Abstract: The present disclosure provides a method for changing passenger seating angle according to an aircraft flight mode utilizing a racked passenger seat configuration in which the seat angle relative to an aircraft longitudinal axis increases as the passenger seat transitions from an upright condition to a reclined condition. Such a passenger seat may be utilized in an aircraft passenger seating arrangement to maximize seating density while complying with defined taxi, takeoff and landing (TTOL) certification criteria for oblique seats, among other applications and benefits.

Abstract: A partition wall arrangement for a cabin of a passenger aircraft includes a partition wall, a seat arrangement secured to the partition wall in an assembled state and containing a carrier structure, and at least one cabin attendant seat. The carrier structure contains a mechanically load-bearing wall structure for the partition wall, a mechanically load-bearing seat structure for the seat arrangement, and at least one fastening device in order to secure the wall structure and the seat structure to each other in the assembled state. In a method for producing the carrier structure or the partition wall arrangement, the wall structure or at least a main component thereof is produced as a milled component by milling out a solid material plate. In a design method, the entire carrier structure is subjected in the assembled state to a load path optimization.

Abstract: A water extractor for use in an environmental control system includes a housing having an inlet end and an outlet end. A fog harvester assembly is mounted within the housing at a location between the inlet end and the outlet end. The fog harvester assembly includes at least one fog harvester insert having a condensing material including plurality of wires arranged in a wire array. At least one of the plurality of wires has a spiral configuration.

Abstract: A method for dehumidifying a perforated acoustic skin includes disposing a sheet of material over a perforated acoustic skin, sealing a periphery of the sheet of material to the perforated acoustic skin to form a cavity between the sheet of material and the perforated acoustic skin, disposing at least one dehumidifier in fluid communication with the cavity, and activating the dehumidifier to remove moist air from a core of the perforated acoustic skin. The dehumidifier(s) may be mounted to the sheet of material.

Abstract: A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.

Abstract: An embodiment of the present invention discloses a repair system for a planetary exploration parachute. The repair system includes a folding piece and a fuse, the fuse is provided in the folding piece, a sensing signal for reflecting an impact force of dust is received by the fuse, fusing is generated in the fuse when the sensing signal is greater than a preset threshold, and the folding piece is changed from a folded state to an unfolded state after the fusing is generated in the fuse, so as to automatically repair a damaged part of the parachute.

Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank; and to control fuel supply so as to select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.

Abstract: Propulsion systems for aircraft include a fan and a low pressure turbine operably coupled to a first shaft, a low pressure compressor and an intermediate pressure turbine operably coupled to a second shaft, and a high pressure compressor and a high pressure turbine operably coupled to a third shaft. A burner is arranged between the high pressure compressor and the high pressure turbine, with a main flow path defined through the propulsion system. A hydrogen fuel system is configured to supply hydrogen fuel to the burner. A condenser is arranged along the main flow path and configured to extract water from exhaust from the burner. An evaporator is arranged along the main flow path and configured to receive a portion of the water to generate steam which is injected into the main flow path upstream from the evaporator.

Abstract: A charge status control system 99 includes: a power generator 40a configured to generate electrical power and to supply it to a load; a battery 32 configured to store the electrical power generated by the power generator 40a and to supply the stored electrical power to the load; an ECU 33 configured to detect a state of charge of the battery 32; and a control unit 91 configured to, if a detection result of a remaining charge amount of the battery 32 by the ECU 33 is a storage threshold or more, control the state of charge of the battery 32 by discharging the electrical power stored in the battery 32 to an external power source 111. According to this, the remaining charge amount of the battery 32 can be maintained to approximately the storage threshold or less to suppress the progression of the deterioration of the battery 32.

Abstract: Disclosed is an electrically driven ducted fan engine, comprising a housing with an inner housing wall, defining a substantially cylindrical inner space and a longitudinal axis, an inlet opening, a rotor with a multitude of rotor blades positioned in the inner space of the housing downstream of the inlet opening, a stator assembly with a multitude of guide vanes extending from a radially central region of the inner space to the inner wall of the housing, and an exhaust opening provided in the housing downstream of the stator assembly, an interstage region defined between the rotor and the stator assembly, a guide vane region defined in which guide vanes extend to the inner wall of the housing and an exhaust section, wherein in at least one of the interstage region, the guide vane region and the exhaust region, acoustic liners are provided to the housing.

Abstract: A latch mechanism is disclosed. In various embodiments, the latch mechanism includes a T-bolt body and a T-bolt comprising a longitudinal rod extending in a longitudinal direction from the T-bolt body and a transverse rod disposed at an end of the longitudinal rod. A safety keeper defining a load slot may be configured to receive the transverse rod whereby the T-bolt is configured to secure the T-bolt body with respect to the safety keeper.

Abstract: A method for controlling an aircraft capable of hovering is described, comprising a first engine; a second engine; at least one rotor; and a transmission interposed between the first and second engine and the rotor; the transmission comprises a first and a second inlet connected respectively to a first outlet member of the first engine and to a second outlet member of the second engine; the method comprises step i) of placing the in a first configuration, in which the first and second engine make available a first and a second power value; or in a second configuration, in which the first engine (makes available a third power value greater than the first power value to the first inlet, and the second engine delivers a nil power value to the second inlet; the method also comprises, characterised in that it comprises the steps of ii) detecting a series of parameters associated with the operating conditions of the aircraft; and iii) enabling the transition of the aircraft from the first configuration to the secon

Abstract: Aircraft Auxiliary Power Unit (APU) controllers and related methods are described herein. An example APU controller includes a sensor interface to receive a signal from a speed sensor. The signal includes pulses representing a rotational speed of an engine of an APU. The APU controller also includes an overspeed detection circuit including a counter to count a number of pulses from the signal occurring within a time interval, a digital-to-analog converter (DAC) to convert the number of pulses into an analog voltage signal and a comparator to: compare the analog voltage signal to an overspeed threshold signal and generate a shutdown command in response to the analog voltage signal exceeding the overspeed threshold signal. The APU controller also includes a valve driver to, in response to receiving the shutdown command, cause a fuel shutoff valve to cease fuel flow to the engine of the APU.

Abstract: A method of logging an observation or maintenance request of an aircraft, the method can comprise: scanning, by a personal internet device connected to a network, a machine-readable code; directing the personal internet device to a user interface of an aircraft log database based on the machine-readable code; and transmitting, by the personal internet device, a log entry to the aircraft log database over the network, wherein the log entry comprises a description of the observation. The method can further comprise transmitting an alert notification to an aircraft maintenance system. An aircraft log system can comprise a personal internet device, a machine-readable code disposed on an aircraft, and an aircraft log database. The aircraft log system can further comprise a manufacturer log database.

Abstract: A system includes a frame and a plurality of machines mounted on the frame, wherein each machine of the plurality of machines includes an actuator, and wherein each machine is configured to operate in a defined condition. The system further includes at least one controller configured to control the actuators so as to exert an excitation of each machine of the plurality of machines. The system further includes at least one sensor configured to measure at least one response indicator of a response of the system to the excitations of the plurality of machines. The system further includes a diagnosis system configured to receive the at least one measured response indicator.

Abstract: Disclosed are methods and devices for determining a load condition of an aircraft. A sensing device is mountable relative to an aircraft strut during loading operations and demountable after loading operations. A data processing device is operable to process output from the sensing device together with aircraft specific data, to determine a load condition of the aircraft.

Abstract: A fixture configured to secure a component in a vehicle includes a panel separating an internal cabin from an external compartment. The panel has a first side facing the internal cabin and a second side facing the external compartment. A hole is disposed within the panel. The component is configured for mounting to the panel via the hole. The component includes a flange configured for abutting the first side of the panel and a coupling feature configured to extend through the hole into the external compartment. A fastener is configured to removably couple with the coupling feature and abut the second side of the panel for fastening the component to the panel.

Abstract: In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall.

Abstract: Aircraft handlers include a plurality of undercarriage support assemblies. Each undercarriage support assembly includes a body, a translation assembly operably attached to the body, and a support member operably coupled to and extending from the body. The support member comprises a support region configured to engage and operably support at least a portion of an undercarriage of an aircraft. The translation assembly is configured to support the undercarriage support assembly on a ground surface and permit the undercarriage support assembly to translate along the ground surface. The aircraft handlers further include one or more drive assemblies configured to move the aircraft handler along the ground surface, in which each drive assembly comprises the translation assembly of an undercarriage support assembly. Methods comprise supporting the undercarriage of the aircraft with the aircraft handler and moving the aircraft along the ground surface with the aircraft handler.

Abstract: A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.

Abstract: A servicing tool may provide a portable, lightweight solution to adjusting the height of struts of aircraft. The tool may provide hydraulic fluid at high pressure to an already pressurized strut. The hydraulic fluid may be supplied to the strut by the tool at a pressure in excess of a pressured gas in the strut to increase the height of the strut. The tool provides techniques to raise and lower the strut when access to high-pressure gas is unavailable. Further, with the application of high-pressure hydraulic fluid, the tool may be used to increase the strut height while also increasing the stiffness of the strut so as to reduce a risk of dynamic rollover.

Abstract: Disclosed is a cart (2) for transporting an aircraft engine, comprising a base frame (4) equipped with wheels (6) for riding on a floor; at least two engine arms (14, 16) extending horizontally and movable vertically relative to the base frame, structured and designed for supporting the aircraft engine; and at least two adapter arms (20) extending horizontally at a higher level than the at least two engine arms, structured and designed for supporting an adapter coupled at the top of the aircraft engine. Disclosed is also a method of transporting an aircraft engine to a test cell.

Abstract: A flow conditioning structure is disposed about a central axis of an unducted thrust producing apparatus. The unducted thrust producing apparatus has a propeller that generates thrust in a working fluid by rotating about the central axis. The propeller is comprised of blades each with a free end. Each blade also has a leading edge where the working fluid enters during forward thrust operation. The flow conditioning structure comprises a structure forming a passage and the structure forming the passage controls a speed and a direction of the working fluid drawn into the unducted thrust producing apparatus so as to approximate operational speeds and operational directions of the working fluid entering the unducted thrust producing apparatus during operations of a vehicle.

Abstract: A method of monitoring friction associated with a plurality of aircraft wheels of an aircraft, the method including, for each of the plurality of aircraft wheels, obtaining wheel speed data associated with the aircraft wheel. The method includes determining, based at least in part on the wheel speed data, deceleration of the aircraft wheel during a time interval, and determining, based at least in part on the determined deceleration, a value indicative of friction associated with the aircraft wheel. The method includes providing, based at least in part on the determined value, a signal indicative of a level of friction associated with the aircraft wheel.

Abstract: A method for monitoring the integrity of a set of air bleed lines from propulsion engines of an aircraft by: at the start of a use of the aircraft, sending air from an auxiliary power unit into the various lines; over a predetermined period of time, acquiring temperature measurements from temperature sensors associated with the lines; for each line, determining a gradient for rate of change in temperature with respect to time during this period of time; determining a discrepancy between the gradient for rate of change in temperature with respect to time corresponding to a line and a gradient for rate of change in temperature with respect to time corresponding to at least one other line; determining a condition indicator for the condition of the line as a function of the discrepancy determined for said line.

Abstract: An apparatus includes an integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring. In a spacecraft application, a spacecraft appendage may be coupled with a deployment mechanism, the deployment mechanism including at least one integral, additively manufactured, actuation device having a rigid portion comprising a shaped structural member and a flexible portion comprising a helical torsion spring.

Abstract: An example of an apparatus includes an inlet to connect to a propellant source a pressure regulator connected to the inlet to reduce propellant pressure from a first pressure at the inlet to a second pressure. The apparatus includes a manifold connected to the pressure regulator to receive propellant from the pressure regulator at the second pressure and includes a plurality of manifold outlets. The apparatus further includes a plurality of gas lines, each gas line extending from a corresponding manifold outlet for connection to a corresponding satellite propellant tank.

Abstract: An attitude control module is described for providing propellant-free attitude control and momentum desaturation to a spacecraft. The attitude control module includes at least one solar sail comprising a reflective surface for reflecting solar photons; and at least one robotic arm coupled to the at least one solar sail, said at least one robotic arm comprising at least 4 degrees of freedom for positioning and orienting the at least one solar sail relative to the spacecraft. A corresponding method for operating the attitude control module to unload excess momentum from a spacecraft is also described.

Abstract: The planar electric motor for aerospace use is a one hundred percent electric thruster or motor and consists of a device capable of generating a thrust force on itself regardless of the environment around it even in vacuum or outer space. The impulse of the motor is produced by the interaction of the force fields generated by the current flowing through a primary conductor and a secondary conductor placed adjacent and parallel to the first conductor one, both being separated by means of an insulating material, the secondary conductor is interrupted, so that in order to complete the circuit, the charge carriers must jump the free space that constitute the secondary conductor breach, to achieve this the motor employs extremely brief high voltage pulses producing small impulses produce by the force of repulsion between both parallel currents that runs in opposite directions.

Abstract: An apparatus comprising a satellite includes a first radiator panel on a first side of a central body of the satellite and a second radiator panel on a second side of the central body is provided. The first radiator panel is thermally attached to the second radiator panel. A third side of the central body is positioned between the first side and the second side. A fourth side of the central body is positioned between the first side and the second side, opposing the third side. The first radiator panel is thermally attached to the second radiator panel by one or more coupling heat pipes, the coupling heat pipes exposed to an exterior environment of the satellite.

Abstract: A toilet for a zero-gravity condition, having: a seat extending from a first end to a second end, and from a first side to a second side; a leg rest at the first end of the seat that is level with the seat; a backrest at the second end of the seat that extends away from the seat, toward an outer end of the toilet, a first sidewall at the first side of the seat and a second sidewall at the second side of the seat, the sidewalls extend away from the seat toward the outer end of the toilet; a basin extending away from the seat toward an inner end of the toilet; a first inflatable member extending about the leg rest, the sidewalls and the backrest, the first inflatable member is configured to inflate against a back, sides and under legs of a person seated against the seat.

Abstract: The present disclosure provides a system that searches for and finds orbital debris that can be a hazard to satellites and the like, for which the debris is sunlit. The system includes a ground-based telescope pointed at the sky; a detector array that detects images of the sunlit debris crossing the field of the detector; and a processing system that computes tracks from the detector data using a hierarchical algorithm, which builds longer tracks from previously computed shorter tracks, determines whether the computed tracks correspond to valid debris detections, and converts the track computations into debris brightness and debris orbital trajectory.

Abstract: A method that includes takeoff of an aircraft assembly in a vertical orientation with a central axis X of the aircraft assembly perpendicular to the ground; rotating the aircraft assembly from the vertical orientation to a horizontal orientation where the central axis X is between ?5° and 20° from true horizontal; and flying the aircraft assembly from a first location to a second location in the horizontal orientation with an aircraft of the aircraft assembly generating forward propulsion for forward flight and a wing body of the aircraft assembly generating aerodynamic lift for the aircraft assembly based on the forward flight in the horizontal orientation, the aerodynamic lift generated by the wing body supporting equal to or greater than 70% of the weight of the aircraft assembly.

Abstract: An agricultural support system includes an unmanned aerial vehicle including a sensor, and an agricultural machine to travel in an agricultural field. When an abnormality occurs in the unmanned aerial vehicle while the agricultural machine performs work in the agricultural field in cooperation with the unmanned aerial vehicle, the unmanned aerial vehicle or the agricultural machine performs an operation different from an operation during the work.

Abstract: Provided is an apparatus or a method that can stabilize flight of an unmanned aerial vehicle after package receiving or package passing. A port as a package receiving or passing apparatus includes: a landing portion on which an aerial vehicle lands; a slider for horizontally moving the landed aerial vehicle to an indoor area; an elevating/lowering portion on which a package-chamber tray taken down from the aerial vehicle in the indoor area is to be placed; a movement control portion for elevating/lowering an elevating/lowering portion; a package moving portion for moving a package between a package storage portion and the package-chamber tray placed on the elevating/lowering portion; and a center of gravity adjustment portion for adjusting the center of gravity position of the aerial vehicle after package receiving or package passing.

Abstract: A method, apparatus and program product perform automatic load profiling to optimize a wrapping operation performed with a stretch wrapping machine. Automatic load profiling may be performed, for example, to determine a density parameter for a load that is indicative of load stability such that one or more control parameters may be configured for a wrapping operation based upon the density parameter. Automatic load profiling may also be performed, for example, to detect a load with a nonstandard top layer, e.g., a load with a top or slip sheet, a load with an easily deformable top layer, a load with a ragged top surface topography and/or a load with an inboard portion, such that a top layer containment operation may be activated during wrapping to optimize containment for the load.

Abstract: A machine for stabilising palletised loads including an apparatus having a reel of covering tape, a gripping device to take a first end of the tape of the reel and make it integral with the load, a first movement apparatus to generate relative revolution of the apparatus around the load about a predetermined revolution axis, a second movement apparatus to generate relative translation motion of the apparatus with respect to the load in a direction parallel to the revolution direction, a cutting device placed in the apparatus to separate the tape from the reel, and a fixing device to fix a second end of the tape to the load.

Abstract: A horizontal packaging machine (M) for packaging a product (P) fed in a horizontal direction (X) comprises a cut-sew group (22) for making on a packaging film (F) transverse welds and a cut to close and separate from each other two successive packs (C1, C2, C3, C4), wherein the cut-sew group (22) comprises a plurality of cut and sew tools (U1, U2, U3) for making the transverse welds and the cut, wherein the transverse welds define the edges of the packs (C1, C2, C3, C4) according to different packaging sizes for the product (P), wherein the cut-sew group (22) comprises an upper shaft (AS) and a lower shaft (AI) driven in rotation independently by means of a respective upper motor (MS) and a respective lower motor (MI), in which each shaft (AS, AI) mounts on it the plurality of cut and sew tools (U1, U2, U3) and in which each cut and sew tool (U1, U2, U3) is composed of an upper tool (US) and a corresponding lower tool (U1).

Abstract: An apparatus for supporting a laundry hamper is disclosed. The apparatus comprises a supporting rod having one or more sides arranged to form a closed frame, one or more mounting brackets, and means for securing the mounting bracket to a door of a cabinet, such as a tilt-out cabinet. Each of the mounting brackets comprises a channel with a recess within which a portion of the supporting rod is inserted therein. The channel comprises a first channel segment and a second channel segment separated by a gap. Each of the first and second channel segments comprises a first side wall and an opposing second side wall integral with a bottom wall to define a generally U-shaped structure. The bottom wall of the first channel segment faces a side opposite from the side at which the bottom wall of the second channel segment faces. Aspects of the invention relate to a laundry hamper assembly comprising the apparatus and at least one laundry hamper being supported thereon.

Abstract: A method for adhering a label, lettering, ink, a tattoo, sketch, design or color (“indicia”) to a substrate comprising the steps of: providing an indicia-bearing backing paper; moistening the indicia-bearing backing paper to form a moistened indicia-bearing layer; providing an adhesive layer between the moistened indicia-bearing layer and the substrate; placing the moistened indicia-bearing layer on the adhesive layer; allowing the indicia to become separated from the backing paper, leaving the indicia upon the substrate; and drying on the substrate.

Abstract: Systems and methods for a single serving beverage preparation cup are provided. The single serving beverage preparation cup may include a plurality of reverse teardrop ribs that may channel water combined with dried ingredients, for example coffee grounds, through the single serving beverage preparation cup. By channeling the combined water and dried ingredients through the single serving beverage preparation cup, the pressure within the single serving beverage preparation cup is reduced, an avenue for extraction is created, varying amounts of dried ingredients can be added, and water may be exposed to a greater proportion of dried ingredients than in conventional systems.

Abstract: A glass hollow container including a finish intended to cooperate with a cap with notches to close the container, wherein the finish has a locking ring whose cross section has a profile substantially in the shape of an ogive.

Abstract: The present application relates to a folded packaging container structure, and a bottom folding-sealing device and process, including: a folded packaging body, which forms a cavity for accommodating a object after being folded; an upper opening, which is located on the folded packaging body, at which a cap is provided at least after the cavity is loaded with the object; a folded part A and a folded part B, which are folded and contacted with each other; a front surface of the folded part A and a front surface of the folded part B are provided as corresponding front surfaces of the folded packaging body and are located between the bottom part and the upper opening; at least a first side surface and a second side surface located between the bottom part and the upper opening are provided between the front surfaces.

Abstract: A container for storage of molten material from an industrial facility, and method of manufacture thereof, is provided to maximize internal volume of the container while providing structural stability. The container includes walls having rounded convex-shaped edges at each wall junction. A first head is connected to the walls at a first end of the container, and a second head closes the second end of the container. The second head is connected to the walls at a second end of the container. Corners are defined at the intersection of the walls with the first head and second head at the first end and the second end respectively. A first flange is connected to the first head to receive molten material, and the first head is shaped as a tapered shoulder to smoothly transition from the first flange to the junction of the walls.

Abstract: A bottle packaging assembly includes a bottle packaging comprising a sidewall enclosure, the sidewall enclosure defining an interior cavity and comprising a first sidewall and a second sidewall opposite the first sidewall; a plurality of bottle insert assemblies arranged laterally side-by-side within the interior cavity, wherein each of the bottle insert assemblies comprises: a first bottle insert arranged proximate to the first sidewall and defining a first bottle opening configured to receive a first portion of a bottle; and a second bottle insert arranged proximate to the second sidewall and longitudinally aligned with the first bottle insert, the second bottle insert defining a second bottle opening configured to receive a second portion of the bottle.

Abstract: A tray for holding one or more articles includes a plurality of panels extending at least partially around an interior space of the tray, the plurality of panels including a bottom panel, at least one lower side panel, at least one upper side panel, and at least one end panel, and a plurality of end flaps foldably connected to a respective panel of the plurality of panels, the plurality of panels forms a plurality of separably connected tray portions such that the tray is separable into respective tray portions.

Abstract: The present invention relates to a collapsible tray with foldable sides that includes a trapezoid panel and two triangle panels. Panel connectors secure together in a movable manner each triangle panel to the trapezoid panel. Side panels are movably interconnected at each end to the foldable side. A base is movably interconnected to each foldable side and each side panel. In use, when a collapsing force is applied to the trapezoid panel or the side panel, the adjacency between the trapezoid panel and the triangle panel folds inward allowing the foldable side, and the side panels to fold flat on top of the base. A drawer is slidably connected to the base where a user can slide the drawer out from the bottom to access contents inside and slide the drawer back under the base for storage. The drawer is useable by the user when the collapsible tray is closed.

Abstract: A transport container for carrying one or more generally planar objects having a base configured to support the one or more generally planar objects. First and second side walls are removably coupled to opposing ends of the base. The first and second side walls are movable substantially along a first axis between an extended position and a contracted position. The first side wall is spaced from the second side wall by a first distance when the first and second side walls are in the extended position and by a second distance when the first and second side walls are in the contracted position. The first and second side walls are movable substantially along a second axis between a deployed position and a collapsed position. The first and second side walls have a first height in the deployed position and a second height different than the first height in the collapsed position.

Abstract: A gas cylinder pallet, including a base, an attachment frame placed on the base, two receptacles arranged below the base and configured to interface with a respective fork tine of a transport device, and an RFD tag arranged below the base between the receptacles. Wherein the gas cylinder pallet is at least 90% formed from metal.