公开(公告)号：EP3019705A4

公开(公告)日：2017-04-26

申请号：EP14851565

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TWELVES WENDELL V ,  COOK III GRANT O

IPC: F01D5/14 ,  F01D5/28 ,  F04D29/02

CPC classification number: C25D5/56 ,  B05D5/00 ,  B05D7/02 ,  B22C7/023 ,  B22C9/043 ,  B22C9/10 ,  B22F5/04 ,  B22F7/08 ,  B28B1/24 ,  B28B7/342 ,  B28B11/04 ,  B28B11/243 ,  B32B3/263 ,  B32B7/12 ,  B32B15/04 ,  B32B15/08 ,  B32B15/20 ,  B32B37/12 ,  B32B37/1284 ,  B32B37/14 ,  B32B2255/10 ,  B32B2307/202 ,  B32B2307/554 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  B62D35/00 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/10 ,  C04B35/76 ,  C04B35/806 ,  C09D5/26 ,  C23C14/20 ,  C23C16/06 ,  C23C18/1633 ,  C23C18/165 ,  C23C18/2013 ,  C23C18/22 ,  C23C18/31 ,  C23C26/00 ,  C23C28/02 ,  C25D3/02 ,  C25D3/38 ,  C25D3/46 ,  C25D5/48 ,  C25D9/04 ,  C25D11/20 ,  F01D5/00 ,  F01D5/147 ,  F01D5/187 ,  F01D5/284 ,  F01D5/288 ,  F01D9/02 ,  F01D9/041 ,  F01D11/08 ,  F01D25/005 ,  F04D29/023 ,  F04D29/324 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/312 ,  F05D2230/314 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2300/10 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/1616 ,  F05D2300/171 ,  F05D2300/177 ,  F05D2300/20 ,  F05D2300/30 ,  F05D2300/44 ,  F05D2300/501 ,  F05D2300/603 ,  F05D2300/611 ,  F05D2300/614 ,  F42B10/02

Abstract: An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed.

Abstract translation: 公开了翼型。 翼型可以包括由高模量电镀形成的前缘，主体部分和后缘。 翼型的主体部分可以由具有比高模量镀层更低的弹性模量的材料形成。 高模量电镀可以改善后缘的刚性，允许形成更薄的后缘，并且具有改善的疲劳寿命。

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

IPC: B64C33/02 ,  B64C19/00

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.

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.

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.

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

IPC: B64C33/02 ,  B64C19/00

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.

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

IPC: B64C3/00 ,  B64C39/02 ,  B64C27/00

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.

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

IPC: B64D27/18 ,  B64D33/04 ,  B64C39/02 ,  B64D29/02

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.

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

IPC: B64C29/04 ,  B64C39/02 ,  B64C11/00 ,  B64C9/00 ,  B64C39/12 ,  B64D27/20

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.

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

IPC: B64D27/18 ,  B64D33/02 ,  B64D33/04 ,  B64D29/02 ,  B64C39/02

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。

公开(公告)号：US20170010622A1

公开(公告)日：2017-01-12

申请号：US15272414

申请日：2016-09-21

Applicant: QFO Labs, Inc.

Inventor： Brad Pedersen ,  Peter Spirov

IPC: G05D1/08 ,  B64C39/00 ,  B64D27/24 ,  B64C15/02 ,  G05D1/00 ,  B64C39/02 ,  B64C27/08

CPC classification number: G05D1/0816 ,  B60V1/06 ,  B60V1/10 ,  B64C15/02 ,  B64C27/08 ,  B64C27/20 ,  B64C39/001 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/10 ,  B64C2201/108 ,  B64C2201/146 ,  B64D27/24 ,  G05D1/0016 ,  G05D1/0022 ,  G05D1/0858

Abstract: A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control.

Abstract translation: 稳态飞行气垫船优选地使用至少两对反向旋转管道风扇来产生类似气垫船的升降机，并且利用稳态悬停控制系统来创建易于控制的飞行器。 稳态悬停控制系统通过真正的线控飞行控制和线控系统控制为飞行器提供真正的动态平衡。