公开(公告)号：US20150197335A1

公开(公告)日：2015-07-16

申请号：US14415433

申请日：2013-09-12

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Guy Dekel ,  Lior Zivan ,  Yoav Efraty ,  Amit Wolff ,  Avner Volovick

IPC: B64C27/52 ,  G05D1/08 ,  G05D1/04

CPC classification number: B64C27/52 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187 ,  G05D1/042 ,  G05D1/0808 ,  G05D1/0858 ,  G05D1/102

Abstract: A control system configured to control an acceleration of an air vehicle which comprises a tiltable propulsion unit that is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle, the control system comprising: (a) an input interface for receiving information indicative of a monitored airspeed of the air vehicle; and (b) a control unit, configured to issue controlling commands to a controller of the tiltable propulsion unit for controlling the acceleration of the air vehicle.

Abstract translation: 一种被配置为控制空中交通工具的加速度的控制系统，该控制系统包括可倾斜的推进单元，该倾斜推进单元可倾斜以提供方向至少相对于空气在一般的垂直推力矢量方向和一般纵向推力向量方向之间变化的推力 车辆，所述控制系统包括：（a）输入接口，用于接收指示所述空中交通工具的监控空速的信息; 以及（b）控制单元，被配置为向所述可倾斜推进单元的控制器发出控制命令，以控制所述空中交通工具的加速度。

公开(公告)号：US20150183520A1

公开(公告)日：2015-07-02

申请号：US14416035

申请日：2013-07-19

Applicant: Andrew Charles ELSON

Inventor： Andrew Charles Elson

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187

Abstract: A method of launching a powered unmanned aerial vehicle, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, wherein the vehicle is prevented from entering its flight mode during ascent, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract translation: 一种发射有功无人驾驶飞行器的方法，该方法包括通过从基本上地平面位置到高架高度附接到比轻空载体提升车辆，其中在上升期间车辆被阻止进入其飞行模式 ，当车辆相对于承运人的速度基本上为零时，导致车辆从载体上脱离，随后车辆随着其高度减小到能够防止任何进一步下降并能够开始独立持续飞行的速度 。

公开(公告)号：US20150183514A1

公开(公告)日：2015-07-02

申请号：US14643857

申请日：2015-03-10

Applicant: DZYNE Technologies, Inc.

Inventor： MARK ALLAN PAGE ,  MATTHEW ROBERT MCCUE ,  ROBERT ANTHONY GODLASKY

IPC: B64C29/02 ,  B64C39/02 ,  B64C3/38 ,  B64C3/34 ,  B64C5/02

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。

公开(公告)号：US09033281B1

公开(公告)日：2015-05-19

申请号：US13410225

申请日：2012-03-01

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D9/00

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203

Abstract: A radio controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV is controlled by radio controls from a hand held controller, with actuators retracting and letting out control lines attached to the parachute in order to control direction of the parachute. The UAV may be launched from a tube using a pressurized tank with a nozzle expelling gas from the tank, the tank and nozzle towing a canister from which the UAV is deployed.

Abstract translation: 公开了一种无线电控制的无人机。 无人机包括一个降落伞，一个圆柱形的电源和控制模块垂直悬挂在降落伞下方。 在一个实施例中，推进源安装在功率和控制模块的顶部，其控制线连接到推进源下方的模块，并且在另一个实施例中，功率和控制模块从推进源上方的点悬挂。 无人机由手持控制器的无线电控制控制，执行器缩回并释放连接到降落伞的控制线，以控制降落伞的方向。 无人机可以使用加压罐从管中发射，喷嘴排出来自罐，罐和喷嘴的气体，其牵引无人机从其部署的罐。

公开(公告)号：US20120248259A1

公开(公告)日：2012-10-04

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: B64C27/24

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。

公开(公告)号：US08251307B2

公开(公告)日：2012-08-28

申请号：US12104432

申请日：2008-04-16

Applicant: Emray R. Goossen

Inventor： Emray R. Goossen

IPC: B64C29/00 ,  B64C13/18

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/126 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/22

Abstract: A manipulator arm system on a ducted air-fan UAV is disclosed herein. The target site may be accurately located by the UAV, and the manipulator system may accurately locate the payload at the target site. The manipulator arm may select tools from a toolbox located on-board the UAV to assist in payload placement or the execution of remote operations. The system may handle the delivery of mission payloads, environmental sampling, and sensor placement and repair.

Abstract translation: 本文公开了一种管道式空气风扇UAV上的操纵臂系统。 目标站点可以由UAV精确定位，并且机械手系统可以准确地定位目标位置的有效载荷。 操纵臂可以从位于无人机上的工具箱中选择工具，以帮助有效载荷放置或执行远程操作。 该系统可以处理任务有效载荷的交付，环境取样以及传感器的放置和修理。

公开(公告)号：US20120131904A1

公开(公告)日：2012-05-31

申请号：US13244583

申请日：2011-09-25

Applicant: Robert S. Violett

Inventor： Robert S. Violett

IPC: F02K5/00 ,  H02K9/06

CPC classification number: B64D27/24 ,  A63H27/02 ,  A63H29/16 ,  A63H29/22 ,  B64C2201/042 ,  B64C2201/162 ,  B64D33/08 ,  H02K5/18 ,  H02K5/20 ,  H02K7/14 ,  H02K11/33 ,  Y02T50/62

Abstract: A power plant for a jet-type model airplanes and UAVs includes an electric motor and a cover. The cover receives a portion of the electric motor and a sleeve into which the electric motor is inserted. The sleeve has a plurality of fins to dissipate heat and create openings into the cover. Air from the fan rotor passes through the openings to cool an electronic speed control member and exits a rear opening in the cover. The cover may also have additional openings for air to enter into the cover.

Abstract translation: 用于喷气型模型飞机和无人机的发电厂包括电动机和盖子。 盖子容纳电动机的一部分和插入电动马达的套筒。 套筒具有多个散热片以散热并在盖中产生开口。 来自风扇转子的空气通过开口以冷却电子速度控制构件并离开盖中的后开口。 盖子还可以具有用于空气进入盖子的附加开口。

公开(公告)号：US08141823B2

公开(公告)日：2012-03-27

申请号：US12949410

申请日：2010-11-18

Applicant: David C. Hursig ,  Steven D. Martinez

Inventor： David C. Hursig ,  Steven D. Martinez

IPC: G05D1/08

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64D45/04 ,  G05D1/0653 ,  G05D1/0858

Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

Abstract translation: 起飞和着陆（VTOL）无人机（UAV）的飞行控制系统增加起飞和着陆模式。 起飞和着陆模式使用可用于飞行控制系统和VTOL无人机现有控制面和节气门控制的数据。 因此，VTOL无人机可以在倾斜的表面上起飞和着陆，而不需要使用设计成在倾斜表面上对无人机进行平坦化的起落架机构。

公开(公告)号：US08070092B2

公开(公告)日：2011-12-06

申请号：US12262428

申请日：2008-10-31

Applicant: Bruce Dan Bouldin ,  Ricardo Burdisso

Inventor： Bruce Dan Bouldin ,  Ricardo Burdisso

IPC: B64C39/06

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  B64D2033/0206

Abstract: A strut support system for a ducted fan unmanned aerial vehicle to suppress noise comprising: a ducted fan fuselage that defines an opening; an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts extending between the ducted fan fuselage and the engine each comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight of the ducted fan fuselage's leading edge.

Abstract translation: 一种用于管道风扇无人机的用于抑制噪声的支柱支撑系统，包括：限定开口的管道风扇机身; 发动机纵向延伸穿过机身中的开口; 驱动机构，其可旋转地安装在所述发动机上，其中风扇安装在由所述开口限定的导管内的所述驱动机构上; 以及在所述风扇风扇机身和所述发动机之间延伸的多个支柱，每个支柱包括通过曲线连接部连接在一起的第一腿部和第二腿部，其中所述第一腿部连接到所述风扇风扇机身，并且所述第二腿部连接到所述发动机 ，其中所述多个支柱位于所述风扇的上游，其中，所述多个支柱中的每一个的所述第一支腿与所述风扇风扇机身之间的连接处在所述风扇风扇机身的前缘的突出部之外。

公开(公告)号：US20110057075A1

公开(公告)日：2011-03-10

申请号：US12949410

申请日：2010-11-18

Applicant: David C. Hursig ,  Steven D. Martinez

Inventor： David C. Hursig ,  Steven D. Martinez

IPC: G05D1/00 ,  B64C29/00

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64D45/04 ,  G05D1/0653 ,  G05D1/0858

Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

Abstract translation: 起飞和着陆（VTOL）无人机（UAV）的飞行控制系统增加起飞和着陆模式。 起飞和着陆模式使用可用于飞行控制系统和VTOL无人机现有控制面和节气门控制的数据。 因此，VTOL无人机可以在倾斜的表面上起飞和着陆，而不需要使用设计成在倾斜表面上对无人机进行平坦化的起落架机构。