Abstract: A boat includes a boat body, a propulsion unit, a steering wheel that turns about a first turning axis and has a circular or substantially circular shape or an arcuate or substantially arcuate shape about the first turning axis, and an operator unit on the steering wheel including a first operator which is located in a first direction with respect to the first turning axis and a second operator which is located in a second direction with respect to the first turning axis, and that performs a throttle operation and a shift operation on the propulsion unit.

Abstract: The invention relates to an arrangement of one or more cryogenic tank containers for storing liquefied natural gas (LNG) or compressed natural gas (CNG) on an open deck of a tugboat. The one or more cryogenic tank containers are removably mounted on and at an aft deck area of the tugboat and are provided with means for supplying LNG or CNG to the engine of the tugboat.

Abstract: Embodiments of the present invention are directed to a passive, automatic wing-control mechanism for sailing vessels. A cam is attached to one end of a rotatable mast as part of a rotatable wing, and a tensioner is configured to exert a constant force perpendicularly against the cam. When a wing is in a no-go sailing angle with respect to an apparent wind, the cam does not exert a torque on the mast. When the wing is outside the no-go sailing angle, the cam exerts a counter-torque to a torque caused by the apparent wind acting on the rotatable wing, causing the wing to remain at a predetermined angle with respect to the apparent wind.

Abstract: The purpose of this invention, which is referred to as a vacuustat, is to generate buoyancy in the atmosphere by means of an evacuated or partially evacuated container, rather than by using a lighter-than-air lifting gas such as hydrogen or helium. This particular vacuustat design comprises a flexible airtight membrane supported by a fractal tensegrity internal structure consisting of a relatively small mass of compressive members forced into higher-order buckling modes through use of tension members. The advantages of such a design over conventional aerostats include superior buoyancy control for ascent and descent, greatly increased flight endurance, and cost-effectiveness in operation. This particular vacuustat design has a much greater lifting efficiency than previous designs, and should also be easier and more cost-effective to manufacture.

Abstract: An energy dispersion plug for use in an unmanned aerial vehicle (UAV) includes a blunt head section, a wedge section, and a rim section. The blunt head section has an outer side for receiving an impact force and an inner side opposite the outer side. The wedge section has a base end and a distal end opposite the base end. The wedge section extends at the base end from the inner side of the blunt head section towards the distal end and the distal end has a smaller cross-sectional area than the base end. The wedge section is shaped and sized to fit into an open end of a hollow structural member of the UAV and to transfer impact energy incident upon the blunt head section into the hollow structural member to shatter the hollow structural member into fragments.

Abstract: A fuselage portion of a vehicle (e.g., an aircraft) is disclosed. The fuselage portion comprises a frame; a floor beam attached to the frame and comprising ends; a structural stanchion comprising a first end and a second end; a first structural coupling joining the first end of the structural stanchion and the floor beam; a second structural coupling joining the second end of the structural stanchion and the frame; a non-structural stanchion comprising a third end and a fourth end; a first non-structural coupling joining the third end of the non-structural stanchion and the floor beam; and a second non-structural coupling joining the fourth end of the non-structural stanchion and the frame.

Abstract: A lock mechanism includes a snapping part and a pressing part configured to be slidably connected with a first body. The pressing part includes a pressing end and an abutting end opposite to the pressing end. The abutting end is configured to abut against the snapping part to make the snapping part engage with a second body and to lock the second body onto the first body.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: A split winglet has a leading airfoil (LA) comprising a LA leading edge, a LA trailing edge, a LA upper surface, and a LA lower surface. The split winglet also has a trailing airfoil (TA) comprising a TA leading edge, a TA trailing edge, a TA upper surface, and a TA lower surface. The split winglet further has a base connected to each of the LA and the TA, the base being configured for connection to a tip of a main airfoil.

Abstract: A bracket (24) for connecting a traverse (20) of a landing gear to a cabin of a helicopter. A landing gear retainer (5) is fixed around the traverse (20) coaxially to the longitudinal direction of the traverse (20) and at least one cabin clamp mount (7) is fixed to the cabin. The landing gear retainer (5) is in between the cabin and upper and lower pendulum bolts (12, 13) and upper and lower pendulum bearings (18, 19). A pendulum (9) is in longitudinal direction of the traverse (20) hinged to the landing gear retainer (5). The invention is further related to an application of such brackets (24).

Abstract: A levered landing gear including a first shock strut having a longitudinal axis, a second shock strut disposed concentrically with the first shock strut along the longitudinal axis such that the first shock strut and the second shock strut extend along a common extension axis, and a truck lever coupled to both the first shock strut and the second shock strut such that the second shock strut pivots the truck lever relative to the first shock strut.

Abstract: An aircraft landing gear shock absorber assembly having an outer casing having a bore which extends through the outer casing. The bore has a first opening and a second opening. A rod is slidably coupled within the bore such that a first end of the rod projects out of the first opening of the bore, the first end of the rod being arranged to be attached to a wheel assembly. A closure is provided for the second opening of the bore. The bore has a reduced width portion relative to the second opening of the bore, and the rod includes a radially enlarged portion that is wider than the reduced width portion of the bore.

Abstract: A drip pan apparatus for a helicopter includes a frame and a drip pan. The frame is secured to a skirt on the airframe of the helicopter. The apparatus includes a drip pan for cooperation with a frame to cover an access opening to a transmission. The drip pan includes a substantially planar member of a fiber-reinforced composite and has a seal surface that is configured to cooperate with a seal surface of the frame. A seal member may be disposed between the substantially planar member and the frame to form a fluid-tight seal. The fiber-reinforced composite may be a carbon fiber-reinforced composite. A method of making the drip pan apparatus includes placing a plurality of sheets of an uncured fiber-reinforced composite material on one another to form an uncured stack. The uncured stack is then cured. A frame and a drip pan may be cut from the cured stack.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

Abstract: Systems and methods for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation.

Abstract: A pedestrian with a cellphone is in a public area. He sees a drone airborne nearby. He rents the drone to control its actions. His phone shows a signal encoding his electronic address, like a phone number. The drone decodes and sends a message with an URL, deep link or linket. The latter is a brand of the drone owner that maps to a deep link. The deep link designates an app in an app store. He installs the app and interacts with the owner, taking control of the drone for a specified time. The app shows images from the drone camera. The drone can crowdsource public safety. And check the presence of players at locations in Augmented Reality games. It can distribute electronic prizes to players. It can distribute keys for cryptosystems. The drone can pick up data from users at different places. Drone-drone interactions can optimise drone routes. Drones can be used with a blimp and electronic billboards to increase crowd use of an app.

Abstract: An unmanned aerial vehicle includes a central body, a plurality of arms extendable from the central body, and a plurality of landing stands. Each of the plurality of arms is configured to transform between a flight configuration where the arm is extending away from the central body and a compact configuration where the arm is folded against the central body. Each of the plurality of landing stands is attached to a distal end of one of the plurality of arms. A first one of the plurality of landing stands is longer than a second one of the plurality of landing stands.

Abstract: Systems and methods using an Unmanned Aerial Vehicle (UAV) to supply one or more batteries include loading the UAV with the one or more batteries as cargo; causing the UAV to fly to a remote location; and at the remote location, inserting the one or more batteries in a battery system for powering thereof. The method can further include, at the remote location, retrieving a second set of one or more batteries from the battery system; and causing the UAV to fly back with the retrieved second set.

Abstract: Vehicles such as unmanned air vehicles that are capable of movement from an open, flight configuration to an enclosed configuration in which all major flight components can be protected by an outer shell are disclosed. In the enclosed configuration, the vehicles can take on standard geometric shapes such as a rectangular prism, sphere, cylinder, or another shape, so as to not be recognizable as an unmanned air vehicle. Embodiments of vehicles can also include interchangeable and/or wireless motor arms, motor arms which are electrically connected to the remainder of the vehicle only when in an open configuration, remote controllers removably attached to the remainder of the vehicle, and clip or other attachment mechanisms for attachment to objects such as backpacks.

Abstract: A lightweight, pocket-sized unmanned aerial vehicle (UAV) that can be held in an outstretched hand by a user for take-off and landing of the UAV. The UAV comprises a semi-toroidal or a substantially toroidal hollow body that defines a duct. The UAV further comprises a motor for rotating a fan that directs air into and out of the duct enabling the UAV to take flight. The UAV comprises a flight-control system that comprises at least two flight control surfaces that can alter the directed air as it flows through the duct for controlling the roll and pitch and optionally the yaw of the UAV during flight. The flight control system may be controlled by a microprocessor controller. The UAV further comprises a payload, with at least a wireless transmitter and receiver unit.

Abstract: Intermodal vehicles may be loaded with items and an aerial vehicle, and directed to travel to areas where demand for the items is known or anticipated. The intermodal vehicles may be coupled to locomotives, container ships, road tractors or other vehicles, and equipped with systems for loading one or more items onto the aerial vehicle, and for launching or retrieving the aerial vehicle while the intermodal vehicles are in motion. The areas where the demand is known or anticipated may be identified on any basis, including but not limited to past histories of purchases or deliveries to such areas, or events that are scheduled to occur in such areas. Additionally, intermodal vehicles may be loaded with replacement parts and/or inspection equipment, and configured to conduct repairs, servicing operations or inspections on aerial vehicles within the intermodal vehicles, while the intermodal vehicles are in motion.

Abstract: A tongue module for a partition, which can be mounted underneath a storage compartment in a passenger cabin of a passenger aircraft, has a base support, which can be attached to a fixed section of the partition. The fixed section can be mounted in the passenger cabin. The tongue module has a tongue, which is guided on the base support in such a way as to be movable, and a guiding device for the tongue. The guiding device has a first guiding section for the translational movement of the tongue between a release position and an intermediate position. A second guiding section is provided for the rotation of the tongue about a rotational axis between the intermediate position and a closed position.

Abstract: An installation arrangement comprising a first carrier element configured to fasten an overhead luggage compartment thereto. The first element includes a main body comprising a tubular opening, a barrel-shaped component arranged inside the tubular opening, the component comprising a through hole extending substantially perpendicular to a component longitudinal axis, and a fastener to fasten a portion of the overhead luggage compartment to the main body of the first carrier element. A second carrier element of the arrangement is a rotary joint connectable to an installation rail, the rotary joint being movable around a longitudinal axis of the installation rail and an axis perpendicular to that longitudinal axis. The installation arrangement also comprises a rod configured to be coupled with the second carrier element and to fit inside the through hole, wherein the rod is connectable to the first carrier element when the rod is arranged inside the through hole.

Abstract: A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

Abstract: A seating device comprises a seat bottom unit, in particular an aircraft seat bottom unit, having an accommodating region for receiving a module, in particular a lifejacket module, with at least one upper wall element which forms at least a support surface for a comfort element.

Abstract: A method of making a support arm includes heating a mold to a glass transition temperature of a thermoplastic material; injecting the thermoplastic material comprising a filler into the mold and allowing the thermoplastic material to conform to the mold; cooling the mold to an ejection temperature to form the support arm; and ejecting the support arm from the mold; wherein a cross-section of the support arm taken along a line from an inner edge to an outer edge of the support arm comprises a first “U” shaped portion and a second “U” shaped portion.

Abstract: Aircraft seat having a first seat element and a second seat element, the second seat element being mounted so as to be adjustable relative to the first seat element, a spring element that moves the second seat element relative to the first seat element being provided, it being possible for the force acting on the second seat element by the spring element to be released by an actuating element such that the spring element is deactivated in a first switching position of the actuating element, and the spring element is activated in a second switching position of the actuating element, where a force limitation element is provided, by which the force acting on the second seat element by the spring element can be limited to a predetermined value such that intermediate states between the first and the second switching positions can also be set.

Abstract: In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; and a plurality of passenger seats coupled to the floor panel, wherein: the plurality of passenger seats is arranged into a plurality of seating rows; and the plurality of passenger seats comprises one or more foldover seats arranged to facilitate access to one or more exits of the rotorcraft.

Abstract: An integrable seat leg for an original equipment manufacturer seat, including a vertical member, including a front end and a rear end, a first side surface and a second side surface, a top surface and a bottom surface, one or more engaging members extending from the bottom surface, and one or more through-bores arranged proximate the top surface to secure the integrable seat leg to the seat, wherein the one or more engaging members are operatively arranged to engage one or more respective apertures in track.

Abstract: A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air.

Abstract: Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, whether an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A convex-shaped housing is mounted to an aircraft and exposed to an airstream. The convex-shaped housing has a testing region that is monitored for ice accretion by an ice detector. A boundary locator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets up to the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of an atmosphere containing super-cooled water droplets that equal or exceed the predetermined size.

Abstract: A parachute is coupled to a rocket where the parachute is extracted by having the rocket pull on the parachute. A parachute strap couples the parachute to an aircraft where at a first point in time, a first section of the parachute strap and a second section of the parachute strap are both secured independently of each other. At a second point in time, the second section of the parachute strap is still secured while the first section of the parachute strap is released where the released first section of the parachute strap gradually becomes taut as the parachute is extracted.

Abstract: A tube connection system for an engine or aircraft includes a Coanda ring defining an annular tube segment which has a branch tube segment extending therefrom. A supply tube assembly defines a plurality of tube segments. Adjacent tube segments are moveably coupled to one another by one of a plurality of variable-positionable couplings. Another of the plurality of tube segments is moveably coupled to the branch segment by another of the plurality of variable-positionable couplings.

Abstract: An engine nacelle comprised of an inlet, an exhaust end, and a composite fan cowl. The composite fan cowl has a core with a thickness varying in a direction moving from the inlet to the exhaust end.

Abstract: A control system for controlling a controlled parameter of an aeronautical equipment device, the controlled parameter being governed by an operating law linking the controlled parameter to a command and to a plurality of input parameters, the control system including a control loop controlling the controlled parameter to a setpoint with the control of the device by the command, the system including an operating law compensation module and a determination module determining a local gain configured to determine the local gain of a static part of a model of the operating law representative of the gain of the controlled parameter in response to a variation in the command in a stabilised operating regime of the operating law, the operating law compensation module using the inverse of the local gain.

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract: Apparatus to store a drogue hose on an aircraft are disclosed herein. An example apparatus includes a pod to be attached to an aircraft to store a drogue hose, a drum disposed in the pod around which the drogue hose is coiled, where an axis of the drum is aligned with a direction of flight of the aircraft, guides to move along a length of the drum to guide the drogue hose as the drogue hose is coiled around the drum, and exit rollers adjacent to a drogue chute cave of the pod, the exit rollers to guide the drogue hose as the drogue hose moves through the drogue chute cave.

Abstract: An aircraft landing system for landing of an aircraft includes at least one force sensor and a processor. The at least one force sensor is coupled with a landing gear of the aircraft for sensing forces applied to the landing gear at a plurality of positions during landing at a landing zone. The processor is configured to receive force measurements from the at least one force sensor.

Abstract: A gimbal includes a rotatable frame assembly and a quick release structure configured to detachably mount a camera to the frame assembly. The frame assembly includes a connector configured to form an electrical connection between the gimbal and the camera.

Abstract: The present disclosure provides a camera mounting apparatus for an airborne oblique photogrammetric system that is simple in structure, scalable in the number of capturing cameras, and adjustable in tilt angle. The camera mounting apparatus includes: at least one oblique hanger plate for mounting an oblique camera, a parallel hanger plate securely connected to an aircraft chassis, and a tilt angle adjusting assembly for connecting the oblique hanger plate to the parallel hanger plate in an angle-adjustable manner. The tilt angle adjusting assembly further includes a first fixed bearing secured to the parallel hanger plate, a second fixed bearing secured to the oblique hanger plate opposite to the first fixed bearing, a hinged bearing hinging the oblique hanger plate to the parallel hanger plate, and an angle adjusting sheet connected between the first fixed bearing and the second fixed bearing.

Abstract: An unmanned aerial vehicle (UAV) system, location and method, for operation with a flight management system, has a controlled access UAV zone for at least one of: UAV landing, UAV loading, and UAV take-off. A sensor can be in communication with a control panel and/or a lock to govern access to the UAV zone. The zone can have a barrier with closure secured by the lock, and controlled by a flight management system. Separate access codes can be provided for departure and destination locations, to enable personnel associated with a delivery request to access those locations, to effect delivery of an article. The codes can be generated and supplied when the flight management system receives a valid delivery request.

Abstract: An aircraft tug apparatus for tugging an aircraft by an aircraft tire includes a turntable on a main base portion of the tug, capable of rotational movement relative to the main base portion. A tire cradle assembly on the turntable releasably holds the aircraft tire, and a latch mechanism holds the tire cradle assembly in a position that confines the aircraft tire. A pivoting arm coupled to the main base portion extends under the turntable. The pivoting arm includes a first plunger and a second plunger extending therefrom, with the first plunger coupled to the pivoting arm using a spring assembly allowing it to move up and down relative to the pivoting arm. The spring assembly is configured such that the pivoting arm may move the second plunger to engage the latch mechanism while the first plunger is impinged by the turntable.

Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (tmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.

Abstract: A service satellite for providing station keeping services to a host satellite has a body, and a gripping mechanism attached to the body. The gripping mechanism is adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring forms an interconnected unit having a combined center of mass. The service satellite has at least two movable thrusters and at least one controller. The at least one controller maintains the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters do not pass through the combined center of mass, and are each offset from the combined center of mass.

Abstract: The invention is an auto-packing apparatus for pouch, and comprises: a pouch conveyor 20, a slot magazine 50, a pickup means 60 to pick up the moving pouches 1 on the pouch conveyor 20 and insert them into the slots 51 of the slot magazine 50, a pouch retainer 100 to retain the pouches 1 dropping from the slot magazine 50, a moving means 130 to move one 80 of the side walls 70,80 of the pouch retainer 100 and an opening means 91 to open and close the lower part of the pouch retainer 100 and a controller 180.

Abstract: An apparatus for filling a product into a container is provided. The apparatus can include a filling unit that can deliver the product into the container. The filling unit can include a pump and a filling nozzle at its one end. The apparatus can also include a drive unit for moving the container in relation to the filling unit between a first position, in which a bottom end of the container is arranged at a maximum distance from the filling nozzle, and a second position, in which the bottom end of the container is arranged at a minimum distance from the filling nozzle. A controller can control delivery of the product through the filling nozzle, control the drive unit, and calculate a new drive unit motion profile for controlling movement from said second position to said first position.

Abstract: A medicine packaging apparatus 10 has a medicine preparing and dispensing portion 20, a packaging portion 150, a pre-packaging photographing portion 100 for reading identification information attached to a medicine in a phase before the medicines are packaged by the packaging portion 150, an individually supplying portion 60 which can individually supply the plurality of medicines received from the side of the medicine preparing and dispensing portion 20 to the side of the pre-packaging photographing portion 100 and a control part 200. The individually supplying portion 60 includes a receiving portion 72 for receiving the medicines from the side of the medicine preparing and dispensing portion 20 and a delivering device 64 which can perform a delivery action for delivering the medicines by individually holding the medicines in the receiving portion 72 and releasing the medicines toward the side of the pre-packaging photographing portion 100.

Abstract: A method and apparatus for pleating or otherwise shaping a web are described herein. The method and apparatus may have numerous applications. In some embodiments, the method and apparatus are used in the formation, filling, and sealing of unit dose packages for consumer products. A method and apparatus for forming sealing two moving webs together, which webs have portions that are non-planar are also described herein.

Abstract: Disclosed herein is a banknote handling apparatus 100 functioning as a paper sheet bundling device configured to bundle stacked banknotes with a tape T. The apparatus includes bundling stackers 4, 4 configured to bundle the banknotes, a tape loop forming unit 92 configured to form a small tape loop L1 from the tape T and then feed the tape T to enlarge the small tape loop L1 into a large tape loop L2, and a second transport unit 8 configured to grip the banknotes stacked in the bundling stackers 4 to transport the banknotes into the large tape loop L2.

Abstract: A method and an apparatus for feeding electronic components are capable of increasing a rate of filling accommodation holes with electronic components. An accommodation plate including accommodation holes, respective openings of which are distributed over a main surface of the accommodation plate, is prepared, and electronic components are loaded onto the main surface of the accommodation plate. A horizontal vibration in an X-axis direction and/or a Y-axis direction and a vertical vibration in a Z-axis direction are applied to the accommodation plate with the main surface of the accommodation plate level. The horizontal and vertical vibrations have an equal number of vibrations and a prescribed phase difference therebetween. The accommodation plate is vibrated so that each of the electronic components is fed into one of the accommodation holes while moving over the main surface of the accommodation plate.