公开(公告)号：US12227291B2

公开(公告)日：2025-02-18

申请号：US18168683

申请日：2023-02-14

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Carlos Alexander Fenny ,  Rohn Lee Olson ,  Andrew James Zahasky

IPC: B64C29/02 ,  B64C1/06 ,  B64C3/10 ,  B64C3/16 ,  B64C11/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/50 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  B64D27/24 ,  B64D31/00 ,  B64U10/20 ,  B64U30/293 ,  B64C1/00 ,  B64C39/00 ,  B64D27/02 ,  B64U30/10 ,  B64U50/11 ,  B64U50/12 ,  B64U50/19 ,  B64U60/50

Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

公开(公告)号：US12049304B2

公开(公告)日：2024-07-30

申请号：US17861702

申请日：2022-07-11

Applicant: Textron Innovations Inc.

Inventor： Eric Stephen Olson

IPC: B64C27/12 ,  B64D35/08 ,  F16D41/04 ,  B64D27/02 ,  F16D41/06

CPC classification number: B64C27/12 ,  B64D35/08 ,  F16D41/04 ,  B64D27/026 ,  F16D2041/0603

Abstract: A tail rotor isolation system for rotorcraft includes a secondary engine, first and second freewheeling units, an isolation assembly and a tail rotor system. The secondary engine is coupled to the input race of the first freewheeling unit. A main rotor system is coupled to the output race of the second freewheeling unit. The isolation assembly is coupled to the output race of the first freewheeling unit and has a fully engaged position coupling the input and output races of the second freewheeling unit and a partially engaged position coupled to the input race but decoupled from the output race of the second freewheeling unit. The tail rotor system is coupled to the input race of the second freewheeling unit such that in the partially engaged position of the isolation assembly, the overrunning mode of the second freewheeling unit isolates the tail rotor system from the main rotor system.

公开(公告)号：US20240239509A1

公开(公告)日：2024-07-18

申请号：US18559224

申请日：2022-04-25

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Benjamin Nicolas FULLERINGER ,  Antoine Pascal MOUTAUX ,  Romain Jean Gilbert THIRIET

IPC: B64D35/022 ,  B64C27/12 ,  B64D35/08 ,  F01D15/10 ,  F02C7/32

CPC classification number: B64D35/022 ,  B64D35/08 ,  F01D15/10 ,  F02C7/32 ,  B64C27/12 ,  F05D2220/50 ,  F05D2220/76

Abstract: A transmission device for a hybrid aircraft comprising a turboshaft engine including a gas generator, a free turbine, and a main rotor, the device comprising a first reversible electric machine coupled to a shaft of the free turbine by way of a first deactivatable coupling means, and to the main rotor, and a second reversible electric machine coupled to a shaft of the gas generator by way of a second deactivatable coupling means, and coupled to the main rotor by way of a third deactivatable coupling means, the second deactivatable coupling means being able to be activated when the second electric machine rotates in a first direction of rotation, and the third deactivatable coupling means being able to be activated when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.

公开(公告)号：US20240228057A1

公开(公告)日：2024-07-11

申请号：US18559698

申请日：2022-04-21

Applicant: LEONARDO S.P.A.

Inventor： Mara Tanelli ,  Jessica Leoni ,  Alberto Bellazzi ,  Francesca Bianchi ,  Luigi Bottasso ,  Andrea Palman

IPC: B64D45/00 ,  B64F5/60 ,  B64C27/12

CPC classification number: B64D45/00 ,  B64F5/60 ,  B64C27/12 ,  B64D2045/0085

Abstract: A computer-implemented method is described for detecting anomalies in a transmission system of an aircraft equipped with a monitoring system, which includes a number of sensors coupled to the transmission system and determines, for each flight of the aircraft a number of respective time intervals and acquires through each sensor, for each of the time intervals, a corresponding primary signal indicative of a corresponding dynamic quantity dependent on the operation of the transmission system during at least part of the time interval. For each sensor, the monitoring system determines, starting from each primary signal acquired through the sensor during a corresponding time interval, a corresponding set of values of at least one corresponding group of synthetic indexes. The method includes detecting anomalies of the transmission system on the basis of the groups of synthetic indexes.

公开(公告)号：US12006036B2

公开(公告)日：2024-06-11

申请号：US18168257

申请日：2023-02-13

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Carlos Alexander Fenny ,  Rohn Lee Olson

IPC: B64C29/02 ,  B64C1/06 ,  B64C3/10 ,  B64C3/16 ,  B64C11/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/50 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  B64D27/24 ,  B64D31/00 ,  B64C1/00 ,  B64C39/00 ,  B64D27/02

CPC classification number: B64C29/02 ,  B64C1/068 ,  B64C3/10 ,  B64C3/16 ,  B64C11/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/50 ,  B64C29/0025 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64D27/24 ,  B64D31/00 ,  B64C2001/0045 ,  B64C39/029 ,  B64D27/026

Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

公开(公告)号：US11970261B2

公开(公告)日：2024-04-30

申请号：US17597316

申请日：2020-07-02

Applicant: SAFRAN ELECTRICAL & POWER

Inventor： Jacques Eche ,  Yann Tondriaux

IPC: B64C11/02 ,  B64C27/12

CPC classification number: B64C11/02 ,  B64C27/12

Abstract: Aircraft comprising a primary propeller driven in rotation by a motor, the motor having a first assembly and a second assembly movable in rotation relative to each other along an axis of rotation, the primary propeller being secured in rotation to one of said first assembly and second assembly, the first assembly and the second assembly being movable in translation relative to each other along a direction of translation defined by the axis of rotation, between a rest position and a service position, characterized in that said aircraft comprises a locking system, comprising a housing and an indexing element, the housing being formed in one among the first assembly and the second assembly, the indexing element being secured to the other among the first assembly and the second assembly, the locking system having an engaged configuration in which the indexing element is at least partially inserted into the housing.

公开(公告)号：US20240017824A1

公开(公告)日：2024-01-18

申请号：US18373172

申请日：2023-09-26

Applicant: Lockheed Martin Corporation

Inventor： James Breen Orbon ,  James McCollough ,  Evan S. Tobin ,  Xiaole Xie ,  Jonathan Frydman

IPC: B64C27/46 ,  B64D13/00 ,  B64C27/12

CPC classification number: B64C27/46 ,  B64D13/006 ,  B64C27/12 ,  B64C2027/8272

Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

公开(公告)号：US11853054B2

公开(公告)日：2023-12-26

申请号：US17603193

申请日：2021-10-12

Applicant: Aergility Corporation

Inventor： James E. Vander Mey ,  Lawrence Winston Yonge, III

IPC: B64C27/02 ,  G05D1/08 ,  B64C11/50 ,  B64C27/10 ,  B64C27/12 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C27/00 ,  B64C27/14 ,  B64D27/24 ,  H02K1/27 ,  B64C11/48 ,  B64C27/82

CPC classification number: G05D1/0858 ,  B64C11/50 ,  B64C27/006 ,  B64C27/02 ,  B64C27/021 ,  B64C27/025 ,  B64C27/027 ,  B64C27/028 ,  B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C11/48 ,  B64C2027/8236 ,  B64D27/24 ,  H02K1/27

Abstract: A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

公开(公告)号：US20230391464A1

公开(公告)日：2023-12-07

申请号：US18449145

申请日：2023-08-14

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Keith David Weaver ,  Michael Pujol ,  Andrew Jordan Birkenheuer ,  Nicholas Plagianos ,  Karl Burge ,  Thomas Mast

IPC: B64D33/08 ,  B64C27/12 ,  F01P1/06 ,  F01P11/10 ,  F16H57/04

CPC classification number: B64D33/08 ,  B64C27/12 ,  F01P1/06 ,  F01P11/10 ,  F16H57/0416

Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.

公开(公告)号：US11829161B2

公开(公告)日：2023-11-28

申请号：US17603180

申请日：2020-04-10

Applicant: Aergility Corporation

Inventor： James E. Vander Mey ,  Lawrence Winston Yonge, III

IPC: B64C27/10 ,  G05D1/08 ,  B64C11/50 ,  B64C27/02 ,  B64C27/12 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C27/00 ,  B64C27/14 ,  B64D27/24 ,  H02K1/27 ,  B64C11/48 ,  B64C27/82

CPC classification number: G05D1/0858 ,  B64C11/50 ,  B64C27/006 ,  B64C27/02 ,  B64C27/021 ,  B64C27/025 ,  B64C27/027 ,  B64C27/028 ,  B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C11/48 ,  B64C2027/8236 ,  B64D27/24 ,  H02K1/27

Abstract: A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.