Abstract: A method for controlling a rotary wing aircraft includes determining a measured airspeed of the rotary wing aircraft based on data from a pitot probe, determining an estimated airspeed of the rotary wing aircraft based on rotor control commands, and determining a blended airspeed based on both the measured airspeed and the estimated airspeed.

Abstract: Disclosed is a collective control arrangement for a helicopter having a plurality of rotor blades, the collective control arrangement comprising: an armrest for a pilots seat, the armrest comprising an elongate channel; and a collective handle comprising: a first end slidably disposed in the elongate channel for coupling to one or more helicopter actuators that control collective pitch of the plurality of rotor blades; and a second end for gripping by a pilot. Advantageously the armrest comprises an elbow support portion configured to be located backwards of the hollow when the armrest is installed in the helicopter.

Abstract: A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.

Abstract: A tiltrotor aircraft is designed to accommodate rotors of different diameters, as well as corresponding wings and fuselages with different span and length, while maintaining very high parts commonality, especially with respect to drive train and power source. This enables design and operation of a fleet of such aircraft with significantly different rotor diameters, which are nevertheless optimized for different missions. In preferred embodiments the rotors are configured to have high stiffness and low weight to reduce aero-structural dynamic issues across the fleet. Also in preferred embodiments drive systems are designed for a full range of speed, torque, and power associated with all intended rotors. Turboshaft engine speeds are restricted to a narrow RPM range, so that a single gearset can be replaced to achieve the desired rotor RPM. Also in preferred embodiments, aircraft in a fleet can differ in folded length, empty weight, payload length by up 50%.

Abstract: A personal aircraft having a frame and at least one rotor. The frame includes a body panel at least partially defining a seat for a user. The at least one rotor is rotatable about a rotational axis. The at least one rotor is operably coupled to a respective portion of the frame and is provided on a first side of the personal aircraft.

Abstract: Disclosed herein is a payload delivery device. The payload delivery device is configured for delivering an explosive component. The payload delivery device comprises a first module having an interior cavity for containing an explosive component. The payload delivery device further comprises at least one attachment module connected to the central module via a connection means. The at least one attachment module having an interior cavity for containing an additional component.

Abstract: A delivery device to deliver a product from an aerial location includes a body defining a payload holding region. The delivery device may further include a coupling mechanism configured to couple the body to a primary vehicle. The delivery device may further include a control feature configured to change a flight characteristic of the body. A method for delivering a product may include positioning a first unmanned aerial vehicle within a threshold distance of a delivery location. The method may further include releasing a second unmanned vehicle from the first unmanned aerial vehicle once the first unmanned aerial vehicle is within the threshold distance. The method may further include causing the second unmanned vehicle to reach the delivery location. The method may further include activating a delivery mechanism to release the product from the second unmanned vehicle to deliver the product to the delivery location.

Abstract: A detachable, self-balancing, pod for an unmanned aerial vehicle. The pod is configured to hold a plurality of different payloads, and to dynamically shift the location of these payloads in order to maintain an optimal center of mass (center of gravity) for the combination pod and UAV. The pod will have its own processor, as well as processor-controlled actuators to shift the payload location inside the pod to optimize balance, and to dispense the different individual payloads in different locations as directed.

Abstract: A self-locking mounting insert is provided for attaching a panel to a vehicle structure. A tab of the panel may be inserted into a keyway of the insert. The tab may slide between a latched and unlatched position within the keyway. When in the latched position, a latching member prevents the tab from being removed from the keyway. By moving a magnet proximate to the latching member, the latching member may be magnetically impelled to move to an unlatched position to permit the tab to be removed from the keyway.

Abstract: A light module for an elongated interior aircraft light comprises a plurality of light sources, which are configured for emitting light of different colors and which are arranged next to each other, forming an array of light sources extending between a first end and a second end along a longitudinal direction (LD). The plurality of light sources include a first light source, which is arranged at the first end, and a second light source, which is arranged at the second end. The first and second light sources are those from the plurality of light sources that result in a difference of the illuminating properties between the first and second light sources being the smallest difference that is possible for all potential pairs of light sources formed from the plurality of light sources.

Abstract: An augmented reality (AR) system for an aircraft obtains an aircraft pose, determines a passenger pose relative to a window, and computes a field-of-view of the passenger. Operations select a set of passenger-relevant points of information (POIs) from a database that satisfy a relevance rule to the real-world objects viewable by the passenger through the window. For each of the passenger-relevant POIs in the set, operations determine an AR indicia to be displayed, and an AR indicia pose where the AR indicia is to be rendered on a display device. Operations generate a display command based on the AR indicia and the AR indicia pose for the passenger-relevant POIs in the set. Operations provide the display command to the display device to display renderings of the AR indicias with the AR indicia poses to augment the real-world objects viewed by the passenger through the window.

Abstract: A method is disclosed herein, including detecting, by a processor, a signal received from a camera, the signal including an image. The method further includes processing, by the processor, the received signal to identify an image included in the signal and determining, by the processor, that the signal includes a discreet message, the discreet message is embedded within an image. The method further includes decrypting, by the processor, the discreet message embedded within the signal and sending, by the processor, the decrypted message to be displayed.

Abstract: A legrest assembly is disclosed. The assembly may include a plurality of frame members. The assembly may include one or more closeout panels arranged proximate to an opening within a storage compartment and configured to at least partially form the opening within the storage compartment and at least partially enclose one or more gaps formed between sidewalls of the storage compartment, the plurality of frame members, and a divan seat frame. The assembly may include a plurality of panel doors configured to open or close, the plurality of panel doors including a plurality of integrated frame members configured to couple the plurality of doors to a frame member of the plurality of frame members. The assembly may include a panel door latch mechanism configured to open the plurality of panel doors, the panel door latch mechanism including a door handle and a door latch assembly.

Abstract: In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe. The body of the air data probe and the components positioned within the body of the air data probe can be constructed from differing materials, resulting in differing coefficient of thermal expansions for each component. Retention features are added to a housing to prevent an epoxy potting from expanding outside its intended region and preventing damage to the electronic components within the housing.

Abstract: In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe, ensuring proper functionality of the air data probe. But the elevated temperatures can have negative effects on the electronic components positioned within the air data probe. Therefore, thermal isolating features are added to a housing to thermally isolate the heated parts of the air data probe from the electronic components within the air data probe, which are required to stay relatively cool for proper functioning.

Abstract: A ring release system is configured to releasably couple a parachute to a payload. The ring release system may comprise a series of release rings affixed to a riser. At least one release ring comprises a removable pin, permitting installation of the release ring after associated components have been stitched together, improving the reliability and manufacturability of the ring release system.

Abstract: A propulsion system for an aircraft is provided that includes an electric generator, a compressor, an internal combustion (IC) engine, a turbine, an electric power storage unit, and an electric motor. The compressor is configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure. The IC engine is configured to selectively intake compressor air during operation and produce an exhaust gas flow during operation. The turbine, powered by exhaust gas flow, is in communication with and configured to power the compressor and the electric generator. The electric power storage unit is in communication with the electric generator. The electric motor is in communication with the IC engine. The electric motor is powered by the electrical power produced by the electric generator, and the electric motor is configured to selectively provide motive force to the IC engine.

Abstract: The present disclosure relates to a hydrogen electric hybrid power plant for a hovercar. The hydrogen electric hybrid power plant comprises a first-stage duct, a transition duct and a second-stage duct. An air outlet end of the first-stage duct is connected to the second-stage duct through the transition duct. A hydrogen reactor is arranged in the first-stage duct, and the hydrogen reactor is fixed with the first-stage duct through a plurality of supporting pieces A. A primary filter screen is arranged at a front end of the first-stage duct and fixed on the first-stage duct through a hoop, so that low-altitude sundries and dust are prevented from entering the reactor. A return pipe is arranged, and the problems of oxygen supply, heat dissipation and cooling and the like of the hydrogen reactor are solved through ducted airflow. A motor power supply requirement of a ducted fan is met.

Abstract: Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

Abstract: An assembly for removably mounting an underwing pylon to a rib of an aircraft wing is provided. The assembly has a prismatic body insertable into a prismatic cavity of the underwing pylon, a threaded retaining element having an upwardly tapered outer conical surface, and a vertical threaded pin inserted through a vertical through hole of the prismatic body. The assembly has an anti-rotation device for rotationally locking the threaded retaining element to the prismatic body relative to a vertical axis.

Abstract: Aircraft engine systems include a core assembly having at least a burner section and a fuel cell configured to generate electrical power. A cryogenic fuel source is configured to supply a fuel through a fuel supply line to each of the burner section and the fuel cell for reaction to generate the electrical power. A system controller is configured to direct fuel to each of the combustor section and the fuel cell. The controller determines if an amount of fuel in the fuel supply line is in excess of that necessary for operation of the core assembly and, based on a determination that excess fuel is present, the controller is configured to direct at least a portion of the excess fuel from the fuel supply line to the fuel cell to generate the electrical power.

Abstract: Aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.

Abstract: Aircraft propulsion systems have aircraft systems including at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems includes at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section arranged along an engine shaft. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander is configured to impart power to the engine shaft.

Abstract: An aircraft beacon light comprises an annular light source support having a plurality of light passing portions; a plurality of light sources, arranged on the annular light source support for a radially outwards emission of light flashes; a light detector for sensing a light output level of at least a subset of the plurality of light sources; and at least one optical element for shaping a beacon light output from light emitted by the plurality of light sources, the at least one optical element having at least one light guiding portion for capturing stray light from at least said subset of the plurality of light sources and for guiding said stray light through the plurality of light passing portions and towards the light detector.

Abstract: Disclosed is an aircraft provided with a light signaling system including at least one light-emitting device at the tip of each wing and at least one light-emitting device at the tip of the tail. Each light-emitting device at the wingtip can be arranged in a recess formed in the profile of the wing and include a covering At least one light source and a protective glass can be arranged on the recess so that the outer surface matches the shape of the wing. The inner surface of the protective glass can be provided with at least one local variation in thickness so as to increase the angular aperture of each wingtip light-emitting device in order to ensure the overlap between the light-emitting devices at the wingtip and the light emitted by the light-emitting device on the tail.

Abstract: The invention relates to a method and a system for transfer of baggage between connecting flights from airlines not having an arrangement for baggage check-through. The passenger books a journey and check-in at a departure airport, shifts to a connecting flight at a transit airport and completes the journey at a destination airport. The passenger check-in the baggage at the departure airport and collects the baggage at the destination airport. The journey comprises transfer of baggage at a transit airport between connecting flights from airlines, not having an arrangement for baggage check-through, by having no alliance, codeshare, or interline agreement between one another.

Abstract: A method for the optimized operation of a transport container conveyor system for items of cargo, in particular of an airport luggage conveyor system, includes: a) introducing an item of cargo into the conveyor system at an introduction point; b) providing larger transport containers of a first category and smaller transport containers of a second category for receiving a respective item of cargo; c) automatically recording a dimension of the item of cargo; d) depending on the recorded dimension, automatically assigning the item of cargo to a transport container of a first or second category; e) automatically loading the assigned transport container with the item of cargo; f) transporting the transport container loaded with the item of cargo on active conveyor sections; g) repeating the above steps for further items of cargo. There is also described a novel conveyor system.

Abstract: Systems (100) for assembling stiffened composite structures comprise a layup mandrel (102) and a network (104) of fluid lines (116) configured to be selectively and fluidically coupled to string bladders (118) positioned relative to the layup mandrel (102).

Abstract: This Invention is a new article of manufacture that provides an Aircraft with a modular high-performance Lift Module System that both creates an alternative modular building method to simplify aircraft construction and modification through removable lift modules and also enables the aircraft to change flight direction or begin flying toward any direction immediately from a standstill or while under momentum without body roll and is controlled by computerized electronic controls such as fly-by-wire.

Abstract: In an embodiment, a method includes: collecting usage and maintenance data for a rotorcraft at a computer of the rotorcraft; sending the usage and maintenance data to a fleet management server; generating individualized equipment data for the rotorcraft according to the usage and maintenance data at the fleet management server, the individualized equipment data including a lightweight digital representation of the rotorcraft and technical publications for the rotorcraft, the lightweight digital representation including mesh-based 3D visualizations of each component of the rotorcraft, the technical publications having views referencing the mesh-based 3D visualizations; sending the individualized equipment data to the computer of the rotorcraft; and persisting the individualized equipment data at the computer of the rotorcraft.

Abstract: A space transportation system intended to be mounted on a space launcher comprising a re-ignitable propulsion device and steerable flaps located at a second end and a monitoring unit, each flap comprising an actuating means configured to modify the orientation of said flap, said monitoring unit being configured to control the activation of the propulsion device and individually control the orientation of the flaps in order to implement the following steps: a launch step during which the propulsion device is off and the flaps are in a retracted position; a return step during which the monitoring unit deploys the flaps and individually controls the orientation of the flaps to slow down the system, the propulsion device being off; a landing step during which the monitoring unit controls the propulsion device and the actuating means to orient the flaps to slow down.

Abstract: A spacecraft propulsion system comprises an attitude adjustment thruster system with multiple thrusters (488a-d) receiving heated propellant via a shared thermal capacitance block (275). The thermal capacitance block (275) receives energy from a solar concentrator (320) and stores the heat.

Abstract: A solar space ship yacht is described, with six cylinders attached to a central-core. Contained within are rotating-water-tanks, thus pointing the solar space ship yacht at the sun. Dual parabolics focus the sun's rays onto rods, which eject steam at high velocity, utilizing high pressure pumps. A graviton is also integrated to provide artificial gravity. An incinerator gasifies garbage, thus also providing additional thrust from the gases. The net result is a solar space ship yacht that can travel from orbit to orbit, at high speeds between planets. Domes provide access and views.

Abstract: A plasma reactor is provided together with a method for generating kinetic energy to propel a craft. The reactor includes an inlet for plasma; a reactor core having an interior chamber and an exterior chamber, the interior chamber being configured to rotate within the exterior chamber; a pair of opposing polar field generators, a first polar field generator connected proximal to an inlet of the interior chamber, and a second polar field generator connected proximal to an outlet of the interior chamber, the pair of polar field generators configured to induce a current in the plasma to generate a toroidal flow therein, wherein the toroidal flow compresses the plasma into a z-pinch flow in a central column between the first polar field generator and the second polar field generator; turbine blades located between the interior chamber and the exterior chamber for generating thrust to convert the z-pinch flow to kinetic energy; and an outlet.

Abstract: A control device includes a memory; and a processor coupled to the memory. The processor is configured to acquire a status of each of a plurality of power distribution pathways provided at a moving body, and select a power distribution pathway having low resistance from among the plurality of power distribution pathways based on the acquired status, and cause power to be distributed via the selected power distribution pathway.

Abstract: A device for imaging light, or a source of the light, includes a window for receiving incident light from the source, at least one metasurface, and at least one wedge prism. The metasurface and the wedge prism form a Risley pair and are displaced independently of each other. Each of the metasurface and the wedge prism are operative to deflect the incident light at an angle that is different from an angle of light incident upon them. Each metasurface includes a plurality of sub-wavelength structures that are operative to interact with the incident light received from the window. The device also includes a lens system that is operative to transmit the incident light received from the at least one metasurface and the at least one wedge prism and focuses it on a focal plane.

Abstract: Vehicles systems, assemblies and methods for payload testing are described. A vehicle assembly, for example a suborbital vehicle assembly, has a housing for accommodating a test payload therein, and a payload exposure system coupled to the housing, operable to: open an aperture in the housing to allow exposure of a housed test payload to an in-flight environment; and close the aperture. The payload exposure system may have an actuator, which may have a drive system, for opening and closing the aperture. The actuator may be a linear actuator, whose operative action may be in an axial direction of the vehicle assembly.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

Abstract: An unmanned aerial vehicle (UAV) assembly includes an UAV and an UAV docking station. The UAV docking station includes a housing, an extension piece, and a door. The housing is provided with an accommodation cavity and a hatch communicating with the accommodation cavity. The extension piece comprises an extension cavity and is connected to the housing. The extension piece is disposed on a side portion of a housing end which is near the hatch, and the extension cavity communicates with the accommodation cavity. The door is connected to the housing and disposed at the hatch, and the door is configured to open or close the hatch. A cross-sectional area where the extension cavity communicates with the accommodation cavity is greater than a cross-sectional area of the accommodation cavity. The UAV can be accommodated in the accommodation cavity of the UAV docking station.

Abstract: An autonomous station for providing accommodation of unmanned vehicles like unmanned air vehicles and/or unmanned underwater vehicles on water is provided. Accordingly, the subject matter station includes a floating platform; pluralities of accommodation mechanism for associating said unmanned vehicles provided in said floating platform in order to be charged and fixed; pluralities of movement items for providing movement of the floating platform on water; an energy supply which stores energy for providing electrical energy to said movement items and to the accommodation mechanisms; an energy generation unit for charging said energy supply; a processor unit connected to the movement item in a manner controlling the movement items; a communication unit for providing communication of the processor unit to a main control center.

Abstract: Proposed is a spoon and chopstick automatic packaging apparatus. The apparatus includes a spoon tray supply portion supplying a spoon tray in which a spoon is mounted in a groove formed in a spoon shape, a chopstick tray supply portion supplying a chopstick tray in which chopsticks are aligned and contained, a spoon moving portion sending down the spoon so that the spoon waits at a spoon entrance, a chopstick moving portion sending down the chopsticks so that the chopsticks wait at a container belt automatic opening and closing portion, a rotary type inspection portion in which the spoon and the chopsticks are placed, an image analysis portion checking a sanitary condition of the spoon and a direction of the chopsticks, a packaging portion packaging the spoon and the chopsticks in a separate packaging bag, and a packaging bag storage portion in which the packaging bag is stored.

Abstract: A machine for packaging a product into flexible packages and which comprises one or more forming and filling units for forming and filling the packages; each forming and filling unit extends along a longitudinal axis and comprises at least one nozzle, feed means configured to make advance along the longitudinal axis a tubular casing of the material with which to make the packages and having an internal surface facing the nozzle, first longitudinal welding means for joining together at least two sides of the tubular casing and second longitudinal welding means, disposed downstream of said first longitudinal welding means, and configured to join together at least two portions of the internal surface of the tubular casing in a marginal end volume.

Abstract: A self-propelled wrapping machine movable on a supporting plane to wrap a load with a film, comprises a self-propelled carriage and an upright fixed to said carriage and slidably supporting an unwinding unit provided with a reel of film; an anchoring element provided with a locking system selectively operable in a closed position or in an open position respectively to tighten or to release an initial flap of the film unwound from the reel; a first gripping unit adapted to position and release the anchoring element with the initial flap of film tightened by the locking system arranged on the supporting plane adjacent to the load in an initial step of the wrapping cycle, and adapted to grasp and lift the anchoring element and activate in an open position the locking system so as to release the initial flap of film after at least one turn travelled by the self-propelled wrapping machine around the load wrapping the load with the film.

Abstract: A beverage brewing cartridge includes a base and a plug. The base includes a sidewall, a fillable end having an opening, and a closed end. The plug is configured to close off the opening. A method of constructing a brewing cartridge includes placing the base of the beverage brewing cartridge on a cartridge seat of a cartridge tool with the closed end against the cartridge seat. A cartridge lock retains the base against the cartridge tool. A portion of brewing material is scooped and poured into the base through a mouth of the cartridge lock and the opening of the fillable end of the base, and then tamped into the base. The plug is positioned above and aligned with the opening of the fillable end of the base, and seated into the opening to close the opening, thereby completing construction of the brewing cartridge.

Abstract: An infeed conveyor for a folding apparatus for folding semi-finalized packs containing a pourable product, the infeed conveyor being configured to receive the semi-finalized packs and to transfer the semi-finalized packs to a folding unit of the folding apparatus. The infeed conveyor comprises one or more pushing elements, a conveying device for advancing the pushing elements along an advancement path and a carrier for the semi-finalized packs. The infeed conveyor further comprises a distance detection device for measuring a distance between the pushing elements and the respective semi-finalized packs.

Abstract: Various embodiments of the present disclosure provide a random case sealer configurable into a bypass configuration in which a tape cartridge is out of the path of a case so the tape cartridge does not apply tape to the case as the case moves past the tape cartridge.

Abstract: A method for producing packaged edible materials is provided. The method includes selecting two or more edible materials and an amount thereof based on a purchaser's input. Each of the edible materials is dispensed separately into a packaging unit that includes multiple pods. The packaging unit with the edible material therein is analyzed for metal levels, weight, and optical characteristics. The pods are then sealed with lidding material.

Abstract: A machine for packing elongate bags for use with a waste disposal apparatus is disclosed herein. The machine comprises means for holding a reel of flexible tubing, the flexible tubing wound on the reel as a film having two parallel edges, the flexible tubing, when opened, forming a ring of elongate flexible tubing having an aperture at at least one end. The machine also comprises a pair of gripping means configured to engage and grip a region proximate to each edge of the film and draw the film of flexible tubing off of the reel, and a jig configured to be inserted into the aperture and hold a portion of the film in a ring around the jig, the jig configured to hold the film adjacent to and in engagement with the gripping means. Operation of the gripping means causes the film of elongate flexible tubing to be drawn over the jig and to be gathered in a ring of compacted flexible tubing around a base of the jig.

Abstract: A machine (328) is selectively operative to transport containers and apply markings such as labels, sleeves, decorations and indicia to the containers (340). The machine includes a suspended container conveyor (SC) (320). SC shuttles (336) are engaged with and selectively independently movable around an SC track (330). The SC shuttles include a respective container engagement fixture (338) and are selectively movable to engage an upper portion of a container. In the container engaged position each container is selectively vertically, rotatably and linearly movable so as to be positioned in operative connection with applicators (434, 436). The applicators are selectively operative to apply markings to respective containers that are in operative connection therewith in a precise and repeatable manner.

Abstract: The invention relates to a labelling device, in particular a price-displaying device, for labelling individual packages (2), comprising: a feed assembly (3) for transporting particular packages (2); a label-dispensing assembly (9) for dispensing a label (8) that can be detached from a material strip (10) in a dispensing direction as far as a transfer position; and a label-application assembly (13) for applying the label (8) dispensed in the transfer position onto the surface of the package (2); wherein the label application assembly (13) comprises a label-suction assembly (15) which picks up a label (8) dispensed by the label-dispensing assembly (9) and holds it in the transfer position, from which position the label (8) is transferred to the surface of the package (2). According to the invention, the label-suction assembly (15) is designed to generate a first airflow and to conduct the airflow such that both a suction force and a compressive force are exerted on the label (8) in the transfer position.