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公开(公告)号：US12049304B2
公开(公告)日：2024-07-30
申请号：US17861702
申请日：2022-07-11
发明人： Eric Stephen Olson
CPC分类号： B64C27/12 , B64D35/08 , F16D41/04 , B64D27/026 , F16D2041/0603
摘要： 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.
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公开(公告)号：US20240239509A1
公开(公告)日：2024-07-18
申请号：US18559224
申请日：2022-04-25
IPC分类号： B64D35/022 , B64C27/12 , B64D35/08 , F01D15/10 , F02C7/32
CPC分类号： B64D35/022 , B64D35/08 , F01D15/10 , F02C7/32 , B64C27/12 , F05D2220/50 , F05D2220/76
摘要： 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.
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公开(公告)号：US20240228057A1
公开(公告)日：2024-07-11
申请号：US18559698
申请日：2022-04-21
申请人： LEONARDO S.P.A.
发明人： Mara Tanelli , Jessica Leoni , Alberto Bellazzi , Francesca Bianchi , Luigi Bottasso , Andrea Palman
CPC分类号： B64D45/00 , B64F5/60 , B64C27/12 , B64D2045/0085
摘要： 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.
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公开(公告)号：US12006036B2
公开(公告)日：2024-06-11
申请号：US18168257
申请日：2023-02-13
IPC分类号： 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分类号： 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
摘要： 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.
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公开(公告)号：US11970261B2
公开(公告)日：2024-04-30
申请号：US17597316
申请日：2020-07-02
发明人： Jacques Eche , Yann Tondriaux
摘要： 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.
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公开(公告)号：US20240017824A1
公开(公告)日：2024-01-18
申请号：US18373172
申请日：2023-09-26
CPC分类号： B64C27/46 , B64D13/006 , B64C27/12 , B64C2027/8272
摘要： 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.
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公开(公告)号：US11853054B2
公开(公告)日：2023-12-26
申请号：US17603193
申请日：2021-10-12
IPC分类号： 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分类号： 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
摘要： 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.
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公开(公告)号：US20230391464A1
公开(公告)日：2023-12-07
申请号：US18449145
申请日：2023-08-14
发明人： Keith David Weaver , Michael Pujol , Andrew Jordan Birkenheuer , Nicholas Plagianos , Karl Burge , Thomas Mast
CPC分类号： B64D33/08 , B64C27/12 , F01P1/06 , F01P11/10 , F16H57/0416
摘要： 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.
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公开(公告)号：US11829161B2
公开(公告)日：2023-11-28
申请号：US17603180
申请日：2020-04-10
IPC分类号： 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分类号： 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
摘要： 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.
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公开(公告)号：US20230348051A1
公开(公告)日：2023-11-02
申请号：US18212032
申请日：2023-06-20
发明人： Yann Lavallee , Scott D. Poster
CPC分类号： B64C27/56 , B64C27/12 , B64C27/82 , B64C13/044
摘要： Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.
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