Abstract: There is described an extending jack plate, comprising several components, in combination. There is a right transom mounting bracket and a left transom mounting bracket. There is a right slide mounting bracket and a left slide mounting bracket slidably coupled to the right and left transom mounting brackets. A slide plate is slidably coupled to the right and a left slide mounting brackets. Adjustment blocks and adjustment rods provide forward and rearward adjustment.

Abstract: A control system and method for deterring theft of a marine vessel. A security control circuit receives a transponder identification code from a transponder. The engine control circuit has a status that is based on a comparison of a stored identification code with the transponder identification code. The status of the engine control circuit is locked if the stored identification code does not match the transponder identification code and the status of the engine control circuit is unlocked if the stored identification code does match the transponder identification code. The security control circuit determines an arbitrated lock status of the control system based on a conjunctive analysis of the locked and unlocked statuses of a plurality of engine control circuits connected to a network bus, and indicates the arbitrated lock status to an operator of the marine vessel.

Abstract: It is proposed a method for steering a seismic vessel associated with a sail line and a current preplot line. The seismic vessel tows at least one acoustic linear antenna including receivers, the receivers receiving signals generated by at least one source and reflected by subsurface's layers at a plurality of reflexion points. The method includes: a) computing distances di, i?{1 . . . n}, from n reflexion points, included in the plurality of reflexion points, to a boundary of an already obtained binning coverage zone associated with an already used previous preplot line; b) computing a distance D, from the n reflexion points to n target reflexion points, as a function of the distances di; and c) providing steering information comprising or based on the distance D to a navigation system or to an operator of a navigation system, to alter the course of the seismic vessel.

Abstract: A wing flap control system on a wing comprising at least two control plates having an opening sized to accommodate a drive shaft, a drive shaft that engages each of the openings in each of the plurality of plates, a sprocket rotatively affixed the drive shaft with the drive shaft penetrating the other control plate, at least two idler sprockets between the control plates, a chain wrapped around the sprocket and idler sprockets, a support arm rotatively coupled to the chain by a chain shoe and to a foreflap, a link arm rotatively coupled to the support arm and to a flap, where movement of the drive shaft causes the foreflap and flap to extend and retract to increase or decrease the surface area of the wing.

Abstract: A process for fabricating an integrated panel structures and the structures thereby fabricated are provided with first and second stiffeners positioned on a base skin so that the stiffeners intersect at respective intersecting regions. First and second fiber-reinforced resin-composite overlapping layers are provided on the first and second stiffeners so that at least lateral regions thereof are laminated to a corresponding region of the base skin. The base skin and the overlapping layers may be assembled with the first and second stiffeners to form a panel preform which may then be subjected to curing conditions so as to co-cure all previously uncured components and thereby form an integrated composite panel structure with mutually intersecting first and second stiffeners.

Abstract: The invention relates to a floor plate for bearing upon a floor framework in an aircraft. The floor framework is formed with a multiplicity of transverse beams which are arranged like a truss, and a multiplicity of longitudinal profiles, especially seat rail profiles, which extend transversely to the transverse beam. At least one sub-assembly, for example a kitchen module and/or a sanitary cell, can be fastened on the floor plate. The floor plate bears upon at least four longitudinal profiles and has at least one connecting point, especially an insert, for fastening of the sub-assembly. In addition, at least one system port is provided for the tool-less, pluggable connecting of the sub-assembly to any on-board systems of the aircraft, especially to electrical systems, to feed-air systems, to exhaust air systems, to fresh-water systems or to waste-water systems.

Abstract: A hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller.

Abstract: The invention provides an aircraft with a ventral fairing able to store equipment and systems in lateral zones. The ventral fairing (20) comprises a first zone of length L1 along the X-axis, where the area of the cross-section perpendicular to the X-axis increases in the direction of the air flow and a second zone of length L2, where the area of the cross-section perpendicular to the X-axis decreases in the direction of the air flow, being L1>L2 and being placed the rear end of said first zone behind the intersection of the trailing edge of the wing (15) with the fuselage (13).

Abstract: A rudder system for an aircraft includes a center box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the center box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a center box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.

Abstract: Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force.

Abstract: A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis.

Abstract: A system (10) having a control plate (15) for controlling the pitch of the blades (5) of a propeller, a power block (20), and a directional control valve (30) for feeding said power block (20) with fluid. The power block (20) is sealed and includes at least a body in which at least one piston (22) that is secured to a piston rod (25) projecting from said body (21) is movable in translation, a repeater rod (50) connecting said piston rod (25) to said control plate (15). The control valve (30) is sealed and comprises a stationary manifold (35) and a movable manifold (40) that is movable in rotation, said stationary manifold (35) being controlled by a control lever (31) connected by repeater means (32) to said repeater rod (50). A respective pipe (60) connects each chamber (23, 24) of said power block (20) to said movable manifold (40).

Abstract: A technique is directed to operating a UAV. The technique involves launching (or guiding) the UAV into flight. The technique further involves performing a series of aileron (or other control surface) deflection evaluations while the UAV is in flight. The technique further involves performing a UAV remedial operation in response to the series of aileron deflection evaluations indicating abnormal aileron behavior, e.g., the UAV can send a warning message to a ground control station (GCS), land the UAV at a target location, deploy a chute, and so on. Such operation enables detection of an unexpected change in the UAV's center of gravity, e.g., due to a blocked fuel bladder connection, icing on one side of the UAV, mechanical failure of an aileron, etc.

Abstract: The invention concerns a device for the active control of a force feedback for a control device, comprising a calculator, a position sensor (3) configured to provide the calculator with an effective position signal (Pm) of the control device, and an actuator (2) ensuring the displacement of the control device at the command of the calculator, the calculator being configured to use the effective position signal and modulate a setpoint current (lc) delivered to the actuator to ensure the position feedback of the displacement of the control device, characterized in that the calculator is further configured to create at least one saturation terminal (Bsat+, Bsat?) according to a predetermined function of the value of the effective position signal of the position/force law kind, and to saturate the setpoint current using the at least one saturation terminal.

Abstract: Techniques are described to simplify operation and maintenance of an aircraft by configuring an avionics unit to wirelessly communicate and receive avionics related data in a seamless fashion. In embodiments, an aircraft is equipped with a regulatory-certified avionics device configured to be installed in the aircraft. The system includes a memory card reader and associated memory card. The memory card includes a wireless transceiver to facilitate communication between the avionics unit and a mobile device (e.g., a tablet computer or smart phone employing a suitable application, a portable avionic device, etc.).

Abstract: An aircraft (10) with improved aerodynamic performances is adapted to keep the directional stability and a very good aerodynamic behavior at medium-high incidence. The aircraft (10) includes a fuselage (12) to which shaped wings (18, 20) are associated, and a nose (52). The aircraft (10) also includes a vortex control device (72) of the extension of the leading edge of the wing at the root (LERX), shaped in order to symmetrize the bursting of the vortices generated by such LERX with a medium-high incidence. Said aircraft comprises removable equipment with at least one dissipation device of incident radar waves, on at least one hot portion of the aircraft.

Abstract: An articulated landing gear may include electrical lines and/or hydraulic lines located within the articulated landing gear. The articulated landing gear may have a hollow structural post and a hollow trailing arm coupled by a pivot joint. The electrical lines and/or hydraulic lines may be routed through an interior of the hollow structural post and through an interior of the hollow trailing arm. A bulkhead within the hollow structural post or the hollow trailing arms may include guide holes. The electrical lines and/or hydraulic lines may be supported by the bulkhead by passing through the guide holes. The electrical lines and/or hydraulic lines may be flexible around the pivot joint.

Abstract: According to one aspect, a controller, including a processor, sets an initial vibration frequency to be applied to an airframe. The controller commands one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency. The controller determines a vibration response of the airframe at the initial vibration frequency using sensors. The controller sweeps through a range of vibration frequencies to be applied to the airframe. The one or more force generators are commanded to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies. The controller determines a range of vibration responses of the airframe over the range of vibration frequencies using the sensors. A global stiffness of the airframe is determined based on the vibration response and the range of vibration responses. The controller reports results of the determined global stiffness of the airframe.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, and a tip region extending from a radial extent of the main region to a blade tip. At least a portion of one of the root region, the main region and the tip region includes an airfoil profile section defined by a scaled set of coordinates in which a set of y/c coordinates listed in Table I are scaled by a selected factor.

Abstract: A rotorcraft rotor fitted with a device for damping lead-lag oscillations of the blades (2) of the rotor. The blades (2) are hinge-mounted on a rotary hub (1) of the rotor via respective sleeves (3). The damper device comprises a set of dampers (6), each individually housed in a respective one of said sleeves (3) and deformable between two fastening points (8, 9), one with the sleeve and the other with an engagement member (7) for engaging the hub (1) via a linkage (10). For each of the sleeve (3), the damper (6) housed by a given sleeve (3) is in hinged engagement with the linkage (10) via a lever arm (11) hinged to the sleeve (3).

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

Abstract: The invention relates to a mounting post that can be selectively installed in a helicopter or other aircraft in order to support a tactical weapon or other equipment and removed when not required so as to free up additional passenger and/or cargo space. Preferably the mounting post can be quickly installed and removed without requiring the use of any tools. An elongated post having one or more T-track along its length is slid through an opening in an aircraft panel, such as the floor, and slid into a bracket with corresponding T-rails. A stop is used to limit further movement of the post through the bracket and a latch is used to selectively allow the post to be removed.

Abstract: A device for stowage of carts including: a first compartment configured to receive carts lined up side by side; a second compartment configured to receive carts lined up side by side, including an aperture allowing cart entry and exit and arranged above the first compartment; a substantially horizontal platform capable of moving in a vertical direction between a lower position in which it is substantially at floor level and a higher position in which it is substantially level with a lower, substantially horizontal wall of the second compartment and facing the opening thereof; and a mechanism arranged in the second compartment for motorized transfer of at least one cart from the second compartment to the platform and vice versa.

Abstract: A vehicle seat that includes a linkage assembly interconnecting a seat pan assembly, seat back assembly and leg rest assembly whereby, as the seat carriage assembly is moved aft the seat pan assembly and the seat back assembly simultaneously adjust to maintain a predetermined seating position during an initial recline motion with the leg rest assembly remaining in a retracted position below the seat pan assembly. The leg rest assembly progressively elevates into a leg-supporting position during a subsequent recline motion as the back rest assembly and seat pan assembly progressively recline towards a lie-flat configuration.

Abstract: A seat fastening device for fastening a seat or for lashing loads to a fastening rail fastened to a floor includes at least one movable fastening means, which is provided for coupling to the fastening rail, a force accumulation unit, an actuating unit and a gear unit. The gear unit is provided to prestress the force accumulator unit in an unlocking operation and to relieve the stress on the force accumulator unit in a locking operation.

Abstract: A system for cooling a heat exchanger on board an aircraft includes an engine bleed air line connected to an engine of the aircraft and adapted to supply engine bleed air to the heat exchanger. The system further includes a process air line branching off from the engine bleed air line such that the engine bleed air is supplied to the process air line and connecting to an input side of a turbine. The system also includes a cooling air line connected to an output side of the turbine such that cooling air produced by an expansion of the engine bleed air supplied to the turbine is supplied to the cooling air line and then to the heat exchanger. The heat exchanger is adapted to transfer cooling energy from the cooling air to the engine bleed air supplied to the heat exchanger from the engine bleed air line.

Abstract: There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a longitudinal direction of convertiplane in helicopter mode and being substantially parallel to longitudinal direction in aeroplane mode; convertiplane also comprises an electrical power storage device; and an electrical machine which comprises, in turn: a stator electrically connected to storage device; and a second rotor operatively connected to a shaft of first rotor; electrical machine acts as an electric motor for driving in rotation said first rotor by using the electrical power stored in storage device; or as an electrical power generator for re-charging storage device by causing the rotation second rotor under the action of a wind current.

Abstract: A hybrid aircraft (1) having a fuselage (2) extending longitudinally along an anteroposterior plane of symmetry (PSYM) from the rear (4) of the aircraft (1) towards the front (3) of the aircraft (1). The aircraft (1) has a rotary wing (6) carried by the fuselage (2) of a lift surface (10) fastened to the fuselage (2) and constituted by a first half-wing (11) and a second half-wing (12). The aircraft (1) has a first propulsion unit (30) carried by the first half-wing (11) and a second propulsion unit (40) carried by the second half-wing (12). Each propulsion unit (30, 40) includes at least one tractor propeller (31, 32, 41, 42), and at least one propulsion unit has two propellers (31-32, 41-42) on the same axis, each of said propellers rotating about an axis of rotation (AX) that is offset transversely from said anteroposterior plane of symmetry (PSYM).

Abstract: An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.

Abstract: Embodiments provide a flying boom that is capable of refueling both receptacle-equipped aircraft and probe-equipped aircraft. In one embodiment, a flying boom includes a refueling tube at an end of the flying boom that is adapted to extend from the end of the flying boom to refuel receptacle-equipped aircraft. The flying boom further includes a retractable hose and drogue assembly at the end of the flying boom that is adapted to extend from the end of the flying boom to refuel probe-equipped aircraft.

Abstract: A multi-zone battery station is provided, comprising a plurality of landing areas configured to support a UAV. The battery station may permit battery life to be reloaded onto a UAV, which may include recharging a battery of the UAV or exchanging the UAV battery for a new battery. The different zones may accommodate different UAV types, different battery types, or operate in accordance with different energy provision rules. A marker may be provided on a landing area to aid in guiding the UAV to an appropriate landing area.

Abstract: A tail cone integrated ram air turbine (RAT) includes a rotatable segment of an aircraft tail cone configured to deploy a set of RAT blades. The tail cone integrated RAT also includes a power transfer shaft connected between the rotatable segment and configured to transfer power to from the rotatable segment to an auxiliary power unit (APU). The tail cone integrated RAT further includes a controller connected to the APU and configured to control power output from the APU. When emergency power for an aircraft is needed, the set of RAT blades is deployed from the rotatable segment of an aircraft tail cone. Mechanical power from the rotatable segment is transferred to an APU generator to produce emergency electrical power.

Abstract: A lining/fairing panel, in particular a lining/fairing panel for an airborne vehicle such as an aircraft or a spacecraft is provided. The lining/fairing panel includes a panel body having a first surface and a second surface opposite to the first surface, an electrically conductive coating applied to the first surface or the second surface, and a via arranged in the panel body reaching from the first surface to the second surface of the panel body. The via is formed in an inner region of the panel body. The borders of the inner region are spaced apart by a predetermined distance from the borders of the first and second surface of the panel body.

Abstract: An aircraft docking system is configured to be located at a docking site. The system comprises distance determining means configured to determine, using electromagnetic radiation signal reception means, at least a distance between the system and an aircraft. The distance determining means are further configured to measure at least one property of a receiver signal received by the signal reception means, the property being related to the visibility at the docking site, compare said measure of the at least one receiver signal property with a threshold value and, depending on the comparison, provide a signal indicative of whether or not the visibility at the docking site is good enough to allow safe docking of the aircraft.

Abstract: Provided is an apparatus to interface a boarding bridge having a first deck and an airplane having a second deck. The apparatus includes a lower-frame assembly, upper-frame assembly, bridge gangplank assembly, and airplane gangplank assembly. The lower-frame assembly includes a plurality of wheel assemblies. The upper-frame assembly is connected to the lower-frame assembly at adjustable height and pivoting position, and includes a third deck atop the upper-frame assembly. The bridge gangplank assembly is connected to a first end of the upper-frame assembly, and includes a fourth deck to connect the first deck and the third deck. The airplane gangplank assembly is connected to a second end of the upper-frame assembly, and includes at least a fifth deck to connect the third deck and the second deck.

Abstract: A collapsible runway side barrier for preventing foreign object debris (FOD) from entering a runway and taxiway is disclosed. The barrier may have an aerodynamic profile, one side of the bather profile may be convex and the other side of the barrier profile may be concave. The side barrier may further have ground attachment elements and may be constructed to collapse if the landing wheels of an aircraft impact the barrier.

Abstract: A control system for a hybrid propulsion spacecraft, configured for transfer between low earth parking orbit (LEO) and a Lissajous L2 orbit (L2O), including a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft, a second control portion communicably connected to a low thrust high specific impulse (LT-HI) engine portion of the hybrid propulsion spacecraft, the first and second control portions being configured to control both the HT engine portion and the LT-HI engine portion to provide an optimal LEO to L2O transfer trajectory, wherein the optimal LEO to L2O trajectory includes an optimal LT-HI trajectory portion, selected from a stable manifold trajectory, and an optimal HT trajectory portion, and wherein the LT-HI trajectory portion and HT trajectory portion are configured for providing a combined optimal trajectory along the LEO to L2O transfer trajectory, and are optimized substantially simultaneously.

Abstract: A solar generator tug is disclosed. The tug can dock with spacecraft to provide power for the spacecraft. Further, the tug may dock with other specialty tugs to form a custom transport system.

Abstract: A propellant tank for containing a propellant with a liquid phase, preferably for a satellite, includes a tank shell wrapped or wound with scintillating glass fibers, a gamma radiation emitter arranged preferably in the center of the tank, and photodiodes allocated to the glass fibers. Preferably, plural glass fibers are wound in cylindrically symmetrical sections around the tank, and the winding axis of the glass fibers extends through the tank outlet. The glass fibers scintillate and emit pulses of light in response to being impinged upon by gamma radiation. The quantity and location of liquid propellant in the tank is determined by evaluating the light signals emitted by the glass fibers. The tank shell is preferably fabricated of a lightweight metal such as aluminum or titanium, to minimize gamma radiation absorption in the tank shell wall, and thereby minimize the required emitting magnitude of the gamma radiation source.

Abstract: The present disclosure relates to the deorbiting of satellites in low orbit that have entered safe hold mode. A device makes it possible to decide in an autonomous manner and on the basis of information existing in the satellite, when and where to trigger a series of short thruster manoeuvres to modify the satellite orbit with the aim of deorbiting.

Abstract: A coupling/uncoupling mechanism maintains, when a male coupling body is coupled to a female coupling body, a condition that the male coupling body is inserted in an insertion space and the other end of a lever member is in a position in proximity to the insertion space, so that an engaging surface of an engaging member is contacted with an engageable surface of the male coupling body. When the male coupling body and the female coupling body are uncoupled, the other end of the lever member moves to a direction to be apart from the insertion space, so that the engaging surface moves toward a withdrawing direction. This allows releasing the contacting of the engaging surface with the engageable surface. This provides that sufficient fastening force can be achieved with a simple configuration and the coupling status can be retained with a smaller force as compared with such a fastening force, and further, a recombination can be easily achieved even after a separation is made.

Abstract: A standard transit tug is disclosed. The tug can dock with spacecraft to provide propulsion for the spacecraft. Further, the tug may dock with other specialty tugs to form a custom transport system.

Abstract: The invention relates to a method, a satellite, and a system or an arrangement with at least one satellite for detecting flying objects that are located in the vicinity of a planet, planetoid or similar celestial bodies. The invention further relates to the use thereof for carrying out said method and particularly to a constellation of LEO satellites (LEO=Low Earth Orbit) as an early warning of ballistic missiles, wherein said constellation comprises only satellites on equatorial orbits or orbits with low inclination. Satellite constellations in the low earth orbit (LEO) for missile detection are used for early warning of ballistic missiles, either by detecting the combustion phase of the flying object or by detection during the free-flight phase. The viewing direction of the sensors can be directed directly toward the earth or at an angle past the atmosphere.

Abstract: A method for compacting and packaging a plurality of slugs of product and apparatus for accomplishing the same. The invention describes collecting weighed product in an intermediate settling device to form compact slugs of product. The device can comprise a single settling chamber for each slug of product or can comprise multiple settling chambers which are axially rotatable. The slugs can be compacted by jostling and/or vibrating the settling device. Thereafter, the slugs of product are discharged to a multiple bagmaking packaging apparatus.

Abstract: An apparatus for collecting a flattened tubular box, for opening-out and transferring the tubular box towards a receiving station has a first member hinged to a frame, bearing first aspirating means. Second, third, and fourth hinged members and the frame forming a four-bar linkage. A fifth member, hinged to the fourth member, bears second aspirating means. An abutting member is arranged between the first member and the receiving station inferiorly of the tubular box. The apparatus is being designed such that when the tubular box is in the folding position, a second wall of the box can be intercepted by the second aspirating means and folded progressively with respect to the first wall, the first aspirating means disengage the first wall, and the box moved by the second aspirating means up to rest on the abutting member with a consequent complete opening-out of the tubular box.

Abstract: Methods and apparatus for tilting and filling a carton with a pouch and a flowable food product are described. The carton can be tilted prior to filling in order to minimize a void between the pouch and a sidewall of the carton. The carton is pivoted to a tilted orientation, such that the sidewall includes a lowermost inclined segment. The pouch is then inserted into the carton either prior to or after pivoting the carton to the tilted orientation so that the pouch can substantially rest against the inclined segment. The flowable food product is then at partially deposited into the carton, such that the flowable food product substantially fills in next to the pouch instead of between the pouch and the inclined segment. After a sufficient height of flowable food product has been deposited into the carton, the carton can be returned to a vertical orientation and closed.

Abstract: A packaging unit for producing sealed packages from a tube of a sheet packaging material fed along a feed path having a first axis; unit comprises: jaws movable cyclically along path between a seal position in which they grip and seal tube to form sealing bands of packages, and a rest position in which they are detached from tube; and folding flaps fitted movably to jaws; folding flaps are movable between: an open position in which they are detached from tube, and a fully closed position in which they cooperate with tube for forming folded flaps in package; the jaws are also cyclically movable in an intermediate position, which is arranged between rest position and seal position; folding flaps are movable relative to the jaws into a partly closed position, which is arranged between open position and fully closed position, when the jaws are set in intermediate position.

Abstract: A turntable assembly for a stretch wrapping machine comprises a frame, a hub rotatably mounted to the frame on a shaft, a turntable mounted to the hub, and a plurality of rollers rotatably mounted to the frame defining a generally horizontal supporting plane for the turntable. Each roller has an axis of rotation generally parallel to the supporting plane and generally passing through the turntable axis of rotation. The frame is constructed so as to elastically deform, upon a load being placed upon the turntable that results in the load not being evenly supported by the rollers, to permit the roller axis of rotation to tilt relative to the horizontal supporting plane while still passing through the turntable axis of rotation.

Abstract: Disclosed is a mobile strapping device for strapping packaged goods with wrap-around strap, including a tensioner for applying a strap tension to a loop of a wrapping strap, and a friction welder for producing a friction weld connection in two areas of the loop of the wrapping strap disposed one on top of the other, and a chargeable energy storage means for storing energy, in particular electrical, mechanical, elastic or potential energy, that can be released as drive energy at least for the friction welder for producing a friction weld connection. The strapping device is provided with a common drive for the tensioner for producing a tensioning motion, and for the friction welder for producing an oscillating friction welding motion and for a transitioning device for producing a transitioning motion of the friction welder from a rest position to a welding position.