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。

公开(公告)号：US08157203B2

公开(公告)日：2012-04-17

申请号：US12262747

申请日：2008-10-31

Applicant: Lloyd E. Kinsey ,  Patrick Kranking

Inventor： Lloyd E. Kinsey ,  Patrick Kranking

IPC: B64C27/22

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。

公开(公告)号：US20110001020A1

公开(公告)日：2011-01-06

申请号：US12829423

申请日：2010-07-02

Applicant: Pavol Forgac

Inventor： Pavol Forgac

IPC: B64C27/26

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/127

Abstract: The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight.

Abstract translation: 所公开的发明包括对众所周知的四角倾斜转子（QTR）飞机的若干改进。 第一个是在机翼飞行期间，一对倾斜转子可以比另一对大得多，被羽毛和停止。 这可以提高车辆空气动力学效率，并且可以用于提高车辆速度。 第二是机翼不像传统的QTR飞机那样以固定的入射角度附着在机身上，而且也可以独立于倾斜转子而相对于机身倾斜。 此外，每个转子和每个机翼可以相对于机身倾斜到任何倾斜角度，无限制，这给予车辆以相对于车辆飞行方向的任何姿态将机身定位的前所未有的能力。

公开(公告)号：US20110001001A1

公开(公告)日：2011-01-06

申请号：US12865429

申请日：2009-02-02

Applicant: Ashley Christopher Bryant

Inventor： Ashley Christopher Bryant

IPC: B64C29/00 ,  B64C39/10

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms (56) are employed, the arms (56) of fore and aft propulsion units (52,54; 53,55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51 ; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Only one propulsion unit (21) may be mounted at each extremity and additional fan units (48,83) may be used.

Abstract translation: 垂直起降（VTOL）飞翼飞机具有一对推进矢量推进单元（2,3; 4,5），其安装在飞行器俯仰轴线（PA）的前后，位于横梁（6,7） ）在机翼结构（1）的相对两端，前部单元（2; 4）和下方的后部单元（3; 5），机翼结构（1）。 推进单元（2-5）直接地或经由臂（56）枢转到斜面（6,7），用于单独的角位移，用于偏航，俯仰和滚动中的推进向导操纵的飞行器，并且用于悬停和 向前和向后飞行 当使用臂（56）时，前后推进单元（52,54; 53,55）的臂（56）通过链条驱动器（57-60）或连杆（61）相互配合。 机翼结构（1; 51; 78）可以具有翅片（47; 84），板条（81）和翼片（82）和其它空气动力学控制表面，并且扩大的横条（84）可以包括舵表面（80）。 每个末端只安装一个推进单元（21），并且可以使用附加的风扇单元（48,83）。

公开(公告)号：US20100288889A1

公开(公告)日：2010-11-18

申请号：US12735312

申请日：2009-01-02

Applicant: Marian Pruzina

Inventor： Marian Pruzina

IPC: B64C29/00

CPC classification number: B64C39/064 ,  B64C2201/027 ,  B64C2201/088

Abstract: The Spring flying device (1) preferably of circular, oval or polygon shape, capable of vertical take-off and landing, comprises the source (5) of flowing medium (6), which flows through chamber (2) consisting of curved bottom face generating buoyancy during flow (3) and curved top medium attracting face (4). The faces (3) and (4) making up chamber (2) have adequate spacing from each other which allows their interaction still; control is provided by deflection (9) and swivelling (10) flaps, pivot-mounted in chamber (2) and acting upon the flowing medium (6). The device (1) may carry missile ramp (18) with protective guide shield (14) with horizontal (15) and radial (16) deflection flaps which streamline the missile exhaust gases (17) to outer top buoyancy face (12), while the missile exhaust gases (17) may be streamlined to apertures (19) of the chamber simultaneously.

Abstract translation: 优选具有垂直起飞和着陆的圆形，椭圆形或多边形形状的弹簧飞行装置（1）包括流动介质（6）的源（5），其流过由弯曲底面 在流动（3）和弯曲顶部介质吸引面（4）期间产生浮力。 组合室（2）的面（3）和（4）彼此之间具有足够的间距，这使得它们的相互作用是静止的; 通过偏转（9）和旋转（10）襟翼提供控制，枢转安装在腔室（2）中并作用在流动介质（6）上。 装置（1）可以携带带有水平（15）和径向（16）偏转翼片的保护引导屏蔽（14）的导弹斜坡（18），其将导弹废气（17）简化为外顶部浮力面（12），同时 导弹废气（17）可以同时流线化到腔室（19）。

公开(公告)号：US07665688B2

公开(公告)日：2010-02-23

申请号：US11691971

申请日：2007-03-27

Applicant: David A Cylinder ,  James C Kellogg

Inventor： David A Cylinder ,  James C Kellogg

IPC: B64C27/24 ,  B64C27/28

CPC classification number: B64C27/24 ,  B64C27/28 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

Abstract: A micro aerial vehicle can be converted during flight between a fixed wing flight mode and a rotary wing flight mode. The canard design micro aerial vehicle includes a fuselage, two tiltable propellers and airfoils arranged at a forward portion of fuselage, a pair of coaxial drive shafts positioned aft of the tiltable propeller and airfoil arranged for contra-rotation, a stop rotor mechanism, and a pair of wing panels, each of the wing panels attached to one of the coaxial drive shafts. The wing panels act as contra-rotating rotor blades in the rotary wing flight mode, and act as fixed wing panels in the fixed wing mode.

Abstract translation: 微型飞行器可以在固定翼飞行模式和旋翼飞行模式之间的飞行过程中转换。 鸭子设计的微型飞行器包括机身，两个可倾斜的螺旋桨和机身，其布置在机身的前部，一对同轴驱动轴，位于可倾斜推进器和翼型的后方，布置成用于反向转动，止动转子机构和 一对翼板，每个翼片连接到同轴驱动轴之一。 翼板作为旋转翼飞行模式中的反转叶片，以固定翼模式作为固定翼板。