公开(公告)号：US12199541B2

公开(公告)日：2025-01-14

申请号：US18401446

申请日：2023-12-30

Applicant: Archer Aviation, Inc.

Inventor： Guy Bernard ,  Geoffrey Bower ,  Diederik Marius ,  Kurt Wagner ,  Stephen Spiteri

IPC: H02P29/00 ,  B64C11/00 ,  B64D31/02 ,  H03K17/56

Abstract: An aircraft system for damping movement of a structural flight element. The aircraft system including a moveable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft is providing power, the controller controls the first transistor to prevent current flow through its terminals and through the resistor. Further, when the power source of the aircraft is not providing power, the first transistor allows current generated by a back EMF (electromotive force) voltage to flow through its terminals and through the resistor, the back EMF voltage being created by movement of the moveable aircraft structure.

公开(公告)号：US11958622B2

公开(公告)日：2024-04-16

申请号：US16875095

申请日：2020-05-15

Applicant: Pratt & Whitney Canada Corp.

Inventor： Richard A. Poisson ,  Paul C. Imel ,  Leonid Guerchkovitch

IPC: B64D31/02 ,  B64D27/02 ,  B64D27/04 ,  B64D27/24

CPC classification number: B64D31/02 ,  B64D27/02 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026

Abstract: A method includes controlling an electric motor of a hybrid-electric powerplant for an aircraft using an EPC (electric powertrain controller) and controlling a heat engine of the hybrid-electric powerplant using an ECU (engine control unit). The method includes performing at least one of the following to protect the hybrid-electric powerplant: using the ECU to power down the electric motor, and/or using the EPC to power down the heat engine.

公开(公告)号：US11945597B2

公开(公告)日：2024-04-02

申请号：US17157580

申请日：2021-01-25

Applicant: Archer Aviation, Inc.

Inventor： Geoffrey C. Bower ,  Nansi Xue ,  Alan Chen ,  Benjamin Goldman ,  Nathan Depenbusch

IPC: B64D31/02 ,  B60L50/60 ,  B60L58/12 ,  B64C27/57 ,  B64C27/59 ,  B64C29/00 ,  B64D27/24 ,  B64D31/14

CPC classification number: B64D31/02 ,  B60L50/60 ,  B60L58/12 ,  B64C27/57 ,  B64C27/59 ,  B64C29/0033 ,  B64D27/24 ,  B64D31/14 ,  B60L2200/10

Abstract: A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.

公开(公告)号：US11945573B2

公开(公告)日：2024-04-02

申请号：US17529556

申请日：2021-11-18

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Mehdi Milani Baladi ,  Randy M Vondrell

IPC: B64C17/06 ,  B64C29/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02

CPC classification number: B64C17/06 ,  B64C29/0033 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02 ,  B64D2027/026

Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

公开(公告)号：US11773788B2

公开(公告)日：2023-10-03

申请号：US17126257

申请日：2020-12-18

Applicant: Safran Nacelles

Inventor： Patrick Gonidec ,  Jean-Paul Rami

IPC: H04B10/00 ,  F02C9/16 ,  B64D31/02 ,  B64D47/02 ,  H04B10/116 ,  H04J14/00

CPC classification number: F02C9/16 ,  B64D31/02 ,  B64D47/02 ,  H04B10/116 ,  B64D2203/00 ,  F05D2220/323 ,  F05D2270/01 ,  F05D2270/301 ,  F05D2270/3061

Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

公开(公告)号：US20220397916A1

公开(公告)日：2022-12-15

申请号：US17344171

申请日：2021-06-10

Applicant: Lockheed Martin Corporation

Inventor： Navid Dadkhah Tehrani

IPC: G05D1/10 ,  B64C27/10 ,  B64C11/00 ,  B64D31/02 ,  G08G5/00

Abstract: Systems and methods for controlling a coaxial rotary-wing aircraft including a co-axial main rotor assembly and a pusher-propeller. One system includes an electronic controller configured to receive a reference velocity of the aircraft and receive a reference flight path angle of the aircraft. The electronic controller is also configured to simultaneously control the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft, by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion.

公开(公告)号：US11505315B2

公开(公告)日：2022-11-22

申请号：US17040896

申请日：2019-04-12

Applicant: Korea Aerospace Research Institute

Inventor： Sung Ho Chang ,  Yu Shin Kim ,  Seong Wook Choi ,  Young Shin Kang ,  Am Cho

IPC: B64C29/00 ,  B64C3/38 ,  B64C5/02 ,  B64C5/06 ,  B64C5/10 ,  B64C13/02 ,  B64C27/20 ,  B64D31/02

Abstract: The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.

公开(公告)号：US11142328B2

公开(公告)日：2021-10-12

申请号：US15896487

申请日：2018-02-14

Applicant: Hamilton Sundstrand Corporation

Inventor： William E. Rhoden

IPC: G01C23/00 ,  B64D31/02 ,  H04L29/06 ,  B64C13/02

Abstract: A powered aircraft includes at least one thrust producing engine and an engine controller controllably coupled to the at least one thrust producing engine. The engine controller includes at least a first control channel and a drag control channel. The first control channel is configured to control the at least one thrust producing engine via thrust control and the drag control channel is configured to control the at least one thrust producing engine via drag control.

公开(公告)号：US10906657B2

公开(公告)日：2021-02-02

申请号：US16012047

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  B64D31/14 ,  B64D33/04 ,  F02C6/20 ,  B64D31/02 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  F02C6/14

Abstract: A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least one auxiliary propulsion fan is configured to selectively receive a motive force from either or both of the at least two gas turbine engines through at least one shaft operatively coupled to the at least one auxiliary propulsion fan.

公开(公告)号：US20200277062A1

公开(公告)日：2020-09-03

申请号：US16709051

申请日：2019-12-10

Applicant: Pratt & Whitney Canada Corp.

Inventor： Frank Becker ,  Xi Wang ,  Antonio Pizzi ,  Charles E. Lents

IPC: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  B64D29/02 ,  B64D41/00 ,  B64D37/04 ,  B64D31/02 ,  B64C3/32 ,  B64C3/34 ,  B60L50/60 ,  B60L15/20

Abstract: An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. At least one airfoil is laterally extending from the fuselage defining an airfoil axis. An electrical system has an electric storage. The electric storage is positioned within the airfoil.