Abstract: A watercraft manoeuvring device for mounting on a watercraft is disclosed comprising an elongate member having a mounting end and an opposed fin end that is spaced from the mounting end. The device includes a mounting formation on the mounting end for mounting on the watercraft and a fin mounted on the fin end. The fin has a bearing surface for interacting with water and the elongate member is capable of flexing when the fin is subjected to hydrodynamic water forces when travelling through water. The device may be integrally formed from a polymeric material. A watercraft such as a surfboard having the watercraft manoeuvring device is also disclosed.

Abstract: A kayak has a front hull portion and a back hull portion. The front hull portion has a front engagement portion. The back hull portion has a back engagement portion that mates in an assembled state with the front engagement portion to form a passenger cockpit. At least one latch is engageable between the front and the back hull portions in the assembled state. A substantial portion of the rotated front hull portion fits within the back hull portion in a stowed state.

Abstract: A boat may have a deck and a plurality of pontoons or hulls supporting the deck of the boat. The boat may include a starboard side pontoon, a port side pontoon, and possibly a middle pontoon. A positioning assembly may be provided with one or more of the foregoing pontoons. Each of the positioning assemblies may comprise a link assembly coupling the deck to the starboard side toon, wherein the link assembly is configured to permit pivoting of the starboard side toon relative to the deck from a retracted position, where the starboard side toon is proximate to an underside of the deck, to an extended position, where the starboard side toon is moved further from the underside, and an actuator provided to position the starboard side toon between the retracted position and the extended position.

Abstract: A flat-bottom fluvial transport boat comprising inflatable buoyancy tanks consisting of at least one pair of port side and starboard inflatable volumes. The paired inflatable volumes are connected to each other by means of one or more pressure balancing means.

Abstract: A free-floating watercraft lift includes a plurality of pairs of tanks each having a first tank and a second tank, a plurality of lower frame assemblies, first and second upper frame assemblies, and a control system comprising at least one blower for selectively providing air to each of the first and second tanks of the plurality of pairs of tanks. The first and second tanks of each pair of tanks are laterally spaced-apart and facing one another. Each one of the lower frame assemblies connects the first tank and the second tank of a separate one of the pairs of tanks The first upper frame assembly connects each of the first tanks of the plurality of pairs of tanks and the second upper frame assembly connects each of the second tanks of the plurality of pairs of tanks.

Abstract: The present disclosure relates, in one aspect of the disclosure, to an inflatable water sport safety garment for providing buoyancy to a wearer comprising a harness structure, at least one handle, and at least one inflatable flotation device. The harness structure may include at least two shoulder portions, at least one torso portion encircling the torso of the wearer and attached to the shoulder portions, and at least one central portion connected to the shoulder portions.

Abstract: The present invention relates to a baby float. The multi-functional baby float comprises a float body and a buoyant tail for increasing the buoyancy of the back; the buoyant tail is detachably connected with the end of the float body; and the back of a head of the float body is provided with an elevating mechanism for raising the head of the float body. The elevating mechanism comprises an inflatable airbag or a connecting structure. The connecting structure comprises some rows of female buckles; the buoyant tail is provided with son buckles; and the buoyant tail is fixedly connected with the float body through the matching of the son buckles and the female buckles. The present invention has the characteristics that the back buoyancy can be increased to prevent roll-back, the buoyant tail can be detached and installed below a headrest.

Abstract: A system and method for sending instrument data from a sub-surface activity, such as data collection by one or more sensors, to another location, e.g., a satellite, a ground-based location, a vessel, etc., with minimal time exposure and minimal visibility of any system components at the water surface. Exemplary embodiments include a motorized payout-and-retrieval system or device, an air injection device, and a water-level sensor with automation control that together can be used to move a vessel, connected to an antenna, from a position in the water column in which the antenna is below the surface to a higher position in which the antenna is at or above the surface for data transmission.

Abstract: An enclosure structure suitable for high-pressure environments includes a feedthrough for coupling components housed within the enclosure structure to components external to the enclosure structure. The enclosure structure includes a housing comprising one or more cavities for receiving one or more electronic components within an interior of the housing and a bore through the housing. The one or more electronic components comprises a connector element and the bore comprises a non-tapered portion and a tapered portion. The non-tapered portion is proximate to the interior of the housing and the tapered portion is proximate to the exterior of the housing. The bore is configured to receive a feedthrough pin for coupling the connector element to an external component external to the enclosure structure. The enclosure structure also includes a feedthrough pin extending through the bore and a potting material disposed within the tapered portion surrounding the feedthrough pin.

Abstract: A method of controlling a marine drive on a marine vessel includes receiving a trim position instruction to adjust a trim position of the marine drive, receiving a steering position of the marine drive, determining an allowable steering angle range based on the trim position instruction and/or the adjusted trim position of the marine drive, and controlling a trim actuator to adjust the trim position of the marine drive based on the trim position instruction, the steering position, and the allowable steering angle range such that the steering position of the marine drive remains within the allowable steering angle range for the adjusted trim position.

Abstract: An outboard motor includes a propeller shaft, a lower case, an upper case, and a splash guard. The lower case houses the propeller shaft. The upper case is located above the lower case. The splash guard includes an upper plate that projects forward from the upper case. The splash guard is separate from the upper case and is attached to the upper case.

Abstract: An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

Abstract: A panel including an outer face sheet; an inner face sheet; a foam disposed between the outer face sheet and the inner face sheet; and a core structure (e.g., a stringer comprising a hat structure) between the foam and the inner face sheet; and between the foam and the outer face sheet. The core structure is protected from impact damage and increases flexural stiffness of the panel on an aircraft wing.

Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

Abstract: A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The ducted fan further includes a fastening device configured to support mounting of the ducted fan on a structural component of the aircraft. The fastening device includes a pin and a guide body. The guide body is configured to receive and guide the pin, the pin is insertable proceeding from the inner wall into a recess of the guide body, a first end of the pin protrudes relative to the outer wall, and the pin is configured to be mounted, via the first end, on a bearing of the structural component of the aircraft.

Abstract: Air acceleration at leading edge of aircraft wing. In one embodiment, a slat disposed along a leading edge of a wing of an aircraft. The slat includes a skin structure having an aerodynamic shape, and a hollow space within the skin structure. The slat further includes a nozzle disposed on the skin structure to accelerate air collected in the hollow space into an external environment outside the slat to increase lift and reduce drag for the wing.

Abstract: A rotor system has a mast axis, a first rotor rotatable about the mast axis in a first direction and the first rotor has a first number of first rotor blades, and a second rotor rotatable about the mast axis in a second direction and the second rotor has a second number of second rotor blades that is different than the first number. The second direction is opposite the first direction.

Abstract: A ducted fan of an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan radially at the outside and that defines a flow channel for air flowing via the fan. The stator-side duct has an inner wall facing toward the fan, an outer wall averted from the fan, and at least one stiffening strut that runs within the flow channel. The stiffening strut, at one respective end, extends through the duct and protrudes radially relative to the outer wall of the duct. At the respective end of the stiffening strut, a fastening device is formed. The fastening device is configured to mount the ducted fan on a structural component of the aircraft. The fastening device has an insert composed of a fiber-reinforced plastic and laminated into the respective end of the stiffening strut.

Abstract: A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The inner wall and outer wall each includes at least one layer composed of fiber-reinforced plastic. At least two honeycomb cores are arranged between the inner wall and the outer wall, the at least two honeycomb cores abutting against one another in an axial direction of the ducted fan. The honeycombs of the at least two honeycomb cores extend at least substantially in a radial direction of the ducted fan. A first of the at least two honeycomb cores is, at least in a region of an abutting surface that adjoins another of the at least two honeycomb cores, enwound or encased by at least one layer composed of fiber-reinforced plastic.

Abstract: A method for improving a blade in an end zone of the blade, spanwise along the blade, and such an improved blade and a rotor comprising the improved blades. The leading edge of the aerodynamic profiles situated in the end zone is shifted from the upper surface half-profile towards the lower surface half-profile, then the leading edge sections of the two half-profiles are modified in order to connect the leading edge to the intermediate sections of the two half-profiles. Next, the blade is manufactured according to the modified aerodynamic profiles. Consequently, the negative camber of the aerodynamic profiles of the blade is thus increased, helping improve the aerodynamic performances of the blade during hovering flight.

Abstract: The present disclosure is directed to rotor assemblies for scissoring rotors, aircraft including the same, and associated methods. In one example, a hub assembly comprises: a first hub subassembly configured to rotate a first blade assembly about an axis of rotation in a first plane, a second hub subassembly configured to rotate a second blade assembly about the axis of rotation in a second plane, and a rotary guide configured to control an axial position of the second hub subassembly relative to the first hub subassembly about the axis of rotation. The rotary guide is configured to adjust the axial position as a function of a lifting force generated by the first blade assembly or the second blade assembly.

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tad conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

Abstract: An amphibious drone having a fuselage, a vertical tail, a wing and a take-off and landing device. The take-off and landing device is on the lower surface of the fuselage or the vertical tail or the wing. The take-off and landing device has a buoyancy unit and a power device, and the power device is capable of generating thrust to push the buoyancy unit to move. The take-off and landing device can be on the lower surface of the drone, and realizes the water support of the drone by symmetrically providing the take-off and landing device. At the same time, the take-off and landing device is further provided with a power device for pushing the drone to be started. The amphibious drone can take off and land by relying on the take-off and landing device, which can be disassembled to adapt to different usage conditions.

Abstract: An apparatus providing continuous tilt and variable pitch for rotors on a fixed wing VTOL aircraft. An actuator on a housing rotates a first pivot point on a motor mount to tilt a motor to horizontal and vertical positions. Simultaneously, an actuator on the motor mount rotates a fork on a second pivot point on the motor mount to adjust the pitch of the rotors attached to a free end of the motor's drive shaft. A lower swash plate on the drive shaft is attached to the fork. An upper swash plate on the drive shaft is attached to the rotors. The swash plates are attached to each other with a shaft bushing attached to a shaft ball bearing. The shaft bushing allows both swash plates to move linearly along the shaft when the fork is rotated. The shaft ball bearing allows the upper swash plate to rotate with the drive shaft while the lower swash plate remains stationary.

Abstract: A drone with vehicular control system/sensors that can share data with other vehicles and that can communicate with the cloud to provide intelligent handling of the irrigation system. The drone can be used to dispense soil additives and to inspect plants/trees on the farm.

Abstract: According to an embodiment of the disclosure, there is provided a drone control system in which the drone user may directly adjust the torque required in the flight environment, that is, the torque required by the drone motor, with the transmitter control when controlling the transmitter stick. According to an embodiment, a drone control system comprises a flight controller receiving a stick control value from a transmitter, converting the stick control value into a motor speed value, and outputting the motor speed value and an electronic speed controller receiving the motor speed value from the flight controller, converting the motor speed value into a motor torque value, converting the motor torque value into a power driving value, and outputting the power driving value to a motor.

Abstract: A method for controlling an aerial vehicle of a specific type, in particular a multirotor VTOL aerial vehicle with preferably electrically driven rotors, in which a) before a flight, a finite number of nominal trajectories (NT) for the aerial vehicle and a finite number of emergency trajectories (CT) arranged around the nominal trajectories (NT) are calculated and stored in a database available on board the aerial vehicle; b) before a flight, a finite number of type-specific admissible flying maneuvers of the aerial vehicle are pre-planned and stored in the database as a maneuver library; c) optionally before a flight, a number of discrete flight levels with different flight altitudes are defined and stored in the database; d) during a flight, the database is accessed by a computer-aided transition planning algorithm, in order, depending on a state of the aerial vehicle recorded by sensors, to change between the nominal trajectories (NT) and the emergency trajectories (CT) and also optionally between the defi

Abstract: The invention relates to a passenger module for a vehicle cabin, the passenger module comprising a first side element, a second side element, a front partition wall, and two seats arranged between the first side element and the second side element, wherein the first side element and the second side element extending parallel to each other; the seats are arranged substantially one behind another and facing substantially in a same direction; wherein the front partition wall is arranged between the seats and connects the first side element and the second side element.

Abstract: The invention relates to a passenger module for a vehicle cabin, the passenger module comprising a first side element, a second side element; and two seats arranged between the first side element and the second side element.

Abstract: The invention relates to a passenger module for a vehicle cabin, the passenger module comprising a first side element, a second side element and two seats arranged between the first side element and the second side element; wherein the first side element and the second side element extending parallel to each other; the seats are arranged substantially one behind another and facing substantially in a same direction; wherein a front seat is positioned angled by a predefined first angle around its vertical axis in a direction towards the first side element; a rear seat is positioned angled by a predefined second angle around its vertical axis in a direction towards the second side element and an aisle of the vehicle cabin.

Abstract: A seat assembly configured to be employed in vehicle seats such as aircraft passenger seats. The seat assembly includes a seat frame having first and second spaced frame members and first and second spaced transverse beams. A plurality of springs positioned proximate an aft end of the seat frame generally above the second transverse beam span between the first and second frame members. A support member is attached to the plurality of springs and to a seat back attachable to the seat frame. A cushion assembly mounts on the seat frame such that the aft end rests on the plurality of springs while the forward end rests on the front transverse beam. In use, as the aft end of the cushion assembly deflects downward toward the second transverse beam the forward end simultaneously rotates around the first transverse beam.

Abstract: An aircraft including: a wing having a leading edge; an electric motor mounted on the wing; and an electric power cable in the wing for providing power to the electric motor, wherein the electric power cable runs through a duct in the wing; the duct comprises an air inlet and an air outlet; and the electric power cable is cooled by air passing through the duct between the air inlet and the air outlet.

Abstract: A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a water separator configured to receive the compressed air from the compressor and remove moisture from the compressed air to dry the compressed air. Furthermore, the system includes a turbine configured to receive the dried air from the heat exchanger, with the dried air expanding as the dried air flows through the turbine. Moreover, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, the moisture removed from the compressed air by the water separator is routed to the defroster to melt the captured frozen particulate matter.

Abstract: A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a heat exchanger configured to receive the compressed air from the compressor and cool the compressed air; a turbine configured to receive the cooled air from the heat exchanger, with the cooled air expanding as the cooled air flows through the turbine. Furthermore, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, at least a portion of the cooled air from the heat exchanger is routed to the defroster to melt the captured frozen particulate matter.

Abstract: Sensor data that includes or more of the following: (1) aircraft state information associated with an aircraft or (2) parachute canopy state information associated with a parachute canopy is received. The parachute canopy is coupled to the aircraft at a point aft of a center of mass of the aircraft. It is determined, based at least in part on the sensor data, whether to generate a control signal associated with maneuvering the aircraft into a nose-up position. A recovery action is performed, including by deploying the parachute canopy; wherein a load on the parachute canopy is reduced in the event the aircraft is in the nose-up position compared to the aircraft being in a nose-down position.

Abstract: A battery module can include multiple cell tubes, a first conductive plate, and multiple first spacers. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The first conductive plate can include multiple first holes and electrically connect first terminals of the multiple cells. The multiple first spacers can be mounted in the multiple first holes and support the multiple tubes and the multiple cells with respect to the first conductive plate, the multiple first spacers being configured to provide thermal and electrical isolation between the multiple battery cells and the first conductive plate.

Abstract: A propulsion system for an aircraft, including at least one rotor and a nacelle cowling extending around the at least one rotor, said nacelle cowling being sectored and including at least one sector. which is fixed and sectors which are retractable in the peripheral direction relative to an axis of rotation of the rotor. The retractable sectors include at least a first series of sectors which are telescopically retractable in or on at least one fixed sector and at least a second series of sectors which are telescopically retractable in or on at least one fixed sector, the at least one fixed sector having an angular extent around the axis which is less than or equal to 90°.

Abstract: An air direction arrangement for an aircraft. The air direction arrangement contains an inlet opening and an inlet channel connected thereto and which is at least partially surrounded by an outer wall. The inlet channel is configured to guide air to an engine of the aircraft. The outer wall contains at least one outlet channel and at least one outlet element. The outlet element is configured to selectively release or close the outlet channel for an air flow from the inlet channel into the environment of the aircraft. The air direction arrangement contains a heat exchanger in the outlet channel to discharge thermal energy to the air flow which is flowing from the inlet channel into the environment of the aircraft.

Abstract: A ramjet including: a combustion area having an air inlet and an exhaust outlet; and a fuel cell in fluid communication with the air inlet and a fuel supply of the ramjet, wherein the fuel cell is in thermal communication with the combustion area.

Abstract: A docking system for drones and a method for operating the same include: a seat part configured to land a drone thereon; a wire provided on the seat part and configured to allow the landing drone to be hung on the wire so that the drone may land on the seat part; and tension adjusters configured to adjust tension of the wire so as to allow the drone to land at a target position of the seat part when the drone is hung on the wire.

Abstract: A method and apparatus for cleaning surfaces of an object. A platform may be moved along a path relative to the object using a robotic device. A liquid may be applied onto the plurality of surfaces of the object using an applicator associated with the platform. The liquid may be worked into the plurality of surfaces using a plurality of cleaning elements associated with the platform to dislodge undesired material from the plurality of surfaces. A plurality of flexible members may be moved along the plurality of surfaces to dry the plurality of surfaces and remove the undesired material from the plurality of surfaces. An airflow may be generated that moves the undesired material into a vacuum duct in a vacuum system.

Abstract: A reduced performance monitoring system for a tiltrotor aircraft includes a physical component of the tiltrotor aircraft configured to displace over time in response to an input, a simulation component configured to generate a simulated displacement response of the physical component, and a comparison module configured to compare a measured physical displacement response of the physical component to the simulated displacement response of the physical component.

Abstract: A carrier rocket system, with a carrier rocket, together with a launch assistance unit, which is detachably connected, or connectable, to the carrier rocket. The carrier rocket system is set up to take off in a horizontal launch via the launch assistance unit when thrust is generated by at least one propulsion unit of the carrier rocket. The launch assistance unit can be detached from the onward-flying carrier rocket after supersonic velocity has been reached, and is set up to fly back to the earth's surface after its detachment from the carrier rocket. The launch assistance unit preferably provides all the necessary structural supports to enable a carrier rocket that has been designed for a vertical launch to use one or more of its essential components without structural modifications. Also disclosed are a take-off method for a carrier rocket system, and a manufacturing method for a carrier rocket system.

Abstract: Disclosed is a method for task planning of a space information network based on resource interchange. The method includes: initializing basic parameters of the space information network; dividing a planning horizon into K time slots of equal length, and constructing a resource time-varying graph for the space information network; sampling a feasible resource combination space of each task, and obtaining a candidate resource combination set comprised of the resource combinations with independence greater than or equal to a threshold n; calculating a conflict relation between resource combinations, and constructing a resource combination conflict graph; obtaining a maximum independent set of the resource combination conflict graph to obtain a global planning result; and searching a neighborhood of the global planning result, and completing a local adjustment of a task planning scheme through the resource interchange, to complete the task planning based on characteristics of the resource interchange.

Abstract: A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all of the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.

Abstract: According to one embodiment a thermosealing machine is provided that includes a movable lower mold with a box formed by a box base, a box structure, and a box frame attached to the box structure. The box frame includes a frame cavity, and the lower mold includes a pad coupled to the box frame with freedom of vertical movement. The thermosealing machine includes a lower stop and an upper stop, the upper stop being operatively coupled to the pad and vertically movable with the pad. The upper stop is configured to move between an inoperative position and an operative position. In the operative position the upper stop is arranged in the path of travel of the lower stop. In the inoperative position the upper stop is arranged outside of the path of travel of the lower stop.

Abstract: A metal coil compression device includes: a lifting device configured to generate a vertically downward pressing force; a cylindrical outer pressure barrel that is supported by the lifting device; a cylindrical inner pressure barrel that is located inside a peripheral wall of the outer pressure barrel; and a connecting mechanism that connects the inner and outer pressure barrels so that the inner and outer pressure barrels are vertically engaged and are supported relatively rotatably in a circumferential direction. The outer pressure barrel has an outer recess being recessed vertically upward from a bottom end. The inner pressure barrel has an inner recess in a peripheral wall of the inner pressure barrel, the inner recess being recessed vertically upward from a bottom end, and a coil pressing surface that makes contact with a top of the metal coil to transmit the vertically downward pressing force to the metal coil.

Abstract: A device for binding rod bundles includes a tilting apparatus, a wire stripper, a binding apparatus, and a collection apparatus. The tilting apparatus includes a tilting platform, a hydraulic cylinder, and an articulated base. The wire stripper includes a main body, a first sliding mechanism, a second sliding mechanism, a first slide block, and a second slide block. The binding apparatus includes an electric clamp, a clamping frame, a sliding rail, a rail base, and a drive motor. The collection apparatus is hinged to the tilting apparatus; the wire stripper is disposed below the tilting apparatus; the tilting platform includes a hinge hole for receiving one end of the clamping frame. The collection apparatus includes a shaft hole for receiving one end of the tilting platform. The hydraulic cylinder is hinged to the articulated base and the other end of the tilting platform is hinged to the hydraulic cylinder.

Abstract: A conveyor device is provided for conveying food products in stacks or interleaved units made of a plurality of slices of cheese or meat products. The conveyor device formats the food products in a specific product format on a plurality of parallel conveyor tracks, and fills a product gap on one of the plurality of parallel conveyor tracks incoming on the input side with a food product so that on the output side all parallel conveyor tracks are supplied with the food products. At least one product sensor is configured to detect a supply of food product on each conveyor track incoming on the input side.

Abstract: A packing cell for packing products in boxes includes a picking system for picking products and stacking them according to a stacking pattern, a support unit for the stacking process, with a rotatable horizontal shaft for placing a support platform in a predetermined angular position for the stacking process, and a box handling robot to transfer empty boxes towards the support unit and full boxes away from the support unit. A method includes placing the support platform in a predetermined angular position adjacent a product picking system, picking and stacking a number of products according to a stacking pattern on the support unit, and removing from the support unit, with a box handling robot, a box containing the stacked products.