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1. 发明公开

EP4345959A1 METHOD OF PRODUCING AN ENCAPSULATED BATTERY CELL 审中-实审
公开(公告)号：EP4345959A1
公开(公告)日：2024-04-03
申请号：EP22198753.0
申请日：2022-09-29
申请人： Volocopter GmbH
发明人： Gutierrez, Pablo
IPC分类号： H01M10/04 , H01M10/613 , H01M10/653 , H01M50/202 , H01M50/229 , H01M50/236 , H01M50/24 , H01M50/249 , H01M50/293 , H01M50/383 , B29B15/12 , B29C48/05 , D04C1/02
摘要： We describe a method of producing an encapsulated battery cell (1), comprising: a) braiding a battery cell (1') with a fibre roving (8ba) to create a braid around the battery cell (1'); b) impregnating the braid with a resin material (8ad); and c) curing the resin material (8ad).

2. 发明公开

EP4318166A1 METHOD OF CONTROLLING A TRANSITION AIRCRAFT AND TRANSITION AIRCRAFT 审中-实审
公开(公告)号：EP4318166A1
公开(公告)日：2024-02-07
申请号：EP22189087.4
申请日：2022-08-05
申请人： Volocopter GmbH
发明人： Yüksel, Burak , Ramesh, Ashwath , Duarte, Lucas
IPC分类号： G05D1/08
摘要： We propose a method of controlling a transition aircraft (1), in particular an electrically powered vertical take-off and landing aircraft, eVTOL, which aircraft (1) comprises a plurality of actuators (2, 3, 4a-c) and which aircraft (1) is able to transition between a first regime for take-off and landing and a second regime for horizontal flight, which method comprises controlling a first subset of actuators from said plurality of actuators (2, 3, 4a-c) in said first regime and a second subset of actuators from said plurality of actuators (2, 3, 4a-c) in said second regime, which method uses a state machine (5a) that is implemented by means of at least one flight control computer (5), which method comprises at least the following steps:
a) providing, to said flight control computer (5), measurements or estimates of a number of flight parameters, which flight parameters preferably comprise a current airspeed (v a ) and of a current attitude (q) of the aircraft (1);
b) depending on a current regime from said first and second regimes, checking by means of said state machine (5a) whether a respective predefined set of conditions (C1-C8) in connection with said current regime are fulfilled, which conditions (C1-C8) are based on a comparison of said flight parameters, preferably of measurements or estimates of a current airspeed (v a ) and of a current attitude (q) of the aircraft (1), respectively, with a respective predefined threshold value;
c) in case all the conditions (C1-C8) in said predefined set of conditions are fulfilled, signalling a corresponding state of the aircraft (1) to a high-level decision maker (5b) and waiting for confirmation regarding a transition from said regime to the other one of said first and second regimes from said high-level decision maker (5b);
d) instructing said flight control computer (5) to make said transition from said current regime to said other one of said first and second regimes if said high-level decision maker (5b) has approved the transition;
e) after making the transition in step d), commanding the aircraft (1) according to said other one of said first and second regimes in accordance with a regime-dependent control law implemented on said flight control computer (5);
f) returning to step a);
wherein step e) comprises gradually blending in a control law for said other one of said first and second regimes over time (t) while blending out a control law for said current regime over time (t).

3. 发明公开

EP4270363A1 VERFAHREN UND SYSTEM ZUM BETREIBEN EINES FLUGGERÄTS 审中-实审转让
公开(公告)号：EP4270363A1
公开(公告)日：2023-11-01
申请号：EP23170272.1
申请日：2023-04-27
申请人： Volocopter GmbH
发明人： ORTLIEB, Markus
IPC分类号： G08G5/00
摘要： Vorgeschlagen wird ein Verfahren zum Betreiben eines Fluggeräts (1), bei dem für eine vorausbestimmte Trajektorie (NT) des Fluggeräts (1) ein die Trajektorie (NT) einhüllendes Volumen bestimmt wird, welches Volumen ein erstes, inneres Volumen und ein zweites, äußeres Volumen umfasst, wobei das zweite Volumen das erste Volumen umgibt, wobei das erste Volumen sich aus einer Mehrzahl erster Einzelvolumina ( TVi ) und das zweite Volumen sich aus einer Anzahl von zweiten Einzelvolumina zusammensetzt, welche Einzelvolumina ( TVi ) an jedem Punkt der Trajektorie (NT) auf Grundlage von Parametern ( v i ) eines tatsächlichen Flugzustands des Fluggeräts (1) zu einem jeweiligen Zeitpunkt berechnet werden.

4. 发明公开

EP4082895A1 AIRCRAFT WITH FOLDING MECHANISM 审中-实审转让
公开(公告)号：EP4082895A1
公开(公告)日：2022-11-02
申请号：EP21170990.2
申请日：2021-04-28
申请人： Volocopter GmbH
发明人： Infante Aguirre, Francisco Javier , Harms, Michael
IPC分类号： B64C3/56 , B64C27/08 , B64C27/52 , B64C29/00
摘要： We propose an aircraft (1) with folding mechanism, the aircraft (1) comprising:
a fuselage (2);
optionally a payload (2') and/or a landing gear (2") attached to said fuselage (2), preferably below said fuselage (2);
at least two longitudinal beams (7.1, 7.2) attached to said fuselage (2), preferably above and/or sideways of said fuselage (2), that preferably extend parallel to each other and parallel to a first axis (x) of the aircraft (1), with a plurality of lifting units (3) attached to each of said longitudinal beams (7.1, 7.2);
at least one crossbeam (8) attached to said fuselage (2), preferably above said fuselage (2), and preferably extending parallel to a second axis (y) of the aircraft (1) and at right angles with respect to said longitudinal beams (7.1, 7.2),
with a plurality of lifting units (3) attached to said crossbeam (8);
wherein said longitudinal beams (7.1, 7.2) are rotatably attached to said fuselage (2) by means of at least one respective first pivot joint devised for pivoting said longitudinal beams (7.1, 7.2) around a respective first pivot axis to a pivoted position (7.1', 7.2'); and
wherein said crossbeam (8) is rotatably attached to said fuselage (2), preferably by means of at least one second pivot joint, for pivoting said crossbeam (8) around a second pivot axis to a pivoted position (8').

5. 发明公开

EP3912908A1 MULTI-ROTOR AIRCRAFT AND METHOD OF CONTROLLING SAME 审中-实审转让
公开(公告)号：EP3912908A1
公开(公告)日：2021-11-24
申请号：EP20175379.5
申请日：2020-05-19
申请人： Volocopter GmbH
发明人： Mores, Sebastian , Rajput, Krishna
IPC分类号： B64C27/08 , B64C27/20 , B64C29/00 , B64C39/00 , G05D27/00
摘要： We propose a method of controlling a multi-rotor aircraft (1), said aircraft (1) comprising at least four lifting rotors (2; R1-R6), each having a first rotation axis which is essentially parallel to a yaw axis (z) of the aircraft (1), and at least one forward propulsion device (3), the at least one forward propulsion device or each of said forward propulsion devices having at least two rotors (P1_R1, P1_R2, P2_R1, P2_R2) that are arranged coaxially with a second rotation axis which is essentially parallel to a roll axis (x) of the aircraft, the at least one forward propulsion device or each of said forward propulsion devices (3, P1, P2) being arranged at a respective distance (+y, -y) from said roll axis (x), the method further comprising: using at least one of the rotors (P1_R1, P1_R2, P2_R1, P2_R2) of the at least one forward propulsion device (3, P1, P2) to control the aircraft's moment about the yaw axis (z) and/or the roll axis (x) independently from each other.

6. 发明公开

EP3901859A1 METHOD OF AND SYSTEM FOR OPERATING AN AIRCRAFT FOR ASSESSING OPERATIONAL RISK 审中-实审转让
公开(公告)号：EP3901859A1
公开(公告)日：2021-10-27
申请号：EP20170891.4
申请日：2020-04-22
申请人： Volocopter GmbH
发明人： Adolf, Florian-Michael , Ortlieb, Markus , Ciarambino, Marco
IPC分类号： G06Q10/04 , G06Q50/28
摘要： We propose a method of operating an aircraft (AC), in particular UAV, for assessing operational risk at a given position in space, comprising: dissimilarly acquiring (S1.1,...,S1.n) multiple heterogeneous geospatial data sets (DL1,...,DLn); deriving metrics for operational risk from each of said data sets(DL1,...,DLn), thus obtaining multiple corresponding geospatial risk layers (RL1,... RLn), by means of a respective risk model; storing said risk layers (RL1,...RLn) in a risk layer database (DB); accessing the risk layer database (DB) during aircraft operation planning and/or during actual aircraft operation to obtain a mission risk map (RMA); operating the aircraft (AC) based on risk information comprised in said mission risk map (RMA), preferably comprising minimizing a mission risk. We also propose a system for carrying out said method.

7. 发明公开

EP3819209A1 METHOD OF OPERATING A SYSTEM AND SYSTEM OPERABLE ACCORDINGLY, PREFERABLY IN THE FORM OF AN AIRCRAFT 有权转让
公开(公告)号：EP3819209A1
公开(公告)日：2021-05-12
申请号：EP19208294.9
申请日：2019-11-11
申请人： Volocopter GmbH
发明人： Zwiener, Jan , Yüksel, Burak , Stephan, Johannes
IPC分类号： B64C13/16 , G05D1/00 , B64D31/06 , B64C27/00 , B64C39/02 , B64C27/08 , G05D1/08
摘要： We disclose a method of operating a system, for example an aircraft (1), said system comprising a structure (5) made from a plurality of structural parts (5a-5d) interconnected via a plurality of mechanical connections, which parts and connections present inherent elasticity, said system further comprising at least one actuator, for example a propulsion unit (3), which actuator is mechanically attached to said structure (5) and which actuator is controlled by means of a control signal ( u i ) generated by a control unit (2), said system further comprising at least one sensor unit (4) for measuring a physical property of the system, the method comprising, during system operation,
a) detecting a first oscillation in an output signal of the sensor unit (4);
b) detecting a second oscillation in the control signal ( u i ), preferably on a computed control signal and, if available, on actuator states;
c) comparing said first oscillation and said second oscillation;
d) based on the comparison in step c), adapting a property of the control signal.

8. 发明公开

EP4417508A1 METHOD OF CREATING AN EMERGENCY EGRESS IN A VEHICLE, EMERGENCY EGRESS AND VEHICLE 审中-公开
公开(公告)号：EP4417508A1
公开(公告)日：2024-08-21
申请号：EP23156626.6
申请日：2023-02-14
申请人： Volocopter GmbH
发明人： Grimm, Tobias , Rodriguez, Javier
IPC分类号： B64C1/32 , B64D25/08 , B64D25/12 , B64D25/14 , B64D25/16
CPC分类号： B64C1/32
摘要： We describe a method of creating an emergency egress (1) in a vehicle, in particular in an aircraft, comprising:
a) providing a vehicle having an emergency egress opening in its chassis or fuselage (3);
b) attaching at least one cover panel (2) to said chassis or fuselage (3), in particular in an edge region of said emergency egress opening, which cover panel (2) at least partly covers said emergency egress opening;
c) embedding in a contact region of said cover panel (2) and said chassis or fuselage (3), either in an interface layer (4) between said cover panel (2) and said chassis or fuselage (3) or in said cover panel (2), at least one fluid-tight bag (4b) in a folded-in or deflated state thereof;
d) inflating said bag (4b) by injecting a fluid under pressure (pi') into said bag (4b);
e) removing said cover panel (2) from said chassis or fuselage (3).
Further described are an emergency egress (1) and a vehicle having same.

9. 发明公开

EP4319045A1 METHOD AND SYSTEM FOR VERIFYING DATA COMMUNICATION INTEGRITY IN AN AIRCRAFT 审中-实审
公开(公告)号：EP4319045A1
公开(公告)日：2024-02-07
申请号：EP22188921.5
申请日：2022-08-05
申请人： Volocopter GmbH
发明人： YÜKSEL, Burak
IPC分类号： H04L9/40 , H04L9/32 , H04L9/00
摘要： We describe a method of verifying data communication integrity in an aircraft, said aircraft comprising at least a first data generating and sending entity (1) and at least a second data receiving entity (5), wherein data generated at said first entity (1) is sent from said first entity (1) to said second entity (5) in the form of messages via a number of intermediate entities (2-4), wherein said data communication is devised in the form of a blockchain that comprises a number of blocks, each one of said blocks being added to the blockchain by a respective one of said entities (1-5) and including a cryptographic hash representative of the prior block in the blockchain, thus linking said two blocks, the method comprising:
a) logging at least a subgroup of the messages, preferably at least each message with predefined important information, most preferably all of the messages, together with a cryptographic hash at at least some of said first, second and intermediate entities, preferably at all of said first, second and intermediate entities (1-5);
b) collecting message logs from each entity (1-5) to be verified, preferably at least from said first entity (1) and said second entity (5), most preferably from all of said first, second and intermediate entities (1-5);
c) comparing at least the messages generated and sent by said first entity (1) and the messages received by said second entity (5);
d) in case that not all of the messages generated and sent by said first entity (1) have arrived at said second entity (5), comparing the message logs of each intermediate entity (2-4) with the message log of said first entity (1) in order to identify an intermediate entity (2-4) in which message loss occurred.

10. 发明公开

EP4056471A1 VTOL AIRCRAFT 审中-实审转让
公开(公告)号：EP4056471A1
公开(公告)日：2022-09-14
申请号：EP21161173.6
申请日：2021-03-08
申请人： Volocopter GmbH
发明人： STOBBE, Martin , RAJPUT, Krishna Pal , MORES, Sebastian
IPC分类号： B64C39/12 , B64C29/00 , B64C3/16
摘要： We propose a VTOL aircraft (1), comprising:
a fuselage (2) for transporting passengers and/or load;
a front wing (3) attached to the fuselage (2);
a rear wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF);
a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the rear wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two lifting units (M1-M6) on each one of the connecting beams (5a, 5b), which lifting units (M1-M6) each comprise at least one propeller (6b) and at least one motor (6a) driving said propeller (6b), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z);
wherein the front wing (3), at least in portions thereof, has a sweep angle γ between γ = 45° and γ = 135°, preferably γ = 75°, and the rear wing (4), at least in portions thereof, has a forward sweep with sweep angle β ≥ 30°, preferably, β = 65°.

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