Abstract: A vessel propulsion device transmits a drive force of an engine to a propulsive force generator. The vessel propulsion device includes a generator that is driven by the engine, a power shutoff detector that detects a power shutoff state in which the drive force of the engine is not transmitted to the propulsive force generator, and a controller configured or programmed to, when the power shutoff detector detects the power shutoff state, select one of a plurality of charging modes to charge a battery connected to the generator and control a target speed of the engine based on a selected one of the charging modes.

Abstract: A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels.

Abstract: A single, common, fuselage and wing design of an aircraft structure provides for two different aircraft models or configurations. A fuselage (12) has a center section cutout area (212). Each wing (16) has an airfoil over substantially its entire span. In one configuration (2A), a center section component (212), such as a wingbox, is inserted into the center section cutout and the wings are connected to opposing sides of the center section component by a side-of-body join. In another configuration (2B), the wings are moved inwardly, joined to the fuselage, and also joined to each other in a centerline join at the centerline (218) of the aircraft wherein a portion (16A) of the airfoil of each wing is then inside the fuselage. Different flaps (210, 220), spacers (222), and/or different engine mount locations (402, 404) may be provided for the wings for the two configurations.

Abstract: An inflight connection system for aircraft having at least one wing with a wingtip includes, for each aircraft, a primary connector selectively extendable from the wingtip, an alignment connector selectively extendable from the wingtip and a male and female connector assembly disposed proximate the wingtip. The primary connectors extend a greater distance from the wingtips than the alignment connectors such that the primary connectors form a first connection between the aircraft when the aircraft are flying in a connection pattern. Thereafter, retraction of the primary connectors reduces wingtip separation of the aircraft such that the alignment connectors form a second connection between the aircraft establishing coarse alignment therebetween. Thereafter, retraction of the primary and alignment connectors further reduces wingtip separation of the aircraft such that the male and female connector assemblies form a third connection between the aircraft establishing fine alignment therebetween.

Abstract: The subject matter of this specification can be embodied in, among other things, a control apparatus includes a first mounting member, an elongate member having a first elongate portion, a second elongate portion, a first axis member between the first elongate portion and the second elongate portion, pivotally mounting the elongate member to the first mounting member and defining a first axis, a track configured as an arc defined about the first axis, and a first feedback assembly supported upon the second elongate portion and providing a first interface device configured to travel along the track in response to movement of the second elongate portion partly about the first axis, wherein the mass of the second elongate portion and the first feedback assembly substantially offsets the mass of the first elongate portion about the first axis member.

Abstract: A hydrostatic automatic flight servo system is provided. The automatic flight servo system includes a manifold that defines a first fluid chamber, and a hydraulic fluid is received in the first fluid chamber. The first fluid chamber includes a first bellows and a second bellows. The automatic flight servo system includes a stick received at least partially within the manifold and pivotally coupled to the manifold. The stick includes a control arm fixedly coupled to the first bellows, and the stick is to receive an input. The automatic flight servo system includes a flight output system pivotally coupled to the manifold. The flight output system includes a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold.

Abstract: An automated and versatile autonomously climbing undercarriage with flight capability that automatically reaches a suitable area for cleaning purposes, repair purposes, and monitoring purposes without being constantly connected to a supply station or base station in the process, and that independently goes to the surface of the facade and independently moves along the surface and away from the surface. The automated and versatile autonomously climbing undercarriage with vacuum suction units as per the invention involves a multicopter with two, three or more rotors or propellers attached to the autonomously climbing undercarriage.

Abstract: A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

Abstract: Techniques for using an unmanned aerial vehicle (UAV) to deliver a payload while generating an expected sound by the UAV during delivery may be provided. For example, during delivery or while in flight, propellers of different sizes that are associated with the UAV may be instructed to modulate at different rotational speeds to thereby generate an expected sound.

Abstract: The present disclosure relates to a gear set, especially for a rotary-wing aircraft, with two intermeshing gear wheels, each mounted on a respective shaft. In particular, in a normal section, the gear wheels of the gear set have different pressure angles on a drive side from the pressure angles on a freewheel side at the beginning of an engagement.

Abstract: A rotorcraft rotor comprising a hub made up of a monolithic body of composite material obtained by stacking successive layers of carbon fiber fabric dusted with a thermoplastic resin and compressed while hot. The hub is provided with branches on which respective blades are mounted via hinge systems, each including a strength member bearing radially against a corresponding branch. The strength members are individually received in sockets defined on fabrication so that when the rotor is set into rotation at a predefined operating speed, the radial thrust seat for enabling the strength members to bear against the branches present bearing surfaces that are cylindrical, the radial thrust seats then being of shape complementary to a cylindrical bearing surface of the corresponding strength member.

Abstract: A directional control system for a rotorcraft having a tail boom including a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom and a duct configured to deliver the forced air to the no-tail-rotor apparatus. The directional control system comprises a heat exchanger having air passages and fluid passages, the air passages in fluid communication with the duct, the fluid passages in heat exchange relationship with the air passages and configured for receiving a cooling fluid, and a forced air driver in fluid communication with the duct for driving the forced air through the duct to the no-tail-rotor apparatus. Methods of providing directional control in a rotorcraft are also discussed.

Abstract: A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.

Abstract: There is provided an unmanned aerial vehicle (UAV) with a flexible propeller guard. The flexible propeller guard may allow the UAV to be resiliently repelled from objects in the UAV's flight path, thereby protecting one or more of the UAV's propellers. The UAV may have foldable arms, movable between a deployed configuration and a stored configuration, and the flexible propeller guard may be used to restrain the folded arms in the stored configuration. The flexible propeller guard may be arranged so as to not interfere with the foldability of the arms.

Abstract: A method includes dispatching a drone to a site. The drone includes audio/visual equipment. The method includes logging a plurality of timestamped locations of the drone and receiving, from the audio/visual equipment, site data captured by an on-site operator of the audio/visual equipment. The method includes correlating a portion of the site data with at least one of the timestamped locations of the drone.

Abstract: Embodiments relate to a client-facing application for interacting with a transport service that transports items via unmanned aerial vehicles (UAVs). An example graphic interface may allow a user to order items to specific delivery areas associated with their larger delivery location, and may dynamically provide status updates and other functionality during the process of fulfilling a UAV transport request.

Abstract: A restraint assembly includes a base member, a pawl, a lock member, and an actuator assembly. The base member has a first side plate spaced apart from a second side plate. The pawl is pivotally coupled to the first side plate and the second side plate by a first pin. The lock member is pivotally coupled to the first side plate and the second side plate by a second pin. The actuator assembly includes a first shape memory alloy actuator that is drivably connected to the pawl and a second shape memory alloy actuator that is drivably connected to the lock member.

Abstract: The present disclosure is generally directed to an aircraft cabin LED lighting system and lighting assembly, in which each LED light is paired with and controlled by a separate microcontroller, which is individually addressable. In various embodiments, a lighting control device (e.g., a control panel for flight attendants) transmits pixel data to various lighting assemblies around the cabin. These lighting assemblies include the microcontroller-LED light pairs. Each LED light is multicolor and includes multiple LEDs (e.g., one for each color). The pixel data defines a color scheme and/or animation sequence. Each pixel maps to one of the microcontroller-LED pairs. The microcontroller controls the intensity of each LED of the LED light according to the pixel data it receives.

Abstract: Embodiments of the present invention provide a water management system for use on board a passenger transport vehicle. The water management system may be used to address and manage excess humidity, water leaks, or any other instance when water or other liquid may collect at a certain location. The disclosure provides a system for managing excess water and for optionally delivering the water to another location. The removal location may be a disposal outlet or it may be a beneficial use of the collected water on-board the vehicle.

Abstract: Armrest for aircraft seat, associated seat and process are provided. The armrest includes a stationary part (12) intended to be connected to the seat, a moving part (14) movable relative to the stationary part (12), between a high position in which the moving part (14) is intended to protrude above a seat bottom of the seat and a low position, and a maneuvering mechanism (18) able to guide the movement of the moving part (14) between the high position and the low position. The maneuvering mechanism (18) includes at least a first connecting rod (26) and a second connecting rod (27), each independently connecting the stationary part (12) to the moving part (14), the first connecting rod (26) and the second connecting rod (27) being arranged parallel to one another during the movement of the moving part (14) between the high position and the low position.

Abstract: A hybrid seat pan and diaphragm apparatus includes a seat pan that has a concave portion and a diaphragm positioned at an occupant-facing side of the seat pan and stretched across the seat pan at a first distance above the concave portion of the seat pan.

Abstract: An airfoil comprises a skin, comprising an external surface and an internal surface, opposite the external surface. The skin is magnetically and electrically conductive. The airfoil also comprises an interior space, formed by the skin. The internal surface faces the interior space. The airfoil additionally comprises a leading edge along the external surface. The airfoil further comprises a hybrid acoustic induction-heating system, configured to impede formation of ice on the external surface. The hybrid acoustic induction-heating system comprises an induction coil within the interior space. At least a portion of the induction coil is sufficiently close to the internal surface to produce an eddy current in the skin when an alternating electrical current is flowing in the induction coil. The hybrid acoustic induction-heating system also comprises at least one magnet within the interior space. At least the one magnet is configured to produce a steady-state magnetic field within the skin.

Abstract: An airfoil comprises a skin, comprising an external surface and an internal surface. The skin has a controlled region. The airfoil also comprises an interior space, formed by the skin. The airfoil additionally comprises a hybrid acoustic induction-heating system, configured to impede formation of ice on the external surface. The hybrid acoustic induction-heating system comprises an induction coil and a control system. At least a portion of the induction coil is sufficiently close to the internal surface to produce an eddy current within the controlled region when an alternating electrical current is flowing in the induction coil. The control system is configured to generate inductive heat and acoustic pressure in the controlled region by supplying the alternating electrical current to the induction coil based, at least in part, on an ambient temperature of a layer of fluid flowing over the external surface.

Abstract: An aircraft includes an airframe parachute system. The parachute system includes an activation system, an extraction system, a harness system, and a parachute assembly.

Abstract: According to various embodiments, disclosed is a beam structure comprising a four-point cross section for an inflatable article comprising an inflatable slide. The beam structure has greater beam strength and provides greater structural support than an inflatable beam having a traditional circular cross section.

Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: An unducted fan for an aircraft turbine engine, including a propeller having a hub and an annular array of blades extending substantially radially outwards from the hub, is provided. The hub includes an annular array of cowls, each of which is mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub. At least one cowl includes, at a circumferential end, a joint edge which is contiguous with a complementary joint edge of an adjacent cowl. The at least one cowl and at least one of the upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including a pivoting about an initial pivot axis circumferentially separated from the at least one joint edge.

Abstract: The disclosure herein relates to a method of controlling the thrust of the jets of a multi-jet aircraft, during the aircraft takeoff phase, which successively comprises a first step of controlling the jets to a first thrust level, until the aircraft reaches a first predetermined speed, and a second step of controlling the jets to a second thrust level, less than the first thrust level, when the aircraft exhibits a speed greater than the first predetermined speed, the first predetermined speed being less than the minimum ground control speed of the aircraft when the jets are at the second thrust level.

Abstract: The disclosure provides in one embodiment an electrical conductor pathway system for diverting an electric charge. The electrical conductor pathway system includes a substrate having a first surface to be printed on and having one or more grounding points. The electrical conductor pathway system further includes a direct write conductive material pattern printed directly onto the first surface via a direct write printing process. The direct write conductive material pattern forms one or more electrical pathways interconnected with the one or more grounding points. The one or more electrical pathways interconnected with the one or more grounding points divert the electric charge from the first surface to the one or more grounding points.

Abstract: Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail. The shuttle is detachable from the motor-driven tape, such that stoppage of the tape can be separate from stoppage of the shuttle. Embodiments further provide a secondary arrestment strap. Further embodiments provide an anti-rollback latch system.

Abstract: A method and apparatus for positioning an end effector relative to a structure. The apparatus may comprise the end effector and a sensor system. The end effector may be configured to perform an operation on the structure. The sensor system may have a plurality of sensors extending outward from the end effector.

Abstract: A method and system for operating an inlet door of an auxiliary power unit are provided. A control signal comprising at least one inlet door command is output. In response to the at least one inlet door command, at least one feedback signal is received and compared to the at least one inlet door command. If the at least one received feedback signal matches the at least one expected feedback signal, operation of the auxiliary power unit is allowed. Otherwise, operation of the auxiliary power unit is inhibited.

Abstract: A multi-degree-of-freedom electromagnetic machine includes a first structure, a second structure, and a control. The first structure is configured to rotate about a spin axis and about a tilt axis that is perpendicular to the spin axis, and includes a first spin conductor, a second spin conductor, and a tilt conductor, which together form a general shape of a surface. The second structure is disposed adjacent to the first structure and includes a plurality of magnets. The control is configured to controllably supply alternating current (AC) to the first and second spin conductors and direct current (DC) to the tilt conductor, wherein the first structure continuously rotates about the spin axis in response to the AC being supplied to the first and second spin conductors, and rotates about the tilt axis to a tilt position in response to the DC being supplied to the tilt conductor.

Abstract: Disclosed is an artificial satellite including a battery pack capable of dissipating heat, at least one radiator capable of conveying the heat dissipated by the battery pack into space, and a low-dissipation equipment item having an individual power flux density of less than 250 watts/m2. The satellite includes a thermally insulating cover delimiting, together with the radiator, an interior isothermal zone in which thermal control takes place by radiation, the battery pack and the low-dissipation equipment being arranged in thermally insulating cover. The battery pack has an operating range of between 0° C. and 50° C. and preferably of between 10° C. and 30° C.

Abstract: An apparatus for packing a food product in a container to be used in infusion machines, preferably to obtain a beverage such as coffee, includes a frame for supporting means for feeding an external body of the container and means for making and inserting a bag configured with fluted sidewalls in the external body. The means for making and inserting the bag has at least one operating unit with a bag making component, an insertion component, and a conveyance for transporting the bag between the making component and the insertion component.

Abstract: A thermoforming packaging machine with a top film forming station, wherein the forming tool upper part and the foaming tool lower part of the top film forming station are disposed above a transportation plane of a lower film. One of the forming tool upper part or the forming tool lower part are operably connected to a lifting mechanism by a traverse system. The lifting mechanism is disposed below the transportation plane of the lower film. The traverse system transfers a lifting force from the lifting device to one of the forming tool upper part or lower part through the transportation plane of the lower film.

Abstract: Disclosed is a supply apparatus for drug packaging, used to supply a plurality of units of a drug to drug packaging members. The supply apparatus includes: a supply unit providing a supply path along which the units of a drug are supplied; a support unit elastically supporting the supply unit in such a manner such that the supply unit is inclined; a vibration unit vibrating the supply unit; and a detection unit detecting the units of a drug passing through the supply unit. According to this structure, it is possible to reduce drug supply errors, thereby improving drug supply efficiency.

Abstract: A rotary feed includes a static part that remains stationary relative to a stationary reference frame and a rotating part that rotates with a rotor. The static part and rotating part run adjacent to each other and define a sealed flow channel for a first medium. A buffer chamber surrounds the static and rotating parts, and the transition between these parts. During operation, a barrier medium charges it at a transition between the static and rotating parts. An outlet connects the buffer chamber to a treatment head to permit a medium in the buffer to be fed to the nozzle for container treatment.

Abstract: A package sorting system is described that can be used to efficiently sort and pack Ropak containers for transporting packages from a sorting facility to a destination facility. The package sorting system can determine a particular Ropak container to place the package in as well as determine if the package was placed in the current Ropak container.

Abstract: Described herein are systems and techniques for determining a pack station for storing inventory in a materials handling facility, routing item packages to pack stations based on size ranges for custom containers and optimizing dimensions of custom containers based on dimensions of a shipping container. For example, the systems described herein may allocate a percentage of inventory to a custom inventory location that is physically near custom container forming devices, thereby reducing the cost to pick, sort, pack and route items for shipment, storing or otherwise handling in a custom container.

Abstract: Disclosed are preforms which incorporate improvements in the region of the neck and upper segment of the body to allow the production of lightweight containers, such as bottles suitable for containing water or other beverages. In accordance with certain embodiments, the improvements include a thinner neck finish area than conventional bottles, where the thinner area is extended into the upper segment of the body portion below the support ring. Reducing the thickness in these areas of the bottle allows for less resin to be used in forming the preform and bottle.

Abstract: A rapidly erected and collapsible container and method of using same are disclosed. The container is movable between a flat and a box configuration. The container includes two primary panels, two secondary panels, and a main link part. The two primary panels, which are movably coupled to the main link part, are configured to move away and sideways from each other, whereby the two primary panels face each other across a gap when the container is in the box configuration. The main link part provides, at least partly, a base panel for the container and may enable maintaining the container in the box configuration. Embodiments foster a container that rapidly, easily, and conveniently transitions from a flat configuration to being ready for use in a box configuration. Moreover, the container may be produced using significantly less material than conventional containers without compromising effectiveness and structural integrity.

Abstract: A blank of foldable sheet material for forming a container is provided. The blank includes a bottom panel, a top panel, and a set of vent panels configured to form at least one venting assembly positioned on the top panel of the container.

Abstract: A container having an interior, comprising a base and four walls. One of the walls having an opening allowing access to the interior. The one of the walls having an at least one catch along a lateral side disposed a wall intermediate location. A door having a rigid upper portion and a rigid lower portion coupled together by a first hinge at a door intermediate location which is positioned at or above the wall intermediate location. The door having at least one rigid latch extending from the upper portion to a location below the door intermediate location when the door is in an unflexed state.

Abstract: A storage case includes a frame, a top plate, and a drawer. The frame includes a bottom plate, side plates, and a rear plate. The top plate covers the upper side of the frame. The drawer is freely pulled out of and pushed into the frame through an open front side of the frame. The side plates of the frame are foldable between an upright position, at which the side plates extend upright from left and right sides of the bottom plate, and a folded position, at which the plates extend along an upper surface of the bottom plate. The rear plate is foldable between an upright position, at which the rear plate extends upright from a rear side of the bottom plate, and a folded position, at which the rear plate extends along a lower surface of the bottom plate.

Abstract: A decorated tab for a beverage container has a lift end, a nose end, and central webbing. An enclosed portion of the central webbing has a coating. A symbol is located on the enclosed region which is created by selective removal of the coating by a laser ablation. The symbol has a boundary profile defining a perimeter of the symbol generated by a continuous, uninterrupted vectorized laser dot pattern defining regions of ablated coating. The symbol has an interior portion generated by a plurality of pulsed rasterized laser dots defining further regions of ablated coating.

Abstract: The invention relates to a plectrum (1) comprising a flat member (2) that is generally sector-shaped form a top view and has an inner face (3) and an outer face (4) from a top view, the outer face (4) having a larger peripheral size than the inner face (3). The invention is characterized in that the flat member (2) is a single piece, a slot (5) which extends into an opening (6) for a rotary bearing is provided on the inner face (3), and the flat member (2) simultaneously forms a rotatable protective clip-on-part for open beverage cans (8) or the like.

Abstract: A pallet includes fire retardant coatings to improve the overall fire performance of the pallet. First, the coatings may be used in combination with fire retardant additives in the plastic material of the pallet in order to reduce the amount of additives, thereby reducing cost and improving the structural performance of the pallet. Alternatively or additionally, the fire retardant coatings may be placed inside the pallet. This eliminates the chance that the fire retardant coating will get worn off during use. For example, the coating could be placed between the reinforcement sheet and the deck or runners, within the columns, etc.

Abstract: In one embodiment, a maintainable pallet is provided with interchangeable support structures and sensors for identifying any damage that the interchangeable support structures may experience. The maintainable pallet may include two side supports, two end supports coupled to the two side supports end-to-end to form a rectangle, a central support position between the two side supports, a plurality of top transverse support fastened onto the two side supports to form a top loading surface and the central support with two-part releasable fasteners, and two bottom transverse supports fastened to the ends of the two side supports to form a bottom surface with two-part releasable fasteners. Sensors, in some embodiments, may be embedded in the two side supports to measure, for example, acceleration, location, or other logistic information.

Abstract: A storage system includes at least two modular containers, at least two anchor members, and at least one coupler. Each of the modular containers includes a bottom wall and a surrounding wall unit with two opposite walls. Each of the two opposite walls has two lateral regions and an elongated depressed region which extends inwardly to form an elongated groove. Each of the anchor members includes a fitted end fitted slidably in a corresponding elongated groove, an enlarged head, and a neck disposed between the fitted end and the enlarged head. The coupler couples the enlarged heads of the at least two anchor members together so as to permit the at least two modular containers to be disposed in their respective orientations.