Abstract: A method for manufacturing a locking arm of a carrier connecting rod includes four steps to press a metal sheet via a first stamping die and a second stamping die to form the metal sheet to include a front section, a bent middle section and a rear section. A stopper is formed to the front section, and a recessed area is formed to one side of the bent middle section. A positioning hole is defined through a center of the recessed area. A guide surface is formed to the bent middle section opposite to the recessed area. The locking arm is pivotably connected to the extendable tube of the carrier connecting rod, and the protrusion of the spring member in the extendable tube is guided by the guide surface to be retractably engaged with the positioning hole. The locking arm is manufactured at low cost and has better structural strength.

Abstract: A conveyance seat includes a saddle-type seat on which an occupant sits to straddle and a seat height adjustment unit which is attached below the seat and is able to adjust a height position of the seat. The seat height adjustment unit includes a rotation link which rotates together with the seat with respect to a chassis to adjust a height position of the seat, an upper link support member that is provided between the seat and the rotation link and is used so that an upper end portion of the rotation link is attached thereto, a lower link support member that is provided between the rotation link and the chassis and is used so that a lower end portion of the rotation link is attached thereto, and a flexible cover member that covers the rotation link from the outside in a front to back direction of the seat and a width direction of the seat.

Abstract: An operating device for a human-powered vehicle includes a base member and an operating member. The base member includes a first end portion, a second end portion, a base body, and an accommodating structure. The first end portion is configured to be coupled to a handlebar. The second end portion is opposite to the first end portion. The base body is configured to accommodate at least one of a hydraulic unit. The accommodating structure is configured to accommodate at least one of circuitry accommodating part and a power-supply accommodating part. The operating member is pivotally coupled to the base member about a pivot axis. The accommodating structure is a separate member from the base body. The accommodating structure is detachably attached to the base body at the second end portion.

Abstract: An electric power assist device for bicycles includes: a dynamic brake controller configured to stop supply of a current from a battery to an electric motor and bring a dynamic brake circuit to an ON state when a crank rotational angle is within one or more predetermined crank rotational angle ranges; a pedaling force estimator configured to estimate a pedaling force put on pedals of a bicycle on a value of reverse current caused by a counter electromotive force and detected by a current sensor when the dynamic brake circuit is in the ON state; and a motor drive controller configured to control the electric motor based on the pedaling force estimated by the pedaling force estimator.

Abstract: A hydrofoil board having a hydrofoil and individually controllable flaps configured to be controlled to stabilize the board in a level position even when incurring waves. The flaps are spaced from the hydrofoil to generate a gap, and direct fluid flowing under the hydrofoil through the gap, and over the flaps. The flaps control the pitch and direction of the hydrofoil board when propelled in motion. A processor uses an internal measurement unit (IMU) to obtain orientation and acceleration information of the hydrofoil board. A global positioning system (GPS) unit is also used as an additional speed and location sensor. The processor combines IMU data with a user/rider's input, such as selected speed and direction via handheld wireless controller, and individually controls the flap motors to position the flaps, and the propulsion motor to set speed. In one example, the controller is configured to bring the hydrofoil board to a complete and stabile stop.

Abstract: This invention relates a removable seat for watercraft 10 of the type having a hull or underside 13 and a deck 14, and wherein the deck is connected to the hull by side portions or rails 15, and said deck includes retaining means in the form of one or more recesses 20 formed in or attached to the deck. The seat includes a seat base 112 and a backrest 111, and anchoring means 130 connected to structural means supporting said backrest, said anchoring means extending generally away from a lower portion of said backrest and a rear portion of said seat base, and wherein said anchoring means is locatable within a respective one of the retaining means 20.

Abstract: An offshore floating structure is provided including a floater with positive buoyancy and a keel with negative buoyancy, as well as active and passive suspenders connecting nodes of the keel and the floater with each other. When the keel at the offshore site is lowered by making the active suspenders longer, the passive suspenders, which have a fixed length and are held taut, causes the keel to rotate about the vertical during lowering.

Abstract: A diving mask includes a mask module including a mask frame, a fixing base fixed to the mask frame and a camera support base. The camera support base is detachably mounted to the fixing base, which facilitates installation and removal of the camera. The fixing base includes a receiving space with an insertion opening, a first locking opening located at a side of the receiving space and a second locking opening located at an opposite side of the receiving space. The camera support base includes an insertion portion and an elastic portion extending from the insertion portion obliquely such that when the elastic portion passes over the insertion opening to be received in the receiving space, the elastic portion is capable of restoring to its original state to selectively engage in the first locking opening or the second locking opening, which allows the shooting direction of the camera to be adjustable.

Abstract: A buoyancy modification module for a modular underwater vehicle may include a first frame configured to connect the buoyancy modification module to other modules, and a first pressure hull with a first flooding region and a first dry region. A first pump arranged in the first dry region can pump water out of the surroundings or a neutral-buoyancy reservoir into the first flooding region and out of the first flooding region into the surroundings or the neutral-buoyancy reservoir. A first gas region that is connected to the first flooding region may include a first gas pressure when the first flooding region is completely empty, and a second gas pressure when the first flooding region is completely flooded. A difference between the first gas pressure and the second gas pressure results from a reduction in space available for gas in the first gas region.

Abstract: Various aspects include a robot and method of using the robot, which includes a chassis and a forward propulsion auger. The chassis may include a forward section a rear section; and a maneuvering gimbal. The forward propulsion auger may be positioned on a leading end of the forward section and coupled to a first drive motor. The forward propulsion auger may include at least one fluid nozzle configured to eject a fluid therefrom.

Abstract: A remote-control unit for control a marine vessel is provided with a thruster actuator and engine actuators. When the marine vessel lacks a thruster, the thruster actuator, when operated, causes the remote-control unit to transmit engine control signals to each of at least two engines to achieve a virtual thruster effect by the marine vessel.

Abstract: An unmanned sailing vehicle comprising: a primary hull; a rigid wing rotationally coupled with said primary hull that freely rotates about a rotational axis of said rigid wing; a boom comprising a first end extending from a leading edge of said rigid wing and a second end extending from a trailing edge of said rigid wing, said first end of said boom comprising a counterweight configured to dynamically balance a wing system comprising said rigid wing, said boom, and said tail with respect to said rotational axis of said rigid wing; a tail coupled to said second end of said boom; a control surface element disposed on said tail and configured to aerodynamically control a wing angle of said rigid wing based on a position of said control surface element; and a controller configured to determine a control surface angle and generate a signal to position said control surface element.

Abstract: Systems, apparatuses and methods provides for technology that moves a locking vent door from an opening position to a locking position, where in the opening position, the locking vent door opens a locking vent, and in the locking position, the locking vent door closes the locking vent. When the locking vent door is in the locking position, the technology prohibits movement of a handle from an engaged position to a disengaged position. When the locking vent door is in the opening position the technology moves the handle from the engaged position to the disengaged position, moves a lock from a locking position to an unlocking position, and moves a pressurization vent door from the pressurization position to the depressurization position based on the lock being moved from the locking position to the unlocking position.

Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

Abstract: An aircraft including a fuselage with one or more wings extending from the fuselage. The aircraft may include one or more apertures in a surface of at least one of the fuselage and the one or more wings. The one or more apertures may be configured to enable air to pass through the one or more apertures when the aircraft is flying.

Abstract: One embodiment is an aircraft including a fuselage; a wing connected to the fuselage; first and second booms connected to the wing on opposite sides of the fuselage; first and second forward propulsion systems attached to forward ends of the first and second booms; first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms; first and second wing-mounted propulsion systems connected to outboard ends of wings; and first and second wing tips fixedly connected to outboard sides of the first and second wing-mounted propulsion systems; wherein the first and second wing-mounted propulsion systems and the first and second wing tips are collectively tiltable between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode.

Abstract: A wing structure for a vehicle includes a plurality of multi-connecting-rod structures, the multi-connecting-rod structures are arranged along the main body of the vehicle, each of the multi-connecting-rod structure being arranged in a direction extending from a main body of the vehicle to a wingtip, each of the multi-connecting-rod structures comprising a plurality of connecting rods, and the connecting rods that are adjacent to each other being connected by a motor, a plurality of groups of ribs are sleeved onto each of the multi-connecting-rod structures, and each group of the ribs comprises a plurality of rib units, wherein in the same group of the ribs, adjacent rib units are connected by a ball hinge. The present technical solution can perform adjustment on a complex flow field or environment, the motion speed and the motion efficiency are significantly improved, and high maneuvering actions can be achieved.

Abstract: An apparatus includes a frame and a plurality of propellers coupled to the frame and configured to produce sufficient thrust to allow the apparatus to hover. Each propeller from the plurality of propellers having a horizontally oriented blade and a first propellor from the plurality of propellors overlapping a second propellor from the plurality of propellers in a vertical plane.

Abstract: A flow body for an aircraft is disclosed having a stiffening structure and a flow surface at least partially enclosing the stiffening structure, the flow surface having a leading edge and a trailing edge at a distance to each other in a chordwise direction, the flow body including a first heating device attached to or integrated into the flow surface in a first chordwise section, a second heating device attached to or integrated into the surface body in a second chordwise section. The first chordwise section and the second chordwise section are distanced from each other, the first chordwise section is closer to the leading edge than the second chordwise section, and at least the second heating device comprises an electric heater.

Abstract: A unmanned aerial vehicle (UAV) includes a fuselage including a top, a bottom, a cavity that forms a cargo bay between the top and the bottom, and a lower access opening in the bottom for lowering a payload from the cargo bay. A movable stage is coupled to the fuselage and adjustable between an upper position in which the stage is above the cargo bay and a lower position in which the stage is at the bottom of the fuselage, the stage including an opening extending through the stage. The UAV also includes a winch disposed in the fuselage and a tether coupled to the winch. The winch is configured to be secured to the payload and is movable through the opening in the stage so as to raise or lower the payload.

Abstract: An in-flight risk management system includes an eye sensor, a seat sensor, and one or more in-flight risk management computers that perform operations including: obtaining history information for a flight crew member, obtaining flight information associated with a flight on which the flight crew member will be present, determining, based on the history information and the flight information, a predicted fatigue profile for the flight crew member, determining, based on the predicted fatigue profile for the crew member, one or more fatigue indicator profiles for the flight crew member, obtaining, from at least one of the eye sensor or seat sensor, one or more measured fatigue indicator values associated with the flight crew member, generating, based on the one or more measured fatigue indicator values, one or more updated fatigue indicator profiles, and generating, based on the one or more updated fatigue indicator profiles, an updated predicted fatigue profile.

Abstract: An interior aircraft lighting assembly comprises: at least one infrared lighting device for emitting infrared light; at least one further lighting device for emitting visible light; a lighting assembly controller for controlling an operation of the at least one infrared lighting device and of the at least one further lighting device; a supplementary infrared lighting device controller; and a power supply network, which is configured for supplying electric power from the lighting assembly controller to the at least one further lighting device. The supplementary infrared lighting device controller is tapped into the power supply network. The lighting assembly controller is configured to provide an electric trigger pulse on the power supply network for activating the at least one infrared lighting device.

Abstract: A lavatory system within an internal cabin of a vehicle includes an enclosure defining an interior chamber, a first lavatory unit within the interior chamber, and a second lavatory within the interior chamber. The first lavatory unit is adjacent to the second lavatory unit. In at least one embodiment, a lavatory within an internal cabin of a vehicle includes an interior chamber defined by one or more outer walls, and a storage compartment extending outwardly from at least one of outer walls. The storage compartment defines an internal storage space that connects to the interior chamber. In at least one embodiment, a lavatory includes a first lavatory unit, a second lavatory adjacent to the first lavatory unit, and a containment compartment common to the first lavatory unit and the second lavatory unit.

Abstract: An aircraft lavatory monument is provided that includes a first lavatory including a first door providing access to the first lavatory from an aisle of an aircraft; a second lavatory proximate the first lavatory, the second lavatory including a second door providing access to the second lavatory from the aisle of the aircraft; and a movable wall disposed between the first lavatory and the second lavatory, the movable wall including a latching mechanism positioned on an exterior edge of the movable wall and accessible from the aisle of the aircraft, where the latching mechanism, responsive to being in a locked position, causes the movable wall to be positioned at a first position separating the first lavatory from the second lavatory and providing privacy therebetween, and where the latching mechanism, responsive to being in an unlocked position, allows the movable wall to collapse thereby forming an enlarged bathroom space.

Abstract: The invention relates to an aircraft seat assembly (14a; 14b; 14c; 14d) comprising at least one aircraft seat device (46a; 46b; 46c; 46d) and at least one additional aircraft seat device (48a; 48b; 48c; 48d) which are arranged at least partly next to one another in at least one common column of seats (36a; 36b; 36c; 36d) and each of which can be adjusted between a sitting position and a lying position. According to the invention, the lying direction (64a; 64b; 64c; 64d) of the at least one aircraft seat device (46a; 46b; 46c; 46d) is oriented in the opposite direction to another lying direction (96a; 96b; 96c; 96d) of the at least one other aircraft seat device (48a; 48b; 48c; 48d).

Abstract: An environmental control system includes an ambient air conduit and a bleed air conduit, an electric compressor connected to the ambient air conduit and a mechanical compressor connected to the electric compressor. The electric compressor is supported for rotation independent of the mechanical compressor. A turbine is operatively connected to the mechanical compressor, the turbine connected to both the ambient air conduit and the bleed air conduit to provide conditioned air to a conditioned air conduit. Computer program products and methods of providing conditioned air to conditioned air loads are also described.

Abstract: A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, each of which includes an electric motor to drive operations thereof, and a supplemental power unit (SPU). The SPU is configured as a thermal engine paired with a generator and is configured to generate electrical power. The first and second hybrid-electric engines are operable normally and off, respectively, with electrical power generated by the SPU being diverted to the electric motor of the second hybrid-electric engine.

Abstract: A system (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, includes at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).

Abstract: A system and method for a blended wing body aircraft with permanent tanks is presented. The aircraft comprises a blended wing body and at least a tank permanently attached the blended wing body. The at least a tank is configured to store liquified gas fuel and further comprises at least a vent configured to vent gaseous fuel from the at least a tank and an insulation to reduce thermal transfer to the liquified gas fuel inside of the at least a tank.

Abstract: An auxiliary power unit system of an aircraft includes an auxiliary power unit (APU), a cooling unit for the APU including a heat exchanger, an air inlet in communication with the APU and/or with the cooling unit, an air inlet door unit located at the air inlet, a first duct configured to draw air into the APU and having an entrance in communication with the air inlet, a second duct having an entrance in communication with the air inlet, the heat exchanger being at least partially located within the second duct, an air turbine located within the second duct downstream of the heat exchanger, and an electrical generator coupled to the air turbine.

Abstract: This application discloses an apparatus and method for displaying pilot control authority. This apparatus and method include using a controller to identify a condition of an aircraft and determine a limitation in pilot control authority. Using this, an indicator on a display may show a visual representation of a pilot control authority, the limitations thereof, and a pilot input.

Abstract: A device for preventing access to an area of an aircraft includes a first vertical frame post designed for attachment to a structure of the aircraft, a second vertical frame post designed for attachment to a structure of the aircraft, a barrier element displaceably connected to the first frame post and including a latching element for detachable connection of the barrier element to the second frame post, and a delay unit including a spring-loaded damping cylinder displaceable into a damping position by a locking movement in opposition to a spring force. The delay unit is designed to release the latching element after a time delay.

Abstract: A composite-material aircraft structure includes: a laminated structure formed by laminating composite-material layers; and a curved structure having a circumferential length difference in a longitudinal direction. The laminated structure is maintained in the entire part including the curved structure. In each of the composite-material layers, the reinforced fiber is constituted by a single continuous fiber not including a joint portion and includes a partial slit portion and a notch portion that is the slit portion in an open state.

Abstract: An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

Abstract: Systems and methods for interlining checked bags between two unaffiliated airlines. The traveler may purchase the interlining service and be assured that the checked bags associated with that service will be automatically transferred from their first flight to their next flight. The traveler does not have to collect the checked bag, and then re-check it onto the second flight, which may allow a traveler to say with in the security zone of the airport, where permitted by airport flow.

Abstract: The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with a main accelerator tube system (MAT). The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and/or for delivery of a payload.

Abstract: A self-deployable array of panels includes a plurality of panels, each panel having a first compressed panel thickness state and a second expanded panel thickness state, and including a spring bias element biased to the second expanded panel thickness state. A plurality of locking hinges hingedly couple each of the panels to an adjoining panel. Each locking hinge is biased to an open position. A release of stored potential energy of both of the spring bias element biased to the second expanded panel thickness state, and the locking hinges biased to the open position causes the self-deployable array of panels to self-deploy from a folded stowed state. A single part offset locking hinge is also described.

Abstract: According to some embodiments, a spacecraft includes an electronics housing having a sun-facing side. The spacecraft further includes a peel-and-stick thermal control material coupled to the sun-facing side of the electronics housing. The peel-and-stick thermal control material includes a non-metallic optical interface coating, a carrier film, and an adhesive.

Abstract: A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

Abstract: A configurable spacecraft attachment and deployment system and a method of constructing a configurable spacecraft attachment and deployment system are provided herein. In one embodiment, the configurable spacecraft attachment and deployment system includes: (1) a connecting structure configured to secure at least one spacecraft to a launch interface, (2) an actuating assembly configured to constrain the spacecraft to the connecting structure before deployment thereof and release the spacecraft from the connecting structure when deployed, and (3) a deploying mechanism coupled to the connecting structure and configured to eject the spacecraft from the attaching structure, wherein the connecting structure, the actuating assembly, and the deploying mechanism are modular components and the connecting structure and deploying mechanism are selected to form the system based on parameters of the spacecraft.

Abstract: A system for landing and charging an autonomous unmanned aerial vehicle (UAV) is disclosed. The UAV comprises a set of battery powered rotors to fly through the air. The UAV further comprises a landing peg that projects beneath the body configured to be received by a socket of a corresponding landing base. The landing base can have a funnel top to make landing easier. The landing peg has a set of power transfer means that connect with power transfer means in the landing base to recharge the batteries of the UAV. The UAV can be guided to land in the landing base by a ring of LEDs on the landing base.

Abstract: Aspects of the disclosure relate to a packaging machine for packaging articles, apparatus for a packaging machine and to a method of packaging articles. The packaging machine comprises an article manipulation apparatus. The article manipulation apparatus comprises a first conveyor for conveying packages. The packages each comprises a carton having at least one displaceable article disposed therein. An article orientation device comprises a tool head movable synchronously in a downstream direction with the first conveyor. The tool head has at least one article gripper for engaging with a displaceable article in the carton. The at least one article gripper is rotatably mounted to the tool head. An article displacement device comprises at least one article displacement tool. The article displacement tool is receivable in an opening in a carton to engage and displace the displaceable article such that it protrudes through a second opening in said carton.

Abstract: An apparatus for filling and sealing bags intended for containing banknotes includes a generally parallelepiped-shaped container, with side walls, a bottom and an upper lid provided with an opening for allowing entry into the container of a bag, made up of flexible plastic film, and of banknotes intended to be introduced into the same bag. The apparatus includes a pair of sealing bars arranged at the upper end of the container and a system for controlling and moving the bars between their respective opening and closing positions.

Abstract: The present disclosure provides a liquid loading device for loading liquid into a product. The product includes a cavity and a liquid inlet communicated with the cavity. The liquid loading device includes a loading module to load liquid into the cavity through the liquid inlet. A sensor senses a pressure in the cavity and generates at least one pressure value. A controller is coupled to the sensor and the loading module, and controls the loading module to operate based on related data. In addition, the present disclosure also provides a liquid loading method.

Abstract: Systems, methods, and apparatus for storing perishable items under reduced pressure conditions. Total atmospheric pressure within a vacuum chamber containing a perishable item is reduced below a total pressure limit. Oxygen partial pressure and total pressure within the vacuum chamber are monitored. When oxygen partial pressure falls below a lower oxygen partial pressure limit, an oxygen-containing gas is admitted to raise oxygen partial pressure above the lower oxygen partial pressure limit. When the total atmospheric pressure reaches or exceeds the total pressure limit, total pressure is once again reduced. The vacuum container or chamber comprises a section of cylindrical pipe open at both ends, a first end cap and a second end cap, and formed of a plastic material. Notwithstanding that the pipe and end caps are formed of plastic, they are formed with a structure capable of withstanding pressure created by a high vacuum in the vacuum container.

Abstract: A high throughput, efficient, and simplified unloading and packaging systems and methods for large-scale production of pharmaceutical units (104) using additive manufacturing. The systems and methods may unload, inspect, package, and trace pharmaceutical units, produced by an additive manufacturing system (900), that are not damaged or deformed. The unloading and packaging system can include one or more unloading and packaging devices (100). The unloading and packaging device can include a modular configuration having modules. Individual modules to be arranged in any relative order, at any location, and with any number in the unloading and packaging device. The flexibility of the modular configuration allows one or more modules to be removed or added at any given time due to, e.g., expansion, downsizing, module repair, module upgrades, etc. High throughput can be achieved by operating unloading and packaging devices independently.

Abstract: A high-precision vertical turnover machine for packaging a photovoltaic assembly includes a first drum conveyor line, a horizontal transfer mechanism driving the first drum conveyor line to move left and right between a receiving station and a first turnover station, a first turnover mechanism located on the left side of the first drum conveyor line, a second turnover mechanism located on the left side of the first turnover mechanism, a distance detecting sensor detecting the distance of the front surface of the photovoltaic assembly on the first turnover mechanism or the distance of the rear surface of the photovoltaic assembly on the first turnover mechanism, and a lifting correction transfer mechanism moving, according to a detection result of the distance detecting sensor, the photovoltaic assembly on the first turnover mechanism to a second turnover station and placing the photovoltaic assembly on the second turnover mechanism precisely.

Abstract: A container and method of making the same is provided herein. The container may be configured to hold a dispensable material. The container can include a first sheet of a material and a second sheet of the material. The first sheet of material includes a folded portion across a first end of the first sheet. The second sheet of material includes a folded portion across a first end of the second sheet. The first sheet and the second sheet are bonded together across the folded portion of the first sheet and the folded portion of the second sheet to form a tip portion. The tip portion includes a passage between the folded portion of the first sheet of material and the folded portion of the second sheet of material.

Abstract: A vacuum station comprising a main housing and a pair of arms extending from the main housing. The arms are configured to hold a roller. The main housing has a front face and a rear face, with the front face having a recess therein. An air path extends from the front face to the rear face. The vacuum station also includes a removable plate having a plurality of suction holes therethrough located within the recess in the front face of the main housing. The removable plate is removably connected to the main housing by magnets. A sheet of labels can be held to the removable plate by a suction force through the air path in the main housing and the suction holes in the removable plate.

Abstract: A labelling machine for labelling a stack of elements is intended for the automated placement of a label located between elements forming part of the stack, and includes a support structure; printing means configured for printing a label to be placed on a stack of elements; a head supported on the support structure, the head being provided with printing means, the head being movable and adjustable at least in height through guiding means and motorized means; and separation means intended for separating two elements superimposed on one another forming part of the stack, such that they vertically separate an element to be handled, generating a free space between the two elements intended for the arrangement of the label.