Lilium eAircraft GmbH

An inceptor apparatus for an aircraft having a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

Disclosed is a crash handling system for an aircraft, comprising an altitude surveillance system adapted to receive altitude data from an altitude sensor and issue an altitude warning signal when a predetermined altitude condition is fulfilled, a crash detection unit, comprising an acceleration detector and issues a crash detection signal when a predetermined acceleration condition is fulfilled, a control unit operatively coupled to the altitude surveillance system and the crash detection unit to receive respective altitude warning signals and crash detection signals; and an energy storage system isolation means operatively coupled to the control unit to electrically isolate an energy storage system of the aircraft upon reception of an activation signal, wherein the control unit transitions from a disabled operation state to an enabled operation state when the altitude warning signal is received; and to issue the activation signal upon reception of the crash detection signal when in enabled state.

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

An airfoil of an aircraft with an ice protection system, the airfoil having a leading edge, the ice protection system comprising a first applying mechanism for applying an ice protection fluid along at least a portion of the leading edge of the airfoil, and an ice protection fluid recovering mechanism for recovering the ice protection fluid applied by the first applying mechanism, the ice protection fluid recovering mechanism being arranged downstream of the leading edge of the airfoil. The ice protection system further comprises a second applying mechanism for applying the ice protection fluid recovered by the ice protection fluid recovering mechanism on at least one area of the airfoil arranged downstream of the leading edge of the airfoil. An aircraft may comprise at least one airfoil provided with the ice protection system. A method may be used to protect the airfoil of an aircraft from ice accumulation.

Electrical servo system for a flight control surface comprising: a flight control surface moveable with respect to a mounting portion; an electric actuator configured to actuate the flight control surface; at least one movement-related flight control surface sensor, which is configured to acquire a quantity related to a movement of the flight control surface; at least one movement-related actuator sensor, which is configured to acquire a quantity related to a movement of the actuator. In order to enhance control accuracy, a controller is provided, which is configured to control according to a cascaded closed loop control, wherein the at least one movement-related flight control surface sensor is used in an outer closed loop control for movement control of the flight control surface, and the at least one movement-related actuator sensor is used in an inner closed loop control for movement control of the actuator.

A system for navigating an aircraft, comprising a flight planning system 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 configured to verify each trajectory of the set of trajectories, an onboard flight management system to be installed at an aircraft and having a storage unit 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 includes a replanning unit 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.

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 ).

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 ), and closing the receiving opening ( 32 ) of the at least one cell compartment ( 30 ).

A battery management system and method for performing a battery state and, optionally, health parameter observation is disclosed, 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 some embodiments, a battery health observation is further performed independently by the two lanes, wherein the first lane employs an aging 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.

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.