Abstract: The present disclosure provides an unmanned aerial vehicle. The unmanned aerial vehicle includes a fuselage, a plurality of rotor propulsion assemblies installed on the fuselage, and a fixed-wing propulsion assembly that is detachably installed on the fuselage. The fixed-wing propulsion assembly is able to rotate relative to the fuselage when the fixed-wing propulsion assembly is installed on the fuselage.

Abstract: An unmanned aerial vehicle (UAV) includes a power system providing flight power to the UAV and a frame assembly supporting the power system and including a center frame and an arm assembly. The arm assembly includes an arm connected with the center frame, a deformation rod, and a support rod parallel to the arm. Two ends of the deformation rod are rotatably connected with the arm and the support rod, respectively. The support rod is configured to move translationally relative to the arm while remaining parallel to the arm, so as to be selectively in a folded state or an unfolded state. Each of two ends of the deformation rod forms a first or a second preset angle with one of the arm and the support rod when the support rod is in the folded or unfolded state. The second preset angle is smaller than the first preset angle.

Abstract: A holding device for a wall module 10 of the cabin lining in an aircraft includes two different clamping devices. The first clamping device 30 has a clamping body 33 having a first clamping jaw 31, which is fixed relative to the clamping body, and a second clamping jaw 32, which is movable relative to the clamping body 33, which in turn is operatively connected or can be temporarily connected to an actuating lever 35. In the closed state, the clamping jaws 31, 32 form a receiving space 36 for the wall module 10. An interlocking device 37 fixes the position of the clamping jaws 31, 32 relative to one another in the closed state.

Abstract: The trailing edge structure of an aircraft wing is subjected, in use, to high temperature efflux from an aircraft's engines. Such elevated temperatures can detrimentally affect the ultimate tensile strength of the trailing edge. An aircraft wing component includes composite material having a first portion including a metal matrix containing reinforcing material, and a second portion including a metal matrix containing hollow metal ceramic spheres, the second portion being adjacent a surface of the composite material. The provision of two portions, one of which contains reinforcing material and the other comprising hollow spheres means that the composite material has both structural strength and heat shielding qualities where they are needed most in the component. The portion of composite containing the hollow metal ceramic spheres acts as an embedded layer of heat insulation.

Abstract: A system to arrest flap over-travel employs a track extending from a flap and engaging an auxiliary support. The track has a deployment profile determining flap motion relative to the support structure during travel between an extended position and a normal retracted position. The deployment profile has a transition portion extending beyond the normal retracted position and terminating in a detent. A resiliently mounted catcher is configured to be displaced by the transition portion during over-travel of the flap beyond the normal retracted position and captured in the detent in a maximum retracted position thereby restraining the flap.

Abstract: A system to arrest flap over-travel employs a track engaging a flap to a support structure. The track has a deployment profile determining flap motion relative to the support structure during travel between an extended position and a normal retracted position. The deployment profile has a transition portion extending beyond the normal retracted position and terminating in a detent. A resiliently mounted catcher is configured to be displaced by the transition portion during over-travel of the flap beyond the normal retracted position and captured in the detent in a maximum retracted position thereby restraining the flap.

Abstract: A slat (108) for the leading edge of a swept aircraft wing includes slat tracks (114) that dictate the path of movement of the slat as it moves from a retracted position (FIG. 7) to a fully deployed position (FIG. 15). Each slat track (114) has a shape that follows a helical path. The motion of the slat thus includes a component of rotation about a first axis, which may be perpendicular to the line of flight (120) and a component of translational movement parallel to the first axis. When viewed from above the slat may move predominantly in a direction parallel to the line of flight (120).

Abstract: An aircraft has a ducted thruster. The ducted thruster includes a duct having an inner wall, a stator hub disposed within the duct, a first stator extending along a first longitudinal axis between the inner wall and the stator hub, and a second stator. The second stator extends along a second longitudinal axis between the inner wall and the stator hub. The second longitudinal axis is either (1) substantially perpendicular to the first longitudinal axis or (2) substantially parallel to the first longitudinal axis and offset from the first longitudinal axis.

Abstract: According to one implementation, a rotating device includes at least one ring, at least one motor and a power transmission mechanism. The least one ring rotates in a circumference direction. The at least one ring includes no hub for housing a motor inside the at least one ring. The at least one motor generates power for rotating the at least one ring. The power transmission mechanism transmits the power to the at least one ring.

Abstract: A propulsion system includes a driving device and a propeller coupled with the driving device. The driving device includes a body portion and a lock portion disposed on the body portion. The lock portion includes a first snap-fitting portion. The propeller includes a hub having a receiving hole, a plurality of blades connected to the hub, and a second snap-fitting portion arranged on an inner wall of the receiving hole and configured to snap with the first snap-fitting portion.

Abstract: A control system having a variable operator interface (VOI) is disclosed, and includes one or more processors and a memory coupled to the processors. The memory stores program code causing the control system to detect an existence and first direction of an operator control input to one or more active inceptors being backdriven from an operator on inceptor detector (OID). The control system is caused to compare the first direction of the operator control input with a second direction of one or more zero-force detent rates to determine a variance and interprets the operator control input as inadvertent based on the variance. In response to interpreting the operator control input as inadvertent, the control system is caused to limit the operator control input to reduce or substantially eliminate movement of the machine caused by inadvertent input by modifying the operator control input based on one or more command modifiers.

Abstract: A control rod assembly is provided for moving a control surface of a flight vehicle. The control rod assembly includes a first connector for connecting to a first structure of vehicle, and a second connector for connecting to a second structure of the vehicle. A connecting rod may be operably coupled between the first and second connectors, and an actuator may be operably coupled to the connecting rod. The actuator may include a screw-and-nut assembly, and a motor that is configured to drive the screw-and-nut assembly. The actuator may be operable such that driving the screw-and-nut assembly via the motor causes the connecting rod to translate linearly along a longitudinal axis to thereby vary a distance between the first and second connectors. The actuators may be electromechanical actuators which may be controlled by a controller without pilot interaction. Two such actuators may be provided on opposite sides of the assembly.

Abstract: An aircraft structure (11) for flow control including a perforated panel (13) having an inner surface (15) directed to a structure interior (17), an outer surface (19) in contact with an ambient flow (21), and a plurality of micro pores (23) connecting the inner and outer surfaces (15, 19). Weight reduction and maintaining required fatigue strength of the structure may be achieved because one or more elongate crack stopper elements (25) are attached to the inner surface (15) of the perforated panel (13), and the crack stopper elements (25) are configured to inhibit crack propagation within the perforated panel (13).

Abstract: A levered landing gear including a first shock strut having a first end and a second end, a truck lever pivotally coupled to the second end of the first shock strut, and a second shock strut disposed between the second end of the first shock strut and the truck lever, where the second shock strut has a first end and a second end, the first end of the second shock strut being coupled to the second end of the first shock strut and the second end of the second shock strut being coupled to the truck lever.

Abstract: A tension-torsion strap, for example for a rotor aircraft, including a continuous length of carbon fiber tow arranged in multiple loops to form an elongated member extending between opposing ends and a flexible cover encasing the carbon fiber tow.

Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.

Abstract: A mechanical power transmission is described that pivots about an axis to vary an angle between an input shaft and an output shaft. In one embodiment, the mechanical power transmission includes an input gear having an input shaft that couples to a drive shaft, an output gear having an output shaft that couples to a tail rotor, a first intermediate gear rotationally coupled to the input gear, and a second intermediate gear rotationally coupled to the output gear. The mechanical power transmission further comprises a shaft that mechanically couples the first intermediate gear with the second intermediate gear, where a centerline of the shaft is coincident with the axis.

Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.

Abstract: An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.

Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

Abstract: An aircraft store ejector systems and subsystems thereof. Embodiments can include a two-reservoir re-pressurization system wherein a remote reservoir is used to maintain desired pressure in a local ejector reservoir. The system can include a release valve having a vent valve and valve piston. The release valve can control release of pressurized gas to a pitch control valve. The pitch control valve can be configured to distribute the pressurized gas between two or more ejector piston assemblies. One or more of the ejector piston assemblies can include multiple concentric piston stages and piston chambers, the piston chambers configured to contain a volume of gas. The ejector piston assemblies can be configured to compress the volume of gas within the piston chambers as the piston stages are extended out from the aircraft. Such compression can provide a return force to the piston stages.

Abstract: A method and a device for measuring a spray area are provided. The method includes obtaining flight data of an unmanned aerial vehicle when performing a spray operation. The method also includes according to the flight data and a spray amplitude of a spray nozzle on the unmanned aerial vehicle for spraying, determining the spray area of the spray operation.

Abstract: An in-flight risk management system includes an eye sensor, a seat sensor, and one or more in-flight risk management computers that perform operations including: obtaining history information for a flight crew member, obtaining flight information associated with a flight on which the flight crew member will be present, determining, based on the history information and the flight information, a predicted fatigue profile for the flight crew member, determining, based on the predicted fatigue profile for the crew member, one or more fatigue indicator profiles for the flight crew member, obtaining, from at least one of the eye sensor or seat sensor, one or more measured fatigue indicator values associated with the flight crew member, generating, based on the one or more measured fatigue indicator values, one or more updated fatigue indicator profiles, and generating, based on the one or more updated fatigue indicator profiles, an updated predicted fatigue profile.

Abstract: A single-piece gas turbine engine bleed duct for a gas turbine engine including: a main airflow conduit configured to transmit a bleed flow to a location outside the gas turbine engine; a pressure regulating valve for regulating airflow through the main airflow conduit; a first inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the first inlet duct including a non-return valve; and a second inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the second inlet duct including a control valve; wherein each of the first and second inlet ducts are directly connectable to an engine casing of a gas turbine engine.

Abstract: This invention relates to electrically-driven propulsors for regional aircraft. These combine fans optimized for quiet regional operations with rotating variable pitch mechanisms contained within the hubs and highly efficient ring electric motors. The ring motors are used to drive annular fans at the inner or outer radius, or a conventional fan at the inner radius. The assembly combines a single fan, fixed or variable pitch, with a row of stators, or multiple counter-rotating fans without stators. Our focus is on propulsors optimized for quiet and efficient regional flights, but many elements apply to long-haul air and several other applications referred to herein.

Abstract: A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

Abstract: A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; and an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool, wherein the electric generator includes a coolant cavity in thermal communication with one or more components of the electric generator; a structural support housing at least partially enclosing the electric generator, the structural support housing including a forward wall located on a forward end of the structural support housing, wherein the forward wall includes a first opening; a first coolant conveying tube extending through the first opening to fluidly connect to the coolant cavity; and a first electrical connector tube extending through the first opening within the first coolant conveying tube to electrically connect to the electric generator.

Abstract: A hybrid-electric propulsion system for an aircraft is provided herein that can include a propulsor and a turbomachine comprising a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. An auxiliary power unit can be operably coupled with a starter motor. An electrical system can comprise a first electric machine coupled to the turbomachine. The first electric machine can be separate from the starter motor. A controller can be configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.

Abstract: A seal arrangement includes a first outer skin and a second outer skin disposed about an axial centerline. The second outer skin is adjacent the first outer skin and includes at least one door. A bulkhead extends substantially radially at least a portion of a distance between the axial centerline and one of the first outer skin and the second outer skin. A first outer frame includes a first portion, a second portion, and a third portion. The first portion of the first outer frame is mounted to the bulkhead. A seal is mounted to one of the at least one door and the second portion. The at least one door is rotatable between a first position and a second position. In the second position the seal contacts the at least one door and the second portion. The third portion is configured to limit a compression of the seal.

Abstract: An aircraft nacelle includes a front portion having an inner wall and an outer wall joined by an annular front frame to delimit a gas passage flow path, the front frame being formed by a plurality of adjacent sheet metal frames which are joined together over at least a portion of the periphery thereof.

Abstract: A ram air turbine (RAT) system can include a fluid circuit, a turbine, a shaft connected to the turbine to turn with the turbine, and a hydraulic pump connected (e.g., directly) to the shaft and connected to the fluid circuit to pump fluid within the fluid circuit. The hydraulic pump can be a variable displacement pump, for example (e.g., configured to govern a speed of the shaft and turbine). The hydraulic pump can be used to power and provide speed control to an electric generator.

Abstract: The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

Abstract: A monitoring system and method are provided for real time monitoring of flaps, landing gears, or tail skids to determine safe taxi, takeoff, and flight readiness. Monitoring units, including scanning LiDAR devices combined with cameras or sensors, mounted in aircraft exterior locations produce a stream of meshed data that is securely transmitted to a processing system to generate a real time visual display of the flaps, landing gears, or tail skid for communication to aircraft pilots to ensure safe aircraft taxi, takeoff, and flight readiness. Actual flap position alignment with optimal flap setting, proper retraction and extension positions of landing gears, and tail skid condition is ensured. Safety of aircraft taxi, takeoff and flight and airport operations are improved when the present system and method are used to prevent incidents related to misaligned flaps and improperly positioned landing gears or tail skids.

Abstract: An information projection and control system for projecting information onto a projection area provided by a vehicle door, comprising at least one control unit that generates information, for projection onto the projection area; at least one projection device that projects the generated information onto the projection area; and at least one movement sensor that detects movements in a sensing area associated with the projection area, wherein the at least one control unit is adapted to control generation of the generated information on the basis of the detected movements.

Abstract: Disclosed is an autonomous hanging storage, docking and charging multipurpose station (“the UAVMCS”) for unmanned aerial vehicles. The UAVMCS enables UAV to approach it, connect to it and fly into it from the bottom up. The UAVMCS is in the form of a cocoon in a closed state, and it is in the form of an umbrella in the open state. The system can be networked with a central control and a plurality of Unmanned Aerial Vehicles (“UAVs”). The UAVMCS can include a base structure connected to a power grid, a station receiving assembly, a remote controller at the base structure enabled to communicate with a UAV and to initiate, control and stop docking and charging processes, a housing with covers, a positioning and stabilizing surface, and a UAV docking charging and refueling frame used for connecting to the docking housing unit. The UAVMCS can be mounted on towers, bridges, posts, electricity pylons, communication structures, buildings, and gas stations, but is not limited to them.

Abstract: A device for docking an unmanned vehicle with a moveable docking station is provided, the device comprising: an interface surface configured to cooperatively engage a counterpart interface surface of a counterpart device; at least one identifying means arranged to be detected by a counterpart device; and at least one sensor configured to detect an at least one identifying means of a counterpart device. Also provided is a method of docking an unmanned vehicle with a moveable docking station, the method comprising: performing a cooperative docking procedure; wherein the cooperative docking procedure comprises each of the unmanned vehicle and docking station capturing the attitude and/or position of the other and, responsive to the captured attitude and/or position, adjusting the respective attitude and/or position of the unmanned vehicle and docking station to a mutually cooperative docking configuration so as to provide docking of the unmanned vehicle with the docking station.

Abstract: A unit for handling an aircraft turbojet engine includes a frame, a front cradle and a rear cradle designed for supporting the turbojet engine, and a plurality of electric actuators. The cradles include devices for securing the turbojet engine. The plurality of electric actuators includes three electric actuators, where a first one and second one are arranged opposite each other, on either side of a longitudinal axis of the frame, connected to the front cradle and arranged for moving same in vertical translation, and where a third actuator is connected to the rear cradle and arranged for moving the same in vertical translation. The handling unit further includes a device for rotary driving of the front cradle about a longitudinal axis of the turbojet engine.

Abstract: A method in a spacecraft for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

Abstract: A package for holding pharmaceutical containers on a filling line includes: a transport and packaging container having a plurality of connected sidewalls, a base, an upper edge opposite the base, and a step defining a step height that is constant relative to the upper edge and less than an overall height defined between the upper edge and the base; and a holder placed in the transport and packaging container and having a plurality of holder openings formed therein. The holder is supported on the step and configured to hold a container in each of the holder openings so the held containers are suspended within the transport and packaging container. The step height is constant and independent of at least one of a shape, a type, or a size of each of the held containers.

Abstract: A medicine packaging apparatus configured to package medicine based on prescription data, including: a feeder configured to feed solid medicine; a storage configured to temporarily store the solid medicine fed from the feeder; and a packaging unit configured to package the solid medicine discharged from the storage, wherein the storage includes: a plurality of storage containers; a holding table configured to hold the plurality of storage containers so as to be individually detachable; and a drive unit configured to drive the holding table to move so that each of the plurality of storage containers held by the holding table is moved between an introduction position where the solid medicine is introduced from the feeder and a discharge position where the solid medicine is discharged to the packaging unit.

Abstract: The method includes covering a first opening of at least one first chute using a lid, delivering air from a pressurized air source into the at least one first chute, and advancing at least one first plunger through a first end of the at least one first chute to transfer a product through a second end of the at least one first chute and into a first open side of at least one first box.

Abstract: A binding machine includes a wire feeding unit, a binding unit, a curl guide and an inductive guide. The inductive guide has a converging passage through which the wire fed by the wire feeding unit and curled by the curl guide passes, and a cross-sectional area of the converging passage decreases along an entry direction of the wire from an opening end portion that the wire enters. The inductive guide has an entry angle regulation part configured to change an entry angle of the wire entering the converging passage, and the inductive guide is provided on an inner side with respect to a virtual line interconnecting the opening end portion and a narrowest part of the converging passage at which the cross-sectional area is the narrowest.

Abstract: A binding machine includes a wire feeding unit configured to feed a wire to be wound on an object to be bound, a binding unit configured to twist the wire wound on the object to be bound, a curl guide configured to curl the wire being fed by the wire feeding unit, an inductive guide configured to guide the wire curled by the curl guide toward the binding unit, and a retraction guide part configured to retract the wire to a downstream side of the binding unit with respect to a feeding direction of the wire that is fed by the wire feeding unit in a direction of curling the wire by the curl guide.

Abstract: The present invention relates to the preservation and packaging of the agricultural products and discloses a gas remover and a method for packaging agricultural products. The gas remover provided herein is capable of effectively removing gas released in a vacuum sealer bag. The gas remover includes calcium hydroxide, which can effectively removes gas released by the plant-based agricultural products in the vacuum sealer bag, avoiding the expansion of the vacuum sealer bag.

Abstract: A bag clamping device for a material bag filling system is provided. A filling tube portion of a material bag can be blown to be in an upright state from a collapsed state through displacement and lift of an X-axis rail, a Y-axis rail and a Z-axis rail and blow of a pair of blowers. A pair of electric clamps is configured to clamp the filling tube portion. A pair of cantilevers is displaced to the bottom of a material filling device. The filling tube of the material filling device is displaced in a Z direction to enter the material bag for blowing air and filling the material. Through a conveyor belt displaced at the bottom in an X direction to carry the material bag with the filled material to a sealing device for sealing, so as to complete the packaging.

Abstract: A portable film packing apparatus includes a main body including a holding-and-drawing rod at the middle portion of the main body, a first combining rod is at a one end, and a second combining rod is disposed at the other end of the main body; a first roller unit having a first roller having its opposite ends respectively fixed with a pair of a first roller unit gears; and a second roller unit having second roller having its opposite ends respectively fixed with a pair of a second roller unit gears, wherein the first roller unit and the second roller unit are provided with the pair of the first roller unit gears and the pair of the second roller unit gears to mesh with each other, wherein a diameter of the first roller is smaller than a diameter of the second roller.

Abstract: A stretch-blown plastic container, includes a container body which encloses a filling volume with a container bottom; a container neck which adjoins an opposite end of the container body, having a container opening and an integrated handle region, the handle region being hollow and joined to the filling volume which is enclosed by the container body; and between the handle region and the container body, a through opening recessed and bordered over its entire periphery by wall parts of the container body and of the handle region which have been welded to one another.

Abstract: Disclosed is a dual container device comprising a bottom container comprising a first base, a top member comprising one or more first openings, and a first wall extending between the first base and the top member, a top container comprising a second base comprising one or more second openings, and a second wall extending from the second base, an intermediate wall extending either upwardly from the upper rim of the first wall or downwardly from the lower rim of the second wall, the intermediate wall for slidably receiving the container that is not attached thereto therethrough, and guides and tracks disposed on the interior surface of the intermediate wall and the exterior surface of the wall of the container received within the intermediate wall such that motion of the top container with respect to the bottom container is restricted to between an open position and a closed position.

Abstract: The disclosure relates to a package comprising a sleeve and an insert received in the sleeve, where the insert is movable between a retracted and extended configuration. The insert includes a carrier having a passage, and a band extending around a wall of the carrier and through the passage. The insert further includes a first member located within the passage when the insert is in the retracted configuration, the first member being attached to the band, wherein at least a portion of the band that overlies the wall is exposed for attachment to the sleeve of the package at a second coupling location on the exposed portion of the band.

Abstract: A top cap for use in combination with a transport system comprises a rectangular layer of material having a first side edge, a second side edge, a first end edge, a second end edge, an upper surface and a lower surface. The layer of material includes a plurality of ribs extending downward from the lower surface and, a plurality of spaced apart projections extending downward below a lower edge of the plurality of ribs. The top cap does not include a downward extending lip along the first side edge and the second side edge.