Abstract: A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.

Abstract: This invention describes a rotating wing that provides lift to an aircraft and that is driven by autorotation. It is a naturally stable rotating wing as it does not generate torque and is very safe because it uses autorotation at all times to drive its blades. The design of the blades allows you to use the autorotation in two different ways. The first dependent on the airflow created by moving the aircraft from one place to another and which provides a cruise flight mode and the second independent of the aircraft's movement from one place to another to provide a static flight mode that includes the ability to take off and land vertically, as well as hover at a static point in the air.

Abstract: An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency.

Abstract: An aircraft includes a wing positioned below a vertical rotor, the wing extending in a transverse direction to a wingtip having an outboard face, and a turbulence feature located on the wingtip and oriented to induce turbulence in the rotor downwash flowing across the outboard face in a direction from a top surface of the wing to a bottom surface of the wing.

Abstract: A method of operating a landing gear controller for an aircraft, including: the landing gear controller receiving one or more signals from at least one position sensor. The one or more signals indicate a position of one of a landing gear bay door and a landing gear when the landing gear bay door or the landing gear, respectively, is part way through a range of travel between two limits of travel. The method may also include the landing gear controller controlling movement of the other of the landing gear bay door and the landing gear on the basis of the one or more signals.

Abstract: A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmember parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

Abstract: A drive augmenter provide supplemental drive power to the wheel of a landing gear with a drive system. The landing gear has a wheel rotatably mounted to an axle, and the drive system selectively provides a driving force to rotate the wheel. The drive augmenter includes a piston slidably disposed with a cylinder, and selective pressurization of the cylinder drives reciprocating translation of the piston within the cylinder. A crank is coupled to the piston by a rod and is also coupled to a crankshaft. The crank is configured to convert translation of the piston into rotation of the crankshaft. The drive augmenter further includes a drive shaft coupled to the wheel and a clutch configured to selectively transfer rotation of the crankshaft to the drive shaft.

Abstract: An autobrake system includes a brake control unit (BCU), and a control knob in electronic communication with the BCU. The BCU is configured to receive a position signal from the control knob, the position signal corresponding a position of the control knob. The BCU is configured to select a braking deceleration based upon the position signal, wherein the braking deceleration continuously changes between a minimum braking deceleration and a maximum deceleration in response to the control knob moving between a first position and a second position for fine tuning of the braking deceleration.

Abstract: A piston engaging member of a piston assembly for engaging a pressure plate of an aircraft brake system, the engaging member comprising a body having a first side configured to selectably engage with the pressure plate, and a mount on a second side of the body configured to mount the piston engaging member with a piston of the piston assembly wherein the body comprises a cellular structure between the first and second sides.

Abstract: A transmission lubricating assembly of a helicopter includes: a transmission including a speed change structure that changes the speed of rotation produced by rotational power input from a prime mover and outputs the resulting rotational power and a housing accommodating the speed change structure; and a lubricator that lubricates the speed change structure. The lubricator includes a collector that collects a mist of a lubricating oil in an internal space of the housing and a dropper that is disposed below the collector and that applies droplets of the lubricating oil to the speed change structure, the droplets resulting from the collected mist being gathered under its own weight.

Abstract: A rotor blade retention device for use in an aircraft having a plurality of blades includes an array of cavities, each cavity adapted to receive a portion of a tension-torsion strap therein. Each cavity is oriented such that, when the portion of the tension-torsion strap is received therein, a central plane of the tension-torsion strap is inclined relative to a blade plane of rotation defined by the plurality of blades. The retention device may have a body that defines an aperture adapted to receive a portion of a rotor mast of the aircraft, may comprise a rotor mast of the aircraft, or may comprise first and second plates that cooperate to form the array of cavities and that are adapted to receive a portion of the rotor mast of the aircraft.

Abstract: A coaxial rotor system includes a center mast non-rotatably disposed at and extending from a helicopter. A rotation axis extends along the center mast. An inner mast is disposed along the center mast and is rotatable about the rotation axis in a first direction. A portion of the inner mast extends above an end of the center mast. An outer mast circumscribes the center mast and is rotatable about the rotation axis in an opposite second direction. The center mast extends above an end of the outer mast. An upper rotor blade assembly is rotatable with the inner mast. A lower rotor blade assembly is rotatable with the outer mast. A control system disposed at the center mast between the upper and lower rotor blade assemblies is operable to adjust pitch of a plurality of upper rotor blades and to adjust pitch of a plurality of lower rotor blades.

Abstract: A vertical take-off and landing aircraft includes a ducted rotary wing. The ducted rotary wing includes a duct and a rotary wing. The duct runs through a body from an upper surface to a lower surface thereof. The rotary wing is provided inside the duct and includes a hub and a blade configured to rotate about the hub. The blade includes a tip inlet, a trailing-edge outlet, and a trailing-edge flow path. The tip inlet is provided on a tip surface of the blade. The trailing-edge outlet is provided at a trailing edge that is an edge on a rear side in a rotation direction of the blade. The trailing-edge flow path allows the tip inlet and the trailing-edge outlet to be in communication with each other.

Abstract: Disclosed is an electric aircraft, which includes a fuselage and at least one wing coupled to the fuselage. The electric aircraft includes a plurality of tilting fans coupled to the at least one wing, the plurality of tilting fans being configured to move between a vertical lift position and a forward flight position. The electric aircraft includes a plurality of tilting mechanisms coupled with at least one tilting fan. The electric aircraft includes a first actuator coupled to a first subset of the plurality of tilting mechanisms. The first subset of tilting mechanisms are identified among the plurality of tilting mechanisms according to a coupling scheme. The first actuator tilts a first group of tilting fans coupled to the first subset of the plurality of tilting mechanisms simultaneously.

Abstract: A method is described for the folding of a convertiplane with a fuselage having a first axis, a pair of wings and a pair of rotors arranged on respective mutually opposite sides of the respective wings; each rotor comprises a mast rotatable about a second axis and a plurality of blades; each wing comprises a first portion fixed with respect to the fuselage; a second tip portion opposite to the first portion; and a third intermediate portion, which is interposed between the associated first portion and second tip portion; the mast of each rotor is integrally tiltable with the second axis and associated second tip portion about a third axis transversal to the second axis and the fuselage so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; the method comprises the steps i) of arranging the convertiplane in the helicopter configuration and ii) rotating a pair of assemblies of respective wings with respect to the fuselage and the associated first portion about respect

Abstract: A flying car that does not require complex transformation between a car and an aircraft, the flying car can quickly take off from a land, such as road or parking, and can land on the road or parking. The flying car is of triangular shape having a broad front and narrow rear. Three motorized members are coupled to three corners of a frame of the flying car. Each of the three motorized members includes a wheel assembly that includes a wheel and a wheel frame, an inner ring and an outer ring coupled to each other, and both mounted to the wheel frame. A fan mounted on the inner ring and one or more turbines mounted on the outer ring.

Abstract: A communication management device provided in a flight vehicle that communicates with a base station management device that manages a plurality of base stations, includes: a first communication unit that transmits and receives control signals of an airframe of the flight vehicle or flight information of the flight vehicle to and from the base station management device; a second communication unit that provides communications among the plurality of wireless terminals as a base station; an acquisition unit that acquires anomaly information indicating that an anomaly of the first communication unit or an anomaly of a flight state of the flight vehicle has occurred, and an anomaly reporting unit that transmits the anomaly information to the base station management device via the second communication unit when the anomaly information is acquired by the acquisition unit.

Abstract: The present disclosure relates to an information processing apparatus and information processing method of more easily capturing image in accordance with more various situations. An imaging device including an imaging function unit and an imaging range variable unit is controlled on the basis of vehicle information that is information regarding a vehicle. For example, on the basis of vehicle information obtained in a patrol car, such as vehicle location and position information, vehicle speed information, vehicle operation information, or vehicle attached equipment information, imaging of a subject by the imaging device provided to a flying body and flight by the flying body are controlled. The present disclosure can be applied to, for example, an information processing apparatus, an image processing apparatus, a communication apparatus, an electronic device, an information processing method, or the like.

Abstract: An unmanned aerial vehicle capable of VTOL operation can include: a vehicle body defining longitudinal and transverse directions and opposing longitudinal sides; a first support boom coupled to the vehicle body at a first transverse axis and extending outwardly from the opposing longitudinal sides; a second support boom coupled to the vehicle body at a second transverse axis positioned rearward from the first transverse axis and extending outwardly from the opposing longitudinal sides; a plurality of electric motors coupled to a one of the first and second support booms, at least two electric motors of the plurality of electric motors positioned on each of the first and second support booms, a rotation axis of each of the at least two electric motors coupled to the second support boom offset in a transverse direction from a rotation axis of each of the at least two adjacent electric motors coupled to the first support boom; a plurality of rotors; and a propulsion system.

Abstract: An aircraft includes a central wing accommodating passengers and/or freight and two lateral wings that pivot on the central wing about respective axes of rotation. The various wings obey the following geometric characteristics: 0.3×Long<Larg<Long, 0.11×Long<Haut<0.25×Long, Env>1.4×Long, wherein Larg being the distance between the two axes, Long being the length of the central wing, Haut being the height of the central wing, Env being the wingspan of the aircraft. The axes of rotation are inclined by an angle relative to the vertical axis of the aircraft such that the lateral pivot from rear to front and vice versa so as to come closer to, or deploy on either side from, the fuselage.

Abstract: Methods, systems and devices of the various embodiments may provide slat-cove fillers configured to reduce leading-edge slat noise on aircraft, such as transport aircraft.

Abstract: Wing assemblies comprise a three-position Krueger flap and an actuation assembly that comprises a drive linkage assembly, a primary linkage assembly coupled between the drive linkage assembly and the three-position Krueger flap, and a secondary linkage assembly. The primary linkage assembly comprises a dual linkage that is pivotally and translationally coupled relative to a wing support structure. The secondary linkage assembly comprises a cam, a follower, and a dual-linkage axle that is coupled to the follower and to the dual linkage and that defines a dual-linkage pivot axis of the dual linkage.

Abstract: A dump gate system for a fluid hopper in a firefighting aircraft. A gate sealably engages a gate opening in the hopper at a closed position. The gate is hingedly connected about the gate opening, and a drive shaft is supported within the hopper. A crank arm is fixed to the drive shaft and is further coupled to the gate by a connecting link. The crank arm and the connecting link define an over-center geometry while the gate is at the closed position, such that weight of the fluid on the gate induces torque on the drive shaft in a gate-closing direction. A linear electric motor is selectively coupled to rotate the drive shaft in a gate-opening direction to thereby enable control of the fluid flow from the hopper according to an angular position of the drive shaft.

Abstract: An unmanned aerial vehicle according to an aspect of the present invention includes: an aerial vehicle body capable of flying; a winding machine provided to the aerial vehicle body and capable of winding and unwinding a linear member an end of which is connectable to a delivery target; and a fall prevention mechanism provided to the aerial vehicle body and capable of holding the delivery target disconnected from the linear member.

Abstract: A system for use in determining a capacity of a storage bin. The system includes a plurality of sensors positioned within the storage bin. Each sensor is configured to determine a used capacity within a portion of the storage bin, and generate a voltage output based on the determined used capacity, wherein the plurality of sensors is configured to generate an aggregate voltage output based on the voltage output of each sensor. A controller is in communication with the plurality of sensors. The controller is configured to receive the aggregate voltage output from the plurality of sensors, determine a minimum voltage output and a maximum voltage output of the plurality of sensors, and determine a total used capacity of the storage bin as a function of the aggregate voltage output, the minimum voltage output, and the maximum voltage output.

Abstract: A seating arrangement for a passenger-carrying vehicle including a first seat and a third seat arranged in a first row and facing in a forward direction, and a second seat located rearwardly of the first and third seats. The third seat is offset forwardly with respect to the first seat, the second seat is offset with respect to each of the first and third seats in a transverse direction that is perpendicular to the forward direction such that it is located between the first and third seats in the transverse direction. The combined effect of the transverse offset of the seats in adjacent rows, together with the forward offset of the seats in any given row provides seated passengers with a larger passenger accommodation region than is provided by conventional seating arrangements.

Abstract: A seating assembly provides direct aisle access for each seat in a row by employing a seat angling with respect to a cabin centerline. The seat angling opens up an area behind each seat back. Seat density may be increased by staggering the seats such that the opened area behind a forward row may be used to provide an armrest for a passenger in a next row. Seat density may be even further increased by overlapping the assemblies (as seen facing the seat) such that: the armrest for the forward row seat overlaps the legroom of the next row seat.

Abstract: Provided is a cushion for an aircraft seat including at least one antimicrobially active pad made of at least one plastic material, the pad having at least two antimicrobially active substances contained therein. The antimicrobially active substances do not contain silver or silver ions, and at least one antimicrobially active flame retardant fabric covering side at least one pad.

Abstract: An assembly is provided for a structure. This assembly includes a composite skin and a thermal anti-icing system. The composite skin extends between an exterior surface and an interior surface. The thermal anti-icing system includes a susceptor and a waveguide. The susceptor and the waveguide are integrated into the composite skin between the exterior surface and the interior surface. The waveguide is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

Abstract: A shock absorber assembly, particularly for attenuating shocks transmitted to a person's body, especially to reduce shock to a paratrooper's body during a tethered cargo tandem jump. Specialized elastic absorber units are disposed in series in connection with a tether or strap to maintain the series configuration. A chain reactive shock absorption can be predetermined, and adjusted based on the expected shock(s) of a given jump. The adjustment is accomplished by selecting the number and type of absorber unit(s) provided an any of two (or more) series chains of the assembly. In use, the complete shock absorber assembly is deployed between a cargo tether and a cargo harness.

Abstract: A regulator arrangement for an inflatable includes a regulator housing comprising a bore, the bore comprising a longitudinal axis, a piston disposed in the bore and configured to translate, with respect to the regulator housing, along the longitudinal axis, an adjuster plug disposed in the bore and axially adjacent the piston, an adjuster plug stop disposed at least partially within the bore, and a spring member disposed between the adjuster plug and the piston. The adjuster plug comprises a tapered head and a shaft portion extending from the tapered head. The adjuster plug stop comprises a tapered surface configured to contact the tapered head.

Abstract: An aircraft engine, has: an upstream stator having upstream stator vanes circumferentially distributed about a central axis; and a downstream stator having downstream stator vanes circumferentially distributed about the central axis, the downstream stator located downstream of the upstream stator relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes being different than a number of the downstream stator vanes, major portions of leading edges of the downstream stator vanes circumferentially overlapped by the upstream stator vanes, the downstream stator vanes including: a first pair of circumferentially adjacent vanes of the downstream stator vanes spaced apart by a first pitch, and a second pair of circumferentially adjacent vanes of the downstream stator vanes spaced apart by a second pitch different than the first pitch.

Abstract: An aircraft with folding mechanism, the aircraft including a fuselage, optionally a payload and/or landing gear attached to the fuselage, at least two longitudinal beams attached to the fuselage that preferably extend parallel to each other and parallel to a first aircraft axis, with lifting units attached to each of the longitudinal beams. At least one crossbeam is attached to the fuselage, and preferably extending parallel to a second aircraft axis and at right angles with respect to the longitudinal beams, with lifting units attached to the crossbeam. The longitudinal beams are rotatably attached to the fuselage by at least one respective first pivot joint configured for pivoting the longitudinal beams around a respective first pivot axis to a pivoted position. The crossbeam is rotatably attached to the fuselage, preferably by at least one second pivot joint, for pivoting the crossbeam around a second pivot axis to a pivoted position.

Abstract: A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, generate a failure notification configured to indicate that the vehicle controller received the failure datum from the sensor, and initiate an automatic response as a function of the failure datum.

Abstract: An exhaust muffler for an APU of an aircraft, including an exhaust gases inlet, an exhaust gases outlet, a peripheral wall configured to guide a flow of exhaust gases between the inlet and the outlet. The peripheral wall includes at least one vacuum chamber to provide thermal insulation.

Abstract: An auxiliary fan based hybrid cooling system of an electric machine is contemplated. The hybrid cooling system comprises a propeller positioned on an exterior portion of an enclosure and mechanically coupled to a rotor, at least one electronic component, a stator, the rotor, and an auxiliary fan disposed within the enclosure, and wherein: in a single cooling mode, the propeller rotates to generate air that is channeled into the enclosure, in a dual cooling mode: the propeller rotates to generate the air that is channeled into the enclosure, a coupling mechanism simultaneously engages the rotor and the auxiliary fan and links the propeller to the auxiliary fan by the engaging of the rotor with the auxiliary fan, and the auxiliary fan, rotates responsive to the rotation of the propeller in the dual cooling mode.

Abstract: An aircraft blade assembly, including: a blade extending from a blade root to an opposite tip; and a heat exchanger disposed on at least a portion of a leading edge of the blade, the heat exchanger including: a first arcuate panel shaped to conform to the leading edge of the blade; and a second arcuate panel mated with the first arcuate panel; wherein at least one of the first and second arcuate panels includes a channel formed thereon to form a fluid passage between the first and second arcuate panels.

Abstract: A propulsion system is described that includes an electrical bus, a generator configured to provide electrical power to the electrical bus, a plurality of propulsors configured to provide thrust by simultaneously being driven by the electrical power at the electrical bus, and a controller. The controller is configured to synchronize a rotational speed of an individual propulsor from the plurality of propulsors with a rotational speed of the generator after the individual propulsor has become unsynchronized with the rotational speed of the generator by controlling at least one of the rotational speed of the generator, nozzle area of the individual propulsor, or a pitch angle of the individual propulsor.

Abstract: An aircraft including a fuselage, a power generator configured to provide power to the aircraft, and at least one fuel tank for holding fuel for the power generator, and a fuel delivery assembly. The fuel tank is positioned in the fuselage and is configured to hold hydrogen fuel in a liquid phase. The fuel tank has a chamber for holding the hydrogen fuel and a fuel extraction line fluidly coupled to the chamber. The fuel extraction line extends from the fuel tank in a forward direction of the fuselage and at a downward angle relative to a centerline of the fuselage. The fuel delivery assembly is fluidly coupled to the fuel extraction line and fluidly connects the fuel tank to the power generator. The fuel delivery assembly is configured to provide the hydrogen fuel from the fuel tank to the power generator.

Abstract: An auxiliary power unit (10) for an aircraft (1) comprises a gas turbine engine comprising an engine core (12). The engine core comprises a core compressor (14) and core turbine (18) coupled by a core shaft (24). The auxiliary power unit further comprises a load spool comprising a load compressor (30), a load turbine (20) and a permanent magnet electric machine (28), each being coupled by a load shaft (26). The load shaft (26) and core shaft (24) are configured to rotate independently of one another.

Abstract: A system is disclosed, in accordance with one or more embodiments of the present disclosure. In one embodiment, the system includes a plurality of image capture devices, a controller communicatively coupled to the plurality of image capture devices, wherein the controller includes one or more processors configured to receive a plurality of reference images including one or more source objects, identify the one or more source objects, determine one or more gestures indicative of one or more control signals of the one or more source objects, determine the one or more control signals; and provide the one or more control signals.

Abstract: A system may include a display and a processor communicatively coupled to the display. The processor may be configured to: output, to the display, a first view of an airport moving map (AMM) having a first map range, the AMM depicting a location of an aircraft on an airport surface; receive aircraft state data and airport surface data; based at least on the aircraft state data and the airport surface data, change the first view of the AMM having the first map range to a second view of the AMM having a second map range; and output, to the display, the second view of the AMM having the second map range.

Abstract: An exterior aircraft light with integrated light output monitoring includes a light source support, at least one light source, arranged on an outward facing side of the light source support, an aperture in the light source support, a light collection surface, arranged to direct an output monitoring light portion of the light, emitted by the at least one light source, through the aperture in a predefined angular range with respect to the light source support. The light also includes a light detector, arranged on a back side of the light source support, and a total internal reflection optical element, arranged to direct the output monitoring light portion, having travelled through the aperture in the predefined angular range with respect to the light source support, to the light detector via total internal reflection.

Abstract: A cargo restraint system includes a driving shaft, a first restraint, and a second restraint. The first restraint is operatively coupled to the driving shaft via a first indexing mechanism arrangement. The second restraint is operatively coupled to the driving shaft via a second indexing mechanism arrangement. The first and second indexing mechanism arrangements are arranged such that rotation of the driving shaft in a first rotational direction causes the first restraint to rotate between a lowered position and a raised position, and further rotation of the driving shaft in the same rotational direction causes the second restraint to rotate between the lowered position and the raised position. The first restraint may be axially offset from the second restraint to allow sequential loading and unloading of cargo.

Abstract: Unmanned aerial vehicle (UAV) launch and recovery is disclosed. A disclosed example apparatus for recovering a UAV includes a base to be mounted to a recovery vehicle, a flexible arm extending from the base to pivot therefrom, the arm having a first end at the base and a second end opposite the first end, the arm to move to counteract a movement of the recovery vehicle, and a coupler mounted on or proximate the second end of the arm, the coupler to be releasably coupled to the UAV.

Abstract: An easy extention of a telescopic rod. The telescopic rod extends in the axial direction by a gas forcibly fed to the inside and is provided with a posture control means.

Abstract: A method for controlling operation of an unmanned aerial vehicle (UAV), includes receiving one or more commands selected by a user via a remote controller of the UAV, and in response to a received landing command: identifying the vehicle from a plurality of vehicles for landing, navigating the UAV to travel in a substantially same direction as the vehicle, and controlling the UAV to land on the vehicle when the UAV approaches the vehicle. The one or more commands includes at least the landing command to land the UAV on a vehicle while the vehicle is in operation.

Abstract: A method for loading an Unmanned Aerial Vehicle with one or more items is disclosed. The method includes determining a weight and a Center of Gravity of each of a plurality of objects. The plurality of objects includes one or more of the Unmanned Aerial Vehicle, a container, one or more items to be delivered, and packaging for securing the one or more items to be delivered within one of the Unmanned Aerial Vehicle and the container. The method also includes optimizing a combined Center of Gravity of the plurality of objects for performing delivery by the Unmanned Aerial Vehicle.

Abstract: A nozzle for cooling a jet engine for maintenance is described. The jet engine includes an exhaust channel for the exit of exhaust gases of the jet engine, the nozzle includes a suction adapter having a round shape adapted to be connected in a sealed manner to the exhaust channel for sucking air from the exhaust channel, and a suction channel in fluid connection with the suction adapter for sucking air from the suction adapter. The suction channel is arranged to be connected to an air suction device. An apparatus for cooling a jet engine for maintenance and a method for maintenance of a jet engine are also described.

Abstract: [Object] To realize an improvement in design accuracy and a reduction in design time in a process of matching an equivalent cross-sectional area of a design shape of a supersonic aircraft to a target equivalent cross-sectional area in a sonic boom reduction method based on an equivalent cross-sectional area.