Abstract: A system for determining a bending moment on an oar during a rowing stroke in the water has an oar handle (9), an oar shaft (1) that extends from the oar handle (9), an oar blade (2) that is disposed on the oar shaft (1) on the side opposite the oar handle (9), at least one strain gauge (4), from the signal of which the bending moment can be determined, wherein the oar shaft (1) is of a multi-part form and wherein a measuring sleeve (3), which joins the two adjacent parts of the oar shaft (1) to each other and which comprises the at least one strain gauge (4), is disposed between two adjacent parts of the oar shaft (1). With a rotation measurement of the oar by means of an additional MEMS, the power against time of the rower can be determined by multiplication of the determined angular rate and the bending moment.

Abstract: A trolling motor assembly comprising a control assembly; a mounting assembly in electrical communication with the control assembly; and a propeller assembly having a motor. The mounting assembly comprises a control mounting bracket that is fixedly attached to a wall of the boat and a removable propeller mounting bracket that can be engaged with the control mounting bracket. When the propeller mounting bracket in an engaged position with the control mounting bracket, signals from an input device of the control assembly actuate the motor of the assembly.

Abstract: Please make the following amendments to the abstract. Material to be inserted in replacement paragraphs or sections is in bold and underline, and material to be deleted is in and/or in if the deletion would be difficult to see. Please replace abstract with the following rewritten abstract: A water muffler of a personal watercraft comprises: a muffler body; and an inlet pipe which is connected to the muffler body and guides an exhaust gas and cooling water to an inner space of the muffler body. The inlet pipe includes: a center pipe wall; an outer pipe wall provided to surround the center pipe wall; an exhaust passage which is provided inside the center pipe wall; and a water passage surrounded by the center pipe wall and the outer pipe.

Abstract: A stand-up type personal watercraft comprises: a body including a hull and a deck; a standing deck is provided in a rear portion of the deck; an engine hood attached to the deck and located in front of the standing deck; a pole storage section formed as a recess on an outer upper surface of the engine hood and extending in a forward and rearward direction; a handle pole which is rotatably attached at a front end portion thereof to the deck, and is pivotable between a stowed position at which the handle pole is stowed in the pole storage section, and an up position at which a rear end portion of the handle pole is placed above and away from the pole storage section; and a storage provided in the engine hood by depressing a portion of an upper surface of the pole storage section.

Abstract: An attachment device for an aircraft monument is disclosed having a pair of spaced apart parallel plates having vertical sides and a rounded upper surface defining an arch. A panel attaches the spaced apart parallel plates along an inner radius, and a pair of lugs including a vertical channel is disposed below the plates for receiving fasteners to connect the attachment device to a rail or planar surface.

Abstract: An aircraft and method of operating the aircraft are provided. The aircraft includes a fuselage including a nose, a tail, and a hollow, elongate body extending therebetween, a wing extending laterally away from the fuselage, the wing including a leading edge in a direction of motion of the aircraft during normal flight and a trailing edge on an opposing edge of the wing, and an engine configured to drive a bladed rotatable member, the engine coupled to at least one of the wing and the fuselage. The aircraft further includes at least one of a forward chine member and an aft chine member extending from the fuselage at a point forward of the engine aftward to a point aft of the bladed rotatable member.

Abstract: Example apparatus and methods are disclosed herein for moving control surfaces on an aircraft wing to control airloads during a wing tip folding operation (from a folded position to an extended position or from an extended position to a folded position). An example method includes determining a position of a control surface on a wing of an aircraft. In the example method, the wing has a fixed wing portion and a wing tip moveably coupled to the fixed wing portion. The example method includes determining a change in the position of the control surface from a first position to second position for facilitating movement of the wing tip while the aircraft is not in flight. The example method also includes moving the control surface to the second position and moving the wing tip between an extended position and a folded position.

Abstract: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

Abstract: A system and method for a reconfigurable aircraft having a fuselage with one or more propellers, at least one tail assembly, a processor, and a memory having instructions stored thereon that, when executed by the processor, cause the system to: determine a safety clearance for the at least one tail assembly; and selectively move the at least one tail assembly upon a determination that the safety clearance is achieved.

Abstract: An aircraft wing has a spoiler movable from a reference position with a deflection angle ?ref to a given target deflection angle ?target by an actuator powered mechanism. An upstream edge of the spoiler is interconnected with the aircraft wing exclusively via a strip element made of a resiliently flexible material and via the actuator powered mechanism. A downstream edge of the strip element extends along the whole or at least along a major part of the upstream edge of the spoiler. The actuator powered mechanism is constructed and arranged such that, while moving the spoiler, the strip element is bent with a constant strain along the strip element. A cross-section of the strip element for all deflection angles ? assumes the form of a ring segment with a radius R(?) at least within a given margin of failure, with ?, ?target, ?ref?[??1; ?2].

Abstract: A rotor damping system includes a rotor blade defining opposed leading and trailing edges, wherein the rotor blade has flexibility in an edgewise direction defined between the leading and trailing edges. A spar is mounted within the rotor blade, wherein the spar is stiff against flexure in the edgewise direction. A damper is operatively connected to the spar for damping relative motion of the spar and blade.

Abstract: A coaxial, dual rotor system includes a first rotor assembly located at a rotor axis and rotatable thereabout and a second rotor assembly located at the rotor axis radially inboard of the first rotor assembly and rotatable thereabout. A rotationally fixed static mast is located radially between the first rotor assembly and the second rotor assembly. A transmission includes a rotor input shaft including a first sun gear and a second sun gear. A star gear arrangement is operably connected to the first sun gear and to the static mast to drive rotation of the first rotor assembly about the rotor axis and a planetary gear arrangement is operably connected to the second sun gear and to the static mast to drive rotation of the second rotor assembly about the rotor axis.

Abstract: A method of rotorcraft state control includes receiving command input indicative of an intended state change in a rotorcraft. The method also includes issuing command output to a rotor actuation system to carry out the intended state change by varying drag and/or efficiency on one or more rotor blades of the rotorcraft. Issuing command output can include issuing a command output to the rotor actuation system to carry out the intended state change by increasing drag at a substantially constant thrust on one or more rotor blades of the rotorcraft.

Abstract: Embodiments of the invention include a vehicle including an engine and a rotor including a plurality of rotor blades in a path of exhaust from the engine. The vehicle includes a rotor control assembly configured to connect the rotor to a rotation force source to rotate the rotor and configured to rotate the rotor at a prescribed minimum rotation rate greater than zero based on at least one of disengaging the rotor from the rotation force source and receiving a control signal to disengage the rotor from the rotation force source. The rotor control assembly is designed to rotate the rotor at the prescribed minimum rotation rate based on at least one system attribute of the vehicle that is affected by a rotation rate of the rotor.

Abstract: An energy kite may be coupled to a tether and ground station via an electro-mechanical bridle. The energy kite may generate a significant amount of lift during power generation and may need to transfer this load to a tether that is anchored at the ground. Transferring the load at a single point would place a substantial bending moment on the energy kite. To mitigate this bending moment, the load may be divided between multiple locations with a bridle system. The bridle system may have a plurality of electrical conductors to conduct electrical power and signals.

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: Disclosed herein are an automatic flight control system and method for an unmanned drone, in which a guidance system installed on a moving object transmits a guide signal, and the unmanned drone automatically flies based on the guide signal, thus allowing the unmanned drone to maintain a uniform distance from the moving object. The presented automatic flight control system for an unmanned drone is configured such that a guidance system transmits a guide signal based on a guidance request signal received from the unmanned drone, and the unmanned drone automatically flies depending on an automatic flight control value that is set based on an automatic flight guide signal when the guide signal is the automatic flight guide signal, and flies to the automatic control location set in response to an automatic location guide signal when the guide signal is the automatic location guide signal.

Abstract: An unmanned vehicle including a body and a frame structure extending from the body and supporting a plurality of propeller assemblies, each propeller assembly including at least one propeller and a corresponding motor with the motor housed in a watertight housing or coated and made corrosion resistant. The propellers comprise a first subset of propellers of the propeller assemblies and a second subset of propellers of the propeller assemblies which rotate in a plane positioned below a plane in which the first subset of propellers rotate, wherein said first and second subset of propellers are configured for independent operation of one another as the vehicle transitions from an air medium to a water medium.

Abstract: Aspects include a system for transferring a payload between drones. The system includes a first drone having a first member and a first controller, the first member having a first coupling device on one end, the first member being configured to carry a payload, the first controller being configured to change a first altitude and orientation of the first drone. A second drone includes a second member and controller, the second member having a second coupling device on one end, the second member being configured to receive the payload, the second controller being configured to change a second altitude and orientation of the second drone. The controllers cooperate to change at least one of first and second orientations to operably engage the first coupling device to the second coupling device for transferring the payload from the first member to the second member.

Abstract: In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.

Abstract: An elevator system includes a shaft extending between at least two decks of a vehicle. A base of the shaft is mounted to a deck structure of at least two decks by a coupling mechanism that accommodates flexing of the deck structure to enable the deck structure to flex independently of the base of the shaft. The elevator system further includes a cab within the shaft. The cab is movable between the at least two decks. The elevator system also includes a pneumatic system in selective communication with an interior of the shaft.

Abstract: A method and apparatus for providing a sliding closet. The sliding closet comprises an exterior wall, a first wall, a second wall, a number of openings, a movement system, and a number of cavities. The exterior wall faces into a passenger cabin of a vehicle. The first wall and the second wall are perpendicular to the exterior wall. The number of openings is parallel to the exterior wall. The number of cavities is formed by the exterior wall, the first wall, the second wall, and the number of openings.

Abstract: A vehicle seat includes a seat pan and a backrest. The seat pan and the backrest are positionable with respect to one another such that the seat is configurable into at least one of a taxi, takeoff and landing position, a napping position, and a sleeping position. A swivel is disposed beneath and supporting the seat, permitting the seat to rotate about a pivotal axis. Base tracking is disposed beneath and supporting the seat, permitting the seat to move in a lateral and a longitudinal direction. A first control is provided to lock and unlock movement of the seat in at least one of the lateral and the longitudinal directions. A second control is provided to lock and unlock the swivel. The swivel is permitted to be unlocked while movement of the seat in the lateral and the longitudinal direction is locked.

Abstract: A flow duct able to be connected to a ram outlet header includes a band having an annular shape and a glove connected to the band. The glove can include a first end that is annular in shape and connected to the band, a body that is curved and has a substantially U-shaped cross section with a first opening, and a second end that has a substantially U-shaped cross section and a second opening that is an extension of the first opening.

Abstract: Air conditioning system for a cabin 6 of an aircraft, the air conditioning system 1 including a pressurized air source 2, a ram air duct 3, an air amplifier 4 and a heat exchanger 5. The air amplifier 4 includes an inlet 41 for work air, a slot 42 suitable for letting the work air exit the air amplifier, and a main fluid zone 43. The inlet 41 is in fluid communication with the pressurized air source 2 and the slot 42 is arranged in fluid communication with the ram air duct 3, in such a way that the work air exiting from the slot 42 produces a suction effect in the ambient air in such a way that this ambient air flows along the ram air duct 3. The air amplifier 4 is arranged so that the ambient air is forced by the suction effect to pass from the inlet 51 to the outlet 52 of the cold side of the heat exchanger 5.

Abstract: An air conditioning system 1 for a cabin 6 of an aircraft. The air conditioning system 1 includes a work air source 2 suitable for providing work air, a distribution and control system 3, a main heat exchanger 4, a turbine 5 and a compressor 7. The inlet 51 of the turbine 5 is in fluid communication with an outlet 61 of the cabin 6 and the outlet 52 of the turbine 5 is in fluid communication with ambient. The inlet 71 of the compressor is suitable for being fed by the work air, and the outlet 72 of the compressor is in fluid communication with the inlet 41 hot side of the main heat exchanger 4, the compressor 7 being moved by the outlet shaft 53 of the turbine 5. The outlet 42 of the hot side of the main heat exchanger 4 is in fluid communication with the inlet 31 of the distribution and control system 3, the outlet 32 of which is in turn in fluid communication with an inlet of the cabin 6.

Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.

Abstract: A de-icing system is provided that includes a member, a coil, and a power supply. The member includes an anti-icing portion. The coil is inductively coupled to the anti-icing portion of the member. The power supply is coupled to the coil, and is configured to provide voltage to the coil. The coil emits electromagnetic energy responsive to power supplied by the power supply. Responsive to the electromagnetic energy, eddy currents are generated in the anti-icing portion that provide heating of the anti-icing portion.

Abstract: The present disclosure provides danger avoidance apparatuses and related methods, such as for use to avoid avalanches. An apparatus may include a container configured to couple to a user, a lift providing mechanism, a descent control mechanism and at least one rip cord engaged with the container and selectively operable by the user. Both the lift providing mechanism and the descent control mechanism may be movably coupled to the container between a packed position within the container and a deployed position exterior to the container controlled via the at least one rip cord. The lift providing mechanism may include an airfoil that provides lift to the user at a first velocity of the user along a first direction. The descent control mechanism may control the descent and reduce the velocity of the user along the first direction from the first velocity in the deployed position.

Abstract: The invention relates to an assembly (60) for an aircraft turbine machine comprising a receiver for a pair of open rotor contra-rotating propellers, the assembly comprising a duct (52), ancillaries routed inside the duct, an attachment case (54), attachment means (62) of the duct on an annular installation portion (64) of the case (54). According to the invention, the attachment means (62) in an assembled configuration include: a split ring (66) fitted with internal projections (71) housed inside orifices (72) in the duct; a radial loading surface (68) of the ring made on the portion (64) the surface (68) being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface (70) of the complementary shaped tapered split ring; means (80) of axially loading the ring along the first direction, these means (80) being blocked in the axial direction on the portion (64).

Abstract: An electric propulsion system includes at least one generator. The electric propulsion system also includes at least one drive engine coupled to the at least one generator. The electric propulsion system further includes at least one electrical device. The electric propulsion system also includes at least one battery integrated isolated power converter (BIIC), where the at least one generator and at least one of the at least one BIIC and the at least one electrical device are coupled, and where the at least one BIIC and the at least one electrical device are coupled.

Abstract: A motorized aircraft is controlled by a drive control means (120) that rotationally drives a propulsion system propeller. The propulsion system propeller is driven by a plurality of electric motors (130). Total output of the plurality of electric motors (130) and required output satisfy the following relationship: Pmax(n?1)/n>Preq (where Pmax is the total output (kW) of the electric motors, n is the number of electric motors, and Preq is the required output (kW)).

Abstract: The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft.

Abstract: A mitigating system for reducing flow drag in aircraft engines uses a mitigating device attached to either the nacelle of an engine to mitigate the flow drag of the airflow moving across the nacelle. The mitigating device has an inner sleeve and an outer sleeve, each of which can be adjusted separately to extend any desired length across the inner surface or outer surface of the nacelle. As the sleeves are extended, they cover a greater number of flow drag elements thereby improving the aerodynamic properties of the aircraft engine.

Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades extending radially outwardly from a fan hub to a blade tip defining a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle. The throat portion has a minimum throat radius measured from a fan central axis greater than a blade tip radius.

Abstract: Auxiliary power unit inlet apparatus and methods are disclosed. An example apparatus includes an aircraft including a fuselage, the fuselage including an air inlet including a first sub-inlet and a second sub-inlet separated from the first sub-inlet; and a door coupled along the air inlet to enable air to separably flow into the first sub-inlet and the second sub-inlet, the door to deter the air from flowing between the first sub-inlet and the second sub-inlet.

Abstract: An actively stabilized refueling drogue including a drogue canopy, drogue straits extending from the drogue canopy, a coupling body, a coupling shroud, a system of fins, and actuators. The coupling body is for connecting a flexible refueling hose to a receiver aircraft fuel intake, so that in-air refueling may occur The drogue struts terminate at the coupling body. The coupling shroud covers the coupling body. The system of fins is for stabilization of the drogue and is attached to the coupling shroud. The actuators are for actuating the fins to achieve aerodynamic stabilization. The actuators are manufactured from a solid state shape memory alloy, such that the fins may be actuated by applying thermal energy to the actuators.

Abstract: An aircraft engine, an electric taxi system and a corresponding method are provided to facilitate taxiing without operation of the core gas turbine engine by driving the fan assembly with the electric taxi system during taxi operations. An aircraft engine is provided that includes a core gas turbine engine including a compressor, a combustor and a high pressure turbine. The aircraft engine also includes a fan assembly coupled to the core gas turbine engine. The aircraft engine further includes an electric taxi system coupled to the fan assembly. The electric taxi system includes an energy storage device and a motor responsive to energy provided by the energy storage device. The motor is coupled to the fan assembly and is configured to drive the fan assembly during taxi operations.

Abstract: The present disclosure provides methods and articles useful in sealing fasteners, including seal caps and in particular translucent or transparent seals or seal caps. In some embodiments, a seal cap which is optically translucent and optionally visibly transparent contains an uncured sealant, which is optionally optically translucent or visibly transparent, and is applied to a fastener. In some embodiments, the sealant is cured by application of actinic radiation to the sealant through the seal cap. In another aspect, a protected fastener construction is provided comprising: q) a fastener; r) a seal cap; and s) a cured sealant; wherein the sealant is optically translucent and optionally visibly transparent.

Abstract: A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system including: a rearward facing tang extending from a rear fuselage portion of a VTOL UAV; one or more metallic contacts disposed on an exterior surface of the tang; a UAV pod including a landing surface; and an opening disposed in the landing surface to receive the tang.

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: In one aspect of the disclosure, an apparatus for manipulating a plurality of curved sheets is provided. Each of the plurality of curved sheets includes an upper surface and a lower surface. The apparatus includes tooling to be coupled to the upper surface of each of the plurality of curved sheets. The tooling is capable of moving the plurality of curved sheets relative to each other and abutting the plurality of curved sheets so that the upper surface of each of the plurality of curved sheets is coextensive with a virtual arcuate surface. The apparatus also includes a welding apparatus capable of welding the plurality of curved sheets together after abutting the plurality of curved sheets.

Abstract: An aerodynamic platform or spacecraft including a habitable 1G centripetal force rotating gravity producing interior corridor within an aerodynamic shell and an aerodynamic drone booster launch system with reentry and reuse capability.

Abstract: A system is described for locating the barycenter of at least one object orbiting in space, such as for example space debris, adapted to allow the physical and mechanical characterization of the identified object, comprising: at least one remote sensor (1) placed on board a station (2) adapted to detect the space coordinates of certain points (Pi) belonging to the identified object (3), with respect to a space reference system; first means for acquiring data related to positions assumed in time by the points (Pi) for reconstructing the trajectory followed by the points (Pi); second means for determining the instantaneous rotation axes of the identified objects associated with the trajectory, for determining a segment perpendicular to each pair of the instantaneous rotation axes in a sequence and for locating the mean point of the segment; and third means for computing a discrete function d(tk) of the length of the segments, for computing an envelope curve (c) of the local maxima of the discrete function d(tk)

Abstract: A source fluid inlet for an automated filling device. The source fluid inlet may comprise features that limit engagement and/or disengagement of a source fluid tubing set from a port in the source fluid inlet except when the port is disposed in a predetermined load position. In turn, engagement and/or disengagement of the source fluid tubing may be selectively allowed to assist in reduction of interconnection errors of one or more source fluid sources. The source fluid inlet may selectively position a source fluid tubing set in a fill position to facilitate fluid communication with a receptacle to be filled (e.g., a syringe). The source fluid inlet further comprises one or more mechanisms for engagement and/or retention of a cap disposed on a syringe.

Abstract: The present invention relates to Packaging machine (1) having a deep-drawing-(2), filling-(7) and/or sealing station (19) to produce a package made from a lower-(8) and an upper (14) film web, wherein, in the filling station (7), a packaging item (16) is placed on the lower film web (8) on an L-board (5) comprising a base (5?) and a flap (5?) foldable connected to the base and folding means (10) to pivot the flap (5?) from an initial flat to a folded position and hold-down means (17) which maintains the flap (5?) in the folded position.

Abstract: A bale tie-off accelerator chamber receives bales from the compression chamber of a baler, keeps them compressed and ties them while a new bale is being compressed. The time required to make a bale using the prior art includes the time it takes to push the material into the pressure chamber and then stepwise apply ties to the bale as it is ejected. The present invention allows the complete freshly-compacted bale to be ejected from the pressure chamber before ties are applied, thus allowing the next bale to be formed without waiting for stepwise tying of the preceding bale.

Abstract: A kit-of-parts of a cup part and a separate cover together form a coffee cup. The cup part includes bottom wall and a circumferential side wall with a circular flange extending outwardly from an upper end of the side wall. The flange has an outer edge. The cover includes a substantially flat circular central portion configured to engage the upper surface of the cup part and to cover the upper opening. A skirt extends downwardly from the circumference of the central portion and is configured to be bent around the outer edge of the flange. A circular beaded edge defines the end of the skirt, where the beaded edge of the cover extends outwardly from the skirt over a distance the beaded edge being configured to be deformed against an underside of the flange to secure the cover onto the cup part and form the coffee cup.

Abstract: A shrink sleeve apparatus is disclosed herein that includes a shrink sleeve applicator, a downstream heat shrink station, and a horizontal conveyor having side-by-side rollers that have a circumscribing outer portion with at least one high traction segment and at least one low traction segment. A method of applying a shrink sleeve to an article is disclosed that includes providing a conveyor having rollers as disclosed herein, positioning the rollers such that low traction segments of the rollers support the article as it passes a shrink sleeve applicator, which applies a shrink sleeve. The high traction segments of the rollers do not interfere with sleeve application. As the conveyor moves the article and sleeve through a downstream heat shrink zone, the rollers are rotated so that the high traction segments contact the article and sleeve to assure rotation of the article and sleeve during heat shrink.

Abstract: The invention relates to a method of operating a packaging machine for wrapping packaging trays for foods using a packaging film, in particular a plastic film, in which the film is supplied to a holding mechanism having two holding means spaced apart from one another to hold the supplied film at two mutually oppositely disposed sides; in which the spacing of the two holding means from one another is then adjusted: and in which a supplied tray is subsequently pressed toward the supplied film by lifting from below, wherein the holding mechanism is adjusted such that the spacing of the two holding means from one another is reduced.