Abstract: Examples relate to modular cargo handling. An example system for positioning and securing cargo includes a pair of rails extending longitudinally in a parallel configuration. The system includes floor beams coupled between coupling links (e.g., sets of wheels) that removably couple to the pair of rails such that each floor beam can move along the length of the rails with less friction. Each floor beam can include one or more coupling points that can be used to secure units of cargos to the floor beams.

Abstract: An aircraft that includes a cabin interior that is bifurcated into first and second sides and includes a pilot zone and a passenger zone aft of the pilot zone, a pilot seat positioned in the pilot zone and on a first side of the cabin interior, and first and second rows positioned in the passenger zone. The front row includes first and second front seats positioned on first and second sides of the cabin interior, respectively. The first and second front seats are angled away from one another and the second front seat is positioned forwardly of the first front seat. The back row includes first and second back seats positioned on first and second sides of the cabin interior, respectively.

Abstract: A tray table assembly and aircraft passenger seat arrangement including the same, the tray table assembly including a rail, along which a carriage slides, disposed within an alcove, from which a tray table can be deployed via a link connecting the tray table to the carriage. The link provides both the connection between the tray table and carriage for positioning the tray table horizontally along the rail and the pivotable connections between the tray table, link, and carriage for adjusting the tray table vertically, perpendicular to the rail path. Thus, the tray table assembly may be hidden in the alcove in a stowed position, partially deployed with the tray table vertically offset from the carriage, fully deployed with the tray table outside of the alcove, and any position in between.

Abstract: The present invention concerns a mounting structure and arrangement. More particularly, but not exclusively, this invention concerns a mounting structure and arrangement for mounting aircraft furniture in an aircraft. The mounting structure comprises a first connection assembly configured for engagement with a first mounting track; and an associated first support. The first support is configured to abut the first mounting track at a location fore or aft of the first connection assembly. The provision of the support may reduce the number of connection assemblies required to properly secure an item of aircraft furniture in an aircraft cabin using the mounting structure.

Abstract: Systems and methods for limiting infiltration of cabin air into the flight deck of an aircraft, where the systems include at least one upper nozzle disposed adjacent to and above an outer upper edge of a flight deck doorway and directed downwardly, and at least one lower nozzle disposed adjacent to and below an outer lower edge of the flight deck doorway and directed upwardly; a conduit system to deliver air from a flight deck air supply to the upper and lower nozzles; and an airflow controller configured to provide sufficient air flow from the flight deck air supply to the upper and lower nozzles to create directional airstreams across the gaps between the closed flight deck door and the upper and lower edges of the flight deck doorway, so that the airstreams limit infiltration of cabin air into the flight deck via the gaps.

Abstract: An aircraft outflow valve with a heat exchanger is disclosed herein. The aircraft outflow valve can include a heat exchanger that includes an air flow path. Air can flow through the air flow path and exit the outflow valve through an opening at the end of the air flow path. Such airflow can regulate the internal pressure of the aircraft and can also dissipate heat from the outflow valve. The outflow valve can further include a liquid coolant flow path. The liquid coolant flow path can be coupled to liquid coolant lines of electronics of the aircraft. Thus, heat from the electronics of the aircraft can be dissipated through heat transfer between the coolant and the outflow valve, which is accordingly cooled by the airflow through the heat exchanger.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.

Abstract: A control system for aircraft anti-icing is disclosed including a conduit coupled at a first end to a source of hot high-pressure bleed air, a control valve in fluid communication with the conduit and an injector head, wherein the control valve is in electronic communication with a controller and configured to regulate the flow of bleed air between the conduit and the injector head, and a first sensor in electronic communication with the controller and configured to report a first data. The system may initialize a control valve to an initial regulated pressure. The system may determine a control temperature and control the control valve based on the control temperature, the first data, and a set value.

Abstract: A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

Abstract: Apparatus and methods for supporting human external cargo from the hoist of a hoist-equipped helicopter are provided. The apparatus has at least one personal harness for supporting a user; and at least one harness segment with a top end point attachable to the helicopter hoist through an attachable fitting and at least one bottom end point directly or indirectly attachable to the personal harness. The harness segment, and the personal harness externally support the user from the helicopter hoist and allows the user to be safely suspended from the helicopter in order for work or rescue operations to be administered by the user.

Abstract: Energy storage systems for aircraft and methods of operating the same are provided. The energy storage system may include a main battery, a propulsion power bus, a non-critical bus, a critical bus, and an engine starter bus. The propulsion power bus may be configured to convey electricity, which is supplied by the main battery, to an electric propulsion machine configured to provide propulsion for the aircraft. The non-critical bus may be configured to convey electricity to a hotel load on the aircraft. The critical bus may be configured to convey electricity, which is supplied by the main battery, to a critical load on the aircraft. The engine starter bus may be configured to convey electricity, which is supplied by the main battery, to an electric starter for a gas turbine engine, where the gas turbine engine is configured to power the electric propulsion machine.

Abstract: Electromagnetic gyroscopic stabilizing propulsion system method and apparatus is an electric gyroscope that creates magnetic fields used to rotate its flywheel. The rotation of its flywheel creates both a gyroscopic effect and thrust with airfoil shaped spokes. The invention attaches to an airframe through an articulating joint that causes the axle of the gyroscope to precess in a vertical orientation regardless of the movements/angle of the airframe. The gyroscope's thrust aligns itself with the axle of the gyroscope. The net effect is that the invention has tremendous efficiency, no external drive because it is also a motor, tremendous power from magnetic leverage of the flywheel, and stability because of the gyroscopic effect.

Abstract: Aircraft spars with integrated power cells, and associated systems and methods are described. A representative aircraft wing spar includes a spar body extending in a spanwise direction, and having a plurality of apertures also extending in a spanwise direction, with individual apertures positioned to receive multiple electrical power cells.

Abstract: A nacelle for a gas turbine engine includes at least one hinge axis extending along the nacelle. At least one cowl is mounted to the nacelle, along the at least one hinge axis, by a plurality of hinges. The plurality of hinges includes at least one latch. The at least one latch includes a clevis and a tang. The clevis and the tang of the at least one latch are configured to receive a hinge pin, through a pin aperture, when the at least one cowl is in a closed condition.

Abstract: A thrust reverser of a nacelle may include an translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

Abstract: Control logic for a power sharing system on a hybrid propulsion aircraft, utilizing parallel multiple control loops outputting difference commands which provide bumpless transfer between control loops without integrator wind up or reset logic, allowing for efficient load distribution between electric generators and batteries powering electric motors.

Abstract: An aircraft includes a fuselage, an engine, a pylon, a nacelle cowling, and a gearbox assembly. The engine is spaced apart from the fuselage and the pylon is disposed between the fuselage and the engine. The accessory gearbox is fixed to the engine and is at least partially disposed in the pylon.

Abstract: Aircraft air separation systems having a compressed air source arranged to supply compressed air, an air separation module arranged to receive air from the compressed air source, the air separation module arranged to separate air into nitrogen enriched air and oxygen enriched air, wherein the nitrogen enriched air is supplied to a fuel tank of the aircraft, and a source of mixing air arranged to fluidly supply the mixing air at a location between the compressed air source and the air separation module such that the mixing air is selectively mixed with the compressed air to generate treated air that is supplied to the air separation module.

Abstract: A fuel oxygen conversion unit includes a contactor; a fuel gas separator, the fuel oxygen conversion unit defining a circulation gas flowpath from the fuel gas separator to the contactor; and an isolation valve in airflow communication with the circulation gas flowpath for modulating a gas flow through the circulation gas flowpath to the contactor.

Abstract: A fuel oxygen conversion unit for a vehicle or an engine of the vehicle includes a contactor; a mechanically-driven, first fuel gas separator defining a liquid fuel outlet and a stripping gas outlet, the fuel oxygen conversion unit defining a liquid fuel outlet path in fluid communication with the liquid fuel outlet of the first fuel gas separator; and a second fuel gas separator positioned in fluid communication with the liquid fuel outlet path at a location downstream of the first fuel gas separator.

Abstract: A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.

Abstract: A method of operating a fuel oxygen reduction unit for a vehicle or a gas turbine engine of the vehicle is provided. The fuel oxygen reduction unit including a contactor and a fuel gas separator, and further defining a stripping gas flowpath in flow communication with a stripping gas inlet of the contactor and a stripping gas outlet of the fuel gas separator. The method includes receiving data indicative of a parameter of a stripping gas flow through the stripping gas flowpath or of a component in flow communication with the stripping gas flow through the stripping gas flowpath; and determining an operability condition of the fuel oxygen reduction unit, or a component operable with the fuel oxygen reduction unit, based on the data received indicative of the parameter of the stripping gas flow or of the component in flow communication with the stripping gas flow.

Abstract: A fuel system for an aircraft includes a fuel source and a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path and stripping gas supply path are each in airflow communication with the fuel source.

Abstract: An engine includes a combustion section and a fuel delivery system in fluid communication with the combustion section for providing fuel to the combustion section. The fuel delivery system includes a fuel oxygen reduction unit defining a circulation gas flowpath. The fuel oxygen reduction unit includes a gas oxygen reduction unit positioned in the circulation gas flowpath for reducing an oxygen content of a flow of stripping gas through the circulation gas flowpath and a pre-heater positioned in thermal communication with the circulation gas flowpath upstream of the gas oxygen reduction unit.

Abstract: An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.

Abstract: An emergency localization device for initiating an emergency measure, wherein the emergency localization device comprises a control unit, at least one acceleration sensor and at least one position sensor, the control unit being configured to receive a plurality of motion and/or position parameters from the acceleration sensor and/or from the position sensor, and by evaluating the plurality of motion or position parameters to determine a risk level for an emergency using a predefined logic, and to initiate an emergency measure if the calculated risk level exceeds a predefined threshold. The emergency localization device is reliable, robust and largely independent of aircraft-mounted systems.

Abstract: A hard landing indicator mountable to a landing gear of an aircraft is provided. The landing gear has components displaceable toward each other upon the aircraft experiencing a landing. The hard landing indicator includes a first portion securable to one of these components and a second portion that projects outwardly from the first portion and oriented toward another component of the landing gear to be positioned within a path of displacement of the second component toward the first component. The second portion is impacted by this component upon this component being displaced during a hard landing of the aircraft. The impact leaves a visual mark on the second portion of the hard landing indicator to indicate that a hard landing has occurred. A landing gear equipped with and a method of installing such indicator are also provided.

Abstract: The present invention relates to a method and an apparatus for recording a flight log of an unmanned aerial vehicle (UAV), a storage medium and a computer device. A log message is generated, the log message is stored in a message storage area, and a buffer area obtains the log message in the message storage area. The log message buffered in the buffer area is written into a memory card when the log message buffered in the buffer area meets any of the following conditions. The conditions include: the log message buffered in the buffer area occupies a storage capacity that reaches a capacity threshold or the log message is buffered in the buffer area for a number of times that reaches a threshold number of times. Each log message is generated independently and each generated log message is written into the buffer area. The event trigger mechanism has good real-time performance and can effectively reduce a probability of log message loss.

Abstract: This invention discloses an aircraft control method, apparatus and an aircraft. The invention relates to the field of aircraft control technologies. The method includes: obtaining ambient luminance data by a luminance sensing apparatus of an aircraft; determining whether the ambient luminance data satisfies a luminance value required for normal running of a vision system of the aircraft; and adjusting, when the ambient luminance data does not satisfy the luminance value required for normal running of the vision system of the aircraft, a working status of a light emitting apparatus on the aircraft to change light emitting luminance of the light emitting apparatus. The foregoing aircraft control method, apparatus and the aircraft can accurately learn a flight environment in which the aircraft is located, thereby effectively implementing vision positioning on the aircraft and more conveniently controlling the aircraft.

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: According to an embodiment, a drone-storable pole elevation system comprises a pole vertically fastened to a ground, an elevation device formed through the pole to be moved up or down by external power, and at least one drone station formed on the elevation device and having a top opening to receive a drone.

Abstract: The invention relates to a navigation satellite (10, 10?, 10?), in particular for a medium earth orbit (MEO), having a housing (12) and a navigation antenna (16) connected to the housing (12) for emission of navigation signals in a preferred direction. Furthermore, the navigation satellite (10, 10?, 10?) has an optical communication system (22) for unidirectional or bidirectional signalling having at least one other satellite advancing in the direction of movement and/or having at least one other satellite following in the direction of movement. The navigation satellite (10, 10?, 10?) has a holder (for example as navigation antenna), which is arranged rotatably on the housing (12) about an axis of rotation (17), the optical communication system being (22) arranged on the holder.

Abstract: A medical dispensing system with dispensing and pathway components, each of which includes a plurality of dispensers and pathways, respectively. The dispensing and pathway components are controlled to minimize contamination between the items being dispensed. Both the dispensing and pathway components have arcs around which the dispensers and pathways are arranged.

Abstract: Embodiments of a cell traverse for an aseptic region of a filling machine for filling packages with flowable products are provided. The cell traverse includes a frame structure with at least one first lateral longitudinal structure, at least one second lateral longitudinal structure opposite the first longitudinal structure, and a plurality of transverse elements arranged between the first and second longitudinal structures and connecting the longitudinal structures. Between the longitudinal structures and the transverse elements there are a plurality of cells of the cell traverse for receiving packages to be filled. At least some of the transverse elements are connected exclusively in an form-fit and/or force-fit manner to the longitudinal structures.

Abstract: A bagging mechanism for packaging ice into plastic bags is provided. The bagging mechanism includes a roll support for supporting a roll of plastic, a feeding unit for feeding a predetermined length of plastic from the roll of plastic along a feeding path, a sealing unit positioned along the feeding path for sealing the length of plastic across a width thereof to define a bottom and a top of the plastic bag, a breaching unit positioned along the feeding path downstream from the sealing unit for breaching at least one layer of the length of plastic, thus defining an opening at a top of the plastic bag, and a spreading unit positioned downstream from the breaching unit, the spreading unit having a plurality of elongated fingers adapted to extend between layers of the plastic and hold the top of the plastic bag open while it is filled with ice.

Abstract: Disclosed is a reconfigurable device for dispensing/distributing tablets in the blister pockets of a packaging strip subjected to longitudinal movement in a substantially horizontal plane of a packaging machine having a blister-packer, the reconfigurable device having a frame designed to be mounted on the blister-packer, the frame having a front attachment wall preferably arranged vertically, at least one accessory for dispensing/distributing the tablets in the blister pockets of the strip, the accessory being designed to be mounted removably on the frame. The device includes an intermediate interface intended to be attached removably to the frame, against the front attachment wall thereof, in order to support the at least one accessory. The interface includes at least one drive member of a mobile element of the accessory/accessories supported thereby.

Abstract: The present invention relates to a method for gathering-up a tubular film portion on at least two gathering fingers of a packaging machine and to a gathering apparatus of a packaging machine for carrying out the method as claimed in the invention. The method is distinguished in that the tubular film portion is expanded at least in a part region when being gathered-up onto the gathering fingers. The gathering apparatus as claimed in the invention is distinguished in that the gathering fingers can be driven into a gathering-up position for gathering-up the tubular film portion, in which gathering-up position the tubular film portion is expanded at least in a part region.

Abstract: The invention relates to a method for sealing partly prepared meals (30), wherein the meals (30) are positioned on a dish unit (1) and covered with a film (15). An interspace (16) between the dish unit (1) that is provided with a meal (30) and between the film (15) is partly evacuated. The sealing machine (200) for sealing a partly prepared meal (30) positioned on a dish unit (1) comprises a film feed (201) in order to feed a film (15) to the dish unit (1), and a suction apparatus (202) in order to evacuate an interspace (16) between the dish unit (1) provided with a meal (30) and between the film (15). Using the sealing machine (200), the interspace (16) between the dish unit (1) provided with a meal (30) and between the film (15) is partly evacuated.

Abstract: An apparatus and method for filling containers with value documents and to a system for processing value documents, wherein the apparatus has: a container receiving device which is adapted to receive a container stack having two or several containers for receiving value documents, a lid receiving device which is adapted to receive a lid stack having two or several lids for closing the containers, a container removal device which is adapted to remove, preferably, the respectively lowermost container from the container stack, a closing device and a transport device which is adapted to convey the container removed from the container stack to a filling station, in which the container can be filled with value documents, and to convey the container filled with value documents to the closing device which is adapted to remove a lid from the lid stack and close the filled container with the removed lid.

Abstract: This invention relates to an apparatus for packing products in cartons; the apparatus includes a first feed line for feeding cartons, a second feed line for feeding products, a plurality of pushing elements, each of which includes a first carriage configured to run on a first rail defining an active path and a second carriage configured to run on a second rail defining an inactive path; a diverting unit is provided which is configured to divert the pushing elements in transit towards the active path or the inactive path and which includes a first diverting rail and a second diverting rail; also provided are detection means for detecting the presence of the carton and/or of the product and switching means for switching the diverting unit.

Abstract: Embodiments of a cell traverse for an aseptic region of a filling machine for filling packages with flowable products are provided. The cell traverse includes a frame structure with a first lateral longitudinal structure and a second lateral longitudinal structure opposite the first longitudinal structure. Also included are a plurality of transverse elements arranged between the first and second longitudinal structures and connecting the longitudinal structures. Between the longitudinal structures and the transverse elements a plurality of cells of the cell traverse are formed for receiving packages to be filled. The cell traverse also includes insert elements, which each have the frame structure, in particular at least one longitudinal structure and/or at least one transverse element, and at least some of the insert elements are detachably connected to the frame structure of the cell traverse.

Abstract: A system for packaging a food product in a container generally includes a conveyance apparatus operable to move trays in a machine direction, a delivery apparatus operable to deposit the food product into cavities of the trays, and a positioning apparatus operable to position covers relative to the trays. The positioning apparatus is configured to position each cover on a respective tray to overlap a flange of the respective tray. The system also comprises an ultrasonic bonding apparatus configured to receive the flange and the cover of each container in the nip between a first bonding module and a second bonding module. At least one of the first bonding module and the second bonding module vibrates at an ultrasonic frequency and delivers ultrasonic energy to at least one of the cover and the flange to seal the container.

Abstract: A sterilizer-filler nozzle assembly for an aseptic packaging machine comprises a form section 40, a product supply duct that has a product outlet portion 4 which lies downstream of a distal end of the form section 40, a sterilization medium supply duct that has a sterilization medium outlet portion 16 which lies between the distal end of the form section 40 and the product outlet portion 4, and an exhaust duct that has an exhaust inlet portion 22 which lies between the distal end of the form section 40 and the product outlet portion 4. A gas supply duct is provided that has a gas outlet portion 10 which lies between the sterilization medium outlet portion 16 and the product outlet portion 4.

Abstract: The present invention relates to a method and an arrangement for emptying a flexible container (30) of bag contents (31) therein. Such a flexible container includes a bottom opening (34) in its lower end and a top opening (37) in its upper end. When this container is to be emptied of its contents, it is placed in an emptying arrangement in such a way that the container's bottom opening lies below the top opening. The flexible container is then turned around an axis of rotation that unites said bottom opening and top opening. The turning motion produced is gradually propagated from the container's upper end towards its lower end whereby the container is twisted into a tight string (32). This twisting contributes to removing the bag contents (31) from the flexible container via the bottom opening (34) provided or made therein.

Abstract: Bottles and containers and methods of use have been disclosed. In an aspect, the bottle comprises a body that includes a first end forming a first aperture and a second end forming a second aperture. The first aperture has a first diameter and the second aperture has a second diameter. The first diameter can be larger than the second diameter. The bottle further includes a first cap removably coupled to the first end of the body and a second cap removably coupled to the second end of the body.

Abstract: A container can include a bottom panel, a sidewall structure attached to a bottom panel and forming a cavity for receiving an article. The sidewall structure can extend substantially orthogonally from the bottom panel. The container can include an at least partially round top panel. The top panel can be configured to latch to the sidewall structure to enclose the cavity. The top panel can be attached to the sidewall structure and/or the bottom panel. In certain embodiments, the top panel can be separate from the body.

Abstract: An apparatus for a tracking device enclosure is disclosed. According to an embodiment of the present invention, the apparatus includes an enclosure that holds a motion tracking device to a shipping container. Further, the enclosure includes one or more first flaps that secure a first motion tracking device within the enclosure such that the first motion tracking device does not move in relation to the enclosure. The one or more first flaps secure the first motion tracking device based on a shape of the first motion tracking device. Also, the enclosure includes one or more second flaps that secure a second motion tracking device within the enclosure such that the second motion tracking device does not move in relation to the enclosure. The one or more second flaps secure the second motion tracking device based on a shape of the second motion tracking device.

Abstract: A repulpable moisture resistant protein box having a composite structure with a fluted medium, a top backing board secured to one side of the fluted medium and a bottom backing board secured to the other side of the fluted medium. The backing boards are impregnated with a hydrogenated triglyceride on the wire side and the fluted medium is also impregnated with a hydrogenated triglyceride. The backing boards each have an outer felt side surface coated with styrene acrylic co-polymer. The protein boxes have a higher compression, moisture resistance and are recyclable.