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公开(公告)号：US20180003128A1
公开(公告)日：2018-01-04
申请号：US15686052
申请日：2017-08-24
Applicant: Jetoptera, Inc.
Inventor： Andrei Evulet
CPC classification number: F02K1/30 , F02B27/06 , F02B37/00 , F02B39/04 , F02C3/04 , F02C7/143 , F02K1/36 , F02K1/38 , F05D2260/4023 , F05D2260/601 , F05D2270/173 , F05D2270/18 , F05D2300/6033 , F23R3/22 , Y02T10/144 , Y02T10/146 , Y02T50/672
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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公开(公告)号：US20170350309A1
公开(公告)日：2017-12-07
申请号：US15670943
申请日：2017-08-07
Applicant: Jetoptera, Inc.
Inventor： Andrei Evulet
CPC classification number: F02B27/06 , F02B37/00 , F02B39/04 , F02C3/04 , F02C6/12 , F02C7/10 , F02C7/143 , F05D2260/4023 , F05D2300/6033 , F23L17/16 , Y02T10/144 , Y02T10/146
Abstract: An internal combustion engine includes an exhaust conduit having an exhaust port fluidically coupled to ambient fluid and having an internal cross-sectional area and an engine cylinder fluidically coupled to the exhaust conduit. A fluidic amplifier is disposed within the exhaust conduit and is fluidically coupled to the engine cylinder. The amplifier is further fluidically coupled to a source of primary fluid and is configured to introduce the primary fluid and at least a portion of fluid from the engine cylinder to the exhaust port.
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公开(公告)号：US20170057648A1
公开(公告)日：2017-03-02
申请号：US15221439
申请日：2016-07-27
Applicant: Jetoptera, Inc.
Inventor： Andrei Evulet
Abstract: 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.
Abstract translation: 耦合到车辆的推进系统。 该系统包括具有出口结构的喷射器，推进流体以预定的可调节速度流动。 具有前缘的控制表面位于出口结构的下游，使得来自喷射器的推进流体流过控制表面。
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公开(公告)号：US12252265B2
公开(公告)日：2025-03-18
申请号：US18235311
申请日：2023-08-17
Applicant: JETOPTERA, INC.
Inventor： Andrei Evulet
IPC: B64C9/38 , B64C15/00 , B64C15/14 , B64C21/00 , B64C21/04 , B64C23/00 , B64C39/02 , B64D27/10 , B64D27/18 , B64D29/02 , B64D33/02 , B64D33/04 , B64U30/10 , B64U50/15 , F02C3/04 , F02C6/04 , F02K1/00 , F02K1/36 , B64U10/25 , B64U20/65 , B64U30/00
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.
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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.
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Patent Agency Ranking
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.
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公开(公告)号：US20240191875A1
公开(公告)日：2024-06-13
申请号：US18220775
申请日：2023-07-11
Applicant: JETOPTERA, INC.
Inventor： Andrei Evulet
IPC: F23R3/52 , F02C3/04 , F02C6/12 , F02C7/10 , F02C7/143 , F02K1/00 , F02K1/36 , F02K3/10 , F23R3/00 , F23R3/32
CPC classification number: F23R3/52 , F02C3/04 , F02C6/12 , F02C7/10 , F02C7/143 , F02K1/002 , F02K1/36 , F02K3/10 , F23R3/002 , F23R3/007 , F23R3/32 , F05D2220/32 , F05D2260/211 , F05D2260/4023 , F05D2300/6033 , Y02T50/60
Abstract: A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.
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公开(公告)号：US20240182166A1
公开(公告)日：2024-06-06
申请号：US18220755
申请日：2023-07-11
Applicant: JETOPTERA, INC.
Inventor： Andrei Evulet , Tyler Smallwood
CPC classification number: B64C29/0066 , B64C29/0033 , B64D27/14
Abstract: A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.
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公开(公告)号：US20240117828A1
公开(公告)日：2024-04-11
申请号：US18142750
申请日：2023-05-03
Applicant: JETOPTERA, INC.
Inventor： Andrei Evulet
CPC classification number: F15D1/08 , B64C15/14 , B64C29/04 , F02C6/08 , F02K1/28 , F02K1/386 , F15D1/007 , F15D1/008 , B60F5/02 , F05D2270/173
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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公开(公告)号：US11148801B2
公开(公告)日：2021-10-19
申请号：US16020116
申请日：2018-06-27
Applicant: JETOPTERA, INC.
Inventor： Andrei Evulet
Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail 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.
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