

Abstract: A cold plate for cooling heat-generating components, includes two plates extending parallel to each other. A core is sandwiched between the two plates to form a sandwich structure, the core including a set of passages for passing a cooling fluid from a first edge to an opposite second edge of the sandwich structure. First and second fluid-tight joining members are disposed respectively on the first and second opposite edges of the sandwich structure, the first fluid-tight joining member including at least one inlet connector and the second fluid-tight joining member including at least one outlet connector for the passage of the cooling fluid. A method for use of the cold plate in particular as a structural part of an avionics equipment item is also provided.

Abstract: An apparatus and method comprising a rack and a translation mechanism. The rack may be configured to hold components. The rack may comprise movable rack segments that are movable independently of each other. The translation mechanism may be configured to move a portion of the movable rack segments relative to another portion of the movable rack segments inside a platform such that internal access to at least a portion of the components is provided inside the platform.

Abstract: An air extraction unit taking the form of a body, the geometric shape of which makes it easier to incorporate into an avionics bay of an aircraft. The air extraction unit derives from a multipurpose approach to the operational components of the avionics bay of an aircraft aimed at achieving weight and cost savings. All of the elements of the air extraction circuit are arranged in a compact housing of the body and are protected by the structure thereof. The air extraction unit can be used as a floor of an avionics bay that can be walked on, with a lateral organization.

Abstract: Reconfigurable payload systems (RPS) and methods of configuring and using the same are disclosed that may be employed to enable external aircraft payloads to be rapidly interchanged or swapped out together with associated internal equipment within a given aircraft so as to modify or change payload capability of the aircraft, e.g., to meet a particular mission and/or to enable use of future payload types as they are developed. The RPS and associated methods may be implemented to allow multiple different payload systems to be swapped in and out on a given aircraft as required based on needs for a given mission.

Abstract: Reconfigurable payload systems (RPS) and methods of configuring and using the same with operational load envelopes are disclosed that may be employed to enable external aircraft payloads to be rapidly interchanged or swapped out together with associated internal equipment within a given aircraft so as to modify or change payload capability of the aircraft, e.g., to meet a particular mission and/or to enable use of future payload types as they are developed. The RPS and associated methods may be implemented to allow multiple different payload systems to be swapped in and out on a given aircraft as required based on needs for a given mission.

Abstract: A body frame of an aircraft lavatory unit includes a front wall having an entrance opened and closed off by a door, side walls on both sides, and a floor surface. The outer surface of the side wall positioned closer to the front constitutes a wall facing backrests of a rear seat row and extending in a latitudinal direction. The lavatory unit is capable of being disposed at a front position in which the wall is disposed behind and near the backrests of the seats of the rear seat rows with the backrests being in an upright position, and at a rear position in which the wall is disposed behind and near the backrests of the rear seat rows of the seats with the backrests being in a reclining position.

Abstract: A stowage bin is provided. The stowage bin includes a bucket, a support assembly, and at least one translating pivot mechanism rotatably coupling the support assembly to the bucket, the at least one translating pivot mechanism including a first component integrally formed with the bucket and comprising a first pin and a first slot, and a second component integrally formed with the support assembly and including a second pin and a second slot, wherein the first and second components engage one another such that the first pin is received in the second slot and the second pin is received in the first slot. The first pin is static with respect to the bucket, and the second pin is static with respect to the support assembly.

Abstract: An aircraft is provided and includes a single sensor and wings extending outwardly in opposite directions from a fuselage. Each wing includes a main section, an engine section supported on the main section and tail surfaces extending transversely relative to the main section. The single sensor is mountable to one of the tail surfaces with a field of view (FOV) representable as a spherical wedge having a dihedral angle exceeding 180°.

Abstract: The invention particularly relates to a computer device (700) for a computer housing center that is transportable in a container. The computer device includes at least one computer cabinet. Said computer device is sized and arranged so as to be movable inside a container into which said computer device is to be placed, and which comprises an absorber system that is suitable, with regard to said computer device, for absorbing the transmission of vibrations to the at least one computer cabinet once the computer device is installed in the container.

Abstract: To provide a glove box that can cause an inner case to operate to open obliquely downward while suppressing large change in the center of gravity in the up-down direction. A mechanism for guiding opening/closing operation of the inner case in the glove box is composed of two types of mechanisms: i.e., a slide mechanism including a guide shaft and a slide guide portion; and a link mechanism including a link member. The inner case is guided in the front-rear direction by the slide mechanism, and a rear portion of the inner case is guided so as to swing downward by the link mechanism.

Abstract: A deployable floor panel arrangement for an aircraft cabin area comprising a substantially planar floor panel with at least one foldable seat arrangement mounted thereto. The seat arrangement comprises at least one backrest which is configured to be moveable between a stowed position in which it extends at an angle of approximately 0° to 40° to the plane of the floor panel and a deployed position in which it extends at an angle of approximately 80° to 180° to the plane of the floor panel.

Abstract: An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using an assembly that secures the payload during descent and releases the payload upon reaching the ground. The assembly can also include a bystander communication module for generating cues for bystander perception. While the assembly securing the payload is being lowered from the UAV, the bystander communication module can generate an avoidance cue indicating that bystanders should avoid interference with the assembly. The assembly also includes sensors that generate data used, at least in part, to determine when the descending assembly is at or near the ground, at which point the assembly releases the payload. The bystander communication module can then cease the avoidance cue and the UAV can retract the assembly.

Abstract: A fastener system (10) having attachment means (15) for attaching an external load to a rotorcraft, said fastener system (10) having a support beam (20) for attaching the attachment means (15) to a rotorcraft, said support beam (20) having a horizontal core (25) and two lateral section members (30) extending in elevation from said horizontal core (25), said fastener system (10) having a support member (50) in a central space (100) between said lateral section members (30) to carry attachment means (15), said support member (50) being connected to each lateral section member (30). Each lateral section member (30) includes a web (31) in elevation connected to the horizontal core (25), each web (31) presenting an obtuse angle (?) relative to said horizontal core (25) in said central space (100), each lateral section member (30) being a sloping section member capable of moving closer to said horizontal core (25) under the effect of vertical forces.

Abstract: Elongate passenger service unit (PSU) assemblies are comprised of a plurality of modular passenger service units, and a plurality of variable-length modular spacer units. The modular spacer units are positioned between the modular passenger service units in an end-to-end manner so as to provide a desired lengthwise array of the passenger service units along the PSU assembly. Transport category vehicles, e.g., aircraft, may thus be provided with inboard and outboard PSU assemblies. The passenger seats may be arranged in a latitudinally side-by-side arrangement and/or may be arranged in a longitudinally staggered arrangement. By providing variable length modular spacer units, therefore, the individual passenger service units may be arranged directly overhead of each passenger seat.