Lilium Patente

The invention refers to an aircraft landing gear assembly for an aircraft, in particular a vertical take off and landing aircraft, comprising a mounting bracket configured to connect to an airframe of the aircraft, a least one wheel connected to and rotatable with respect to the mounting bracket about a horizontal rotational axis, an electric drive actuator including a first electromotor configured to turn the wheel around the horizontal rotational axis; and a steering actuator including a second electromotor configured to turn the at least one wheel and/or the mounting bracket around a vertical rotational axis; a single electronic control unit controlling both the electric drive actuator as well as the electric steering actuator.

An aircraft (1) comprising at least one airfoil and at least one engine (5) arranged on the trailing edge (12) of the airfoil, the engine (5) comprising an engine housing (6) and an engine inlet (7), an ice protection system (9) provided on at least one region of the airfoil and/or the engine housing (6) which is/are arranged upstream of the engine inlet (7), the ice protection system (9) comprises an ice shedding device adapted for shedding ice formations formed on the airfoil and/or the engine housing (6) into ice pieces and the ice shedding device is adapted to control the size of the shed ice pieces to stay below a predetermined maximum size. Method of removing ice formations from an airfoil of an aircraft wherein at least one engine is arranged on the trailing edge of the airfoil, comprising the following steps: removing the ice formations on the airfoil from the airfoil by breaking the ice formations into pieces using an ice protection system and controlling the size of the removed ice pieces to stay below a predetermined maximum value by the ice protection system.

The present invention relates to a battery management system for an electric air vehicle such as an eVTOL aircraft for observing a battery system state and optionally a battery health state of an energy storage system of the air vehicle. Based on an observation result, a state prediction, in particular, a prediction of the remaining accessible energy, can be carried out during a flight according to a planned flight profile and a range of the flight is determined. Hence, it can be confirmed during the flight that the intended destination can be safely reached with the remaining accessible energy. Otherwise, an alert to an operator is issued. State observation according to the present invention is performed using a two-lane architecture, wherein vehicle management computers are integrated in each of two independent and dissimilar lanes each including battery cell measurement equipment and independently performing a state observation using dissimilar algorithms.

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). The invention further relates to an aircraft equipped with at least one pair of such wing assemblies.

Ducted fan engine (1) configured for providing thrust for an aircraft (100), in particular an aircraft having vertical takeoff and landing capability, comprising: a shroud (3) having a substantially circular cross section; a stator (5) having one or more substantially radially extending stator vanes (51); and a rotor (7) rotatably supported by the shroud; wherein the rotor comprises at least 19 rotor blades (71), in particular at least 25 rotor blades.

The present invention relates to a method for monitoring the integrity of an inertial measurement assembly (10) of an aircraft, the measurement assembly comprising at least one high-grade measurement unit (20); and at least two low-grade measurement units (30, 40); wherein each of the measurement units (20, 30, 40) comprises a sensor unit (22, 32, 42) and a processing unit (24, 34, 44) operatively coupled to the respective sensor unit (22, 32, 42), wherein the respective sensor units (22, 32, 42) measure accelerations and angular rates of the aircraft and provide raw data based on said measurements; wherein the respective processing units (24, 34, 44) process the raw data provided by the sensor units (22, 32, 42) and provide processed data reflecting the velocity and/or attitude of the aircraft; the method comprising: at a sensor monitoring unit (50), receiving the raw data output by each of the sensor units (22, 32, 42) and evaluating according to at least one predetermined criterion whether the raw data of each sensor unit (22, 32, 42) are consistent with one another; and at an attitude monitoring unit (52), receiving the processed data output by each of the processing units (24, 34, 44) and evaluating according to at least one predetermined criterion whether the processed data of each processing unit (24, 34, 44) are consistent with one another. The invention furthermore relates to a corresponding inertial measurement assembly (10) of an aircraft with integrated integrity monitoring and an aircraft comprising such an assembly.

The invention refers to a passenger aircraft, in particular passenger aircraft capable of vertical take-off and landing, comprising: a fuselage including at least one cabin for carrying one or more human passengers and a cargo bay for holding passenger luggage with an opening located in the rear of the fuselage for accessing the cargo bay, and a door adapted to selectively close or open the opening, wherein the door is adapted to open upwardly.

The invention relates to 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.

The present disclosure 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 motor (26) and the at least one servo motor (28), respectively, based on control commands output by the computing section (18).

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 and a second position 338 the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.

A battery module (10) for a vehicle, in particular for an aircraft, comprises two end plates (12) and a cell stack (14) comprising an arrangement of several interconnected battery cells (16), in particular pouch cells, that are arranged in a row along a stacking direction (S), wherein the cell stack (14) is sandwiched between the two end plates (12) in the stacking direction (S), wherein the battery module (10) further comprises a separate tube-like enclosure (18) comprising a heat insulating material, the tube-like enclosure having a front opening (18f) and a back opening (18b) that are closed by the end plates (12), so that the tube-like enclosure (18) and the two end plates (12) form a housing (20) in which the cell stack (14) is accommodated.