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。

公开(公告)号：US20160311530A1

公开(公告)日：2016-10-27

申请号：US15204547

申请日：2016-07-07

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64C29/00 ,  B64C27/28 ,  B64D31/00 ,  B64C39/02 ,  B64C27/82 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64C1/14 ,  B64C27/52 ,  B64C27/26 ,  B64D17/24

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。

公开(公告)号：US20160152005A1

公开(公告)日：2016-06-02

申请号：US14903908

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. ROACH ,  Grant O. COOK

IPC: B32B15/04 ,  B32B37/12 ,  B32B37/14

CPC classification number: C25D5/56 ,  B05D5/00 ,  B05D7/02 ,  B22C7/023 ,  B22C9/043 ,  B22C9/10 ,  B22F7/04 ,  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: A composite laminate component is disclosed. The composite laminate component may comprise a composite laminate including a plurality of sub-laminates, and a metallic layer encapsulating one or more of the sub-laminates. The sub-laminates may be joined by a bond between the metallic layers.

Abstract translation: 公开了一种复合层压组件。 复合层压组件可以包括包括多个次层压板的复合层压材料和包封一个或多个次层压板的金属层。 亚层压板可以通过金属层之间的结合来连接。

公开(公告)号：US20160146022A1

公开(公告)日：2016-05-26

申请号：US14903856

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wendell V. Twelves ,  Grant O. Cook

IPC: F01D5/28 ,  B62D35/00 ,  F42B10/02 ,  F01D9/04 ,  B64C39/02

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: 公开了一种翼型件。 翼型件可以包括由高模量镀层形成的前缘，主体部分和后缘。 翼型件的主体部分可以由具有比高模量镀层低的弹性模量的材料形成。 高模量电镀可以提高后缘的刚度，允许更薄的后缘，并且具有改善的疲劳寿命。

公开(公告)号：US20150108282A1

公开(公告)日：2015-04-23

申请号：US14385506

申请日：2013-02-14

Applicant: The Ritsumeikan Trust

Inventor： Katsuya Kanaoka

IPC: B64C15/12 ,  B64C39/02

CPC classification number: B64C15/12 ,  B63B2035/008 ,  B63H25/04 ,  B63H25/46 ,  B63H2025/465 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/10 ,  B64C2201/146 ,  G05D1/10 ,  G05D1/102

Abstract: A holonomic floating mobile object is operated under gravity and includes a main body and six or more thrusters for generating thrust by changing the momentum of a fluid. The six or more thrusters are controlled independently of one another such that the thrust is set at a desired value. The six or more thrusters are arranged in a fuselage coordinate system defined on the main body, such that the range in which a total thrust vector obtained by combining vectors of the thrust generated by all of the thrusters can be generated spans a six-dimensional space with three directions of translation and three directions of rotation. Incoming and outgoing flows to and from one of the thrusters are spaced apart from incoming and outgoing flows to and from the other thrusters and even apart from every other fuselage structure aside from that one thruster.

Abstract translation: 完整的浮动移动物体在重力作用下运行，包括主体和六个或更多个用于通过改变流体动量产生推力的推进器。 六个或更多个推进器彼此独立地控制，使得推力被设定在期望的值。 六个或更多个推进器被布置在限定在主体上的机身坐标系中，使得可以产生通过组合由所有推进器产生的推力的矢量而获得的总推力向量的范围跨越六维空间 具有三个方向的翻译和三个方向的旋转。 来往于其中一个推进器的进出流量与进入和离开其它推进器的进出流量间隔开，甚至除了一个推进器之外的每个其他机身结构。

公开(公告)号：US08210471B2

公开(公告)日：2012-07-03

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

IPC: B64C33/00

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：US10046850B2

公开(公告)日：2018-08-14

申请号：US15088615

申请日：2016-04-01

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble ,  Matthew Curran

IPC: B64C3/42 ,  B64C1/26 ,  B64C39/02

CPC classification number: B64C3/42 ,  B64C1/26 ,  B64C1/28 ,  B64C3/38 ,  B64C3/385 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/028 ,  B64C2201/10

Abstract: An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.

公开(公告)号：US20170283033A1

公开(公告)日：2017-10-05

申请号：US15088615

申请日：2016-04-01

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble ,  Matthew Curran

IPC: B64C3/42 ,  B64C39/02 ,  B64C1/26

CPC classification number: B64C3/42 ,  B64C1/26 ,  B64C1/28 ,  B64C3/38 ,  B64C3/385 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/028 ,  B64C2201/10

Abstract: An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.

公开(公告)号：US20170183092A1

公开(公告)日：2017-06-29

申请号：US15457455

申请日：2017-03-13

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：US09645580B2

公开(公告)日：2017-05-09

申请号：US15272414

申请日：2016-09-21

Applicant: QFO Labs, Inc.

Inventor： Brad Pedersen ,  Peter Spirov

IPC: G05D1/08 ,  B60V1/06 ,  B60V1/10 ,  B64C27/20 ,  B64C39/00 ,  B64C39/02 ,  G05D1/00 ,  B64C15/02 ,  B64C27/08 ,  B64D27/24

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.