公开(公告)号：US20240182179A1

公开(公告)日：2024-06-06

申请号：US18218999

申请日：2023-07-06

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

摘要： A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

公开(公告)号：US11279479B2

公开(公告)日：2022-03-22

申请号：US16833638

申请日：2020-03-29

申请人： Textron Innovations Inc.

发明人： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Matthew Edward Louis

IPC分类号： B64C29/00 ,  B64D27/16 ,  B64C11/48 ,  B64D35/06 ,  B64C11/00 ,  B64D35/02 ,  B64C27/22 ,  B64D33/04 ,  B64D35/04 ,  B64C3/10 ,  B64C19/00 ,  B64C27/26 ,  B64C27/30 ,  B64C9/20 ,  B64C21/08 ,  B64C27/78 ,  B64C21/04 ,  B64C39/10 ,  B64C9/18 ,  B64C15/02 ,  B64C15/14 ,  B64C21/00

摘要： An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.

公开(公告)号：US11174007B2

公开(公告)日：2021-11-16

申请号：US16197668

申请日：2018-11-21

申请人： SUBARU CORPORATION

发明人： Maki Kikuchi ,  Hiroki Kato

IPC分类号： B64C23/00 ,  B64C21/00 ,  F15D1/00

摘要： A flow control apparatus includes a plasma actuator, a storage device, and a control circuit. The plasma actuator causes discharge in a discharge area by applying an alternating-current (AC) voltage between electrodes to form an induced flow of gas. The electrodes are shifted relatively to each other with a dielectric disposed between them. The storage device stores a changing condition of an AC voltage waveform for changing a gas flow state formed in a flow control area of gas from a first state to a second state by adding the induced flow of gas. The control circuit refers to the changing condition of the AC voltage waveform and control the AC voltage waveform based on the changing condition of the AC voltage waveform, in a case of changing the gas flow state formed in the gas flow control area from the first flow state to the second flow state.

公开(公告)号：US11142330B2

公开(公告)日：2021-10-12

申请号：US16117305

申请日：2018-08-30

申请人： Aurora Flight Sciences Corporation

发明人： Gary Richard Papas ,  Neil Titchener ,  Brian M. Yutko ,  Clint Church ,  Jian Long Tian

IPC分类号： B64D35/00 ,  B64D27/14 ,  B64C21/00 ,  B64D33/04 ,  F16H1/22 ,  F16H37/06 ,  B64C1/16 ,  B64C21/06 ,  F02K3/062

摘要： An aircraft with an integrated boundary layer ingesting propulsion having a mechanically-distributed propulsion system. The mechanically-distributed propulsion system may include an engine to generate a mechanical drive power, a drive shaft, a direction-reversing transmission, and a propulsor fan. The drive shaft may be operatively coupled to the engine to receive the mechanical drive power. The direction-reversing transmission may have a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power, which is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft. The propulsor fan may be coupled to the second rotating shaft to convert the mechanical drive power into thrust.

公开(公告)号：US11077939B1

公开(公告)日：2021-08-03

申请号：US16833619

申请日：2020-03-29

申请人： Textron Innovations Inc.

发明人： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Steven Ray Ivans ,  Matthew Edward Louis

IPC分类号： B64C29/00 ,  B64C27/22 ,  B64D33/04 ,  B64C19/00 ,  B64C3/10 ,  B64C27/30 ,  B64C27/26 ,  B64C15/14 ,  B64C21/00

摘要： An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a binary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a plurality of ducted fans in a tandem lateral orientation. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

公开(公告)号：US10974812B1

公开(公告)日：2021-04-13

申请号：US16166230

申请日：2018-10-22

申请人： Troy S Prince ,  Richard Kolacinski ,  Mehul Patel

发明人： Troy S Prince ,  Richard Kolacinski ,  Mehul Patel

IPC分类号： B64C5/12 ,  F42B15/01 ,  B64C23/06 ,  F42B10/64 ,  G05D1/00 ,  F41G7/00 ,  B64C21/00 ,  G05D1/08 ,  F42B10/62 ,  F42B10/02 ,  F42B10/14 ,  F42B10/60 ,  F42B10/00

摘要： The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

公开(公告)号：US10919636B2

公开(公告)日：2021-02-16

申请号：US16221362

申请日：2018-12-14

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64C9/38 ,  B64D33/04 ,  B64C39/02 ,  B64C15/14 ,  B64C15/00 ,  B64C21/00 ,  B64D27/10 ,  B64C21/04 ,  F02K1/36 ,  F02K1/00 ,  F02C3/04 ,  F02C6/04 ,  B64C23/00 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02

摘要： A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

公开(公告)号：US20200339257A1

公开(公告)日：2020-10-29

申请号：US16675104

申请日：2019-11-05

申请人： Jetoptera, Inc.

发明人： Andrei Evulet

IPC分类号： B64C29/04 ,  B64C39/12 ,  B64D27/20 ,  B64C11/00 ,  B64C39/02 ,  B64D33/02 ,  B64C29/02 ,  B64C15/00 ,  B64D33/04 ,  B64D27/10 ,  B64C9/38 ,  B64D29/02 ,  B64C21/00

摘要： A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

公开(公告)号：US10737771B2

公开(公告)日：2020-08-11

申请号：US15819560

申请日：2017-11-21

申请人： Airbus Operations GmbH

发明人： Dirk Elbracht ,  Bruno Stefes

IPC分类号： B64C23/06 ,  B64C21/08 ,  B64C3/52 ,  B64C9/16 ,  B64C21/00

摘要： An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.

公开(公告)号：US10717519B2

公开(公告)日：2020-07-21

申请号：US16134644

申请日：2018-09-18

申请人： THE BOEING COMPANY

发明人： Matthew T. Lakebrink ,  Mortaza Mani

IPC分类号： B64C21/00 ,  B64C21/02 ,  B64C21/04

摘要： Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system is disclosed herein. In one example, the active flow control system includes an airframe and a plurality of fluidic oscillators. The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators is mounted about a curvature of the airframe. Each fluidic oscillator includes a body and an integral nozzle coupled to the body. The body has an inflow portion and a narrow nozzle inlet formed opposite the inflow portion. The integral nozzle is coupled to the body by the narrow nozzle inlet. The narrow nozzle inlet forms a single fluid flow path from the inflow portion to the narrow nozzle inlet.