公开(公告)号：US20250021715A1

公开(公告)日：2025-01-16

申请号：US18767300

申请日：2024-07-09

Applicant: Airbus Defence and Space GmbH ,  AIRBUS DEFENCE AND SPACE, S.A.U.

Inventor： Stefan Neumeier ,  Alasdair Cook ,  Antonio Perez Acal ,  Janaina Ribas De Amaral

IPC: G06F30/15

Abstract: An apparatus management system for controlling at least one function of an apparatus, such as a vehicle, operated by an operator and exposed to a potential impact approaching the apparatus, includes: an impact reaction system, configured for generating a command for controlling the at least one function of the apparatus; wherein the impact reaction system includes: an intervention control unit; and an operator notification unit. The intervention control unit includes at least one control model configured for assessing at least one command for controlling the at least one function of the apparatus to perform an intervention to avoid the impact. The operator notification unit is configured to issue at least one notification to the operator regarding the at least one command. The intervention control unit is configured to output the at least one command for controlling the at least one function of the apparatus subsequent to issuance of the notification.

公开(公告)号：US12116145B2

公开(公告)日：2024-10-15

申请号：US18477264

申请日：2023-09-28

Applicant: Airbus Defence and Space GmbH

Inventor： Christoph Meisner ,  Kay Dittrich ,  Mircea Calomfirescu ,  Sven Brinkmann

IPC: B64F5/10 ,  B64C1/14

CPC classification number: B64F5/10 ,  B64C1/14

Abstract: A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required is disclosed having an outer structure, a reinforcing plate which is mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure. The reinforcing plate has a through-opening along the surface normal of the contact surface, and a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement.

公开(公告)号：US20240302487A1

公开(公告)日：2024-09-12

申请号：US18596958

申请日：2024-03-06

Applicant: Airbus Defence and Space GmbH

Inventor： Andre FRANKE ,  Julia POINTNER

IPC: G01S5/14

CPC classification number: G01S5/14

Abstract: A method and system for determining a position of a transmitter includes synchronizing receivers by forwarding a list of measurement parameters from a central control unit to the receivers, wherein the list of measurement parameters contains a multiplicity of measurement time intervals, measuring signals by the receivers using the list of measurement parameters, forwarding data relating to the measured signals from the receivers to the central control unit, wherein the data relating to the measured signals contain a measurement time and a measurement position of the measured signal, and evaluating the forwarded data to determine the position of the transmitter by the central control unit.

公开(公告)号：US12065259B2

公开(公告)日：2024-08-20

申请号：US17765152

申请日：2020-09-30

Applicant: Airbus Defence and Space GmbH

Inventor： Borja Sanz Lopez ,  Clemens Brand ,  Michael Jost ,  Winfried Lohmiller ,  Georg Söllinger ,  Dieter Grebner ,  Oliver Motlik

IPC: B64D37/22 ,  B64D37/30 ,  B64U50/32 ,  H01M8/0656 ,  H01M8/18

CPC classification number: B64D37/22 ,  B64D37/30 ,  B64U50/32 ,  H01M8/0656 ,  H01M8/18 ,  H01M2250/20

Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

公开(公告)号：US12027638B2

公开(公告)日：2024-07-02

申请号：US18159736

申请日：2023-01-26

Applicant: Airbus Defence and Space GmbH

Inventor： Claus Zimmermann

IPC: H01L31/054 ,  H01L31/0304 ,  H01L31/048 ,  H01L31/0725 ,  H01L31/18

CPC classification number: H01L31/0547 ,  H01L31/0304 ,  H01L31/03046 ,  H01L31/0725 ,  H01L31/1844 ,  H01L31/048 ,  H01L31/1892

Abstract: A photovoltaic assembly dual junction solar cell for space use including a solar cell stack including first and second subcells stacked on each other and each including an epitaxially grown light absorbing layer. The first subcell is adjacent to a solar cell stack front, light-receiving surface and the second subcell is adjacent to a solar cell stack rear surface. The first subcell light absorbing layer has a larger bandgap than the second subcell light absorbing layer. A light reflecting element positioned adjacent to a second subcell light absorbing layer rear side is configured to reflect photons having an energy smaller than the bandgap energy of the second subcell light absorbing layer and/or photons having an energy larger than the bandgap energy of the second subcell light absorbing layer and smaller than the bandgap energy of the first subcell light absorbing layer with a reflectivity of at least 90%.

公开(公告)号：US20240196584A1

公开(公告)日：2024-06-13

申请号：US18530278

申请日：2023-12-06

Applicant: Airbus SAS ,  Airbus Defence and Space GmbH

Inventor： Alois FRIEDBERGER ,  Patrice LEFEBURE ,  Caroline PETIOT

IPC: H05K13/04 ,  H05K1/02 ,  H05K13/08

CPC classification number: H05K13/0486 ,  H05K1/0292 ,  H05K13/083 ,  H05K2201/09418

Abstract: A part comprising a body and a film bonded to a surface of the body and incorporating an electronic circuit. This electronic circuit comprises at least one electronic component, conductive lines connected to the electronic component and at least two connection terminals positioned on at least one of the conductive lines, each connection terminal having a cross-section, in a plane parallel to the surface of the body, greater than twice the cross-section of a conductive line. By virtue of the connection terminals, which are distributed over the electronic circuit, it is possible to replace a faulty circuit segment with a repair circuit segment.

公开(公告)号：US11933852B2

公开(公告)日：2024-03-19

申请号：US17804509

申请日：2022-05-27

Applicant: Airbus Helicopters Deutschland GmbH ,  Airbus Defence and Space GmbH

Inventor： Philipp Weinreiter ,  Kristian Zimmermann

IPC: G01R31/382 ,  G01R31/36 ,  H01M10/48 ,  H01M50/51

CPC classification number: G01R31/382 ,  G01R31/3646 ,  H01M10/482 ,  H01M10/486 ,  H01M50/51

Abstract: A battery and an electrical battery monitoring device are disclosed having a first group of sensing switches connected in series on a first monitoring circuit, the sensing switches, a second group of electrical sensing switches connected in series on a second monitoring circuit, an input unit to provide an input to the first and second monitoring circuits, a monitoring unit to receive an output from the first and second monitoring circuits, wherein the monitoring unit receives at least two outputs from two measuring points of the first monitoring circuit, the two measuring points being separated by at least one sensing switch. The location of a defective battery cell may be early detected and precisely located by the monitoring of the battery cells in rows and columns.

公开(公告)号：US11876265B2

公开(公告)日：2024-01-16

申请号：US17462297

申请日：2021-08-31

Applicant: Airbus Defence and Space GmbH

Inventor： Kristian Zimmermann ,  Stephan Friedl ,  Christian Metzner

IPC: H01M8/10 ,  H01M8/0258 ,  H01M8/0202 ,  H01M8/122 ,  H01M8/1006

CPC classification number: H01M8/10 ,  H01M8/0258 ,  H01M8/0269 ,  H01M8/1006 ,  H01M8/122 ,  H01M2250/20

Abstract: In order to improve usability of hybrid or fully electric aircraft, a fuel cell having improved efficiency and increased volume/weight specific energy density is provided. The fuel cell has a self-supporting membrane structure that is formed as a triply periodic level surface, which separates a first cavity supplied with gaseous fuel from a second cavity supplied with gaseous oxidizer in a gas-sealed manner while connecting the cavities in an ion-conductive manner.

公开(公告)号：US20230376048A1

公开(公告)日：2023-11-23

申请号：US18248288

申请日：2021-10-05

Applicant: Airbus Defence and Space GmbH

Inventor： Tobias NEUHAUSER

IPC: G05D1/02 ,  H04W4/46

CPC classification number: G05D1/0293 ,  H04W4/46

Abstract: A method for determining a correction value of a state of an object in an association with a plurality of objects. The method includes: each object in the association recording its own absolute state in an existing coordinate system; a first object in the association recording a relative state of the first object in relation to one or more other objects in the association; the first object transmitting the recorded relative state and its own recorded absolute state via a data connection to one or more of the other objects in the association; exchanging recorded relative states and recorded absolute states in the association of objects so that all objects have the same uniform information status; each object calculating a correction value for all objects in the association based on the uniform information status; an object applying its own correction value to its own recorded absolute state.

公开(公告)号：US11772809B2

公开(公告)日：2023-10-03

申请号：US17535995

申请日：2021-11-27

Applicant: Airbus Defence and Space GmbH

Inventor： Wolfgang Stangl ,  Robert Osterhuber ,  Philipp Ernstberger

IPC: F02K1/12 ,  B64D33/04 ,  B64D27/20 ,  B64D29/04 ,  B64C1/16 ,  F02K1/00 ,  F02K1/80

CPC classification number: B64D33/04 ,  B64C1/16 ,  B64D27/20 ,  B64D29/04 ,  F02K1/002 ,  F02K1/006 ,  F02K1/1223 ,  F02K1/80

Abstract: A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.