Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a speed control mode, where a speed of the rotorcraft is proportional to a pilot control command; detecting a high longitudinal acceleration condition; upon detection of the high longitudinal acceleration condition, temporarily disabling the speed control mode and stabilizing the rotorcraft while the speed control mode is disabled; and reestablishing the speed control mode when a measured longitudinal acceleration of the rotorcraft falls below a first threshold.

Abstract: A force sensing element is used in a pressure transducer. The force sensing element includes a flat, disc-type spring having a unitary body that circumscribes a central axis, and a plurality of spirals that are continuous with each other and extend radially outwardly from the central axis. The plurality of spirals includes nested symmetrical flights having walls with a non-uniform thickness, and the disc spring is uniformly deflectable along the central axis in response to force acting on the disc-type spring. The spring is configured to have a high accuracy and a high fatigue life such that the spring is suitable for use in high-pressure applications that may require repeatability while operating with over 10 million cycles of unidirectional or bi-directional axial loading.

Abstract: A hard-landing detection system includes a wheel assembly, a shock strut mechanically coupled to the wheel assembly and to landing gear structure of the landing gear assembly, a controller having a processor, and a tangible, non-transitory memory configured to communicate with the processor. The tangible, non-transitory memory has instructions stored thereon that, in response to execution by the processor, cause the hard-landing detection system to perform operations that include detecting, by the processor, a landing event and determining, by the processor, whether the landing event is hard. The hard-landing system may further include a stroke position sensor and detecting the landing event may include using the stroke position sensor to measure a stroke profile of the shock strut. Further, determining whether the landing event is hard may include comparing, by the processor, the stroke profile of the shock strut to a predetermined maximum shock strut stroke.

Abstract: Systems and methods for tuning power transmission circuits may sweep a power frequency applied to a transmission coil across a plurality of frequencies. The transmission coil may be inductively coupled to a receiving coil and separated from the receiving coil by an air gap. A current and/or voltage at the transmission coil may be measured in response to the power frequency being at each frequency of the plurality of frequencies. A transmission frequency may be selected based at least in part on the measured current and/or the measured voltage.

Abstract: In one embodiment, an apparatus may comprise a rotor blade. The rotor blade may comprise a plurality of blade segments; one or more attachment fittings for coupling the plurality of blade segments; and one or more actuators for adjusting an orientation of the plurality of blade segments.

Abstract: A gearbox system includes a first drive gear rotatable about an axis of rotation and a second drive gear disposed coaxial with the first drive gear and rotatable about the axis of rotation. An input shaft provides a first torque and includes an input gear. Driving pinions are operably connected to the input gear and positioned between the first drive gear and the second drive gear compliantly along a direction parallel to the axis of rotation. Each driving pinion drives the first drive gear in a first direction about the axis of rotation and drives the second drive gear in a second direction opposite the first direction about the axis of rotation. Each driving pinion transfers an equal second torque to the first drive gear and the second drive gear.

Abstract: The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

Abstract: The unmanned flying body is provided with a gas detector, a distance meter, and an altitude controller. The gas detector emits diagonally downward to the forward side in a moving direction of the unmanned flying body a detecting light frequency-modulated by a predetermined modulation frequency setting a predetermined frequency as a central frequency. The gas detector receives the light, returned from a measurement target to which the detecting light is emitted (an area on a pipe member for transferring gas, irradiated with the detecting light), as first light. The measurement target is checked for gas leakage based on the received first light. The distance meter measures the distance between the gas detector and the measurement target. The altitude controller controls the flight altitude of the unmanned flying body based on the measured distance.

Abstract: A moving body identification system for identifying moving bodies, whereby: moving state information is acquired, including first position information of multiple moving bodies which are detected by a moving state monitoring device monitoring moving states of the moving bodies; predetermined report information is acquired from the moving bodies, including second position information of the moving bodies measured by themselves; and registration statuses of the moving bodies are identified on the basis of the first position information and the second position information.

Abstract: Disclosed herein is a booster aircraft system having a host aircraft and one or more booster UAVs coupled thereto. When necessary, such as during takeoff and climb of the host aircraft, the booster UAVs operate to boost the thrust of the host aircraft. The booster UAVs are configured to detach from the host aircraft when no longer needed (e.g., at cruising altitude/speed), thus removing their weight from the host aircraft. Each booster UAV includes wings, one or more propulsors, a control system, and landing gear, which enable the booster UAV to return autonomously to a predetermined location once detached from the host aircraft to be refueled and reused.

Abstract: A tandem wing aircraft having a fore wing, an aft wing, and a middle wing, attached relative to the aircraft and each other such that the middle wing provides a substantial portion of the total lift at landing speeds, and a minimal portion of the total lift at cruise speeds. At cruise speeds, induced drag is minimized, permitting higher speeds, greater fuel efficiency, and/or greater payload. Advantageously, the wing loading at cruise speeds is higher providing better passenger comfort while still providing controllability and safety at landing speeds.

Abstract: Embodiments described herein may help to provide medical support via a fleet of unmanned aerial vehicles (UAVs). An illustrative UAV may include a housing, a payload, a line-deployment mechanism coupled to the housing and a line, and a payload-release mechanism that couples the line to the payload, wherein the payload-release mechanism is configured to release the payload from the line. The UAV may further include a control system configured to determine that the UAV is located at or near a delivery location and responsively: operate the line-deployment mechanism according to a variable deployment-rate profile to lower the payload to or near to the ground, determine that the payload is touching or is within a threshold distance from the ground, and responsively operate the payload-release mechanism to release the payload from the line.

Abstract: A lock assembly includes a pawl body having first restraint surface and a second restraint surface, wherein the pawl body rotates between an extended position and a retracted position, an inner pawl rotatably coupled to the pawl body, wherein the inner pawl is rotated away from the second restraint surface in the retracted position of the pawl body, and a biasing member associated with the inner pawl, wherein the biasing member urges the inner pawl to be aligned with the second restraint surface in the extended position of the pawl body.

Abstract: A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. Provision is made on at least one of the wall parts for a fixing section which is overlapped by the floor panel. Also described is an aircraft which features such a cabin monument.

Abstract: A galley monument has at least one galley element and at least one charging station integrated in a slide-in compartment in the galley monument for charging electrical energy storage of personal electronic devices. The charging station has a locking element having a locking mechanism. The locking mechanism is equipped with an emergency intervention mechanism for opening the locking element in emergency situations.

Abstract: An implementation of a contoured class divider for dividing an aircraft cabin includes a panel positioned between an aft seat and a forward seat, the panel having an aft-facing convex contour closely matching an aft-facing contour of a seatback of the forward seat and configured to enhance space utilization. The contoured class divider may include an articulation system to articulate at least a portion of the panel from a first position (normal operation) to a second position (emergency landing). The contoured class divider may provide up to an additional 12 inches of space which can be used to reduce seat pitch (and thereby enhance passenger comfort) or increase the number of rows of seats on a given aircraft.

Abstract: An energy absorbing backshell including a non-metallic core, a non-metallic casing surrounding the non-metallic core, a tube on the top surface of the non-metallic core and non-metallic casing.

Abstract: An energy absorbing assembly includes an attachment component configured to be coupled to a mounting structure. The energy absorbing assembly also includes an anchor that has a tip portion, a shaft, and a head. The anchor is configured to extend through the attachment component such that the head is disposed on a first side of the attachment component and the tip portion is disposed on a second side of the attachment component and is configured to be coupled to the mounting structure. The energy absorbing assembly also includes a deformable member configured to be positioned concentrically around the shaft of the anchor. The deformable member is configured to be retained between the first side of the attachment component and the head of the anchor.

Abstract: A method of making a support arm includes heating a mold to a glass transition temperature of a thermoplastic material; injecting the thermoplastic material comprising a filler into the mold and allowing the thermoplastic material to conform to the mold; cooling the mold to an ejection temperature to form the support arm; and ejecting the support arm from the mold; wherein a cross-section of the support arm taken along a line from an inner edge to an outer edge of the support arm comprises a first “U” shaped portion and a second “U” shaped portion.

Abstract: An adapter rail system for mounting objects to a floor rail in a transportation means includes an elongate adapter rail element, an arresting element and a movement rail element. The adapter rail element has a surface contour having regularly consecutively arranged neckings and widenings, which surface contour corresponds to an opening contour of a floor rail, which includes regularly consecutively arranged grid openings, which are penetrated by a slit. The adapter rail element has protrusions extending perpendicular to the plane spanned by the surface contour and are each arranged in the region of a necking. The arresting element has a surface contour corresponding to the opening contour of at least one grid opening. The arresting element is dimensioned to be flush between two adjacent protrusions of the adapter rail element onto the adapter rail element. The movement rail element is connectable with the protrusions of the adapter rail element.

Abstract: The invention relates to a canopy, in particular for a paraglider, parachute, flexkite, or surfkite, comprising an upper sail and a lower sail as well as profile-forming ribs, characterized in that at least two different zones are formed in the canopy that have different opening and emptying times.

Abstract: The invention seeks to get around the problems of mass and complexity of pylons made up of assembled box sections. In order to do so, the invention effectively proposes organizing the engine-wing interface around a substantially uniform framework configured to incorporate the multiple functions (transmission, safety) and house the pylon equipment (extinguishers, heat exchanger etc.). This framework forms a structural assembly capable of transmitting load and of forming an aerodynamic fairing suited to this framework. A pylon according to the invention comprises a single structural and multifunctional framework (10) made up of main canals (11; 11a to 11e) housing equipment and transmission systems (41a to 41c) between the engine and the wing structure, and a latticework (20) of arms (12) and of nodes (13) connecting the arms together.

Abstract: The present disclosure provides a method and a system for controlling operation of an engine of an aircraft. A first engine power limit associated with a thrust limit for a propeller coupled to the engine is obtained. The first engine power limit is compared to a second engine power limit associated with a mechanical limit for the engine and to a third engine power limit associated with a thermal limit for the engine. A maximum engine power limit is set at a lowest value of the first, second, and third engine power limits.

Abstract: A power demand anticipation system for a rotorcraft includes an engine subsystem having an engine with a power output. The power demand anticipation system also includes one or more sensors including a cyclic control sensor. The one or more sensors are operable to detect one or more flight parameters of the rotorcraft to form sensor data including a cyclic control position. A power demand anticipation module is in data communication with the engine subsystem and the one or more sensors. The power demand anticipation module is operable to anticipate a power demand of the engine using the sensor data to form a power demand anticipation signal. The engine subsystem is operable to adjust the power output of the engine based on the power demand anticipation signal received from the power demand anticipation module.

Abstract: Fuel tank inerting and fire suppression systems and methods for an aircraft are provided. The systems include a fuel tank, a first reactant source fluidly connected to the fuel tank, the first source arranged to receive fuel from the fuel tank, a second reactant source, a catalytic reactor arranged to receive a first reactant from the first source and a second reactant from the second source to generate an inert gas that is supplied to the fuel tank to fill a ullage space of the fuel tank, and a fire suppression inert gas supply system arranged to direct the inert gas to a fire suppression system, wherein the fire suppression inert gas supply system includes a fire suppression inert gas supply controller to control a flow of inert gas to the fuel tank and the fire suppression system.

Abstract: A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

Abstract: A method for policing and managing the operation of a flying, unmanned aircraft in the event of usurpation of control of, malfunction of, or ill-intentioned use of, this aircraft includes the steps of (a) detecting inappropriate operation of the aircraft; (b) transmitting a takeover command to the aircraft to interrupt control of the operation of this aircraft by a first pilot and relinquish control of the aircraft to a second pilot; and (c) transmitting control commands to the aircraft to control its operation by the second pilot, until the need for alternate pilot control of the aircraft has ended or until the aircraft has landed safely.

Abstract: Fire- and electromagnetic interference (EMI)-resistant aircraft components and methods for manufacturing the same are provided. A fire-and EMI-resistant aircraft component includes an article comprised of a polymeric material. A fire-retardant material layer overlies the article. A thermally and electrically conductive coating material layer is disposed intermediate the article and the fire-retardant material layer. Optionally, at least one continuous electrically conductive element is integrated with the polymeric material of the article.

Abstract: A method that recommends capturing a stream of images of the landing zone, using a first imaging system to calculate position information for the landing zone on the basis of at least one real image of the stream, using an autopilot system to determine a current position of the landing zone at the current calculation instant, using a second imaging system to verify the presence of a landing zone at the current position in the real image, and generating an alarm if the presence is not found.

Abstract: An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

Abstract: A satellite propelled by laser ablation comprises: a device for managing the attitude and the orbit of the satellite; a device for capturing and potentially for processing the target spaceborne body; a device for external communication; a laser ablation propulsion device comprising one or more lasers and a module for managing the one or more lasers that is suitable for determining the one or more laser beams to be generated on the captured target spaceborne body according to the movement desired for the satellite; and a device for visually inspecting the target spaceborne body.

Abstract: Systems, methods, and apparatus for dual condenser loop heat pipes for satellites with sun-normal radiators are disclosed. In one or more embodiments, a disclosed method for a satellite thermal management system comprises heating, in an evaporator, a liquid to convert the liquid to a vapor. The method further comprises passively circulating within tubing, from the evaporator, the vapor to a first radiator not illuminated by a sun and to a second radiator illuminated by the sun. Also, the method comprises converting the vapor to the liquid when the vapor is within the first radiator not illuminated by the sun. Further, the method comprises passively circulating within the tubing, from the first radiator not illuminated by the sun, the liquid to the evaporator.

Abstract: A system for transferring a particulate material from a first container to a second container including an upper portion, a lower portion and a sieve. The upper portion having a housing and a high frequency vibrator, the housing having a first end, a second end opposite the first end, and a gasket positioned adjacent the first end. The lower portion having a collector funnel, a low frequency vibrator and a collar securing the low frequency vibrator to the collector funnel. The sieve having a mesh size, a perimeter and a gasket positioned adjacent the perimeter. The upper portion is releasably secured to the first container and the sieve is releasably secured between the second end of the upper portion and the lower portion.

Abstract: Shown and described is a device for the drying of packaging, in particular composite packaging for foodstuffs, including: a conveyor belt with cells for receiving the packaging, and at least one drying facility for drying the packaging. In order to achieve particularly efficient drying of the packaging, it is envisaged that the drying facility has at least one contact element with at least one contact surface. Also shown and described are the use of such a device for the drying of packaging filled with foodstuffs, a method for drying packaging, and a packaging for foodstuffs.

Abstract: The invention relates to a folding device (10) for transporting an outer cardboard package (20) having folding lines and for folding at least one side flap (21) of the outer cardboard package (20). The folding device (10) comprises at least one conveyor system with a guiding unit (11) and with at least two transporting units (30) disposed on the guiding unit (11) for the transport of the outer cardboard packages (20) in a transport direction (TR). The at least two transporting units (30) are disposed in a row at the conveyor system and are transported in transport direction (TR) through and/or by the conveyor system. Each transporting unit (30) comprises an own, individually controllable drive (32) and further at least one folding unit (35) for folding over at least one side flap (21) of an outer cardboard package (20).

Abstract: The invention relates to improvements in or relating to the packaging of food 36 between a first plastic film 16 and a second plastic film 18 using a packaging apparatus 10. A tray 24 is formed from the first plastic film 16, the tray having a floor 33 with at least one channel 32. An absorbent pad 34 is provided on the floor 33 of the tray 24. A portion of food 36 is provided on the floor 33 of the tray 24. The second plastic film 18 is placed on the tray 24 to sandwich the absorbent pad 34 and the portion of food 36 between the plastic films 16, 18. The packaging apparatus 10 is operated to urge the two plastic films 16, 18 together and to create a seal therebetween. At least one duct 76 is formed between said at least one channel 32 and at least one of the second plastic film 18, the absorbent pad 34, and the portion of food 36.

Abstract: A packaged unit includes a cluster of products and a shrink film that secures the products to each other. The shrink film is wrapped around the cluster, thereby forming a lateral opening that would otherwise result in a shrink eye. A closure formed by placing a portion of the shrink film against the cluster at in the region of the lateral opening forms a closed surface with overlapping fold regions of the shrink film, thus avoiding the shrink eye.

Abstract: A cable tie tensioner includes a first plate body and a second plate body. The first plate body includes a first pivot portion, a first operation handle, and a cutting member. The second plate body includes a second pivot portion and a second operation handle corresponding to the first pivot portion and the first operation handle. The second plate body is provided with a pressing member. When in use, a tie section of a cable tie is inserted through the pressing member, the second operation handle is operated to move toward the first operation handle, and the pressing member clamps the excessive tie section of the cable tie to be pulled so that an article can be tied up. After the article is tightened, the cutting member is used to cut off the excessive tie section of the cable tie.

Abstract: A conveyor and packaging system includes an upstream conveyor that transports stacks biscuits in a plurality of lanes into buckets of a bucket conveyor. The bucket conveyor transports the buckets in a direction perpendicular to the length of the buckets to a packaging area, where transfer devices transfer the biscuit stacks to an input of a packaging machine. The transfer device can transfer the stacks without use of an intermediary conveyor.

Abstract: The invention provides a method for assembling a dispensing system (1) for dispensing a fluid medium under pressure, the method including: providing a valve cup (10) including a valve (50) and a bag (100), the valve (50) configured to attach to an opening of the bag (100), wherein the valve cup (10) is either formed from a first plastic or includes a lining (70) formed from the first plastic; inserting the valve (50) into the opening of the bag (100) and fluidly sealing the bag (100) to the valve (50); providing a container (30), the container (30) including an opening (32) and suitable for storing a fluid medium under pressure and formed, at least in part, from a second plastic; inserting the bag (100) into the container (30) and positioning the valve cup (10) at the opening (32) of the container (30); pressurising the internal volume of the container (30); and welding the valve cup (10) to the container (30) to thereby provide a seal between the valve cup (10) and the opening (32) of the container (30).

Abstract: One feature pertains to a device that includes a main body having a bottle-receiving end that receives an end of a bottle having a mouth and forms an airtight seal between an exterior surface of the bottle and an interior air cavity of the main body. The device also includes an actuator assembly that drives a stopper securement device into a stopper positioned within the mouth of the bottle and retracts the stopper securement device to remove the stopper from the mouth of the bottle. The device also includes a vacuum pump that evacuates air out of the interior air cavity and the bottle's headspace after the stopper has been removed to create a vacuum within the headspace. The actuator assembly may also drive the stopper securement device and the stopper back into the mouth of the bottle to reseal the bottle while the headspace is under vacuum.

Abstract: To provide a filling device that realizes simplification of device configuration, improvement of design freedom, and redaction of production loads, and that prevents formation of a pointed peak on the upper surface of packed contents, or uneven filling of the container. Provided is a filling device (10) including a filling nozzle (20), a contents supplier (30), a plunger (40), and a gas supplier (50). A gas inlet (25) connected to the gas supplier (50), a gas outlet (26) opened to the nozzle hole (23), and a gas flow passage (27) are formed in the filling nozzle (20). The gas (A) supplied from the gas supplier (50) is ejected from a gap between an inner circumferential surface of the nozzle hole (23) and an outer circumferential surface of the plunger (40) at a lower end of the filling nozzle (20).

Abstract: Examples of the disclosure provide a system and method for autonomously opening bags using a mechanical arm. The mechanical arm includes actuators that move the mechanical arm in response to a trigger, a gripping component that attracts a portion of the bag in response to contact with the bag using a static electric charge, a nozzle that provides an introduction of compressed air into an environment relative to the opening of the bag, and a trigger mechanism that provides the trigger to the mechanical arm such that the mechanical arm brings the gripping component into contact with the bag using the one or more actuators and provides an expulsion of a portion of the compressed air via the nozzle to open the bag.

Abstract: An anvil of an ultrasonic sealing apparatus that includes a horn provided with a strip-shaped vibration applying surface at an end face thereof, the anvil being provided with an abutment surface at an end face thereof, the ultrasonic sealing apparatus sandwiching a laminate of two or more sheets between the vibration applying surface and the abutment surface and melting thermoplastic resin on the sheets by ultrasonic vibration delivered to the vibration applying surface, thereby bonding the laminate. The abutment surface includes a strip-shaped welding surface portion projected toward the horn, and the end face thereof is opposed to the vibration applying surface, and a plurality of block members arranged along the strip-shaped welding surface portion in an extending direction of the welding surface portion without being in contact with each other, and the plurality of block members has a height equal to or lower than the welding surface portion.

Abstract: A package system suitable for sterilizing cyanoacrylate compositions and providing the sterile cyanoacrylate compositions a shelf life of at least 24 months, wherein the package system comprises: an ampoule comprising a chamber comprising a cyanoacrylate monomer, wherein the chamber is defined by an opening and sidewalls, wherein the ampoule comprises a material comprising a cyclic olefin copolymer; a multilayer foil seal sealing the opening of the ampoule; and a secondary package housing the ampoule.

Abstract: A packaging machine, comprising a control unit, at least one measurement device and a plurality of work units for different processes. One of the work units is designed as a sealing station which comprises at least one moisture sensor designed as the measurement device which is functionally connected to the control unit and is designed to detect moisture within the sealing station as a time-dependent measured variable during a program sequence of the sealing station. The program sequence may comprise an evacuation process, wherein the control unit is designed to calculate a rate of change in the moisture during the evacuation process of the sealing station. The control unit may abort the evacuation process performed on the sealing station, based on the rate of change, before reaching a target vacuum pressure within the sealing station, immediately or after a specified delay time elapses.

Abstract: An item packaging carousel is disclosed. The carousel includes a first tier and a second tier, each of the first tier and the second tier including a plurality of item receptacle compartments, each item receptacle compartment configured to hold at least one item receptacle; a motor configured to rotate at least one of the first tier or the second tier to bring one of the plurality of item receptacles to an active filling position; and an item packaging carousel control system including a processor and communications circuitry, the communications circuitry configured to receive item information from an item scanning system, and the item packaging carousel control system configured to provide a rotation signal to the motor to cause at least one of the first tier or the second tier to rotate to bring a selected one of the plurality of item receptacle compartments to an active filling position based on the received item information.

Abstract: An apparatus to permit transferring the retaining-and-centering unit that has been supplied to the first handling-station in a receiving direction thereof to a second handling-station includes a carrier that carrier secures a securing device to the first handling-station, a receiving unit, a drive, and a securing apparatus that cooperate to detachably secure a retaining-and-centering unit to a first-handling station. The securing apparatus detachably secures the retaining-and-centering unit to the first handling-station. The receiving unit, which is on the carrier, connects the securing apparatus to the carrier. The drive moves the receiving unit parallel to the receiving direction.

Abstract: The present disclosure relates to a container and a system for containing liquid crystal, in the field of manufacture of display devices. The container for containing liquid crystal comprises a bottle body. The lower part of the bottle body is a concave structure, the bottom surface of the concave structure is a flat surface or a concave surface, and the opening of the concave structure faces to the opening of the bottle body. The present disclosure solves the problem of the low one-round utilization ratio of the liquid crystal in the liquid crystal bottle and increases the one-round utilization ratio of the liquid crystal in the liquid crystal bottle. This disclosure is applied to display devices.