Abstract: An aircraft propulsion system includes a turbomachine and at least one electric motor. The motor includes a first half-motor and a second half-motor that include, respectively, a first stator and a second stator cooperating with a common rotor of the motor. The propulsion system further includes at least one first energy source (B) capable of delivering a DC voltage and at least one electric generator (PMG) driven by the turbomachine. The electric generator generates an AC voltage to form a second energy source and is associated with an active rectifier that transforms the AC voltage into a DC voltage. The value of the DC voltage is controlled by the active rectifier, the output of which is connected to the first energy source.

Abstract: A wheel well fairing for reducing drag on an aircraft fuselage configured with an open wheel well for stowing landing gear of the aircraft. The wheel well fairing includes a Coanda fairing having a convex-shaped lower portion and an upper portion. The upper portion is configured for positioning adjacent an interior vertically-orientated sidewall of the wheel well, and the convex-shaped lower portion has a bottom surface configured to extend substantially parallel to and positioned adjacent with an outer hull surface of the fuselage. The convex-shaped lower portion is curved inwardly within the wheel well between the upper portion and bottom surface. The Coanda fairing is positioned at an aft portion of the wheel well to redirect airflow out of the wheel well in a rearward direction along the bottom hull surface of the fuselage.

Abstract: An aerial vehicle includes a propulsion unit and a fuselage unit. The propulsion unit includes a rotary shaft extending in a first direction and thrust producing mechanisms provided at both ends of the rotary shaft and produces a propulsion force for flying in air. The fuselage unit is suspended from the propulsion unit below the rotary shaft, has a center of gravity at a position below the rotary shaft, is configured to freely rotate around the rotary shaft, and is capable of storing an article.

Abstract: An actuation system for an aircraft can include an actuator and a plurality of clutches connected to and structured to be moved by the actuator. The actuation system can include a plurality of control levers connected to the plurality of clutches and structured to be moved by the plurality of clutches when the plurality of clutches are moved by the actuator. The actuation system can include a processor connected to the actuator and to the plurality of clutches. The processor can identify one or more clutches connected to one or more control levers of the plurality of control levers for controlling an operation of the aircraft, and cause the one or more clutches connected to the one or more control levers to be in an engaged stat. The processor can activate the actuator to cause movement of the one or more control levers via the one or more clutches.

Abstract: An aircraft wing is disclosed including a closed surface wing tip device which includes an element or actuator within the wing tip for deforming/morphing the shape of the wing tip between geometrical configurations having different aerodynamic properties, for example including one with better overall fuel efficiency for a shorter journey and one with overall fuel efficiency better suited for a longer journey. The device includes a lower winglet with an essentially planar portion spaced apart from the main body of the wing by a blended transition region which is shaped such that the curvature of the local dihedral increases in the outboard direction. The device includes an upper aerofoil structure which with the winglet essentially forms the closed surface. There is also disclosed an aircraft wing tip device having a sigmoid shaped (e.g. S-shaped) aerofoil structure blending in with a main wing of the aircraft.

Abstract: A support stay is provided to improve failsafe configurations for movable parts of an aircraft. The support stay supports the movable part with a primary body and a separate secondary body. The primary body and the secondary body provide separate load paths. The secondary body is attached to the primary body by a mechanical connection, e.g., rivets. If one of the bodies becomes structurally compromised, for example by a crack, this configuration does not transfer shear load between the primary and secondary body, so that the other body does not become structurally compromised.

Abstract: An up-down flapping wingtip is provided for a ground effect vehicle. The wingtip is positionable at an anhedral angle to control the wingtip clearance from ground. Variable wingtip clearance reduces the risk of damage due to collision with the ground or water, thereby permitting more efficient flight at lower altitude with an equivalent safety. The wingtip is positioned by a wingtip flap and an actuator. The wingtip anhedral angle is controlled by a flight control system. A sensor is included for determining whether an object lies in the path of the wingtip. The sensor communicates with the flight control system in order to vary the flapping angle of the wingtip to increase clearance from the ground or water, thus avoiding impact with the object. The wingtip anhedral angle is reduced to increase the wingspan for flight out of ground effect.

Abstract: An aerodynamic device includes a main aerodynamic body having a leading edge and a trailing edge, a flight control surface coupled to the main aerodynamic body near the trailing edge of the main aerodynamic body, and a translating body coupled to the flight control surface. The translating body is moveable relative to the flight control surface between a sealed position and a retracted position to define a gap. The translating body is extended toward the main aerodynamic body while in the sealed position to close the gap. The translating body is retracted away from the main aerodynamic body while in the retracted position to widen the gap. The gap adjusts an airflow flowing between the main aerodynamic body and the flight control surface.

Abstract: An assembly configured to be mounted within an interior of a vehicle. The assembly includes a monument wall configured to be mounted in the interior of the vehicle. A panel is configured to attach to a support structure above the monument wall with the panel having a first edge and a second edge. A latch configured to be mounted to the panel between the first edge and the second edge. A pull member is attached to the panel and comprises an elongated member attached to the latch and a handle. A translating hinge is configured to be mounted to the second edge of the panel to provide for translating and pivoting movement of the panel within an access area between the monument wall and the support structure to connect and disconnect the panel from the support structure.

Abstract: An electrical vertical takeoff and landing (eVTOL) aircraft includes an electrical propulsion unit that has a propeller or a fan configured to be driven to rotate by an electric motor arranged to receive electrical power from an inverter. The inverter includes a carrier substrate, and a converter commutation cell including a power circuit. The power circuit includes at least one power semiconductor switching element. Each power semiconductor switching element is comprised in a power semiconductor prepackage. A heat sink is arranged to remove heat from the respective power semiconductor prepackage. The heat sink is spaced apart from the carrier substrate to define a heat sink gap between the carrier substrate and the heat sink. A converter parameter ?, which is defined as a size of the heat sink gap divided by a maximum electric field strength in the heat sink gap, is less than or equal to 20 nm2/V.

Abstract: Systems, devices, and methods including one or more rib mounting flanges, where each rib mounting flange comprises: a spar opening configured to receive a main spar of a wing panel; one or more holes for receiving cross-bracing cables; and one or more holes for receiving cross-bracing cables; and one or more holes for connecting the rib mounting flange to an adjacent rib mounting flange.

Abstract: An aircraft wing including a fixed wing and a wing tip device rotatable about a hinge at the tip of the fixed wing is disclosed. The wing further includes a hinged panel at the boundary between the wing tip device and the fixed wing. In the flight configuration the panel is closed such that the panel is substantially flush with the upper surface of the wing, and the hinged panel is located in the path of a moveable element (for example part of an actuation mechanism, such as a curved rack). In the ground configuration the panel is hinged open to a position outside the path of the moveable element such that clashing of the moveable element with the stationary structure at the tip of the fixed wing is avoided.

Abstract: A radiofrequency (RF) shielding conduits that can be embedded within a doorframe and/or a door of a magnetic resonance imaging (MRI) room are disclosed. The RF shielding conduits can form, upon closing of door onto the doorframe, an RF shielding channel to enclose and/or allow passage of tubing of medical equipment extending from an interior of the MRI room to an environment that is external to the MRI room, while providing a RF shielding of the MRI room.

Abstract: A tail sitter aircraft includes a wing with a closed front section and a fuselage, from which the wing extends. The wing includes a first portion projecting from the fuselage and a second portion spaced from the first portion. The aircraft includes first and second connecting section that are interposed between the first and second portions. The fuselage extends parallel to a first axis and the first and second portions extend parallel to a second axis orthogonal to the first axis. The first axis is arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position.

Abstract: Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.

Abstract: Methods and systems for adjusting a force feel profile of an inceptor of an aircraft are provided. The force feel profile is based on a baseline value of an operating parameter of the aircraft and defines an amount of resistive force applied to the inceptor as a function of displacement of the inceptor. An embodiment of the method includes receiving data indicative of a current value of the operating parameter. Based on a difference between the current value and the baseline value of the operating parameter, a portion of the force feel profile corresponding to a range of displacement values is shifted to adjust an amount of resistive force defined by the portion of the force feel profile for the range of displacement values.

Abstract: Systems, devices, and methods including a wing panel; a spar disposed in the wing panel, where the spar comprises: an upper cap; a lower cap; a honeycomb core connected between at least a portion of the upper cap and the lower cap; an inner face sheet; and an outer face sheet, where at least a portion of the honeycomb core is disposed between the inner face sheet and the outer face sheet.

Abstract: An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a rear portion with a concave surface, such that the fairing acts as a lift-generating surface when the aircraft is in flight.

Abstract: An aircraft is provided which includes a fuselage having a first wing with curved wingtips positioned above a second wing having curved wingtips. Rotor assemblies located in between the curved wingtips of the first and second wing, are employable to both provide vertical thrust for vertical take off of the aircraft and auto rotation to generate electric energy to recharge an onboard electric power supply. The first wing may be formed in a V-shape, and additional rotor assemblies to provide forward and vertical thrust to the airplane can be included on rotatable canards.

Abstract: A door assembly for a seat unit provided within a vehicle cabin, in particular an aircraft cabin, the door assembly comprising at least a fixed base structure, a door element movably mounted on the base structure and which is movable between a fully retracted position and at least one deployed position, and a door slide device provided between the base structure and the door element to movably support the door element on the base structure. Further, the door slide device comprises at least a slide carrier bracket fixed to the base structure or the door element, at least one slide unit which is coupled to the slide carrier bracket in a normal operation mode, and at least one separate auxiliary slide arrangement.