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公开(公告)号：US20250010987A1
公开(公告)日：2025-01-09
申请号：US18892293
申请日：2024-09-20
Applicant: Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company , The Boeing Company
Inventor： Michael J. Duffy , Oliver Daniel Ensslin , Emanuele Marano
Abstract: The present disclosure provides systems, apparatuses, and methods relating to a fan apparatus including a lift fan mounted in a duct and a cover for the lift fan. In some examples, a fan apparatus has a louvered cover including louvers having different chord lengths and/or different projection distances relative to one another when the louvers are in an intermediate (transitional) position. In some examples, a fan apparatus includes a louver actuation assembly configured to move louvers of the fan apparatus rotationally and translationally between open and closed positions. In some examples, a fan apparatus includes a fluid-actuated sealing assembly configured to form a seal between a sealing member and a cover, such as a louvered cover.
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公开(公告)号：US12129024B2
公开(公告)日：2024-10-29
申请号：US17555299
申请日：2021-12-17
Applicant: Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company , The Boeing Company
Inventor： Michael J. Duffy , Oliver Daniel Ensslin , Emanuele Marano
CPC classification number: B64C29/0025 , B64C3/38 , B64C21/02 , F02K1/002
Abstract: The present disclosure provides systems, apparatuses, and methods relating to a fan apparatus including a lift fan mounted in a duct and a cover for the lift fan. In some examples, a fan apparatus has a louvered cover including louvers having different chord lengths and/or different projection distances relative to one another when the louvers are in an intermediate (transitional) position. In some examples, a fan apparatus includes a louver actuation assembly configured to move louvers of the fan apparatus rotationally and translationally between open and closed positions. In some examples, a fan apparatus includes a fluid-actuated sealing assembly configured to form a seal between a sealing member and a cover, such as a louvered cover.
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公开(公告)号：US20220194575A1
公开(公告)日：2022-06-23
申请号：US17555299
申请日：2021-12-17
Applicant: Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company , The Boeing Company
Inventor： Michael J. Duffy , Oliver Daniel Ensslin , Emanuele Marano
Abstract: The present disclosure provides systems, apparatuses, and methods relating to a fan apparatus including a lift fan mounted in a duct and a cover for the lift fan. In some examples, a fan apparatus has a louvered cover including louvers having different chord lengths and/or different projection distances relative to one another when the louvers are in an intermediate (transitional) position. In some examples, a fan apparatus includes a louver actuation assembly configured to move louvers of the fan apparatus rotationally and translationally between open and closed positions. In some examples, a fan apparatus includes a fluid-actuated sealing assembly configured to form a seal between a sealing member and a cover, such as a louvered cover.
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公开(公告)号：US12134461B2
公开(公告)日：2024-11-05
申请号：US16224029
申请日：2018-12-18
Applicant: The Boeing Company
Inventor： Michael J. Duffy , Naveed Moayyed Hussain , Matthew Aaron Novick , John Jian Dong
Abstract: Apparatus for controlling multi-rotor vehicle vibrations and related methods are disclosed herein. An example apparatus includes a vibration level detector to determine a vibration level of a frame of a vehicle based on data received from a sensor of the vehicle, the vehicle including a rotor. The apparatus includes a rotor operation analyzer to determine an operational parameter of the rotor based on the vibration level. The apparatus includes a communicator to transmit an instruction including the operational parameter to a controller of the rotor.
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公开(公告)号：US11027836B2
公开(公告)日：2021-06-08
申请号：US16035245
申请日：2018-07-13
Applicant: The Boeing Company
Inventor： Roger W. Lacy , Michael J. Duffy , David H. Mason
Abstract: A rotorcraft has a frame and a plurality of rotors connected to the frame. The frame has a roll axis and a pitch axis. Each of the rotors includes a rotor shaft. The rotor shaft of each of the rotors is canted with respect to at least one of the roll axis and the pitch axis. The rotor shaft of each of the rotors may be canted between 3 and 15 degrees. Each of the rotors may be a co-axial co-rotating rotor. The rotors may be oriented in opposing pairs across the frame. Both rotors in each opposing pair rotate in the same direction. The rotorcraft may include at least two additional rotors, each having a forward cant. Each of the additional rotors may be a co-axial contra-rotating rotor.
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Patent Agency Ranking
公开(公告)号：US20160123182A1
公开(公告)日：2016-05-05
申请号：US14531826
申请日：2014-11-03
Applicant: The Boeing Company
Inventor： Anthony Samaritano , Daniel I. Newman , Michael J. Duffy
CPC classification number: B64C39/026 , B64C27/08 , B64C27/20 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2211/00
Abstract: Disclosed herein is one embodiment of a thrust system that includes at least one modular thrust unit and at least one control module. The at least one modular thrust unit includes a base that is made from structural members that are inter-connectable in a plurality of different structural configurations. The at least one modular thrust unit further includes at least one thrust generator coupleable to the base in a thrust configuration and at least one power source operable to deliver power to the at least one thrust generator. The at least one control module is coupleable to the at least one modular thrust unit and operable to control at least one of the at least one thrust generator and the at least one power source.
Abstract translation: 本文公开了一种推力系统的一个实施例，其包括至少一个模块推力单元和至少一个控制模块。 所述至少一个模块推力单元包括由能够以多个不同结构构造相互连接的结构构件制成的基座。 所述至少一个模块化推力单元还包括至少一个推力发生器，所述至少一个推力发生器以推力构造联接到所述基座，并且至少一个动力源可操作以将动力输送到所述至少一个推力发生器。 所述至少一个控制模块可耦合到所述至少一个模块推力单元并且可操作以控制所述至少一个推力发生器和所述至少一个动力源中的至少一个。
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公开(公告)号：US11673657B2
公开(公告)日：2023-06-13
申请号：US16428668
申请日：2019-05-31
Applicant: The Boeing Company
Inventor： Michael J. Duffy , Joshua B. Jarvis , Roger W. Lacy , David M. Neely , Eric J. Schulze
Abstract: Multi-rotor rotorcraft comprise a fuselage, and at least four rotor assemblies operatively supported by and spaced-around the fuselage. Each of the at least four rotor assemblies defines a spin volume and a spin diameter. Some multi-rotor rotorcraft further comprise at least one rotor guard that is fixed relative to the fuselage, that borders the spin volume of at least one of the at least four rotor assemblies, and that is configured to provide a visual indication of the spin volume of the at least one of the at least four rotor assemblies. Various configurations of rotor guards are disclosed.
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公开(公告)号：US11332235B2
公开(公告)日：2022-05-17
申请号：US16036516
申请日：2018-07-16
Applicant: The Boeing Company
Inventor： Andrew Leung , Michael J. Duffy , Mary E. Beckman , John Jeffrey Mattero , Rene Woszidlo
Abstract: Active fluid control systems and related methods are disclosed. A disclosed example active fluid control system includes a plurality of plenums coupled together to define a fluid flow passageway, and a plurality of fluidic actuators coupled to outer surfaces of respective ones of the plenums. The fluidic actuators define actuator inlets and actuator outlets. The fluid flow passageway defined by the plenums to fluidly couple the fluidic actuators and a pressurized fluid supply source. The plenums are configured to couple to an aircraft structure supporting an aerodynamic surface to enable the actuator outlets to be mounted to the aerodynamic surface. The fluidic actuators are configured to provide the pressurized fluid to the aerodynamic surface to modify an aerodynamic characteristic of the aerodynamic surface.
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公开(公告)号：US10787245B2
公开(公告)日：2020-09-29
申请号：US15169879
申请日：2016-06-01
Applicant: The Boeing Company
Inventor： Michael J. Duffy , Rene Woszidlo
IPC: B64C21/04 , B64C21/08 , B64C21/06 , B62D35/00 , B63B1/32 , B63G8/00 , B64C5/02 , B64C9/14 , B64C9/00
Abstract: A method and apparatus for controlling an airflow. The method draws air through a group of inlets. The group of inlets is located in a group of locations on the vehicle such that the group of inlets actively controls the airflow relative to an aircraft when drawing the air. The method compresses the air drawn by the group of inlets in a group of air compressor units located in an aircraft structure to form pressurized air. Further, the method sends the pressurized air through a group of exit ports in the aircraft structure. The pressurized air flowing out of the group of exit ports actively controls the airflow for an aircraft, enabling an improved performance of the aircraft.
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公开(公告)号：US10013885B2
公开(公告)日：2018-07-03
申请号：US15292609
申请日：2016-10-13
Applicant: The Boeing Company
Inventor： Michael J. Duffy , John J. Mattero
IPC: G08G5/00
CPC classification number: G08G5/0013 , G08G5/0021 , G08G5/0026 , G08G5/0052 , G08G5/006 , G08G5/0069 , G08G5/0082
Abstract: An aircraft deconfliction system including a registration system having an airspace database, a registered airspace, wherein registration details of the registered airspace are logged in the airspace database, and an aircraft assigned to the registered airspace, the aircraft including a flight control system, a guidance computer controlling the flight control system based on a pilot input, and an override unit in communication with the guidance computer, wherein the override unit overrides the pilot input when the aircraft breaches the registered airspace.
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