公开(公告)号：US20240391584A1

公开(公告)日：2024-11-28

申请号：US18669673

申请日：2024-05-21

Applicant: University of Florida Research Foundation, Inc.

Inventor： Subrata Roy ,  Alexander Lilley ,  Miguel Visbal

IPC: B64C23/00 ,  H05H1/24

Abstract: The present disclosure presents systems and methods for dynamic stall control in aircrafts. One such method involves positioning one or more counter-flow point embedded electrode plasma actuator devices on an edge of an airfoil of an aircraft, wherein a counter-flow point embedded electrode plasma actuator device comprises at least a first electrode that is unexposed and embedded under a surface of the airfoil and a second electrode positioned on or in a top surface of the airfoil; and/or activating the one or more counter-flow point embedded electrode plasma actuator devices during a flight of the aircraft, wherein a dynamic stall angle of a pitching airfoil is increased during the flight of the aircraft by forcing plasma over the edge of the pitching airfoil.

公开(公告)号：US20240262517A1

公开(公告)日：2024-08-08

申请号：US18586428

申请日：2024-02-24

Applicant: Joby Aero, Inc.

Inventor： JoeBen Bevirt ,  Gregor Veble Mikic ,  Joey Milia ,  Rob Thodal ,  Vishnu Vithala

IPC: B64D27/24 ,  B64C1/38 ,  B64C21/08 ,  B64C23/00 ,  B64C27/32

CPC classification number: B64D27/24 ,  B64C1/38 ,  B64C23/005 ,  B64C21/08 ,  B64C27/32 ,  B64C2230/04

Abstract: An aircraft propulsion system with an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

公开(公告)号：US11933334B2

公开(公告)日：2024-03-19

申请号：US18320154

申请日：2023-05-18

Applicant: Deep Science, LLC

Inventor： Alexander J. Smits ,  Ivan Marusic ,  David Wine ,  Brian Holloway

IPC: F15D1/12 ,  B64C23/00 ,  F15D1/00 ,  F15D1/06 ,  B62D35/00 ,  B64C9/02 ,  B64C9/04 ,  B64C21/00

CPC classification number: F15D1/12 ,  B64C23/005 ,  F15D1/007 ,  F15D1/065 ,  B62D35/00 ,  B64C9/02 ,  B64C9/04 ,  B64C21/00 ,  B64C2230/12 ,  F15D1/008

Abstract: Systems and methods are described herein to implement transverse momentum injection at low frequencies to directly modify large-scale eddies in a turbulent boundary layer on a surface of an object. A set of transverse momentum injection actuators may be positioned on the surface of the object to affect large-scale eddies in the turbulent boundary layer. The system may include a controller to selectively actuate the transverse momentum injection actuators with an actuation pattern to affect the large-scale eddies to modify the drag, fluid mixing, heat transfer, and/or other interactions of the fluid flow with the surface. In various embodiments, the transverse momentum injection actuators may be operated at frequencies less than 10,000 Hertz.

公开(公告)号：US11905983B2

公开(公告)日：2024-02-20

申请号：US17154763

申请日：2021-01-21

Applicant: Deep Science, LLC

Inventor： Brian C. Holloway ,  David William Wine

IPC: F15D1/00 ,  B64C23/00 ,  H05H1/24 ,  B64C21/10 ,  F15D1/12

CPC classification number: F15D1/0075 ,  B64C23/005 ,  H05H1/2406 ,  B64C21/10 ,  B64C2230/12 ,  F15D1/007 ,  F15D1/12 ,  Y02T50/10

Abstract: A fluid control system includes a dielectric-barrier discharge (DBD) device, and processing circuitry. The processing circuitry is configured to obtain a streamwise length scale of a fluid flowing over a surface. The processing circuitry is also configured to obtain a convective time scale of the fluid flowing over the surface. The processing circuitry is also configured to operate the DBD device, based on the streamwise length scale and the convective time scale, to adjust a flow property of the fluid.

公开(公告)号：US11834186B2

公开(公告)日：2023-12-05

申请号：US17006965

申请日：2020-08-31

Applicant: General Electric Company

Inventor： Brendan Michael Freely ,  Kurt David Murrow ,  Michael James McMahon ,  Andrew Breeze-Stringfellow

IPC: B64D27/02 ,  B64D27/24 ,  B64C23/00 ,  B64D31/12 ,  F04D25/16

CPC classification number: B64D27/02 ,  B64C23/00 ,  B64D27/24 ,  B64D31/12 ,  F04D25/166

Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.

公开(公告)号：US11794881B2

公开(公告)日：2023-10-24

申请号：US17879128

申请日：2022-08-02

Applicant: United States of America, as represented by the Secretary of the Navy

Inventor： Stuart H. Rubin

IPC: B63B1/36 ,  B64C23/00 ,  B63B1/34

CPC classification number: B64C23/005 ,  B63B1/34 ,  B63B1/36

Abstract: A maritime vehicle includes a surface for contacting a fluid medium through which the maritime vehicle is propelled. The maritime vehicle also includes an array of transducers and a controller. The transducers in the array are arranged across the maritime vehicle's surface for generating pressure waves in the fluid medium. Each transducer in the array is arranged to vibrate for generating a respective pressure wave, which propagates away from the surface in the fluid medium. The controller vibrates the transducers in the array so that the pressure waves control the drag of the maritime vehicle from the fluid medium.

公开(公告)号：US11718388B2

公开(公告)日：2023-08-08

申请号：US17508638

申请日：2021-10-22

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA ,  TOHOKU UNIVERSITY

Inventor： Hidemasa Yasuda ,  Akio Ochi ,  Kenji Hayama ,  Tomoka Tsujiuchi ,  Kazuyuki Nakakita ,  Taku Nonomura ,  Atsushi Komuro ,  Keisuke Takashima

IPC: B64C23/00 ,  B64C23/04 ,  B64C27/04

CPC classification number: B64C23/04 ,  B64C23/005 ,  B64C27/04 ,  B64C2230/12 ,  B64C2230/28

Abstract: A flow control method is a flow control method of controlling flow around a blade of a rotary wing, a plasma actuator being disposed at the blade. The flow control method includes: determining a characteristic frequency ratio that is a characteristic value among frequency ratios, each of the frequency ratios being a ratio between an actuator driving frequency and an angle of attack changing frequency, the actuator driving frequency being a frequency of an applied voltage applied to the plasma actuator, the angle of attack changing frequency being a frequency at which an angle of attack of the blade changes in accordance with a rotation angle of the blade; setting the actuator driving frequency such that the frequency ratio becomes the characteristic frequency ratio; and applying a voltage of the set actuator driving frequency to the plasma actuator to control the flow around the blade.

公开(公告)号：US20230202646A1

公开(公告)日：2023-06-29

申请号：US18111192

申请日：2023-02-17

Applicant: DELOS AEROSPACE LLC

Inventor： Steven SULLIVAN

IPC: B64C23/00 ,  B64C21/10

CPC classification number: B64C23/005 ,  B64C21/10 ,  F05D2270/172 ,  B64C2230/26 ,  B64C2230/12 ,  Y02T50/10

Abstract: Disclosed are methods and apparatuses for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface geometries promotes vortex-mixing of high and low flow fluids. The methods and apparatuses can be combined with various drag reduction techniques, such as the use of riblets of various types and/or compliant surfaces (passive and active). Such combinations form unique structures for various fluid dynamic control applications to suppress transiently growing forms of boundary layer disturbances in a manner that significantly improves performance and has improved control dynamics.

公开(公告)号：US11655055B2

公开(公告)日：2023-05-23

申请号：US17053066

申请日：2019-02-19

Applicant: Vikrant Sharma

Inventor： Vikrant Sharma

IPC: B64G1/00 ,  B64G1/14 ,  B64C23/00 ,  B64G1/40 ,  B64G1/64

CPC classification number: B64G1/002 ,  B64G1/14 ,  B64C23/005 ,  B64G1/402 ,  B64G1/641

Abstract: The embodiments herein disclose a retrofitted or in built or add-on kit/device for airborne vehicles to reduce the aerodynamic drag thereby increasing performance parameters/metrics of the vehicles. Drag reduction is achieved through shape/contour optimization, and/or heat/energy/fluid addition to the flow in neighbourhood of the vehicle. The device is designed with an external surface to offers the minimum drag. The device is configured to deposit heat/energy/fluid in neighbourhood of flying vehicle in several ways by generating/injecting hot gases in neighbourhood of vehicle for energy/heat addition, thereby causing maximum drag reduction. Heat/energy/fluid is added through the nozzles in the add-on kit/device.

公开(公告)号：US11639667B2

公开(公告)日：2023-05-02

申请号：US16192718

申请日：2018-11-15

Applicant: SUBARU CORPORATION

Inventor： Hiroki Kato ,  Maki Kikuchi

IPC: F01D11/10 ,  B64C23/00 ,  F01D11/20 ,  F15D1/00 ,  B64C11/00 ,  B64C27/82 ,  B64C29/00

Abstract: A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.