Abstract: An outboard motor, includes: an engine; and an accommodation cover forming an accommodation space accommodating the engine. The accommodation cover includes: a lower cover configured to accommodate a lower part of the engine; an upper cover attached to the lower cover and configured to accommodate an upper part of the engine; and a plurality of lock portions provided in a connection part between the lower cover and the upper cover facing the accommodation space and configured to fix the upper cover to the lower cover. A part of the plurality of lock portions includes an interlocking mechanism configured to lock or unlock the part of the plurality of lock portions simultaneously in response to a single operation.

Abstract: There is provided a battery supporting structure to be provided in a vessel, the battery supporting structure including a supporting part that supports a battery, wherein the supporting part is movable between below and above a deck of the vessel by rotating around a rotary shaft provided in the vessel.

Abstract: An example method for launching a high-altitude balloon includes securing a launch collar around a balloon envelope to form a choke point separating an upper portion of the balloon envelope from a lower portion of the balloon envelope. The balloon envelope is structurally secured to a launch platform via a tether that is coupled to the launch collar. The launch collar is configured such that release of the launch collar from the choke point releases the balloon envelope from the launch platform.

Abstract: A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.

Abstract: A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

Abstract: A seat track assembly is disclosed. The seat track assembly includes an elongate titanium crown, an elongate carbon-fiber reinforced polymer (CFRP) flange, and an elongate CFRP base. The elongate titanium crown is configured to removably secure a plurality of seats to the seat track assembly. The elongate CFRP flange is configured to support the elongate titanium crown. The elongate CFRP base has a top, two sidewalls extending vertically from opposing sides of the top, and two bottom flanges each extending laterally outward from a corresponding sidewall of the two sidewalls. A fastener is insertable through aligned holes defined by the elongate titanium crown, the elongate CFRP flange, and the elongate CFRP base to mechanically fasten the elongate titanium crown, the elongate CFRP flange, and the elongate CFRP base to each other.

Abstract: A joining structure adapted to join adjacent tube structures together while providing high strength with low weight. The joining structure may be of composite materials, and may include warp tows in the longitudinal direction of the tubes and have weft tows cross-woven into a fabric, which may be a carbon fiber. The joining structure may be Y-shaped and adapted to join three composite sheets together. The weft tows may also be wound around a central cluster of tows, or tows, which may provide extra strength. The tubes may be pressurized in use, such as in an aircraft fuselage.

Abstract: A turbine engine module having longitudinal axis X including an unducted propeller for rotating about the longitudinal axis X; —at least one flow straightener wiht a plurality of stator vanes extends substantially along a radial axis Z, each stator vane having a root and a blade rising radially from the root; and—a pitch change system for changing the pitch of the stator vanes. At least two adjacent stator vanes are connected to each other by at least one retaining member coupled to the blades of the stator vanes by at least one pivot shaft and mounted radially from the root of the stator vanes. The pivot shaft extends along a pivot axis B coaxial with the pitch adjustment axis A to enable the stator vanes to pivot about the pivot axis B. An anti-vibration unit dampens vibration of the pivot shaft.

Abstract: A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.

Abstract: A control surface system for a body located in an air and/or space vehicle. The control surface system having at least one control surface which is located on the body and which, by moving relatively to the body, enables air flow to be controlled and the air vehicle to maneuver accordingly. The control surface system having at least one actuator which is made of an electroactive polymer material which is located on the body and which changes its form depending on electrical energy and based thereon, triggers the control surface.

Abstract: An avionics system can provide data to a first receiving component associated with a proprietary first protocol and a second receiving component associated with a non-proprietary second protocol. A configuration tool generates a first configuration file comprising instructions for a data access component to provide a first data output to the first receiving component, and a second data output to the second receiving component. The configuration tool can generate a second configuration file including instructions to convert the second data output. The data access component can receive a definition database defining the first protocol to convert the data according to the non-proprietary second protocol. The data access component can provide the requested data to the first and second receiving components in accordance with the non-proprietary second protocol. The second receiving component is configured convert the data received based on the second configuration file.

Abstract: Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

Abstract: A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

Abstract: An unmanned aerial vehicle (UAV) system energized by power lines includes a UAV, a charging mechanism and an electric circuit. The charging mechanism is operatively coupled to a body of the UAV. The charging mechanism can connect to power transmission lines deployed near an air space in which the UAV is airborne and operating. The charging mechanism can draw power from the power transmission lines to power a flight of the UAV. The electric circuit is onboard the UAV. The electric circuit can generate charging currents based on the power drawn from the power transmission lines to power the flight of the UAV while the UAV is airborne.

Abstract: An aerial vehicle, comprising: one or more motors, one or more sensors, and a flight sub-system. The one or more sensors configured to detect data. The flight sub-system includes an attitude controller module; a rate controller module; and a compensator module. The compensator module is configured to: determine a maximum RPM of the one or more motors or a maximum torque of the one or more motors; receive a torque vector from the rate controller module; determine a rotational speed of the one or more motors to generate a desired flight orientation based upon the torque vector; and consider sensor data from the one or more sensors to adjust the rotational speed of the one or more motors.

Abstract: An unmanned cargo loading and transport system adapted for operation with an unmanned aerial vehicle (UAV) comprising a payload pad comprising a plurality of support members movable from an extended mode to a retracted mode when exposed to a lateral force applied to the support members and a payload container adapted to attach to a UAV and pick up cargo from the payload pad by transferring the weight of the cargo from the payload pad to the payload container. The lower portion of the payload container comprises two generally opposed cargo doors movably mounted at opposed sides and movable inwardly to a closed position and outwardly to an open position to receive cargo when the payload container is positioned at the payload pad. The system further comprises a motive power mechanism coupled to the cargo doors for selectively moving the doors between their open and their closed positions.

Abstract: Described herein are methods and systems for picking up, transporting, and lowering a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the winch system may include a motor for winding and unwinding the tether from a spool, and the UAV's control system may operate the motor to lower the tether toward the ground so a payload may be attached to the tether. The control system may monitor an electric current supplied to the motor to determine whether the payload has been attached to the tether. In another example, when lowering a payload, the control system may monitor the motor current to determine that the payload has reached the ground and responsively operate the motor to detach the payload from the tether. The control system may then monitor the motor current to determine whether the payload has detached from the tether.

Abstract: In a lavatory arrangement comprising a vacuum flushing system, the lavatory arrangement comprises a folding toilet bowl.

Abstract: Improved seating arrangements for a vehicle cabin of a passenger transport system, in particular of an aircraft are disclosed. Examples herein provide improved seating arrangements providing a high density of seats and increased PAX numbers while ensuring privacy, comfort and a direct aisle access to each passenger. For example, the seating arrangements provided herein are applicable to narrow body aircrafts and wide body aircrafts, in particular in view of business class solutions.

Abstract: The seating systems comprise a seat module and a seat track assembly comprising a plurality of seat-receiving regions, a seat track, and an electrical distribution system. The electrical distribution system comprises a plurality of track electrical contacts disposed along the seat track in the seat-receiving regions. The seat module comprises a base coupler configured to couple with the seat track at any seat-receiving region and a seat module electrical system having a seat electrical contact. The base coupler and the seat track are configured to position the seat electrical contact in connection with the track electrical contact of any seat-receiving region to which the base coupler is coupled. The methods comprise coupling the base coupler to a seat-receiving region, which comprises forming a connection between the seat electrical contact and the respective track electrical contact of the seat-receiving region, and providing electricity to the seat module via the electrical connection.

Abstract: An insert for an air intake of a suction duct, the insert including an inner portion configured to extend within the suction duct, a mating portion configured for sealingly engaging the air intake, and an outer portion configured for extending outside of the suction duct. The inner portion includes a conduit having a central axis extending along an inlet direction at the inlet end and along an outlet direction at the outlet end, the inlet and outlet directions being non-parallel. The outlet end has a smaller cross-sectional area than that of the suction duct. The insert includes an inlet in fluid communication with the inlet end of the conduit. The outer portion includes a curved lip surrounding at least part of an inlet opening of the inlet, the lip configured to direct a flow into the inlet opening and toward the inlet end of the conduit.

Abstract: A system for stowable propulsion in an electric aircraft that includes at least a propulsor mounted on at least a structural feature that includes at least a rotor and at least a motor mechanically coupled to the at least a rotor, where the motor is configured to cause the rotor to rotate as a function of an activation datum, at least a sensor communicatively coupled to the at least a propulsor configured to detect a position datum as a function of the configuration, generate a clearance datum as a function of the position datum, transmit the clearance datum to a flight controller, and a flight controller communicatively coupled to the at least a propulsor and the at least a sensor configured to receive the clearance datum from the at least a sensor and generate the activation datum as a function of the clearance datum.

Abstract: An electrical propulsor motor may include a stator having a hollow cylinder with an inner cylindrical surface and an outer cylindrical surface, rotor incorporated in a hub of a propulsor and mounted to the stator, including a first cylindrical surface facing the inner cylindrical surface, where the inner cylindrical surface and first cylindrical surface form a first air gap, a second cylindrical surface facing the outer cylindrical surface, wherein the outer cylindrical surface and the second cylindrical surface form a second air gap, and a plurality of axial impeller vanes mounted to at least one of the first cylindrical surface and the second cylindrical surface and within at least one of the first air gap and the second air gap and positioned to force air through the at least one of the first air gap and the second air gap when the rotor rotates about the axis of rotation.

Abstract: In a power supply system of an aircraft, when electric power is supplied from a power generation unit to a drive unit, the electric power is supplied from the power generation unit to the drive unit via a first power transmission path, and a voltage is applied to a second power transmission path by a fault detection circuit in a state in which the power generation unit and the drive unit are disconnected from the second power transmission path, and when the power generation unit is started, electric power of the fault detection circuit is supplied to the power generation unit in a state in which the power generation unit is connected to the second power transmission path.

Abstract: A fuel-cell system for powering an electrical load, the system having first and second fuel cells, each having a positive node and a negative node. The positive node of the second fuel cell is electrically coupled to the negative node of the first fuel cell, and the positive node of the first fuel cell and the negative node of the second fuel cell are electrically coupled to the electrical load. Each fuel cell is electrically coupled to the electrical load without a power converter.

Abstract: In an embodiment, proprotor pitch ranges used during nominal cruise flight may be varied. By selecting ideal combinations of proprotor pitch angle and proprotor rpm, instead of the proprotor blade pitch bearing spending most of its time in a first range, multiple ranges may be alternated between. Additionally, in an aircraft with multiple proprotors, the portion of total thrust produced by each individual proprotor may be varied over time in order to allow for proprotor blade pitch angle to be varied without varying proprotor rpm. By properly cycling between different blade pitch ranges, bearing life can be significantly increased.

Abstract: A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

Abstract: Measures for monitoring and manufacturing tanks for cryogenic liquids. The tank is manufactured in a way that signal and power lines from a control unit to sensors of the cryogenic tank are integrated with the tank walls. The conductive track structure so formed has a layer structure that uses the naturally occurring or artificially generated insulating layer on the tank wall material as a substrate on top of which conductive paths are formed that connect the sensors to the control unit.

Abstract: A tank wall liner for a fuel tank includes a liner body made of a liner material. The liner material is a sealant or composite of sealant and fiber and/or textile materials. Multiple tank wall liners are installed on a tank wall and form a lining surface that seals the fuel in the tank from the tank skin. Also, a tank with the tank wall liner, an aircraft with a tank forming a portion of the fuselage, and methods of manufacturing the tank wall liner and the tank.

Abstract: An installation configuration for a ram air turbine on an aircraft arranged to operate during a low speed operation. An example aircraft includes a fuselage and a lifting body connected to the fuselage and configured to provide a lifting force on the fuselage, the lifting body including a suction surface and a pressure surface disposed on opposite sides of the lifting body from each other, the suction surface extending from a leading edge of the lifting body to a trailing edge of the lifting body. A ram air turbine is coupled to the lifting body and configured to move between a retracted position where the ram air turbine is stowed inside the aircraft and an extended position where the ram air turbine is disposed above the suction surface of the lifting body.

Abstract: A system and method include a phase determination control unit configured to receive position data of an aircraft. The position data includes height of the aircraft, altitude of the aircraft, and distance of the aircraft from one or more locations. The phase determination control unit is further configured to determine variables from messages received from the aircraft. The variables relate to the height of the aircraft, the altitude of the aircraft, and the distance of the aircraft from the one or more locations. The phase determination control unit is further configured to apply fuzzy logic to the variables to determine scores for possible phases of flight of the aircraft, identify a highest score among the possible phases of flight, and determine the highest score as an actual phase of flight of the aircraft.

Abstract: A method and a system for monitoring a laminar flow on a surface of an aircraft is disclosed including observing a surface of an aircraft by an optical sensor, and processing an image data of that surface by an image processing system in order to determine an actual extend of a laminar flow on the surface. The actual extend of the laminar flow on the surface is compared with a previous extend of the laminar flow on the surface, and/or with a potential maximum extend of laminar flow on the surface determined from flight parameters of the aircraft. A reduction or a possible optimization of the laminar flow is detected and further processed to improve the laminar flow.

Abstract: An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV.

Abstract: A method is provided for supporting flight operations of vertical takeoff and landing (VTOL) aircraft in an urban air mobility (UAM) environment that includes a vertiport. The method includes accessing first observed weather data obtained by sensors located on-site at the vertiport and second observed weather data obtained by sensors onboard VTOL aircraft. A data fusion is performed to integrate the first observed weather data and the second observed weather data to produce a collection of weather data that describes the weather in an environment of the vertiport, and an environment of the VTOL aircraft. And a weather map is produced based on the collection of weather data, the weather map illustrating one or more meteorological features of the weather in the environment of the vertiport and/or the VTOL aircraft, the weather map produced for use in supporting flight operations of the VTOL aircraft.

Abstract: Provided is a passenger boarding bridge monitoring device, for passenger boarding bridges each including: a rotunda; a tunnel unit; a travel device; a cab; and detectors that detect a rotational angle of the rotunda and the cab and a length of the tunnel unit. The monitoring device calculates a current position of a virtual line based on detection values of the respective detectors of the one bridge, the virtual line being shifted outward from a profile of the one bridge and conforming to the profile; calculates a current position of a virtual line based on detection values of the respective detectors of the other bridge, the virtual line either extending along or being shifted outward from a profile of the other bridge; and determines whether or not the two virtual lines are in a state of crossing each other, and if so, performs a first coming-close hindering process.

Abstract: A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

Abstract: Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite.

Abstract: Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

Abstract: Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite.

Abstract: Disclosed are an attitude estimation method, a terminal, a system and a computer-readable storage medium. For the problem of attitude and sensor bias estimation, a cascade solution method is provided. The first part of the cascade is a Kalman filter applied to an LTV system, and the second part of the cascade is a nonlinear attitude observer built in SO(3). In the estimation process, only one constant inertial reference vector needs to be measured explicitly in body-fixed coordinates, and the complexity of the attitude estimation algorithm is greatly simplified by exploiting the geometric relationship between the inertial reference vector and the Earth angular velocity vector. At the same time, the time-varying characteristics of the implemented Kalman filter help to avoid the tedious empirical gain adjustment process that often relies on sets of piecewise constant gains, to improve the convergence speed of the algorithm.

Abstract: An electrodeless plasma thruster with close ring-shaped gas discharge chamber (1,10) can include a gas discharge chamber (1,10) close ring shaped in fluid communication with a propellant storage system (10,70). An antenna (3,30) can be positioned on the exterior of the gas discharge tube (1,10). A guide tube (2,20) can be coupled with the gas discharge chamber (1,10) at a first end and have a second open end. A magnetic system (7,50) can be positioned on the second end of the guide tube (2,20). The magnetic system (7,50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11,80) and a control module (12,90).

Abstract: A liquid-driven propulsion device includes a first and a second chamber. The first chamber includes a first seal movable or deformable within the first chamber, the first seal being configured to separate a working liquid in the first chamber from a first space having a first pressure. The second chamber includes a second seal movable or deformable within the second chamber and configured to separate a working liquid in the second chamber from a second space having a second pressure. The first and the second chambers are coupled to each other to enable a flow of liquid between the first and second chambers. When the first pressure is greater than the second pressure, the working liquid in the first chamber moves in a first direction and the working liquid in the second chamber moves in a second direction to provide a propulsion force applied to the liquid-driven propulsion device.

Abstract: A ruggedizing apparatus for electronic equipment in a spacecraft is provided that can achieve both a radiation shielding effect and a heat-dissipation effect. The ruggedizing apparatus includes: a pressure vessel that is filled with a coolant and places at least a heat-generating electronic circuit of the electronic equipment within the pressure vessel, wherein the heat-generating electronic circuit is immersed in the coolant; and a forced liquid-flow generator placed within the pressure vessel, wherein the forced liquid-flow generator causes the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

Abstract: A method of establishing a system for gathering surveillance data in a hostile environment. The method comprises the steps of providing a movable tractor for ground hauling a trailer, and providing a drone which can be operated independently from the tractor. The trailer has a floor pan for supporting a relay sensor dispensing mechanism and a platform above the floor pan, with a hole for dispensing relay sensors therethrough. The relay sensor dispensing mechanism has an elevator for holding a stockpile of relay sensors, and elevating the relay sensors through the hole. The method comprises disposing at least one relay sensor in the elevator, elevating the relay sensor to a pickup position at or above the platform and retrieving the relay sensor with a drone for subsequent deposition in the hostile environment. The relay sensor then gathers and transceives surveillance data for use and interpretation by an operator. Optional a conveyor chute may replenish the elevator when it is depleted of relay sensors.

Abstract: The invention relates to a hybrid drone for transporting or delivering objects 124, comprising at least one first wing 102 having an airfoil, at least one first and one second longitudinal drive unit 104, wherein the first longitudinal drive unit 104 and the second longitudinal drive unit 104 are arranged on the at least one wing 102, an object-holding device 110 formed on an upper side or on an underside between the first and second longitudinal drive units 104 and for holding an object 124, and a regulating unit formed for regulating the hybrid drone, in particular the drive units, based on control signals.

Abstract: In an apparatus and a packaging process of capsules with an opening closed by a laminar lid obtained by cutting a strip, the ability of transporting the laminar lids in several lines is introduced, reducing the overall dimensions. The apparatus includes: a cutting device with a mechanism defining a portion of the strip where the strip is tensioned in a respective cutting plane, and one or more punches obtaining the laminar lids from the strip; a carousel-like transfer device, having transfer members movable along a closed path, with gripping heads configured to receive respective laminar lids from the cutting device. The cutting plane is in a vertical position, and the mutual position of the cutting device and the transfer device defines a gripping spot of the closed path, the laminar lids being retained in the transfer members on a respective plane in a vertical position.

Abstract: A coupling device for coupling a component to an article includes a first retaining member that retains the component, a second retaining member that retains the article, a movement system for moving the first retaining member and the second retaining member between a non-operating position where the component and the article are spaced apart from one another, and an operating position where the component and the article are in a coupling position, and a detection system for detecting the positioning of the component on the first retaining member. The detection system includes an image detector device for capturing at least one image of the component when the component is retained by the first retaining member, and a processing unit provided for analysing the image captured by the image detector device and verifying if the component is retained on the first retaining member in a predefined position.

Abstract: A system for packaging a product into separate bags, including a station for providing a partly closed bag and adding a quantity of the product into the partly closed bag, a closing station for closing the partly closed bag with the quantity of the product therein, a separating station for separating the closed bag from the sheet-shaped material, and an analyzing station for analyzing the closed bag, where the analyzing station is positioned between the closing station and the separating station and where the closed bag hangs from another bag when analyzed.

Abstract: The invention relates to a filling flow divider for food products and to a method for discharging food products and a filling machine, wherein the filling flow divider has an inlet via which an inflowing mass flow can be divided into a plurality of partial mass flows, transported further in a plurality of partial lines and discharged portion-wise onto or into an object via their outlet, and a plurality of commonly driven dosing devices for adjusting the volume flow of the respective partial mass flows. In this context, a valve device is arranged in each of the respective partial lines, which can divert the partial mass flow such that no mass is discharged via the outlet of the respective partial line.

Abstract: A displacement device for a handling device, including an articulation mechanism on which the handling device is accommodated, wherein the handling device is displaceable by the articulation mechanism between a first position and a second position. The articulation mechanism has a four-pivot arrangement with a first link and a second link, wherein the first link is connected to the second link via a coupler. The coupler has a receiving section for receiving the handling device, wherein the first link, the second link and the coupler are matched to one another so that a substantially rectilinear displacement of the handling device takes place from the first position into the second position. In a method for displacement of a handling device by such a displacement device, the handling device is displaced substantially rectilinearly by the articulation mechanism between the first position and the second position. A packaging machine includes the displacement device.