Abstract: An aerial vehicle includes: a main body; two main wings arranged to the main body; two main wing tilting control units coupled to the main wings to control the main wings to tilt independently; two main propulsion units arranged to the main wings; tail wings arranged to a rear side of the main body; a rudder arranged to the tail wing; a rudder tilting control unit to control the rudder to tilt; a tail propulsion unit arranged to the rear side of the main body; a tail tilting control unit to control the tail propulsion unit to tilt; a power unit to provide power to the main and tail propulsion units; and a position control unit to control the main wing tilting control units, the main propulsion units, the rudder tilting control unit, the tail propulsion unit, the tail tilting control unit to adjust position of the aerial vehicle.

Abstract: This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a fuselage or wing. The UAV may include a tail and/or a swing arm that is rotatably coupled to the fuselage and that rotate between different positions. The swing arm may be selectively coupled to cargo. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon.

Abstract: An aircraft system includes a wing member and a plurality of unmanned aircraft systems selectively connectable to the wing member. The wing member has a generally airfoil cross-section, a leading edge and a trailing edge. The unmanned aircraft systems have a connected flight mode while coupled to the wing member and an independent flight mode when detached from the wing member. In the connected flight mode, the unmanned aircraft systems are operable to provide propulsion to the wing member to enable flight. The unmanned aircraft systems are operable to be launched from the wing member to perform aerial missions in the independent flight mode and are operable to be recovered by the wing member and returned to the connected flight mode. Thereafter, in the connected flight mode, the unmanned aircraft systems are operable to be resupplied by the wing member.

Abstract: A solar cell module for an unmanned aerial vehicle is disclosed. The solar cell module includes a carrier base and a solar cell unit. The carrier base is disposed on the unmanned aerial vehicle. The solar cell unit has a plurality of solar cells attached to the carrier body. A ratio of the power provided by the solar cell unit to the weight of the solar cell module is equal to or greater than 0.1 (W/g).

Abstract: A semi-automated lock assembly is provided and includes a housing, a pawl rotatably coupled to the housing to occupy and rotate between retracted and erected positions relative to the housing and a torque generating assembly. The torque generating assembly is secured within the housing and is coupled to the pawl to apply torque assist to an erecting rotation thereof without opposing a retracting rotation thereof.

Abstract: An aircraft lavatory comprising an enclosure having a door, a first side wall, a rear wall, a ceiling, and a second side wall, wherein the second side wall includes a sink, the second side wall defining a plane and wherein the sink is inwardly disposed from said plane. To create space for a stowage compartment, an additional side wall parallel to, and adjacent to, said second side wall is formed. This space houses a stowage compartment accessible from outside said lavatory, the stowage compartment formed between said second side wall and said additional wall.

Abstract: A galley cooling system for an aircraft includes a trolley compartment which includes a cooling unit. A first cooling fluid manifold connects to a cooling fluid outlet or a cooling fluid inlet and has a first cooling fluid manifold wall defining a portion of a lateral boundary of a receiving space of the trolley compartment. A first cooling fluid opening is in the first cooling fluid manifold wall connecting the first cooling fluid manifold to the receiving space of the trolley compartment. A second cooling fluid manifold connected to the cooling fluid inlet or outlet of the cooling unit has a second cooling fluid manifold wall defining a portion of an upper boundary of the receiving space of the trolley compartment, a second cooling fluid opening in the second cooling fluid manifold wall to connect the second cooling fluid manifold to the receiving space of the trolley compartment.

Abstract: Components and systems of an aircraft seating assembly are disclosed. The aircraft seating assembly can include a seat pan, a connection frame, and one or more mounts for removably coupling the seat pan to the connection frame. The aircraft seating assembly can include a back support having a removably coupled cushioning member. The aircraft seating assembly can include a tilt system which can allow the back support to articulate relative to the connection frame. The aircraft seating assembly can include a retention system coupled to the back support, the retention system can retain an object in place when in a closed configuration.

Abstract: Tubular bodies for use in frames for seats of vehicles such as aircraft are described. A tube can include a sidewall that has a variable thickness along the length of the tube. The variable thickness of the sidewalls can result in the tube having a variable inner diameter along the length of the tube. The tube may also include a variable outer diameter.

Abstract: Systems and methods for de-icing an aircraft surface. The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells formed in the recess, together or alternatively, according to the designed effect on the erosion shield surface.

Abstract: A system and method for monitoring icing conditions that are suitable ice formation on an aircraft and propulsion system. The system includes instrumentation that instantaneously detects ambient humidity, ambient temperature and ambient pressure. The sensed information is transmitted to a controller that evaluates the information to determine whether certain pressure, temperature and humidity criteria are favorable for icing and, declaring icing conditions. The system also includes an aircraft engine-mounted ice mitigation system. When conditions for ice formation are favorable, the controller either informs the pilot that conditions for ice formation are favorable or automatically activates the ice mitigation system, or both. The pilot optionally may inactivate the ice mitigation system. When sensed conditions indicate that conditions for ice formation are not favorable, the controller determines whether the ice mitigation system is activated and inactivates the system if activated.

Abstract: An apparatus comprising a conductive network and one or more Faraday cages, wherein the one or more Faraday cages and conductive network are configured to integrate with a parachute and be packed, deployed, and recovered without damaging the parachute, one or more Faraday cages, or conductive network. A system comprising a conductive network and one or more Faraday cages, wherein the one or more Faraday cages and conductive network are configured to integrate with a parachute and be packed, deployed, and recovered without damaging the parachute, one or more Faraday cages, or conductive network. A method comprising arranging one or more Faraday cages to at least partially shield a conductive network, wherein the one or more flexible Faraday cages and conductive network are configured to integrate with a parachute and be packed, deployed, and recovered without damaging the parachute, one or more Faraday cages or conductive network.

Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.

Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.68×RFP?0.518, such that the propulsion engine may operate at a desired efficiency.

Abstract: An air supply plenum for an engine, the plenum being disposed upstream of an air intake of the engine, the air intake being provided in a casing of the engine. The air supply plenum includes a first lateral wall and a second lateral wall which together form a conduit in which an air flow flows as the engine functions. Each lateral wall includes a step which forms a transverse recess relative to the direction of the air flow in the air supply plenum, such that an aerodynamic separation occurs in the step when the engine is operating.

Abstract: An inerting system for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

Abstract: A method of recovering performance of an air separation module (ASM) is described. A recovery system includes an air source providing inlet air, a filter to output clean air and a heater heating the air. The ASM is coupled to the system and comprises a hollow fiber membrane to output nitrogen enriched air (NEA) exhaust. The method comprises operating the system with the air source and heater in a default condition; measuring an initial purity of NEA exhaust; adjusting the air source and/or heater based on the initial purity; operating the system after adjusting the air source and/or heater; returning the air source and heater to the default condition; measuring a recovered purity of NEA exhaust; and determining whether the recovered purity is within tolerance. If the recovered purity is within tolerance, system operation is terminated. If the recovered purity is not within tolerance, the steps are repeated.

Abstract: Combined modality hover drift cueing methods, systems and computer readable media are disclosed. For example, some implementations can include a system comprising one or more sensors, and a combined modality hover drift cueing controller coupled to the one or more sensors and configured to determine hover drift and to control a plurality of indicators in response to determined hover drift. The system can also include a mode selector coupled to the combined modality hover drift cueing controller and configured to provide an indication of mode selection between one of a first mode, a second mode and a third mode, wherein the first mode is a combined modality mode. The system can further include a peripheral vision hover drift indicator coupled to the controller and mounted on an inside surface of an aircraft cockpit, and a tactile feedback indicator coupled to the controller.

Abstract: Systems and methods are disclosed for passively detecting air turbulence using one or more infrasonic sensors mounted on an aircraft. The system may include one or more infrasonic sensors that are mounted on the aircraft and configured to detect infrasound. The system may also include a processor configured to receive output signals from the one or more infrasonic sensors and detect air turbulence away from the aircraft based on the output signals received from the one or more infrasonic sensors. The detected air turbulence may include natural or man-made turbulence including wake turbulence, clear air turbulence, mountain waves, or events such as a rocket launch.

Abstract: A vehicle attitude display such as a Primary Flight Display presents pitch and bank information by displaying a vehicle avatar as fixed, with respect to a moving artificial horizon while displaying a movable symbol at a position along the vehicle avatar that is proportional to the symmetry of the vehicle. Parts of the display are dynamically emphasized or de-emphasized to support rapid assimilation of key data. Display format may be dynamically adjusted depending on vehicle use conditions. Display is intended for use both in-vehicle, and remotely.

Abstract: Systems and methods for lightning strike materials are disclosed. The material may include a carbon fiber tow. Carbon nanotubes may be grown on carbon fibers within the carbon fiber tow. The carbon nanotubes may cause the carbon fibers to separate, decreasing a carbon tow fiber volume fraction of the tow. The growth of the carbon nanotubes may be controlled to select a tow fiber volume fraction of the tow. The lightning strike material may transmit electricity to decrease damage to the composite structure in case of a lightning strike.

Abstract: A rotorcraft and an automatic landing system and method thereof are provided in the present disclosure. The automatic landing system of the rotorcraft includes a controller, a laser emitter, a camera, an electronic governor and a motor configured to drive a propeller of the rotorcraft to rotate. The laser emitter and the camera are both locate in a bottom portion of an airframe of the rotorcraft. The laser emitter has two emission heads, laser beams emitted from the two emission heads respectively are symmetrical about a central axis, the central axis is perpendicular to a horizontal plane of a ground, and an angle between each laser beam and the central axis is an acute angle. Simply with an operation of the laser emitter, the camera and the controller, the flight speed and displacement of the rotorcraft can be controlled to realize automatic landing in the present disclosure.

Abstract: An integrated aircraft lighting and display panel includes high-density arrays of micro-scale light-emitting diodes (LED) set into a flexible printed circuit board (PCB). The PCB and LED arrays may be set into structural layers corresponding to overhead panels, side panels, bin panels, divider panels, doorway panels, or other interior structural panels of the aircraft. The LED arrays may be activated by a controller to provide cabin lighting, indicate aircraft signage, display high-resolution image or video graphics, or any simultaneous combination of all three. The panel may have a translucent or transparent decorative outer skin which may mimic the outward appearance of wood, stone, bamboo, or other decorative materials while the integrated lighting and display panels are inactive. Highly reflective core materials, such as an aluminum core in a honeycomb pattern, may guide the luminous output of the LED arrays through the outer skin.

Abstract: A method and apparatus for automatically aligning and connecting a passenger boarding bridge (PBB) with the passenger door of an aircraft or other vessel. A sensory suite module includes cameras and sensors to scan the apron for obstacles and identify an aircraft based on external features. The sensory suite module also includes one or more high-precision active laser line profilers to detect the vertical and lower edges of an aircraft door. A controller module provides precise control and movement of the distal end of the PBB and guides the distal end of the PBB to the passenger door. The system can be activated by a remote triggering panel module.

Abstract: A tool assembly includes a support frame including support beams and support mounts supporting the support beams. The support frame is rigid and used to transport the tool assembly. A support tool is supported by the support frame and includes a faceplate and a supporting grid structure formed with the faceplate as a monolithic structure defined by a series of AM layers. The faceplate has a supporting surface at a top of the support tool for supporting a working component. The supporting grid structure engages the support beams such that loads are transferred between the support tool and the support frame through the support beams. The support frame maintains dimensional stability of the support tool during transport and when resting within an allowable tolerance of the support tool.

Abstract: Systems and methods are provided for a curved aircraft substructure repair stiffener. The curved aircraft substructure repair stiffener may be formed by cutting a flat pattern, cutting a plurality of slits into the flat pattern, and bending the flat pattern a plurality of times. The curved aircraft substructure repair stiffener may be coupled to a portion of an aircraft to strengthen a portion of the aircraft. In certain examples, the portion of the aircraft may have been weakened due to repairs and the curved aircraft substructure repair stiffener may strengthen the section. In certain examples, one or more web stock may be coupled to the curved aircraft substructure repair stiffener to further stiffen the curved aircraft substructure repair stiffener.

Abstract: A method for planning the acquisition of images of areas Z1, . . . , ZN of the Earth, by a spacecraft on a mission around the Earth. Each area Zi of the Earth being associated with a request Ri such that a visual accessibility time interval Ti corresponds to the area Zi. For each interval Ti, discrete acquisition opportunities for acquiring area Zi are determined such that a start date, a period of execution, a local kinematic constraint and a weight is associated with each of the discrete acquisition opportunities. The discrete acquisition opportunities for acquiring areas Zi are grouped into a set D. The discrete acquisition opportunities Di of the set D are categorized by ascending start date. The kinematic compatibility between the discrete acquisition opportunities of set D is assessed. An optimal sequence of discrete acquisition opportunities is determined having a maximum weight, and being kinematically compatible.

Abstract: A propulsion system for an orbiting vehicle such as a low-Earth orbit (LEO) satellite includes a set of surfaces over which a gas passes during orbital flight, and a plurality of electrodes on the surfaces. The electrodes are configured to create an electric field having a spatial field pattern in response to field signals, experienced by passing gas molecules as an oscillating field having a frequency on the order of a polarization-resonance frequency of the molecules to impart a propulsive traveling-wave dielectrophoretic force to the passing molecules. The electrodes extend over sufficient area to impart sufficient traveling-wave dielectrophoretic force to the gas to overcome aerodynamic drag and thereby sustain orbital flight of the vehicle. A power source applies the field signals to the electrodes, providing sufficient power to overcome power lost to aerodynamic drag and thereby sustain orbital flight.

Abstract: A passive thermal system for use in satellites includes a solid radiator panel with a plurality of heat pipes attached to a surface thereof. In addition to their heat transporting capability, the heat pipes strengthen the radiator panel to which they are coupled. In some embodiments, the heat pipes are structurally modified to increase their area moment of inertia.

Abstract: A method comprises operating a remote sensing vehicle comprising a host bus platform and a variable pitch instrument platform movably coupled to the host bus platform in at least one degree of freedom. The method comprises establishing a pointing position and scanning a target surface with the variable pitch instrument platform. The variable pitch instrument platform is dynamically movable relative to the host bus platform to vary the pointing position of the variable pitch instrument platform, thereby decoupling payload pointing from the host bus platform. Thus, payload data collection is independent of attitude control of the host bus platform. A method is provided of varying ground-sample-distance (GSD) value with a remote sensing vehicle. A remote sensing vehicle comprises a host bus platform and a variable pitch instrument platform for scanning or data collection of a target surface, and an dynamic coupling device (e.g.

Abstract: A folding unit for producing packages from sealed packs having at least one flap to be folded, the folding unit including a conveying device carrying at least one pushing element arranged for interacting with the at least one flap, and a supporting element onto which the conveying device abuts when the at least one pushing element interacts with the at least one flap. The conveying device also includes at least one rolling element rolling onto the supporting element.

Abstract: A method of filling a container with a viscous content by providing a container that has an inner surface formed by using a thermoplastic resin and, specifically, an olefin resin, applying an edible oil or a liquid paraffin on the inner surface of the container to form an oil film thereon, and filling the container that has the oil film formed on the inner surface thereof with a viscous content that has a viscosity at 25° C. of not less than 100 mPa·s.

Abstract: An apparatus (1) for the production of plastics material liquid containers (10) with a conveying device (2) which conveys the plastics material containers (10) along a pre-set conveying path (P), with a shaping device (4) which shapes plastics material pre-forms into the plastics material containers (10), with a first filling device (12) which is arranged downstream of the shaping device (4) along the conveying path and which fills the plastics material containers (10) with a liquid, and with a cooling device (8) which is arranged between the shaping device (4) and the first filling device (12) and which cools at least one area of the wall of the plastics material containers (10) by acting upon it with a flowable medium. According to the invention the cooling device has a second filling device (8) which fills a liquid into the container, which liquid is used for cooling a base area (10a) of the plastics material container (10).

Abstract: A fully automated pharmaceutical product packaging machine is capable of selectively depositing one or more different solid pharmaceutical products into an individual cavity for each of a plurality of individual patient product package cavities. The system employs a plurality of solid pharmaceutical product dispensing canisters which are capable of selectively dispensing a pre-designated number of solid pharmaceutical products. The machine fills a template containing temporary storage cavities and the template is automatically positioned over a sheet of clear plastic material containing a plurality of cavities corresponding to the cavities in the template. A barrier between the cavities in the template and the sheet of clear plastic material is moved and the pharmaceuticals in the template cavities drop into the corresponding cavities in the clear plastic sheet of material.

Abstract: A bag forming device and a bag machine are provided. The bag forming device comprises at least two bag forming units, wherein each bag forming unit comprises a deflection element and a folding element, and the forming tubes of the folding elements are arranged in a first direction in sequence. The packaging film is moved in a moving route when moving through the deflection element, and film moving positions are provided in the deflection element in the moving route for passing through of the packaging film to make deflection of the packaging film. The present invention reasonably adjusts the moving direction of the packaging films, and the direction of the longitudinal openings of the packaging films after longitudinal folding.

Abstract: A former assembly for forming and fabricating bags from flexible sheet material is provided. The former assembly can include a base plate having an aperture that extends from a first surface to a second surface thereof. A bracing post can be attached to the base plate on the first surface proximate the aperture. An annular space can be formed between the tube and the base plate. The annular space can be sized for the passage of the flexible sheet material.

Abstract: A winding device for loads includes a reel-holder roll adapted for receiving a reel of an extensible plastic film; a vertical column, along which the reel-holder roll is movable; and a lifting plane adapted to receive a load movable along the column, so that the winding device can be used as both a winder and a lifter for forming the load.

Abstract: A hydraulic steel strapping machine for strapping a steel strip around a package, including a clamping and cutting section and a tensioning section. An objective of the present invention is to minimize the weight and the volume of the steel strapping machine. The clamping and cutting section comprises a clamping cylinder, disposed on a top position of a front end of the hydraulic steel strapping machine along a Z direction and supported by a support frame, for driving a linkage mechanism. A cylinder pin is disposed in the linkage mechanism along a X direction and is sleeved by a lifting lug fixed onto a bottom surface of a piston of the clamping cylinder. A pressing part is sleeved around the cylinder pin, a cutter, a return spring and a transverse cutter are disposed below the pressing part. The linkage mechanism comprises two groups of connecting rods.

Abstract: The object of the invention is to realize an apparatus for automatically and precisely filling single containers in succession with a pre-defined amount of products; each container is filled with two distinct loads of products, wherein the first load is determined according to its weight roughly measured, and the second load is determined numerically based on the difference between said first load and a pre-defined conventional weight; the apparatus comprises a first conveyor, a second conveyor loaded automatically with the products transported by the first conveyor, a third conveyor which is loaded with the agricultural products transported by the second conveyor and that transfers the products poured and present onto it inside a succession of single containers, weighing means able of weighing the total weight of the products on the whole present on the second conveyor, wherein the third conveyor is able of transferring the products poured and present on it in a succession of single containers; there is arra

Abstract: A food storage appliance is provided including a housing, a lid pivotally attached to the housing movable between an open and closed position, an elongated heat sealing element, an elongated resilient bumper mounted on an underside of the lid with a plurality of elastic members which bias the bumper into an extended position when the lid is open, and when the lid is moved to the closed position the bumper sandwiches a portion of a food storage container to be sealed against the heat sealing element while the elastic members allow the bumper to adjust to maintain even pressure on the food storage container along the elongated heat sealing element.

Abstract: A sterilization unit comprises at least one nozzle pipe for injection of a sterilization agent into a packaging container to be sterilized. The sterilization unit is driven to move in an axial direction, in a downward stroke and an upward stroke, corresponding to a longitudinal direction of the nozzle pipe such that it is inserted into an open end of the packaging container during sterilization thereof. The nozzle pipe is suspended such as to be displaceable in relation to the sterilization unit, in the axial direction.

Abstract: A sand bag shovel having an elongated rod connected to a connecting member and the connecting member attached to a scoop. The scoop has a pair of sidewalls and a front wall with tapered panels that form a peak. A funnel is used with the scoop that has a flange that extends outwardly from a top opening.

Abstract: A label applicator, system, and method for applying labels to curved sides of objects, such as cell culture dishes, is provided. In an aspect, the label applicator includes a body having a first side and a second side, the second side comprising a curved surface; a base; at least one first resilient member having a defined length between a first end and a second end; and at least one second resilient member engaging the body and the base, wherein the second end of the at least one first resilient member is configured to removably attach to a label and, when the label is in contact with the second end and an object, to apply a pressure to the label that increases as the at least one first resilient member and at least one second resilient member are compressed. The system may also include a label verifier and/or label verification system.

Abstract: Plastic container (1) being composed of a neck (3), a shoulder (5), a body (4) and a base section (2), where the base section (2) comprises at least two tie members (6a) extending from a central area (8) to the side wall of the base (2). According to the invention, the tie members (6b, 6c) and/or the function of the tie members (6b, 6c) of the base (2) at least in certain areas extend into the body section (4) or into the body (4) and the shoulder section (5) of the plastic container (1).

Abstract: A mold system for forming a container having a longitudinal axis and a transverse direction that extends transverse to the longitudinal axis. The mold system includes a sidewall system for molding the sidewall portion of the container. The mold system also includes a base system for molding the base portion of the container. The base system is operable for forming the entire base portion of the container including a central pushup portion, a contact surface for supporting the container, and at least one strap extending along the base portion in the transverse direction. The strap defines a strap surface that is spaced offset in a direction parallel to the longitudinal axis from the contact surface. The strap surface extends in the transverse direction to be adjacent the sidewall portion such that the at least one strap surface is visible from a side of the container.

Abstract: A biaxially stretched, blow molded container obtained by molding a laminated test tube shaped preform molded by an injection molding process. The container has a neck, a body, and a bottom, and having an outer shell and an inner bag to be laminated in a peelable manner with an outer layer inner surface. The inner bag can be deflated under a pressure drop therein. The outer layer and an inner layer have a laminar structure in which the lamination extends from a predetermined position of the neck to a lower end face. The layers are peeled from each other, starting from a lamination interface between the layers. This interface is exposed outside at the lower end face of the gate mark and can be used as an air intake vent that enables outside air to be taken into the space between layers.

Abstract: A ventilation board is manufactured from a corrugated board comprising at least one depressed portion on both sides of the board in such a way that flutes of the corrugated layer between said depressed portions are exposed to form a plurality of passageways for passage of fluid across the board, in other words, from one side to the other side of the board. The depressed portion is formed by forming a cut on the surface of each side of the board in such a way that the cut penetrating from one side of the board passes through the corrugated layer of the corrugated board but does not pass through the other side of the corrugated board, and depressing the cuts in such a way that the flutes between the depressed portion get exposed in order to provide passageways for passage of the fluid across the board.

Abstract: A laminated package for solid products in powder or grain form, includes a set of stiffening notches, a dispensing mouth with a seal, valves for loading inert gas, in which the lateral folds of the upper face are folded inwards under the front and rear flaps, and the lateral folds of the lower face are folded outward and folded and stuck on the lower face over the front and rear flaps, and a method for forming the package.

Abstract: A method of preparing a container includes manipulating it from an open toward a fully closed configuration. In the open configuration, first and second top end flaps are folded outwardly such that a first pair of handle apertures defined in a first endwall and first top end flap are aligned and a second pair of handle apertures defined in the second endwall and second top end flap are aligned along a first direction. The manipulating step comprises: folding top side flaps inwardly along a second direction until the side flaps are substantially perpendicular to the endwalls, thereby at least partially covering a top opening of the container; and folding the end flaps inwardly until they are substantially parallel with the side flaps, wherein the top side flaps underlie the respective ones of the pairs of handle apertures that are defined in the first and second top end flaps.

Abstract: A return shipping system can include an outer container and a collapsible shock absorbing frame which can include a resilient sheet attached thereto for providing retention or suspension packaging of an article to be shipped within the outer container. The outer container can have a collapsed state suitable for shipping with the collapsible shock absorbing frame nested therein, the collapsible shock absorbing frame also in a collapsed state. The outer container can have an erect or expanded state suitable for shipping with the collapsible shock absorbing frame nested therein, the collapsible shock absorbing frame being in a locked or deployed state and configured to retain an article for shipping within the outer container.