Abstract: Embodiments described herein provide recirculation-based alternating blowdown sea chest. The sea chest has a cover assembly with a plurality of grates thereon. Each grate is connected with a pipe in fluid communication with a pump. The pump provides suction while a plurality of valves modulate the flow of water through the system. A recirculation pipe promotes the blowdown of fluids within the system and permits tandem function of water intake and expulsion resulting in maximum efficiency of the sea chest with continuous functionality while in use.

Abstract: A windlass assembly for a marine craft anchoring system is disclosed. The assembly comprises, before attachment to the craft, a windlass portion and a bow roller portion connected to each other via a connection portion. The connection portion provides a mechanical link between the windlass portion and the bow roller portion, secures alignment between the windlass portion and the bow roller portion and fixes the spacing between the windlass portion and the bow roller portion.

Abstract: A stone dumping vessel having symmetrical stone compartments includes a hull, a stone conveying unit, and an oblique fallpipe unit. The hull has a control cabin. A cannula compensating device of the oblique fallpipe unit is disposed on a side of the hull and connected with a fallpipe. Two sides of the control cabin are symmetrically provided with the stone compartments and dynamic positioning (DP) system cabins, respectively. The stone compartments are operated independently for automatically unloading stones to the stone conveying unit disposed at a lower center thereof. The stones are conveyed by independent conveyor systems disposed at the left and right of the control cabin to the fallpipe. The dynamic positioning (DP) system cabins and the cannula compensating device are adapted to position the hull and the fallpipe respectively so that the stone dumping vessel having symmetrical stone compartments can achieve high accuracy of stone dumping.

Abstract: An assembly includes a mask, a support piece, a filler piece and a mount piece. The mask has a frame that includes a right lens frame attached to a left lens frame by a bridge that supports a nosepiece, the frame further including a top surface and a connection region that is cut out from the top surface of the frame at the location of the bridge. The support piece is seated inside the connection region. The filler piece is seated inside the connection region and secured inside the connection region by the support piece. The mount piece has a bottom section, and a mount support extending vertically from the bottom section to receive a camera mount. The bottom section is seated inside the connection region and secured inside the connection region by the support piece when the mount piece is secured to the connection region.

Abstract: A first stage pressure regulator is provided. A valve body has an inlet and an outlet that define a pressure chamber therebetween. The valve body defines a pressure compensation chamber having an opening fluidly communicating the pressure compensation chamber with the surrounding water. The first stage pressure regulator comprises an inlet tubular union removably received into the inlet. A removable high pressure orifice body defines an orifice therethrough. The orifice body is carried by the valve body proximate the inlet. A valve seat is within the valve body.

Abstract: A trim control system automatically controls trim angle of a marine propulsion device with respect to a vessel. A memory stores trim base profiles, each defining a unique relationship between vessel speed and trim angle. An input device allows selection of a base profile to specify an aggressiveness of trim angle versus vessel speed, and then optionally to further refine the aggressiveness. A controller then determines a setpoint trim angle based on a measured vessel speed. If the user has not chosen to refine the aggressiveness, the controller determines the setpoint trim angle from the selected base profile. However, if the user has chosen to refine the aggressiveness, the controller determines the setpoint trim angle from a trim sub-profile, which defines a variant of the relationship between vessel speed and trim angle defined by the selected base profile. The control system positions the propulsion device at the setpoint trim angle.

Abstract: To easily grasp a relationship of parameter values which influence a log velocity of a ship, with the log velocity of the ship caused by the parameters, a ship characteristic estimating device is provided, which includes a data outputter configured to output a plurality of parameter data respectively including rotational speed data of a propeller of a ship, and wind velocity vector data of wind force that may act on the ship, and an estimator configured to receive the plurality of parameter data outputted from the data outputter, estimate values corresponding to the respective parameter data to be log velocity vectors of the ship, and output them as first output values. The rotational speed data are same as each other and the wind velocity vector data are different from each other.

Abstract: The present disclosure relates to a propulsion control system (30) for controlling a marine vessel (10) comprising at least four propulsion units (20, 22, 24, 26). The marine vessel (10) comprises a longitudinal centre line (L) and a transversal line (T). The transversal line (T) extends in a direction perpendicular to the longitudinal centre line (L) and also extends through the steering axis of the aftmost of the propulsion units. The marine vessel (10) comprises four quadrants (I, II, III, IV) defined by the longitudinal centre line (L) and the transversal line (T) wherein a first (I) and a second (II) quadrant are located on the same side of said longitudinal centre line (L). When a combined sway and yaw motion is desired, the thrust of one propulsion unit is directed towards the second (I) quadrant, and the thrust of the other propulsion units is directed towards the first (II) quadrant.

Abstract: A monument for a cabin of a vehicle, in particular of an aircraft or spacecraft, having an outer housing side and a fastening rail for fastening connection elements in a longitudinal direction of the fastening rail in order to fix the monument in position inside the cabin, wherein the fastening rail has a receiving space extending in the longitudinal direction of the fastening rail, which space is designed to receive and fasten mounting feet of the connection elements to the fastening rail, and wherein the fastening rail is integrated in the outer housing side.

Abstract: Systems and methods are provided for securing aircraft sidewall. One embodiment comprises a hanger for supporting sections of sidewall for an aircraft. The hanger includes an elongated vertical member that attaches to a frame of the aircraft, and sets of keyholes that are each arranged in a vertical pattern along the member and that are each configured to support a corresponding section of sidewall of the aircraft. Each keyhole includes a receptacle dimensioned to receive a fitting from a section of sidewall, and a slot dimensioned to slidably accept the fitting via the receptacle to secure the fitting in place. The slot size of keyholes in each set varies from one end of the vertical pattern to another end of the vertical pattern.

Abstract: An airfoil for a rotor blade of a rotary wing aircraft, the airfoil having a predetermined maximum thickness to chord ratio and comprising, between a leading edge and a trailing edge, an extrados and an intrados, the intrados being defined by predetermined intrados coordinate value pairs and the extrados being defined by predetermined extrados coordinate value pairs, wherein a maximum error of each one of the predetermined intrados coordinate value pairs and the predetermined extrados coordinate value pairs amounts to ±3%.

Abstract: An aircraft comprises a wing, a wing tip device at the tip of the wing and an actuator. The actuator is arranged to effect movement of the wing tip device between a flight configuration for use during flight and a ground configuration in which the wing tip device is moved away from the flight configuration such that the span of the aircraft is reduced. The aircraft comprises a carriage guide, such as a track assembly, fixed relative to the wing, and a carriage arranged to move along the track assembly as the wing tip device moves between the flight and ground configurations. The carriage carries the wing tip device on a pivot, such that the wing tip device is rotatable relative to the carriage, about the pivot, as the carriage moves along the track assembly.

Abstract: The invention relates to a locking mechanism for a folding wing tip. The locking mechanism has a locked configuration, in which a first part is received in a second part such that the first part may not be withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part may be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism.

Abstract: A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.

Abstract: Hub assembly and propeller blade assemblies incorporating partial hub assembly having a backing plate with a set of partial root seats and a set of clamps selectively operably couplable to the backing plate with each clamp defining a second partial root seat and wherein when a clamp is coupled to the backing plate a root seat is formed, propeller blades having roots are received within the root seats.

Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole p = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.

Abstract: An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.

Abstract: An unmanned aerial vehicle (UAV), or drone, includes a fuselage, left and right airfoil-shaped wings connected to the fuselage to generate lift in forward flight, a left thrust-generating device supported by the left wing, and a right thrust-generating device supported by the right wing. The UAV further includes a vertical stabilizer, a top thrust-generating device mounted to a top portion of the vertical stabilizer, and a bottom thrust-generating device mounted to a bottom portion of the vertical stabilizer. An onboard power source is provided for powering the thrust-generating devices. The left, right, top and bottom thrust-generating devices provide forward thrust during forward flight and also provide vertical thrust to enable the unmanned aerial vehicle to take-off and land vertically when the fuselage is substantially vertical and further enabling the unmanned aerial vehicle to transition between forward flight and vertical take-off and landing.

Abstract: A response drone for detecting incidents within a coverage area including multiple zones is provided. With customer permission or affirmative consent, the drone may be programmed to (1) detect (or receive an indication of) triggering activity associated with one of the zones; (2) determine or receive a navigation path to that zone; (3) travel to that zone based upon the determined navigation path; (4) collect sensor data using drone-mounted sensors; and (5) transmit the collected sensor data to a user computing device associated with the coverage area for review. The response drone may be an autonomous drone in wireless communication with a smart home controller that detects triggering activity associated with an insurance-related event (e.g., fire). The autonomous drone may automatically deploy to mitigate damage to insured assets (e.g., a home or personal belongings). The autonomous drone data may be used for subsequent insurance claim handling and/or damage estimation.

Abstract: An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side.

Abstract: An airbag container may be inflated and used to protect an item placed within the airbag container. The airbag container may include an inflatable portion that includes sidewalls that extend between a cover to a base. The airbag container may include an orifice to receive gas to inflate the sidewalls, the cover, and the base to an inflation pressure. The airbag container may include an inner cavity defined within the sidewalls, the cover, and the base. The inner cavity may be unpressurized when the inflatable body is at the inflation pressure. The cover may be at least partially separable from the sidewalls to enable insertion of an item in the inner cavity. The cover may then be securable to the sidewalls to securely contain the item in the inner cavity.

Abstract: A mobile galley cart including a wheeled insulated housing having a door configured to open to access to the interior of the housing, a thermoelectric chiller mounted near the bottom of the cart, cold air ducting in fluid communication with the thermoelectric chiller and opening to the interior of the housing, and warm air ducting including a warm air exhaust arranged to exhaust warm air from the mobile galley cart. A mobile galley cart system including a cart configured to dock at a separate service wall to provide service connections therebetween.

Abstract: A toilet system that includes a waste receptacle including an outlet configured to channel waste therethrough. The system also includes a conveyor assembly including a housing that includes an inlet and at least one outlet. The inlet is coupled in flow communication with the outlet of the waste receptacle. The conveyor assembly also includes a transport mechanism positioned within the housing, and the transport mechanism is operable to actively transport the waste from the inlet towards the at least one outlet of said housing.

Abstract: A construction kit for a housing structure of a monument for a cabin of a vehicle, in particular of an aircraft includes a plurality of integrally formed sandwich panels which each have two cover panels, which surround a core, and are formed with panel connecting structures which are each formed as a plug region or as a mating plug region. The mating plug region is formed so as to be complementary to the plug region in such a way that a plug region of a sandwich panel can be plugged into the mating plug region of another sandwich panel to connect the sandwich panels.

Abstract: An armrest table has an armrest casing, a frontward-moving stand, an upward-moving stand, and at least one table panel. The frontward-moving stand is front and rear movably mounted in the armrest casing. The table panel is up and down moveably mounted in the frontward-moving stand. The table panel can be rotated to be horizontal when moved to a highest position of its movement route. The frontward-moving stand and the table panel can be received in the armrest casing when the table panel is moved to a lowest position of its movement route. The armrest table is mounted beside the seat, and thus the passenger can adjust the height of the table panel.

Abstract: In an illustrative embodiment, a tray table for mounting to a lower seatback region of an aircraft passenger seat includes a tray table support bracket stowable to a position approximately parallel with the lower seatback region, and pivotably deployable to provide access to a tray table slideably coupled to the support bracket and configured to provide a substantially horizontal work surface when in a deployed state. In the stowed position, the tray table may be substantially positioned below a tray table deployment height such that additional clearance is provided on the seatback above the tray table for one or more accessory items such as a larger monitor in portrait orientation.

Abstract: An aircraft includes a plurality of seats and an input device coupled to each of the plurality of seats. The aircraft also includes a remotely controlled nozzle positioned proximate each seat of the plurality of seats. Each nozzle includes an actuator assembly including at least one actuator and an actuator shaft. The at least one actuator is configured to move the actuator shaft between an open position and a closed position to control an airflow through the nozzle in response to a signal received from a respective input device of the input devices, wherein the signal represents a position of the actuator shaft.

Abstract: An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

Abstract: An airfoil comprises a skin, comprising an external surface and an internal surface. The skin has a controlled region. The airfoil also comprises an interior space, formed by the skin. The airfoil additionally comprises a hybrid acoustic induction-heating system, configured to impede formation of ice on the external surface. The hybrid acoustic induction-heating system comprises induction coils and a control system. Each one of the induction coils has a portion, arranged sufficiently close to the internal surface to produce an eddy current within the controlled region. The control system is configured to generate inductive heat and traveling-wave acoustic pressure in the controlled region by supplying different phases of the alternating electrical current to the induction coils based, at least in part, on an ambient temperature of a layer of fluid flowing over the external surface.

Abstract: A one-time flare mechanism system for use with an aerial payload system is described which uses minimal actuation force to produce a reliable flare with minimal shock to the payload, parafoil and rigging.

Abstract: An apparatus and method according to one or more embodiments are provided for a latching mechanism. The latching mechanism may be implemented, for example, as a positive lock latching mechanism that provides a positive indication when a latch is not engaged. In one example, an apparatus includes a latch arm comprising a slotted hole and a latch hook configured to engage a pin. The latch includes a bifold handle coupled to the latch arm, the bifold handle comprising a first handle portion and a handle extension portion, wherein the first handle portion comprises a lock hook configured to translate through the slotted hole to engage the pin and the handle extension portion is configured to move away from the first handle portion when the lock hook is not engaged with the pin. Additional systems and methods are also provided.

Abstract: A throttle system for providing throttle control for an engine on an aircraft includes a throttle quadrant assembly (TQA) module (92, 94) in electrical communication with a throttle lever (86) for receiving a position signal (88, 90) indicative of a magnitude for a throttle of the engine, the TQA module (92, 94) being operative to convert the position signal (88, 90) into a throttle signal, an engine electronic control (EEC) module (100, 102) connected to the TQA module (92, 94) to translate the throttle signal (88, 90) into a throttle control signal for the engine, and at least one signal/power line connecting the TQA module (92, 94) to the EEC module (100, 102). The signal/power line at least carries the throttle signal from the TQA module to the EEC module.

Abstract: The invention is a watercraft to aircraft refueling system (“WARS”). A WARS is a refueling system based from a watercraft, such as a surface ship or submarine. A WARS would typically include an elevation apparatus to lift a refueling hose above the water. The elevation apparatus can compose a lifting or swiveling mechanism. In some embodiments both a lifting and swiveling mechanism is used. The WARS lifts the refueling hose above the water, allowing an aircraft to engage with the WARS. The refueling hose may also include a telescoping mechanism or a rotor apparatus or a pressurized water nozzle system to elevate the refueling hose and assist in engaging a WARS with an aircraft.

Abstract: Methods and apparatus for detecting airflow control surface skew conditions are disclosed herein. An example apparatus includes an aircraft wing, a support linkage, and a flap coupled to the aircraft wing via the support linkage. The example apparatus includes a sensor coupled to the flap at a location proximate to the support linkage. The sensor is configured to generate vibration data for the location. The example apparatus includes a detector communicatively coupled to the sensor. The detector is to detect a skew condition of the flap based on the vibration data.

Abstract: A method for policing and managing the operation of a flying, unmanned aircraft in the event of usurpation of control of, malfunction of, or ill-intentioned use of, this aircraft includes the steps of (a) detecting inappropriate operation of the aircraft; (b) transmitting a takeover command to the aircraft to interrupt control of the operation of this aircraft by a first pilot and relinquish control of the aircraft to a second pilot; and (c) transmitting control commands to the aircraft to control its operation by the second pilot, until the need for alternate pilot control of the aircraft has ended or until the aircraft has landed safely.

Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.

Abstract: A foil deployment mechanism comprises a first drum rotatable about a first longitudinal axis, and a second drum rotatable about a second longitudinal axis. The foil deployment mechanism further comprises a cable, the cable comprising a first section which extends from a lower part of the second drum to an upper part of the first drum, a second section which is wound around a part of the first drum facing away from the second drum, a third section which extends from a lower part of the first drum to an upper part of the second drum, and a fourth section which is wound around a part of the second drum facing away from the first drum, wherein the first section and the third section intersect each other between the first drum and the second drum when being viewed along the first longitudinal axis.

Abstract: The invention relates to a flywheel device for position stabilization of a spacecraft, comprising a carrier (1), a rotor (2), a magnetic drive (4) for the rotatingly driving the rotor (2) relative to the carrier (1), and a roller bearing (3) arranged between the rotor (2) and the carrier (1). A magnetic force can be generated between the rotor (2) and the carrier (1) by means of the magnetic drive (4) in order to pre-stress the rolling bearing (3). The outer diameter (A) of the rotor (2) can have, for example, only a maximum of 2.5 times of the rolling bearing diameter (W).

Abstract: Methods and systems may provide for a structure having a plurality of interconnected panels, wherein each panel has a plurality of detection layers separated from one another by one or more non-detection layers. The plurality of detection layers may form a grid of conductive traces. Additionally, a monitor may be coupled to each grid of conductive traces, wherein the monitor is configured to detect damage to the plurality of interconnected panels in response to an electrical property change with respect to one or more of the conductive traces. In one example, the structure is part of an inflatable space platform such as a spacecraft or habitat.

Abstract: An apparatus and methods for producing at extremely high production speeds small pouches filled with tobacco or other granular, powdered or solid content. An endless web substrate, with or without flavor film thereon, is formed into a tubular shape with a longitudinal seam. The tube is cut to individual lengths, and a procession of tubes is crimp-closed at one end, filled and crimp-closed at the other end to complete pouch production. During production, the seams formed at the crimped ends of the pouch are parallel to one another and the longitudinal seam of the pouch is midway between the sides of the pouch and orthogonal to the seams formed at the crimped ends of the pouch.

Abstract: Described is a unit for filling containing elements (2) of single-use capsules (3) for extraction or infusion beverages, comprising: a line (4) for transport of containing elements (2) designed to contain a dose (33) of product; a station (SR) for filling the containing elements (2) comprising: at least a first containing seat (S1) designed to receive a dose (33); a substation (ST1) for forming a dose (33) inside the first containing seat (S1); at least a second containing seat (S2) designed to receive the dose (33) from the first containing seat (S1); a substation (ST2) for transferring the dose (33) from the first containing seat (S1) to the second containing seat (S2); devices (7) for moving the first containing seat (S1) between the forming substation (ST1) and the transfer substation (ST2) and vice versa; a substation (ST3) for releasing the dose (33) from the second containing seat (S2) to a containing element (2); further devices (8) for moving the second containing seat (S2) between the transfer subst

Abstract: The present invention relates to a filling device for heterogeneous products or products which have solid or semi-solid suspended elements with variable dimensions and compactness. The valve of the invention can be used in net weight filling machines. In particular, the invention relates to a filling device (1) for filling machines, comprising a hollow body (2) in which a shutter member (3) is movably fitted and acts in cooperation with a dispensing member (4), which is coaxial to said shutter member (3), to close or open a dispensing opening (5) for a product (P) to be dispensed into a container (C), characterized in that said dispensing member (4) comprises a rotatable shaft (10) comprising a screw portion (14) adapted to impart a dispensing pressure and a mixing to the product (P).

Abstract: Banknote processing equipment is disclosed, which comprises a chamber having an open end for insertion of a bag into the chamber and an extractor adapted to establish a lower ambient pressure between the chamber and the bag to that within the bag to cause the bag to expand into an open configuration during a banknote filling operation, whereby the banknote processing equipment can deposit banknotes in the bag.

Abstract: A tool for tensioning, cutting and/or punching a band of a band-type clamp, a band and buckle attachment, and a band punch attachment are provided. The tool includes a nose piece to receive a tail of the band and a lever pivotably secured to the nose piece. The band and buckle attachment includes a main body having a band guide slot and a blade guide intersecting the band guide slot. A blade is movably positioned in the blade guide. A blade biasing element is positioned between the blade and the main body. The band punch attachment includes a main body having a band guide slot and a punch mechanism rotatably mounted on the main body. The punch mechanism includes a punch guide having a passageway and a punch tool movably positioned in the punch guide. A spring is positioned in the passageway urging the punch tool in a predetermined direction.

Abstract: A filling device and method for filling a container with floating and/or suspended products, in particular for apples and pears. The device has a frame provided with a supply tank fillable with aqueous liquid, and a vacuum chamber for realizing an underpressure in at least a part of the supply tank; immersion means operatively connected to the frame for the purpose of placing the container into or removing the container from the supply tank; and feeder for feeding to the supply tank the aqueous liquid in which the floating and/or suspended products are entrainable. The feeder includes a flow tube or flow channel with which the floating and/or suspended products are carriable into the vacuum chamber.

Abstract: Various embodiments of the present disclosure provide a new method and apparatus for fixing the end of a roll of wrapping film web to and releasing the end of the roll of wrapping film end from a circular guide wrapping machine when a new roll of wrapping film web is installed or when the wrapping film web has torn apart.

Abstract: An opening apparatus for a gusseted tube which is fed in from a tube supply for the purpose of the later transfer to a device. The opening apparatus has at least two suction cheek arranged on each of two sides of the gusseted tube. Each suction cheek is arranged on one side of the gusseted tube and has a contact region which interacts with the gusseted tube and has a suction region with a protective device which lets an air flow through. The two suction cheeks lie opposite one another to be moved apart in a direction orthogonally with respect to the folded-together gusseted tube. An opening apparatus has both side cheeks of a pair arranged such that they can be moved along the outer face of the gusseted tube away from the other pair of suction cheeks to the outside.

Abstract: An automated packaging line for C- or U-shaped profiles are related methods are disclosed. An example method includes transferring a first profile and a second profile to a first location, each of the first and second profiles having a u-shaped or c-shaped cross-section defining an external convex side and an internal concave side. The example method also includes rotating a first blade and a second blade about a horizontal central axis, where the first blade and the second blade are coupled to opposite ends of a pair of rotor arms including a first rotor arm and a second rotor arm. The first and second rotor arms rotate about axes that are parallel to and offset from each other. The example method also includes inserting the first profile into the first blade with the internal concave side of the first profile facing upwards as the first blade moves upward through its rotation.

Abstract: A process for using a first labeling system that is a constituent of a block-form first container-handling includes, before switching between said labeling and non-labeling modes of a labeling unit thereof, providing a control signal to a control unit that controls the labeling machine, the control signal being indicative of a gap in container flow. the control signal occurs before the gap in container flow reaches a container inlet of the first labeling system.

Abstract: A coated box with anti-stain coating on portions of exterior surfaces of the coated box, which also has uncoated exterior surfaces to which a water-based adhesive is applied to adhere to portions of an interior facing surface to form a box shape that includes folds at creases at scored lines.