Lilium Patente

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Provided is a solid state power controller (SSPC). The SSPC comprises a power supply line configured to be connected between a power source and a load. Further, the solid state power controller comprises a semiconductor switching unit provided on the power supply line and configured to switch between at least two states according to a command signal. The at least two states include a conducting state and a non-conducting state. Further the solid state power controller comprises a state machine, which is configured to exhibit at least two states, including an ON state and an OFF state. The state machine is further configured to output the command signal according to a current state of the state machine.

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Valve apparatus for controlling fluid flow through a duct of an air conditioning system of an aircraft, the valve apparatus comprising:• a valve seat body (2) having a valve seat hole (3) being configured to allow the fluid to flow through it,• a damper body (4) for closing the valve seat hole (3),• wherein the valve seat body (2) and the damper body (4) are movable relative to each other between an open configuration and a closed configuration, wherein in the open configuration the fluid may flow through the valve seat hole (3) and in the closed configuration the damper body (4) interacts with the valve seat body (2) in a sealing manner such that the fluid may not flow through the valve seat hole (3),• wherein the valve seat hole (3) has a hole contour formed by a hole edge (5) and the damper body has a damper contour formed by a damper edge (6), the hole edge and the damper edge being configured to interact with each other in the sealing manner thereby forming a circumferential sealing line having a circumferential sealing length,• wherein the hole contour has a plurality of hole protuberances (7) and the damper contour has a plurality of damper protrusions (8), so that the circumferential sealing length is larger than a reference length being defined by a length of a circumference of an equal area circle (EAC) having an area equal to an area of the valve seat hole (3),• wherein the valve apparatus comprises a solenoid actuator (9) having an actuator rod for transmitting an actuator force, the solenoid actuator being mounted for moving the damper body (4) relative to the valve seat body (2) towards the closed or open configuration, and• wherein force transmission means (11) are arranged between the actuator rod (10) and the damper body (4), the force transmission (11) means being configured to apply a closing force to the damper body that is larger than the actuator force.

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An engine (100) for an aircraft is presented comprising a rotor (101), an electric motor (103) actuating the rotation of the rotor (101) and an ECU (104) controlling the electric motor (103), wherein the rotation of the rotor (101) provides a main flow of air causing the thrust of the engine (100) and wherein the ECU (104) is located within the volume defined by the main flow.

The present disclosure relates to an actuator (1) for generating an actuating movement for a primary flight control surface (2). This actuator (1) comprises an electric motor (5) and a reduction gear coupled thereto. This reduction gear is formed as a harmonic drive gear (strain wave gear) (6). The disclosure also relates to a civil aircraft equipped with such an actuator (1). In this aircraft, the actuator (1) according to the disclosure can be used in particular as a flap actuator for adjusting a flap structure (2) pivotally hinged to a trailing end of a wing structure (3).

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The present invention provides an engine 310 of a vertical take-off and landing aircraft 300, wherein the engine is configured to be movable with respect to an aircraft component 342 of the aircraft 300 between a hover position for take-off and landing, and a cruise position for forward flight, wherein the engine 310 comprises an aerodynamic component 332 having at least one aerodynamic element 334 movable between a first position 336 according to a first operational state of the aircraft, and a second position 338 according to a second operational state of the aircraft, the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.

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The present invention relates to a battery management system and method for performing a battery state and optionally health parameter observation, in particular cell state-of-charge (SOC) observation, with two redundant, independent and dissimilar lanes. Specifically, a SOC determination in a first one of the lanes is based on Coulomb Counting. The other lane employs a different algorithm than Coulomb Counting. In embodiments, a battery health observation is further performed independently by the two lanes, wherein the first lane employs an ageing model and the other lane a different (dissimilar) algorithm. On the basis of state and health observation, state (state of function) of the battery system can be predicted to determine a range of flight in accordance with a predetermined flight profile.

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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, 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.

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.

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).