公开(公告)号：US06676084B2

公开(公告)日：2004-01-13

申请号：US10168588

申请日：2002-06-24

Applicant: Jean Asseline ,  George De Noni

Inventor： Jean Asseline ,  George De Noni

IPC: B64D1734

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires. The wings (13) are a caisson-type supple parachute and are connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

Abstract translation: 由具有推进式螺旋桨（19）的热力发动机（20）推进的用于遥感的小型无线电控制飞行装置，该装置能够以35Km / h的最大速度短时起飞和着陆并飞行。 该装置包括荚和翼，荚（1）是刚性三轮车，可通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6）。 底座是焊接的单件元件，包括发动机，螺旋桨，油箱和无线电控制。 顶点是焊接的单件元件。 下平面和两个横向平面包括组装在基部和顶点的翼梁（11,12）。 下平面在其三个端角处包括两个后轮（8）和前轮（9），前轮设置成朝向顶点的前部突出，并且轮是低压轮胎。 机翼（13）是沉箱式柔软的降落伞，并且通过两个前吊索（17）和作用在两个翼片/副翼上的两个制动吊索（18）以可调节的方式连接到吊舱。

公开(公告)号：US20040004157A1

公开(公告)日：2004-01-08

申请号：US10296137

申请日：2003-06-30

Inventor： Lance A. Liotta

IPC: B64D027/00 ,  B64D029/00

CPC classification number: B64C39/066 ,  A63H27/00 ,  B64C39/028 ,  B64C2201/105 ,  B64C2201/107

Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.

Abstract translation: 一种专为遥控慢速飞行，室内或室外小型场地设计的飞机。 升降体由一系列以径向对称构造布置的轻型平面或薄型翼型表面（A1，A2，A3，A4）限定。 悬挂在由薄翼面（A1，A2，A3，A4）形成的空腔（O）内的是推力发生螺旋桨系统（C），其向上倾斜并且可以远程调节，以便改变推力角 在腔（O）内的向量用于转向。 飞行中的运动方向的提升，稳定性，转向和一般控制是在没有任何正式的机翼，方向舵，尾翼或控制面的情况下完成的。

公开(公告)号：EP1242279B1

公开(公告)日：2004-01-07

申请号：EP00990085.3

申请日：2000-12-20

Applicant: Institut de Recherche pour le Développement ( IRD)

Inventor： ASSELINE, Jean ,  DE NONI, George

IPC: B64C39/02 ,  B64C31/036 ,  B64D47/08

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: The invention concerns a small-size radio-controlled flying device propelled by a heat engine (20) with pusher propeller (10) for remote sensing, said device enabling short take-off and landing and a maximum flying speed of 34 Km/h. The device comprises a nacelle and a wing system, the nacelle (1) being a rigid three-wheeled carriage capable of being disassembled by denesting a more or less pyramidal jig with rear base (2) and front top (7), a lower plane (3) two lateral planes (4, 5) and an upper plane (6), the base being a single-piece welded element and comprising the engine, the propeller, a tank and the remote sensing unit, the top being a single-piece welded element, the lower plane and the two lateral planes comprising side members (11, 12) at least assembled at the base and at the top, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being arranged overlapping forward in the top and the wheels being low pressure tyres, the wing system (13) being a wing box flexible parafoil, said wing system being linked to the nacelle adjustable by two front suspension cables (17), two braking suspension cables (18) acting on the two flaps/wings.

公开(公告)号：EP1242279A1

公开(公告)日：2002-09-25

申请号：EP00990085.3

申请日：2000-12-20

Applicant: Institut de Recherche pour le Développement ( IRD)

Inventor： ASSELINE, Jean ,  DE NONI, George

IPC: B64C39/02 ,  B64C31/036 ,  B64D47/08

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: The invention concerns a small-size radio-controlled flying device propelled by a heat engine (20) with pusher propeller (10) for remote sensing, said device enabling short take-off and landing and a maximum flying speed of 34 Km/h. The device comprises a nacelle and a wing system, the nacelle (1) being a rigid three-wheeled carriage capable of being disassembled by denesting a more or less pyramidal jig with rear base (2) and front top (7), a lower plane (3) two lateral planes (4, 5) and an upper plane (6), the base being a single-piece welded element and comprising the engine, the propeller, a tank and the remote sensing unit, the top being a single-piece welded element, the lower plane and the two lateral planes comprising side members (11, 12) at least assembled at the base and at the top, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being arranged overlapping forward in the top and the wheels being low pressure tyres, the wing system (13) being a wing box flexible parafoil, said wing system being linked to the nacelle adjustable by two front suspension cables (17), two braking suspension cables (18) acting on the two flaps/wings.

公开(公告)号：EP3152630A4

公开(公告)日：2017-06-21

申请号：EP15806519

申请日：2015-06-09

Applicant: VAN CRUYNINGEN IZAK ,  VAN WART ROBERT

Inventor： VAN CRUYNINGEN IZAK ,  VAN WART ROBERT

IPC: H02G1/02 ,  G01R31/08 ,  G05D1/10

CPC classification number: B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/14 ,  G01R29/0878 ,  G01R31/085 ,  G01R31/40 ,  G05D1/101 ,  H02G1/02

Abstract: FIG. 1 shows airframe 10 with electromagnetic field sensor 12, adjustable reference electromagnetic field strength 14, comparator 16, parachute 18, parachute trigger 19, and inspection camera 20 inspecting a transmission line corridor containing towers 40, 42, and 44, phase conductors 46, 48, and 50, and shield wires 52 and 54. Reference electromagnetic field strength 14 is adjusted before the flight to set the minimum electromagnetic field strength before parachute trigger 19 deploys parachute 18. The reference electromagnetic field strength 14 corresponds to a radius, and thus virtual tunnel 22, outside of which airframe 10 cannot fly without deploying parachute 18, regardless of the state of the autopilot, GPS signal, or radio link.

Abstract translation: 图。 具体实施方式图1示出了具有电磁场传感器12，可调参考电磁场强度14，比较器16，降落伞18，降落伞触发器19和检查摄像机20的机身10，检查包含塔40,42和44，相导体46,48 和50以及屏蔽线52和54.在飞行之前调整参考电磁场强度14以在降落伞触发器19展开降落伞18之前设置最小电磁场强度。参考电磁场强度14对应于半径，并且因此虚拟 不管自动驾驶仪，GPS信号或无线电链路的状态如何，机身10在其外部不能飞翔而没有展开降落伞18。

公开(公告)号：EP2521670B1

公开(公告)日：2014-03-19

申请号：EP09760232.0

申请日：2009-10-28

Applicant: Swissavia

Inventor： BERTHIER, Bernard

IPC: B64C31/036 ,  B64C39/02

CPC classification number: B64C31/036 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107

公开(公告)号：WO2017134658A1

公开(公告)日：2017-08-10

申请号：PCT/IL2017/050118

申请日：2017-02-01

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ZIVAN, Lior ,  DEKEL, Guy

IPC: B64D1/18

CPC classification number: B64D1/18 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/107 ,  B64C2201/12

Abstract: An aerial spraying assembly is provided, including a manifold member, having a plurality of spray nozzles for enabling aerial spraying of a fluid material therefrom, and, a support structure including a base structure and at least one non-rigid support for supporting the manifold member in spaced spatial relationship with the base structure via the non-rigid support, the base structure being fixedly mountable to an aerial platform. Also provided is an aerial spraying assembly configured for selectively deploying between a compact configuration and a deployed configuration, including a manifold member, including a plurality of spray nozzles for enabling aerial spraying of a fluid material therefrom at least in the deployed configuration, the manifold member being suspendable from a base structure via at least one non-rigid support at least during aerial spraying, the base structure being fixedly mountable to an aerial platform, and, wherein in the compact configuration the aerial spraying assembly is circumscribed by an imaginary geometrical envelope, and wherein in the deployed configuration, at least a part of the aerial spraying assembly is outside of the imaginary geometrical envelope. Also provided is an aerial platform including such aerial spraying assemblies. Also provided is an airborne spraying system including a plurality of such aerial platforms, and a central controller for controlling operation of the aerial platforms to spray a desired ground zone with the fluid material. A corresponding method for aerial spraying a fluid material over a desired ground zone, is also provided.

Abstract translation: 提供了一种空中喷涂组件，其包括歧管构件，该歧管构件具有多个喷射喷嘴以用于从中喷射流体材料，以及支撑结构，该支撑结构包括基底结构和至少一个非基底结构 - 刚性支撑件，用于通过非刚性支撑件将歧管构件支撑在与基座结构间隔开的空间关系中，基座结构可固定地安装到空中平台。 还提供了一种空中喷涂组件，该空气喷涂组件被配置用于在紧凑构型和展开构型之间选择性地展开，所述展开构型包括歧管构件，所述歧管构件包括多个喷射喷嘴，所述多个喷射喷嘴用于至少在展开构型下从其空中喷射流体材料， 至少在空中喷涂期间，所述基础结构可固定地安装到高空平台，并且其中在紧凑构型中，所述空中喷涂组件由假想的几何外壳包围， 并且其中在展开配置中，所述空中喷涂组件的至少一部分位于所述假想几何包络的外部。 还提供了包括这种空中喷涂组件的空中平台。 还提供了包括多个这种高空平台的空中喷洒系统，以及用于控制高空平台的操作以用流体材料喷洒期望的地面区域的中央控制器。 还提供了用于在期望的地面区域上空气喷射流体材料的相应方法。

公开(公告)号：WO2017013137A1

公开(公告)日：2017-01-26

申请号：PCT/EP2016/067217

申请日：2016-07-19

Applicant: DCNS

Inventor： MORESVE, Julien, Pierre, Guillaume

IPC: B64C25/68 ,  B64F1/02

CPC classification number: B64F1/025 ,  B64C25/68 ,  B64C2201/107 ,  B64C2201/182 ,  B64C2201/187

Abstract: Ce système de récupération d'un aéronef télépiloté (1), notamment sur une plateforme navale (2), est caractérisé en ce que l'aéronef comporte des moyens (3, 4) en forme de crochet adaptés pour accrocher un organe de guidage (6), relié à la plateforme et adapté pour guider l'aéronef (1) vers un tapis de chute (7) placé sur une zone d'appontage correspondante (8) de la plateforme.

Abstract translation: 用于检索远程驾驶飞机（1）的系统，特别是在海军平台（2）上的特征在于，该飞行器包括钩形装置（3,4），其被设计成接合引导装置（6），该引导装置 平台并且被设计成将飞机（1）引向位于平台的相应着陆区域（8）上的着陆垫（7）。

公开(公告)号：US09738383B2

公开(公告)日：2017-08-22

申请号：US15391517

申请日：2016-12-27

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D17/00 ,  B64C39/02 ,  B64D17/80 ,  B64C1/26

CPC classification number: B64C39/024 ,  B64C1/26 ,  B64C3/56 ,  B64C2201/104 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203 ,  B64D17/00 ,  B64D17/80

Abstract: A remotely controlled or autonomously controlled UAV is disclosed. The UAV has both wings and a deployable parachute to enable both fixed wing flight and paraglider flight. The UAV can fly at a higher speed to a mission area as a fixed wing craft, and loiter over the area as a powered paraglider. In some embodiments, the wings are jettisoned over the mission area and the UAV configured as a powered paraglider completes its mission. In other embodiments the UAV flies to the mission area as a fixed wing craft, deploys the parachute to loiter as a powered paraglider and then jettisons the parachute to fly under a fixed wing back to a base. The former embodiment cannot fly back to a base, they may be used to carry and deploy bombs or grenades, while the latter may be used for surveillance, deliver supplies or the like.

公开(公告)号：US09527596B1

公开(公告)日：2016-12-27

申请号：US14716785

申请日：2015-05-19

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D17/00 ,  B64C11/00 ,  B64C39/02 ,  B64C3/56

CPC classification number: B64D17/00 ,  B64C3/56 ,  B64C11/001 ,  B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203

Abstract: A remotely 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 may be flown under a parachute and guided by remote control, or the control module (fuselage) may be released from the parachute and extendable fixed wings deployed to enable the UAV to be flown as a fixed wing vehicle.

Abstract translation: 公开了遥控无人机。 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。 无人机可以在降落伞下飞行并由遥控器引导，或者控制模块（机身）可以从降落伞释放并且可伸展的固定翼部署以使无人机作为固定翼车辆飞行。