Lilium Patente

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A vapor cycle refrigeration system (100) for an aircraft comprises a compressor (10), a condenser unit (20) with a condenser radiator (22), a condenser fan (24) and a condenser air duct (26) configured to direct a stream of air generated by the condenser fan (24) through the condenser radiator (22), an expansion device (30), an evaporator unit (40) with an evaporator radiator (42), an evaporator fan (44) and an evaporator air duct (46) configured to direct a stream of air generated by the evaporator fan (44) through the evaporator radiator (42), and a piping system (50) connecting the compressor (10), the condenser radiator (22), the expansion device (30) and the evaporator radiator (42) in a closed circuit for a refrigerant,wherein each of the compressor (10), the condenser radiator (22), the condenser fan (24), the expansion device (30), the evaporator radiator (42), the evaporator fan (44) and the piping system (50) is fully supported directly or indirectly by at least one of the condenser air duct (26) and the evaporator air duct (46), preferably by the condenser air duct (26), in such a manner that the system (100) is self-supporting.

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The invention refers to an aircraft, particularly an aircraft capable of vertical take-off and landing, comprising a fuselage, and a variable lift body defining an aerofoil and being moveably attached to the fuselage, wherein the variable lift body is pivotable around a first axis extending in the wing span direction; wherein a rotary actor adapted to cause the variable lift body to pivot in relation to the fuselage arranged within the aerofoil.

The present invention provides a wing structure for a vertical take-off and landing aircraft (10), comprising a wing (16) and at least two engines (18), each engine of the two engines being mounted to the wing (16) such as to be movable between a hover position with vertical thrust direction and a cruise position with horizontal thrust direction, wherein one of the two engines is mounted to a leading edge (22) of the wing and the other one of the two engines is mounted to a trailing edge (24) of the wing.

The invention refers to an aircraft, in particular to a vertical take-off and landing aircraft, and to a wing of such aircraft comprising a plurality of actuated flaps (2) each having at least one propulsion unit (4) included, the flaps BEING arranged next to each other along the wing span and independently actuated to pivot and further comprising an elastic seal in a gap between at least two of the flaps.

Rotor assembly (10), comprising a plurality of individual blade elements (12a, 12b, 12c), a first and a second ring element (14a, 14b), wherein the first and second ring elements (14a, 14b) are directly or indirectly coupled to each other by means of at least coupling unit thus forming a hub section (14) of the rotor assembly (10), wherein further each of the blade elements (12a, 12b, 12c) engages with at least one of the ring elements (14a, 14b) such that the blade elements (12a, 12b, 12c) are equidistantly distributed around the circumference of the hub section (14).

The present invention relates to an electrode comprising at least one metal foil and at least two layers each comprising at least one lithium ion acceptor.

A battery module (10) for a vehicle (100), in particular for an aircraft, comprises a housing (20), a cell stack (14) accommodated in the housing (20), an internal channel system (26) for heat transfer fluid disposed in the housing (20), a fluid inlet connector (42) and a fluid outlet connector (44) connected to the internal channel system (26) and adapted to being connected to an external thermal management system, wherein the fluid inlet connector (42) and the fluid outlet connector (44) are self-sealing connectors molded into the housing (20), preferably self-sealing and dripless connectors.

System 10 for navigating an aircraft 12, comprising a flight planning system 14 configured to prepare a set of at least three different trajectories for a flight from a departure point to a destination point, a flight verification system 16 configured to verify each trajectory of the set of trajectories, an onboard flight management system 26 to be installed at an aircraft 12 and having a storage unit 28 for storing the set of trajectories, wherein the flight management system is configured to select one of the trajectories from the set of trajectories as an active trajectory for a current flight of the aircraft, wherein the flight management system 26 includes a replanning unit 30 configured to change, during the current flight, the active trajectory by selecting a second trajectory from the set of trajectories as the active trajectory for the current flight, such as to continue the current flight based on the second trajectory t.

Provided is a power distribution network. The power distribution network comprises a ring-formed power line and a plurality of power nodes connected to the ring-formed power line. In addition, the power distribution network includes a plurality of circuit protection units, wherein each of the circuit protection units is provided between one of the plurality of power nodes and the ring-formed power line or on the ring-formed power line between two adjacent power nodes. The present invention is defined by the appended claims and is not limited to the particulars of the embodiments of the above detailed description.

An aircraft landing gear is presented comprising a drive with a preferably electric motor, a gear and at least one wheel having a rim, the gear is configured to transmit torque generated by the motor towards the wheel for driving the wheel of the landing gear, the rim has an axially extending rim section and the gear and/or the motor is at least partially surrounded by the axially extending rim section. In order to obtain a very compact arrangement at least one elastic member is provided, which is located at least partially between the motor and the wheel, preferably between the gear and the wheel, for transmitting torque of the motor towards the wheel.