公开(公告)号：US3887146A

公开(公告)日：1975-06-03

申请号：US43248974

申请日：1974-01-11

Applicant: UNIV RUTGERS

Inventor： BRIGHT COOPER B

IPC: B64C29/00 ,  B64C29/04 ,  B64C15/14

CPC classification number: B64C29/00

Abstract: Vertical and short take-off and landing (V/STOL) aircraft has at least one structural element which is an inflatable gas storage compartment rechargeable with compressed air from the engine compressors. This air when used in combination with suction air and compressed air from the engine compressors under control of the pilot produces in the case of vertical take-off and landing (VTOL) air flotation beneath the aircraft initiating vertical lift-off and completing a short hover just prior to the instant of touchdown during landing and during the remaining part of the take-off and landing maneuver augments lift and stability and control by such as enhancing the boundary layer and moving compressed air over the control surfaces. This air when used for short take-off and landing (STOL) flight when speed is below power-on stall can augment lift and stability and control by such as enhancing the boundary layer and moving compressed air over the control surfaces.

Abstract translation: 垂直和短的起飞和着陆（V / STOL）飞机具有至少一个结构元件，其是可充气的可充气的气体储存室，其具有来自发动机压缩机的压缩空气。 当在飞行员控制下来自发动机压缩机的吸入空气和压缩空气结合使用时，这种空气在飞行器下方的垂直起飞和着陆（垂直起降）空气浮选的情况下产生垂直起飞并完成短悬停 就在着陆时的触地之前，在起飞和着陆操作的剩余部分，通过增加边界层和在控制表面上移动压缩空气来提升和稳定和控制。 当速度低于开机失速时，用于短时起飞（STOL）飞行的空气可以通过增加边界层和将压缩空气移动到控制表面上来增加提升和稳定性以及控制。

公开(公告)号：US3525485A

公开(公告)日：1970-08-25

申请号：US3525485D

申请日：1968-08-21

Applicant: VER FLUGTECHNISCHE WERKE

Inventor： PFAFF FRITZ ,  STAUFENBIEL ROLF ,  VOLKER HEINRICH

IPC: B64C29/00 ,  B64C15/00 ,  B64C29/04

CPC classification number: B64C29/0091

公开(公告)号：US12103675B2

公开(公告)日：2024-10-01

申请号：US17956344

申请日：2022-09-29

Applicant: Youngsub Ahn

Inventor： Youngsub Ahn

IPC: B64C29/04 ,  B60L50/60 ,  B64C1/00 ,  B64C11/00 ,  B64C39/02 ,  B64D27/24 ,  B64D35/06 ,  B64D35/08 ,  B64U20/60 ,  B64U20/75 ,  B64U30/294 ,  B64U50/14 ,  G05D1/00 ,  B64U30/20 ,  B64U50/19

CPC classification number: B64C29/04 ,  B60L50/66 ,  B64C1/00 ,  B64C11/001 ,  B64C39/024 ,  B64D27/24 ,  B64D35/06 ,  B64D35/08 ,  B64U20/60 ,  B64U20/75 ,  B64U30/294 ,  B64U50/14 ,  G05D1/0016 ,  B60L2200/10 ,  B64C2001/0081 ,  B64U30/20 ,  B64U50/19 ,  B64U2201/20

Abstract: A propeller-enclosed airlifting air tube apparatus contains a unique multi air-tube structure that functions as a plurality of air outtakes to produce stable lift force with one or more propellers enclosed in the apparatus. By encapsulating the propellers within the outer shells, the airlifting air tube apparatus is able to reduce potential bodily harm and property damage risks during a flight operation in a densely-populated environment or in another environment involving tight spaces. The airlifting air tube apparatus encapsulates one or more pairs of contra-rotating propellers inside a drone casing to enhance operational safety while minimizing the overall footprint of the apparatus. Furthermore, the airlifting air tube apparatus incorporates a novel airflow control dish-based flight control steering unit configured to change directions and altitudes of the apparatus by dynamically adjusting the airflow to each outtake air tube with the airflow control dish.

公开(公告)号：US20240182167A1

公开(公告)日：2024-06-06

申请号：US18218964

申请日：2023-07-06

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: B64C29/04 ,  B64C3/10 ,  B64C5/06 ,  B64C15/12 ,  B64C39/06 ,  B64C39/12 ,  B64D33/04

CPC classification number: B64C29/04 ,  B64C3/10 ,  B64C5/06 ,  B64C15/12 ,  B64C39/066 ,  B64C39/12 ,  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 tad conduit is fluidly coupled to the generator. First and second fore ejectors are 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 includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

公开(公告)号：US20240150014A1

公开(公告)日：2024-05-09

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 ,  B64C39/02 ,  B64C39/12 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04

CPC classification number: B64C29/04 ,  B64C9/38 ,  B64C11/001 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0273 ,  B64U10/25 ,  Y02T50/10 ,  Y02T50/40

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：US20230009569A1

公开(公告)日：2023-01-12

申请号：US17837892

申请日：2022-06-10

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: F15D1/08 ,  F02K1/38 ,  F02K1/28 ,  B64C29/04 ,  F15D1/00 ,  B64C15/14 ,  F02C6/08

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.

公开(公告)号：US11505316B2

公开(公告)日：2022-11-22

申请号：US16675104

申请日：2019-11-05

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

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

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：US20220333624A1

公开(公告)日：2022-10-20

申请号：US17853665

申请日：2022-06-29

Applicant: JETOPTERA, INC.

Inventor： ANDREI EVULET

IPC: F15D1/08 ,  F02K1/38 ,  F02K1/28 ,  B64C29/04 ,  F15D1/00 ,  B64C15/14 ,  F02C6/08

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.

公开(公告)号：US20220219806A1

公开(公告)日：2022-07-14

申请号：US17642457

申请日：2020-09-11

Applicant: Alexandru Balan

Inventor： Alexandru Balan

IPC: B64C11/00 ,  B64C15/14 ,  B64C7/02 ,  B64C27/20 ,  B64C29/04

Abstract: This present disclosure relates generally to propulsion systems and, more particularly, to adaptive ducted fan propulsion systems for use with aircraft such as unmanned aerial vehicles. Embodiments of ADF systems in accordance with the present disclosure feature automatic, fast operation, increase the intake section of the air mass fed to a propeller, and can increase thrust by 35%-40% as compared to existing ducted fans.

公开(公告)号：US20180334252A1

公开(公告)日：2018-11-22

申请号：US15832299

申请日：2017-12-05

Applicant: Yao-Chang Lin

Inventor： Yao-Chang Lin

IPC: B64C29/04 ,  B64C15/02 ,  B64D35/04

Abstract: A lightweight flying vehicle includes a carrier body, at least two fan-tube propulsion devices, two steering devices and a flight wing. The fan-tube propulsion devices are respectively disposed at two opposite sides of the carrier body and have a sufficient propulsion force. The steering device is disposed on a moving line of the airflow discharged from the fan-tube propulsion devices and is configured to change a direction of the airflow discharged from the air discharge opening, so that the lightweight flying vehicle is in a high-speed flight mode. The flight wing can provide a lift power in the high-speed flight mode.