公开(公告)号：US20160023760A1

公开(公告)日：2016-01-28

申请号：US14801479

申请日：2015-07-16

Applicant: Insitu, Inc.

Inventor： Wayne Goodrich

IPC: B64C39/02 ,  G05D1/12 ,  B64C11/00

CPC classification number: B64C39/024 ,  B64C5/06 ,  B64C11/48 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/162 ,  F41H11/02 ,  F41H13/0006 ,  G05D1/12

Abstract: Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV toward a target UAV, and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage, one or more fins carried by the fuselage, counter-rotating propellers carried by the fuselage, and a disabling system that is configured to disable the target UAV.

Abstract translation: 公开了用于对抗无人驾驶飞行器的系统和方法。 代表性的方法包括将拦截器无人机指向目标无人机，并且将拦截器无人机沿着受控飞行路径引导回地面，例如响应于不与目标无人机接合的指令和/或响应于不成功 订婚。 另一个代表性的方法包括通过从拦截器UAV部署禁用元件（例如网）来禁用目标UAV以接触目标UAV。 代表性系统包括目标采集系统，发射控制系统和拦截机无人机所承载的接合系统。 在特定实施例中，拦截器UAV可以具有大致圆柱形的机身，由机身承载的一个或多个翅片，由机身携带的反向旋转螺旋桨，以及被配置为禁用目标UAV的禁用系统。

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：US20150370250A1

公开(公告)日：2015-12-24

申请号：US14688998

申请日：2015-04-16

Applicant: Skydio, Inc.

Inventor： Abraham Bachrach ,  Adam Bry ,  Matthew Donahoe

IPC: G05D1/00 ,  B64C39/02 ,  G05D1/10

CPC classification number: G05D1/0016 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64D47/08 ,  G01C21/165 ,  G01C23/00 ,  G05D1/0027 ,  G05D1/0044 ,  G05D1/0094

Abstract: Methods and systems are described for new paradigms for user interaction with an unmanned aerial vehicle (referred to as a flying digital assistant or FDA) using a portable multifunction device (PMD) such as smart phone. In some embodiments, a magic wand user interaction paradigm is described for intuitive control of an FDA using a PMD. In other embodiments, methods for scripting a shot are described.

Abstract translation: 描述了使用诸如智能电话的便携式多功能装置（PMD）与无人驾驶飞行器（称为飞行数字助理或FDA）进行用户交互的新范例的方法和系统。 在一些实施例中，描述了魔术棒用户交互范例，用于使用PMD直观地控制FDA。 在其他实施例中，描述了用于脚本化镜头的方法。

公开(公告)号：US20150360777A1

公开(公告)日：2015-12-17

申请号：US14698803

申请日：2015-04-28

Applicant: Sima MOTTALE

Inventor： Sima MOTTALE

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C27/04 ,  B64C27/10 ,  B64C39/08 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/146 ,  B64D47/08 ,  Y02T50/55

Abstract: The present invention discloses an unmanned aerial vehicle capable of transforming its shape, comprising a) a control apparatus b) one or more propellers being fixed to the control apparatus, c) a multitude of flaps which are foldable reversibly from an open to a closed position, wherein the flaps provide i) in open position about a disc shape which is about in parallel to the plane of the rotating propeller, and ii) in closed position a shuttlecock shape, wherein, at least one of the flaps comprises a battery recharge element, such as a solar panel, photovoltaic element or elements, an electromagnetic harvesting element, a thermoelectric generator and/or a solar thermoelectric generator. The present invention relates also to a rotating disc being suitable for the vehicle, as well as the use of the vehicle and the rotating disc.

Abstract translation: 本发明公开了一种能够转换其形状的无人驾驶飞行器，包括：a）控制装置; b）固定在控制装置上的一个或多个螺旋桨，c）多个襟翼，其可从开放到闭合位置可逆地折叠 ，其中所述翼片提供i）围绕与所述旋转螺旋桨的平面平行的盘形状的打开位置，以及ii）在关闭位置中的羽毛球形状，其中所述翼片中的至少一个包括电池再充电元件 ，例如太阳能电池板，光电元件或元件，电磁收集元件，热电发电机和/或太阳能热电发电机。 本发明还涉及适用于车辆的旋转盘以及车辆和旋转盘的使用。

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：US20150321759A1

公开(公告)日：2015-11-12

申请号：US14696220

申请日：2015-04-24

Applicant: PARROT

Inventor： Christine Caubel

IPC: B64C39/02 ,  B64C27/00

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C27/006 ,  B64C2201/024 ,  B64C2201/108

Abstract: The drone (10) comprises a drone body (12) and a plurality of propulsion units (16) to drive propellers (18). Removable lateral bumpers (22) extend beyond the area of rotation of the propellers, each bumper being connected to the propulsion units on the same side by connection arms (24) each comprising a pair of elastically deformable elongated blades with at their end a clamp of mounting on a barrel (26) of the motor. Under the effect of an external transverse effort exerted in a median region, the two blades may be deformed in the direction of a mutual moving closer towards a mounting/dismounting position producing, by leverage, an opening of the clamp, so as to secure the bumper arm to the propulsion unit, and conversely the mounting/dismounting of the bumper by detachment of the clamp from the barrel, by the only transverse effort exerted on the connection arms.

Abstract translation: 无人机（10）包括无人机体（12）和多个驱动螺旋桨（18）的推进单元（16）。 可拆卸侧向缓冲器（22）延伸超过螺旋桨的旋转区域，每个保险杠通过连接臂（24）连接到同一侧的推进单元，连接臂（24）各自包括一对可弹性变形的细长叶片，在其端部具有 安装在电机的枪管（26）上。 在施加在中间区域中的外部横向力的作用下，两个叶片可以在相对移动的方向上变得更靠近安装/拆卸位置，通过杠杆作用产生夹具的开口，从而固定 保险杠臂到推进单元，相反地，通过由连接臂上施加的唯一横向作用力使夹具从筒体脱离而使保险杠的安装/拆卸。

公开(公告)号：US20150274286A1

公开(公告)日：2015-10-01

申请号：US14668857

申请日：2015-03-25

Applicant: Yefim Kereth

Inventor： Yefim Kereth

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/82 ,  B64C27/32

CPC classification number: B64C27/10 ,  B64C27/08 ,  B64C27/12 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108

Abstract: An asymmetric multirotor helicopter has a structure supporting at least one main and two secondary propulsion systems. A flight control unit controls the helicopter by varying the relative speed of each of the main and secondary propulsion systems. Each main propulsion system includes at least one main motor drive and a main drive shaft that carries and propels a main differential contra-rotating transmission configured to share the power provided by the main drive shaft with two contra-rotating output shafts. Each secondary propulsion system includes at least one secondary motor drive and a secondary drive shaft that carries and propels respective secondary propulsion blades. The two contra-rotating output shafts support and propel for mutually contra-rotation motion two sets of main propulsion blades. The main drive shaft rotates in the same direction as one of the secondary drive shafts and at least one secondary drive shaft rotates in an opposite direction.

Abstract translation: 不对称的多转子直升机具有支撑至少一个主要和两个二次推进系统的结构。 飞行控制单元通过改变每个主推进系统和次推进系统的相对速度来控制直升机。 每个主推进系统包括至少一个主电动机驱动器和主驱动轴，其承载并推进构造成通过两个反转输出轴共享由主驱动轴提供的动力的主差速反转传动装置。 每个次级推进系统包括至少一个次级电动机驱动器和辅助驱动轴，其承载并推进相应的次级推进叶片。 两个反转输出轴支撑和推进相互反转运动两组主推进叶片。 主驱动轴沿与第二驱动轴中的一个方向相同的方向旋转，并且至少一个副驱动轴沿相反方向旋转。

公开(公告)号：US09126693B1

公开(公告)日：2015-09-08

申请号：US14257955

申请日：2014-04-21

Applicant: SZ DJI TECHNOLOGY CO., LTD

Inventor： Jun Shi ,  Xu Yang Pan

IPC: B64D31/06 ,  B64C29/00 ,  B64D27/00 ,  B64C39/02 ,  B64C27/00

CPC classification number: G05D1/042 ,  B64C27/00 ,  B64C29/00 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/14 ,  B64D31/06 ,  G05B11/42 ,  G05D1/0669

Abstract: Systems, methods, and devices are provided for assisted takeoff of an aerial vehicle. The aerial vehicle may takeoff using a first control scheme and switch to a second control scheme for normal flight when a takeoff threshold is met. The first control scheme optionally does not use integral control while the second control scheme may use integral control. The aerial vehicle may determine that a takeoff threshold is met, based on an output to a motor of the aerial vehicle and/or an acceleration of the aerial vehicle.

Abstract translation: 提供系统，方法和装置用于飞行器的辅助起飞。 当满足起飞阈值时，航空器可以使用第一控制方案起飞并切换到用于正常飞行的第二控制方案。 第一控制方案可选地不使用积分控制，而第二控制方案可以使用积分控制。 飞行器可以基于对飞行器的马达的输出和/或飞行器的加速度来确定满足起飞阈值。

公开(公告)号：US20150136897A1

公开(公告)日：2015-05-21

申请号：US14404195

申请日：2013-05-31

Applicant: Florian Seibel ,  Michael Wohlfahrt ,  Michael Kriegel

Inventor： Florian Seibel ,  Michael Wohlfahrt ,  Michael Kriegel

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2211/00 ,  B64D27/24 ,  Y02T50/62

Abstract: The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or Unmanned Aerial System (UAS), comprising a rigid wing (2) which enables aerodynamic horizontal flight, and at least four rotors (4, 4′) which are driven by means of controllable electric motors (5) and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism (7), wherein all electric motors (5) and rotors (4) are arranged on the wing (2).

Abstract translation: 本发明涉及一种飞机（1），优选是无人驾驶飞机（UAV），无人机或无人空中系统（UAS），其包括能够进行空气动力学水平飞行的刚性翼（2）和至少四个转子 '），其通过可控电动机（5）驱动，并且其可以通过枢转机构（7）在垂直起始位置和水平飞行位置之间枢转，其中所有电动机（5）和转子（4） ）设置在机翼（2）上。

公开(公告)号：US09035802B2

公开(公告)日：2015-05-19

申请号：US13641325

申请日：2010-12-22

Applicant: James M. McCollough ,  Erik Oltheten ,  Nicholas Lappos

Inventor： James M. McCollough ,  Erik Oltheten ,  Nicholas Lappos

IPC: G08B21/00 ,  B60Q1/00 ,  B64C27/04 ,  B64D43/00

CPC classification number: G01C23/00 ,  B60Q1/00 ,  B64C27/00 ,  B64C27/006 ,  B64C27/04 ,  B64C27/52 ,  B64C29/00 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/121 ,  B64D43/00 ,  B64D45/00 ,  G01C21/00 ,  G01D7/02 ,  G05D17/02

Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

Abstract translation: 电力安全系统被配置为在飞行器中提供电力信息。 电力安全系统包括具有电力需求指示器和功率可用指示器的电力安全仪器，每个指示器位于显示器上。 所需电源指示灯和电源指示灯的位置表示执行悬停飞行操作所需的电力和功率。 电力安全系统可以在飞行计划模式或当前飞行模式下操作。 电力安全系统使用至少一个传感器来测量对所需功率和可用功率有影响的变量。