The present invention relates to a high-performance battery cell (10) for driving an electric aircraft, comprising a plurality of layers (12) stacked one to another to form a cell stack (100; 200; 300; 400), the cell stack (100; 200; 300; 400) comprising at least two electrode layers (102, 104; 202, 204; 302, 304; 402, 404) comprising a cathode layer and an anode layer, and coating layers (120, 122, 124; 220, 222, 224; 320, 322, 324; 420, 422, 424) applied to the electrode layers (102, 104; 202, 204; 302, 304; 402, 404), wherein at least one of the electrode layers (102, 104; 202, 204; 302, 304; 402, 404) and/or at least one of the coating layers (120, 122, 124; 220, 222, 224; 320, 322, 324; 420, 422, 424) comprises at least one degassing channel (16) connecting an inner portion of the cell stack (100; 300; 400) with an edge portion of the cell stack (100; 300; 400), and/or at least one weakened portion (202a,b, 204a,b; 302a,b, 304a,b) pre-defining at least one path of weakness connecting an inner portion of the cell stack (200:300; 400) with an edge portion of the cell stack (200; 300; 400).
H01M 50/211 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for pouch cells
2.
ELECTRICAL SERVO SYSTEM FOR A FLIGHT CONTROL SURFACE, METHOD OF DETECTING SENSOR FAILURE, AND METHOD FOR DETERMINING CORRECT FUNCTION OF A MOVEMENT RELATED FLIGHT CONTROL SURFACE SENSOR
Electrical servo system for a flight control surface comprising: a flight control surface (4) moveable with respect to a mounting portion (2); an electric actuator (8) configured to actuate the flight control surface (4); 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 (4); at least one movement related actuator sensor which is configured to acquire a quantity related to a movement of the actuator (8). 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.
An aircraft (1) comprises at least two propulsion units (4, 5) being pivotable provided on the aircraft (1), the propulsion units (4, 5) being arranged adjacent to each other along an arrangement direction and respectively comprising: a propulsion rotor (41) being rotatable about a rotation axis (42), configured to contribute in thrust generation, and configured to suck air along an airflow direction substantially perpendicular to the arrangement direction; a duct (43) configured to guide air to the propulsion rotor, the duct (43) comprises a non-circular inlet portion (44), a circular downstream portion (47) being substantially circular about the rotation axis (42) and being located downstream of the inlet portion (44) along the airflow direction, and an air guiding portion (46) guiding air from the non-circular inlet portion (44) to the circular downstream portion (47) and establishing the transition therebetween, the air guiding portion (46) having an upper (46a) and a lower air guiding portion (46b) which are spaced apart from each other and provided on respective upper and lower sides of the rotation axis (42). In order to enhance performance, the aircraft (1) further comprises at least one septum (7) which is interposed between two rotation axes (42) of two adjacent propulsion rotors (41), the at least one septum (7) extending on the upstream side along the airflow direction with respect to the circular downstream portion (47) and between the upper and lower air guiding portions (46a, 46b), the at least one septum having a guiding surface (71) having at least one tangential plane parallel to the rotation axis (42), and preferably perpendicular to the arrangement direction.
An aircraft includes at least two propulsion units being pivotable and arranged adjacent to each other along an arrangement direction. The propulsion units include a propulsion rotor and a duct for guiding air to the rotor. The duct has a non-circular inlet portion, a circular downstream portion located downstream of the inlet portion along the airflow direction, and an air guiding portion guiding air from the non-circular inlet portion to the circular downstream portion and establishing the transition therebetween. The air guiding portion has upper and lower portions. The aircraft further includes at least one septum interposed between rotation axes of two adjacent propulsion rotors. The septum extends on the upstream side along the airflow direction with respect to the circular downstream portion and between the upper and lower air guiding portions and has a guiding surface having at least one tangential plane parallel to the rotation axis.
An inceptor apparatus for an aircraft comprises 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.
A method of operating an aerial vehicle (1), the aerial vehicle (1) comprising a plurality of propulsion units (4, 5) arranged to be pivotable about at least one axis along an angular position and configured to generate a thrust force and/or a lift force, wherein the angular position and/or the thrust force of the plurality of propulsion units (4, 5) are controlled based on a translational movement related command, in particular, a force command, of the aerial vehicle (1) regarding at least one degree of freedom and a rotational movement related command, in particular, a moment command of the aerial vehicle (1) regarding at least one degree of freedom. In order to ensure flight safety, if it is determined that a combination of the translational movement related command and the rotational movement related command causes a saturation in the angular position and/or the thrust force of at least one of the plurality of propulsion units (4, 5), the translational movement related command is adjusted in at least one degree of freedom such that the rotational movement related command is met.
A device bus node associated with an aircraft device has a plurality of communication ports for connecting with a respective bus of an electronic or optoelectronic bus system of a distributed system of an aircraft. The device bus node is configured to receive bus messages from at least one controller bus node of a controller sub-system of the distributed system and perform a self-configuration procedure after that each of its communication ports was connected with a respective different one of the busses of the electronic or optoelectronic bus system, for being fully operational in the distributed system, wherein the self-configuration procedure determines, based on bus messages received at its communication ports, at least part of individual configuration data being associated to the device bus node as part of the distributed system and being needed by the device bus node to enable a processing of a respectively received bus message.
A rotor for a ducted fan engine includes rotor blades, each having a blade body with a root section to be connected to a drive shaft to receive a primary driving load to provide a primary load section and a tip section at the opposite end of the blade body, being arranged circumferentially to form the rotor; a rotationally symmetrical load bearing element being in force transferring contact with the plurality of blade bodies in a load bearing section located between the root section and the tip section, to provide a secondary load path for at least a part of reaction loads of the blade bodies, wherein the blade bodies of the rotor blades are made of a composite material, comprising a polymeric matrix and continuous reinforcing fibres embedded in the polymeric matrix, wherein the load bearing element is made of a composite material, comprising a polymeric matrix and chopped reinforcing fibres embedded in the polymeric matrix.
The invention relates to a rotor (10) for a ducted fan engine (100), comprising: - a plurality of rotor blades (20), each having a blade body (22) with a root section (24) to be connected to a drive shaft (110) to receive a primary driving load to provide a primary load section and a tip section (26) at the opposite end of the blade body (22), being arranged circumferentially to form the rotor (10), - a rotationally symmetrical load bearing element (30) being in force transferring contact with the plurality of blade bodies (22) in a load bearing section (28) located between the root section (24) and the tip section (26), to provide a secondary load path (SLP) for at least a part of reaction loads (RL) of the blade bodies (22), - wherein the blade bodies (22) of the rotor blades (20) are made of a composite material, comprising a polymeric matrix and continuous reinforcing fibres embedded in the polymeric matrix, - wherein the load bearing element (30) is made of a composite material, comprising a polymeric matrix and chopped reinforcing fibres embedded in the polymeric matrix.
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.
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
11.
METHOD OF FABRICATING A PRE-LITHIATED ELECTRODE AND LITHIUM-ION BATTERY CELL
The present invention provides a method of fabricating a pre-lithiated electrode, comprising: disposing a Li-PET sheet comprising a layer of lithium metal adjacent to a prefabricated electrode comprising a layer of anode material; contacting a surface of the layer of anode material with a surface of the layer of lithium metal; and calendering the layer of lithium metal and the prefabricated electrode together. The present invention further provides a lithium-ion battery cell comprising such pre-lithiated electrode.
A method of fabricating a pre-lithiated electrode comprises: disposing a Li-PET sheet comprising a layer of lithium metal adjacent to a prefabricated electrode comprising a layer of anode material; contacting a surface of the layer of anode material with a surface of the layer of lithium metal; and calendering the layer of lithium metal and the prefabricated electrode together. The present disclosure further provides a lithium-ion battery cell comprising such pre-lithiated electrode.
The present invention relates to a power controller with a current limiting function for pre-charging a capacitive load, wherein current limitation is implemented by means of power transfer modulation control under specific switching conditions. Specifically, by use of resonant circuit elements (resonant tank) and an accordingly adapted modulation controller, a zero-voltage switching condition (ZVS) when modulating the power transfer is achieved. This results in low power dissipation and little electromagnetic interference. Therefore, a capacitive load can be charged faster and with less power dissipation than in conventional approaches.
H02H 9/00 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
H02H 9/02 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess current
H02H 3/02 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details
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.
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B64D 45/08 - Landing aidsSafety measures to prevent collision with earth's surface optical
15.
Systems and Methods for Monitoring Energy System Performance of a Vehicle
Various embodiments of the teachings herein include methods for operating a vehicle. The methods may include: accessing a travel plan identifying an intended destination and a predicted state of the energy store including a predicted value for a parameter of the energy store upon arrival; determining an instantaneous location; determining a predicted value for the first operating parameter based on the location and the travel plan; measuring an instantaneous value for the parameter; calculating a first deviation between the predicted value and the instantaneous value; calculating an expected final value for the parameter upon reaching the intended destination based on the instantaneous value; calculating a second deviation between the predicted final value and the expected final value; indicating to an operator both of the deviations; and executing one or more changes to controls of the drive system in response to at least one of the two deviations.
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
G07C 5/02 - Registering or indicating driving, working, idle, or waiting time only
16.
METHOD FOR CONTROLLING A TRANSITION OF A VERTICAL TAKE-OFF AND LANDING AIRCRAFT FROM HOVER FLIGHT TO CRUISE FLIGHT AND VICE VERSA
During the transition of a vertical take-off and landing aircraft from hover flight to cruise flight and vice versa, a method for controlling this transition is configured to push propulsion units of the VTOL aircraft through an unstable flow condition zone within a predetermined time period. Each propulsion unit is mounted to a mounting portion of the aircraft in a movable manner about at least one degree of freedom and comprises a flap serving as a lifting and control surface and at least one engine connected with the flap, and each propulsion unit receives command signals for flap angle and engine speed or speeds so that each propulsion unit generates a thrust force and/or a lift force.
A system for determining a position of an autonomous or automated aircraft during its approach to a landing site comprises: a ground-based visual landing aid having a radiating surface, which radiates light in the form of light cones arranged discretely in a two-dimensional grid, wherein a navigation light is formed by a plurality of adjacent light cones, the light cones forming the navigation light change depending on a deviation of the aircraft from a target landing path; and an aircraft-based digital receiver, which, during the landing, continuously detects the positions of the light cones forming the navigation light along the radiating surface and determines, on the basis of the detected positions, a state of the aircraft, wherein the system is configured to generate commands for autonomously landing the aircraft or for assisting a pilot in landing the aircraft on the landing site based on the determined state of the aircraft.
An electrical power distribution network of an electric power system of an aircraft is operated in at least one normal operation mode such that it provides for load sharing across electrical power sources (A, B, C, D) with respect to electrical loads (AA, BB, CC, DD), wherein the electrical power distribution network, in case of an electrical fault, is operated in at least one electrical failure mitigating operation mode, which provides for electric fault isolation, such that a network portion of the electrical power distribution network including the electrical fault is isolated from at least one other network portion of the of the electrical power distribution network.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
20.
BATTERY ASSEMBLY, IN PARTICULAR FOR USE IN AN ELECTRICAL PROPULSION VTOL AIRCRAFT, AND ELECTRICAL PROPULSION VTOL AIRCRAFT COMPRISING SUCH A BATTERY ASSEMBLY
Disclosed is a battery assembly, comprising a battery box, comprising a housing including a base plate and a cover; at least one battery cell stack mounted inside the housing, wherein each battery cell stack comprises a plurality of battery cells stacked on top of the base plate along a stacking direction and electrically connected in series or in parallel; electrical connectors disposed on the outer side of the housing; and an interface unit for coupling with an electronics unit; and an electronics unit, comprising electronic control components; and an interface unit for coupling with the battery box; wherein in use the battery box and the electronics unit are interfaced by their such respective interface units such that operation of the at least one battery cell stack is controlled by the electronic control components of the electronics unit. Furthermore, the invention relates to an electrical propulsion VTOL aircraft comprising such a battery assembly.
H01M 50/209 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for prismatic or rectangular cells
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
H01M 50/507 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing comprising an arrangement of two or more busbars within a container structure, e.g. busbar modules
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 50/242 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions adapted for protecting batteries against vibrations, collision impact or swelling
The present disclosure relates to systems and methods for simplified, more efficient and more reliable aircraft control. In particular, the present disclosure relates to more efficient use of display capabilities, in particular, of interactive displays in monitoring, control, and operation of aircraft systems. According to a particular aspect, a common operation of groups of circuit breakers in an aircraft electrical system, preferably by means of an interactive display, is provided. The interactive display may be hierarchically organized into plural levels of display windows showing different levels of detail. In accordance with another particular aspect, a general synoptics summary display showing a status overview of all aircraft systems on a single display window is provided.
H02H 3/04 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection Details with warning or supervision in addition to disconnection, e.g. for indicating that protective apparatus has functioned
B64D 43/00 - Arrangements or adaptations of instruments
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
Disclosed is an electrically driven ducted fan engine, comprising a housing with an inner housing wall, defining a substantially cylindrical inner space and a longitudinal axis, an inlet opening, a rotor with a multitude of rotor blades positioned in the inner space of the housing downstream of the inlet opening, a stator assembly with a multitude of guide vanes extending from a radially central region of the inner space to the inner wall of the housing, and an exhaust opening provided in the housing downstream of the stator assembly, an interstage region defined between the rotor and the stator assembly, a guide vane region defined in which guide vanes extend to the inner wall of the housing and an exhaust section, wherein in at least one of the interstage region, the guide vane region and the exhaust region, acoustic liners are provided to the housing.
The present invention relates to an electrically driven ducted fan engine (10), comprising a housing (12) with an inner housing wall (12a), defining a substantially cylindrical inner space (14) and a longitudinal axis (L), an inlet opening (16) provided in the housing (12), a rotor (20) with a multitude of rotor blades (20a), which is arranged to be driven in rotation by means of an electrical motor (22) and positioned in the inner space (14) of the housing (12) downstream of the inlet opening (16) with respect to the longitudinal axis (L) of the engine (10), a stator assembly (24) with a multitude of guide vanes (24a) extending from a radially central region of the inner space (14) to the inner wall (12a) of the housing (12), which is fixedly arranged in the inner space (14) of the housing (12) downstream of the rotor (20) with respect to the longitudinal axis (L) of the engine (10), and an exhaust opening (26) provided in the housing (12) downstream of the stator assembly (24) with respect to the longitudinal axis (L) of the engine (10), wherein with respect to the longitudinal axis (L) of the engine (10), an interstage region (30) is defined between the rotor (20) and the stator assembly (24), a guide vane region (32) is defined in the longitudinal section in which the guide vanes (24a) extend to the inner wall (12a) of the housing (12) and an exhaust section (34) is defined between the stator assembly (24) and the exhaust opening (26), wherein in at least one of the interstage region (30), the guide vane region (32) and the exhaust region (34), acoustic liners are provided to the housing (12).
The present invention relates to an electrode assembly (100), comprising in a stacked manner a first anode layer (112), an anode current collector layer (114), a second anode layer (116), a separator layer (118), a first cathode layer (120), a cathode current collector layer (122), and a second cathode layer (124). In the electrode assembly (100) according to the present invention, the anode current collector layer (114) and/or the cathode current collector layer (122) comprises at least two conductive layers (122a, 122c) wherein between neighbouring pairs of conductive layers (122a, 122c), a respective heat spreading layer (122b) is interposed.
H01M 50/124 - Primary casingsJackets or wrappings characterised by the material having a layered structure
H01M 4/505 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides of manganese of mixed oxides or hydroxides containing manganese for inserting or intercalating light metals, e.g. LiMn2O4 or LiMn2OxFy
H01M 4/525 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides of nickel, cobalt or iron of mixed oxides or hydroxides containing iron, cobalt or nickel for inserting or intercalating light metals, e.g. LiNiO2, LiCoO2 or LiCoOxFy
Disclosed herein is an electrode assembly, comprising in a stacked manner a first anode layer, an anode current collector layer, a second anode layer, a separator layer, a first cathode layer, a cathode current collector layer, and a second cathode layer. In the electrode assembly, the anode current collector layer and/or the cathode current collector layer comprises at least two conductive layers wherein between neighbouring pairs of conductive layers, a respective heat spreading layer is interposed.
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
B60L 58/26 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries by cooling
26.
AIRFOIL OF AN AIRCRAFT, AIRCRAFT WITH AN ICE PROTECTION SYSTEM AND METHOD OF ICE PROTECTING THE AIRFOIL
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.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
The present invention is directed to a laminated film (10) for packaging of pouch- type battery cells (26), the laminated film (10) comprising a plurality of layers including: a first polymer layer (12), a second polymer layer (16), a metal barrier layer (18) disposed between the first polymer layer (12) and the second polymer layer (16), characterized in that the layers further include a heat spreading layer (20) made of a thermally conductive material, wherein the heat spreading layer (20) is integrated within the laminated film (10) such as to be disposed between the first polymer layer (12) and the second polymer layer (16).
H01M 50/129 - Primary casingsJackets or wrappings characterised by the material having a layered structure comprising three or more layers with two or more layers of only organic material
H01M 50/131 - Primary casingsJackets or wrappings characterised by physical properties, e.g. gas permeability, size or heat resistance
The present invention is directed to a laminated film for packaging of pouch-type battery cells, the laminated film comprising a plurality of layers including: a first polymer layer, a second polymer layer, a metal barrier layer disposed between the first polymer layer and the second polymer layer, characterized in that the layers further include a heat spreading layer made of a thermally conductive material, wherein the heat spreading layer is integrated within the laminated film such as to be disposed between the first polymer layer and the second polymer layer.
H01M 50/46 - Separators, membranes or diaphragms characterised by their combination with electrodes
H01M 50/129 - Primary casingsJackets or wrappings characterised by the material having a layered structure comprising three or more layers with two or more layers of only organic material
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
29.
BATTERY CELL COMPRISING DEGASSING CHANNELS AND/OR PATHS OF WEAKNESS
The present invention relates to a high-performance battery cell (10) for driving an electric aircraft, comprising a plurality of layers (12) stacked one to another to form a cell stack (100; 200; 300; 400), the cell stack (100; 200; 300; 400) comprising at least two electrode layers (102, 104; 202, 204; 302, 304; 402, 404) comprising a cathode layer and an anode layer, and coating layers (120, 122, 124; 220, 222, 224; 320, 322, 324; 420, 422, 424) applied to the electrode layers (102, 104; 202, 204; 302, 304; 402, 404), wherein at least one of the electrode layers (102, 104; 202, 204; 302, 304; 402, 404) and/or at least one of the coating layers (120, 122, 124; 220, 222, 224; 320, 322, 324; 420, 422, 424) comprises at least one degassing channel (16) connecting an inner portion of the cell stack (100; 300; 400) with an edge portion of the cell stack (100; 300; 400), and/or at least one weakened portion (202a,b, 204a,b; 302a,b, 304a,b) pre-defining at least one path of weakness connecting an inner portion of the cell stack (200; 300; 400) with an edge portion of the cell stack (200; 300; 400).
H01M 4/133 - Electrodes based on carbonaceous material, e.g. graphite-intercalation compounds or CFx
H01M 4/134 - Electrodes based on metals, Si or alloys
H01M 4/1393 - Processes of manufacture of electrodes based on carbonaceous material, e.g. graphite-intercalation compounds or CFx
H01M 4/1395 - Processes of manufacture of electrodes based on metals, Si or alloys
H01M 4/38 - Selection of substances as active materials, active masses, active liquids of elements or alloys
H01M 4/58 - Selection of substances as active materials, active masses, active liquids of inorganic compounds other than oxides or hydroxides, e.g. sulfides, selenides, tellurides, halogenides or LiCoFySelection of substances as active materials, active masses, active liquids of polyanionic structures, e.g. phosphates, silicates or borates
H01M 4/48 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides
Electric engine (10), in particular electric aircraft engine, comprising a ring-shaped stator core (12) and a rotor rotatably supported within the stator core (12), wherein the stator core (12) has a plurality of radially inward-facing teeth (14) and a plurality of windings (16) wound around each of the teeth (14) to form individual coils (18), wherein the windings (16) of each coil (18) have active portions (22) between adjacent teeth (14) and end winding portions (20) arranged at axial ends of each teeth (14), and wherein at least one thermally conductive heat extraction component (26) is provided at the end winding portions (20).
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 5/18 - Casings or enclosures characterised by the shape, form or construction thereof with ribs or fins for improving heat transfer
31.
MULTI-STAGED AXIAL COMPRESSOR PROPULSION MOTOR FOR AN ELECTRIC PROPULSION AIRCRAFT
The present invention relates to a multi-staged axial compressor propulsion motor (10) for an electrical propulsion aircraft, comprising a housing (16), defining a substantially cylindrical inner space (16a) and a longitudinal axis (L); at least two compressor stages (12, 14) arranged in the inner space (16a) of the housing (16) in a rotatable manner one behind the other along the longitudinal axis (L), wherein each compressor stage (12, 14) comprises an inner blade ring (12b, 14b) and an outer blade ring (12c, 14c) with a plurality of blades (12a, 14a) extending between the inner (12b, 14b) and outer (12c, 14c) blade rings; and an electrical drive assembly (24) adapted to drive at least two of the compressor stages (12, 14) in a counter-rotating manner.
F04D 25/06 - Units comprising pumps and their driving means the pump being electrically driven
H02K 16/02 - Machines with one stator and two rotors
H02K 21/12 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets
H02K 1/32 - Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 9/06 - Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
32.
DUCTED FAN ENGINE, ARRAY OF DUCTED FAN ENGINES, AND AIRCRAFT
In a Ducted fan engine (1), configured for providing thrust for an aircraft (too), in particular an aircraft (100) having vertical takeoff and landing capability, comprising a fan stator (3) having one or more substantially radially extending vanes (31); a shroud (11) circumferentially surrounding the fan stator (3); a fan rotor (5) rotatably supported by the fan stator (3); at least one electromotor (2) configured for driving the fan rotor (5), wherein in particular the electromotor is arranged within the fan stator (3); it is provided that at least one heat pipe (4) configured for dissipating heat from the electromotor (2) is arranged in at least one vane (31).
The present invention relates to shrouded fan engine having an acoustic liner (10) for damping sound waves, comprising a base portion (14) on one side of the acoustic liner (10), wherein the base portion (14) is adapted to attach the acoustic liner (10) to an engine structure (18) of the engine, an impingement face (12) on another side of the acoustic liner (10), wherein the impingement face (12) is formed from a substantially liquid-tight material, at least one first channel (24) extending from the impingement face (12) in a direction towards the base portion (14), wherein a wall of the first channel (24) is formed from a substantially liquid-tight material, a damping portion (20) arranged between the impingement face (12) and the base portion (14), wherein the damping portion (20) is formed from an acoustic damping material, and at least one second channel (32) which connects the first channel (24) and the damping portion (20).
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
34.
Time variable electrical load sharing in a power distribution network of an aircraft
An electrical power distribution network of an electric power system of an aircraft is operated such that it sequentially adopts a plurality of different partial load sharing modes in a time variable manner, which provide for partial load sharing across electrical power sources (A, B, C, D) with respect to associated electrical loads (AA, BB, CC, DD), by sequentially switching between a plurality of different partial load sharing configurations of the electrical power distribution network, each partial load sharing configuration being associated to a particular one of the partial load sharing modes.
An electrical power distribution network (306) of an electric power system (300) of an aircraft is operated in at least one normal operation mode such that it provides for load sharing across electrical power sources (A, B, C, D) with respect to electrical loads (AA, BB, CC, DD), wherein the electrical power distribution network (306), in case of an electrical fault, is operated in at least one electrical failure mitigating operation mode, which provides for electric fault isolation, such that a network portion of the electrical power distribution network (306) including the electrical fault is isolated from at least one other network portion of the of the electrical power distribution network.
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 13/50 - Transmitting means with power amplification using electrical energy
An electrical power distribution network of an electric power system of an aircraft is operated in at least one normal operation mode such that it provides for load sharing across electrical power sources (A, B, C, D) with respect to electrical loads (AA, BB, CC, DD), wherein the electrical power distribution network, in case of an electrical fault, is operated in at least one electrical failure mitigating operation mode, which provides for electric fault isolation, such that a network portion of the electrical power distribution network including the electrical fault is isolated from at least one other network portion of the of the electrical power distribution network.
An electrical power distribution network (306) of an electric power system (300) of an aircraft is operated such that it sequentially adopts a plurality of different partial load sharing modes in a time variable manner, which provide for partial load sharing across electrical power sources (A, B, C, D) with respect to associated electrical loads (AA, BB, CC, DD), by sequentially switching between a plurality of different partial load sharing configurations of the electrical power distribution network, each partial load sharing configuration being associated to a particular one of the partial load sharing modes.
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
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.
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.
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.
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
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.
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
The present disclosure relates to a battery management system for an electric air vehicle such as an eVTOL aircraft for observing a battery system state and 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, is carried out during a flight. In particular, the observation and prediction is performed by two independent and dissimilar lanes of the battery management system. A first lane predicts the battery state according to a pre-defined flight profile representing a worst-case scenario. A second lane predicts the battery state according to a planned flight profile so as to determine a range of the flight. Hence, it can be confirmed during the flight that the intended destination can be safely reached with the remaining accessible energy.
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
B60L 58/16 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to battery ageing, e.g. to the number of charging cycles or the state of health [SoH]
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 43/00 - Arrangements or adaptations of instruments
G01R 31/3842 - Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
G01R 31/392 - Determining battery ageing or deterioration, e.g. state of health
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
43.
METHOD AND ASSEMBLY FOR MONITORING THE INTEGRITY OF FREE INERTIAL POSITION AND VELOCITY MEASUREMENTS OF AN AIRCRAFT
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.
G01S 19/47 - Determining position by combining measurements of signals from the satellite radio beacon positioning system with a supplementary measurement the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial
G01P 21/00 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass
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.
G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
45.
AIRCRAFT ENGINE COMPRISING A VARIABLE AREA EXHAUST NOZZLE
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.
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.
The present invention provides an engine of a vertical take-off and landing aircraft, wherein the engine is configured to be movable with respect to an aircraft component of the aircraft between a hover position for take-off and landing, and a cruise position for forward flight, wherein the engine comprises an aerodynamic component having at least one aerodynamic element movable between a first position and a second position the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 13/32 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cam mechanisms
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
48.
AIRCRAFT HAVING A DUCTED FAN ENGINE OR AN ARRAY THEREOF
Embodiments of the disclosure are directed to a ducted fan engine configured for providing thrust for an aircraft, in particular an aircraft having vertical take-off and landing capability. The ducted fan engine includes a shroud, a stator, and a rotor rotatably supported by the shroud. The shroud has a substantially circular cross-section. The stator has at least one substantially radially-extending stator vane. The rotor comprises at least 19 rotor blades, in particular at least 25 rotor blades.
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; 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.
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 disclosure is defined by the accompanying claims and is not limited to the particulars of the embodiments of the above detailed description.
H02H 7/22 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systemsEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for switching devices
B64D 41/00 - Power installations for auxiliary purposes
An engine for an aircraft is presented comprising a rotor, an electric motor actuating the rotation of the rotor and an ECU controlling the electric motor, wherein the rotation of the rotor provides a main flow of air causing the thrust of the engine and wherein the ECU is located within the volume defined by the main flow.
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.
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
G01R 31/3842 - Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
G01R 31/392 - Determining battery ageing or deterioration, e.g. state of health
G01R 31/396 - Acquisition or processing of data for testing or for monitoring individual cells or groups of cells within a battery
G01R 31/389 - Measuring internal impedance, internal conductance or related variables
B60L 58/12 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
B60L 58/16 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to battery ageing, e.g. to the number of charging cycles or the state of health [SoH]
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.
H01M 10/0525 - Rocking-chair batteries, i.e. batteries with lithium insertion or intercalation in both electrodesLithium-ion batteries
H01M 10/0569 - Liquid materials characterised by the solvents
H01M 4/62 - Selection of inactive substances as ingredients for active masses, e.g. binders, fillers
H01M 4/525 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides of nickel, cobalt or iron of mixed oxides or hydroxides containing iron, cobalt or nickel for inserting or intercalating light metals, e.g. LiNiO2, LiCoO2 or LiCoOxFy
H01M 4/505 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides of manganese of mixed oxides or hydroxides containing manganese for inserting or intercalating light metals, e.g. LiMn2O4 or LiMn2OxFy
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.
The present invention relates to an aircraft, comprising a fuselage, at least one pair of wings and a battery system for providing power to electrical systems of the aircraft, wherein the battery system comprises at least one battery pack, each battery pack comprises a number of individual battery modules, which are directly or indirectly coupled to one another, and the at least one battery pack is disposed between an inner structural wall defining an interior space of the fuselage and an outer fairing wall of the fuselage. The fuselage is provided with a rack mounting mechanism comprising a number of mounting brackets, each for exchangeably mounting one of the battery modules to the aircraft, and each of the battery packs is a virtual battery pack, which is obtained by electrically connecting a predetermined number of the battery modules.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B60L 50/64 - Constructional details of batteries specially adapted for electric vehicles
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.
H01M 4/131 - Electrodes based on mixed oxides or hydroxides, or on mixtures of oxides or hydroxides, e.g. LiCoOx
H01M 4/1391 - Processes of manufacture of electrodes based on mixed oxides or hydroxides, or on mixtures of oxides or hydroxides, e.g. LiCoOx
H01M 4/36 - Selection of substances as active materials, active masses, active liquids
H01M 4/505 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides of manganese of mixed oxides or hydroxides containing manganese for inserting or intercalating light metals, e.g. LiMn2O4 or LiMn2OxFy
H01M 4/525 - Selection of substances as active materials, active masses, active liquids of inorganic oxides or hydroxides of nickel, cobalt or iron of mixed oxides or hydroxides containing iron, cobalt or nickel for inserting or intercalating light metals, e.g. LiNiO2, LiCoO2 or LiCoOxFy
H01M 4/62 - Selection of inactive substances as ingredients for active masses, e.g. binders, fillers
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 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, is carried out during a flight. In particular, the observation and prediction is performed by two independent and dissimilar lanes of the battery management system. A first lane predicts the battery state according to a pre-defined flight profile representing a worst case scenario. A second lane predicts the battery state according to a planned flight profile so as to determine a range of the flight. 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 to immediately deviate to the closest alternate airfield for landing. Thus, full redundancy of prediction, excluding a single point of failure leading to a catastrophic event, is achieved.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
G01R 31/382 - Arrangements for monitoring battery or accumulator variables, e.g. SoC
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
The invention refers to an aircraft (1, 3), particularly an aircraft (1, 3) capable of vertical take-off and landing, comprising a fuselage (3, 4), and a variable lift body (5, 7) defining an aerofoil (51, 53) and being moveably attached to the fuselage (3, 4), wherein the variable lift body (5, 7) is pivotable around a first axis extending in the wing (4) span direction. wherein a rotary actor (11) adapted to cause the variable lift body (5, 7) to pivot in relation to the fuselage (3, 4) arranged within the aerofoil.
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.
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.
H02H 3/08 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to excess current
H02H 9/00 - Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
H03K 17/08 - Modifications for protecting switching circuit against overcurrent or overvoltage
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.
H01M 50/211 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for pouch cells
H01M 50/229 - Composite material consisting of a mixture of organic and inorganic materials
H01M 50/231 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by the material of the casings or racks having a layered structure
H01M 50/233 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by physical properties of casings or racks, e.g. dimensions
H01M 50/30 - Arrangements for facilitating escape of gases
62.
BATTERY MANAGEMENT SYSTEM FOR AN ELECTRIC AIR VEHICLE
The present invention relates to a battery management system and method for performing a battery health parameter observation, in particular cell impedance observation, with two redundant, independent and dissimilar lanes. Specifically, a cell impedance observation in a first one of the lanes is based on Electrochemical Impedance Spectroscopy, EIS. The other lane employs a different algorithm than EIS. In embodiments, a battery state observation is further performed independently by the two lanes, wherein again the first lane employs EIS 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.
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
G01R 31/389 - Measuring internal impedance, internal conductance or related variables
G01R 31/392 - Determining battery ageing or deterioration, e.g. state of health
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
63.
BATTERY MANAGEMENT SYSTEM AND METHOD FOR AN ELECTRIC AIR VEHICLE
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.
G01R 31/36 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
G01R 31/3828 - Arrangements for monitoring battery or accumulator variables, e.g. SoC using current integration
G01R 31/3842 - Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
G01R 31/392 - Determining battery ageing or deterioration, e.g. state of health
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
An engine for an aircraft is presented comprising a rotor, an electric motor actuating the rotation of the rotor and an ECU controlling the electric motor, wherein the rotation of the rotor provides a main flow of air causing the thrust of the engine and wherein the ECU is located within the volume defined by the main flow.
A battery management system and method for performing a battery health parameter observation, in particular, cell impedance observation, with two redundant, independent and dissimilar lanes. Specifically, a cell impedance observation in a first one of the lanes is based on Electrochemical Impedance Spectroscopy, EIS. The other lane employs a different algorithm than EIS. In embodiments, a battery state observation is further performed independently by the two lanes, wherein again the first lane employs EIS 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.
G01R 31/392 - Determining battery ageing or deterioration, e.g. state of health
G01R 31/389 - Measuring internal impedance, internal conductance or related variables
G01R 31/396 - Acquisition or processing of data for testing or for monitoring individual cells or groups of cells within a battery
G01R 31/3842 - Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
G01R 31/367 - Software therefor, e.g. for battery testing using modelling or look-up tables
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B60L 58/12 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
B60L 58/16 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to battery ageing, e.g. to the number of charging cycles or the state of health [SoH]
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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.
A vapor cycle refrigeration system for an aircraft comprises a compressor, a condenser unit with a condenser radiator, a condenser fan and a condenser air duct configured to direct a stream of air generated by the condenser fan through the condenser radiator, an expansion device, an evaporator unit with an evaporator radiator, an evaporator fan and an evaporator air duct configured to direct a stream of air generated by the evaporator fan through the evaporator radiator, and a piping system connecting the compressor, the condenser radiator, the expansion device and the evaporator radiator in a closed circuit for a refrigerant, wherein each of the compressor, the condenser radiator, the condenser fan, the expansion device, the evaporator radiator, the evaporator fan and the piping system is fully supported directly or indirectly by at least one of the condenser air duct and the evaporator air duct such that the system is self-supporting.
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
68.
FAULT TOLERANT AIRCRAFT FLIGHT CONTROL SYSTEM AND AIRCRAFT PREFERABLY HAVING SUCH AN AIRCRAFT FLIGHT CONTROL SYSTEM
A flight control system for an aircraft comprises a flight control computer system connected via a bus system with a plurality of bus nodes, which each are configured to at least one of controlling an associated aircraft device based on command messages received from the flight control computer system via the bus system and sending information messages to the flight control computer system via the bus system. The bus system is a redundant bus system comprising plural independent bus sub-systems, wherein each bus node is configured to communicate with the flight control computer system via two different bus sub-systems, wherein each bus node further is configured to communicate with the flight control computer system on basis of an associated predetermined bus communication protocol via a first bus sub-system and on basis of an associated predetermined bus communication protocol via a second bus sub-system.
A battery module for a vehicle, in particular for an aircraft, comprises a housing, a cell stack accommodated in the housing, an internal channel system for heat transfer fluid disposed in the housing, a fluid inlet connector and a fluid outlet connector connected to the internal channel system and adapted to being connected to an external thermal management system, wherein the fluid inlet connector and the fluid outlet connector are self-sealing connectors molded into the housing, preferably self-sealing and dripless connectors.
H01M 10/647 - Prismatic or flat cells, e.g. pouch cells
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 10/6556 - Solid parts with flow channel passages or pipes for heat exchange
H01M 50/211 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for pouch cells
H01M 50/249 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders specially adapted for aircraft or vehicles, e.g. cars or trains
The present invention 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).
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
H02M 3/156 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators
H02M 1/44 - Circuits or arrangements for compensating for electromagnetic interference in converters or inverters
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.
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.
Embodiments of the disclosure are directed to an aircraft, particularly an aircraft for vertical take-off and landing. The aircraft includes a fuselage, and a variable lift body defining an aerofoil. The variable lift body is moveably attached to the fuselage. The variable lift body is pivotable around a first axis extending in the wing span direction. The rotary actor is adapted to cause the variable lift body to pivot in relation to the fuselage arranged within the aerofoil. (FIG. 1a)
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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.
The present invention relates to an aircraft (10), comprising a fuselage (12), at least one pair of wings (14) and a battery assembly for providing power to electrical systems of the aircraft (10), wherein the battery assembly comprises a number of individual battery modules (18) which are directly or indirectly coupled to one another, the fuselage (12) is provided with a mounting assembly (16) with a number of mounting positions (16a, 16b, 16c) for each holding one of the battery modules (18), and the number of mounting positions (16a, 16b, 16c) is larger than the number of battery modules (18) such that in a mounted state of all battery modules (18), at least one of the mounting positions (16a, 16b, 16c) remains vacant (20) thus defining a placement configuration of the battery modules (18) and the vacant mounting positions (20), and/or the mounting assembly is provided with at least one displacement assembly which allows to displace at least one of the battery modules with respect to the fuselage.
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.
The present invention 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).
A flight control system (10) for an aircraft comprises a flight control computer system (12), which is connected via an electronic or optoelectronic bus system (22) with a plurality of bus nodes (14, 16, 18, 20), which each are configured to at least one of controlling an associated aircraft device based on command messages received from the flight control computer system via the bus system and sending information messages to the flight control computer system via the bus system. According to one aspect of the invention, the electronic or optoelectronic bus system is a redundant electronic or optoelectronic bus system (22) comprising plural independent bus sub-systems (22a, 22b), wherein each bus node is configured to communicate with the flight control computer system (12) via two different bus sub-systems (22a, 22b) of the plural independent bus sub-systems, wherein each bus node further is configured to communicate with the flight control computer system on basis of an associated predetermined bus communication protocol via a first bus sub-system (22a) of the respective two different bus sub-systems, and on basis of an associated predetermined bus communication protocol via a second bus sub-system (22b) of the respective two different bus sub-systems.
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.
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
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.
The present invention relates to an aircraft (10), comprising a fuselage (12), wings (14, 16), and a battery system comprising at least one battery pack (24) which is disposed between an inner structural wall (20) defining an interior space (18) of the fuselage (12) and an outer fairing wall (22) of the fuselage. It also relates to an aircraft (10), comprising a fuselage (12), wings (14, 16) and a battery system comprising at least one battery pack (24), each having a number of individual battery modules (26), the fuselage (12) comprising a rack mounting mechanism (40) for the battery modules (26). It also relates to an aircraft (10), comprising a fuselage (12), wings (14, 16), and a battery system comprising at least one battery pack (24) with a number of individual battery modules (26), each battery pack (24) being a virtual battery pack (24), which is obtained by electrically connecting a predetermined number of the battery modules (26).
An inceptor apparatus (30a; 30b) for an aircraft comprises a primary inceptor member (32a; 32b) 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 (50a; 50b) provided at an upper portion of the primary inceptor member (32a; 32b) and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
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