Abstract: The present invention provides a bicycle comprising a pivot interface between a battery and a frame. The pivot interface includes a pivot mount defining a recess on one of the frame and the battery, and an eccentric boss on the other of the frame and the battery. The boss has a first boss width that is insertable into the recess when the battery is in a first position, and the boss further has a second boss width larger than the first boss width and creating an interference fit with the recess when the battery is in a second position. At least one of the pivot mount and the boss is resilient in order to accommodate the interference fit. Preferably, the pivot mount is on the frame and the boss is on the battery, and also the pivot mount preferably comprises a resilient material.

Abstract: A bicycle transmission device is basically configured to improve the detection accuracy of the tilt angle of the road surface. The bicycle transmission device has a transmission for changing the gear ratio of the bicycle, and a tilt sensor disposed on the transmission and that outputs a signal that reflects the inclination of the transmission.

Abstract: A bicycle transmission control apparatus is provided that can perform a shift control according to the traveling environment of the bicycle. The bicycle transmission control apparatus includes a controller that operates a transmission according to a parameter that represents a traveling state of a bicycle and predetermined shifting conditions. The controller sets the predetermined shifting condition based on the parameter representing a running state of the bicycle and on a tilt angle of the bicycle.

Abstract: A bicycle derailleur includes movable member, chain guide member and resistance applying member. The movable member is connected to linkage assembly. The chain guide member is pivoted to the movable member. The resistance applying member is connected between the movable member and the chain guide member. The resistance applying member includes pivot base, first engagement member and second engagement member. The pivot base includes pivot part and pressing part. The pressing part extends radially outwardly from the pivot part. The first engagement member is pivoted to the pivot part and pressed by the pressing part. The second engagement member is engageable with the first engagement member so that the first engagement member is only rotatable with respect to the second engagement member in a rotatable direction.

Abstract: A compact shift controller in a straddle type vehicle wherein the layout can be determined more freely, and a rider can mount and dismount the vehicle more easily. In a straddle type vehicle including a body frame; a footrest on which a rider places his/her foot; a shift lever arranged in front of the footrest, and rotated by the rider's operation by foot to shift gears of the vehicle; a shift detection mechanism for detecting operation of the shift lever and an engine supported to the body frame, the footrest is supported to a center frame constituting a part of the body frame below a seat of the rider, and the shift detection mechanism is connected to the shift lever, provided in front of the footrest and the center frame, and is supported to a lower frame constituting a part of the body frame.

Abstract: An anti-piracy device for ships comprises a blocking device, such as a metal plate, to block an opening from the exterior to the interior of a ship, such as a window or porthole. The anti-piracy device also includes mounts, which are mounted permanently to the interior wall of the ship, to which the blocking device can be removably fastened, by nuts or the like. This allows the device to be installed when entering dangerous waters, but removed and stored when traversing safe waters.

Abstract: A flexible lifting tether system for lifting a marine vehicle or object is described which is capable of significantly improving the primary characteristics of an existing cable by enhancing load-carrying capabilities (e.g. in air), modifying the tether to have altered specific gravities in water, and relieving torsional stresses when in operation.

Abstract: Certain aspects of the present disclosure generally relate to motion compensation between water-borne objects, and, more particularly, to synchronizing motion between a remotely operated vehicle (ROV) and a docking station of a launch and recovery system (LARS). An exemplary method includes receiving a measurement corresponding to a particle motion in water surrounding an ROV and synchronizing motion of a docking station with a motion of the ROV based at least in part on the measurement corresponding to the particle motion.

Abstract: A buoy comprising: an annular upper portion disposed on a lower portion; a drain hole disposed in the upper portion proximate to the lower portion; a handhold disposed in the upper portion distal to the lower portion; an attachment member disposed in the lower portion and protruding from a bottom of the lower portion, wherein the bottom is opposite the upper portion; and wherein at least one of the upper portion and the lower portion comprises a closed cell foam.

Abstract: A launch, recovery, and handling system includes a track system arranged on a deck of a ship and a stern door of the ship. The launch, recovery, and handling system also includes an aft cradle and a forward cradle that are connected to the track system and moveable in first and second directions along the track system. The aft cradle is moveable from a first position at a first area inside the ship to a second position on the stern door for at least one of launching and recovering a payload.

Abstract: The invention relates to a vessel comprising a FIG. 1a barge loading system (10) for loading a secondary vessel positioned alongside the vessel (1) with a mixture of water and material, comprising a discharge pipe (11) and a discharge head (12). The barge loading system (10) comprising at least two moveable crane arms (20) connected to the discharge head (12). The crane arms (20) being arranged to move the discharge head (12) to an overboard position. The crane arms (20) comprise respective base arm portions (21) rotatably connected to a deck (2) of the vessel (1) and respective remote arm portions (22). The remote arm portions (22) are with one end rotatably connected to respective base arm portions (21) and with another end connected to the discharge head (12). The barge loading system (10) comprises cable systems arranged to move the base arm portions (21) and the remote arm portions (22).

Abstract: A personal floatation assembly includes a housing that has a first end, a second end, a first lateral side, a second lateral side, a top wall and a bottom wall. The housing is comprised of a flexible and air impermeable material such that the housing can be inflated to support a body on water. A torso support is positioned on the top wall. The torso support is elongated and extends between the first lateral edge and the second lateral edge. The torso support is spaced between 2.0 feet and 3.0 feet from the first end and is spaced from the second end at least 2.0 feet. The torso support is comprised of a flexible and air impermeable material such that the torso support can be inflated.

Abstract: A securing arrangement for securing a water craft fin to a water craft having a fin plug, the fin plug having a first open cavity configured to receive a base portion (4018) of the water craft fin. The securing arrangement includes a resilient biasing rod (4030) and a protruding member (4035) cooperating with the biasing rod (4030). The protruding member (4035) is adapted to actuate when the base portion (4018) of the fin is inserted into the first open cavity of the fin plug so that the biasing rod (4030) and the protruding member (4035) inhibit removal of the fin from the first open cavity.

Abstract: A tourniquet device includes a tourniquet strap having an outward facing surface and an inward facing surface, the outward facing surface being covered with a plurality of hook fasteners, the inward facing surface having a section that is provided with a plurality of loop fasteners, a first end and a second end, the first end comprising a buckle, the second end having a cavity, and a securement strap configured for storage within the cavity, the securement strap including a terminal end that includes a pull tab, the securement strap is configured to be selectively placed in a stored position and a deployed position.

Abstract: The present invention is an inflatable safety garment. The invention preferably defines an inflatable safety Jacket having improved deployment cushion fill rates and standup times and having a simplified mechanical activation system. The inflatable safety garment is useful in mitigating or preventing injury that may otherwise occur to the wearer of the inflatable safety garment if the wearer were to not wear the inflatable safety garment and be involved in an accident or crash.

Abstract: The patent discloses a multihull watercraft with a unique hull configuration providing numerous benefits. By relocating the passenger cabins from the float hulls to the upper hull, the accommodation space and the float hulls may be independently optimized. The new configuration also provides reduced windage, and creates additional deck space for easier boarding, recreational use, and safer access to shore craft. A new sailing rig is also disclosed that is easier to operate and maintain than the conventional Bermuda rig. The entire rig can be rotated with a single winch or control wheel to achieve the optimum angle of attack into the wind.

Abstract: A system and method control a trim device that positions a trimmable marine apparatus with respect to a marine vessel. A trim system is operated in an automatic mode, in which a controller sends signals to actuate the trim device automatically as a function of vessel or engine speed, or a manual mode, in which the controller sends signals to actuate the trim device in response to commands from an operator input device. An operating speed of the propulsion system is determined. When the operating speed has crossed a given operating speed threshold, the trim system is subsequently operated in the automatic or manual mode depending on whether the operating speed increased or decreased as it crossed the operating speed threshold and whether the trim system was operating in the automatic or manual mode as the operating speed crossed the operating speed threshold.

Abstract: A trim control system automatically controls trim angle of a marine propulsion device with respect to a vessel. A memory stores trim base profiles, each defining a unique relationship between vessel speed and trim angle. An input device allows selection of a base profile to specify an aggressiveness of trim angle versus vessel speed, and then optionally to further refine the aggressiveness. A controller then determines a setpoint trim angle based on a measured vessel speed. If the user has not chosen to refine the aggressiveness, the controller determines the setpoint trim angle from the selected base profile. However, if the user has chosen to refine the aggressiveness, the controller determines the setpoint trim angle from a trim sub-profile, which defines a variant of the relationship between vessel speed and trim angle defined by the selected base profile. The control system positions the propulsion device at the setpoint trim angle.

Abstract: Some embodiments are directed to a transmission that includes an input shaft connected to a crankshaft, an output shaft contained within a transmission housing, an input gear contained within the transmission housing and connected to the input shaft, and an output gear contained within the transmission housing and connected to the output shaft and engaging the input gear. A directional gear assembly is contained within the transmission housing at a location between the output shaft and the drive shaft. The directional gear assembly includes a first configuration in which the output shaft drives the drive shaft in a first rotational direction, a second configuration in which the output shaft drives the drive shaft in a second rotational direction that is opposite to the first rotational direction, and a third configuration in which the drive shaft is disconnected from the output shaft.

Abstract: An electronic Control system for controlling a water vessel in regards to its propulsion, and thrust vectors and its steering. A helm wheel that has an electronic output that governs the steerage of a water vessel. The control system determines the reactive speed and number of turns needed to accomplish a given turn, this pre-selected speed and distance traveled gives the rudder two different sets of parameters for full rotation of the Helm wheel from full rudder to the Port to full rudder to the starboard The rudder or outboard motor has a sensor that gives the control system information by way of a variable voltage as to its direction and where the rudder is parked. The steering actuator has a dual motor set up that supply's enough power and torque to control the steering cable and slide bar of three outboard engines.

Abstract: An intelligence, surveillance, and reconnaissance system is disclosed including a ground station and one or more aerial vehicles. The aerial vehicles are autonomous systems capable of communicating intelligence data to the ground station and be used as part of a missile delivery package. A plurality of aerial vehicles can be configured to cast a wide net of reconnaissance over a large area on the ground including smaller overlapping reconnaissance areas provided by each of the plurality of the aerial vehicles.

Abstract: A flexurally controlled system (100) comprises an elongated structure (102), a tendon (112) attached to the elongated structure (102), and an actuator (118) operable to apply a tensile load to the tendon (112). The actuator (118) is operable to apply the tensile load to the tendon (112) when at least one of the first side (108) of the elongated structure (102) is under a first tensile stress or the second side (110) of the elongated structure is under a first compressive stress. The actuator is also operable to apply no load to the tendon (112) when the first side (108) and the second side (110) of the elongated structure (102) are not under stress. The tendon (112) is non-coaxial with a central axis (122) of the elongated structure (102) and is aligned with at least one region of the elongated structure (102).

Abstract: A stiffened fuselage component made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element and a plurality of elongated stiffening elements forming a stiffening element pattern comprising a plurality of node points and being attached to an inner surface of the skin element. At least some of the node points are defined by an intersection of at least two stiffening elements at an acute angle or an obtuse angle. At least some of the elongated stiffening elements are shaped so as to define an internal cavity delimited by an inner surface of the stiffening elements and covered by the skin element.

Abstract: An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.

Abstract: A fuselage skin window unit for an aircraft, an aircraft with such a fuselage skin window unit and a method for manufacturing such a fuselage skin window unit are described. The fuselage skin window unit includes a fuselage skin section and a window pane section. The fuselage skin section is part of a fuselage skin of the aircraft and has a pattern of pinhole perforations. The window pane section is transparent and arranged so that it covers the pinhole perforations.

Abstract: An asymmetric aircraft (1) and an aircraft (1) that can operate from small ships (8) and be stored in high density with three aircraft or more in one helicopter hangar (107) without needing a landing gear or wing fold. These aircraft slide into and out of the hangar on dollies (90) like circuit boards in a computer and are launched and recovered using a large towed parafoil (6).

Abstract: Embodiments described herein relate to multicopters with separate engines to power each rotor, wherein the multicopters also include with unique controls to guide the multicopter.

Abstract: A self-righting aeronautical vehicle comprising a hollowed frame and a lift mechanism. The exterior of the frame and center of gravity are adapted to self-right the vehicle. The frame can include sealed, hollowed sections for use in bodies of water. The frame can be spherical in shape enabling inspection of internal surface of partially or fully enclosed structures. Inspection equipment can be integrated into the vehicle and acquired data can be stored or wirelessly communicated to a server. A controlled or other mass can be pivotally assembled to a pivot axle spanning across the interior of the frame. The pivot axis can rotate about a vertical axis (an axis perpendicular to the elongated axis). The propulsion mechanisms can be adapted for use as a terrestrial vehicle when enclosed in a sealed spherical shell.

Abstract: Systems and methods using an Unmanned Aerial Vehicle (UAV) to perform physical functions on a cell tower at a cell site include flying the UAV at or near the cell site, wherein the UAV comprises one or more manipulable members; moving the one or more manipulable members when proximate to a location at the cell tower where the physical functions are performed to effectuate the physical functions; and utilizing one or more counterbalancing techniques during the moving ensuring a weight distribution of the UAV remains substantially the same.

Abstract: A method of aircraft fuel distribution includes selecting a longitudinal center of gravity and predicting a rate of change of the center of gravity during flight. Fuel is located in a tail fin tank of a vertical tail fin of the aircraft, and is transferred from the tail fin tank forward at a predetermined transfer rate to counteract the predicted rate of change thereby maintaining the selected center of gravity. An aircraft fuel distribution system includes a center main fuel tank, a tail fin tank and a tail fin fuel pump to pump fuel between the tail fin tank and the center main fuel tank. An electronic controller operates the tail fin fuel pump such that fuel is flowed between the tail fin tank and the center main fuel tank at a predetermined transfer rate to maintain automatically an optimal position of a longitudinal center of gravity of the aircraft.

Abstract: A system and method for robust lift generation through flow separation suppression are presented. A fluid flow is ejected over a lifting surface from a fluid ejection orifice, and a flow direction of the fluid flow over the lifting surface is directed using a plurality of vanes configured in the fluid ejection orifice. The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes.

Abstract: A drag reduction system for an aircraft may include an air ejector having an ejection port located between an aft portion of an airfoil main element and a forward portion of a trailing edge device. The air ejector may be configured to discharge an air jet from the ejection port in such a manner that the air jet passes over the upper surface of the trailing edge device.

Abstract: A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel.

Abstract: A method of preloading an aircraft assembly involving a step of operating an extendible preloading tool to move a landing gear strut to decrease the distance between first and second link attachment joints for attachment of a preloading linkage. A tool and aircraft assembly are also provided.

Abstract: A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

Abstract: A lockable actuator has lock segments that move into recesses inside a piston to enable the piston to move. The lock segments may also move radially outwardly from the recesses in the piston to engage a bevel edge of a cylinder housing assembly to lock the piston. Lock rams having ramps force the lock segments radially outwardly into engagement with the bevel edge of the cylinder housing assembly.

Abstract: An aircraft landing gear arrangement comprises a nose landing gear assembly and at least one main landing gear assembly. The nose landing gear assembly has a nose landing gear wheel with a high energy brake apparatus therein. The main landing gear assembly has a main landing gear wheel with a high energy brake apparatus therein and a main landing gear wheel with a motor therein. The motor is used for driving the main landing wheel during taxiing of the aircraft.

Abstract: An aircraft landing gear assembly includes a mechanical structural linkage having a shock absorber and a linkage abutment which are biased apart by a mechanical spring. The force required to deform the spring sufficiently to place the linkage abutment at a predefined distance with respect to the shock absorber abutment is less than the breakout force of the shock absorber.

Abstract: A method of driving rotation of a rotor of an aircraft, said aircraft having at least two fuel-burning engines and an electric motor suitable for driving rotation of said rotor. Said rotor is driven by using said engines together. An authorization is generated only during at least one predetermined stage of flight, said authorization authorizing the use of the electric motor in order to drive said rotor in rotation. While said authorization is valid and if one of said engines has failed, then an operation order is generated to require said electric motor to operate. While said operation order is valid, said rotor is driven by each engine that has not failed together with said electric motor.

Abstract: A rotor hub assembly is provided including an open rotor hub having a base plate and a plurality of rotor members mounted about a circumference of the base plate. The rotor members are configured to form a plurality of rotor blade openings between adjacent rotor members, and a central opening between all of the rotor members. A plate includes a central body portion and a plurality of arms. Each of the plurality of arms is configured to mount to one of the plurality of rotor members such that the central body portion is generally positioned within the central opening of the open rotor hub.

Abstract: According to one embodiment, a flight control device includes a grip, a stick associated with the grip, and a gimbal. The stick defines a first axis. The gimbal includes a first platform, a second platform, a first electro-rheological elastomeric bearing, and a second electro-rheological elastomeric bearing. The first platform is coupled to the stick and configured to rotate on a second axis that is perpendicular to the first axis. The second platform is in mechanical communication with the first platform and configured to rotate on a third axis that is perpendicular to the second axis. The first electro-rheological elastomeric bearing defines the second axis, and the second electro-rheological elastomeric bearing defines the third axis. The first and second electro-rheological elastomeric bearing being configured to each have a variable stiffness.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that includes a substantially polygonal perimeter frame and a central frame. The perimeter frame includes a front wing, a lower rear wing, and an upper rear wing. The wings provide lift to the UAV when the UAV is moving in a direction that includes a horizontal component. 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 (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV may also include one or more thrusting motors and corresponding thrusting propellers. When the UAV is moving horizontally, the thrusting motor(s) may be engaged and the thrusting propeller(s) will aid in the horizontal propulsion of the UAV.

Abstract: A system for a tail-sitter aircraft includes a fuselage having one or more propellers, a wing structure coupled to the fuselage, and a drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member. The drag rudder assembly is configured to produce a stabilizing force on the wing structure during higher speeds of the aircraft in tandem rotor flight.

Abstract: In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.

Abstract: Submersible unmanned aerial vehicles (UAVs) and associated systems and methods are disclosed. A representative submersible UAV includes a support structure, a power source carried by the support structure, and a plurality of propellers carried by the support structure and coupled to the power source. The propellers can include a plurality of first laterally spaced-apart propellers positioned above a plurality of second laterally spaced-apart propellers along an axis extending upwardly from the support structure.

Abstract: A vehicle constructed in the shape of tetrahedral. The vehicle may be an aircraft, a space-craft, a sub-surface vehicle, or an unmanned drone. A tetrahedral body component is one of: a regular tetrahedron, an extended tetrahedron, a foreshortened tetrahedron, a tapered tetrahedron, and a truncated tetrahedron. A means for propulsion is mounted to at least one of the faces of the tetrahedral body component. The means for propulsion may include a turbine engine, a water jet, a gas jet, or electromagnetic propulsion. In another embodiment, the means for propulsion include an engine and a propeller. The engine block is mounted internal to the tetrahedral body component, and is located at the intersection of a tetrahedral shape with a cube shape. The engine block is mounted to the tetrahedral body component by struts perpendicular to the faces of the engine block.

Abstract: An aircraft having a main body defining a passenger compartment therein, an upper shell portion above the main body and a lower shell portion below the main body, further includes a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another. An engine assembly is supported on the main body in communication with a central thrust opening in the lower shell portion so as to be arranged to provide upward thrust to the main body.

Abstract: Conception introduced for performing powered flight of aircraft by performing work against gravity force, using gliding wing as steady support, namely “flying elevator” conception, and aircraft developed, based on cyclorotor scheme with elaborated steering solution, continuing in flexible handling and control. Said aircraft correctly and optimally implements said conception after presented detailed modeling, simulation and analyzing, having ability for flight with exceptionally high propulsion efficiency, moderate lift to drag ratio and short takeoff and landing. Additionally, it has ability for recuperative descent and deceleration, utilizing direct driving from high torque electrical engines, which can optionally hybridized with combustion engine, and covers speed range up to limits of subsonic flight.

Abstract: This disclosure is generally directed to an Unmanned Aerial Device (UAV) that uses a removable computing device for command and control. The UAV may include an airframe with rotors and an adjustable cradle to attach a computing device. The computing device, such as a smart phone, tablet, MP3 player, or the like, may provide the necessary avionics and computing equipment to control the UAV autonomously. For example, the adjustable cradle may be extended to fit a tablet or other large computing device, or retracted to fit a smart phone or other small computing device. Thus, the adjustable cradle may provide for the attachment and use of a plurality of different computing devices in conjunction with a single airframe. Additionally the UAV may comprise adjustable arms to assist in balancing the load of the different computing devices and/or additional equipment attached to the airframe.

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.