Abstract: A method of preventing fouling of a submerged structure, the method comprising: activating, by one or more computing devices, at least one transducer and at least one sensor attached to a structure; monitoring, by one or more computing devices, data collected by the at least one sensor related to the submerged structure and the salinity of the water; generating, by one or more computing devices, a predetermined sound wave from the at least one transducer based on the data collected by the at least one sensor; altering, by one or more computing devices, the at least one transducer based collected data from the at least one sensor; and autonomously adjusting, by one or more computing devices, at least one of the at least one transducer.

Abstract: An outboard motor that has an actuator and a gear change mechanism. The outboard motor also comprises an operation position sensor that detects the operation position of an operation part, a shift position detection unit that detects the actual shift position of the gear shift mechanism, an actuator detection unit that detects the state of the actuator, and a control device. The control device performs failure determination or drive control of the actuator on the basis of at least two pieces of the detected information.

Abstract: A marine propulsion system for a marine vessel includes at least two marine drives, a control system communicatively connected to the at least two marine drives and configured to detect that at least one of the marine drives is running and that least one of the marine drives is not running and determine, based on a trim position of each of the at least one non-running marine drive, that at least one non-running marine drive is trimmed down. The control system then controls each of the at least one running marine drive based on an output limit restriction until the at least one non-running marine drive is sufficiently trimmed up.

Abstract: A personal flotation device is provided that includes a housing, a canister disposed within the housing and storing a compressed gas, an inflatable member coupled to the housing, a channel within the housing, and a compressible member positioned within the channel. The channel extends from an exit point of the canister to the inflatable member such that the canister can be in fluid communication with the inflatable member. The compressible member is configured such that (i) when the personal flotation device is located less than a predetermined depth below a surface of water, the compressible member prevents the compressed gas from the canister from reaching the inflatable member, and (ii) when the personal flotation device is located greater than or equal to the predetermined depth below the surface of water, the compressible member compresses and thereby allows the compressed gas from the canister to inflate the inflatable member.

Abstract: An apparatus, method and computer program for controlling propulsion of marine vessel. The propulsion is implemented by a foil wheel propulsion system. The method includes: receiving a wheel operation status from a wheel drive; receiving a plurality of foil operation statuses from a plurality of foil drives; receiving a command from a vessel control system; generating wheel control data for the wheel drive to control a foil pitch function of the foil wheel propulsion system based on the command in view of the wheel operation status; and generating foil control data for the plurality of the foil drives to further control the foil pitch function of the foil wheel propulsion system based on the command in view of the wheel operation status and the plurality of foil operation statuses, wherein a reference torque of the foil control data for each foil drive is generated using a foil feedforward model.

Abstract: A marine vessel includes a hull, a jet pump including an impeller, a plurality of motors, and a transmission to transmit outputs of the plurality of motors to the impeller of the jet pump.

Abstract: A trolling motor secondary mount for mounting a trolling motor to the squared off bow of a boat such as a pontoon. The secondary mount allows the trolling motor to be stored in a travelling or stowed position wherein the lengthwise shaft of the trolling motor aligns parallel with the squared off end of the bow, while the primary trolling motor mount allows the trolling motor to be rotated into the water at a mid portion of the bow of the boat.

Abstract: The disclosure relates to a method for operating an internal combustion engine of a watercraft, in particular on inland waters, in which (i) in an electrolysis unit for the production of hydrogen, water is split into hydrogen and oxygen, (ii) a carbon dioxide sorption unit extracts carbon dioxide from the ambient air, (iii) the hydrogen and the carbon dioxide are fed to a methanol synthesis unit for the production of methanol, and are synthesized therein to methanol, (iv) a photovoltaic unit absorbs solar energy and converts it into electrical energy. The electrolysis unit, the carbon dioxide sorption unit and the methanol synthesis unit are powered by the electrical energy generated in the photovoltaic unit. The methanol produced is transported by means of a distributor system to at least one tank of the watercraft, and is fed from the tank as required to the internal combustion engine, and therein is combusted to generate mechanical energy.

Abstract: Disclosed is a hand held wing rig a center strut of which has recessed grips.

Abstract: Fabric air shaft ventilator with instant opening and fastening for boats. The invention relates to a device for improving air circulation on board boats. It consists of a frustoconical-shaped fabric (8) whose air inlet (1) is maintained in position by two rods (2) and (4) maintained in the form of loops in contact with the deck of the boat and whose air outlet (3) is positioned inside the deck hatch. The device can be oriented in all directions and does not require anchoring at height, so that it can be used on all deck hatches of sailboats and motorboats. The rod (1) is folded in a figure of eight so as to occupy less space when it is not in use. The device according to the invention is particularly intended to improve comfort on board boats by improving air circulation.

Abstract: A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1?) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

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: An exemplary aircraft includes a wing positioned below a vertical rotor, the wing extending to an outboard end, and an anhedral winglet extending from the outboard end through an angular transition to a tip, the anhedral winglet having an external surface exposed to the rotor downwash and the external surface is contoured to generate local wing lift in response to the rotor downwash.

Abstract: A multirotor aircraft that comprises a body, at least three motors and at least one wing that is connected to the body. The wing is designed to be folded and unfolded during flight of the multirotor aircraft and designed to change during the flight a low-drag creation position to a lift creation position, and vice versa. At least one motor has a greater motor power than another motor and the distance from the strong motor to the center of gravity of the multirotor aircraft is shorter than the distance from the another motor to the center of gravity. The wing is positioned in the geometric area between the motors.

Abstract: Embodiments are directed to systems and methods for controlling a tiltrotor aircraft using a flight control system. A flight control computer is configured to control aircraft effectors in response to inputs from inceptors. The flight control computer stores instructions for controlling aircraft effectors. The instructions cause the flight control computer to perform the steps of converting a signal representing longitudinal motion of a first inceptor into a fore-and-aft translational rate command for the tiltrotor aircraft; converting a signal representing lateral motion of the first inceptor into a side-to-side translational rate command for the tiltrotor aircraft; converting a signal representing longitudinal motion of a second inceptor into a height rate command for the tiltrotor aircraft; and converting a signal representing lateral motion of the second inceptor to a yaw rate command for the tiltrotor aircraft.

Abstract: This disclosure describes a moonroof accessory panel. The moonroof accessory panel may be a structure that may be removably attached to a moonroof area of a vehicle. The moonroof accessory panel may be used to hold a drone associated with the vehicle such that the drone may take-off from and land on the moonroof accessory panel. The top of the moonroof accessory panel may also be accessible from the cabin of the vehicle such that a user may place the drone on top of the moonroof accessory panel while inside the cabin. The moonroof accessory panel may also be used for other purposes beyond holding drones as well.

Abstract: A control system acquires predicted tsunami information, and generates a flight plan for unmanned aerial vehicles. The flight plan includes flight paths along safety boundaries between an expected damage area and a safe area. The expected damage is an area expected to be damaged by the tsunami indicated by the predicted tsunami information. The safe area is an area to be safe from damage caused by the tsunami. The control system transmits the flight plan to the unmanned aerial vehicles.

Abstract: A freighter aircraft for long-distance travel, the freighter aircraft comprising a blended wing body having a main body, a transition, and wings with no clear demarcation between the wings and the main body along a leading edge of the freighter aircraft, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the freighter aircraft through air, a fuel storage located within the blended wing body, the fuel storage having a fuel capacity wherein the fuel capacity is configured for long-range flight, and a cargo bay located within the main body; the cargo bay configured to have a freighter capacity, wherein freighter aircraft is a long-range aircraft, the freighter aircraft including a ton-miles per sortie between 135,000 and 450,000.

Abstract: Various embodiments are described of an unmanned aerial vehicle having a wing. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

Abstract: A seat system for a passenger aircraft. The seat system includes a passenger seat frame having a backrest support assembly including a backrest and a spreaders and spar tube assembly; and a seat bottom support assembly. The seat system further includes a solenoid-actuated recline lever assembly including an armrest or center console connected to the spreaders and spar tube assembly; a counter-balanced solenoid actuator positioned in the seat bottom support assembly; and a passenger operated release switch attached between the solenoid actuator and the armrest or center console. The seat system may further include a seat back tray table attached to the back of the passenger seat frame.

Abstract: Described are passenger seat bottom assemblies that include a layered seat bottom assembly formed of a first face sheet, a lightweight core layer, and a second face sheet bonded together, preferably in a flat or substantially flat arrangement. The core layer can be a honeycomb structure, e.g. a metal or aluminum honeycomb, or a foam, that confers a high strength and stiffness to the seat bottom assembly with minimal forming and minimal weight.

Abstract: An environmental control system includes a plurality of inlets for receiving a plurality of mediums including a first medium and a second medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. A ram air circuit includes a ram air shell having at least one heat exchanger positioned therein and a compressing device is arranged in fluid communication with the ram air circuit and the outlet. The compressing device includes a compressor and at least one turbine operably coupled via a shaft. The environmental control system is operable in a first mode and a second mode. In the second mode, a pressure of the second medium output from the compressor is equal to the pressure of the second medium provided to the outlet.

Abstract: According to one implementation, a propulsion system includes a rotor, a motor and an anti-icing mechanism. The rotor has blades. The motor rotates the rotor. The anti-icing mechanism deices the blades using heat generated by driving of the motor. Further, according to one implementation, an aircraft includes the above-mentioned propulsion system. Further, according to one implementation, an anti-icing method of a rotor having blades includes deicing the blades using heat generated by driving of a motor for rotating the rotor.

Abstract: A propulsion system for a propeller of an aircraft is described, wherein the propulsion system allows for transmission of electrical power such as for a deicing system for the propeller. The propulsion system comprises a rotatable shaft for transmission of mechanical power; aircraft end electrical connections at an aircraft end of the shaft for connection to first and second terminals of a source of electrical power; propeller end electrical connections at a propeller end of the shaft and being for connection to first and second terminals for supplying electrical power to electrical components on the propeller; and a mechanical coupling at the propeller end of the shaft for mounting the propeller to the shaft. The shaft comprises: an inner conductor extending along the length of the shaft; an outer conductor extending along the length of the shaft; and an electrical insulator extending along the shaft in between the inner and outer conductor.

Abstract: An inflatable girt for an evacuation slide may comprise a sleeve section, an upper section coupled to the sleeve section, and a lower section coupled to at least one of the sleeve second and the upper section. The sleeve section defines a plurality of first inflatable chambers. The upper section defines a plurality of second inflatable chambers. The lower defines a plurality of third inflatable chambers.

Abstract: A hybrid engine including features to meet aircraft thrust, passenger airflow, and fuel cell requirements. The engine includes a combustor burning the same fuel as the fuel cell. The engine has electric motors to utilize the power output of the fuel cell. The engine shafts have sprags to allow motors to drive the compressors and over run the turbines. The engine has variable flowpath geometry to bypass the combustor.

Abstract: An aircraft propulsion system for an aircraft having a nacelle that includes a pylon structure is provided. The system includes compressor and turbine sections, an IC engine, a fan, and an IC engine cooling system. The compressor section is powered by a first electric motor. The turbine section is configured to power a first electric generator configured to produce electrical power. The first fan is rotationally driven by a second electric motor. The fan has a hub and a plurality of fan blades extending radially outward from the hub. The hub is disposed in the pylon interior region and the fan blades are configured to extend outside of the pylon structure. The fan is positioned downstream of the compressor section. The IC engine cooling system has a heat exchanger and a pump configured to provide coolant communication between the IC engine and the heat exchanger.

Abstract: An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of the electrical motor, in response to a first pulse width modulation (PWM) vector, and a second inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector. The first PWM vector and the second PWM vector are substantially equal and opposite vectors.

Abstract: An assembly including a support panel of an internal fixed structure, a thermal protection element and a plurality of fastening systems. Each fastening system includes a female part secured to the support panel and which has, in its interior, a circular shoulder, and a male part including a sleeve pierced with a main bore, a slide movable in translation in the main bore and a plurality of balls. For each ball, the sleeve has a secondary bore, and each ball is movable along the secondary bore between a locking position and an unlocking position. The slide is movable in translation between a blocking position and an unlocking position. Such an assembly makes it possible to fasten the thermal protection element to the support panel in a simple and rapid manner, also permitting easy removal if necessary.

Abstract: A method is provided for operating a system of an aircraft. During this method, rotation of a propulsor rotor is driven using mechanical power output by a powerplant. The powerplant includes a first drive device and a second drive device. The first drive device generates a first portion of the mechanical power. The second drive device generates a second portion of the mechanical power. A ratio between the first portion of the mechanical power and the second portion of the mechanical power is adjusted to control vibrations of the powerplant.

Abstract: A hydrogen boiloff capture system. The hydrogen boiloff capture system having a cryogenic tank for storing liquid hydrogen. The hydrogen boiloff capture system also includes an intermediate tank fluidically coupled with the cryogenic tank. The intermediate tank is configured to receive hydrogen gas boiloff from the cryogenic tank. The intermediate tank is further configured to provide the hydrogen gas boiloff to a lighter-than-air craft to regulate buoyancy of the lighter-than-air craft. The intermediate tank is also configured to provide the hydrogen gas boiloff to a hydrogen fuel cell coupled to the lighter-than-air craft.

Abstract: A system and method for using a fuel with an engine, an airframe having an aircraft heat load, a fuel tank, and a fuel oxygen reduction unit are provided. The method includes receiving an inlet fuel flow in the fuel oxygen reduction unit for reducing an amount of oxygen in the inlet fuel flow; separating a fuel/gas mixture within the fuel oxygen reduction unit into an outlet gas flow and an outlet fuel flow exiting the fuel oxygen reduction unit; controlling a first portion of the outlet fuel flow to the engine; and controlling a second portion of the outlet fuel flow to the airframe to transfer heat between the second portion of the outlet fuel flow and the aircraft heat load.

Abstract: Aspects of the disclosure provide fuel receptacle and boom tip position and pose estimation for aerial refueling. A video frame is received and within the video frame, aircraft keypoints for an aircraft to be refueled are determined. Based on at least the aircraft keypoints, a position and pose of a fuel receptacle on the aircraft is determined. Within the video frame, a boom tip keypoint for a boom tip of an aerial refueling boom is also determined. Based on at least the boom tip keypoint, a position and pose of the boom tip is determined. Based on at least the position and pose of the fuel receptacle and the position and pose of the boom tip, the aerial refueling boom is controlled to engage the fuel receptacle. Some examples overlay projections of an aircraft model on displayed video for a human observer.

Abstract: A tamper detection system for a life vest storage container (10) on board a passenger aircraft (A), includes a receptacle (4) having an access opening with a closable lid (7); a first electrically conductive monitoring pad (1) formed on the closable lid (7); a second electrically conductive monitoring pad (2) formed on the receptacle (4); a non-conductive sealing member (3) including conductive patches of adhesive on the bottom side of two opposite edges of the sealing member and a conductive element leading between the two patches, the two patches applied to electrically conductive monitoring pads (1, 2); and a monitoring system (5) electrically coupled to the monitoring pads (1, 2) and configured to measure an electrical parameter associated with the electrically conductive path (C1, C2, CS) formed by the monitoring pads (1, 2) and the electrically conductive element within the sealing member (3).

Abstract: A recoil device is provided for a gun having a barrel with a breech. The device includes a breech nut, a brake assembly, a pneumatic spring and a counter-recoil buffer. The breech nut has first and second adjacent sides. The brake assembly includes a brake cylinder that mounts to the breech nut on the first side. The pneumatic spring mounts to the breech nut on the second side. The counter-recoil buffer attaches to the pneumatic spring. The brake cylinder and the pneumatic spring internally push fluids for recoil absorption and return in response to firing the gun.

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall.

Abstract: Techniques and methodologies for servicing a shock strut are provided that account for the variability in gas solubility of the shock strut while in-service. These examples incorporate knowledge of the shock strut's stoke history in order to estimate/predict the amount of gas in solution, its percentage saturation, etc. This may permit a more refined knowledge of the true servicing state of the shock strut.

Abstract: A system and method for transferring energy and mass (supplies) in low-gravity environments. The system comprises a launcher and a receiver. The launcher hurls a capsule at a high velocity such that, when caught by the receiver, a portion of the kinetic energy of the launched capsule is converted to potential energy and stored. The stored energy is used at the receiver end for applications such as living habitats, mining operations, life-support systems, etc. In some instances, a portion of the initial energy is used to lob the capsule back, if desired. Launchers and receivers can be set up in different spatial configurations in a low-gravity environment such as in a circle with a centrally located launcher, a launcher downstream of a chain of receivers, or other configurations.

Abstract: A system for generating magnetic fields in one or more axis, the system comprising a primary electromagnet comprising a first coil having a first axis wherein the first coil is formed of a superconductor, a cooling element configured to cool the first coil below the critical temperature of the superconductor, a power source configured to energise the primary and secondary and electromagnets, wherein the primary electromagnet comprises a frame member, and wherein the frame member is suspended from at least one bracket by a thermally insulating structural member and/or a thermally insulating spring.

Abstract: Systems and methods for receiving a descending rocket, which may be at sea. The rocket may descend vertically with the nose higher than the nozzle. The rocket body may be angled as it descends. A boom arm with hooks may extend at an angle to the rocket body to engage a cable suspended by a semisubmersible platform at sea. The platform may include a dampened cable and lateral straps for securing and rotating the rocket into a horizontal orientation. The platform may receive a ship and purge water to elevate the platform for placing the horizontal rocket onto the ship.

Abstract: A visual inspection posable invertebrate robot (VIPIR) borescope camera system can inspect components in difficult to reach locations. The system enables dexterous robotic inspection of worksites and areas that were heretofore impossible to inspect via extravehicular activities (EVA) and fixed situational awareness cameras. VIPIR may include: (1) a main drive assembly; (2) a reel system; (3) a video borescope assembly (VBA); (4) an enhanced motorized zoom lens (EMZL); (5) a fixed camera assembly (FCA); (6) a support structure; and/or (7) a main electronics box (MEB).

Abstract: Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

Abstract: Provided are methods for manufacturing a multi-ingredient beverage filter cartridge comprising the steps of: adding an amount of a first soluble beverage medium to the container having an internal bottom end, sidewall, and an access opening opposite the internal bottom end; leveling at least a portion of a top surface of the added first soluble beverage medium so that such top surface is substantially in the range of 1 mm to 11 mm from the internal bottom end; adhering a filter medium to the sidewall such that the filter medium does not contact the first soluble beverage medium, top surface; adding an amount of a second soluble beverage medium to the container such that the second soluble beverage medium forms a layer on top of the filter medium; and enclosing the container with a sealed lid.

Abstract: A process for producing a blister strip is provided. The blister strip contains two or more different formulations of powdered medicament for inhalation. The blister strip has a base in which blister cavities are formed. A first set of cavities each contain a first medicament formulation and are covered by a first lid material. A second set of cavities each contain a second medicament formulation and are covered by a second, separate lid material.

Abstract: A method operates a packaging machine for wrapping a packaging film around packaging trays. The method includes: feeding the packaging film to a holding mechanism having two spaced-apart holders that hold the packaging film at two opposite sides; pressing a packaging tray against the packaging film by raising the packaging tray from below; and guiding opposite sides of the packaging film below the packaging tray. The packaging tray is raised by a raising device that raises a lifting platform from a transfer position into a packaging position, the lifting platform receives the packaging tray, and the packaging tray is transported from a loading position to the transfer position by a feed belt. The lifting platform is held in a middle position by the raising device while the feed belt is transporting the packaging tray between the loading position and the transfer position on an intermediate piece.

Abstract: The present invention involves a rotary peristaltic pump and associated method employing the relaxation of pressure on flexible tubing between the rotor and stator of the pump to restore the rotor to a start angle while a valve on the output of the pump is closed to avoid progress of fluid through the system. Three different implementations of the pump and method are presented including reciprocating the stator, reciprocating the rotor, and retracting the idler rollers of the rotor into the rotor to relieve the pressure on the flexible tubing. A controller ensures the appropriate switching and timing of the valve and rotor of the pump. The pump and associated method are directed to the precision dispensing of pharmaceutical fluids into containers, including containers held in container nests.

Abstract: A system for evacuating and sealing containers filled with product, for example, food product, includes an enclosed, sealed housing wherein the pressure level and the atmospheric content can be controlled. A vacuum shroud is positioned in registry with a container entrance opening in the housing, the shroud connectible to a vacuum source and to a source of replaceable gas to replace the ambient air to be removed from the container. The shroud is advanceable to seal the container entrance opening and is retractable from the container entrance opening. A container transport system inserts the container through the housing entrance opening and into the shroud. Thereupon, a sealing system seals the housing from the ambient after the container has been inserted into the shroud. After the air in the container has been replaced with an inert gas and then the shroud retracted, a closure subsystem applies a cover to the evacuated container.

Abstract: Example embodiments relate to a system for filling a stand-up pouch. The system includes a pouch fill injector having a pouch fill spout, a seal jaw assembly having a first jaw and second jaw with receiving areas to interface with the pouch fill tube, and a pouch opening device to open an end of a pouch. Unlike prior art systems, the system of example embodiments does not require a vacuum assist to fill a stand-up pouch.

Abstract: The system comprising containment equipment is intended for the aseptic transfer of a powder, namely for emptying a container filled with powder into a collection container and/or for filling a container with powder from a storage container. The containment equipment has a working chamber surrounded by a housing. A robot is installed in the containment equipment, having an arm arrangement that moves over a pivot range. If there is a collection container it has an inlet leading from the working chamber, and if there is a storage container it has an outlet leading off into the working chamber. The container can be closed at least with a first closure element. A transfer head is mounted at the inlet into the collection container and/or at the outlet of the storage container, each protruding into the working chamber. The passive part forms the double flap together with an active part contained in the transfer head.

Abstract: A packaging machine is for packaging articles with a film. The packaging machine has: a housing; an infeed belt configured to feed an article to be packaged in a transport direction to a film packaging device in the packaging machine; and a weighing device configured to determine a weight of the article. The weighing device has a weighing belt configured to convey the article from the weighing device to the infeed belt in the transport direction. The weighing device is rigidly connected to the infeed belt. The weighing device and the infeed belt together form an infeed module that is removeable from the housing. The removable infeed module has a shared fastener for being releasably fastened to the housing.