公开(公告)号：US20240359807A1

公开(公告)日：2024-10-31

申请号：US18139675

申请日：2023-04-26

Applicant: Rockwell Collins, Inc.

Inventor： Darin M. Underwood ,  D. Mark Fejfar

IPC: B64D37/00

CPC classification number: B64D37/005

Abstract: A fuel quantity indicator system (FQIS) for an aircraft or other vehicle includes memory/data storage and a fuel quantity processing unit (FQPU). A neural network trained via machine learning and running on the FQPU receives fuel quantity (FQ) inputs from fuel tank sensors, e.g., tank density, fuel volume, water presence within the tank, at or near a given measurement time. The neural network additionally receives fuel flow (FF) inputs from flow sensors at the measurement time, indicating fuel flow to engines and auxiliary power units (APU) of the vehicle. Based on the FQ inputs and the FF inputs, the neural network calculates an estimated fuel quantity (EFQ) remaining, e.g., across all fuel tanks at or near a particular measurement time.

公开(公告)号：US20240174372A1

公开(公告)日：2024-05-30

申请号：US18522340

申请日：2023-11-29

Applicant: Airbus Operations Limited

Inventor： Dylan Vignola

IPC: B64D37/00 ,  B64C3/34

CPC classification number: B64D37/005 ,  B64C3/34

Abstract: An aircraft including a wing, a first pressure sensor and a second pressure sensor, wherein each pressure sensor is configured to measure pressure of a liquid within the wing and has a known position within the wing. The aircraft includes a processing system configured to receive first pressure data from the first pressure sensor, receive second pressure data from the second pressure sensor, and determine a bending state of the wing based on the first pressure data, the second pressure data, and the known positions of the first and second pressure sensors within the wing.

公开(公告)号：US20240150033A1

公开(公告)日：2024-05-09

申请号：US18356655

申请日：2023-07-21

Applicant: Airbus Operations SAS

Inventor： Pierre-Olivier MARTIN ,  Lionel CZAPLA ,  Mathieu BELLEVILLE

IPC: B64D37/30 ,  B64D37/00 ,  F02C7/232

CPC classification number: B64D37/30 ,  B64D37/005 ,  F02C7/232

Abstract: A supply system for an aircraft, wherein the supply system has a supply module with outlet pipes, feed pipes connected to dihydrogen tanks, and means for channeling the dihydrogen in the feed pipes towards the outlet pipes, a distribution module having introduction pipes connected to the outlet pipes via heaters, distribution pipes connected to an engine, and means for channeling the dihydrogen in the introduction pipes towards the distribution pipes, and a control unit which commands the means of the supply module and of the distribution module depending on the information provided by the detection means. Also an aircraft with such a supply system.

公开(公告)号：US20230294838A1

公开(公告)日：2023-09-21

申请号：US18184828

申请日：2023-03-16

Applicant: Eaton Intelligent Power Limited

Inventor： Sandip Balasaheb GAIKWAD ,  Ranjit Dinkar PATIL ,  Michael OLSZTYN ,  Graham Peter BAKER

IPC: B64D37/00 ,  B64D37/30 ,  G01F23/18

CPC classification number: B64D37/005 ,  B64D37/30 ,  G01F23/18

Abstract: A measurement system and method for liquid quantity in a receptable, the measurement system including a plurality of sensor units at various locations of the receptacle, the receptable including the liquid therein, each of the plurality of sensor units being on an outside surface of the receptacle, a data receiver coupled to the plurality of sensor units via one or more connectors and configured to receive measurements from the plurality of sensor units via the one or more connectors, and a processor coupled to the data receiver and configured to convert the received measurements from the plurality of sensor units to a measured quantity of liquid inside the receptable.

公开(公告)号：US11749851B2

公开(公告)日：2023-09-05

申请号：US16449146

申请日：2019-06-21

Applicant: Hamilton Sundstrand Corporation

Inventor： Malcolm Macdonald ,  Charles E. Lents

IPC: H01M10/63 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6561 ,  B64D37/00 ,  F28F27/02 ,  H01M10/48

CPC classification number: H01M10/63 ,  B64D37/005 ,  F28F27/02 ,  H01M10/486 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6561 ,  F28F2250/06 ,  H01M2220/20

Abstract: A battery thermal management system for an air vehicle includes a first heat exchange circuit, a battery in thermal communication with the first heat exchange circuit, and a heat exchanger positioned on the first heat exchange circuit. The heat exchanger is operatively connected to a second heat exchange circuit. The system includes a controller operatively connected to the second heat exchange circuit. The controller is configured to variably select whether heat will be rejected to the second heat exchange circuit. A method for controlling a thermal management system for an air vehicle includes determining an expected fluid temperature of fluid in a fluid heat exchange circuit. The method includes commanding a flow restrictor at least partially closed or commanding the flow restrictor at least partially open.

公开(公告)号：US11603205B2

公开(公告)日：2023-03-14

申请号：US17164789

申请日：2021-02-01

Applicant: Victor A Grossman

Inventor： Victor A Grossman

IPC: B64D7/00 ,  B64D37/00 ,  B64F5/00 ,  B64F1/22 ,  B64F1/28 ,  F41A9/87 ,  B64F5/60 ,  B64F5/50 ,  B63B35/50 ,  B64D37/04

Abstract: Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

公开(公告)号：US11542031B2

公开(公告)日：2023-01-03

申请号：US16629702

申请日：2018-07-11

Applicant: Safran Aerosystems

Inventor： Philippe Bulard ,  Christophe Mendes ,  Loïc Boissy ,  Hichem Amara

IPC: B64D37/08 ,  B64D37/00

Abstract: Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.

公开(公告)号：US11480113B2

公开(公告)日：2022-10-25

申请号：US16428283

申请日：2019-05-31

Applicant: Airbus Operations (S.A.S.)

Inventor： Alvaro Ruiz Gallardo

IPC: F02C9/52 ,  F02C7/22 ,  B64D37/00

Abstract: A method and system for acquiring fuel characteristics on board an aircraft. The method for acquiring fuel characteristic on board an aircraft includes a least one tank and comprises a determination step determining a fuel circuit in one tank among the tank or tanks. The circuit includes at least one pump pumping the fuel from the tank into the circuit. A fuel properties measurement unit and a first valve are configured to open or close the circuit. A filling step includes filling the circuit with fuel. An acquisition step includes acquiring a value respectively for each of the fuel characteristics of the tank, and a transmission step includes transmitting, to a user device, a signal representative of the acquired values of the fuel characteristics.

公开(公告)号：US11326527B2

公开(公告)日：2022-05-10

申请号：US16259321

申请日：2019-01-28

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Michael Crowley

IPC: F02C9/28 ,  F16K37/00 ,  B64D37/00 ,  F02C7/232 ,  F02C7/236 ,  F02C9/26

Abstract: A valve apparatus for an aircraft fluid system is disclosed including a valve housing and a valve member. The valve member is configured to move between a first position in which fluid is able to flow along the fluid flow path, and a second position in which the fluid flow path restricted. A valve member drive means is configured to operate the valve member via an actuator external to the housing. The valve apparatus further includes a sensor configured to monitor a feature in the housing to determine the position of the valve member.

公开(公告)号：US20220135239A1

公开(公告)日：2022-05-05

申请号：US17517858

申请日：2021-11-03

Applicant: AIRBUS HELICOPTERS

Inventor： Luca COSSETTI ,  Francois MALBURET

IPC: B64D31/00 ,  B64D27/10 ,  B64D27/24 ,  B64D37/00 ,  B64C27/00 ,  F02C7/22

Abstract: A method for controlling at least a first turboshaft engine and a second turboshaft engine of a rotorcraft, which set a common kinematic linkage in motion, the rotorcraft having an output electric machine cooperating with a first output kinematic linkage of the first turboshaft engine, the rotorcraft having an input electric machine cooperating with a gas generator of the second turboshaft engine. The method includes the following steps: supplying fuel to the first turboshaft engine, operating the output electric machine in electrical energy generator mode, supplying fuel to the second turboshaft engine, and operating the input electric machine in motor mode in order to supply a second non-zero power to said common kinematic linkage.