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公开(公告)号：US08720814B2
公开(公告)日：2014-05-13
申请号：US13442544
申请日：2012-04-09
Applicant: Frick A. Smith
Inventor： Frick A. Smith
CPC classification number: B64C29/0033 , B64C1/1415 , B64C1/1476 , B64C27/22 , B64C27/26 , B64C27/28 , B64C27/52 , B64C27/82 , B64C29/00 , B64C29/0016 , B64C39/02 , B64C39/024 , B64C2201/04 , B64C2201/088 , B64C2201/10 , B64C2201/104 , B64C2201/108 , B64C2201/162 , B64D17/24 , B64D17/34 , B64D17/62 , B64D17/64 , B64D17/80 , B64D27/02 , B64D31/00 , B64D35/04
Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.
Abstract translation: 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。
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公开(公告)号：US20120048994A1
公开(公告)日：2012-03-01
申请号：US13023772
申请日：2011-02-09
Applicant: Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs
Inventor： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs
CPC classification number: B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
Abstract translation: 比空中飞行器，具有扑翼的飞机，例如鸟巢飞机，其中角度定向控制是通过在扫掠角度行程和/或控制可变翼膜张力的过程中可展开的翼的偏转的可变差分扫掠角来实现的 。
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公开(公告)号：US20190202553A1
公开(公告)日：2019-07-04
申请号：US16294713
申请日：2019-03-06
Applicant: AeroVironment, Inc.
Inventor： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
CPC classification number: B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
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公开(公告)号：US20190193864A1
公开(公告)日：2019-06-27
申请号：US16221371
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
CPC classification number: B64D29/02 , B64C9/38 , B64C15/00 , B64C21/00 , B64C21/04 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/0273 , F02C3/04 , F02C6/04 , F02K1/002 , F02K1/36 , F05D2220/90 , Y02T50/166 , Y02T50/32 , Y02T50/44
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：US20180312268A1
公开(公告)日：2018-11-01
申请号：US16031539
申请日：2018-07-10
Applicant: JETOPTERA, INC.
Inventor： Andrei Evulet
IPC: B64D29/02 , B64D27/10 , B64C15/00 , B64C21/00 , B64C21/04 , B64C39/02 , B64C9/38 , B64D33/04 , B64D33/02 , B64D27/18
CPC classification number: B64D29/02 , B64C9/38 , B64C15/00 , B64C21/00 , B64C21/04 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/0273 , Y02T50/166 , Y02T50/32 , Y02T50/44
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.
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Patent Agency Ranking
公开(公告)号：US20180208306A1
公开(公告)日：2018-07-26
申请号：US15923878
申请日：2018-03-16
Applicant: AeroVironment, Inc.
Inventor： Matthew Todd Keennon , Karl Robert Klingebiel , Alexander Andryukov , Bart Dean Hibbs , John Peter Zwaan
CPC classification number: B64C33/025 , B64C19/00 , B64C33/02 , B64C2201/025 , B64C2201/10 , B64C2201/146
Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.
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公开(公告)号：US09802700B1
公开(公告)日：2017-10-31
申请号：US14824467
申请日：2015-08-12
Applicant: Jonathan M. Essary
Inventor： Jonathan M. Essary
CPC classification number: B64C39/024 , B64C27/00 , B64C2201/10
Abstract: A rotary aircraft includes a cylindrical enclosure configured to form an open housing with a top opening and a bottom opening; a hover disc disposed within the open housing of the cylindrical enclosure and configured to direct airflow entering through the top opening, the hover disc forming a center opening; and a fan extending through the center opening of the hover disc and configured to direct airflow through the hover disc.
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公开(公告)号：US20170283080A1
公开(公告)日：2017-10-05
申请号：US15625907
申请日：2017-06-16
Applicant: Jetoptera, Inc.
Inventor： Andrei Evulet
CPC classification number: B64D27/18 , B64C9/38 , B64C15/00 , B64C21/00 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D29/02 , B64D33/02 , B64D33/04 , B64D2033/0273 , Y02T50/166 , Y02T50/32
Abstract: 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.
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公开(公告)号：US20170240275A1
公开(公告)日：2017-08-24
申请号：US15456450
申请日：2017-03-10
Applicant: Jetoptera, Inc.
Inventor： Andrei Evulet
CPC classification number: B64C29/04 , B64C9/38 , B64C11/001 , B64C15/00 , B64C21/00 , B64C29/02 , B64C39/024 , B64C39/12 , B64C2201/021 , B64C2201/048 , B64C2201/088 , B64C2201/10 , B64C2201/104 , B64C2201/162 , B64D27/10 , B64D27/20 , B64D29/02 , B64D33/02 , B64D33/04 , B64D2033/0273 , Y02T50/166 , Y02T50/44
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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公开(公告)号：US20170057647A1
公开(公告)日：2017-03-02
申请号：US15221389
申请日：2016-07-27
Applicant: Jetoptera, Inc.
Inventor： Andrei Evulet
CPC classification number: B64D33/04 , B64C9/38 , B64C15/00 , B64C15/14 , B64C21/00 , B64C21/04 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D27/18 , B64D29/02 , B64D33/02 , B64D2033/0273 , F02C3/04 , F02C6/04 , F02K1/002 , F02K1/36 , F05D2220/90 , Y02T50/166 , Y02T50/32 , Y02T50/44
Abstract: A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.
Abstract translation: 耦合到车辆的推进系统。 该系统包括凸表面，耦合到凸表面的扩散结构以及耦合到凸表面的至少一个导管。 导管构造成将由车辆产生的初级流体引入凸表面。 该系统还包括联接到凸表面的入口结构，并且被构造成向漫射结构引入车辆可接近的次级流体。 扩散结构包括终端，其被配置为向所述系统提供用于引入的初级流体和次级流体的流出。
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