Abstract: Motor vehicle sub-assembly (10) comprising a first part (20) made of plastic material forming an outer bodywork skin, and a second part (30) made of plastic material forming an internal structure to which said first part (20) is attached, characterised in that the second part (30) comprises at least one mechanical reinforcement (40) made of thermoplastic material having a Young's modulus less than that of the plastic material of the second part (30), and a coefficient of elongation at break greater than that of the plastic material of the second part (30).

Abstract: An integrated hinge and striker assembly is affixed to one of a first and second vertically aligned sidewalls of a motor vehicle for connecting a tailgate to the motor vehicle. The integrated hinge and striker assembly includes a hinge base, the hinge base being vertically aligned with a first end portion, a center portion, and a second end portion, a hinge extending from the first end portion of the hinge base, a striker extending from the second end portion of the hinge base, and wherein a vertical axis is defined parallel to the hinge base and running through the striker and the hinge. Integration ensures proper operation of a bi-directional hinge that allows the tailgate to be opened to one of two different open positions.

Abstract: A tilting pump apparatus includes a pump operation unit arranged between a mudguard, which is configured to obstruct foreign objects entering from a front side, and a tilting pump, which is configured to be rotated for generating hydraulic pressure to transmit movement of the mudguard generated by depressing the mudguard as rotational force for rotating the tilting pump.

Abstract: A motorcycle headlamp includes a carrier, a light fixture mounted on the carrier, and at least one sensor for detecting features of an area lying in front of the motorcycle in the direction of travel. An opening is provided in the carrier, and the sensor can be arranged in the opening.

Abstract: An aerodynamic umbrella includes a dual durometer skeleton forming an aerodynamic rectangular dome of an apex and a plurality of triangles extending from the apex thereof over a motorcyclist. A front triangle portion thereof is attached to a motorcycle at multiple points on a motorcycle handlebar and front end. A waterproof translucent skin is attached to the skeleton and a portion of the skin attached to the front isosceles triangle and a dome portion over a motorcyclist head is transparent. A remainder of the waterproof translucent skin is highly colored for safety purposes. A rear skirt is attached to the rear triangle on a side opposite the apex. The rear skirt portion is wedged between the motorcyclist and a seat of the motorcycle when sat upon by the motorcyclist to provide an adjustable point of attachment of the umbrella to the motorcycle and to the motorcyclist versus a rear spoiler.

Abstract: An oscillation-type vehicle includes a front vehicle body that suspends a front wheel in a steerable manner, a rear vehicle body that suspends left and right drive wheels, and an oscillation mechanism that causes the front vehicle body and the rear vehicle body to oscillate relative to each other. The oscillation-type vehicle being capable of carrying out drive control of the left and right drive wheels such that the drive wheels behave differently from each other in response to oscillation of the oscillation-type vehicle, wherein the drive control of the left and right drive wheels is carried out using information on the oscillation and information on a speed of vehicle.

Abstract: Flexibility in design of steering characteristics is enhanced in a leaning vehicle including two front steerable wheels. A vehicle includes a body frame, a left front wheel, a right front wheel, a rear wheel, a leaning mechanism, a steering mechanism, and a leaning-responsiveness-adjusting mechanism. The leaning mechanism includes arms rotatably supported by the body frame. The arms rotate with respect to the body frame so that the body frame leans. The steering mechanism mechanically transfers rotation of the handle to the left front wheel and the right front wheel. Accordingly, the body frame leans in the direction opposite to the rotation direction of the handle. The leaning-responsiveness-adjusting mechanism controls a motor by using an instruction value based on a time derivative value of a physical quantity generated by a motion of a rider affecting leaning of the body frame to thereby adjust responsiveness of leaning of the body frame.

Abstract: An electric vehicle includes a battery having a housing. The housing includes a rear side which is defined as a side facing away from a forward travelling direction of the electric vehicle. The electric vehicle further includes a frame, a motor having a housing, and a pivot shaft stack-up assembly co-aligned along a pivot shaft axis. The pivot shaft stack-up assembly includes first and second portions of the frame, a swingarm extending therebetween, and an idler bracket. A shock mount is integral with the battery housing. The shock mount extends from the rear side of the battery housing. The battery housing is configured as a stressed chassis member in which each of the motor housing, the frame, and the pivot shaft stack-up assembly are aligned thereof. The shock mount provides a path along which a load is directed to the battery housing.

Abstract: A brake assembly has a lever configured to press a knee against a pushrod of a piston of a master cylinder assembly. The knee is configured to receive removable inserts that allow a user to modify the angle at which the lever activates the master cylinder assembly. The master cylinder assembly can include protrusions on the outer surface of the cylinder to protect the cylinder from impact damage.

Abstract: A clip for selectively setting a position of a snowmobile ski and a method for adjusting the position. A snowmobile, snowmobile ski assembly, adjustment kit, and a method to adjust snowmobile ski stance also disclosed. The clip includes a connecting portion for selectively to the ski bolt, the connecting portion defining a space having an opening span less than a diameter of the ski bolt, and a central span greater than the opening span, at least one member of the connecting portion being deflected during connection to the ski bolt; and a gripping portion. The method includes removing the clip from the ski bolt on a first side of the ski leg, sliding the ski laterally relative to the ski leg along the ski bolt, and connecting the clip to the ski bolt on a second side of the ski leg.

Abstract: Buoyant sun protection devices have a canopy are provided. A connecting structure has a longitudinal member connected to a first and second elbow. The elbows are connected to first and second crossmembers. The crossmembers each having a distal end attached to a first and a second end cap. A first float has an aperture therethrough. The first float is sized to fit over the longitudinal member. An arc float includes a portion having an aperture centered therein. The aperture includes an outer wall sized to fit around the first and second end caps and the crossmembers. The arc float includes at least two cutouts. A rotatable sun protection canopy is attached to the cross members in the area of the at least two cutouts for surrounding a user within a with a buoyant sunshade.

Abstract: A mooring apparatus (5a; 5b; 5c; 5d) comprising a socket (10a; 10b; 10c; 10d) having a seat (15a, 15a?; 15b, 15b?; 15c, 15c?; 15d, 15d?) and a connection member (20a; 20b; 20c; 20d), wherein the connection member (20a; 20b; 20c; 20d) is receivable, such as removably receivable, in the socket (10a; 10b; 10c; 10d) and rotatable on the seat (15a, 15a?; 15b, 15b?; 15c, 15c?; 15d, 15d?). A method of configuring a mooring apparatus (5a; 5b; 5c; 5d) wherein the method comprises providing a mooring apparatus (5a; 5b; 5c; 5d) and locating the connection member (20a; 20b; 20c; 20d) in the socket (10a; 10b; 10c; 10d) and/or on the seat (15a, 15a?; 15b, 15b?; 15c, 15c?; 15d, 15d?), and rotating the connection member (20a; 20b; 20c; 20d) until the connection member (20a; 20b; 20c; 20d) is retained by the socket (10a; 10b; 10c; 10d).

Abstract: A rope clasp device for securing a rope eliminates the need for a knot in a rope by selectively clasping and encasing at least one portion of a rope in a toothed clamp. The rope clasp device comprises a base, at least one, but generally two swinging doors, and a lock. The swinging doors are pivotably coupled to the base in order to be moved between an open position and a closed position. In the closed position, a pair of channels for passage of a rope is defined between the base and the doors. The channels are defined by a plurality of clasping teeth to retain the rope therein.

Abstract: A disconnectable spread mooring and riser tower system for a vessel floating at a water surface. The system comprises a forward chain table assembly releasably connected to the vessel at the bow via a first connector assembly, and an aft chain table assembly releasably connected at the stem via a second connector assembly. Mooring legs are attached to the chain table assemblies and are capable of being anchored at spaced locations on a seafloor. The first and second connector assemblies are arranged and designed to unlock and release the forward and aft chain table assemblies from the vessel. A riser tower system fixed to the seafloor may be located near the moored vessel and flexible jumper hoses can be extended between the riser tower system and the vessel to transfer fluids, air, power and control signals.

Abstract: A swimming board having a buoyant board body having an upper surface defining, with a continuous body sidewall, a channel recessed into the board body and disposed proximal to the second end of the board body and having a strap fastening assembly coupled to the board body and with a groin strap and a waist strap that define apertures for receiving a user's legs and retaining the user to the board body.

Abstract: Described herein is a system for stabilising a watercraft with a hull. The stabilising system comprises a stabilising fin fixed with respect to a shaft of the fin, a driving system comprising an electric motor with hollow shaft and a reduction gear with hollow shaft for turning the shaft of the fin, and a control system configured for receiving identification data on the roll of the watercraft and for driving the electric motor as a function of the roll. In particular, the casing of the driving system comprises a toroidal portion configured for being inserted in an opening of the hull, wherein the toroidal portion comprises features for fixing the casing to the hull. The reduction gear comprises an output connected to the shaft of the fin and an input.

Abstract: A marine outboard motor is provided with an internal combustion engine comprising an engine block defining at least one cylinder, an air intake configured to deliver a flow of air to the at least one cylinder, a crankcase in which a crankshaft is mounted for rotation about a crankshaft axis which is substantially vertical when the marine outboard is vertical, and a crankcase ventilation system configured to vent blow-by gases from the crankcase and to supply vented blow-by gases to the air intake. The crankcase ventilation system comprises a lubricant separation chamber for separating lubricant from the blow-by gases. The lubricant separation chamber is defined by the crankcase and extends along the length of the crankcase substantially parallel to the crankshaft axis.

Abstract: A propulsion control system for a marine vessel includes a plurality of propulsion devices steerable to propel the marine vessel, at least one proximity sensor that determines a relative position of the marine vessel with respect to an object, wherein the at least one proximity sensor has a field of view (FOV). A controller is configured to identify a trigger condition for expanding the FOV of the at least one proximity sensor and control thrust and/or steering position of at least one of the plurality of propulsion devices to expand the FOV of the at least one proximity sensor by inducing a roll movement or a pitch movement of the marine vessel.

Abstract: A boat maneuvering support device supports maneuvering of a boat including a first propulsion device having a variable turning angle, a second propulsion device for generating a propulsive force for moving the boat in a left-right direction, and a steering mechanism for changing a turning angle of the first propulsion device and an output of the second propulsion device. The boat maneuvering support device includes a control unit which controls the turning angle of the first propulsion device and/or the output of the second propulsion device, a detection unit which detects a rotational speed of a propeller of the first propulsion device, and a calculation unit which obtains a rotational power of the boat based on the turning angle designated by the operation of the steering mechanism and the rotational speed. The control unit controls the output of the second propulsion device based on the rotational power.

Abstract: The propulsion unit comprises an electric actuator and a tiller coupled the electric actuator. The electric actuator includes a housing having a first end and second end. There is an output shaft fully received within the housing. The output shaft includes a coupling portion and a tiller is coupled the coupling portion of the output shaft such that such that a line of action of the actuator is in the same plane as the tiller.

Abstract: Systems and methods are provided for installing splice fittings. One embodiment is a method for forming a splice between stringers. The method includes aligning a web of a splice fitting with a web of a first stringer and a web of a second stringer, and coupling the first stringer and the second stringer by installing fasteners that secure the web of the first stringer to the web of the splice fitting, and by installing fasteners that secure the web of the second stringer to the web of the splice fitting.

Abstract: The invention proposes a simple system, with small space requirement, without hinge arms or sealing skirt, while providing secure and effective opening. To achieve this, the invention provides a door opening by a lateral guidance defining an integrated doubling-back kinematics, towards the interior then the exterior of the fuselage. An opening system of an emergency door (1) is positioned in an aircraft fuselage (2), the door and the fuselage comprising respective frameworks (11, 21) extending opposite each other.

Abstract: A door panel is included in a nacelle assembly for use with a gas turbine engine to block and allow access selectively to the gas turbine engine. The nacelle assembly includes a nacelle wall, a sleeve, and the door panel. The nacelle wall is arranged at least partway around the gas turbine engine and formed to define an opening that extends through the nacelle wall. The door panel is located in the opening and movable relative to the nacelle wall. The sleeve is coupled with one of the nacelle wall and the door panel and configured to move relative to the nacelle wall or the door panel toward and away from the other of the nacelle wall and door panel to adjust a size of a gap between the door panel and the nacelle wall.

Abstract: The present invention relates to an unmanned helicopter. The unmanned helicopter comprises a fuselage. Two arms are respectively disposed on each of two sides of the fuselage. One end of each arm is connected to the fuselage, and the other end of each arm is provided with a rotor having a motor. The unmanned helicopter is characterized in that: the four arms are grouped into a front group and a rear group, two arms in each group are disposed symmetrically along the axis of the fuselage, the fuselage is movably connected to each arm, an angle between a length direction of any one of the two arms in each group and a corresponding rotation axis is an angle r, an angle between the rotation axis and a horizontal surface of the fuselage is an angle a, and an angle between a projection line of the rotation axis on the horizontal surface of the fuselage and the axis direction that extends outward the fuselage is an angle b.

Abstract: An attachment assembly for connecting an actuator to a frame, a method for manufacturing this attachment assembly and a method for reducing backlash in an attachment assembly. The attachment assembly comprises: an outer yoke having a first end and an opposite second end and defining an internal cavity at said second end. The outer yoke has an aperture provided at its second end connected to the cavity; and an inner yoke located within the cavity. A tie bar having a ball shaped end extends through said aperture such that the ball shaped end is positioned within the cavity and cannot pass through the aperture. A spring is provided at said first end of said outer yoke that is configured to bias the inner yoke in the direction of the aperture. The attachment also includes shearable means for holding the inner yoke.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for redundant actuation of control surfaces. An example apparatus includes a control surface of an aircraft, and an actuator to move the control surface. The example apparatus also includes an electric motor to move the actuator; the electric motor communicatively coupled to an electrical system of the aircraft. The example apparatus also includes a hydraulic motor to move the actuator, the hydraulic motor fluidly coupled to a hydraulic system of the aircraft. The example apparatus also includes a sensor to detect incorrect operation of the hydraulic system. The example apparatus also includes a switch operatively coupled to the sensor, the switch to enable operation of the electric motor in response to the detected incorrect operation of the hydraulic system.

Abstract: An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

Abstract: An energy absorbing landing system for an aircraft having a fuselage includes landing legs rotatably coupled to the fuselage configured to outwardly rotate when receiving a landing load having a magnitude. The energy absorbing landing system also includes an energy absorption unit coupled to the fuselage and cables coupling the energy absorption unit to the landing legs. The energy absorption unit is configured to selectively apply a resistance to the outward rotation of the landing legs via the cables based on the magnitude of the landing load, thereby absorbing the landing load when the aircraft lands.

Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.

Abstract: An aircraft including a body, a first propeller assembly, a second propeller assembly, a flight control surface, and a parachute. The first propeller assembly is coupled to the body and configured to provide vertical lift. The second propeller assembly is coupled to the body and configured to provide horizontal thrust. The flight control surface is operably coupled to the body. The parachute extends from the body and is arranged to facilitate aircraft takeoff.

Abstract: A cycloidal rotor is provided having a flexible by actuators or self-flexing blade-positioning tack, which can be brought into shape corresponding to currently desired blade orbit. This rotor can also be provided with frontal shielding or partial enclosure to assure that rotor operates at any speed as if in hovering flight; rotor track can be inclined to produce forward thrust or external thrusters can be used. Optionally in other embodiments blade orbit shape is determined by a variable cam mechanism or the inclination of blade positioning track of fixed shape to produce a change of its projected shape onto blades' plane of operation thus changing blades elliptic orbit. Blade centrifugal force countervailing mechanism is also proposed.

Abstract: An electronic device is disclosed. The electronic device includes a sensor, an actuator, and a processor. The sensor is configured to sense at least one external object in a direction of 360 degrees outside the electronic device. The actuator configured to allow the electronic device to move or yaw. The processor is configured to verify an angle corresponding to a location of the at least one external object among the 360 degrees and a distance between the at least one external object and the electronic device using the sensor. When the distance does not belong to a specified range, the processor is also configured to move the electronic device in a direction corresponding to the angle using the actuator such that the distance belongs to the specified range.

Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having a wing with oppositely disposed wing tips. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms and aft rotors are coupled to the aft ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the tip booms, and a forward thrust orientation, wherein the aft rotors are aft of the tip booms.

Abstract: Systems and methods are described for managing overhead bin space in an aircraft or other vehicle. An available space or the used space with an overhead bin can be measured using a set of sensors. Using information from the set of sensors, a dongle can determine a shape and volume of the used or unused space within the overhead bin. With this information, the available space can then be reported including the number of roller bags that would fit in the overhead bin or whether there are objects that are not roller bags within the overhead bin.

Abstract: An air supply and return system for a heat exchanger of a galley includes a supply duct configured to extend from the heat exchanger to a cart compartment of the galley, an air-through supply vent in flow communication with the supply duct and configured to be in flow communication with an air-through galley cart in the cart compartment, an air-over supply vent in flow communication with the supply duct and configured to be in flow communication with the cart compartment for supplying cooled airflow for an air-over galley cart in the cart compartment, and a return duct configured to extend from the cart compartment to the heat exchanger to return air to the heat exchanger. The return duct has an air return device in flow communication with the return duct and configured to be in flow communication with the cart compartment to receive airflow therefrom.

Abstract: Systems and methods provide airflow to a first area from a second area within a vehicle. The system includes a fan mounted within a door separating the first area from the second area. The fan is configured to direct airflow from the second area into the first area. The fan having a shield positioned adjacent to the second area that is configured to conceal the fan.

Abstract: An anti-icing/de-icing system for an airfoil structure having multiple layers is provided and includes a thermal article, wherein the thermal article is embedded within the airfoil structure to be located between the multiple layers. The thermal article includes a first terminal end, a second terminal end and a thermal expanded mesh material which connects the first terminal end with the second terminal end, and wherein the thermal expanded mesh material is configured to have at least one predetermined resistance between the first terminal end and the second terminal end.

Abstract: An aspirator for an inflatable assembly may comprise a housing and an inlet flap biased away from an interior of the housing. A pressure relief flap may be biased toward the interior of the housing. A manifold may be located in the interior of the housing and configured to output a primary gas flow toward an outlet of the housing. A nozzle may be fluidly coupled to the manifold. The nozzle may be configured to output the primary gas flow to the manifold.

Abstract: Methodologies to deal with electrical systems and power source failures for electric vertical takeoff and landing aircraft (eVTOL) design with distributed propulsion using multiple electric motors minimize required power source energy to perform an emergency landing procedure. Interconnecting electric loads and power sources in the “Ring Topology” concept considers combination of electric loads and power sources in order to reduce the impact on the loss of a power source, as well as to better utilize the remaining energy of the remaining power sources if any load becomes unavailable.

Abstract: A system for controlling aircraft movement includes a frame extending across a width of a runway. The system includes an attachment mechanism coupled to the frame and configured to be releasably connected to a portion of an aircraft. The system includes a conveying system configured to, with the aircraft coupled to the frame during take-off of the aircraft, accelerate the aircraft. The conveying system is further configured to, during landing of the aircraft, decelerate the aircraft.

Abstract: A runway arrangement comprising: a first runway section (202-1) designated as a landing runway section; a second runway section (202-2) designated as a take-off runway section; and a sterile safety area (210); wherein the first and second runway sections are linked by the sterile safety area (210); the runway arrangement comprising a missed approach point for aircraft due to land on the first runway section, displaced from the start of the second runway section (202-2) by a distance greater than H/tan ?1; where H is a safe turning height and ?1 is an angle of ascent following a missed approach; wherein H is greater than 150 m and ?1 is greater than 2°.

Abstract: A system for lifting and transporting an aircraft comprising a trailer, a lower and an upper inflatable airbag system and a plurality of ties. The trailer can comprise a rigid frame having an upper surface and a lower surface and a plurality of hook ups for attaching ties to the aircraft, at least one pair of wheels. The lower inflatable airbag system is configured for placement below the lower surface of the trailer and the upper inflatable airbag system is configured for placement above the upper surface of the trailer. A method of using the system comprises placing the system underneath the aircraft, inflating the airbag systems, attaching the wheels to the frame of the trailer, securing the aircraft to the trailer, deflating the lower inflatable airbag system, and transporting the aircraft.

Abstract: A public transportation system combines a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software having specifications, standards, processes, capabilities, nomenclature, and concepts of operations that together include a concerted, comprehensive, multi-modal, future system for moving people and goods that is herein named Quiet Urban Air Delivery (QUAD) and in which uniquely-capable, ultra-quiet, one to six-seat, electrically-powered, autonomous aircraft (SkyQarts) fly sub-193 kilometer trips on precise trajectories with negligible control latency and perform extremely short take-offs and landings (ESTOL) with curved traffic patterns at a highly-distributed network of very small, airports (“SkyNests”) that themselves have standardized compatible facilities that interoperate with SkyQarts as well as with versatile, autonomous electric-powered payload carts (EPCs) and robotic delivery carts (RDCs) to provide safe, fast, on-demand, community-accep

Abstract: The object is to provide an aircraft component positioning device, an aircraft assembly system, and an aircraft assembly method with which it is possible to precisely dispose components on a planar member of an aircraft without using a positioning jig. A positioning device (2) includes a detection unit (5) that detects positions of a plurality of first components installed on a planar member of an aircraft, a virtual position creation unit (6) that creates a virtual position between the plurality of first components on the basis of the positions of the plurality of first components that are detected, and a position determination unit (7) that, on the basis of the virtual position that is created, determines an installation position of a second component, different from the plurality of first components, that is installed on the planar member.

Abstract: In order to improve and facilitate shimming between two parts, a deformable shim is provided that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.

Abstract: A spray containment system for a wing-body section includes a forward module, a center module, and an aft module. The forward module has a forward closeout panel configured to engage a forward end of a fuselage center section of the wing-body section. The center module has opposing module side panels each configured to engage a wing lower surface of a wing of the wing-body section. The aft module has an aft closeout panel configured to engage an aft end of the fuselage center section. The forward module and the aft module are independently movable and are configured to be assembled around the wing-body section to define an internal environment that is sealed from an external environment for containing contaminants including at least one of vapors, overspray, and liquids generated during application of one or more of coatings, sealants, and adhesives to localized areas of the wing-body section.

Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.

Abstract: A nanosatellite with an illumination element, and an arrangement of nanosatellites in low earth orbit (LEO) arranged to controllably apply their illumination to be visible on the ground. The nanosatellites may be coordinated to provide illumination events visible on the ground at particular locations and particular times. Each nanosatellite has an illumination element that provides a sustained external illumination event being of at least momentary duration and to be visible from the ground. The event forms at least part of a display for viewing from the ground.

Abstract: One aspect of the disclosure is a method of packaging a plurality siding panels. The method includes providing a plurality of siding panels, each siding panel having a front face, a rear face, top edge, a bottom edge, and a support member secured to the rear face, placing a first siding panel vertically within a box, the box having a first side, a second side, a top side, and a bottom side, and placing a second siding panel vertically within the box next to the first siding panel.

Abstract: An apparatus for dispensing lids has at least one magazine lane including an entrance end, an exit end, and a longitudinal length defined therebetween. The at least one magazine lane further includes a plurality of side guides along the longitudinal length for guiding the lids therebetween and a pair of rollers for carrying the lids thereon. The apparatus further has a throat plate at or near the exit end, the throat plate including an opening. At least one of the throat plate, the side guides, or the rollers is adaptable so as to accommodate different sizes and/or shapes of lids.