Abstract: Disclosed is a wing assembly, the wing assembly defining a direction of flow with respect to which the wing assembly is configured to create lift for an aircraft, comprising a main section configured to be mounted to a fuselage to extend from the fuselage in an extension direction of the wing; and a plurality of flap sections each with a body part, which are mounted to the main section in a pivotable manner to be individually pivotable around a pivot axis over a range of angular orientations including a horizontal orientation in which the body part of the flap section is substantially aligned with the main section to form an elongate and substantially continuous cross-section; and a vertical orientation in which the flap section is angled downwards with respect to the main section. An aircraft equipped with at least one pair of such wing assemblies is also described.

Abstract: Embodiments according to the invention relate to a decoder for providing decoded parameters of a neural network on the basis of an encoded representation, wherein the decoder is configured to obtain a first multi-dimensional array comprising a plurality of neural network parameter values using a decoding of neural network parameters and wherein the decoder is configured to obtain a re-ordered multidimensional array using a reordering, in which a first dimension of the first multi-dimensional array is rearranged to a different dimension in the re-ordered multidimensional array. Furthermore, encoders, methods and computer programs using a reordering are disclosed.

Abstract: An electric drive with a fan for an aircraft, wherein the electric drive comprises an electric machine, in particular a permanently excited electric machine, with a stator and a rotor, and the propeller comprises a shaft and rotor blades, wherein the rotor blades are attached to the shaft, the rotor comprises a laminated core and magnets, wherein the laminated core forms an annular arrangement around the shaft, and the rotor blades, the shaft, the laminated core and the magnets are connected in a thermally conductive manner so that the rotor blades form a heat sink for the magnets.

Abstract: The invention relates to a winding device (100) for winding a fibre coil, comprising a coil carrier (110) for wrapping with fibre (210) in order to produce a coil body (220) made of wound fibres (210), a fibre supply (120) for supplying a fibre (210) for wrapping the coil carrier (110), and an adhesive device (130) for producing droplets of adhesive (140) for bonding the outermost layer of fibres (210) on the coil body (220) to fibres (210) freshly laid onto the coil body (220).

Abstract: The present invention relates to an integrated controller unit (10) for controlling at least one engine motor (26) and at least one servo motor (28), comprising a power link section (12) for connecting the controller unit (10) to an external power supply (14) and supplying power to the individual sections of the controller unit (10), a data link section (16) for connecting the controller unit (10) to an external data source, a computing section (18) operatively connected with the power link section (12) and the data link section (16) for receiving data from the external data source, performing computing tasks based on the received data and outputting control commands, an engine interface section (20) for driving the at least one engine motor (26), and a servo interface section (22) for driving the at least one servo motor (28), wherein the engine interface section (20) and the servo interface section (22) are both operatively connected to the computing section (18) and adapted to drive the at least one engine

Abstract: The present invention relates to a wing assembly (10) for an aircraft with a fuselage and at least one pair of wings, the wing assembly (10) defining a direction of flow (F) with respect to which the wing assembly (10) is configured to create lift for the aircraft, comprising a main section (12), which is configured to be mounted to the fuselage in a fixed manner so as to extend from the fuselage in an extension direction of the wing; and a plurality of flap sections (14) each with a body part (16), which are mounted to the main section (12) in a pivotable manner so as to be individually pivotable around a pivot axis (A) by means of a pivoting means (18) over a range of angular orientations including a horizontal orientation in which the body part (16) of the flap section (14) is substantially aligned with the main section (12) to form an elongate and substantially continuous cross-section; and a vertical orientation in which the flap section (14) is angled downwards with respect to the main section (12).

Abstract: An aircraft includes a fuselage and first and second pairs of aerofoils, the aerofoils of each pair extend from opposing sides of the fuselage. Each aerofoil includes a first lift body and a second lift body which is arranged behind the first lift body in a direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil. At least one engine is arranged on the second lift body of at least one of the first and second pairs of aerofoils.

Abstract: An aircraft includes a fuselage and first and second pairs of aerofoils, the aerofoils of each pair extend from opposing sides of the fuselage. Each aerofoil includes a first lift body and a second lift body which is arranged behind the first lift body in a direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil. At least one engine is arranged on the second lift body of at least one of the first and second pairs of aerofoils.

Abstract: An aerofoil for an aircraft includes an engine, a first lift body, and a second lift body which is arranged behind the first lift body in the direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil.

Abstract: An aerofoil for an aircraft includes an engine, a first lift body, and a second lift body which is arranged behind the first lift body in the direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil.

Abstract: A mechanism for stowing and/or adjusting a ducted propeller of a flying object, the flying object comprising a fuselage and at least one pair of wings, the outer walls of which together define a shell of the flying object, comprising a ducted propeller comprising a substantially cylindrical duct, which defines a longitudinal axis of the ducted propeller and is open at the base faces thereof, a rotor comprising a plurality of rotor blades, which is set up to rotate in a plane perpendicular to the longitudinal axis of the ducted propeller, and a drive device for driving the rotor; a receiving chamber, provided in the fuselage and/or a wing of the flying object, for the ducted propeller; a mechanism which is set up to transfer the ducted propeller from a stowed state into a deployed state.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: Engraftment of therapeutic cells and agents to a target site in an organism is enhanced by mechanical, chemical and biological methods and systems.

Abstract: A transient suppression circuit is provided. The circuit comprises a first node having positive and negative terminals and being configured to be electrically coupled to a switching control circuit. The switching control circuit is operative to provide power to an inductive load. The circuit includes a second node having positive and negative terminals and being configured to be electrically coupled to the inductive load. A first conductor is connected between the positive terminals of the first and second nodes and is configured to provide a current path between the switching control circuit and inductive load. The circuit further includes a second conductor connected between the negative terminals of the first and second nodes and is configured to provide a return current path between the inductive load and the switching circuit. One of the first and second conductors further includes a switching device selectively coupling the inductive load and switching circuit.