Abstract: The invention relates to a method for determining the direction and the amplitude of a force applied to a system (IO) comprising a stationary portion (13) and a mobile portion (12) which can deform when exposed to said force. Mechanical deformations applied to the mobile portion when exposed to said force are measured by measuring a distance between the stationary portion and the mobile portion in the direction of application of the force, and the distance measurements are processed in order to determine the amplitude and the direction of the force.

Abstract: An outboard motor includes: a driveshaft housing configured to accommodate a driveshaft; and a gear case bulging laterally below the driveshaft housing and configured to accommodate a gear device, wherein an inside of the driveshaft housing communicates with an inside of the gear case, an introduction port for introducing lubricating oil into the gear case is opened on the driveshaft housing, and a confirmation port for causing the lubricating oil introduced into the gear case to flow out is opened on a front end side of the gear case.

Abstract: One embodiment of a method of controlling low-speed propulsion of a marine vessel includes receiving user input to engage an automatic speed control mode and then, when the automatic speed control mode is engaged, receiving the user input indicating at least one of a selected lure identifier and a selected fish identifier. A desired speed parameter is then determined based on the selected lure identifier and/or the selected fish identifier. The propulsion device is then controlled to automatically maintain the desired speed parameter.

Abstract: A linking member between a first and a second structural member of a fuselage of an aircraft allowing improved dissipation of stresses. The linking member has a first part made of a solid structure and at least one second part made of a lattice structure. The first part made of the solid structure is configured to dissipate static stresses and to withstand fatigue up to a predetermined maximum stress and fatigue threshold. This configuration allows improved dissipation of the stresses exerted on the linking member.

Abstract: An emergency opening device (1) for an aircraft door having: a tubular operating member (2); elastic compression device (3). The operating member (2) includes a first end element (10) and a second end element (11) that can move in translation with respect to one another. The first end element (10) having a cylindrical retractable rotary stop (20), that can move between a first angular position of transmission and a second angular position of release.

Abstract: An emergency opening device (1) for an aircraft door having: a tubular operating member (2); elastic compression device (3). The operating member (2) has a first end element (10) and a second end element (11) that can move in translation with respect to one another. The first end element (10) includes a removable driving stop (20).

Abstract: A public transportation vehicle comprises a passenger cabin, comprising a cabin floor, and a plurality of seating tracks, fixed to the cabin floor at locations along the passenger cabin. The public transportation vehicle further comprises a plurality of passenger seats selectively releasably fixed to at least one seating track of the plurality of seating tracks. The public transportation vehicle additionally comprises at least one cargo cart that is selectively releasably fixable to at least one seating track of the plurality of seating tracks.

Abstract: A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.

Abstract: A control lever assembly for controlling an aircraft system. The lever includes: a housing having an outer side and an aperture defined by a rim; and a control lever extending through the aperture and movable in the aperture; the control lever having an outer cover member arranged to slide over the outer side of the housing and cover the rim throughout the range of movement of the control lever.

Abstract: A winged vertical take-off and landing aircraft with compound control surfaces comprising flaps and ailerons which can be operated simultaneously with each other offers improved aerodynamic performance and maneuverability. Configuration of the compound control surfaces may be varied to optimize performance in hovering (vertical) flight modes, cruising (horizontal) flight modes, and transitional flight modes.

Abstract: An electro-hydraulic circuit includes a supply line that connects between a hydraulic supply device that supplies hydraulic fluid and a driving part to be driven by a hydraulic pressure of the hydraulic fluid; a switching valve disposed in the supply line to switch between switching lines for the hydraulic fluid supplied to the driving part; a pilot hydraulic line connected to the switching valve to supply the hydraulic fluid for switching between the switching lines; a check valve disposed in the pilot hydraulic line; a solenoid valve disposed in the pilot hydraulic line to change a supply state of the hydraulic fluid to the switching valve; a sealing material disposed in the switching valve to seal the hydraulic fluid; and a relief valve disposed in the pilot hydraulic line to release the pilot hydraulic pressure

Abstract: Within examples, a system is described that includes a control lever for controlling operation of a device, a first actuator coupled to the control lever via a rod, and a resettable frangible link coupling a second actuator to the control lever via the rod. The resettable frangible link enables separation of coupling of the second actuator from the control lever based on an applied force to the rod by the first actuator.

Abstract: The left and right main landing gears on an aircraft are normally controlled by separate hydraulic power packs (HPP). Each HPP is sized for the load of the respective main landing gear. During failure of one of the HPP, a backup valve actuates to allow the other HPP to operate both main landing gears. With the backup valve actuated, the pump of the functioning HPP is coupled to the reservoirs of both HPPs and to the load paths to both main landing gears.

Abstract: A device for determining a state of a rotor of a rotorcraft. The rotorcraft comprises a fuselage and a main rotor provided with a hub rotating about a mast of the rotor and with a plurality of blades whose second ends describe a trajectory defining a tip path plane. The device includes a sensor for measuring an angular velocity of a blade about a pitch axis. The device thus makes it possible to determine a state of the rotor, comprising, for example, estimates of a longitudinal cyclic pitch and of a lateral cyclic pitch of the blade with respect to the tip path plane.

Abstract: A tail rotor isolation system for rotorcraft includes a secondary engine, first and second freewheeling units, an isolation assembly and a tail rotor system. The secondary engine is coupled to the input race of the first freewheeling unit. A main rotor system is coupled to the output race of the second freewheeling unit. The isolation assembly is coupled to the output race of the first freewheeling unit and has a fully engaged position coupling the input and output races of the second freewheeling unit and a partially engaged position coupled to the input race but decoupled from the output race of the second freewheeling unit. The tail rotor system is coupled to the input race of the second freewheeling unit such that in the partially engaged position of the isolation assembly, the overrunning mode of the second freewheeling unit isolates the tail rotor system from the main rotor system.

Abstract: A rotor system for electrically powered rotorcraft is described, providing the benefits of autorotation for safety, and fast thrust response, regardless of rotor inertia. The rotor system includes a rotor hub and two or more rotor blades, and an electric motor driving the rotor hub. The rotor hub includes a mechanism which adapts the collective incidence of the rotor blades in response to the torque applied by the electric motor. When there is little or no motor torque, the rotor hub holds the blades at a shallow incidence, which supports autorotative descent. During autorotative descent, the motor controller coupled to the electric motor utilizes electrical braking to moderate the rotor RPM and thrust. When the electric motor provides power to the rotor for normal flight, the collective blade incidence adjusts in response to the motor torque, providing a fast response in rotor thrust, thus avoiding the lag in rotor thrust that would occur through RPM control.

Abstract: A blade for an open rotor includes a pressure side and a suction side, the pressure side and the suction side intersecting at a leading edge and a trailing edge, wherein for at least 30% of a span of the blade, the meanline of the airfoil section is shaped such that a relative curvature parameter is greater than 1.2 in a first region, less than 0.75 in a second region, and greater than 0.9 in a third region, wherein the relative curvature parameter of a region is defined by ??n/??tot/?(x/c)n wherein ? corresponds to the inverse tangent of the slope of a meanline curve, subscript n indicates the region, and x/c is a chordwise location normalized by the chord and wherein the first region comprises at least x/c=0.0 to 0.15 and the third region comprises at least x/c=0.80 to 1.0.

Abstract: A VTOL aircraft (1) having a fuselage (2) for transporting passengers and/or load, front and rear wings (3, 4) attached to the fuselage, a right connecting beam (5a) and a left connecting beam (5b), which connecting beams structurally connect the front wing and the rear wing, and which connecting beams are spaced apart from the fuselage, and at least two lifting units (M1-M6) on each one of the connecting beams. The lifting units each include at least one propeller (6b) and at least one motor (6a) driving the propeller, preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation. The front wing, at least in portions thereof, has a sweep angle ? between ?=45° and ?=135°, and the rear wing, at least in portions thereof, has a forward sweep with sweep angle ??30°.

Abstract: A cotton topping unmanned aerial vehicle having cutter discs and front grain lifting baffle plates is provided, the unmanned aerial vehicle includes an unmanned aerial vehicle body, a carrying component, a grain lifting component, and a cutting component. The carrying component includes a suspension, an electric push rod mounting base, an electric push rod, a motor mounting base, and motors. An upper end of the electric push rod is bolted to the electric push rod mounting base. The motor mounting base is welded to a lower end of the electric push rod. The grain lifting component is grain lifting baffle plates which include a left baffle plate and a right baffle plate, and both the left baffle plate and the right baffle plate are welded to guard plates.

Abstract: A carrying apparatus associated with drones and similar vehicles, and carrying a passenger or a load is provided. The carrying apparatus includes a center part having a predefined geometrical shape, a first lateral wall encircling a volume, wherein the first lateral wall begins in a manner encircling the center part and decreases towards a first end provided at a first direction and a second lateral wall, wherein the second lateral wall begins in the manner encircling the center part and decreases towards a second end provided at a second direction.

Abstract: A system for remote pilot control of an electric aircraft in autopilot mode including a remote computing device configured to receive a user input and generate a control datum as a function of the pilot input, a flight controller configured to receive the control datum from the remote computing device, and generate a command datum as a function of the control datum and an authority status, and the remote computing device configured to receive the command datum from the flight controller, and display the command datum.

Abstract: UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

Abstract: A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.

Abstract: An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

Abstract: An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

Abstract: A novel gas propulsion device comprises one or more high-frequency linear actuators (such as a voice coil linear actuator or a piezoelectric linear actuator) attached to one or more gas propulsion elements having a concave internal surface facing a first side thereof. Linear actuators operate to cause reciprocal movements of each gas propulsion element at a sufficient speed, such as a subsonic or supersonic speed, and suitable amplitude to form a high gas pressure zone on the first side of the gas propulsion element and a low gas pressure zone on the second side thereof. The gas pressure differential in turn causes propulsion of gas away from the device along the longitudinal axis or to the side of it if the gas propulsion element is tilted. The invention may be used as a main or secondary thrust engine for an aircraft.

Abstract: A projectile delivery module to be mounted on an aerial vehicle includes a projectile delivery system including a kinetic projectile and a base system. The kinetic projectile includes a projectile body, an RF receiver, and an onboard steering system including: a steering mechanism operable to change an attitude, orientation, and/or direction of flight of the kinetic projectile; and a steering actuator. The base system includes: an RF transmitter to communicate with the RF receiver; a projectile holder; a target tracking system; and a projectile guidance system including a projectile tracking system and a projectile control system.

Abstract: In one aspect, an unmanned aerial system for crowd control, includes a chassis for attaching components of the unmanned aerial system and one or more rotary wings, each of the one or more rotary wings drivable by a respective motor. A container stores a pressurized source of a crowd control agent and a nozzle is provided for dispersing the crowd control agent into the air. An electronically controlled valve selectively places the nozzle into fluid communication with the container. In a further aspect, a modular unmanned aerial system for crowd control is provided.

Abstract: The invention relates to a passenger module for a vehicle cabin, the passenger module comprising a first side element, a second side element and two seats arranged between the first side element and the second side element; wherein the first side element and the second side element extending parallel to each other; the seats are arranged substantially one behind another and facing substantially in a same direction; wherein a front seat is positioned angled by a predefined first angle around its vertical axis in a direction towards the first side element; a rear seat is positioned angled by a predefined second angle around its vertical axis in a direction towards the second side element and an aisle of the vehicle cabin.

Abstract: A slanted aircraft seat privacy panel may include a body. The body may be defined by a contour line along at least a portion of a height of the body. The contour line may be a straight line slanted at an angle relative to a vertical line. The vertical line may be defined relative to a floor of the aircraft cabin. The contour line being slanted may generate increased shoulder space in the passenger compartment in the aircraft cabin. The increased shoulder space in the passenger compartment may use a portion of non-fully utilized space in an adjacent passenger compartment in the aircraft cabin. The passenger compartment and the adjacent passenger compartment may be offset relative to an aisle in the aircraft cabin. A portion of each of the passenger compartment and the adjacent passenger compartment may be formed by the slanted aircraft seat privacy panel.

Abstract: A swinging seatpan assembly for a passenger seat includes a fixed seatpan frame attached to the seat structure and a mobile seatpan frame pivotably attached to the fixed seatpan frame by rollers configured for translation through slots in the fixed seatpan frame. Passengers occupying middle and aisle seats of a multiple-seat block or assembly may engage their respective swinging seatpan assemblies to allow an occupant of a window seat to enter/egress their seat without the middle-seat and aisle-seat passengers leaving their seats for the aisle. For example, the passenger may engage a release to unlock and push the mobile seatpan frame so that the mobile seatpan frame pivots rearward/downward, temporarily increasing the seat pitch distance and allowing the window-seat passenger increased egress space.

Abstract: A bulkhead-mounted aircraft seat assembly configured for independent vertical and horizontal adjustment includes an aircraft seat (seatback and seat frame/cushion) for supporting a pilot, passenger, or other occupant. Parallel rails attach to the bulkhead and extend along the bulkhead (vertically or near vertically) with opposing slots set into each rail. A sled translates along the rails via paired sliding members set into the slots, each pair of sliding members connected to an axle extending through the sled. A four-bar linkage attached to the sled and to the aircraft seat; the four-bar linkage extends from a default position to allow the aircraft seat to translate along a horizontal linear rail under the seat while maintaining a stable vertical reference point above the cabin floor. The seat is independently configured for substantially vertical adjustment via a metering plate attached to the bulkhead.

Abstract: A hinge having a center element, a first leaf element articulated on the center element and rotatable about a first axis, and a second leaf element articulated on the center element and rotatable about a second axis. The leaf elements have mounting elements for a leaf. The hinge has a mounting member to fasten the center element to an air passenger seat. In the mounted state of the hinge on the air passenger seat and in the arranged state of the leaves, the leaves are present such that they can be moved relative to the remaining air passenger seat. The first and the second axes are present on the hinge so as to extend in a bearing plane and so as to be spaced apart from one another.

Abstract: An aircraft including a fuselage having a side wall at least partially defining a passenger cabin and a crown section of the aircraft. The passenger cabin includes an overhead zone, a passenger zone, and a floor zone. An air supply duct is positioned within the crown section, and the air supply duct is configured to pressurize the crown section with air. At least one return air outlet is defined in the floor zone. An interior structure is coupled to the side wall and extends between the passenger cabin and the crown section. The interior structure includes a plurality of nozzles oriented to discharge the pressurized air from the crown section along an airflow path that extends downward through the overhead zone, downward through the passenger zone, and then towards the at least one return air outlet.

Abstract: An emergency escape slide container includes a first portion having a first end wall and a first side wall, the first side wall and the first end wall defining a first storage space that is sized and shaped to receive an emergency escape slide. The first side wall also includes a first rolling mechanism. The emergency escape slide container also includes a second portion having a second end wall and a second side wall, the second side wall and the second end wall defining a second storage space sized and shaped to receive the emergency escape slide. The second side wall also includes a second rolling mechanism. The first portion and the second portion cooperate to define a third storage space therebetween, the third storage space being equal to a combination of the first storage space and the second storage space.

Abstract: A system for controlling an aircraft power network including at least a first propulsion assembly having at least one left-hand starter-generator and a second propulsion assembly having at least one right-hand starter-generator as well as other electrical motors, the system including first and second power electronics boxes each including at least two so-called generic control boards for controlling the power network, each of these at least two generic control electronics boards being connected by a fast communication link to separate first and second data switches, the first and second data switches of the first power electronics box being respectively connected to the first and second data switches of the second power electronics box by a first fast communication bus.

Abstract: A lightning strike protection material for an aircraft includes an electrically-conductive grid with grid-forming members and nodes where grid-forming members overlap or intersect. A plurality of the grid-forming members and/or nodes include an outward-facing surface, and at least a portion of the outward-facing surface is concave.

Abstract: In an aircraft, latches are used to secure cargo within the cargo hold of the aircraft. Such latches include a base plate configured for rigid attachment to a surface of the cargo hold, a latch head attached to the base plate and configured to prevent a movement of at least one cargo unit in a Y-direction and a Z-direction and to allow a movement of the at least one cargo unit in an X-direction, and a roller assembly attached to the base plate, opposite the latch head, and comprising at least one roller, the roller being configured to provide a vertical support to the at least one cargo unit in the Z-direction while allowing the movement of the at least one cargo unit in the X-direction.

Abstract: Unmanned aerial vehicle (UAV) facilities, suitable for use by both emergency and non-emergency UAVs, comprise a housing having first and second moveable platforms. The second moveable platform is arranged adjacent the first moveable platform. A cover is arranged above the second moveable platform. A drive system operates the first and second moveable platforms and the cover.

Abstract: A fueling system is for an aircraft having a tank with a compartment configured to be filled with fuel. A discharge conduit extends from the compartment to an outside of the tank. A sampling arrangement has a sample container and a sample conduit extending from the compartment to the sample container. The fueling system further has a gas propellant arrangement comprising a pressurized gas source. The gas propellant arrangement is configured to provide pressurized gas to the compartment and to the sample container.

Abstract: Systems and methods are provided for assembling an aircraft. The method includes receiving a lower half barrel section of fuselage that is inverted to a keel-up orientation; and installing a floor grid into the lower half barrel section while inverted.

Abstract: A spacecraft for changing an orbit or an attitude of a target in outer space by irradiating the target with a laser, the spacecraft includes: a laser apparatus configured to generate the laser; a focusing unit configured to converge the laser; a detecting unit configured to acquire detection information including a distance between the spacecraft and the target; and an irradiation control unit configured to control the focusing unit on the basis of the distance so that the laser converges on the target.

Abstract: A propeller for an aircraft includes at least two blades, arranged about a central hub, which is coupled to at least one motor, driven by a power source. At least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub. An inner surface of each of the at least one sleeve member includes at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element. Each of the at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position. Each of the at least one sleeve member positions its blade in an operational position when its, at least one, projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element.

Abstract: An unmanned aerial vehicle (UAV) comprising a battery holding portion configured to releasably hold a first battery to provide electrical power to the UAV, the battery holding portion being configured to hold the first battery in a position relative to a direction of travel of the UAV such that, upon the UAV encountering a second battery positioned in the path of travel of the UAV, the first battery receives a mechanical impulse from the second battery causing the first battery to be released from the battery holding portion and the second battery replaces the first battery to become held by the battery holding portion to provide electrical power to the UAV.

Abstract: A system 100 for sheet coil packaging is provided. The system 100 preferably comprises: a sheet coil rotating arrangement 120, arranged to rotate a sheet coil 116 to enable it to be wrapped; first 112 and second 113 industrial robots, having first 108 and second 109 robot arms, arranged to wrap the sheet coil 116 using a wrapping tool 110, using sequences of the first robot arm 108 inserting the wrapping tool 110 into a central hole 118 of the sheet coil 116 and handing over the wrapping tool 110 to the second robot arm 109, and the second robot arm 109 transporting the wrapping tool 110 along the outside of the sheet coil 116 and handing it back to the first robot arm 108, as the sheet coil 116 is rotated by the sheet coil rotating arrangement 120; and two outer edge protection mounting devices 210, 220, arranged at opposite ends of the sheet coil 116 to feed out edge protection material 250 along an outer edge of the sheet coil 116 as the sheet coil 116 is rotated by the sheet coil rotating arrangement 120.

Abstract: Provided are methods and compositions for improving storage and/or transportation of food, flowers, plants, or the like by coating of the same with silk proteins or other substances including silk fibroin, chitin, acetylated monoglycerides, shellac, starch, high fructose corn syrup, mayauba wax, maydelilla wax, beeswax, vegetable oil, paraffin oil, ethylenediaminetetraacetic acid, cellulose, pectin, alginate, chitosan, gum Arabic, soy protein, zein, casein, and/or whey.

Abstract: The present invention relates to a vacuum-packed coconut, a preparation method thereof and a ready-to-drink trimmed coconut. The preparation method comprises the following steps: removing a shell of a fresh coconut to obtain a peeled coconut; letting the peeled coconut stand-still at room temperature for at least 10 hours to obtain a still-stood coconut; heating the still-stood coconut with a fluid at a temperature from 70 to 110° C. for 15 minutes to 40 minutes to obtain a fluid-heated coconut; and putting the fluid-heated coconut into a packing bag and then vacuuming the packing bag to obtain a vacuum-packed coconut. The advantages of the present invention include no air-pollution, stable quality, hygiene and prolonged storage period of the coconut products while maintaining the rich flavor of traditional roasted coconut.

Abstract: A system for packing a case with articles, the system including a conveying device to convey articles to be packed, in a serial configuration and a support for a case to be packed with the articles in which the articles are configured to be placed in a plurality of rows, including a first row, a second row adjacent to the first row and a last row adjacent to a side wall of the case.

Abstract: A method for providing a packaging material is provided. The method comprises feeding a web of packaging material through a packaging material processing unit; determining a target position of the packaging material; and controlling a printing unit to print an RFID antenna at the target position, wherein the material used for printing the RFID antenna is conductive substance. A packaging material is also provided.

Abstract: A system for assembling a container and closure comprising an expanding collet which has a plurality of pivoting collet segments, each configured to simultaneously pivot radially outward about a pivot point and comprising. The collet comprises a lip that is engagable with the rim of the open end of the container and an angled tip positioned radially inward from the lip and shaped to press a countersink portion of the closure against an interior wall of the container as the collet segments pivot radially outward. As the container and the chuck are brought together, the rim engages with the lips of the collet segments and causes the angled tips of the collet segments to pivot outward toward the interior wall of the container, thereby pushing the countersink portion of the closure against the interior wall of the container.