Abstract: A method for image generation, preferably including: generating a set of mission parameters for a UAV mission of the UAV associated with aerial scanning of a region of interest; controlling the UAV to perform the mission; generating an image subassembly corresponding to the mission; and/or rendering the image subassembly at a display.

Abstract: An electric aircraft includes a forward wing and an aft wing both located on a top side of a fuselage and both having an upward dihedral angle. The forward wing has a straight or slightly forward-swept leading edge. The aft wing has a swept leading edge. A plurality of propeller engines are located on a leading-edge side of the forward wing. A single propeller engine may be located on a top side of an aft end of the fuselage; alternatively, a plurality of propeller engines are located on the aft wing on either its leading or trailing edge. The propeller engines are each powered by an electric motor. An unobstructed cargo door is located on a side of the fuselage, aft of the forward wing.

Abstract: The invention provides a float plane having a fuselage, a wing, and two floats mounted to the fuselage. In one group of embodiments, the float plane is a firefighting float plane that includes a water tank and a water scooping assembly. In another group of embodiments, the float plane includes a spreader bar suspension assembly. In certain embodiments, the float plane is a firefighting float plane that includes a water tank, a water scooping assembly, and a spreader bar suspension assembly.

Abstract: In one embodiment, a method includes removing a cargo handling rail from a cargo floor of an aircraft and installing a brace system directly into the cargo floor. The brace system includes a support plate and a spreader bar. The support plate is parallel to the cargo floor and has a surface that interfaces with the cargo floor and multiple slots for rollers. The spreader bar is parallel to the cargo floor and perpendicular to a cargo handling rail face and parallel to the support plate.

Abstract: A protective aviation garment is designed to protect a crewmember during flight. The garment includes a bladder layer which retains a pressurized fluid and applies pressure to the user. The bladder layer is semi-permeable, being impermeable to both oxygen and nitrogen and permeable to water vapor. A first fluid tube is formed as part of the bladder layer to deliver the pressurized fluid to the interior of the bladder layer. A cover layer is formed from a fire-retardant fabric surrounding the exterior of the bladder layer. The cover layer is sealed around the first fluid tube and allows the first fluid tube to pass therethrough. The thigh seals are configured to seal the bladder layer to the user such that the bladder layer forms a lower volume and an upper volume. The first fluid tube delivers the first pressurized fluid to the lower volume.

Abstract: A partition including, but not limited to, a first body comprising a planar, foldable material. The partition further comprises a plurality of flat substrates resistant to folding. The partition further comprising an adhesive. The substrates are adhered to the first body by the adhesive and arranged in a repeating pattern that defines a plurality of columns and rows. Each column and each row is spaced apart from its neighbor, thus defining longitudinal gaps between the columns and lateral gaps between the rows. The first body folds laterally along the longitudinal gaps in an accordion-like manner and contemporaneously folds longitudinally along the lateral gaps in an accordion-like manner. The partition contracts both laterally and longitudinally when first body contemporaneously folds laterally and longitudinally. The partition extends both laterally and longitudinally when the first body contemporaneously unfolds laterally and longitudinally.

Abstract: A seat back assembly for a passenger seat, such as but not limited to an aircraft passenger seat, includes a seat back and a backrest assembly. The backrest assembly includes a backrest and a headrest. The backrest is movable relative to the seat back between a stowed position and a deployed position. The headrest is supported on the backrest and is movable relative to the backrest between a stowed position and a deployed position.

Abstract: Apparatuses, systems, and methods comprising acoustically absorptive air ducts comprising an internally positioned structure component as an endoskeleton and an air impervious inner layer, and an acoustically absorptive foam outer layer, environmental control systems comprising such air ducts, and vehicles incorporating such environmental control systems are disclosed with methods for manufacture and installations are disclosed.

Abstract: A multi-zone anti-icing system for an aircraft part. The system includes at least two or more-part zones configured with the aircraft part and an electrothermal heater associated with at least one part zone of the aircraft part; at least one resistive temperature detector (RTD) associated with each part zone of the aircraft part configured to generate temperature data associated with each part zone. A controller coupled to the electrothermal heater and configured to implement an algorithm of a control logic for an anti-icing operation that uses feedback temperature data from at least one RTD at an associated part zone wherein the feedback temperature data is analyzed by the controller via the algorithm to assess reliability of the temperature data generated by the at least one RTD associated with each part zone.

Abstract: A system for a blended wing body aircraft with a combustion engine is illustrated. The aircraft comprises a blended wing body, at least a fuel source located within the blended wing body and configured to store a fuel, wherein the fuel includes liquid hydrogen, and at least a propulsor configured to propel the blended wing body aircraft. The at least a propulsor comprises a combustion engine configured to burn the fuel from the fuel source and produce mechanical work to power the at least a propulsor.

Abstract: An aircraft propulsion system having a variable airflow capture area is provided. The propulsion system includes a main propulsion source and an auxiliary propulsion source. In a first mode, the auxiliary propulsion source is stowed within an aerodynamic profile of the aircraft, and the main propulsion source provides all of the propulsion force for powering flight of the aircraft. In a second mode, the auxiliary propulsion source is deployed to augment the airflow capture area of the main propulsion source and increase an overall airflow capture area of the propulsion system. In the second mode, the auxiliary power source is operated by power extracted from the main propulsion source. The main propulsion source may include one or more low bypass ratio engines. The auxiliary power source may include one or more auxiliary thrust fans coupled at a plurality of locations on the aircraft.

Abstract: In an embodiment, a system may comprise at least two power supplies which may comprise a first power source, a first step-down converter, a first switching device, a first bus, a second power source, a second step-down converter, a second switching device, and a second bus, the first and second buses being electrically separate. An exemplary system may further comprise an alternate power supply comprising a third power source and an alternate step-down converter connected to at least the first and second buses via at least a third switching device, the alternate power supply acting as a backup power supply configured to be used after a failure of one or more of the at least two power supplies. In some embodiments, the first and second switching devices may be controlled by at least a first controller and the at least third switching device may be controlled by an alternate controller.

Abstract: An electric aircraft according to an embodiment of the present invention comprises: a fuselage equipped with a power means, a front spar and a rear spar extending from the fuselage to an end of a wing, and a plurality of ribs extending from the rear spar to the front spar and coupled to the front spar and the rear spar, in which a plurality of solid state batteries are mounted in a plurality of individual spaces partitioned by the front spar, the rear spar, and the plurality of ribs, respectively, and the front spar and the rear spar are used as members for serial connection of the plurality of solid state batteries, and the plurality of ribs are used as members for parallel connection of the plurality of solid state batteries.

Abstract: A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.

Abstract: A takeoff location and a landing location are received for an autonomous vertical takeoff and landing (VTOL) vehicle that includes a plurality of rotors. An autonomous and noise-reduced flight trajectory for the autonomous VTOL vehicle is determined based at least in part on the takeoff location, the landing location, a jerk function, and a noise function, including by minimizing the jerk function and minimizing the noise function. A set of one or more desired forces or moments is determined for the autonomous VTOL vehicle based at least in part on autonomous and noise-reduced flight trajectory. A plurality of motor control signals is determined for the plurality of rotors based at least in part on the set of one or more desired forces or moments.

Abstract: A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.

Abstract: A flammability reduction system and method for controlling air pressure and allowing an air separation module (ASM) to consume less pressurized air includes a pressure limiting valve that is dynamically controlled based upon a defined pressure setpoint. A flammability reduction system and method for predictively monitoring the ASM's health and its remaining useful life includes a flow and/or oxygen sensor that are used to detect trends in ASM flow rate and/or oxygen content in the inert gas produced by the ASM. A flammability reduction system and method for controlling heat load includes flow and temperature sensors for calculating heat load of a component, and controls one or more valves to adjust temperature and/or flow rate to control the heat load based upon a heat load setpoint.

Abstract: An aircraft light is provided which can illuminate an illuminated area with appropriate levels of illuminance. An aircraft light is configured, including: at least one or more light-emitting elements as light sources; and an inner lens configured to project light emitted from the light-emitting elements onto a desired area, in which the inner lens has a lens that splits light of a single light-emitting element in different directions. According to this aspect, both a far illumination area and a near illumination area can be illuminated, and the luminous intensity can also be adjusted by adjusting the amount of a beam to be split; therefore, an illuminated area can be illuminated with appropriate levels of illuminance.

Abstract: The present application describes an apparatus having a processor configured to receive a plurality of sensor measurements for each sensor of a plurality of sensors of the system. The processor may be configured to compare the plurality of sensor measurements from each sensor to a respective threshold value, determine, based on the comparisons, a condition of the system having a degraded state and one or more conditions of the system having a normal state, and select at least one of the one or more conditions of the system having a normal state. The processor may be configured to input the condition having degraded state and the at least one condition having a normal state into a diagnostic model. Further, the processor may be configured to isolate, using the diagnosis model, a failed or degraded component of the system.

Abstract: A reusable floating device suitable for launching a space rocket has a support structure which includes a toroidal balloon housing and a rigid platform attached thereto; an elongated rigid structure surrounded by said support structure, releasably connected thereto, and adapted for attachment to a space rocket; at least one buoyant gas balloon within said balloon housing; and a compressor module and at least one rigid-walled tank carried by said platform. The compressor module is in confined flow communication with the at least one buoyant gas balloon and the at least one rigid-walled tank.

Abstract: A dual mode engine for propelling a spacecraft, including a combustion chamber having a flange end, an open nozzle end, and an enclosed chamber portion extending therebetween, a propellant tank in fluidic communication with the combustion chamber, an electronic controller, a power source operationally connected to the electronic controller, and a fluid flow motivator operationally connected to the electronic controller and connected in fluidic communication with the propellant tank. The engine further includes a chemical propulsion portion further including a propellant inlet port operationally connected to the combustion chamber and disposed adjacent the flange end, an ignition trigger electrode positioned in the combustion chamber adjacent the propellant inlet port and operationally connected to the electronic controller and operationally connected to the power source, wherein the propellant inlet port is fluidically connected to the propellant tank.

Abstract: A launch vehicle dispenser attach structure is disclosed. The launch vehicle dispenser attach structure includes a launch vehicle adapter, and a polygonal extruded cylinder comprising tapered side and an essentially closed end. The polygonal extruded cylinder connects to the launch vehicle adapter. The tapered sides and the closed end of the polygonal extruded cylinder provide mounting interfaces for connecting satellite dispensers. A mounting interface of the mounting interfaces includes a separation ring for transforming the launch vehicle dispenser attach structure into a free flying satellite. The launch vehicle dispenser attach structure is particularly useful for attaching multiple payload separation systems to launch vehicle.

Abstract: A retaining and releasing device for spaceships retains and releases a body to/from a support structure. A releasing bolt keeps the releasable body and the support structure connected in a position for locking the retaining and releasing device. A locking device for locking the releasing bolt in the support structure has a case and a segmented ring. The case is movable axially relative to the releasing bolt and includes an end with a through-slot. A releasing system includes an actuator, a rod having the same orientation as the releasing bolt, with a locking pin, cooperating with the slot, and a compression spring. The actuator locks the rod in a position for locking the retaining and releasing device. The compression spring is in contact with the case of the locking device and disposed around the rod to rotate the rod. The device includes a system for removing the releasing bolt.

Abstract: [Problem to be Solvent] To provide an aerial vehicle that can efficiently reduce the horizontal dimensions of the airframe. [Solution] The aerial vehicle according to the present invention includes two first frames arranged in a second direction intersecting a first direction, with the first direction being longitudinal, two second frames arranged in the first direction by overlapping the two first frames, with the second direction being longitudinal, first rotor blades mounted to both ends of the first frame, and second rotor blades mounted to both ends of the second frame, wherein the second frame is provided with a hinge part capable of folding the second frame at a midway thereof.

Abstract: An airfoil profile for an aircraft, such as an unmanned aerial system. The airfoil profile includes a leading edge portion and a trailing edge portion that are spaced apart along a chordwise direction, an airfoil centroid; and an upper airfoil surface and a lower airfoil surface. The airfoil surfaces are shaped such that the pressure center of the lifting force is arranged at the same chord location as the airfoil centroid or closer to the trailing edge portion along the chordwise direction than the airfoil centroid. With this, a pitch-down momentum is generated that urges the leading edge portion towards a lower angle of attack.

Abstract: An aerial vehicle may include a fuselage; and one or more propellers coupled to the fuselage, wherein the aerial vehicle may have at least a taking off or landing state and a cruise state. In response to the aerial vehicle being in the taking off or landing state, an angle between a longitudinal axis of the fuselage and a horizontal plane may be within a first angular range and in response to the aerial vehicle being in the cruise state, an angle between the longitudinal axis of the fuselage and the horizontal plane may be within a second angular range. A maximum value of the second angular range may be less than a minimum value of the first angular range. In response to the aerial vehicle switching between the takeoff or landing state and the cruise state, the fuselage and the propellers may tilt as a whole.

Abstract: A base station may include a base body, a landing pad, and a base station opening and closing structure. The base station opening and closing structure may include an open state and a closed state. In the open state, the base station opening and closing structure may provide a landing space for an aerial vehicle to land on the landing pad, and in the closed state, the base station opening and closing structure may provide an accommodating space to accommodate the aerial vehicle. During a process of the base station opening and closing structure transitioning from the open state to the closed state, the base station opening and closing structure may be configured to propel some blades of the aerial vehicle partially protruding out of the accommodating space to fold or retract so as to accommodate the aerial vehicle within the accommodating space.

Abstract: A drone pod may receive, stow, and launch a drone. The drone pod may include a housing, a canopy movably coupled to the housing, a platform movably coupled to the housing, and a drone bay. The drone pod may be configured to move the canopy to expose the drone bay and raise the platform relative to a floor of the drone bay to receive the drone, lower the platform toward the floor of the drone bay and move the canopy to enclose the drone bay to stow the drone, move the canopy to expose the drone bay and raise the platform relative to the floor of the drone bay to launch the drone. The drone pod may be mounted on a vehicle. A system may include a drone pod and a drone, wherein the drone pod is configured to receive, stow, and launch the drone.

Abstract: A bag opener device for facilitating the opening of thin plastic bags comprising a pair of arms operative to angularly move toward and away from each other between a closed position and an open position. Each of the arms has a tab on the distal end thereof and a handle portion, and in one preferred embodiment, an inclined surface which is in a plane transverse to the plane of the arms. In use, the arms are squeezed together to cause the distal tabs to engage each other and grip the sides of the plastic bag to be opened and, upon further squeezing of the arms, to cause the tabs to slip relative to each other and thereby cause the bag sides to slide and thereby open the bag.

Abstract: A turret assembly rotatably mountable to a container sealing system. The turret assembly includes an annular turret having a plurality of arcuate container pockets arrayed about an outer periphery of the turret and an annular chamber located radially inward of the outer periphery of the turret, and a hub removably secured within the annular chamber of the turret, wherein the hub is adapted to be rotatably secured to the container sealing system. A turret system for use with a can seamer is also provided, and includes two or more annular turrets, and a hub removably securable within the annular chamber of the two or more annular turrets for selectively mounting the annular turrets to the hub and the can seamer.

Abstract: Time required for initial operation and operation immediately after wound body replacement is shortened. A packaging device packages an object to be packaged using a wound body. An elongated sheet-shaped packaging material is wound into the wound body. The wound body includes a recording medium that stores information. The information recorded in the recording medium includes remaining amount information indicating a remaining amount of the packaging material in the wound body. The packaging device includes a drive unit that generates driving force in order to rotate the wound body, an information reader that reads the remaining amount information stored in the recording medium, and a controller that controls the packaging device. The controller sets a rotation speed of the wound body based on the remaining amount information read by the information reader.

Abstract: A machine for forming a container from a blank of sheet material includes a frame and an identification tag applicator mounted to the frame. The blank includes a first surface that forms an interior surface of the container and a second surface that forms an exterior surface of the container. The identification tag applicator is configured to apply an identification tag to the first surface of the blank. The machine also includes a mandrel assembly mounted to the frame and located operationally downstream from the identification tag applicator. The mandrel assembly includes a mandrel having an external shape complimentary to an internal shape of at least a portion of the container. The machine also includes a lift assembly configured to lift the blank having the identification tag adhered thereto towards the mandrel and wrap the blank about the mandrel.

Abstract: A labeling machine, which includes a conveyor for conveying containers to be labeled and at least one labeling station provided with an unwinding assembly for a label ribbon on which a plurality of labels are printed in succession, and at least one drum which is provided, peripherally, with runners which have at least one relief portion, in relief with respect to the lateral surface of the drum; a spreading roller for spreading adhesive on the label ribbon; at least one of the runners has at least one contoured part in order to allow the application, by the spreading roller, on the portion of the label ribbon and/or of the labels that is on the contoured part, of at least one adhesive imprint which has at least one region without adhesive.

Abstract: A plastic container includes a base, an opening, and a plurality of panels. In embodiments, the plurality of panels are configured for digital printing. Systems and methods for digital printing on plastic containers with a plurality of panels are also disclosed.

Abstract: A carton with a detachable buffer plate set includes a bottom plate, two long side plates, an upper cover, two short side plates, two reinforcing side plates, and a detachable buffer plate set. The long side plates and the short side plates are connected to the bottom plate. The upper cover is connected to one of the long side plates. The two reinforcing side plates are connected to the two short side plates respectively. The detachable buffer plate set is detachably connected to one of the reinforcing side plates. Accordingly, by detaching the detachable buffer plate set for supporting and buffering, products of similar size or products with accessories of different sizes may use the same-sized cartons and paper-plastic boxes, so that extra die-cutting costs and storage costs are avoided.

Abstract: The present subject matter discloses a package structure for a plastic storage box with an integrated hinge structure. The package structure comprises an installation cavity formed between the several boards of the plastic storage box, wherein the rest of the boards are stacked in the installation cavity in the storage box packaging state. Furthermore, the package volume of the boards for the storage box is compact, the packaging is convenient, and the boards are securely stored during transportation.

Abstract: The present invention relates to a hybrid panel, comprising a panel comprising: a core, a first protecting layer on a first side of said core and a second protecting layer on a second side of said core; said panel defining an outside geometry thereof; and an overmolded portion which overlays at least a part of said panel, thereby changing said geometry of said panel at said part of said panel.

Abstract: The container has a base and lateral walls. The system of the invention comprises at least one retention support configured to be mounted on an area of the internal surface of the container; where said retention support is in contact with at least part of a body to be secured, which rests on the base of the container. The body to be secured is restrained inside the container on a plane selected from among a horizontal plane parallel to the base of the container, a vertical plane perpendicular to said base of the container, and two perpendicular planes: the horizontal plane parallel to the base of the container and the vertical plane perpendicular to the base of the container.

Abstract: A liner for use in a container can include a liner wall defining an interior cavity of the liner. The liner includes a top portion and a bottom portion sealed to the liner wall, the tip portion comprising an opening. The liner further includes a disk sealed to the top portion of the liner, the disk covering the opening.

Abstract: An envelope has front panel and a back panel, the front panel and the back panel joined along three edges and open along a fourth edge to provide an opening to an interior of the envelope. A foldable flap extends from the front panel to close the opening. The front panel, back panel and flap are formed of a compostable plastic film, and the envelope is configured to be entirely compostable as-is by a recipient.

Abstract: A paper-based packaging article includes outer and intermediate paper plies and an inner polymer film ply. A first adhesive layer is disposed between the inner and intermediate paper plies for gluing the inner polymer film ply to the intermediate paper ply. A second adhesive layer is disposed between the intermediate and outer paper plies for gluing the intermediate paper ply to the outer paper ply. The first and second adhesive layers overlap and are coaligned. The outer and intermediate paper plies and the inner polymer film ply are adjoined to form a multiwall structure, wherein the first adhesive layer and the second adhesive layer are coaligned with each other on the multiwall structure. The first adhesive layer comprises a first plurality of adhesive spots and the second adhesive layer comprises a second plurality of adhesive spots, wherein the adhesive spots of the first plurality of adhesive spots do not overlap with the adhesive spots of the second plurality of adhesive spots.

Abstract: The present invention provides a sheet material container being made of a sheet material and including a body portion and a bottom portion that is to be disposed on a placement surface, and the sheet material including a plurality of film layers. A body portion sheet that constitutes the body portion includes a bonding portion where peripheral edge portions of the sheet materials are bonded. In a bottom surface sheet that constitutes the bottom portion, a non-adhesive region is provided in the plurality of film layers. The non-adhesive region forms a bottom filler-filled portion. The bottom filler-filled portion extends annularly around a non-filled portion, and includes at least three protruding leg portions that are to be placed on the placement surface so as to allow the container to stand by itself. The protruding leg portions protrude toward the placement surface past other portions in the bottom filler-filled portion due a leg forming portion.

Abstract: A container with multi-chambers is described. Each hair coloring substance of the multi-chamber is stored in its sub-chamber. The final hair coloring solution is formed by mixing the hair coloring substances in mixing sub-chambers in liquid communication with the interior of each of the sub-chambers. An optional mixing nozzle is also used in conjunction with the mixing chamber, and the mixing nozzle may include a helical mixing tool.

Abstract: Hinged closures for containers are provided. The hinged closures allow for a closure that can be held in the open position with a large opening angle. The hinged closures include a lid portion and a tamper evident band interconnected by a hinge portion. The hinge portion can be formed from two connecting bands and a central flexible band, or a continuous band having variable thickness and a central thinner flexible area.

Abstract: Disclosed is a housing for a catheter, the housing comprising: a body; a cap assembly comprising a cap and a tamper-evidence ring, wherein the cap is attached to the body and the tamper-evidence ring in an unopened configuration and is configured to be irreversibly detached from the tamper-evidence ring when the cap is removed from the body, the housing further comprising at least one anti-rotation mechanism to prevent rotation of the tamper-evidence ring upon rotation of the cap, and at least one axial retention mechanism configured to axially retain the tamper-evidence ring when irreversibly detached from the cap.

Abstract: A device for sealing a vessel, having a stopper for closing the vessel, the stopper including a sealing mechanism for sealing with the vessel; an attachment ring for attaching the stopper to the vessel, the ring has a sleeve provided with a radial flange with a central opening, and first attachment mechanism to be attached to the vessel; a cover having a radial disc and second attachment mechanism; a blocking element having an axial wall and a complementary attachment mechanism engaging in the assembled state with the second attachment mechanism. The axial wall has on one portion of its periphery a tearable tab defined between two grooves forming bridges of thin material, the tab having, on one side, a gripping portion and ending, on the opposite side, with a flared portion such that, once torn, the axial wall opens out along the entire height allowing removal of the blocking element.

Abstract: Comprising a body (1) having a neck (4) which comprises at least one opening (2) which is covered by a lid (3) characterised in that: the neck (4) comprises at least a mouth (7), that defines the opening (2), and a recess (5) in the walls of the neck (4), both the mouth (7) and the recess (5) having an elliptical shape, being the major axis of the ellipse of the mouth (7) and of the recess (5) between 5-15% longer than the minor axis, the lid (3) comprises an extension (6) shaped as an ellipse directed towards the inner side of the lid (3), the major axis of the ellipse of the extension (6) being between 5-15% longer than the minor axis, the ellipse of the mouth (7) is smaller than the ellipse of the lid (3), the recess (5) has a frustoconical configuration that defines an angle ?, and the extension (6) has, in its inner face (9), which is located in front of the recess (5), an inverted frustoconical configuration with respect to the frustoconical configuration of the recess (5), having an angle ? and th

Abstract: A closure with an overcap and fitment is disclosed, wherein the overcap is removably attachable to the fitment, and wherein the fitment includes a spout and a removable inner portion that may be removed to allow contents to pass through the fitment.

Abstract: A dispensing package for a floor treatment composition. The dispensing package includes a coupling shell and a container. The coupling shell is provided with a dispensing opening and at least one front aperture. The container includes a membrane seal engaged with a sealing surface of the container. The coupling shell can provide for a connection between a container and a dispensing system.