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    PNEUMATIC COLLAPSIBLE EJECTORS SUPPLY SYSTEM FOR AIRCRAFT PROPULSION
    3.
    发明专利
    PNEUMATIC COLLAPSIBLE EJECTORS SUPPLY SYSTEM FOR AIRCRAFT PROPULSION 未知

    公开(公告)号：AU2023316948A1

    公开(公告)日：2024-12-19

    申请号：AU2023316948

    申请日：2023-06-23

    Applicant: JETOPTERA INC

    Inventor： EVULET ANDREI

    IPC: B64C13/48 ,  B64C21/01 ,  B64C21/04 ,  B64D33/04

    Abstract: A propulsion system includes at least one conduit, the conduit configured to carry distribute motive fluid, the conduit further configured to collapse when not supplied with motive fluid from a compressor and inflate when supplied with motive fluid from a compressor, and at least one ejector in fluid communication with the at least one conduit, wherein the compressor supplies compressed air to the at least one ejector for producing thrust, and wherein the at least one ejector, when not in use, is retractable into a volume of an airfoil streamlining the outside of said airfoil.

    Vertical take off and landing aircraft with fluidic propulsion system
    4.
    发明专利
    Vertical take off and landing aircraft with fluidic propulsion system 未知

    公开(公告)号：AU2021278813A1

    公开(公告)日：2023-01-05

    申请号：AU2021278813

    申请日：2021-04-27

    Applicant: JETOPTERA INC ,  EVULET ANDREI

    Inventor： EVULET ANDREI

    IPC: B64C29/00 ,  B64C21/02 ,  B64C21/08 ,  B64C39/08

    Abstract: An aircraft includes a fuselage and a primary airfoil having a first upper surface. The first upper surface has a recess disposed therein. A conduit is in fluid communication with recess. An ejector is disposed within the recess. The ejector is configured to receive compressed air via the conduit The ejector is further configured to produce a propulsive efflux stream. A secondary airfoil is coupled to the primary airfoil, and has a second upper surface. The ejector is positioned such, that the efflux stream flows over the second surface. The second surface is oriented so as to entrain the efflux stream to flow in a direction substantially perpendicular to the first upper surface.

    Configuraciones de eyector y perfil aerodinámico
    6.
    发明专利
    Configuraciones de eyector y perfil aerodinámico 未知

    公开(公告)号：ES2844127T3

    公开(公告)日：2021-07-21

    申请号：ES18165126

    申请日：2016-07-27

    Applicant: JETOPTERA INC

    Inventor： EVULET ANDREI

    IPC: B64C9/38 ,  B64C21/04

    Abstract: Una aeronave, que comprende: un cuerpo principal (504); un perfil aerodinamico primario (503) acoplado al cuerpo principal (504); un generador de gas (501) acoplado al cuerpo principal (504) y que produce una corriente de gas; un conducto (505) en comunicacion de fluidos con el generador de gas (501); un eyector (502) en comunicacion de fluidos con el conducto (505) e incorporado en el perfil aerodinamico primario (503), el eyector (502) comprende una estructura de salida de la cual la corriente de gas fluye directamente desde el borde de salida del perfil aerodinamico primario (503) a una velocidad ajustable predeterminada; y un perfil aerodinamico secundario (506) colocado en tandem con el perfil aerodinamico primario (503), el perfil aerodinamico secundario (506) que tiene un borde delantero (507) y esta ubicado directamente aguas abajo de la estructura de salida de manera que la corriente de gas del eyector (502) fluya sobre el borde delantero (507) del perfil aerodinamico secundario (506), caracterizada porque la totalidad del perfil aerodinamico secundario (506) puede girar alrededor de un eje orientado paralelo al borde delantero (507).

    Fluidic propulsive system and thrust and lift generator for aerial vehicles
    9.
    发明专利
    Fluidic propulsive system and thrust and lift generator for aerial vehicles 未知

    公开(公告)号：AU2016315450B2

    公开(公告)日：2020-06-18

    申请号：AU2016315450

    申请日：2016-09-02

    Applicant: JETOPTERA INC

    Inventor： EVULET ANDREI

    IPC: B64C21/04 ,  B64C23/00 ,  B64C39/12 ,  B64D27/02 ,  B64D33/04 ,  F02C3/32 ,  F02K1/28

    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.

    VARIABLE GEOMETRY THRUSTER
    10.
    发明专利
    VARIABLE GEOMETRY THRUSTER 未知

    公开(公告)号：SG11201901116VA

    公开(公告)日：2019-03-28

    申请号：SG11201901116V

    申请日：2017-08-24

    Applicant: JETOPTERA INC

    Inventor： EVULET ANDREI

    IPC: F02K1/00 ,  F02K1/36 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/11 ,  F02K1/28

    Abstract: A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

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