Abstract: A foldable scooter is disclosed with two rotational connections to the steering column, and a fixing structure that maintains the frame elements fixed relative to each other and stable when riding. Once the fixing structure is disengaged, the frame elements are free to rotate relative to each other such that the scooter can be folded into a more compact dimension.

Abstract: A vehicle wheel axle assembly comprises an axle element with a first outer face and a second outer face and a clamping assembly including a clamping element and a gripping element. The gripping element includes an axially inwardly facing grip face and an axially outwardly facing pressure face. The clamping element includes a helical threaded portion and an axially inwardly facing clamping face. The clamping assembly includes an elastically resilient element to axially bias said grip face to be axially inward and distal from said clamp face. The pressure face is axially inboard of the clamping face. The gripping element is rotatable relative to said clamping element. The clamping element is rotationally coupled to the gripping element by a coupling means at a coupling interface.

Abstract: A bicycle includes a frame having a longitudinal axis, a first member, and a first pivot link assembly including a first link configured to rotate around a first pivot point. The first pivot point may have a first axis of rotation that is non-orthogonal to the longitudinal axis of the first frame, and the first frame may be coupled with the first member through the first pivot link assembly. Some examples also include a second pivot link assembly including a second link configured to rotate around a second pivot point having an axis of rotation that is non-orthogonal to the longitudinal axis of the frame.

Abstract: A bicycle brake assembly includes a brake unit, a fixing structure and an alignment structure. The brake unit includes first and second brake arms. The fixing structure is configured to operatively couple the brake unit to a brake supporting portion of a bicycle frame. The alignment structure is disposed in the vicinity of the fixing structure. The alignment structure is configured to align the brake unit to the brake supporting portion.

Abstract: A system includes a computer in a bicycle, and the computer has a processor and a memory. The computer is programmed to determine user characteristics for a user of the bicycle, with the user characteristics including pedaling force and pedaling cadence; calculate a power contribution at least in part according to the user characteristics; select one or more operational parameters for a bicycle motor according to the power contribution; and apply the operational parameters to operation of the bicycle motor.

Abstract: The Gear Reduction Tricycle Wheel invention provides two methods of operation of a tricycle with the use of a simple locking pin. When the pin is inserted into the wheel, it operates as a standard wheel would. Without the pin in place, the wheel requires about four times less effort to move with a similar reduction in speed. This gives the option to move with superior control up, down, and over difficult terrain and within limited space (indoor, home, daycare). One can get the sensation of a good ride without the required distance. This new design in the wheel includes gears within the wheel where spokes usually are. In the absence of spokes, side disc plates support the tire rim and the gear axles.

Abstract: A barge-coupling device that is operable to assist in the tightening of cables that are utilized to secure two marine vessels together in preparation for towing. The barge-coupling device further includes a tubular body having a first end and a second end. A hollow bore is present through the tubular body extending between the first end and second end. A first shaft and a second shaft are movably mounted to the tubular body. A handle is included having a lower portion wherein the lower portion has disposed therein a first gear and a second gear. The first gear is operably coupled to the tubular body and the second gear is mounted above the first gear and operably coupled thereto. A keeper rotatably mounted the second gear and is configured to couple with a power tool so as to rapidly rotate the second gear.

Abstract: There is provided a floating structure. The floating structure according to the present invention comprises a main body including leg wells; legs penetrating the leg wells and having cords and racks; a unit installation means positioned in the main body as surroundings of the leg wells. According to the present invention, a jacking unit is installed in the main body by the unit installation means.

Abstract: A water sports board, such as a surf board, is described which has a rider operated center fin that is rotatably mounted on the lower side of the board which aids in steering the board. The central fin is rotatably moved by a center fin assembly that includes a driving mechanism such as a tiller or arm secured to a rotatable shaft passing through the board that is secured to the rotatable central fin. The rider uses his or her rear foot to apply a force to the tiller or arm which moves the tiller and in turn moves the center fin so as to steer the board.

Abstract: A waterway marker illuminating assembly includes a base that has a top side and a bottom side. The bottom side is abutted against and attached to a boat. A post is attached to the top side and extends upwardly therefrom. A housing is attached to an upper end of the post distal to the base. A laser light emitter is mounted in the housing and emits laser light when the laser light emitter is turned on. The laser light emitter illuminates a waterway marker such that a boat operator can easily see the waterway marker.

Abstract: Mine neutralization provides for radio control of a small boat having associated therewith: a projection mounted onto the boat and pointing forward; a primary magnet; a housing holding the primary magnet and joined at the front end of the projection; a fluid-dynamically shaped explosive device detachably attached underneath the boat; at least one secondary magnet affixed to the explosive device; and, a rope or cable tautly connected at its upper end to the primary magnet and at its lower end to the explosive device. The boat journeys near a floating mine to bring about magnetic interaction between the primary magnet and the mine. The primary magnet magnetically attaches to the mine, and a pulling force is exerted on the explosive device. The explosive device detaches from the boat, moves toward the mine, and magnetically attaches (via at least one secondary magnet) to the mine.

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements rapidly inflated and rigidized using an acrylic adhesive and UV light generated by combustion, which find use, for example, in rapidly deploying and supporting the wing of an aerial vehicle and wind turbine towers.

Abstract: A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.

Abstract: An edge flap arrangement for an aircraft wing includes a main flap element and an actuator. A linkage arrangement supports the main flap. The linkage arrangement includes a drop hinge link arrangement. The drop hinge link arrangement includes a fixed strut and a drop link. The fixed strut and the drop link are pivotally connected by a hinge point. The hinge point includes an hourglass bearing. The hourglass bearing includes an inner member, an outer member, and a plurality of hourglass rollers. Any combination of the inner member, the outer member, and the hourglass rollers are fabricated from CREN, Cronidur 30, XD15NW, 422 Stainless Steel, CRES, and/or 440C Stainless Steel. A cage is disposed between the inner member and the outer member. The cage includes a plurality of first rails and a plurality of second rails. Opposing pairs of first rails and second rails define a plurality of pockets.

Abstract: A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.

Abstract: A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced.

Abstract: The present disclosure relates to a method and an apparatus for the contactless measurement of the steering angle of an aircraft landing gear, in particular of a nose landing gear. Furthermore, this present disclosure relates to an aircraft landing gear, in particular a nose landing gear, which allows a contactless measurement of the steering angle.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly that may rotate about an axis from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears.

Abstract: A vertical take-off and landing aircraft includes a propulsion mechanism having a fan for generating lift and thrust, an engine for supplying motive power to the propulsion mechanism, a frame coupling the propulsion mechanism and the engine, seating connected to and suspended from the frame so as to be swingable back and forth relative to the frame, a control stick connected to the frame, and a landing undercarriage connected to the seating, wherein the propulsion mechanism is connected to the frame such that the drive shaft of the fan is directed vertically during landing, and the frame is moved relative to the seating by manipulating the control stick, to change the orientation of the propulsion mechanism. The thrust can be controlled with simple configuration, and take-off and landing can be performed safely even in a small space surrounded by obstacles.

Abstract: Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device.

Abstract: Aspects include a system for transferring a payload between drones. The system includes a first drone having a first member and a first controller, the first member having a first coupling device on one end, the first member being configured to carry a payload, the first controller being configured to change a first altitude and orientation of the first drone. A second drone includes a second member and controller, the second member having a second coupling device on one end, the second member being configured to receive the payload, the second controller being configured to change a second altitude and orientation of the second drone. The controllers cooperate to change at least one of the first and second altitude, and the first and second orientation to operably engage the first coupling device to the second coupling device for transferring the payload from the first member to the second member.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: A toilet assembly for a vehicle comprises a first toilet compartment including a first opening, a first foldable toilet compartment door for closing the first opening, and a first toilet opposite to the first opening. An adjacent second toilet compartment includes a second opening, a second toilet compartment door for closing the second opening, and a second toilet opposite to the second opening. A forward dividing flap is rotatably supported by the front wall and situated between the first toilet compartment and the second toilet compartment for at least partially dividing the first toilet compartment from the second toilet compartment, wherein the forward dividing flap is rotatably supported at the front wall, the first toilet compartment door is retractable to a side facing away from the dividing flap, the first toilet is further from the front wall than is the second toilet, and the forward dividing flap closes the first opening when the first toilet compartment door is retracted.

Abstract: A ventilation nozzle assembly is described that includes a first air outlet channel configured to provide an air flow in a first direction, a second air outlet channel adjacent the first air outlet channel configured to provide an air flow in a second direction, a third air outlet channel adjacent the second air outlet channel and configured to provide an air flow in a third direction, and a fourth air outlet channel adjacent the third air outlet channel and configured to provide an air flow in a fourth directions. An air flow from the third air outlet channel is configured reduce an impact of the air flow from the fourth air outlet channel has on the air flows from the first air outlet channel and the second air outlet channel.

Abstract: A heat exchanger with at least one cooling segment having a first, a second, and a third portion. A first heat carrier flow path, through which a first heat carrier medium flows, extends through the first portion. A second heat carrier flow path, through which a second heat carrier medium flows, extends through the second portion. A first coolant flow path, through which a first coolant medium flows, extends through the third portion. The heat exchanger comprises at least one cooling body, a second coolant medium flowing through a second coolant flow path extending through the cooling body. The first and the second heat carrier flow paths are thermally coupled, respectively, to the first and the second coolant flow path, to discharge heat energy of at least one of the first and the second heat carrier medium to at least one of the first and the second coolant medium.

Abstract: A system for cooling an aircraft includes a fuel tank, a fuel delivery system, a cooling system, and a heat exchanger. The fuel tank is configured to hold cooled fuel for the aircraft. The fuel delivery system is configured to provide at least a portion of the fuel from the fuel tank to an engine of the aircraft. The cooling system is configured to absorb heat generated by components on the aircraft. The heat exchanger is thermally connected to the fuel delivery system and the cooling system. The heat exchanger is configured to transfer at least a portion of the heat from the components on the aircraft to the cooled fuel. The system may further include a two or three phase expendable liquid system. The expendable liquid system is configured to transfer heat to a frozen or liquid coolant to vaporize and expend the coolant from the aircraft.

Abstract: Described are a parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. The parafoil comprises flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible members may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle.

Abstract: A life vest stowage device (1) comprises a receptacle (2) for stowing a life vest (3). The receptacle (2) has an opening (4) through which the life vest (3) is inserted into and removed from the receptacle (2). A closure is provided, by which the opening (4) can be opened and closed. The closure comprises a tongue (5) on a first side of the opening (4). The tongue (5) is arranged such that it can be folded across the opening (4) to obstruct the opening (4). On a second side of the opening (4), opposite to the first side of the opening (4), there is provided a pocket (6). The pocket (6) is arranged so that the tongue (5) can be inserted into the pocket (6) when the tongue is folded to obstruct the opening (4). With the tongue (5) folded to obstruct the opening (4) and inserted in the pocket (6), first and second strips (7, 16) of a second material are aligned with one another and can be squeezed together so that the closure is substantially flat.

Abstract: Systems, apparatuses, and methods for overcoming the disadvantages of current air transportation systems that might be used for regional travel by providing a more cost effective and convenient regional air transport system. In some embodiments, the inventive air transport system, operational methods, and associated aircraft include a highly efficient plug-in series hybrid-electric powertrain (specifically optimized for aircraft operating in regional ranges), a forward compatible, range-optimized aircraft design, enabling an earlier impact of electric-based air travel services as the overall transportation system and associated technologies are developed, and platforms for the semi-automated optimization and control of the powertrain, and for the semi-automated optimization of determining the flight path for a regional distance hybrid-electric aircraft flight.

Abstract: A power-distribution panel has a circuit-breaker panel that is completely separable from an aircraft and from a back chassis connected to the aircraft. The back chassis is mechanically mounted to the aircraft and electrically connected to both a power-supply bus and a power-distribution harness of the aircraft. The circuit-breaker panel can be removably coupled to the back chassis to complete a plurality of circuits from the power supply bus to a plurality the plurality of circuits that receive power via the power-distribution harness. In some embodiments, the circuit-breaker panel can be slideably coupled to the back chassis without the use of tools. Electrical connectors may provide electrically connectivity between the circuit-breaker panel and the back chassis. The electrical connectors may have back chassis portions that align with circuit-breaker panel portions so as to provide such electrically connectivity automatically when the circuit-breaker panel is coupled to the back chassis.

Abstract: In one aspect, a ram air turbine stall recovery system includes a ram air turbine, a hydraulic pump powered by the ram air turbine with the hydraulic pump having a pump inlet and a pump outlet, an electric generator powered by the ram air turbine, a bypass line that connects the pump outlet to the pump inlet, a bypass valve located on the bypass line between the pump outlet and the pump inlet; and a controller responsive to an input signal that indicates a potential stall condition of the ram air turbine. The controller causes the bypass valve to open to allow a hydraulic fluid to flow through the bypass line in order to reduce a pressure within the hydraulic pump.

Abstract: According to one example embodiment, a method of assessing reliability of an aircraft component includes identifying, aboard an aircraft, a first probability of failure of the aircraft component installed on the aircraft. One or more measurements representative of at least one load applied against the aircraft component are received. Determined, aboard the aircraft, is a second probability of failure of the aircraft component based on the first probability of failure and the received one or more measurements representative of the at least one load applied against the aircraft component, the second probability of failure representing a probability of failure of the aircraft component after application of the at least one load.

Abstract: According to one example embodiment, a method of assessing use of an aircraft component installed on an aircraft includes assessing whether received one or more measurements are sufficient to support calculation of a usage-based change in remaining useful life and, if the one or more measurements are sufficient to support calculation of the usage-based change in remaining useful life, calculating the usage-based change in remaining useful life based on the received one or more measurements and changing the second remaining useful life of the aircraft component by the difference between the default change in remaining useful life and the usage-based change in remaining useful life.

Abstract: Systems and methods for displaying a location reference indicator (LRI) associated with an ownship icon are provided. In various embodiments, an airport moving map (AMM) is displayed, and the ownship icon is displayed in the AMM, where the ownship icon represents the ownship. A degree of zoom of the AMM is determined. In response to a determination that the degree of zoom is not within a range of center referenced threshold values, a first LRI is displayed that indicates that the icon representing the ownship is not to scale with other objects displayed in the AMM. In response to a determination that the degree of zoom is within the range of center referenced threshold values, a second LRI is displayed.

Abstract: A wearable electronic display system detects aircraft flight related conditions, compares the detected flight related conditions with rules or procedures, retrieves flight condition information relating to phase of flight, and displays small amounts of contextually relevant flight condition information on a display screen.

Abstract: A composite vehicle architecture without a current return network for reducing lightning threats. A plurality of modular equipment centers (MECs) are spatially distributed throughout the vehicle. Equipment loads within the vehicle are each serviced by the nearest MEC. Twisted and shielded electrical conductor pairs provide secondary power to the equipment loads to minimize the amount of wire throughout the aircraft as well as the return currents on the aircraft.

Abstract: A method and device including a unit to extract a linear terrain profile stored in memory, a terrain height for a current distance of the aircraft, a unit for determining a current height of the aircraft with respect to the terrain, using at least one measurement taken by a radar altimeter, a unit for computing a first current altitude of the aircraft, using the terrain height and the current height, a unit for computing a second current altitude of the aircraft, corresponding to an altitude on an approach profile of the current position of the aircraft and a unit for computing the difference between the first and second current altitudes, the difference being transmitted to a guidance unit to vertically guide the aircraft.

Abstract: A camera assembly is disclosed for mounting on a vehicle (e.g. an aircraft). An exemplary camera assembly can include: a fixture (e.g. a rotatable drum); a camera; and a mirror; wherein the fixture is arranged to be rotated relative to the vehicle about an axis; the camera is mounted on the fixture such that the camera has a substantially fixed position relative to the fixture; the mirror is mounted on the fixture such that, if the fixture rotates, the mirror rotates; the mirror is rotatable relative to the fixture about a further axis, the further axis being substantially perpendicular to the axis; and the camera is arranged to detect electromagnetic radiation reflected by the mirror. The axis and the further axis may intersect.

Abstract: A carrier for a movable object to couple a carried object to the movable object, wherein the carrier has at least two rotational axes; wherein a combined rotation about the at least two rotational axes controls an orientation of the carried object or compensates a movement and a vibration of the movable object, so as to stabilize the carried object; wherein an angle formed by the two rotational axes is a non-right angle to reduce a rotation radius of the rotation, thereby reducing an equivalent moment of inertia; and wherein a center of gravity of a load applied on each axis of the two rotational axes coincides with a corresponding axis.

Abstract: An aerial vehicle docking system includes a landing pad and an aerial vehicle. The landing pad has a concave landing surface and a depression. The aerial vehicle has landing gear and a protrusion. The protrusion is shaped to mate with the depression. The protrusion and the landing gear are positioned on a bottom surface of the aerial vehicle.

Abstract: A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).

Abstract: A system and method for preventing a gimbal from exceeding a predetermined gimbal rate limit includes receiving a gimbal rate command and a gimbal rate feedback signal representative of sensed gimbal rate. The gimbal rate command and the gimbal rate feedback signal are compared, in a control circuit, to determine a gimbal rate error. A predetermined gain scaling factor is applied, in the control circuit, to the gimbal rate command to generate a scaled gimbal rate command. The gimbal is disabled when the gimbal rate error is greater than or equal to the scaled gimbal rate.

Abstract: A device is provided for filling granular, pulverulent and free-flowing materials into a container, preferably a hose- and sack-shaped container, made of geotextile material. The device includes a housing that allows the advancement of the material and in which a conveying device is arranged. On the entry side of the conveying device the material can be filled in and on the exit side thereof a hose made of geotextile material receives the material. The hose can be shaped on the jacket of the housing, and can be unwound as a web from a feeding device that is designed like a roll. Longitudinal sides of the web can be connected to each other by a device in the region of the jacket. The housing includes a tubular body that extends perpendicular to the direction of advance and is arranged vertically, the tubular body interacting with a feeding device for the geotextile material, which rotates about the jacket of the tubular body and is designed as an unrolling device.

Abstract: A binding medium clamping mechanism includes a rotatable clamping element configured to clamp a binding medium, a driving element configured to drive the clamping element, a one-way transmission element connected between the driving element and the clamping element, and a rotatable clamping head opening element configured to open the clamping element, wherein in the case that the clamping element rotates in a first rotation direction to a position for waiting to clamp the binding medium, the positions of the clamping element and the clamping head opening element interferes with each other, to open the clamping element, and in the case that the clamping element rotates in a second rotation direction opposite to the first rotation direction, the clamping head opening element is pushed by the clamping element to rotate in the first rotation direction to move out of a moving track of the clamping element.

Abstract: A handling apparatus includes a container input, a furnishing carousel, a furnishing module, an application element, and a grouping device. The furnishing carousel rotates about a central axis and has the furnishing module and application element nearby. The furnishing module applies a furnishing feature to a surface of a container, and the application element applies adhesive to the container on a surface outside that surface of a container that is provided with a furnishing feature. The grouping device, which is either a compartmenting or compacting device, is immediately after the furnishing carousel and/or an outlet apparatus. The grouping device groups, compacts, or temporary presses together containers. The container input is either a single-track container feed, a multi-track container feed, a single-track container stream, or a multi-track container stream.

Abstract: An apparatus and method is described herein for automatically labeling using labels having a fluid activatable adhesive along the back surface of such label. The apparatus has multiple pallets each being positionable with the lowermost label of a stack of one or more labels to releasably secure by suction the label against the pallet, and multiple pads each being positionable with respect to pallets to receive labels from the pallets and then releasably retain such labels until application onto containers. Fluid for activating adhesive is applied by an applicator onto labels retained upon the pad to change the fluid activatable adhesive along the label's back surface from a non-tacky state to a tacky state just prior to application of the label onto container.

Abstract: A packing box of a portable device is provided, which includes a main plate body and a frame plate body. Plates, which are adjacent to the main plate body and the frame plate body, are respectively disposed with fold-lines; such that a first side plate of the main plate body overlaps a first bonding plate and a third side plate overlaps a second bonding plate to form an accommodating space.: first frame plate, a second frame plate and a third frame plate of the frame plate body are overlapped with one another, so that the first frame plate, the second fame plate and the third frame plate, which are overlapped with one another, separate the accommodating space through a third bounding plate of the frame plate body. When the main plate body and the frame plate body are flattened, the plates are parallel to one another and flat-shaped.

Abstract: The invention relates to a pack including a group of stackable containers each of which includes a body, a shoulder, a neck, and a bottom defining a recess shaped so as to receive the neck and at least part of the shoulder of an identical underlying container; and a flexible film enclosing the group of containers, said film having bottom openings aligned with each hollow recess. The film closely fits the base of the containers on a bottom contact area that annularly extends around the bottom openings; and the film further has top openings through which the necks extend, the film closely fitting the shoulders of the containers on a top contact area that annularly extends around the top openings.

Abstract: A container and lid assembly is described for storing or transporting contents therein. Embodiments provide a protective security feature in the container and lid assembly. In at least some aspects of the invention a container body is disclosed having an opening, and a lid body is configured to cover the opening of the container body to form an assembly. An extended bumper portion is disposed at a periphery of the container body and substantially at the opening, wherein the bumper portion comprises a removable tear strip integrated into the material of the bumper portion. The tear strip is configured to prevent access to security mechanism of the assembly.

Abstract: A container (100) includes a first container portion (101) and a second container portion (102). One or both can include an end member (105) and a cylindrical sidewall (103) extending from the end member. The cylindrical sidewall can include a central layer (301), an inner wrap (302), and an outer wrap (303). The central layer and the outer wrap can define one or more axially aligned apertures (304,305). A hang tab (106) defining a loop (107) and one or more socles (307,308) can be inserted through the apertures with the loop disposed exterior of the cylindrical sidewall and the one or more socles disposed between the central layer and the inner wrap.