公开(公告)号：US12168520B2

公开(公告)日：2024-12-17

申请号：US17778148

申请日：2020-12-09

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： David Lemay ,  Jean-Philippe Jacques Marin

IPC: H02P1/16 ,  B64D31/12 ,  B64D31/16 ,  H02P5/50 ,  H02P5/74

Abstract: A system (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, includes at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).

公开(公告)号：US20240337214A1

公开(公告)日：2024-10-10

申请号：US18746225

申请日：2024-06-18

Applicant: General Electric Company

Inventor： David Alexander Hiett ,  Stefan Joseph Cafaro ,  Robert Jon McQuiston ,  David Marion Ostdiek

IPC: F02C6/14 ,  B64D27/02 ,  B64D27/24 ,  B64D31/12 ,  F01D15/10 ,  F02C6/00

CPC classification number: F02C6/14 ,  B64D27/24 ,  B64D31/12 ,  F01D15/10 ,  F02C6/00 ,  B64D27/026 ,  F05D2220/76

Abstract: A method is provided for operating a hybrid-electric propulsion system having a first engine, a second engine, a first electric machine coupled to the first engine, and a second electric machine coupled to one of the first engine or the second engine. The method includes: receiving data indicative of a first engine operating parameter, a second engine operating parameter, or both; determining a first engine operating parameter margin, a second parameter operating margin, or both; determining a load share for the first engine, the second engine, or both, or between the first engine and the second engine based on the first engine operating parameter margin, the second engine operating parameter margin, or both; and transferring a first amount of power to or from the first electric machine and a second amount of power to or from the second electric machine in response to the determined load share.

公开(公告)号：US12077308B2

公开(公告)日：2024-09-03

申请号：US17721015

申请日：2022-04-14

Applicant: Textron Innovations Inc.

Inventor： Charles Eric Covington ,  Chia-Wei Su ,  Darren Gregory Lang

IPC: B64D35/08 ,  B64D31/12

CPC classification number: B64D31/12 ,  B64D35/08

Abstract: A method of operating a multi-engine drive system of an aircraft includes driving a main rotor of the aircraft by a main engine of the multi-engine drive system at an operating speed of the main engine, operating a supplemental engine of the multi-engine drive system at approximately 80% of an operating speed of the supplemental engine, wherein, during the operating step, a clutch interoperably coupled to the supplemental engine is interoperably decoupled from the main rotor and, responsive to a command to interoperably engage the clutch, if the clutch successfully engages such that the clutch is interoperably coupled to the main rotor, providing, by the supplemental engine, power to the main rotor.

公开(公告)号：US11939049B2

公开(公告)日：2024-03-26

申请号：US17947357

申请日：2022-09-19

Applicant: Hyundai Motor Company ,  Kia Corporation

Inventor： Woo Suk Jung ,  Hee Kwang Lee ,  Hyun Seok Hong ,  Hyun Woo Jun

IPC: B64D35/02 ,  B60L53/00 ,  B60L58/12 ,  B64C27/32 ,  B64C27/82 ,  B64C29/00 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D31/10 ,  B64D31/12 ,  B64D33/02

CPC classification number: B64C27/82 ,  B60L53/00 ,  B60L58/12 ,  B64C27/32 ,  B64C29/0025 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D31/10 ,  B64D31/12 ,  B64D33/02 ,  B64D35/02 ,  B60L2200/10 ,  B64C2027/8227 ,  B64D27/026 ,  B64D2033/0213

Abstract: In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.

公开(公告)号：US11939047B2

公开(公告)日：2024-03-26

申请号：US17746591

申请日：2022-05-17

Applicant: AIRBUS HELICOPTERS

Inventor： Kamel Abdelli

IPC: B64C27/57 ,  B64C27/26 ,  B64D31/12 ,  B64D35/04

CPC classification number: B64C27/57 ,  B64C27/26 ,  B64D31/12 ,  B64D35/04

Abstract: A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

公开(公告)号：US20230382546A1

公开(公告)日：2023-11-30

申请号：US17752020

申请日：2022-05-24

Applicant: BETA AIR, LLC

Inventor： Collin Freiheit ,  Nicholas Moy

IPC: B64D31/12 ,  B64D27/24 ,  B64C29/00 ,  B64C11/50

CPC classification number: B64D31/12 ,  B64D27/24 ,  B64C29/0025 ,  B64C11/50

Abstract: A system for propulsor synchronization using electronic brakes is disclosed. The system includes a controller located in an electric aircraft configured to receive a first signal from a first propulsor sensor of a plurality of propulsor sensors, the first propulsor sensor configured to measure a first motion parameter of a first propulsor of a plurality of propulsors. The controller may receive a second signal from a second propulsor sensor of the plurality of propulsor sensors, the second propulsor sensor configured to measure a second motion parameter of a second propulsor of the plurality of propulsors. The controller may synchronously decelerate the first propulsor and the second propulsor based on the first motion parameter and the second motion parameter.

公开(公告)号：US20230211889A1

公开(公告)日：2023-07-06

申请号：US17568892

申请日：2022-01-05

Applicant: General Electric Company

Inventor： Honggang Wang ,  Kum Kang Huh ,  Michael Anthony Benjamin ,  Koji Asari

IPC: B64D31/12 ,  B64D27/24 ,  B64D27/10

CPC classification number: B64D31/12 ,  B64D27/24 ,  B64D27/10 ,  B64D2027/026

Abstract: Systems and methods of aircraft thrust management are provided. For example, a propulsion system for an aircraft comprises a fuel cell assembly comprising a fuel cell, a turbomachine, and a controller comprising memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the propulsion system to perform operations including receiving data indicative of a propulsion system thrust discrepancy and modifying an output of the fuel cell in response to receiving data indicative of the propulsion system thrust discrepancy. Modifying the fuel cell output may include modifying output products, an electrical power output, or both of the fuel cell to balance the thrust provided by the propulsion system.

公开(公告)号：US20230211876A1

公开(公告)日：2023-07-06

申请号：US17569996

申请日：2022-01-06

Applicant: Bell Textron Inc.

Inventor： Thomas Dewey Parsons

IPC: B64C27/12 ,  B64D31/12 ,  B64D31/10 ,  B64D45/04 ,  F02C9/42

CPC classification number: B64C27/12 ,  B64D31/12 ,  B64D31/10 ,  B64D45/04 ,  F02C9/42 ,  F05D2220/329 ,  F05D2270/093 ,  F05D2270/13

Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.

公开(公告)号：US20230124967A1

公开(公告)日：2023-04-20

申请号：US17952603

申请日：2022-09-26

Applicant: ALETHOS, INC.

Inventor： George Peter Kelesis ,  Christian Mendy

IPC: G06F21/62 ,  H04L9/08 ,  G06F21/60 ,  H04L9/40 ,  B64C27/00 ,  B64C27/08 ,  B64C27/12 ,  B64C27/57 ,  B64D31/10 ,  B64D31/12 ,  B64D45/00

Abstract: Methods and systems are configured to store user data and control access to the user data, wherein the data is stored remotely from the user (such as external to a user's computing device) and the user's data is maintained anonymously. Content is stored in association with a user identifier and access by third parties is controlled by linked third party identifiers.

公开(公告)号：US20230045047A1

公开(公告)日：2023-02-09

申请号：US17967678

申请日：2022-10-17

Applicant: BOMBARDIER INC.

Inventor： Thineshan KATHIRCHELVAN ,  Stephen COLAVINCENZO ,  Alexis CARON-L'ECUYER

IPC: F02C9/00 ,  G01H17/00 ,  B64D31/12

Abstract: Systems and method for synchrophasing aircraft engines are disclosed. One method comprises receiving data indicative of a sensed vibration level associated with a first aircraft engine and a second aircraft engine operating at a substantially same operating speed and commanding one or more momentary changes in operating speed of the second aircraft engine until the sensed vibration level substantially reaches a target vibration level. The momentary changes in operating speed of the second aircraft engine is commanded irrespective of phase information associated with imbalances of the first and second aircraft engines.