公开(公告)号：US12103674B2

公开(公告)日：2024-10-01

申请号：US18122502

申请日：2023-03-16

申请人： Kitty Hawk Corporation

发明人： Pranay Sinha ,  Damon Vander Lind

IPC分类号： B64C13/00 ,  B60L50/64 ,  B60L53/00 ,  B64C13/48 ,  B64C27/82 ,  B64C29/00 ,  B64C39/12 ,  B64D27/02 ,  B64D27/24 ,  B64D27/40 ,  B64D31/06 ,  G05D1/00

CPC分类号： B64C29/0033 ,  B60L50/64 ,  B60L53/00 ,  B64C13/48 ,  B64C27/82 ,  B64C39/12 ,  B64D27/02 ,  B64D27/24 ,  B64D27/40 ,  B64D31/06 ,  G05D1/101 ,  B60L2200/10 ,  B64C2027/8209 ,  B64D27/026 ,  B64D27/402

摘要： A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.

公开(公告)号：US09248908B1

公开(公告)日：2016-02-02

申请号：US13916283

申请日：2013-06-12

申请人： The Boeing Company

发明人： Leo J. Luyks

IPC分类号： B64C27/00 ,  B64C27/12 ,  B64C27/52

CPC分类号： B64C27/12 ,  B64C27/04 ,  B64C27/52 ,  B64C27/82 ,  B64C2027/8209 ,  B64D27/24 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

摘要： A helicopter has a propulsion system that includes a diesel engine driven electric generator, battery storage, power inverters for converting AC current to DC current and converting DC current to AC current, and an electric motor powered main rotor and an electric motor powered tail rotor. The propulsion system is integrated with electric controls of the main rotor electric motor and the tail rotor electric motor to provide additional system efficiencies. The design of the helicopter allows a single engine helicopter to be just as safe as a twin engine design helicopter while consuming less fuel. The helicopter design also includes a main rotor tilt system which tilts the rotation axis of the main rotor forward during high-speed flight to improve the aerodynamic efficiency of the helicopter airframe and rotary wing.

摘要翻译： 直升机具有推进系统，其包括柴油发动机驱动的发电机，蓄电池存储器，用于将交流电流转换为直流电流并将直流电流转换成交流电的电力逆变器，以及由电动机供电的主转子和电动马达尾转子。 推进系统与主转子电动机和尾转子电动机的电气控制集成，以提供额外的系统效率。 直升机的设计允许单引擎直升机与双引擎设计直升机一样安全，同时消耗更少的燃料。 直升机设计还包括主转子倾斜系统，其在高速飞行期间向前倾斜主转子的旋转轴线，以提高直升机机身和旋翼的空气动力学效率。

公开(公告)号：US08931732B2

公开(公告)日：2015-01-13

申请号：US12018217

申请日：2008-01-23

申请人： Jayant Sirohi ,  Timothy Fred Lauder ,  Mark R. Alber ,  Daniel Bazzani

发明人： Jayant Sirohi ,  Timothy Fred Lauder ,  Mark R. Alber ,  Daniel Bazzani

IPC分类号： B64C27/00 ,  B64D27/24 ,  B64C27/22 ,  B64C27/68 ,  B64C29/00 ,  B64C39/02

CPC分类号： B64D27/24 ,  B64C27/22 ,  B64C27/68 ,  B64C29/00 ,  B64C39/024 ,  B64C2027/8209 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/108 ,  Y02T50/44 ,  Y02T50/64

摘要： A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation.

摘要翻译： 具有沿着旋转轴安装的电动马达的旋翼飞机，以围绕旋转轴线驱动转子系统。

公开(公告)号：US20130264412A1

公开(公告)日：2013-10-10

申请号：US13765798

申请日：2013-02-13

申请人： EUROCOPTER

发明人： Nadine Dyrla

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C2027/8209 ,  F15B2211/40507 ,  F15B2211/415 ,  F15B2211/41572

摘要： A rotary wing aircraft (1) provided with a main lift rotor (2), a tail rotor (5), and a power plant (4) driving a main gearbox (3) that co-operates with said main rotor (2), said tail rotor (5) being provided with a plurality of blades (10) of variable pitch (I) and with a pitch modification device (20), and said aircraft (1) having control means (30) for controlling said pitch modification device (20). The aircraft (1) includes an electric motor (9) for rotating said tail rotor (5) and regulator means (TRCU) connected to the control means (30) and also to the electric motor (9) and to the pitch modification device (20). The regulator means (TRCU) generate a first setpoint concerning pitch that is transmitted to the pitch modification device (20), and a second setpoint for controlling a motor parameter that is transmitted to the electric motor (9).

摘要翻译： 设有主提升转子（2），尾转子（5）和驱动与所述主转子（2）配合的主变速箱（3）的动力装置（4）的旋翼机（1） 所述尾部转子（5）设置有多个可变节距（I）的叶片（10）和间距改变装置（20），并且所述飞行器（1）具有控制装置（30），用于控制所述桨距修正装置 （20）。 飞机（1）包括用于使所述尾部转子（5）旋转的电动机（9）和与控制装置（30）连接的调节装置（TRCU），并且还连接到电动机（9）和螺距改型装置 20）。 调节器装置（TRCU）产生关于传播给桨距修正装置（20）的桨距的第一设定点，以及用于控制发送到电动机（9）的电机参数的第二设定点。

公开(公告)号：US11772807B2

公开(公告)日：2023-10-03

申请号：US16905657

申请日：2020-06-18

申请人： Textron Innovations Inc.

发明人： Chen Kuang ,  Marc Bustamante ,  Thuvaragan Senthilnathan ,  Marc Ouellet ,  Guillaume Biron

IPC分类号： B64D31/00 ,  B64D31/04 ,  B64C27/82 ,  B64D27/24 ,  H02P5/50 ,  H02P9/06 ,  H02P9/08 ,  H02P5/46 ,  G05B9/03 ,  H02P101/30

CPC分类号： B64D31/04 ,  B64C27/82 ,  B64D27/24 ,  G05B9/03 ,  H02P5/46 ,  H02P5/50 ,  H02P9/06 ,  H02P9/08 ,  B64C2027/8209 ,  B64C2027/8227 ,  B64D2221/00 ,  H02P2101/30

摘要： An architecture for an electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the one or more generators, each motor of the plurality of motors connected to a blade to provide thrust, a first and a second power bus electrically connected between the one or more generators and the first and the second plurality of motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second plurality of motors, each of the first and second controllers serving as a primary and a backup controller, and dual channels in communication between pilot input sensors and the first and the second controllers, and the dual channels including an additional channel to provide redundant communication to the first and second controllers.

公开(公告)号：US11772785B2

公开(公告)日：2023-10-03

申请号：US17108592

申请日：2020-12-01

申请人： Textron Innovations Inc.

发明人： Marc Ouellet ,  Guillaume Biron ,  Alexis Dugré ,  Thuvaragan Senthilnathan

IPC分类号： B64C27/82 ,  B64C27/00

CPC分类号： B64C27/00 ,  B64C2027/8209 ,  B64C2027/8227 ,  B64C2027/8254 ,  B64C2027/8272

摘要： A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

公开(公告)号：US09174728B2

公开(公告)日：2015-11-03

申请号：US13719839

申请日：2012-12-19

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Andree Altmikus ,  Manuel Kessler

IPC分类号： B64C27/06 ,  B64C27/12 ,  B64C27/82 ,  B64C27/72 ,  B64C27/78 ,  B64C27/20 ,  H02K7/116 ,  H02K7/14 ,  H02K16/00

CPC分类号： B64C27/12 ,  B64C27/82 ,  B64C2027/8209 ,  B64C2027/8254 ,  H02K7/116 ,  H02K7/14 ,  H02K16/00

摘要： The invention is related to an electrical powered tail rotor (1) of a helicopter comprising a housing (2) around the tail rotor (1), and at least one permanent magnet energized synchronous motor with a stator (6, 7) with an increased number of poles (9). Said at least one synchronous motor is integrated as a torus (8) around an opening of the housing (2) encompassing the tail rotor (1). Blades (4) of the tail rotor (1) are fixed to at least one rotating component (10, 11) of said at least one synchronous motor. Supply means provide for electric energy to said at least one synchronous motor. Blade pitch control means are provided at the torus (8).

摘要翻译： 本发明涉及一种包括围绕尾部转子（1）的壳体（2）的直升机的电动尾部转子（1），以及具有定子（6,7）的至少一个永磁同步电动机，其具有增加的 极数（9）。 所述至少一个同步电动机围绕围绕尾部转子（1）的壳体（2）的开口围绕圆环（8）集成。 尾部转子（1）的叶片（4）固定在所述至少一个同步电动机的至少一个旋转部件（10,11）上。 供应装置为所述至少一个同步电动机提供电能。 叶片俯仰控制装置设置在环面（8）处。

公开(公告)号：US20130170985A1

公开(公告)日：2013-07-04

申请号：US13719839

申请日：2012-12-19

申请人： EUROCOPTER DEUTSCHLAND GMBH

发明人： Andree Altmikus ,  Manuel Kessler

IPC分类号： B64C27/12

CPC分类号： B64C27/12 ,  B64C27/82 ,  B64C2027/8209 ,  B64C2027/8254 ,  H02K7/116 ,  H02K7/14 ,  H02K16/00

摘要： The invention is related to an electrical powered tail rotor (1) of a helicopter comprising a housing (2) around the tail rotor (1), and at least one permanent magnet energized synchronous motor with a stator (6, 7) with an increased number of poles (9). Said at least one synchronous motor is integrated as a torus (8) around an opening of the housing (2) encompassing the tail rotor (1). Blades (4) of the tail rotor (1) are fixed to at least one rotating component (10, 11) of said at least one synchronous motor. Supply means provide for electric energy to said at least one synchronous motor. Blade pitch control means are provided at the torus (8).

摘要翻译： 本发明涉及一种包括围绕尾部转子（1）的壳体（2）的直升机的电动尾部转子（1），以及至少一个具有定子（6,7）的永磁同步电动机，其具有增加的 极数（9）。 所述至少一个同步电动机围绕围绕尾部转子（1）的壳体（2）的开口围绕圆环（8）集成。 尾部转子（1）的叶片（4）固定在所述至少一个同步电动机的至少一个旋转部件（10,11）上。 供应装置为所述至少一个同步电动机提供电能。 叶片俯仰控制装置设置在环面（8）处。

公开(公告)号：US20100123039A1

公开(公告)日：2010-05-20

申请号：US12317313

申请日：2008-12-22

申请人： Andreas Buhl ,  Michael Koros

发明人： Andreas Buhl ,  Michael Koros

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C2027/8209

摘要： The present invention relates to a tail rotor system for an aircraft, in particular for a helicopter, with a multi-blade tail rotor with fixed blade angle of attack and to a method for controlling a tail rotor system for an aircraft, in particular for a helicopter.

摘要翻译： 本发明涉及一种用于飞行器，特别是用于直升机的尾部转子系统，其具有固定叶片角度的多叶片尾部转子和用于控制用于飞行器的尾部转子系统的方法，特别是用于 直升机。

公开(公告)号：US11787537B2

公开(公告)日：2023-10-17

申请号：US17380687

申请日：2021-07-20

申请人： Kitty Hawk Corporation

发明人： Pranay Sinha ,  Damon Vander Lind

IPC分类号： B64C29/00 ,  G05D1/10 ,  B64C13/48 ,  B64C39/12 ,  B64D27/24 ,  B64D27/26 ,  B60L53/00 ,  B60L50/64 ,  B64C27/82 ,  B64D27/02 ,  B64D31/06

CPC分类号： B64C29/0033 ,  B60L50/64 ,  B60L53/00 ,  B64C13/48 ,  B64C27/82 ,  B64C39/12 ,  B64D27/02 ,  B64D27/24 ,  B64D27/26 ,  B64D31/06 ,  G05D1/101 ,  B60L2200/10 ,  B64C2027/8209 ,  B64D2027/026 ,  B64D2027/264

摘要： A hybrid power system includes a first power source that includes an internal combustion engine, a second power source that includes a battery, and a power controller. The hybrid power system is included in a vertical takeoff and landing (VTOL) vehicle that flies in a transitional mode between a hovering mode and a forward flight mode. The power controller selects one or more of the first power source and the second power source to power a rotor included in the VTOL vehicle, including by: during a landing, the power controller determines when to have the second power source provide power to the rotor, in order to supplement power provided to the rotor by the first power source, based at least in part on one or more flight state variables associated with a flight computer.