公开(公告)号：US20220363401A1

公开(公告)日：2022-11-17

申请号：US17319155

申请日：2021-05-13

申请人： BETA AIR, LLC

发明人： Herman Lucas Norbert Wiegman ,  Nathan William Joseph Wiegman ,  Lochie Ferrier ,  Riley Clinton Griffin

IPC分类号： B64D31/06 ,  B64C13/04 ,  B64D27/24 ,  B64C21/00

摘要： An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.

公开(公告)号：US20220204168A1

公开(公告)日：2022-06-30

申请号：US17549799

申请日：2021-12-13

申请人： LIEBHERR-AEROSPACE TOULOUSE SAS

发明人： Vincent BALOCCHI

IPC分类号： B64D13/08 ,  B64D15/04 ,  B64C21/00

摘要： The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.

公开(公告)号：US20210300537A1

公开(公告)日：2021-09-30

申请号：US16833630

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 ,  B64C27/26 ,  B64D33/04 ,  B64C15/14 ,  B64C21/00 ,  B64C27/30

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 trinary 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 and forward 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 bypass air combines with engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

公开(公告)号：US20210284352A1

公开(公告)日：2021-09-16

申请号：US17332085

申请日：2021-05-27

申请人： Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company

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

IPC分类号： B64D35/00 ,  B64C21/00 ,  B64D27/14 ,  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：US11059600B2

公开(公告)日：2021-07-13

申请号：US16221397

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：US10988239B2

公开(公告)日：2021-04-27

申请号：US15653557

申请日：2017-07-19

申请人： Ramot at Tel-Aviv University Ltd.

发明人： Avraham Seifert ,  Isaac Dayan ,  Tom Shtendel

IPC分类号： B64C21/00 ,  F15B21/12 ,  B64C21/02 ,  B64C21/08 ,  F15D1/12 ,  F15C1/00 ,  F15C1/14 ,  F15D1/00 ,  F15C1/08 ,  F15C1/22

摘要： An active separation control system, comprising a fluidic oscillatory actuator having an ejector member, an oscillator member, and a joining channel between said oscillator member and said ejector member, all mounted on at least one flexible member, said fluidic oscillatory actuator being mountable on a rotatable door of a vehicle such that said flexible member assumes a different shape when said door is closed than when said door is open, wherein said joining channel is also flexible to assume a shape of said flexible member.

公开(公告)号：US10858088B2

公开(公告)日：2020-12-08

申请号：US15689831

申请日：2017-08-29

申请人： David E. Shormann

发明人： David E. Shormann

IPC分类号： B64C3/14 ,  B64C21/10 ,  F04D29/18 ,  F04D29/24 ,  F01D9/04 ,  F03D1/06 ,  F03B17/06 ,  B64C11/18 ,  B64C21/00 ,  F01D5/14

摘要： An airfoil body may include a plurality of tubercles along a leading edge of the airfoil body and a plurality of crenulations along a trailing edge of the airfoil body, wherein at least one of a position, a size, and a shape of the plurality of tubercles and the plurality of crenulations varies in a non-periodic fashion. The non-periodic fashion may be according to a Fibonacci function and may mimic the configuration of a pectoral fin of a humpback whale. The tubercles and crenulations may be defined with respect to a pivot point. The spanwise profile, including the max chord trailing edge curvature, may closely follow divine spirals and related Fibonacci proportions. The spanwise chord thickness may vary in a nonlinear pattern. Related methods are also described.

公开(公告)号：US20200339269A1

公开(公告)日：2020-10-29

申请号：US16786894

申请日：2020-02-10

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  B64C39/02 ,  B64C21/00 ,  B64D33/02 ,  B64C9/38 ,  B64C15/00 ,  B64D27/10

摘要： An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

公开(公告)号：US10352171B2

公开(公告)日：2019-07-16

申请号：US16012315

申请日：2018-06-19

申请人： Alexander J. Shelman-Cohen

发明人： Alexander J. Shelman-Cohen

IPC分类号： B64C21/00 ,  F01D5/14 ,  F03D1/06 ,  B64C21/10 ,  B63B1/34 ,  B64C11/20 ,  C09K3/00 ,  F15D1/12 ,  F04D29/00

摘要： Airfoil and hydrofoils systems with structures having a surface texture defined by fractal geometries are described. Raised portions or fractal bumps can be included on the surfaces, forming a surface texture. The surface textures can be defined by two-dimensional fractal shapes, partial two-dimensional fractal shapes, non-contiguous fractal shapes, three-dimensional fractal objects, and partial three-dimensional fractal objects. The surfaces can include indents having fractal geometries. The indents can have varying depths and can be bordered by other indents, or bumps, or smooth portions of the airfoil or hydrofoil structure. The fractal surface textures can reduce vortices inherent from airfoil and hydrofoil structures. The roughness and distribution of the fractal surface textures reduce the vortices, improving laminar flow characteristics and at the same time reducing drag. The systems are passive and do not require applied power.

公开(公告)号：US20180339765A1

公开(公告)日：2018-11-29

申请号：US15606051

申请日：2017-05-26

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Alan H. Epstein ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC分类号： B64C23/02 ,  B64C21/00

摘要： A propulsion system for an aircraft comprises at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. An aircraft is also disclosed.