Abstract: A stepper scooter provides step pads that are connected to a laterally arranged rocker bar assembly. Vertical movement of the step pads causes the rocker bar assembly to reciprocally pivot which translates drive chains which cause rotation of the drive wheel or wheels. The rocker bar assembly comprises two four bar linkages between a center fork and each step pad. An alternate embodiment uses the rocker bar to reciprocally rotate a gear axle which drives a bevel gear arrangement to rotate the drive wheel or wheels via one-way bearings. Another embodiment incorporates a chain and sprocket drive between the bevel gear arrangement and the drive wheel or wheels, wherein the one-way bearings are replaced with a one-way sprocket drive. A stand is provided that is useful with any of the above scooter embodiments. The stand lifts the wheels of the scooter off the ground or floor by supporting a rear sprocket tube of the scooter to render the scooter effectively immobile during use.

Abstract: An electric motorcycle includes an electric motor, a motor controller for controlling the operation of the electric motor, a gearbox that can be of a used or new fuel engine-based vehicle and rotatable by the electric motor, and a main drive shaft coupled between the electric motor and the gearbox. Subject to the optimal power transmission performance of the gearbox, the electric motor is capable of producing the most appropriate driving speed in the starting state or any of a variety of travelling state, achieving optimal output efficiency and significantly reducing power consumption and enhancing endurance.

Abstract: A bicycle control device for issuing at least one command to at least one bicycle equipment comprises a body configured to be mounted on the bicycle, at least one manual actuation member associated with the body, and a clicking mechanism. The clicking mechanism comprises a magnetic clicking switch having a first element that is fixed with respect to the body, and a second element that is movable with respect to the first element and actuatable by said at least one manual actuation member when said manual actuation member issues said command.

Abstract: The invention relates to a watercraft (10) having a hull (4) and at least one float (5), which is connected to the hull (4) via at least one kinematic connection (6), wherein the kinematic connection (6) comprises a first leg (1), which is linked at one end on the hull (4) and at the other end on the float (5) and is variable in its length by a first actuator (11), characterized in that the kinematic connection (6) comprises a second leg (2), which is linked at one end on the hull (4) and at the other end on a leg (1, 3) extending between hull (4) and float (5), preferably on the first leg (1) and is variable in its length by a second actuator (12), and/or a third leg (3), which is linked at one end on the first leg (1) or on the hull (4) and at the other end on the float (5) and is variable in its length by a third actuator (13), wherein the linkage point of the first leg (1) on the float (5) is spaced apart from the linkage point of the third leg (3) on the float (5).

Abstract: Embodiments relate generally to a turret system for use in a floating vessel. The turret system may comprise a turret body and windlass subsystem. The turret system may comprise top and bottom surfaces, first and second mooring line storage sections, and first and second mooring line channel sections. Each mooring line storage section may include an opening and cavity. Each opening is operable to receive a mooring line. The first and second mooring line channel sections may be separate elongated passageways for first and second mooring lines, respectively, to be directed through the turret body and an exterior of the floating vessel without coming into contact with one another. The windlass subsystem may comprise a rotatable member, and configured to be transportable between locations. When the windlass assembly is configured to be secured to the turret body, the windlass assembly is configurable to control a movement of a mooring line.

Abstract: An LNG tank container transport ship, according to one embodiment of the present invention, which has a load space on the inside thereof, in which LNG tank containers storing liquefied natural gas are loaded, comprises: a crane which is arranged on the upper part of the load space so as to catch a container to be transported; at least one horizontal transport frame which guides the horizontal direction movement of the crane; and at least one vertical transport frame which is connected to the horizontal transport frame so as to guide the movement of the crane in the direction perpendicular to the horizontal transport frame. According to one embodiment of the present invention, there is an effect of providing a dedicated transport ship for LNG tank container transport by having therein a separate load space so as to load LNG tank containers.

Abstract: A system for automatically returning a flotation device to a user when the user becomes separated from it and is greater than some predetermined distance away. The user may have a tracking device that is operable to determine its location and transmit this information to an automatic recovery unit coupled to the flotation device. The recovery unit may be configured to activate when it is greater than the predetermined distance from the tracking device, and may be operable to propel the flotation device steering it toward the tracking device to close the distance between them.

Abstract: A portable, lightweight, removable step device mounted to a paddle board to assist animals onto the board. The device is attached to a paddle board and can be placed on a board of any size or shape. The device may be secured without requiring any alteration to the paddle board or it may be affixed with more permanent means. Additionally, the device may pivot, allowing the paddler to adjust the position of the step device to accommodate the entry angle of the approaching animal and may fold up and out of the water to reduce water resistance.

Abstract: A recreational sport boat includes a hull having starboard and port sides and a transom, a generally horizontal platform, and a pair of wake-modifying devices positioned aft of the transom. The generally horizontal platform extends aft of the transom and is configured to support a human weighing at least 100 lbs. on an upper surface thereof. The pair of wake-modifying devices are attached to the platform. One of the wake-modifying devices is positioned on a port side of the platform's centerline, and another of the wake-modifying devices is positioned on a starboard side of the platform's centerline. Each wake-modifying device is moveable between a non-deployed position and a deployed position in which the wake-modifying device is angled downwardly at an angle relative to the top surface of the generally horizontal platform.

Abstract: A watercraft lift system including one or more laterally-adjustable components and a related method are disclosed. The watercraft lift system can include a cradle assembly and optionally at least one side guide, which can be connected to the cradle assembly. The cradle assembly can include substantially parallel first and second cradle rails. One or both of the first cradle rail and the at least one side guide can be movable in a lateral direction between a wider watercraft-receiving position and a narrower watercraft-received position. In an example, lateral movement of the first cradle rail and/or the at least one side guide from the watercraft-receiving position to the watercraft-received position occurs automatically upon entry of a watercraft into the confines of the watercraft lift system. The watercraft lift system can further comprise an actuator to cause lateral movement of the first cradle rail and/or the at least one side guide.

Abstract: A need exists for a tank regulator that can reduce a pressure of more than about 4,300 psi to a much lower pressure. The present disclosure describes a piston regulator that allows for pressure to be reduced from an inlet pressure of about 5,000 psi or more to outlet pressure of about 2,000 psi or less. The regulator includes intermediate chambers to provide step-down pressures along the piston. The internal chambers enable to hold pressure differentials between the high-pressure inlet and the low-pressure outlet. The pressure in the intermediate chambers is maintained by a pressure-limiting valve to control the pressure differentials across piston seals. These seals allow the piston to actuate while maintaining a seal between the various pressure chambers.

Abstract: A pollutant reduction device and method are provided. The pollutant reduction device comprises: an exhaust gas pipe for discharging exhaust gas of a combustion engine; a cleaning water supply pipe for supplying cleaning water; a scrubber for spraying the cleaning water, which is supplied through the cleaning water supply pipe, at the exhaust gas flowing in through the exhaust gas pipe; and a cleaning water discharge pipe for discharging the cleaning water inside the scrubber and supplying the same to a ballast water tank.

Abstract: A vessel propulsion device transmits a drive force of an engine to a propulsive force generator. The vessel propulsion device includes a generator that is driven by the engine, a power shutoff detector that detects a power shutoff state in which the drive force of the engine is not transmitted to the propulsive force generator, and a controller configured or programmed to, when the power shutoff detector detects the power shutoff state, select one of a plurality of charging modes to charge a battery connected to the generator and control a target speed of the engine based on a selected one of the charging modes.

Abstract: A hydraulic system for supplying fluid to an actuator comprising a variable speed prime mover drivingly coupled to a variable displacement hydraulic pump. The system is configured to deliver hydraulic fluid via fluid conduits to an actuator. It may deliver hydraulic fluid to an actuator at a first hydraulic pressure at a first rate of pressure rise; and at a second hydraulic pressure at a second rate of pressure rise. The first hydraulic pressure may be greater than the second hydraulic pressure; and the first hydraulic rate of pressure rise may be lower than the second hydraulic rate of pressure rise.

Abstract: A locking mechanism for unmanned aerial vehicle (UAV) is provided by the present invention, includes: a motor, a base, a blade and a locking component; wherein the base comprises a mounting groove for the blade inserting in; the locking component is configured to fixedly connect the base and a rotor of the motor by passing through the base and the blade; the blade is configured to rotate freely relative to the locking component in a range of angles. The locking component of the present invention is convenient for assembly and disassembly, with a light weight and a small structure.

Abstract: The basic of my invention is to use a more powerful engine then that in current car and to modify its structure and handling. This saucer car can drive in current narrow roadway with the retractable propeller. When obstacle in front, with the new “differential”, it can diverse power vertically, in that way to convert it into a helicopter. In Case the obstacle is a lake or river, the umbrella bottom, acting as propeller too, makes the car floating and sails on water. The propellers are rotated in opposite direction in order to keep car in neutral direction.

Abstract: A control unit for controlling movement of a stabilizer and an elevator on an aircraft, the control unit comprising a processor which is configured to receive a pitch reference command from a flight control input device of the aircraft, determine, based on the pitch reference command, an elevator command configured to command the elevator in the aircraft nose-up or nose-down direction, determine a difference between the elevator command and a desired elevator value corresponding to the pitch reference command, determine a threshold value as a desired maximum elevator deflection at a given pitch reference command, compare the difference with the threshold value and in response thereto generate a command signal configured to retain a current position of the stabilizer when the difference is smaller than or equal to the threshold value, and to command the elevator in the aircraft nose-up or nose-down direction based on the pitch reference command.

Abstract: An aircraft include a landing gear is disclosed. The landing gear comprises a main strut and an inboard stay assembly connected to the aircraft fuselage such that landing gear loads can be transferred from the inboard stay assembly into the fuselage. The landing gear also comprises a sidestay connected to the wing such that landing gear loads can be transferred from the sidestay into the wing and a link assembly connected to the aircraft such that landing gear loads can be transferred via the link assembly into the aircraft. The landing gear is arranged such that, in use, when the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the aircraft via one or more of the inboard stay assembly, the sidestay and the link assembly.

Abstract: The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.

Abstract: An aircraft landing gear assembly having: a bogie beam coupled to a strut; a steerable axle mounted on the bogie beam, first and second wheel assemblies, mounted on the axle, each wheel assembly including a wheel and a brake disc attached to each wheel and arranged to rotate with the wheel; first and second brake plates mounted on the axle arranged to provide a braking force to the wheels upon contact with the first and second brake discs; a cross member coupled between the first and second brake plates; a brake rod, pivotally connected to the cross member at a first end and arranged to be attached to an anchor point on the aircraft landing gear at a second end; wherein the pivot axis of the axle and the pivot axis of the cross member are generally coaxial.

Abstract: To provide a multicopter that enables it to prevent generation of a vortex ring state of a rotor and control lift and thrust efficiently and elaborately. This is solved by a multicopter having a plurality of rotors installed radially to a frame, wherein at least one of the plurality of rotors is provided with a cylindrical duct surrounding and enclosing the rotor; and the duct is formed in a shape making an air flow from an air intake side to an air outlet side of the rotor imbalanced in a circumferential direction of the duct.

Abstract: A laminated elastomeric bearing has layers of elastomeric material and layers of metal. A tab is located on a periphery of one of the layers of metal and protrudes from the bearing. A thermoelectric device is coupled to the tab, and heat generated within the bearing during use is conducted to the tab and to the thermoelectric device, allowing for measurement of the heat.

Abstract: The invention relates to aviation, and more particularly to designs for vertical take-off and landing aircraft. The present vertical take-off and landing aircraft comprises jet propulsion units containing compressors, overflow valves, air tanks, and a nuclear power plant. Turbines are provided with hybrid engines capable of running on electricity or liquid fuel. On the outside of the aircraft, each turbine is provided with a corrugated tip, consisting of two parts: a base and an extendable part. The bases of the tips are pivotally mounted on the turbine for rotation about their own axis and are coupled to a lateral orientation system for altering the pumping direction. The other part of the corrugated tip is coupled to an angle adjusting system, which, optionally, extends one side of the corrugated part outside the body in order to alter the pumping angle by more than 90 degrees from vertical to horizontal.

Abstract: A method of recovering communication transmission function of an aerospace vehicle. In operation, a remote control center receives, from a ground-based station, a request of recovering the communication transmission function of the aerospace vehicle being in operation and not on a ground. The request includes positioning information of the aerospace vehicle. In response to the request, the remote control center sends an instruction to an unmanned aircraft vehicle (UAV) in air. The UAV functions as an electromagnetic wave transmission relay station, and the instruction includes the positioning information of the aerospace vehicle. Thus, the UAV may track the aerospace vehicle according to the instruction, and establish a two-way communication between the remote control center and the aerospace vehicle via the UAV as the electromagnetic wave transmission relay station. Thus, the remote control center may perform recovery of the communication transmission function of the aerospace vehicle via the UAV.

Abstract: A law enforcement drone system is provided. The system features an unmanned aerial vehicle, having a wireless transceiver, an airframe, a propulsion system, a navigation mechanism, a processor, a memory, a power source, and at least one fuel tank. The system also features a control system having a wireless transceiver, an input device, capable of receiving a user's input and converting the user's input to electrical signals, a processor, and a memory. The control system is in wireless communication with the vehicle such that the control system is capable of utilizing the propulsion system in substantially real-time.

Abstract: Unmanned aerial vehicles (“UAVs”) which fly to destinations (e.g., for delivering items) may land on transportation vehicles (e.g., delivery trucks, etc.) for temporary transport. An agreement with the owner of the transportation vehicles (e.g., a shipping carrier) may be made, and the associated transportation vehicles that are available for landings may be identified by markers on the roof or other identification techniques. Different types of communications may be provided as part of a landing process (e.g., a notification regarding a proposed landing may be sent including a request for a confirmation that the proposed landing is acceptable, etc.). The routes of the transportation vehicles may be known and utilized to determine locations where UAVs will land on and take off from the transportation vehicles.

Abstract: A galley system includes a galley compartment defining a cavity. The galley compartment has a door that allows access to the cavity. A galley cart is positionable in the cavity of the galley compartment that has a first opening and a second opening. An air supply and return system is coupled in flow communication with the first opening of the galley cart and the second opening of the galley compartment. A space is defined about the galley cart when the galley cart is positioned in the cavity. The space provides flow communication between the second opening of the galley cart and the second opening of the galley compartment.

Abstract: Method and apparatus for providing a modular unit through a confined entryway. The modular unit includes portions that are foldable between a transit configuration and a deployed configuration. In the transit configuration, the modular unit can fit through the confined entryway. In the deployed configuration, the modular unit may not fit through the door, but can have larger dimensions. Once past the confined entryway, the foldable portions can be quickly moved to the deployed configuration and fixed in place with a small number of pins or other fasteners. In some instances, multiple modular units may be attached together to form a larger unit. The modular units can include foldable portions, and the modular units can be connected together with a relatively small number of fasteners.

Abstract: The present invention relates to an aircraft seat arrangement that is reconfigurable between a plurality of usable configurations. The aircraft seat arrangement comprises a seat having a forward seat portion (10) and a rearward seat portion (12). The forward seat portion (10) is reconfigurable between a first configuration whereby the forward seat portion (10) is in a side by side configuration with the rearward seat portion (12), and a second configuration wherein the forward seat portion (10) is displaced to be at least partially above the rearward seat portion (12).

Abstract: The present invention relates to an aircraft seat having a seat base, a seat unit, and a floor attachment assembly, where a first side of the seat base is configured to be fastened to the seat unit, and a second side of the seat base is configured to be fastened to the floor attachment assembly, and the floor attachment assembly is configured to be mechanically connected to a floor structure of an aircraft in order to fasten the aircraft seat to the aircraft, where the seat base is formed by at least one flexurally rigid shell component, where the shell component has a cavity for receiving at least one functional element, with the cavity being closed.

Abstract: An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin includes an environmental control system having at least one pneumatic air cycle air conditioning unit, a bleed air port in the at least one thrust providing jet engine, a non thrust providing auxiliary supply unit configured to provide electricity and compressed air on ground and during flight, and at least one compressed air line. The at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit. The environmental control system is coupled with the at least one compressed air line. Further, the auxiliary supply unit is dimensioned to exclusively operate the environmental control system by delivering compressed air, and bleed air from the bleed air port is selectively providable to the environmental control system for redundancy.

Abstract: A dual primary deicing system for a rotary-wing aircraft, according to an exemplary aspect of the present disclosure includes, among other things, an electrothermal heating element system; and a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly.

Abstract: Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.

Abstract: The present invention relates to a detachable floating equipment to deploy on impact with the water and enabling stabilization of the aircraft for the prevention of the aircraft from sinking, until the surviving passengers and crew members is been rescued.

Abstract: An aircraft engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan connected to the turbine via a shaft. The fan is positioned aft of the turbine, and the shaft is at least partially disposed in a fan inlet flowpath.

Abstract: A propulsion system for an aircraft includes an engine (e.g., piston engine, or turbine) having an axis made to be nonparallel with the longitudinal axis of the aircraft. This is enabled using an electrical, hydraulic, or other system to transfer energy generated by the engine (e.g., via electrical wiring, fluid conduits, etc.) to remotely power a motor used to drive a thrust-creating device (e.g., propeller or ducted fan). That the engine is able to be freely oriented allows for it being positioned without regard to any mechanical restraints existing in conventional arrangements.

Abstract: An aircraft where an engine creates mechanical energy. That energy is then converted into another transmittable form, e.g., electrical using a generator, or hydraulic using a pump, and is delivered to remotely-located motors and thrusters, e.g., propellers at one or more locations on the aircraft. The general concept makes the engine as well as the motors used scalable to accomplish overall efficiency objectives.

Abstract: Aircraft fuel tank inerting systems and methods are provided. The aircraft fuel tank inerting systems include a fuel tank having fuel therein, an evaporator container fluidly connected to the fuel tank and arranged to receive inerting fuel from the fuel tank, the evaporator container evaporating the inerting fuel to generate a first reactant, a second reactant source arranged to supply a second reactant, and a catalyst fluidly connected to the evaporator container and arranged to receive the first reactant and the second reactant, wherein the catalyst includes a catalyst material to induce a chemical reaction between the first reactant and the second reactant to generate an inert gas, wherein the inert gas is supplied into an ullage of the fuel tank.

Abstract: A display device for displaying the attitude of an aircraft with respect to a fixed direction in space is described, said device comprising: a first element that can be fastened to the aircraft; and a second element, which is free to move with respect to the first element, following a change in position of first element with respect to the fixed direction; the second element in turn comprising: a mass, which is designed to return the second element to the same stable position with respect to the fixed direction when the first element changes its position with respect to the fixed direction; and a visual indication, which is representative of the position of the fixed direction, as the position of the first element changes.

Abstract: A method and system for creating a constellation of electronic devices for providing optical or radio-frequency operations relating to earth surface data collection applications on a predetermined geographical area. On each of a plurality of (commercial) airplanes at least one electronic device from the constellation is provided, and during its flight each airplane has a flight path over at least a portion of the geographical area. Each electronic device is configured for the operations during the flight with an earth coverage range for the operations determined by an individual airplane coverage range of a portion of the earth surface as provided by the associated airplane. One or more electronic devices are activated for the operations when the individual airplane coverage of the one or more airplanes associated with the one or more electronic devices is within the geographical area.

Abstract: A computer implemented method for managing data of a remote system includes receiving, at a processor on the remote system, fundamental data from a monitored subsystem of the remote system and/or at least one associated subsystem of the remote system as specified by a diagnostic protocol for the monitored subsystem and wirelessly transmitting the fundamental data to a remote support center that is separate from the remote system. The remote system applies additional, non-certified, logic to determine if augmented diagnostic data is desired. The method also includes wirelessly receiving a signal from the remote support center including at least one of a request for augmented data or a diagnostic protocol change command. The method also includes receiving the augmented data from the monitored subsystem and/or the at least one associated subsystem and/or at least one other subsystem of the remote system, and transmitting the augmented data to the remote support center.

Abstract: A system and method for monitoring a critical component (e.g., an electrical deicing heater) on an aircraft. A first electrical current is input into the critical component, a second electrical current is returned from the critical component, and an electrical differential current of the critical component is detected. The electrical differential current is the difference between the first electrical current and the second electrical current. An electrical differential current signal is generated from the detected electrical differential current. The electrical differential current signal is compared to a differential current threshold, and precautionary action is triggered based on the comparison. A deterioration trend of the critical component is monitored by tracking variations in the electrical differential current of the critical component over time.

Abstract: The disclosed subject matter relates to a component design system for generating aircraft component designs. The component design system includes a database having a set of rules representative for different load characteristics of different component geometries. The component design system further includes an input module for inputting user-specific load characteristics relating to an aircraft component to be generated and a processing unit for determining a variety of geometrically different aircraft component designs based on the input user-specific load characteristics and the set of rules. The disclosed subject matter also relates to an aircraft assembly system having a component design system, a method for generating aircraft component designs, a program element, and a computer-readable medium.

Abstract: A control system for a satellite comprises a power source and control system, a propulsion system having individually selectable solid fuel motors, a communication interface and an attitude determination and control system (ADCS). The ADCS receives power from the power source and control system and further receives desired orbital or positional instructions via the communication interface. Based on the desired orbital or position instructions, the ADCS generates and provides commands to the propulsion system. In turn, the propulsion system selects and fires one or more motors of the individually selectable solid fuel motors responsive to the commands received from the ADCS. A satellite may comprise the disclosed satellite control system as well as attitude control components and/or sensor components operatively connected to the satellite control system.

Abstract: A deployment system for solar panels has the panels spring loaded to deploy, but held folded against a satellite framework, held folded by trigger bars engaging slots or notches in hinge bodies holding the solar panels. A remotely-operable linear actuator moves the trigger bars to disengage the trigger bars to release the panels to deploy.

Abstract: A multi-functional composite structure has a modular design that can be altered depending on an extreme environment in which the structure will be exposed such as hazardous radiation, micro-meteoroid and orbital debris impacts, extreme temperature changes, etc. The material combinations employed in the multi-functional composite structure provide a supporting structure with low weight and maximum protection from radiation, debris impacts and temperature variations.

Abstract: Systems and methods for aseptically filling pharmaceutical containers with pharmaceutical fluid are disclosed. In one general aspect, these are based on an aseptically sealable chamber that includes a transfer wall to which pre-sealed pharmaceutical source and receiving containers are mounted aseptically. A robotic arm and a syringe store are disposed within the chamber along with a sterilizing facility for establishing in the chamber an aseptic condition. The robotic arm can grip and operate syringes to inject and/or extract pharmaceutical products from the containers by piercing their closures with the needles of the syringes.

Abstract: The present invention relates to a process for packaging a dianhydrohexitol, in the form of an aqueous solution in a container comprising a metal-based layer. It also relates to the container containing the aqueous solution of dianhydrohexitol.

Abstract: Apparatuses and methods for tamping the contents of a container are disclosed. An embodiment of an apparatus includes a tamp head for tamping the contents of the container; and a container support assembly structured and arranged to temporarily support the bottom surface of the container during tamping, the container support assembly comprising a support element having a protrusion extending upward from a substantially flat and horizontal upper surface, wherein the protrusion is sized and shaped to correspond to the size and shape of the bottom surface of the container.

Abstract: Described is a compensating device applicable on intermittent advancement packaging machines with wrapping material constituted by a film made of a flexible plastic material, for continuous compensating of a stretching of the film during drawing thereof, the machine comprising a first drawing group of the film, a mobile element able to exert a determined force on the film during advancement, the mobile element being conventionally known as a dancer and a second drawing group of the film arranged downstream of the first drawing group, where each drawing group is provided with a sensor for detecting markers located at regular intervals along the film, the compensating device being constituted by a third drawing group, located between the first and second drawing groups, the third drawing group being provided with a marker sensor, the third drawing group being provided with independent motorisation and an automatic roller opening system.