Lilium

The present invention relates to a method (10) of detecting engine stall in an engine (1100) of a vertical take-off and landing aircraft (2000) under flight conditions (FC). The engine (1100) comprises a rotor (1130). In the method (10), a rotor torque (M_rotor) and a rotor speed (n_rotor) of the rotor (1130) are acquired. Based thereon, a stall ratio (SR) between the acquired rotor torque (M_rotor) and rotor speed (n_rotor) is determined. The determined stall ratio (SR) is compared with a stall boundary (SB) for the engine (1100), which is based on the acquired rotor torque (M_rotor) and rotor speed (n_rotor), for detecting occurring engine stall. The result of the comparison is outputted as a detection result (DR). The invention relates further to a computer program product, a control system (100), a propulsion system (1000) and an aircraft (2000) utilizing and implementing said method (10).

The present invention provides an aircraft with an electric propulsion system, a fuselage (10) configured to host payload and energy storage elements (20), and lift generating wings attached to the fuselage (10). The fuselage (10) comprises an aerostructure to bear and distribute loads between the fuselage (10) and the wings. The aerostructure comprises a structure of frames (30), stringers and skin panels (41, 42, 43). A plurality of frames (30) are separated in a longitudinal direction of the fuselage (10) and arranged in parallel to each other, defining holding spaces (22) in between adjacent frames (30). A plurality of stringers extending predominately in the longitudinal direction of the fuselage (10) are separated in a circumferential direction of the fuselage (10) and are attached to a number of the frames (30). A plurality of skin panels are attached to the frames (30) and stringers, wherein a first (41) and second (42) set of the skin panels are defining the outer shape of the fuselage (10), the second set of the skin panels (42) covering the holding spaces (22) to the outside of the fuselage, and a third set of the skin panels (43) is covering and separating an interior of the fuselage (10) from the holding spaces (22). The holding spaces (22) are configured to host the energy storage elements (20), which are attached at least to the frames (30) and/or stringers of the aerostructure.

This patent application introduces a wing assembly for aircraft, featuring an innovative approach to integrating a servo actuator control unit (SCU) (5) within the propulsion unit (2). The assembly includes a main section for attachment to the aircraft's fuselage and a pivotally connected flap section (1). The propulsion unit (2), integral to the flap section (1), is configured with inlet and exhaust areas (2a, 2b) to facilitate thrust production. The SCU (5) is uniquely integrated into a skin part (2c) of the propulsion unit (2), positioning it in the path of airflow generated during flight. This strategic placement enhances heat dissipation by utilizing the airflow, effectively reducing the need for additional cooling mechanisms and contributing to a lighter, less complex aircraft design. The direct exposure of the SCU (5) to airflow helps maintain it within safe operational temperature ranges, potentially increasing its reliability and service life. The configuration focuses on improving thermal management and aerodynamic efficiency, aligning with current trends in aerospace for more efficient, robust, and environmentally conscious aircraft wing assemblies.

Welding preparation device (1) for preparing at least two battery cell tabs (P1, P2) for welding comprising: a clamping mechanism (2) comprising: a support part (3); and a clamping part (4) for clamping the at least two battery cell tabs (P1, P2) at a clamping force exertion portion (41) thereof together with the support part (3) therebetween within a clamping region (CR) by a clamping force along a clamping force direction. In order to improve welding quality, the clamping mechanism (2) has an access portion (7) which, in a clamped state, allows access to the clamping region (CR) in order to provide a weld seam to the battery cell tabs (P1, P2).

The invention is related to a Method for producing a battery device (10), in particular for use in an electric aircraft, comprising the following steps:- Providing a battery housing (20) with at least one cell compartment (30) having one receiving opening (32) and surrounding compartment walls (34) for holding a battery module (40) with multiple battery cells (42),- Stacking multiple battery cells (42) on top of each other to create at least one battery module (40),- Inserting the at least one battery module (40) into the at least one cell compartment (30) through the receiving opening (32),- Closing the receiving opening (32) of the at least one cell compartment (30).

The invention is related to a Battery housing (10) for accommodating a battery device (20) with multiple battery cells (22) for an electric aircraft (100), comprising at least one inner wall (30) and at least one outer wall (40) forming together a battery volume (50) for holding the multiple battery cells (22), characterised in that the at least one outer wall (40) comprises an outside surface (42) wherein the outside surface (42) has an aerodynamical shape for completing a part of a fuselage (110) of the electric aircraft (100).

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The invention refers to an aircraft (2), particularly an aircraft (2) capable of vertical take-off and landing, comprising a load carrying structure (4), and a variable lift body (6) defining an aerofoil (55) and being moveably attached to the load carrying structure (4), wherein the variable lift body (6) is pivotable around a first axis;wherein a rotary actor is adapted to cause the variable lift body (6) to pivot in relation to the load carrying structure (4) arranged within the aerofoil (55).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …