Abstract: A splash guard for a snorkel tube has an extension pipe, a pivot member pivotally mounted on the extension pipe, a space surrounded by the extension pipe and the pivot member, a float member pivotally mounted on the pivot member and located in the space, a closure member disposed on the pivot member, and a cover disposed on the extension pipe. The extension pipe has a first aperture and a second aperture in opposition. The pivot member has two pivot arms and a support portion. A pivoting limit is formed in a surface of the support portion facing the extension pipe which is selectively abutted by the float member. The closure member selectively seals the first aperture. The cover has a socket selectively engaged by the projection. The present invention can prevent inadequate sealing and has the advantages of light weight and small volume.

Abstract: A method for for assessing severity of an underwater dive includes calculating a dive severity index by: (a) determining the gas breathed by the diver; (b) measuring the dive time; (c) determining the depth profile of the dive; (d) calculating a dive severity index based on a function of steps (a), (b) and (c); and (e) assessing severity based on the dive severity index calculated in step (d), wherein the steps (a), (b), (c), (d) and (e) are carried out in real time, at each instant of the dive time of the diver, and step (d) is performed according to the formula: DSI=k1*f(GAS)*f(D)*f(T), where: DSI is the dive severity index, k1 is an arbitrary constant, f(GAS) is a function of the inhaled gas, f(D) is a function of the dive depth, and f(T) is a function of the dive time.

Abstract: Traction air device with multiple wing contours for a wind power generation plant and wind power generation plant utilizing the air device.

Abstract: A method for charging an auxiliary voltage source that provides power for at least one additional component, the additional component being in addition to an electric drive that is powered by a main voltage, is described. The method includes electrically connecting a protection and/or control circuit to the main voltage source via a DC-to-DC converter configured for power supply, and to the auxiliary voltage source via a reverse blocking valve. The method further includes electrically connecting the main voltage source to the auxiliary voltage source via a charging device. The method still further includes charging the auxiliary voltage source via the main voltage source.

Abstract: A system and method of reducing corrosion in the ballast tanks of a ship is comprised of a central inert gas manifold extending down into the furthest reaches of the ballast tank, a plurality of lateral gas distribution manifolds extending away from the central manifold, and a plurality of downwardly projecting diffusers connected to the lateral gas distributors that release the inert gas at multiple simultaneous points within the ballast tank space. A method is further presented for using the diffuser array to sparge the ballast water with the inert gas to inhibit microbiological induced corrosion.

Abstract: A structural member for an aircraft or spacecraft has at least one fiber plastic composite, the fiber plastic composite having at least one or a plurality of plies. The structural member also has at least one pre-stressing means providing internal stresses to the fiber plastic composite. The fiber plastic composite and the pre-stressing means are configured and arranged to form a balanced system the internal stresses of which are essentially balanced to zero in a cured state of the said system. The balanced system of the structural member is able to counteract loading stresses exerted to the airframe in service such, that a damage caused by the loading stress is easily detectable visually.

Abstract: A moisture control assembly for use with a support beam extending through an insulation layer is provided. The insulation layer is positioned between an outer wall and an inner wall. The assembly includes: a moisture path close-out structure coupled to the insulation layer at an aperture defined through the insulation layer, the moisture path close-out structure including an opening substantially aligned with the aperture and configured to receive the support beam therethrough; and a coupling mechanism configured to secure the moisture path close-out structure to the support beam such that the moisture path close-out structure is partially pulled away from the insulation layer, the coupling mechanism and the moisture path close-out structure configured to direct liquid flow down and away from the support beam and along the insulation layer.

Abstract: A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.

Abstract: Protective covers (e.g., “liners”) for use in protecting aircraft cargo hold floors from potentially harmful or dangerous fluids and other substances, and from physical damage, are described herein. In some embodiments, the cargo pit liners described herein can include a plurality of raised portions and adjacent recesses that provide a protective barrier between cargo and a floor of the cargo pit. The raised portions can facilitate movement of cargo and improve impact resistance, and the recesses can collect and retain potentially detrimental fluids.

Abstract: A propeller for an aircraft having a fuselage and a pair of fixed wings includes a mounting member secured to at least one wing. At least one blade is rotatably connected to each mounting member and has an airfoil shape. The at least one blade is in a locked condition during take-off and landing of the aircraft extending parallel to a leading edge of the wing and in an unlocked, rotating condition during flight for propelling the aircraft.

Abstract: A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

Abstract: Describes a deflection mechanism of the flap panels of an aircraft, the aforesaid deflection mechanism being connected to a wing of an aircraft by means of a first fixed structure and to the flap panels by linkage points, in order to support and deflect the flap panels in desired positions, the deflection mechanism of the flap panels of an aircraft comprises of a set of moving hinged links pivotally connected with each other and linked to a first fixed structure, and a hinged drive link connected to the flap panel and to a second fixed structure, the set of moving hinged links being linked to the flap panel by at least one linkage point in order to pivot jointly the moving hinged links deploying the flap panels in an initially predominantly rectilinear and subsequently deflected trajectory and at the same time aligned with a longitudinal direction of the aircraft, without the use of tracks and rollers, the hinged drive link being pivoted from the movement of the flap panels by the set of moving hinged links.

Abstract: A fluidic actuator for influencing a flow of a surrounding fluid along a flow surface has a blowing duct for connecting to a pressurized-fluid source, and has a surface blowing opening formed in the flow surface, and a suction duct for connecting to a surface suction opening formed in the flow surface, wherein the suction duct flows into the blowing duct at an entrainment opening.

Abstract: A landing gear lock assembly includes a first lock link, and a second lock link, a first end of the second lock link being rotatably coupled to the second end of the first lock link so that the first and second lock links unfold relative to each other in a first rotation direction. A toggle lock mechanism has a crank link and a toggle link rotatably coupled to each other, the toggle link being rotatably coupled to the second lock link, and the crank link being rotatably coupled to the first lock link so that the toggle link rotates relative to the second lock link, in a direction opposite the first rotation direction, to rotate the second lock link to a fully extended position relative to the first lock link. Rotation of the toggle link mechanically locks the second lock link in the fully extended position.

Abstract: Off-board gyrocopter take-off systems and associated methods are disclosed. A representative method includes restraining a gyrocopter from vertical and lateral movement, pre-rotating a fixed-pitch lift rotor of the gyrocopter via a power source located off the gyrocopter, and releasing the gyrocopter for vertical movement to allow the gyrocopter to lift under a force provided by the lift rotor. Optionally, the method can further include interrupting or reducing power from the power source to the gyrocopter as a way to release the gyrocopter for vertical movement.

Abstract: To provide an unmanned rotorcraft and a method for measuring a distance to a circumjacent objet around the rotorcraft, enabling it to prevent its airframe from colliding with a circumjacent object when flying and prevent its airframe from falling down when landing, while suppressing an increase in airframe cost. This is solved by an unmanned rotorcraft including a distance sensor to measure a distance between its airframe and a circumjacent object around it, the distance sensor and its detection direction being fixed to the airframe, and a method for measuring a distance to a circumjacent objet around the rotorcraft, adapted to watch or watch out for a circumjacent object around the airframe by turning the airframe automatically in a yaw direction under predefined conditions or to measure a difference of elevation at landing points of all legs of the airframe.

Abstract: An aerial vehicle includes a body having a center and a number of spatially separated thrusters. The spatially separated thrusters are statically coupled to the body at locations around the center of the body and are configured to emit thrust along a number of thrust vectors. The thrust vectors have a number of different directions with each thruster configured to emit thrust along a different one of the thrust vectors. One or more of the thrust vectors have a component in a direction toward the center of the body or away from the center of the body.

Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

Abstract: A system and method for controlling an altitude loss of an aircraft in response to a power loss event, includes obtaining at least one aircraft condition from at least one sensor, determining a present aircraft energy state of the aircraft from the at least one aircraft condition via an energy analysis unit, wherein the present aircraft energy state includes an aircraft potential energy and at least one of an aircraft kinetic energy and a rotor rotational kinetic energy, calculating a flight path to partially utilize at least one of the aircraft kinetic energy and the rotor rotational kinetic energy to initiate an autorotation state of the aircraft via a flight path controller, wherein the flight path controller minimizes an aircraft potential energy loss associated with the flight path, and initiating the autorotation state of the aircraft via the flight path.

Abstract: An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a hybrid electric propulsion system having a port propulsor and a starboard propulsor, with the port and starboard propulsors attached to the wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position. The hybrid electric propulsion system additionally includes an electric power source including a combustion engine and an electric generator, with the electric generator being driven by the combustion engine. The electric generator is in electrical communication with each of the port and starboard propulsors for powering the port and starboard propulsors.

Abstract: An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.

Abstract: An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a first primary thrust propulsor and a first secondary thrust propulsor, the first primary thrust propulsor being different than the first secondary thrust propulsor. Both the first primary thrust propulsor and the first secondary thrust propulsor are mounted to the same one of: a starboard side of the aft wing assembly, a port side of the aft wing assembly, a starboard side of the forward wing assembly, or a port side of the forward wing assembly.

Abstract: An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a propulsion system having a port propulsor and a starboard propulsor. The port and starboard propulsors are each attached to the wing assembly on opposing sides of the fuselage and are rotatable between a forward thrust position and a vertical thrust position. The propulsion system also includes a supplemental propulsor mounted to the fuselage to provide certain efficiencies for the aircraft.

Abstract: A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.

Abstract: Disclosed is a submarine and flying automobile including a submarine-shaped automobile body, a waterjet installed inside the automobile body, a gas turbine engine installed inside the automobile body, a pair of tandem rotors installed at a predetermined interval at a top of the automobile body, a bow trim tank and a stern trim tank which are installed at front and rear portions of an inside of the automobile body, a pair of trim lines configured to connect the bow trim tank and the stern trim tank, and a tail wing propelling part engaged to a rear portion of the automobile body.

Abstract: A navigation termination system of an unmanned vehicle (UV) is provided. The system includes a plurality of sensors connected to the UV and configured to detect motion of the UV; a power supply configured to power the movement of the UV; a processing circuitry; and a memory, the memory containing instructions that, when executed by the processing circuitry, configure the system to: determine, based on sensory signals captured by the plurality of sensors, a navigation termination event; and disrupt a connection between the power supply and a motion mechanism of the UV when the navigation termination event occurs.

Abstract: The present invention provides a safety link assembly for use with an aerial delivery apparatus, the assembly comprising a main body, an ejectable connector, a retaining mechanism comprising a retaining lever rotatably mounted on a rotary axis on the main body and rotatable between a first retaining position, and a second releasing position, and a securing mechanism comprising a securing member moveable between a first securing position, and a second non-securing position, wherein the distance from the first region of the retaining lever to the rotary axis is less than the distance from the second region of the retaining lever to the rotary axis. The invention also provides methods of performing an aerial delivery from an aircraft.

Abstract: In some embodiments, methods and systems of dispensing an insecticide to defend a crop-containing area against crop-damaging pests include an unmanned vehicle having a sensor that detects a crop-damaging pest in the crop-containing area and captures pest detection data, and an insecticide output device including at least one insecticide directed at the pest. The unmanned vehicle transmits the captured pest detection data via the network to the computing device and, in response to receipt of the captured pest detection data via the network from the unmanned vehicle, the computing device accesses an electronic database to determine an identity of the at least one pest. Based on the determined identity of the crop-damaging pest, the computing device transmits a control signal to the unmanned vehicle to cause the insecticide output device of the unmanned vehicle to dispense one or more insecticides specific to the identified crop-damaging pest.

Abstract: A method, system, and/or computer program product ameliorates mosquito populations. A flying drone is deployed over an area. Sensor readings that identify a presence of water in the area are received, and one or more processors determine a confidence level L that the water in the area is stagnant water. The flying drone is then directed to perform an amelioration action against the mosquito larvae based a value of the determined confidence level L.

Abstract: In some embodiments, methods and systems of pollinating crops include one or more unmanned vehicles including a pollen applicator configured to collect pollen from a flower of a first crop and to apply the pollen collected from the flower of the first crop onto a flower of a second crop and a sensor configured to detect presence of the pollen applied to the flower of the second crop by the pollen applicator to verify that the pollen collected from the flower of the first crop by the pollen applicator was successfully applied by the pollen applicator onto the flower of the second crop.

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

Abstract: Side-facing belted aircraft seats include a tactile signaling unit to induce movement of the seat occupant. For such purpose, the signaling unit may be provided with a signaling lid covering a female buckle of a lap belt restraint assembly. The signaling lid is moveable between a closed position wherein engagement of a male tab of the lap belt with the female buckle is precluded and an open position wherein engagement of the male tab with the female buckle is allowed. The signaling lid thereby provides tactile stimulation when in the open position thereof to induce the seated occupant to shift on the cushioned seat so that a midsaggital plane of the occupant is aligned with an offset plane of the seat that is offset by a predetermined distance toward one side of the seat relative to a midplane of the seat.

Abstract: An air conditioning system for an aircraft regulates the extracted engine bleed airflow by assessing a plurality of parameters that indicate the actual aircraft operating conditions, external environment and system performance capabilities, aiming at substantially reducing the demand of extracted engine bleed air (fuel consumption reduction) and concurrently complying with pressurization, ventilation and thermal load requirements. The ECS airflow is optimized based on the aircraft operating conditions and external environment. Then, ECS airflow is further optimized based system performance capabilities by fixing the air conditioning system outlet temperature to lower or higher values and then regulating the ECS airflow through the flow control valve to still meet the thermodynamic performance required to properly maintain the aircraft cabin environment.

Abstract: An apparatus and method for deicing a surface upon which ice accumulates, on for example an aircraft wing. The apparatus and method for the deicing module include an actuating component, a casing, and a movable member. The movable member breaks ice that has accumulated on a surface of the wing.

Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a base member, and a retaining member at least partially defining a first aperture and a cavity. The pivot is configured to extend at least partially into the first aperture. The cavity is configured to accommodate a portion of the link arm.

Abstract: A control system for a gas turbine engine includes a processing system operable to control a speed of the gas turbine engine and a memory system. The memory system is operable to store instructions executable by the processing system to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally adjust an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit according to the at least one performance parameter.

Abstract: A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

Abstract: Systems, apparatus, and methods may control movement of an object through a fluid. The systems, apparatus, and methods may utilize one or more rotatable control units, each including a plurality of control fins to generate a force at least partially perpendicular to a direction of travel of the object through the fluid.

Abstract: Systems and methods for lightning strike materials are disclosed. The material may include a carbon fiber tow. Carbon nanotubes may be grown on carbon fibers within the carbon fiber tow. The carbon nanotubes may cause the carbon fibers to separate, decreasing a carbon tow fiber volume fraction of the tow. The growth of the carbon nanotubes may be controlled to select a tow fiber volume fraction of the tow. The lightning strike material may transmit electricity to decrease damage to the composite structure in case of a lightning strike.

Abstract: An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV.

Abstract: A multi-stage, intercooled centrifugal compressor with integral power generator system for a mobile, ground-based aviation support cart is disclosed. A bootstrap-type turbo compressor module which can supply cooled air. The system may be operated in one of several modes: high pressure “bleed air” (e.g., 35-50 psig) for jet engine start, conditioned or cooled air (e.g., 2-5 psig) for aircraft cooling purposes, or electrical ground power. Electrical ground power and conditioned air may also be supplied simultaneously if desired.

Abstract: Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

Abstract: Systems and methods for high-speed non-destructive inspection of a half- or full-barrel-shaped workpiece, such as a barrel-shaped section of an aircraft fuselage. Such workpieces can be scanned externally using a mobile (e.g., translating) arch gantry system comprising a translatable arch frame disposed outside the fuselage section, a carriage that can travel along a curved track carried by the arch frame, a radially inward-extending telescopic arm having a proximal end fixedly coupled to the carriage, and an NDI sensor unit coupled to a distal end of the telescoping arm. The stiffeners of the fuselage sections can be scanned using a mobile scanner platform disposed inside the fuselage section, which platform comprises a radially outward-extending telescopic arm rotatably coupled to a mobile (e.g., holonomic or linear motion) platform and an NDI sensor unit coupled to a distal end of the telescoping arm.

Abstract: A vertically oriented barrier filling assembly for filling barrier tubing with a filling material and coiling filled barriers is disclosed. The barrier filling assembly includes a barrier filling device positioned above a barrier receiving device. The barrier filling device includes a coiler hopper that funnels the filling material to a barrel. An auger situated in the barrel includes a shaft and a fighting, with rotation of the auger feeding the filling material to empty barrier tubing attached to the barrel. Filled barriers are coiled on a vertically adjustable floor of the barrier receiving device as the barrier tubing is filled by moving the coiler hopper and/or the barrel in an orbital path. A system for filling and coiling barriers includes a supply hopper, the assembly, a processing station, and one or more conveyors, the system having a process flow from the storage hopper to the assembly to the processing station.

Abstract: An apparatus for filling a container with a flowable product from a product supply includes a filling station that receives the flowable product from the product supply. The filling station includes (i) a line through which the flowable product flows between the product supply and the container, (ii) a fill valve that is configured to selectively control flow of the flowable product within the line, and (iii) a capacitive sensor configured so that during a filling operation the capacitive sensor is operable to sense, through the container, when the flowable product reaches a predetermined fill level within the container. The capacitive sensor is positioned outside and spaced apart from the container during the filling operation. Additionally, at least a portion of the capacitive sensor is positioned below a mouth of the container being filled during the filling operation.

Abstract: A medicine packaging apparatus 10 has a packaging paper supplying part 42; a sealing device 50 for forming a packaging bag; a medicine introducing part 80 for introducing the medicines M from an opening portion of the packaging bag P in an unsealed-state; a detecting part 90 for detecting presence of the medicines M in an introducing path for the medicines M by the medicine introducing part 80 and a determining part which can determine that a packaging failure occurs under a condition that the presence of the medicines M is detected by the detecting part 90 within a time period after a timing of starting to seal the packaging bag P in which the medicines M have been introduced and before a timing of introducing the medicines M to be packaged in a subsequent packaging bag P through the medicine introducing part 80.

Abstract: The present invention concerns a device and method for reefing a portion of tubular film, the reefing device having at least one reefing finger and at least one drive unit. The drive unit has advancing means, which, for reefing the portion of tubular film, is brought into operative connection with the reefing finger at least at the height of a point of engagement, while enclosing the portion of tubular film, and moves the portion of tubular film in relation to the reefing finger. The device according to the invention and the method according to the invention are distinguished in particular in that the position of the at least one point of engagement can be changed along the reefing finger as reefing progresses or the position of the point of engagement on the reefing finger is changed.

Abstract: Methods and packages for storing film strips while reducing or eliminating stress cracking during storage, including use of packages having an inner surface made from polymeric materials exhibiting various physical properties and including films and pouches that are annealed.

Abstract: The present invention has been made in an effort to more assuredly substitute oxygen in a vial. A gas substitution apparatus according to the exemplary embodiment of the present invention includes: a first gas substitution unit which seals a periphery of an opening of a vial disposed in a gas substitution section, and guides a flow of a first substitution gas to be supplied into the vial; and a second gas substitution unit which is coupled to an upper side of the first gas substitution unit, and guides a flow of a second substitution gas to be supplied directly into the vial.

Abstract: The invention relates to a container handling machine (1) having at least one operative unit (18) comprising first support means (21) to support a base (12) of a filled and closed container (3), second support means (24) cooperating with an end (17) of the container (3) opposite the base (12), a plunger (31) selectively moved along its axis (E) to perform a deformation operation on the base (12) of the container (3) from a first swollen configuration to a second inwardly-retracted configuration, and actuator means (35) selectively activated to move the plunger (31) along its axis (E) between a first position, detached from the base (12) of the container (3), and a second position, in which the plunger (31) defines the second configuration of the base (12); the machine (1) further comprises a control unit (41) configured to selectively activate the actuator means (35) for moving the plunger (31) along its axis (E); the second support means (24) are maintained at a constant distance from the first support means