公开(公告)号：US09604715B2

公开(公告)日：2017-03-28

申请号：US15052398

申请日：2016-02-24

Applicant: Karem Aircraft, Inc.

Inventor： Abe Karem ,  Benjamin Tigner

IPC: H04W4/00 ,  B64C3/52 ,  B64C11/30 ,  B64C3/24 ,  B64C13/00 ,  B64C39/02 ,  B64C39/10 ,  B64C25/10 ,  H04B7/185

CPC classification number: B64C3/52 ,  B64C3/24 ,  B64C3/42 ,  B64C3/546 ,  B64C11/30 ,  B64C13/00 ,  B64C25/10 ,  B64C39/02 ,  B64C39/024 ,  B64C39/04 ,  B64C39/10 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64D27/24 ,  H04B7/18506

Abstract: A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.

公开(公告)号：US20170072755A1

公开(公告)日：2017-03-16

申请号：US15350458

申请日：2016-11-14

Applicant: Andrew H B Zhou ,  Dylan T X Zhou ,  Tiger T G Zhou

Inventor： Andrew H B Zhou ,  Dylan T X Zhou ,  Tiger T G Zhou

IPC: B60F5/02 ,  B64C37/00 ,  B60K16/00 ,  G05D1/08 ,  G08G5/04 ,  B60R11/04 ,  B64C39/02 ,  B64C3/56

CPC classification number: B64C35/008 ,  B60F5/02 ,  B60K16/00 ,  B60K2016/003 ,  B60R11/04 ,  B64C29/0033 ,  B64C29/0066 ,  B64C29/0075 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/141 ,  B64C2201/162 ,  G05D1/0816 ,  G05D1/0858 ,  G08G5/04

Abstract: The invention pertains to an automobile and more particularly, to a flying car. A flying car, comprises a body, adapted for carrying the payload from once place to another, a tail attached to body at rear end adapted for stabilizing the vehicle, plurality of wheels at the bottom of car connected to a power transmission system, plurality of foldable wings on the sides of body, adapted for creating the pressure difference and creating lift to the vehicle. Further, plurality of jet engines adapted for driving the jet flying car on surface as well as on air. A gimbaled swivel propulsion (GSP) thrust vector control, to controls the direction of the thrust generated by the engines. And plurality of parachutes attached to the flying jet car to safe land the flying jet car under emergency.

Abstract translation: 本发明涉及一种汽车，更具体地涉及一种飞行车辆。 一种飞行车，包括适于承载有效载荷从一个地方到另一个的主体，尾部，其安装在适于稳定车辆的后端的主体，连接到动力传动系统的轿厢底部的多个轮，多个 身体两侧的可折叠的翅膀，适用于产生压力差并产生车辆升力。 此外，多个喷气发动机适于在表面以及空气上驱动喷气式飞行汽车。 一个万向旋转推进（GSP）推力矢量控制，以控制发动机产生的推力方向。 并且多个降落伞附着在飞机上，以安全地飞行的喷气式飞机在紧急情况下。

公开(公告)号：US09567088B2

公开(公告)日：2017-02-14

申请号：US14460013

申请日：2014-08-14

Applicant: SWIFT ENGINEERING, INC.

Inventor： Robert Godlasky ,  Nate Ogawa ,  Andrew Streett

IPC: B64D27/02 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

Abstract translation: 垂直起落飞行器包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持固定的方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到达基本水平的飞行路径的路径。

公开(公告)号：US20170015403A1

公开(公告)日：2017-01-19

申请号：US15210521

申请日：2016-07-14

Applicant: Zerotech (Shenzhen) Intelligence Robot Co., Ltd

Inventor： Yucheng LIANG ,  Fuhua AI

IPC: B64C1/30 ,  B64C39/02

CPC classification number: B64C1/30 ,  B64C1/063 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/20

Abstract: An unmanned aerial vehicle arm adjustment device for adjusting an unmanned aerial vehicle arm into a folding state or an extracting state with respect to a fuselage of the aerial vehicle includes: left and right curb plates connected to the fuselage; a rocking arm connected to the unmanned aerial vehicle arm, wherein one end of the rocking arm is articulated with the left and right curb plates, and a first engaging part is provided on the rocking arm; and a locking member articulated with the left and right curb plates, wherein the locking member is provided with a second engaging part for engaging with the first engaging part; wherein the locking member is adapted to rotate in a first direction to force the second engaging part to engage with the first engaging part so as to hold the rocking arm such that the unmanned aerial vehicle arm is in the extracting state; and wherein the locking member is adapted to rotate in a second direction opposite to the first direction to force the second engaging part to disengage with the first engaging part so as to release the rocking arm such that the unmanned aerial vehicle arm is able to be rotated into the folding state.

Abstract translation: 用于将无人驾驶飞行器臂调整成相对于飞行器的机身的折叠状态或提取状态的无人驾驶飞行器臂调节装置包括：连接到机身的左右路缘板; 连接到无人驾驶飞行器臂的摇臂，其中摇臂的一端与左右路缘板铰接，在摇臂上设置有第一接合部; 以及与所述左右路缘板铰接的锁定构件，其中，所述锁定构件设置有用于与所述第一接合部接合的第二接合部; 其中所述锁定构件适于沿第一方向旋转以迫使所述第二接合部与所述第一接合部接合，以便保持所述摇臂，使得所述无人驾驶飞行器臂处于所述提取状态; 并且其中所述锁定构件适于沿与所述第一方向相反的第二方向旋转，以迫使所述第二接合部分与所述第一接合部分脱离，以便释放所述摇臂，使得所述无人驾驶飞行器臂能够旋转 进入折叠状态。

公开(公告)号：US20170008625A1

公开(公告)日：2017-01-12

申请号：US15164718

申请日：2016-05-25

Applicant: Orville Olm ,  Zenon Dragan

Inventor： Orville Olm ,  Zenon Dragan

IPC: B64C29/02 ,  B64C3/56 ,  B64C3/32 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/20 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.

Abstract translation: 垂直起飞和着陆（VTOL）无人驾驶飞机系统（UAS）可以通过折翼设计独特地实现垂直起降，同时还可以在机翼延伸时配置为动力飞行。 在具有扩展翼的动力飞行机构中，VTOL UAS可以保持受控的动力飞行作为双推杆的设计。 无人驾驶飞机系统可以以垂直起降飞行系统以零空速（或近零空速）起飞的姿态折叠起来，使用主发动机推力以及作为垂直起降飞机的向心推力来维持受控飞行。 从空中飞行任务飞行状态到动力飞行的空降过渡，反之亦然，可能使VTOL UAS在每个制度中持续控制飞行。

公开(公告)号：US20160355250A1

公开(公告)日：2016-12-08

申请号：US15172710

申请日：2016-06-03

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Nicholas L. Barnes ,  Ryan M. Alderfer ,  Timothy J. Marley ,  Stephen J. Schober

IPC: B64C3/56 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/201 ,  F16C2326/43

Abstract: A deployment or hinge mechanism and, more particularly, a compact unmanned aerial vehicle (UAV) wing deployment mechanism is provided. The deployment mechanism includes a hinged mechanism that stows in a stacked configuration and deploys in a level configuration.

Abstract translation: 提供了一种部署或铰链机构，更具体地，提供了一种紧凑的无人机（UAV）机翼展开机构。 展开机构包括铰接机构，其以堆叠结构的方式收纳并以水平配置展开。

公开(公告)号：US09452820B1

公开(公告)日：2016-09-27

申请号：US14924304

申请日：2015-10-27

Applicant: Wirth Research Limited

Inventor： Nicholas J. P. Wirth

IPC: B64C3/56 ,  B64C3/16 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C3/16 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/201

Abstract: An unmanned aerial vehicle 2 comprising: a fuselage 4; and a wing 6 comprising a central wing section 12 pivotably mounted to the fuselage 4 and a pair of outer wing sections 14a, 14b pivotably mounted to the central wing section 12; wherein the wing 6 has a folded configuration in which the central wing section 12 and the outer wing sections 14a, 14b are stacked on top of one another and are aligned with a longitudinal axis of the fuselage 4; and a deployed configuration in which the central wing section 12 is substantially perpendicular to the fuselage 4 and the outer wing sections 14a, 14b extend from the central wing section 12 away from the fuselage 4.

Abstract translation: 一种无人驾驶飞行器2，包括：机身4; 以及机翼6，其包括可枢转地安装到机身4的中心翼部分12和可枢转地安装到中心翼部分12的一对外翼部分14a，14b; 其中翼6具有折叠构造，其中中心翼部12和外翼部14a，14b彼此堆叠并且与机身4的纵向轴线对准; 以及中央翼部12基本上垂直于机身4并且外翼部14a，14b从中心翼部12远离机身4延伸的展开构造。

公开(公告)号：US09434471B2

公开(公告)日：2016-09-06

申请号：US13899252

申请日：2013-05-21

Applicant: Paul E Arlton ,  David J Arlton

Inventor： Paul E Arlton ,  David J Arlton

IPC: B64C27/10 ,  B64C27/605 ,  B64C7/00 ,  B64C39/02 ,  B64C27/14 ,  B64C27/82

CPC classification number: B64C27/605 ,  B64C7/00 ,  B64C27/10 ,  B64C27/14 ,  B64C39/024 ,  B64C2027/8236 ,  B64C2027/8281 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

公开(公告)号：US20160244144A1

公开(公告)日：2016-08-25

申请号：US15052398

申请日：2016-02-24

Applicant: Karem Aircraft, Inc.

Inventor： Abe Karem ,  Benjamin Tigner

IPC: B64C3/52 ,  B64C3/24 ,  H04B7/185 ,  B64C39/02 ,  B64C39/10 ,  B64C25/10 ,  B64C11/30 ,  B64C13/00

CPC classification number: B64C3/52 ,  B64C3/24 ,  B64C3/42 ,  B64C3/546 ,  B64C11/30 ,  B64C13/00 ,  B64C25/10 ,  B64C39/02 ,  B64C39/024 ,  B64C39/04 ,  B64C39/10 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64D27/24 ,  H04B7/18506

Abstract: A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.

Abstract translation: 描述了具有分段翼的太阳能飞行器，其可以在飞行期间重新配置以优化太阳能的收集。 飞机具有刚性结构，耐恶劣天气，并配置为依靠高空和常规条件下的自由飞行控制，从而提供超过2个月的飞行时间。 该飞机特别适合用作电信网络的一部分。 还讨论了包含这种飞机的电信网络。

公开(公告)号：US20160176503A1

公开(公告)日：2016-06-23

申请号：US14590464

申请日：2015-01-06

Applicant: The Boeing Company

Inventor： Jonathan David Gettinger

IPC: B64C3/56 ,  B64C39/02 ,  B64C5/12

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C5/12 ,  B64C2201/102

Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.