公开(公告)号：US20160244158A1

公开(公告)日：2016-08-25

申请号：US14121001

申请日：2014-08-13

Applicant: USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINSTRATION

Inventor： WILLIAM J. FREDERICKS ,  Mark D. Moore ,  Ronald C. Busan ,  Paul M. Rothhaar ,  David D. North ,  William M. Langford ,  Christopher T. Laws ,  William T. Hodges ,  Zachary R. Johns ,  Sandy R. Webb

IPC: B64C29/00 ,  B64C3/40 ,  B64C9/14 ,  B64C39/02 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64D27/24 ,  B64D27/26

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

Abstract translation: 提供了系统，方法和装置，其将先进的车辆配置（例如先进的飞行器配置）与电力推进的输注结合在一起，从而能够在保持完全垂直起飞和着陆的同时保持四倍的范围和耐力增加（“VTOL “）和车辆的悬停能力。 实施例可以提供具有垂直起落架和巡航高效能力的车辆，而不使用地面基础设施。 一种实施方式的车辆可以包括被配置为倾斜运动范围的翼，连接到翼的第一系列电动马达，并且每个被配置成驱动相关翼翼推进器，构造成在所述运动范围内倾斜的尾部，第二系列 耦合到尾部并且每个被配置为驱动相关联的尾部螺旋桨的电动马达以及连接到第一系列电动机和第二系列电动机的电推进系统。

公开(公告)号：US09376208B1

公开(公告)日：2016-06-28

申请号：US14662097

申请日：2015-03-18

Applicant: Amazon Technologies, Inc.

Inventor： Nicholas Kristofer Gentry

IPC: B64C39/02 ,  B64D27/24 ,  B64D27/02

CPC classification number: B64D35/08 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/145 ,  B64D27/24 ,  B64D2027/026 ,  G05D1/042 ,  G08G5/006 ,  Y10S903/93

Abstract: An unmanned aerial vehicle (“UAV”) is configured with a redundant power generation system on-board the UAV. A redundant power system on-board the UAV can selectively utilize an auxiliary power source during operation and/or flight of the UAV. The power system on-board the UAV may include a battery and at least one auxiliary power source comprising a combustion engine. The combustion engine on-board the UAV may be selectively operated to charge the battery when a charge level of the battery is below a full charge level, and/or to power one or more propeller motors of the UAV.

Abstract translation: 无人驾驶飞行器（“UAV”）配置有无人机上的冗余发电系统。 无人机上的冗余电力系统可以在UAV的运行和/或飞行期间选择性地利用辅助电源。 UAV上的电力系统可以包括电池和包括内燃机的至少一个辅助电源。 当电池的充电水平低于完全充电水平时和/或为UAV的一个或多个螺旋桨电动机供电时，可以选择性地操作在UAV上的内燃机对电池充电。

公开(公告)号：US20160023753A1

公开(公告)日：2016-01-28

申请号：US14795505

申请日：2015-07-09

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64C27/22 ,  B64C25/00

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

Abstract: A vehicle is provided and includes a wing having opposite surfaces and opposite sides and first and second engines disposed to drive wing movement and being respectively supported asymmetrically on the opposite surfaces and at the opposite sides of the wing.

Abstract translation: 车辆被设置并且包括具有相对表面和相对侧的机翼，并且第一和第二发动机设置成驱动机翼运动并分别支撑在机翼的相对表面和相对侧上的不对称。

公开(公告)号：US20160001878A1

公开(公告)日：2016-01-07

申请号：US14768476

申请日：2014-02-06

Applicant: NES&TEC CO.,LTD.

Inventor： Ki-Seong LEE

IPC: B64C27/28 ,  B64C39/02

CPC classification number: B64C27/28 ,  B64C3/38 ,  B64C3/58 ,  B64C9/323 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/185 ,  B64C2201/187

Abstract: Disclosed is an easy landing drone. The drone includes: a propeller changing direction; a propeller tower supporting the propeller; a body connected to the propeller tower; a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body; a pair of auxiliary wings disposed in the pair of holes, respectively; and an actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings.

Abstract translation: 披露了一个简单的降落无人机。 无人机包括：螺旋桨改变方向; 支撑螺旋桨的螺旋桨塔; 连接到螺旋桨塔的主体; 主翼相对于主体的水平轴对称地布置，并且具有围绕主体的重心的一对孔; 一对辅助翼分别设置在该对孔中; 以及致动器，其通过所述一对辅助翼连接到固定到所述主翼的基轴，并且控制所述一对辅助翼的角度。

公开(公告)号：US20150367932A1

公开(公告)日：2015-12-24

申请号：US14046927

申请日：2013-10-05

Applicant: Dillon Mehul Patel

Inventor： Dillon Mehul Patel

IPC: B64C3/10 ,  B64C25/10 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104

Abstract: An aerial vehicle compromising of a streamline delta wing structure, an M-wing structure accomplished through dihedral and dropped wing tips, and a variable incidence tail. The structure of the vehicle produces high lift and drag while maintaining stability and control at high angles of attack.

Abstract translation: 一种航空器损坏流线型三角翼结构，通过二面和落下的翼尖实现的M翼结构和可变入射尾。 车辆的结构产生高的提升和拖动，同时保持高的迎角的稳定性和控制。

公开(公告)号：US20150336663A1

公开(公告)日：2015-11-26

申请号：US14507313

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： JAMES DONALD PADUANO ,  PAUL NILS DAHLSTRAND ,  JOHN BROOKE WISSLER ,  ADAM WOODWORTH

IPC: B64C27/52 ,  B64C39/02 ,  B64C29/02

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

Abstract translation: 根据本发明的一个方面的垂直起飞（VTOL）飞机包括机身，具有位于机身尾端的全移动水平稳定器的尾翼，机身具有位于机身的大致中间位置 翼的远端​​，其中翼被配置成使用位于机身的每一侧上的倾斜铰链在基本上直的机翼构型和倾斜翼结构之间转换。 垂直起落飞行器还可以包括一个或多个可伸缩的弹簧支撑件，其中可伸缩的弹簧支撑构造成从翼的远端中的每一个展开。

公开(公告)号：US20150284075A1

公开(公告)日：2015-10-08

申请号：US14243540

申请日：2014-04-02

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64C27/22 ,  B64C3/42 ,  B64C39/02 ,  B64C29/00 ,  B64C25/10

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

Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, inboard wings extending from opposite sides of the fuselage to define a support plane and engine nacelles disposed along the wings. Each of the wings includes ground alighting elements and a variable geometry such that a portion of the ground alighting elements are alignable with the support plane during in-flight conditions and displaceable from the support plane.

Abstract translation: 提供垂直起飞和降落（VTOL）飞机，并包括机身，内侧翅膀从机身的相对侧延伸，以限定沿机翼设置的支撑平面和发动机舱。 每个翼包括地面下落元件和可变几何形状，使得地面下落元件的一部分在飞行状态期间与支撑平面对准并且可从支撑平面移位。

公开(公告)号：US20150267996A1

公开(公告)日：2015-09-24

申请号：US14281680

申请日：2014-05-19

Applicant: AeroVironment, Inc.

Inventor： Guan H. Su ,  Marcos Henry Rodriguez

IPC: F41F3/00 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。

公开(公告)号：US20150102157A1

公开(公告)日：2015-04-16

申请号：US14460013

申请日：2014-08-14

Applicant: SWIFT ENGINEERING, INC.

Inventor： Robert Godlasky ,  Nate Ogawa ,  Andrew Streett

IPC: B64C29/00 ,  B64C3/56 ,  B64D27/02

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在固定方向（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：US08991751B2

公开(公告)日：2015-03-31

申请号：US13429156

申请日：2012-03-23

Applicant: Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

Inventor： Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。