Abstract: A springer front end assembly for a motorcycle is provided. The assembly is generally universal in that it can be incorporated with substantially any make and/or model of a motorcycle to replace the front end suspension of the motorcycle with a springer front end suspension. Few to no modifications are made to the motorcycle. A spring retainer is added to the components of the front end of a motorcycle, and springs or other resilient members are included to provide the suspension for the springer front end. A method of replacement is also included, wherein the existing front end of a motorcycle is replaced with a springer assembly.

Abstract: An electronically controlled suspension system for a bicycle includes at least one spring element between first and second parts the bicycle, both parts being movably interconnected. At least one parameter of the spring element is modified. At least one actuator influences the spring element to modify the at least one parameter. An electronic module produces a control signal for the at least one actuator. A control device is influenced by the control signal produced by the electronic module. The control device is connected to at least one of the electronic module and the actuator through a radio signal. A corresponding method controls the suspension system for the bicycle and a computer program executes the method.

Abstract: “IMPROVEMENTS INTRODUCED IN AN ELLIPTICAL DRIVE MECHANISM AND A STEERING MECHANISM, APPLICABLE TO VELOCIPEDES IN GENERAL,” more specifically, it is about elliptical velocipedes (1) of the bicycle, tricycle, and scooter type, with said velocipedes having a tubular crossmember (2A) where the basic components are mounted, namely: fork (2b), handlebar mounting (2c), front wheel, rear wheel, center sprocket, and cranks, as well as an elliptical drive mechanism (M1) and a steering mechanism (M2). The structural frame (2) has a crossmember (2A), whose end is aligned with the imaginary center of the rear wheel, a tubular transverse shaft with tubular connections (3a) installed on its end portions, while a guide rod (3) that functions as a path for the sliding of the respective block (4) is attached to each of said connections.

Abstract: A motorcycle has an engine and an exhaust gas pipe which is connected thereto, as well as a motorcycle rear wheel swingarm. The motorcycle rear wheel swingarm has a closed cavity which is in fluid connection with the exhaust gas pipe by way of a connecting element.

Abstract: A seagoing vessel having within its hull a plurality of longitudinally placed structural tubulars running the length of the tubeship. The tubulars are placed side by side and attached to each other and to the underside of the tubeship deck. According to one design, the tubeship hull is constructed upside down, layer by layer.

Abstract: A boat includes a hull, a deck and a living area, the latter delimited at the front by a windscreen and having a fixed structure, extending from that area, supporting boat functional members such as antennas and the like, there being a one-piece mobile rigid canopy, moved by moving members and adapted to take at least a first working position in which it is arranged above the living area and at least a second working position in which it is separated from the latter and is associated to the deck in front of the windscreen, the rigid canopy resting on and being constrained to the windscreen and to the fixed structure when it is in its first working position. The moving members are articulated structures placed laterally to the deck.

Abstract: A watercraft includes a hull provided with a stern compartment inside the hull, the compartment being closed at least on the bottom by a movable portion of a stern platform arranged at one end of the compartment itself which opens up astern of the watercraft, wherein the movable portion can be lowered relative to the hull into the water where the watercraft is floating. The movable portion of the stern platform shifts with a translational motion along the hull without moving away therefrom.

Abstract: A lifting device to retrieve a marine vehicle comprises a lifting arms portion pivotally connected with a vehicle capture portion. The lifting arms portion and the vehicle capture portion rotate independently of each other. The vehicle capture portion comprises a capture connector having a probe for insertion into a latch opening in the vehicle to thereby attach the vehicle to the lifting device. The lifting arras portion further comprises two lifting arms and two vehicle pads for engaging the vehicle when it is captured. As the vehicle rolls during recovery operations, springs disposed between the vehicle capture portion and lifting arms portion dampen rotational motion. Lift line connections are provided on distal ends of the vehicle capture portion, and the lifting arms.

Abstract: A submersible active support structure for turbine towers and substations or similar elements, in offshore facilities, which is made up of hollow concrete bodies joined together by means of segments or beams, through which water passes from one body to another, with a pumping system that regulates the inclination of the structure based on the overturning moment, equipped with means for regulating immersion, which regulate the amount of water in the hollow bodies such that, in its working position, the center of gravity of the structure is below the center of buoyancy thereof, and the area of the cross-section of the structure at the waterline is smaller than the sum of the submerged cross-sections of said hollow bodies. In addition, the assembly may operate with a traditional mooring system.

Abstract: A system for controlling a towrope winch may comprise a computing device configured to send and receive data to and from the towrope winch, and a towrope winch application configured to operate on the computing device, in which the computing device is configured to operate the towrope winch based on data inputted by the user to the towrope winch application. A towrope winch user interface may comprise a processor configured to send and receive data to and from a towrope winch, and a towrope winch application configured to operate with the processor, in which the processor is configured to operate the towrope winch based on data inputted by the user to the towrope winch application.

Abstract: The present invention includes: first and second tanks and each configured to store a fluid containing fine powder; a communication pipe through which the first and second tanks and communicate with each other; and a transfer portion configured to transfer the fluid stored in a desired one of the first and second tanks to the other tank. Each of the tanks and includes a first chamber and a second chamber that are separated by a deformable dividing wall. Each of the first chambers stores an incompressible fluid, and each of the second chambers stores the fluid having higher specific gravity and viscosity than the incompressible fluid. The second chambers of the first and second tanks communicate with each other through the communication pipe. When the incompressible fluid is supplied to the desired first chamber, the transfer portion can discharge the incompressible fluid from the other first chamber.

Abstract: An active heave compensation system comprises a motor generator to interact with a load so as to drive the load in a first part of a heave motion cycle and to regenerate at least part of energy with which the load has been driven in a second part of the heave motion cycle, and an electrical storage element for storing the regenerated energy. The active heave compensation system further comprises a power supply electrically connected to the motor generator and the electrical storage element for providing electrical power to at least the motor generator, and a control unit configured to control the power supply substantially in synchronism with the heave motion.

Abstract: This invention is directed to a watercraft launch and storage assembly including: a mounting assembly; a first step; a watercraft cage pivotally carried by the mounting assembly having a launch position and a storage position; a continuous loop included in the watercraft cage for receiving and surrounding at least a portion of a watercraft; and, a watercraft cage plane defined through the watercraft cage that is generally perpendicular to the waterline when the watercraft cage is in the storage position so that when a watercraft is received by the watercraft cage and in the storage position an angle defined between a plane running through the width of the watercraft and the watercraft cage plane is greater than 90° reducing the amount of water and debris that can enter the watercraft in the storage position.

Abstract: A submersible vessel comprising: an elongated hull; at least one propeller mounted on a forward end of said hull and adapted to move said hull through water; said at least one propeller being of a size and configuration such that when it is rotated at an appropriate speed, it generates supercavitated water flowing from said at least one propeller and thence along an outer surface of said hull so as to diminish friction on the outer surface of said hull and facilitate high underwater speeds.

Abstract: Disclosed herein are an underwater docking system and a docking method using the system. An exemplary embodiment of the present invention relates to a system for docking a target body on a docking station under water, the system comprising: a guide unit provided to the docking station to transmit at least one guide signal to the target body; an agent unit connected to the docking station by a smart cable and disposed at a position spaced apart from the docking station so that the agent unit is moored under the water in a direction corresponding to a tidal current; and the target body configured to be guided toward the agent unit by the guide signal and then connected to a portion of the agent unit.

Abstract: A waterproof floatation case is provided for an outboard motor which is suitable for use during deployment for covert operations with an inflatable motor craft. The encased propulsion unit can be mounted without the need for removing the case and the two panels of the case butterflied between the motor and watercraft to permit full operation of the motor. A 2-way valve permits suction to be drawn down on the case evacuating excess air and corrosive fluids from the encased motor.

Abstract: The present invention relates to a rim driven propeller unit for a vessel, where a number of permanent magnets (4) are arranged round the propeller unit's rotatable rotor housing (1), comprising a number of propeller blades (3), and a number of permanent magnets round the propeller unit's external, stationary casing (2) housing the rotatable rotor housing, where the permanent magnets round parts of the rotatable rotor housing and the external, stationary casing's circumference are provided located above one another with like polarity, while other parts of the rotatable rotor housing and the external, stationary casing are provided located facing one another with opposite polarity, whereby the rotor housing and the stationary casing are repelled by and attracted to one another respectively, thereby being prevented from coming into contact with one another.

Abstract: An aircraft fuselage panel system for an aircraft of the type having a tubular fuselage frame includes a plurality of generally U-shaped frame members are each adapted to receive a portion of the tubular fuselage frame therein. Each frame member includes a plurality of apertures therethrough. A plurality of metal tabs are fixed to the tubular fuselage frame and include at least one aperture therethrough axially aligned with one of the apertures of one of the frame members. A rigid panel is adapted for fixing between each metal tab and the frame members. Each panel has a plurality of apertures therethrough each axially aligned with one of the apertures of the metal tabs and the frame members. A plurality of mechanical fasteners are adapted for fixing the panel between each metal tab and one of the frame members. The panel and frame member are fixed to the fuselage frame thereby.

Abstract: A rotary wing aircraft comprising a fuselage, a cabin volume enclosed by the fuselage, a main rotor arranged above the fuselage, a tail rotor mounted on a tail, the tail being attached to a rear part of the fuselage supporting the tail at its rear end, whereas the tail includes two beam boom elements, one element extending at the port side and the other element extending at the starboard side of the rotary wing aircraft, the front root end of each element being hinged to the corresponding lateral side of the fuselage, and both elements being canted with respect to the longitudinal axis of the rotary wing aircraft so as to be interconnected to each other at the rear portion of the tail.

Abstract: A method for producing a connecting element for at least two components of an aircraft structure. A hollow initial profile is formed comprising a wall following a closed path in the initial profile cross-section. The wall has a first, second and third section. Material is removed from the wall in one region of the initial profile, to obtain one opening in the one region, the opening extending at least partially within the first section. A portion of the second section and a portion of the third section form part of the connecting element and are each formed so as to be adapted to at least partially abut against the structure. The one opening is formed such that material initially forming part of the wall in the first section and remaining after the formation of the opening forms a stabilizing section connecting the portions of the second and third sections.

Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

Abstract: A hatch assembly for use in a vehicle is provided. The hatch assembly includes a hatch structure including an upper portion and a lower portion, an armrest support rail coupled to the hatch structure and defining a shade slot between the hatch structure and the armrest support rail, and a shade sized for insertion through the shade slot. The shade is configured to selectively translate between the upper portion and the lower portion of the hatch structure through the shade slot.

Abstract: A seat rail cover for a seat rail includes a first longitudinal section and a second longitudinal section. The first longitudinal section includes a first cover element and a first support element. The first support element extends in a longitudinal direction of the seat rail cover and protrudes from the first cover element transversely to the longitudinal direction. The second longitudinal section includes a second cover element and a second support element. The second support element extends in longitudinal direction and protrudes from the second cover element transversely to the longitudinal direction. The first longitudinal section is movable in longitudinal direction of the seat rail cover with respect to the second longitudinal direction from a non extended state to an extended state. Such a seat rail cover provides a variable length and may improve the dispersion of loads applied to the cover elements of the seat rail cover.

Abstract: A drive mechanism for deforming a skin of a deformable structural component of a fluid-dynamic flow body to provide a space-saving drive concept for large deformations under great loads. The drive mechanism comprises a linearly movably driven linear movement unit, and a transmission element configured to translate linear movement of the linear movement unit into rotary movement of a rotatably mounted load introduction device of the structural component to introduce a deformation force onto the skin.

Abstract: A fuel management system may include a first fuel tank and a second fuel tank. The fuel management system may also include an intelligent crossfeed valve positioned between the first fuel tank and the second fuel tank and configured to allow fuel to flow between the first fuel tank and the second fuel tank. The fuel management system may also include a sensor configured to detect an amount to which the intelligent crossfeed valve is open. The fuel management system may also include an engine controller connected to the sensor and configured to cause the intelligent crossfeed valve to close in response to the intelligent crossfeed valve being open a third predetermined amount.

Abstract: An air cushioned landing system for an air vehicle comprises an inflatable and deflatable skirt (113) in the form of a tube having inner (101) and outer (100) walls. The inner wall defines a central plenum (116) within the skirt, the skirt including gas pockets (130) arranged to stiffen one or more regions of at least one of the inner (101) and outer (100) sidewalls during deflation of the skirt. A gas pocket fan inflates the gas pockets prior to and during deflation of the skirt, wherein the gas pockets are constrained to move from a mutually spaced apart position when the skirt is inflated, to a mutually closely adjacent position when the skirt is fully deflated.

Abstract: An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) landing gear assembly that includes adjustable landing gear extension that may be extended or contracted so that the body of the UAV is contained in a horizontal plane when the UAV is landed, even on sloping surfaces. For example, when a UAV is landing, the slope of the surface may be determined and the landing gear extensions adjusted based on the slope so that the body of the UAV remains approximately horizontal when the UAV lands and is supported by the landing gear extensions.

Abstract: A suspension device (10) provided with at least one suspension means (20) comprising a flapper (21) performing pendulum motion, the flapper (21) being provided with a mass support (25) supporting at least one flapping mass (30). The mass support (25) is hinged to a carrier structure (2) for isolating and to a holder bar (15) for holding said mechanical assembly. The suspension device (10) includes at least one force generator (70), said suspension device (10) having at least one computer (50) connected to a measurement system (55) measuring the levels of vibration, and to said force generator (70) to regulate said amplitude and said phase actively by controlling the force generator (70) as a function of at least one measurement signal coming from said measurement system (55).

Abstract: An aerial vehicle may be equipped with propellers having reconfigurable geometries. Such propellers may have blade tips or other features that may be adjusted or reconfigured while the aerial vehicle is operating, on any basis. Propellers having reconfigurable blade tips joined to blade roots may cause the blade tips to be aligned with the blade roots, or substantially perpendicular to the blade roots, e.g., in order to counter adverse effects of tip vortices, or at any intervening angle. The propellers may be reconfigured at predetermined times during operation of an aerial vehicle, or upon sensing one or more operational characteristics or environmental conditions, as may be desired or required.

Abstract: Systems and methods for controlling an unmanned aerial vehicle within an environment are provided. In one aspect, a system comprises one or more sensors carried by the unmanned aerial vehicle and configured to provide sensor data and one or more processors. The one or more processors can be individually or collectively configured to: determine, based on the sensor data, an environment type for the environment; select a flight mode from a plurality of different flight modes based on the environment type, wherein each of the plurality of different flight mode is associated with a different set of operating rules for the unmanned aerial vehicle; and cause the unmanned aerial vehicle to operate within the environment while conforming to the set of operating rules of the selected flight mode.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for ground control point assignment and determination. One of the methods includes receiving information describing a flight plan for the UAV to implement, the flight plan identifying one or more waypoints associated with geographic locations assigned as ground control points. A first waypoint identified in the flight plan is traveled to, and an action to designate a surface at the associated geographic location is designated as a ground control point. Location information associated with the designated surface is stored. The stored location information is provided to an outside system for storage.

Abstract: A lightweight aircraft passenger seat assembly comprises at least one seat portion and at least one supporting portion for supporting the at least one seat portion relative to an aircraft structure. In order to provide an improved lightweight aircraft passenger seat assembly having a reduced weight, size and complexity as compared to conventional lightweight passenger seat designs, the invention provides a lightweight aircraft passenger seat assembly, comprising at least one seat portion with at least one seat shell for an aircraft passenger and at least one supporting portion for supporting the at least one seat portion relative to an aircraft structure, wherein the at least one seat shell and the at least one supporting portion are constructed as lightweight components.

Abstract: A seat for an aircraft is provided that includes a seat pan, having a seat pan front edge and a seat pan rear edge, a backrest, having a backrest top edge and a backrest bottom edge, where the backrest bottom edge is articulately disposed adjacent to the seat pan rear edge, a headrest, having a headrest top edge and a headrest bottom edge, where the headrest bottom edge is articulately disposed adjacent to the backrest top edge, a tracking device disposed beneath the seat pan and being attachable to a floor of the aircraft, the tracking device permitting the seat pan to translate in at least one of a lateral direction and a longitudinal direction, and a swivel connected between the tracking device and the seat pan, permitting the seat pan to rotate with respect to the tracking device.

Abstract: A device for securing an aircraft seat includes a base linked to the seat. The base includes a mechanism for fastening the base to a rail of an aircraft. The mechanism can be moved between locked and unlocked positions by an operating lever. The operating lever includes a visual indicator for indication of the locked and unlocked positions of the mechanism.

Abstract: In a method for controlling an aircraft air conditioning system, a heating or cooling demand of an aircraft region to be air conditioned is determined. A volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device which comprises a cylindrical stop housed in an extension of the second sleeve and comprising a front face against which a second end of the articulation spindle can come to bear, and a bolt-and-nut able to adopt a locked state, in which it passes through the stop and the extension so as to immobilize the stop in the extension, and an unlocked state, in which it does not pass through the stop and allows the stop to be removed from the extension.

Abstract: An acoustic liner that may be for a turbofan engine includes a first panel that may be non-permeable and a permeable panel spaced from the first panel. A non-permeable wall located between the first panel and the permeable panel faces in a first direction away from the first panel and a non-permeable wall, also between the panels, faces in a second direction away from the first panel and traversing the first direction. The liner may further include a plurality of sidewalls spaced from one-another, extending between the panels, and through the walls.

Abstract: One example of an aircraft fuel line assembly clamp member includes a c-shaped outer shell and a plurality of spokes. The c-shaped outer shell is sized to be positioned within an outer tube of an aircraft fuel line assembly. The plurality of spokes is arranged on an inner surface of the outer shell. The plurality of spokes protrudes from the inner surface towards a center of the outer shell to define a shape to receive an inner tube of the aircraft fuel line assembly. The plurality of spokes is also spaced apart on the inner surface.

Abstract: Apparatus and methods described herein provide for boundary layer flow sensor and corresponding determination of the flow characteristics of an ambient airflow over an aerodynamic surface. According to one aspect of the disclosure provided herein, the boundary layer flow sensor includes a body configured for mounting within or below the aerodynamic surface, a pressure port configurable between an open state for taking pressure measurements within the boundary layer of the ambient airflow and a closed state that protects the pressure port from contaminants when not in use.

Abstract: A graphical in-flight message representation system comprises a sensor configured to measure a characteristic of a flight of an aircraft and a communication device configured to send and receive in-flight messages. An in-flight message is a message communicated during the flight of the aircraft. The system also comprises a display unit configured to display a graphical flight progress indicator and one or more message icons, each of the one or more message icons corresponding to a respective in-flight message. The graphical flight progress indicator is representative of the characteristic of the flight measured by the sensor. Each of the one or more message icons are displayed in location relative to the graphical flight progress indicator based on the measured characteristic of the flight when the respective in-flight message was communicated.

Abstract: A satellite support structure to support at least one device of the satellite. The support structure includes structural elements with at least one of the structural elements being a damping connector linking at least two other structural elements of the support structure. The damping connector includes an elastomer element and at least one flat angle bracket having at least two wings to be linked by the respective connectors to the damped structural elements. The elastomer element is made from elastomer material with loss angle ? greater than ten degrees and is arranged such that the transmission of forces between one of the wings of the flat angle bracket and the connectors is achieved entirely via the elastomer element.

Abstract: A low-density article comprising a flexible substrate and a pyrolizable material impregnated therein, methods of preparing, and devices using the article are disclosed. The pyrolizable material pyrolizes above 350 C and does not flow at temperatures below the pyrolysis temperature. The low-density article remains flexible after impregnation and continues to remain flexible when the pyrolizable material is fully pyrolized.

Abstract: An aseptic filling machine of envelope-type bags provided with a filling mouth closed by a removable cap, comprising an empty bag supply device, a discharge device configured to discharge full bags, a carousel device on which at least two filling stations are located; each filling station comprising a sterile chamber; a raising device configured to raise the mouth of the empty bag internally of the sterile chamber; an overpressure device configured to place the chamber in slight overpressure; a removal device configured to remove the cap and positioning it by a side of the mouth; and a dispenser-batcher device that is vertically slidable and configured to engage with the mouth.

Abstract: In some embodiments, quality assurance systems for verifying branding of at least one medication container associated with at least one of a prescription and medication order are provided.

Abstract: A cardboard packaging is produced from a flat cardboard blank by simple manual folds and without using tools, and is used for packing elongate objects having bent ends. The cardboard packaging has a rectangular central portion and two rectangular side portions which are symmetrically arranged on opposing sides of the central region so as to be inclined at the same angle relative to the central portion, such that a concave upper face and a convex lower face of the cardboard packaging result. The front faces of the side and central portions, and the rear faces of the side and central portions each form parallel planes, overlap regions resulting between the side portions and the central portion. The surfaces of the side portions are each connected to the surface of the central portion by two tuck-in flap connections designed as counter-tuck-in flap connections.

Abstract: An overpack salvage drum including a drum body and a lid. A bottom wall and side wall of the drum body cooperate to define an interior of the drum body. The lid is configured to close an open top of the drum body. The lid includes at least two independent lid threads to engage with corresponding independent drum threads provided on the drum body. The lid includes a plurality of alternating castellations having a flat inner facing side and castellations having an arcuate inner facing side, which can be interdigitated with castellations on another lid when two lids are stacked together, or can be used to lock with a drum body to rotationally secure a drum body relative to the lid when in a stacked arrangement. The lids include lugs and recesses, or rings that allow for secure stacking of the lids.

Abstract: The reclosing mechanism for containers, particularly beverage containers, has the latch (3) fitted slidingly in the opening (5). Formed on the top side of the latch (3) there is an attachment (14) shorter than the opening (5) and narrower than the latch (3), where the attachment (14) is fitted with a pull tab (4) longer than the attachment (14) and fixed to the attachment (14) with a hinge (6) and a connector (7) which serves as the seal before the first opening. Formed on the opposite longitudinal sides of the attachment (14) there are catches (8) fitted slidingly on the guides (13) formed on the longer side walls of the opening (5). On the top surface of the element in which the opening (5) is made there are protrusions (10) formed on the side of the pull tab (4) front, on which the pull tab (4) rests and blocks the sliding of the latch (3) in the closed position.

Abstract: Disclosed is a self-assembly formed by a series of longitudinal members and cross members, all of the longitudinal members being identical to one other and all of the cross members being identical to one other, such that only two types of parts are required to construct the structure. Owing to the shape of the parts, they can be assembled to one another to create a solid structure without requiring any other connecting materials or elements. The longitudinal members comprise a series of slots into which narrowed segments of the cross members are inserted. Once the cross members have been inserted into the slots they are trapped therein by moving the longitudinal members and, in order to prevent this movement occurring in the opposite direction, other cross members are inserted into slots provided in the longitudinal members for this purpose.

Abstract: A front semiconductor opening wafer container for large diameter wafers includes a container portion and a door. The container portion includes a left closed side, a right closed side, a closed back, an open front, and an open interior including a plurality of slots for receiving and containing the wafers. The door is attachable to the container portion to close the open front and selectively latchable to the container portion. Optimized sag control is provided as well as enhanced structural rigidity, and wafer seating features.