公开(公告)号：US09365290B1

公开(公告)日：2016-06-14

申请号：US14837866

申请日：2015-08-27

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: B64C29/00 ,  B64C29/02 ,  B64C11/00 ,  G05D1/08 ,  G05D1/10

CPC classification number: B64C29/02 ,  B64C11/001 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162 ,  G05D1/0858 ,  G05D1/102

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract translation: 飞机包括机身，机翼，风扇和控制器。 机翼和管道风扇耦合到机身。 控制器可操作以以垂直飞行模式，水平飞行更多地控制飞行器，并且将飞行器从垂直飞行模式转换到水平飞行模式。

公开(公告)号：US20150232178A1

公开(公告)日：2015-08-20

申请号：US14378604

申请日：2013-02-13

Applicant: Johannes REITER

Inventor： Johannes Reiter

IPC: B64C29/00 ,  B64C37/00 ,  B64C3/38

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C3/385 ,  B64C27/00 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0075 ,  B64C29/02 ,  B64C37/00 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线 （121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。 第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕 机身轴（101）。 第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的 第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转 轴（101）。

公开(公告)号：US09085354B1

公开(公告)日：2015-07-21

申请号：US13868539

申请日：2013-04-23

Applicant: Google Inc.

Inventor： Eric Peeters ,  William Graham Patrick

IPC: B64C27/26 ,  B64C29/00

CPC classification number: B64C29/02 ,  B64C17/00 ,  B64C2201/088

Abstract: Systems and methods for vertical takeoff and/or landing are disclosed herein. An aerial vehicle may include a first propulsion unit and a second propulsion each rotatably connected to a body. The aerial vehicle may include a first wing and a second wing each rotatably connected to the body. And the aerial vehicle may include a control system configured to: position the first propulsion unit, the second propulsion unit, the first wing, and the second wing; operate the first propulsion unit and the second propulsion unit; and rotate the first propulsion unit, the second propulsion unit, the first wing, and the second wing.

Abstract translation: 本文公开了用于垂直起飞和/或着陆的系统和方法。 飞行器可以包括第一推进单元和第二推进件，每个推进单元和第二推进件可旋转地连接到主体。 飞行器可以包括第一翼和第二翼，每个翼可旋转地连接到主体。 并且该飞行器可以包括控制系统，其被配置为：定位第一推进单元，第二推进单元，第一翼和第二翼; 操作第一推进单元和第二推进单元; 并且旋转第一推进单元，第二推进单元，第一翼和第二翼。

公开(公告)号：US08936212B1

公开(公告)日：2015-01-20

申请号：US12861986

申请日：2010-08-24

Applicant: Qiang Fu ,  Xu Zhang

Inventor： Qiang Fu ,  Xu Zhang

IPC: B64C15/12

CPC classification number: B64C37/02 ,  B64C3/56 ,  B64C29/0033 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/165 ,  Y02T50/14

Abstract: System and method to construct vertical and/or short takeoff and landing (V/STOL) aerial vehicles capable of being folded into compact size, and capable of be combined with one or more such vehicles to form bigger composite aerial vehicles. Airframe of the vehicle comprises a plurality of wings on lateral or periphery of thrust generators, wherein arrangements of wings make it possible to optionally fold wings without moving thrust generators. Folding transforms such vehicles into ground vehicles which can share roads and house parking lots with conventional ground vehicles. Therefore such vehicles can be used as V/STOL flying cars. Means are provided for attaching to and detaching from one or more similarly equipped vehicles in flight or before takeoff, so that multiple vehicles can form a large composite vehicle. Compactness, combinability and V/STOL capability enable versatile applications.

Abstract translation: 构建能够折叠成紧凑尺寸的垂直和/或短起飞（V / STOL）飞行器的系统和方法，并且能够与一个或多个这样的车辆组合以形成更大的复合飞行器。 车辆的机身包括在推力发生器的侧面或周边上的多个翼，其中翼的布置使得可以可选地折叠翼而不移动推力发生器。 折叠将这种车辆转换成可与常规地面车辆共享道路和房屋停车场的地面车辆。 因此，这种车辆可以用作V / STOL飞行车。 提供了用于在飞行中或起飞之前附接和分离一个或多个类似装备的车辆的装置，使得多个车辆可以形成大型复合车辆。 紧凑性，组合性和V / STOL功能可实现多种应用。

公开(公告)号：US20140231594A1

公开(公告)日：2014-08-21

申请号：US14061723

申请日：2013-10-23

Applicant: Robert Marcus

Inventor： Robert Marcus

IPC: B64C19/00 ,  B64D45/00

CPC classification number: B64C19/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/088 ,  B64D45/00

Abstract: An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.

Abstract translation: 飞行器包括独立控制的水平推进器和垂直升降器，以提供设计和操作简单性，同时允许六度自由度的精确飞行和使用诸如工具，传感器和仪器的安装设备。 每个水平推进器和垂直升降器可以安装为恒定间距的固定轴转子，同时仍然允许精确控制偏航，俯仰，滚动，水平运动和垂直高程。 陀螺仪和倾斜仪可用于进一步提高飞行精度。 控制器管理施加水平推进器和垂直升降器的推力，以补偿由使用安装在飞行器上的工具和其他装置产生的力和扭矩。

公开(公告)号：US20140217229A1

公开(公告)日：2014-08-07

申请号：US14347375

申请日：2012-09-14

Applicant: Keen Ian Chan

Inventor： Keen Ian Chan

IPC: B64C29/02 ,  A63H27/00 ,  B64C13/24 ,  B64F5/00 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C13/24 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  G05D1/0669 ,  Y10T29/49826

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.

Abstract translation: 能够进行垂直和水平飞行模式的无人飞行器（UAV），组装无人机的方法和用于组装无人机的一套零件。 无人机包括翼结构，其包括细长的相等的第一和第二翼; 支撑结构，包括联接到所述机翼结构的中间位置并且在与所述机翼结构垂直的相反方向上延伸的第一和第二部分; 以及四个螺旋桨，每个螺旋桨安装到第一和第二翼中的相应一个以及第一和第二部分，用于在垂直和水平飞行模式期间为无人机提供动力。

公开(公告)号：US20130206921A1

公开(公告)日：2013-08-15

申请号：US13397569

申请日：2012-02-15

Applicant: James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler

Inventor： James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler

IPC: B64C29/00

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.

公开(公告)号：US08434710B2

公开(公告)日：2013-05-07

申请号：US12740005

申请日：2008-11-20

Applicant: Inderpal Singh Hothi ,  Jon Robert Stoackley ,  Steven John Stoackley

Inventor： Inderpal Singh Hothi ,  Jon Robert Stoackley ,  Steven John Stoackley

IPC: B64C27/22

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088

Abstract: An unmanned aerial vehicle (UAV) in the form of a “tail sitter” flying wing adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors on miniature helicopter rotor heads at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing comprises, to each side of its longitudinal axis, an inner section with swept back leading and trailing edges, and an outer section with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge.

Abstract translation: 一种无人机（UAV），以“尾巴”飞翼的形式适用于垂直起飞和着陆，并且作为直升机和机翼飞行之间的飞行之间的过渡。 车辆由车载电池供电，并在机翼顶部的微型直升机转子头上配备转子，用于升降机，起飞和着陆期间以及向前推力。 在平面图中，翼片在其纵向轴线的每一侧包括具有扫掠的前缘和后缘的内部部分，并且具有更垂直于纵向轴线的前缘的外部部分仅被轻度地扫掠或基本上不被刮除，以及 前沿后缘。

公开(公告)号：US08314374B2

公开(公告)日：2012-11-20

申请号：US11455709

申请日：2006-06-20

Applicant: Burak Uzman

Inventor： Burak Uzman

IPC: F41G7/20 ,  F41G7/24 ,  F41G7/30

CPC classification number: F42B12/365 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/122 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F41G7/30 ,  F42B15/01 ,  F42B15/10 ,  G05D1/0038

Abstract: A lightweight, man-portable weapon delivery system includes a fuselage, and first and second wings mounted to opposing sides of the fuselage. The system includes an electric motor for driving a propeller for providing thrust to propel the system. The electric motor is mounted to the fuselage, and configured to be remotely started by a user. The system includes an imaging device mounted to the system and configured to capture images of a theater of operations of the system. The system includes a communication circuit in communication with the imaging device and configured to transmit the images from the imaging device to the user for viewing the theater of operations of the system for remotely steering the system. The communication circuit is configured to receive commands from the user for steering the system into the target. The system includes a payload configured to store the ordnance.

Abstract translation: 轻便的便携式武器传送系统包括机身，以及安装在机身相对两侧的第一和第二翼。 该系统包括用于驱动螺旋桨以提供推力以推动系统的电动马达。 电动机安装在机身上，并被配置为由用户远程启动。 该系统包括安装到系统并被配置为捕获系统的操作剧场的图像的成像装置。 该系统包括与成像装置通信的通信电路，并且被配置为将图像从成像装置传输到用户，以观看用于远程转向系统的系统的操作剧场。 通信电路被配置为从用户接收命令以将系统转向目标。 系统包括配置为存储军械的有效载荷。

公开(公告)号：US20120153087A1

公开(公告)日：2012-06-21

申请号：US12186693

申请日：2008-08-06

Applicant: Daniel Ross Collette ,  Joseph Scott Helsing, JR.

Inventor： Daniel Ross Collette ,  Joseph Scott Helsing, JR.

IPC: B64C39/00 ,  B64D47/08 ,  B64D37/02 ,  B64C7/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2211/00

Abstract: A pod for an unmanned aerial vehicle is provided that may be removed and re-attached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的舱架，其可以被移除并重新附接到车辆。 荚包括外壳，在其中可以携带各种有效载荷。 车架上的第一表面包括多个连接或电迹线。 多个附件用于将荚可移除地附接到第一表面。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。