Abstract: An exterior panel is formed of superplastic materials, including an exterior skin of titanium to accommodate high thermal stresses imposed on hypersonic transport vehicles during hypersonic flight. The exterior skin is fixed to an underlying reinforcing skeletal structure consisting of a superplastic formable reinforcement (SFR) layer, for example a titanium, zirconium, and molybdenum (TZM) alloy, which supports the exterior skin whenever the latter may be heated to temperatures exceeding 1200 degrees Fahrenheit. The exterior panel includes a separate interior skin configured for attachment to a frame member such as a rib, stringer, or spar of the hypersonic transport vehicle. A multicellular core is sandwiched between the exterior and interior skins to impart tensile and compressive strength to the exterior panel. In one disclosed method, the core is superplastic formed and diffusion bonded to the exterior and interior skins.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.

Abstract: Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.

Abstract: An apparatus and its method of use provide a preload to the assembly of large structures, for example the assembly of an aircraft wing panel to an aircraft wing frame. The apparatus and its method of use preloads the aircraft wing panel of the aircraft wing structure and presses the aircraft wing panel against the aircraft wing frame of the aircraft wing structure, temporarily securing the aircraft wing panel against the aircraft wing frame and indexing the aircraft wing panel to the aircraft wing frame for the installation of permanent fasteners securing the aircraft wing panel to the aircraft wing frame.

Abstract: A leading edge slat of a wing element of an aircraft. The aircraft defining a mark including a main fuselage axis x and a spanwise axis y. The wing procuring a lift along an axis z. The wing element having a skin forming the leading edge slat, a spar linked to the skin and a stiffening structure linked on the leading edge side to the spar and to the skin. The stiffening structure being formed from a formed sheet metal having a plurality of bosses distributed according to the length of the leading edge. The bosses extending between the spar and the inner face of the skin.

Abstract: Rupture fairings are disclosed. A disclosed example fairing for use with an aircraft includes a surface to at least partially define an exterior surface of the aircraft when the fairing is installed onto the aircraft, and a membrane to rupture during flight of the aircraft, where the membrane defines at least a portion of the exterior surface.

Abstract: A flap actuation mechanism incorporates a flap bracket attached to a flap and coupled to an underwing structure with a pivotal coupling. A crankshaft is configured for over center rotation and has aligned inboard and outboard crank arms extending from axially spaced inboard and outboard journals disposed in the underwing structure and configured to rotate about a rotation axis of the inboard and outboard journals. A crank pin is connected between the inboard and outboard crank arms. An actuating rod has a first end rotatably coupled to the crank pin and a second end coupled to the flap bracket. Rotation of the crankshaft displaces the actuating rod to cause rotation of the flap bracket and the flap.

Abstract: Aircraft, auto speed brake control systems, and methods for controlling drag of an aircraft are provided. In one example, an aircraft includes an aircraft structure. A drag device is operatively coupled to the aircraft structure between a stowed and a deployed position and/or an intermediate deployed position. A speed brake controller is in communication with the drag device to control movement. An autothrottle-autospeedbrake controller is in communication with the speed brake controller and is configured to receive data signals. The autothrottle-autospeedbrake controller is operative to direct the speed brake controller to control movement of the drag device between the stowed position and the deployed position and/or the intermediate deployed position in response to at least one of the data signals.

Abstract: Disclosed herein is a system for actuating a flap coupled to a wing of an aircraft in a streamwise direction. The system comprises a geared rotary actuator comprising a drive gear that is rotatable about a first rotational axis. The system also comprises a crank shaft comprising a driven gear in gear meshing engagement with the drive gear of the geared rotary actuator to rotate the crank shaft about a second rotational axis. The second rotational axis is angled relative to the first rotational axis. The system further comprises a crank arm co-rotatably coupled to the crank shaft and configured to be coupled to the flap. Rotation of the crank shaft about the second rotational axis rotates the crank arm in a direction perpendicular to the second rotational axis.

Abstract: A hydraulic system 300 for an aircraft including a backup hydraulic pressure source 216 to provide hydraulic pressure to a brake 222 in the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic system 300 also includes a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear 100. The backup hydraulic pressure source 216 is arranged to provide hydraulic pressure to the landing gear backup system in the event of a failure condition of a primary landing gear hydraulic pressure source.

Abstract: This invention presents a unique propulsion and maneuver-control system for crafts and devices. This invention develops its desired thrust force vectors from the vectors sum of centrifugal force vectors of rotating masses and their controlled gyroscopic force vectors. Also shown are applications of this propulsion and maneuver-control system for future VTOL-Hovering-Flying crafts, Scooters, Surfboards, marine/submarine-crafts, earth, moon, mars satellites disks and space-crafts. This invention has great potentials of creating new businesses in aerospace markets, all planets' weather modification business, bring people of the world closer together and perform critical tasks of modify trajectories to prevent run-away asteroids from hitting the earth.

Abstract: Described herein are methods and systems to dampen oscillations of a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the UAV's control system may dampen the oscillations by causing the UAV to switch to a forward flight mode in which movement of the UAV results in drag on the payload, thereby damping the oscillations. In another example, the control system may cause the UAV to reduce an extent flight stabilization along at least one dimension, thereby resulting in damping of the detected oscillations due to energy dissipation during movement of the UAV along the dimension. In this way, the control system could select and carry out one or more such techniques, and could do so during retraction and/or deployment of the tether.

Abstract: An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

Abstract: Aircraft landing gear forward trunnion support assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side and a forward trunnion support assembly. The forward trunnion support assembly includes first and second vertical support fittings coupled to the rear side of the rear spar, and a trunnion housing with a bearing. The trunnion housing is coupled between the first and second vertical support fittings. A central axis of the bearing is perpendicular to the rear side of the rear spar. The forward trunnion support assembly also includes a side load fitting disposed on the rear side of the rear spar. A first end of the side load fitting is coupled to the second vertical support fitting, and a second end of the side load fitting is coupled to the rear spar.

Abstract: A composite structure may comprise a composite core comprising a composite material, and a heat resistant system coupled to the composite core comprising a binder and/or at least one of a heat dissipation material or a thermal barrier material. The heat dissipation material may comprise boron nitride, graphene, graphite, carbon fiber, carbon nanotubes, aluminum foil, and/or copper foil, and the thermal barrier material may comprise montmorillonite, aluminum hydroxide, magnesium hydroxide, silicate glass, mica powder or flake, aluminum oxide powder, titanium dioxide powder, and/or zirconium oxide powder. The binder may comprise at least one of polyvinyl alcohol, polyvinyl alcohol copolyacetate, polyacrylamide, polyethylene glycol, polyethylenimine, polyurethane, polyester, or latex.

Abstract: An aircraft hubcap/wheel cover which uses ambient airflow (120 mph-175 mph) to rotate wheels on the landing gear of an aircraft accomplished by using slightly protruding slats, blades, scoops or other air capturing shapes, (once the landing gear has been lowered). These air capturing shapes are integrated as part of the hubcap/wheel cover during manufacture and are directly determined by ground speed applicable to that aircraft with the ultimate purpose being tire longevity. The wheel cover hubcap is a single piece design and has no moving parts.

Abstract: The present invention relates to a maintenance apparatus for a shock absorber of a landing gear, comprising a liquid reservoir which can be connected to an interior space of the shock absorber via a liquid line, a gas reservoir which can be connected to the interior space via a gas line, a coupling member for sealingly coupling the liquid reservoir and the gas reservoir, wherein the maintenance apparatus is configured to allow an exchange to occur of liquid and gas between the liquid reservoir and gas reservoir, respectively, and the interior space, the maintenance apparatus comprising control means for determining that a partial volume of the interior space occupied by the gas reaches a reference level as a result of the exchange and for bringing the partial volume of the interior space of the shock absorber respectively occupied by the gas and the liquid to a target level. The invention also relates to a maintenance method.

Abstract: A ground effect craft having a ground effect wing, a plurality of sponsons, and a control system is disclosed. The ground effect wing may include a fore ground effect wing and an aft ground effect wing. The ground effect wing may generate a stabilizing moment on at least one sponson to stabilize the ground effect craft. The plurality of sponsons may be dynamically coupled to the body. The plurality of sponsons may be dynamically coupled to each other. The dynamic coupling may permit the sponsons to move relatively independent of the body and each other, thereby stabilizing the ground effect craft. The ground effect craft may include a stabilizing wing.

Abstract: An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

Abstract: The present disclosure is directed to a propeller driven remote control flying device having an enclosed body. The motor and propellers of the device can be contained within the enclosed body. The enclosed body can include a plurality of pores through which air passes, with one side of the body generally functioning as an air intake, and the opposite side of the body functioning as an air outlet. The pores can be sufficiently small so as to prevent contact between persons, animals or articles and the motor driven propellers.

Abstract: Various embodiments of a foldable unmanned aerial vehicle having a multi-layer laminate structure and extendible arms are disclosed.

Abstract: An aircraft control system and control method are disclosed. The system comprises a remote control apparatus with a first control rod and a flight controller associated with an aircraft. The first control rod is configured to move in a first movement direction to control a motion of the aircraft in a first motion direction when an external force is applied on the first control rod and after a withdrawal of the external force, the first control rod returns to a preset position. The remote control apparatus operates to generate one or more control signals corresponding to the withdrawal of the external force. The flight controller controls the aircraft to maintain a flight state based on said control signals and one or more state signals, which are generated based on a measurement of the flight state by a flight controller associated with the aircraft state measurement sensors carried by the aircraft.

Abstract: A method, system and apparatus are provided for generating and dispersing plumes of reflective aerosols. Methods include: supplying fuel to an engine of an aircraft for combustion; supplying an additive to the fuel, where the additive includes at least one of a reflective aerosol or a precursor thereof; combusting the fuel and the additive to the fuel in the engine; and generating, in the exhaust from the engine, a plume of reflective aerosol, where the reflective aerosol reflects sunlight.

Abstract: Described are seating arrangements having at least one set of columns that include an aisle column of seating units positioned adjacent a wall column of seating units. The aisle column is positioned adjacent an aisle, and the wall column is positioned adjacent an exterior wall. Each seating unit has a bed position having a head end and a foot end, wherein at least a height-limited portion of the foot end is less than a delineating height that separates a lower portion of the aisle from a upper portion of the aisle. The seating units in the adjacent columns are longitudinally aligned and positioned adjacent one another, as well as being angled with respect to each other. The height-limited portion of the foot ends in the aisle column is positioned adjacent the aisle, and the height-limited portion of the foot ends in the wall column is positioned within a concave portion of the exterior wall.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. The leading edge assembly includes a plurality of structural layers and a plurality compliant layers alternately stacked with each other to facilitate thermal expansion and movement between the plurality of structural layers, while also providing a thermal break between the plurality of structural layers.

Abstract: Filtration apparatus are disclosed. An example filtration apparatus includes a housing including a plurality of walls defining a cavity, a filter located in the cavity, and a cleanout system coupled to the housing. The cleanout system includes a cleanout passageway between an outer surface of the housing and the filter. The cleanout system includes a cleanout inlet accessible from the outer surface of the housing and a cleanout outlet in fluid communication with the filter. The cleanout system enables removal of particulate from the filter without removing the filter from the housing.

Abstract: A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.

Abstract: An aircraft environmental control system comprising a bleed air or compressed ambient air input and a RAM air input, heat exchanger means for receiving bleed air from the bleed air input and RAM air from the RAM air input and using RAM air to cool the bleed air, and means for providing the cooled bleed air to an interior of the aircraft; the system further comprising means for feeding back exhaust air emitted from the interior of the aircraft to combine with the RAM air to further cool the bleed air or compressed ambient air.

Abstract: The invention lies in the field of skydiving and relates to a securing aid (100) for parachutists (20), which has a leg strap connector (101) and a connection element (102) for securing a parachutist (20) in an airplane (104) during the flight preceding the parachute jump. The securing aid (100) is connected or connectable, for example, to the leg strap (13) of a parachute system (10). The securing aid (100) according to the invention thus contributes to increasing the safety of parachutists (20) during the flight preceding the parachute jump.

Abstract: This invention relates to the use of an automatic safety parachute deployment system for drones (UAVs), which utilizes an airflow trigger that deploys one or more parachutes under certain aerodynamic conditions from the upward airflow during a flight malfunction. The system is mechanically activated without the use of electronics, batteries or an ejection spring which reduces the complexity and weight.

Abstract: An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

Abstract: This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.

Abstract: A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.

Abstract: Various methods enable a processor of a robotic vehicle to determine when the robotic vehicle has been stolen so that a self-recovery operation may be performed. Determining whether the robotic vehicle has been stolen may include evaluating, by a processor of the robotic vehicle, unauthorized use indicia, and determining that the robotic vehicle is stolen in response to determining that unauthorized use indicia exceed a threshold. Evaluating unauthorized use indicia may include determining whether an Integrated Circuit Card Identifier of a Subscriber Identify Module matches a stored value, determining whether a paired controller is different from a usual controller, determining whether the operator's skill has changed, and evaluating one or more trust factors that are observable features of normal operation.

Abstract: A method and device for inspecting the structural damage on the skin of an aircraft after a lightning strike, the skin has marks derived from the lightning strike, wherein the marks represent a Visual Damage (VD) and a Structural Damage (SD). The method includes for every mark: measuring the area of paint that has been removed by the lightning strike, and comparing the measured area with an area threshold value, wherein the threshold value is related to the Structural Damage (SD) of every mark.

Abstract: A method for conditioning to reduce lightning strike effects is provided herein. The method includes positioning a plurality of tabs on a component. The plurality of tabs are electrically conductive. The component includes at least one of a composite material and a metal material having at least one joint. The method includes positioning the component on a support that is electrically insulated, and connecting a plurality of wires between an initial set of the plurality of tabs and a pulse generator. The pulse generator is configured to generate a plurality of current pulses through the plurality of wires. The plurality of current pulses imitate a plurality of lightning strikes. The method further includes striking the component with the plurality of current pulses from the pulse generator, and reconnecting the plurality of wires to one or more different sets of the plurality of tabs between the plurality of current pulses.

Abstract: An aircraft lighting system (ALS) and apparatus which includes: a lighting generator control unit (LGCU) controlling a light source generator for generating a first, second and third type of light to each passive light head; a light bus coupled to the light source generator to receive the first, second, and third types of light and for converting the first type of light to a fourth type of light; a plurality of light transmission elements coupled to the light source generator; a plurality of light switches responsive to a switch command from the LGCU to optically not direct or direct light from the light bus to a light transmission element; a light conversion element connected for converting the first type to the fourth type of light; and the LGCU configured to command the light source generator to generate light in accordance with a load profile.

Abstract: An aircraft beacon light for an aircraft wing with a foldable wing tip includes a housing, a lens cover, and at least one light source arranged between the housing and the lens cover, wherein the aircraft beacon light is configured to emit flashes of red light in operation, and wherein the housing and the lens cover are shaped to embed the aircraft beacon light into a hinge assembly coupling the foldable wing tip to a main wing portion of the aircraft wing.

Abstract: Disclosed is a naval platform equipped with a deck-landing/takeoff zone for at least one aircraft and dolly-type mechanism for handling the aircraft to move it over the deck-landing/takeoff zone. The dolly-type mechanism includes a vacuum disc for immobilizing the dolly and thereby securing the aircraft in position on the deck-landing/takeoff zone, the operation of which is triggered by an analyzer of the behavior of the platform in order to avoid any risk of uncontrolled movement of the aircraft.

Abstract: A precision approach path indicator (PAPI) employs an LED light source with first and second arrays of LEDs or other efficient light sources, disposed one above the other and emitting their respective color lights along an optic axis to a collimating lens of focal length f. First and (optional) second aperture plates positioned along the optic axis, each being a respective frame with a cut-out defining a horizontally elongated aperture for light passing along the optic axis. Intermediate aperture plate(s) can be positioned between the first and second aperture plates. The first frame is positioned between the light source and the collimating lens at the focal distance f from the lens. The optional second aperture plate is positioned at the collimating lens and covers top, bottom, and side edge portions of the lens.

Abstract: A dolly for placement beneath a landing gear of an aircraft that enables transport of the aircraft without rolling the tire of the aircraft. The dolly includes a platform for a tire to rest on and a channel for positioning the tire. The dolly includes a winch for translating the dolly and aircraft tire relative to each other such that the landing gear is brought to rest on the platform, and one or more stops for securing the aircraft landing gear with respect to the dolly. Once positioned, the dolly can be used while transporting the aircraft, either by hand pushing, a hand towbar, a motorized tug with a towbar, or other mode. The dolly is useful for moving aircraft in tight spaces and is also useful for transporting aircraft with damaged landing gear or flat tires.

Abstract: An aircraft fuselage assembling jig includes: a base provided with a plurality of frame indexes for positioning both ends of a plurality of aircraft fuselage frames; a plurality of header plates, each of which protrudes from the base so as to extend along an aircraft fuselage panel, the header plates being arranged parallel to each other in an axial direction of the aircraft fuselage panel; and a plurality of electric cylinders radially provided on each of the plurality of header plates, the electric cylinders moving respective receiving members in a radial direction of the aircraft fuselage panel, the receiving members contacting a skin included in the aircraft fuselage panel.

Abstract: An assembly including a support tower and at least two support systems, each bearing a panel of a section of an aircraft fuselage and including four fixing points. The support tower includes a tower extending along an axis X, a seat on which the tower is mounted and which is rotationally mobile about the axis X, and, for each fixing point, a fixing base mounted on a three-dimensional adjustment system mounted on the tower and motorized to displace the fixing base in two horizontal directions and one vertical direction, where each fixing point and the associated fixing base can be locked with one another to ensure the fixing of one with the other, and that can be unlocked to allow them to be separated. Such an assembly makes it possible to keep the various elements of the section vertical during assembly and allows for a space saving on the ground and a saving on transfer utilities.

Abstract: A multi-layer shell structure for a vehicle and method of providing a multi-layer shell structure for a vehicle. The multi-layer structure includes a thermal protection system (TPS) layer, a structural layer connected to the TPS layer, and a high tensile fabric barrier layer bonded to the structural layer. Room-temperature-vulcanizing silicone may be used to bond the TPS layer to the structural layer and bond the high tensile fabric barrier layer to the structural layer. The high tensile fabric barrier layer may create a seal on the structural layer. The multi-layer shell structure may include inner shell enclosing a passenger and/or cargo compartment and an annulus between the inner shell and the high tensile fabric barrier layer. The high tensile fabric barrier layer may prohibit entry of gas into the annulus in the event a hole is created through a portion of the multi-layer shell structure.

Abstract: A lunar orbiting satellite system executes orbit planning of assigning a function (positioning, communication, and flashing) to an artificial satellite (AS) depending on a relative position of the AS to the moon at a time when the moon and the AS are observed from an input point on the earth, and correcting the relative position, which changes in accordance with the moon revolution period. The system includes: a satellite orbit planner which assigns a function to each ASs forming an AS group flying around the moon depending on a relative position of each ASs to the moon at a time when the moon and ASs are observed from an input point on the earth, and set a target orbit according to the function; and a satellite controller which causes the each ASs to execute control based on the function to implement switching of the function.

Abstract: A vertical bag-making/filling machine (1) comprises: a film-feeding unit (8) which intermittently feeds a film (F) formed into a tubular shape downward; a nozzle (10) supplying contents (X) into the film; a sealing-off unit (17) arranged below a lower end of the nozzle and forming a bag body (Fg) by heat-sealing the film in a transverse direction; a lower shaping unit (30) regulating swelling of the film on the lower side of the sealing-off unit; an upper shaping unit (40) regulating the swelling of the film on the upper side of the sealing-off unit; and a separating unit (25) for separating the bag body (G) fully filled with the contents by cutting the transverse seal (Y1, Y2) formed by the sealing-off unit.

Abstract: Disclosed are a vacuum suction nozzle for improving vacuum suction performance and a vacuum suction apparatus including the same. The nozzle includes blade portions extending from both sides thereof so as to reduce a gap occurring between the nozzle and an outer skin material for a vacuum insulation panel (VIP) or other vacuum wrapping paper when the outer skin material or vacuum wrapping paper is sealed, thereby minimizing the occurrence of a leak and thus enabling efficient vacuum suction. Further, the nozzle achieves efficient vacuum suctioning by ensuring a suction channel inside the vacuum insulation panel (VIP) or other vacuum wrapping paper through a protrusion extending to the front of the nozzle.

Abstract: A thermoforming packaging machine that includes a film holder for receiving a lower film supply roll and one behind the other in a sequential arrangement along a production direction a pretreatment station for pretreating the lower film web, a forming station for forming troughs in the lower film web by thermoforming, an insertion line for filling the troughs with products and a sealing station for sealing the troughs with a top film. A transport device is configured to transport the lower film web along the production direction through the pretreatment station, further to the forming station, further to the insertion line and finally to the sealing station. A deflection unit arranged at least partially below the pretreatment station is configured to deflect the lower film web before reaching the pretreatment station. The pretreatment station may include a punching or slitting unit to punch or slit the lower film web.

Abstract: A filling device for aseptic filling of pouches comprising a pouch fill assembly having a movement assembly, a plug removing assembly and a filling assembly. The movement assembly defining an aseptic zone and configured to direct a pouch having a spout and a plug sealing the spout through the pouch fill assembly from an inlet to an outlet. The plug removing assembly having at least one plug removing station including a grasping assembly, a plug retaining structure and an actuator assembly. The filling assembly having at least one filling station structurally configured to dispense a flowable material into the pouch through the spout.

Abstract: A wire guide assembly is provided for the accurate labeling of different diameter elongated objects, wires, or cables within a wrapping mechanism of an elongated object label applicator. The label applicator guide permits elongated objects of different diameters to be placed within substantially the center of the wrapping mechanism to continuously facilitate proper application of a label to different sized elongated objects.