公开(公告)号：US12162599B2

公开(公告)日：2024-12-10

申请号：US17969616

申请日：2022-10-19

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: B64C29/04 ,  B64C9/38 ,  B64C11/00 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/12 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64U10/20 ,  B64U50/12 ,  B64U70/80 ,  B64U20/20 ,  B64U50/14 ,  B64U101/64

Abstract: 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：US20240246661A1

公开(公告)日：2024-07-25

申请号：US18158102

申请日：2023-01-23

Applicant: The Boeing Company

Inventor： Adam Nadel ,  Nikola Baltadjiev ,  Anthony Prete ,  Brian Whipple

IPC: B64C15/00 ,  B64C11/00 ,  B64C29/00

CPC classification number: B64C15/00 ,  B64C11/001 ,  B64C29/0033

Abstract: Flow control ducted fans are disclosed. A disclosed example flow control apparatus for use with an aircraft includes a duct defining an inner cavity with a primary flow path, a fan disposed in the inner cavity, an aperture on an exterior surface of the duct and upstream from the fan, the aperture fluidly coupled to the inner cavity to define a secondary flow path, and a door to control a degree to which the aperture is opened.

公开(公告)号：US20240228053A1

公开(公告)日：2024-07-11

申请号：US18235311

申请日：2023-08-17

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: 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 classification number: 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

Abstract: 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：US11866193B2

公开(公告)日：2024-01-09

申请号：US16945800

申请日：2020-07-31

Applicant: Volo Alto, LLC

Inventor： Nicholas R. Guida

IPC: B64D45/00 ,  B64C15/00 ,  G05D1/10 ,  G07C5/00 ,  G07C5/08 ,  B64D47/08

CPC classification number: B64D45/00 ,  B64C15/00 ,  B64D47/08 ,  G05D1/101 ,  G07C5/008 ,  G07C5/085 ,  B64D2045/0085

Abstract: A flight augmentation system with optical sensors to capture information from aircraft instruments. The system may determine a status of the aircraft based on the captured information and provide guidance to an operator. The system may collect long term data and determine an operational history of a pilot or an aircraft. The system may provide instruction based on the data or provide to interested third parties.

公开(公告)号：US11803194B2

公开(公告)日：2023-10-31

申请号：US17963632

申请日：2022-10-11

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Wayne K. Schroeder

IPC: F42B10/66 ,  G05D1/08 ,  B63G8/16 ,  B63H25/46 ,  B64C15/00 ,  B64G1/26 ,  F42B19/01

CPC classification number: G05D1/08 ,  B63G8/16 ,  B63H25/46 ,  B64C15/00 ,  B64G1/26 ,  F42B10/661 ,  F42B19/01 ,  G05D1/0858

Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.

公开(公告)号：US20200331589A1

公开(公告)日：2020-10-22

申请号：US16389686

申请日：2019-04-19

Applicant: Darold B. Cummings

Inventor： Darold B. Cummings

IPC: B64C15/00 ,  B64D27/26 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D27/12 ,  B64D27/14 ,  B64C7/02

Abstract: An aircraft having a fuselage with a nose and a flat tail at opposite ends and a pair of wings extending therefrom. A pair of nacelles are detachably connected to the top of respective ones of the wings to be spaced from the fuselage to establish an air flow space therebetween, Each wing-mounted nacelle includes a plurality of fans, a corresponding plurality of electric motors to drive the fans, and dividers that separate the fans from one another. Each wing-mounted nacelle also includes a pair of rotatable air inlet slats at an air intake end and a pair of rotatable air exhaust flaps at an air exhaust end that are rotated relative to one another to control horizontal propulsive thrust, thrust vectoring and thrust reversing of the aircraft. A third nacelle is mounted on top of the flat tail of the fuselage between a pair of horizontal turbo generators.

公开(公告)号：US10704496B2

公开(公告)日：2020-07-07

申请号：US15601540

申请日：2017-05-22

Applicant: The Boeing Company

Inventor： Robert Michael Lee

IPC: F02K1/00 ,  F02K1/76 ,  B64D33/04 ,  F02K1/40 ,  B64C15/00 ,  B64C15/14 ,  B64C9/00 ,  B64C9/02 ,  B64C9/06 ,  B64C13/00 ,  B64C13/16 ,  B64C21/00 ,  B64C21/02 ,  B64C21/04 ,  B64C21/08 ,  B64C9/38 ,  B64C9/32

Abstract: Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

公开(公告)号：US10464668B2

公开(公告)日：2019-11-05

申请号：US15456450

申请日：2017-03-10

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

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

Abstract: 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：US10358229B2

公开(公告)日：2019-07-23

申请号：US15135040

申请日：2016-04-21

Applicant: ROLLS-ROYCE plc

Inventor： Matthew Moxon

IPC: B64D33/02 ,  B64C15/00 ,  B64C21/00 ,  B64D27/02 ,  B64C3/50 ,  B64C11/00 ,  B64D27/10 ,  B64D27/24 ,  B64D29/04 ,  B64D33/04

Abstract: An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode.

公开(公告)号：US20190118958A1

公开(公告)日：2019-04-25

申请号：US16221397

申请日：2018-12-14

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

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

Abstract: 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.