公开(公告)号：WO2006059324A1

公开(公告)日：2006-06-08

申请号：PCT/IL2005/001276

申请日：2005-11-30

Applicant: ISRAEL AIRCRAFT INDUSTRIES LTD. ,  SIRKIS, Omri

Inventor： SIRKIS, Omri

IPC: B64C9/18 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

Abstract translation: 提供了一种用于着陆固定翼飞机的方法，其中执行反演机动，使得飞机的背面面向地面，并且飞机的下侧面向远离地面。 在开始或完成这个机动之后，引起深度失速，飞机几乎垂直下降，降落在其上侧，从而最小化其下侧的冲击载荷或损坏。 在配置用于执行该方法的特定空气动力学配置中，可以以正常飞行中的方式存放的翼片（24）以空气动力学方式在飞行器和深度档位上引起负俯仰时刻。

公开(公告)号：WO2005032939A1

公开(公告)日：2005-04-14

申请号：PCT/AT2004/000327

申请日：2004-09-28

Applicant: AUTHERITH, Franz

Inventor： AUTHERITH, Franz

IPC: B64C27/20

CPC classification number: B64C27/20 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/185 ,  B64D2201/00

Abstract: Das „ A F O " ist gekennzeichnet durch das neuartiges System der Bauart wie beschrieben , und das A F O senkrecht über Grund und Wasser abheben und landen lassen ( Fig. 1 bis Fig. 5 ), dadurch wird die Flugsicherheit und Effizienz gegenüber den bekannten und herkömmlichen Luftfahrzeugen jeder Bauart wesentlich verbessert. Die aerodynamischen Komponenten mit Auswirkungen sind ein wesentlicher Faktor und wirken bei einer sinnvollen A F O Konstruktion ( Fig. 2 ) begünstigend , z.B. Autorotation zum Landen - Notlanden , bessere Stabilität bei Aktion und Reaktionskräften , der Bodeneffekt hebt zusätzlich den A F O Körper, wenig Rezirkulation da der Rotorabwind (downwash) durch den umfassenden A F O Körper ( Fig. 1 ) eingegrenzt ist. Bei einer Hybriden Konstruktion ( Fig. 3 ) wird der Luftschiffteil abhebefähig so konstruiert , dass der statische Aufhieb erst durch die dynamische Auftriebsunterstützung des A F O Systems erfolgt und somit das Hybride Luftschiff exakter und schneller manövrierbar wird. Die Machbarkeit ist gegeben und kann mit dem derzeitigen Stand aller bekannten Techniken sowie auch den bekannten und verfügbaren Mitteln ohne weiteres gebaut werden. Alle die beschriebenen Möglichkeiten sind vom kleinsten Modell bis zu den größten kommerziell einsetzbaren Luftfahrzeugen und Raumfahrzeugen anwendbar ( Fig. 1 ).

Abstract translation: 所述“AFO”作为由类型的新颖的系统来描述的特征，并且AFO起降垂直地上和水空白（图1至图5），其特征在于飞行安全和效率相对于已知的和常规的飞机，每 设计显著改善。 具有效果的气动组件是一个主要因素，并采取行动以有意义的A Fø结构（图2）有利于，例如 自转着陆 - 紧急降落，在地面效应作用力和反作用力改善的稳定性也增强了A FÒ体，小的再循环由于转子下洗（下洗）由综合A Fö体为界（图1）。 在飞艇部分的混合结构（图3）被构造abhebefähig使静Aufhieb仅通过支撑A F O系统的动态升力发生，因此，混合飞船精确，快速回旋是。 可行性，并给出可以与所有已知技术的现状以及事不宜迟知名的和可用的手段来建立。 描述的所有操作都是，从最小到最大的模型可以商购用于飞机和空间飞行器适用（图1）。

公开(公告)号：US20180065745A1

公开(公告)日：2018-03-08

申请号：US15698341

申请日：2017-09-07

Applicant: Flytrex Aviation Ltd.

Inventor： Yariv BASH ,  Amit REGEV ,  Vadim ZLOTNIK

IPC: B64C39/02 ,  B64D17/80 ,  B64D31/04 ,  B64D31/06

CPC classification number: B64C39/024 ,  B64C2201/185 ,  B64D17/80 ,  B64D31/04 ,  B64D31/06

Abstract: A navigation termination system of an unmanned vehicle (UV) is provided. The system includes a plurality of sensors connected to the UV and configured to detect motion of the UV; a power supply configured to power the movement of the UV; a processing circuitry; and a memory, the memory containing instructions that, when executed by the processing circuitry, configure the system to: determine, based on sensory signals captured by the plurality of sensors, a navigation termination event; and disrupt a connection between the power supply and a motion mechanism of the UV when the navigation termination event occurs.

公开(公告)号：US20180050805A1

公开(公告)日：2018-02-22

申请号：US15556649

申请日：2016-03-10

Applicant: KAPI electronics GmbH

Inventor： Holger Kalinka

IPC: B64D17/72 ,  B64D17/80 ,  B64D45/00

CPC classification number: B64D17/72 ,  B64C39/024 ,  B64C2201/185 ,  B64D17/80 ,  B64D25/12 ,  B64D45/00 ,  B64D2045/0085

Abstract: The invention relates to a method and a device for an intelligent parachute rescue system for manned and unmanned aerial vehicles (14), wherein no pyrotechnic propellants are used, but compressed air (4a) extracted from a pressure bottle (4).

公开(公告)号：US20170225792A1

公开(公告)日：2017-08-10

申请号：US15503089

申请日：2015-08-11

Applicant: DroneTech Studio, LLC

Inventor： Liang Wang ,  Daniel Joseph Bodenstein ,  Ryan Michael Welsh ,  Kevin Ian McWilliams

IPC: B64D17/70 ,  B64D17/80 ,  B64C39/02

CPC classification number: B64D17/70 ,  B64C39/024 ,  B64C2201/185 ,  B64D17/80

Abstract: Various embodiments of the present disclosure relate to a parachute deployment system for an unmanned aerial vehicle (UAV). In some examples, the parachute deployment system includes a base attached to the unmanned aerial vehicle, a deployment tray mechanically connected to the base, an acceleration mechanism for propelling the deployment tray away from the base, a parachute cover releasably secured over the deployment tray, a parachute stowed between the deployment tray and the parachute cover, and a triggering mechanism. Upon activation of the triggering mechanism, the parachute cover is released and the deployment tray is propelled away from the base, which rapidly deploys the parachute away from the UAV.

公开(公告)号：US09716862B1

公开(公告)日：2017-07-25

申请号：US13668397

申请日：2012-11-05

Applicant: The Boeing Company

Inventor： Joseph Wilbur Evans

IPC: H04N7/18

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/082 ,  B64C2201/088 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/185 ,  H04N7/185

Abstract: Systems and methods for capturing situational awareness information are provided. The systems and methods include a portable aircraft configured to obtain situational awareness information. The portable aircraft includes a body including deployable wings, a stability device coupled to the body, the stability device including deployable tail fins, a propulsion device configured to propel the portable aircraft aloft, a capture device configured to selectively capture situational information, and a communications device configured to transmit captured situational information to a ground based receiver.

公开(公告)号：US20170101180A1

公开(公告)日：2017-04-13

申请号：US15391517

申请日：2016-12-27

Applicant: Richard D. Adams

Inventor： Richard D. Adams

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

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：US09611044B2

公开(公告)日：2017-04-04

申请号：US15111147

申请日：2015-10-12

Applicant: Skycat Oy

Inventor： Henri Hiisilä

IPC: B64D17/00 ,  B64D19/00 ,  B64D17/70 ,  B64D1/12 ,  B64D25/00 ,  B64C39/02 ,  B64D17/64

CPC classification number: B64D17/70 ,  B64C39/024 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/185 ,  B64D1/04 ,  B64D1/12 ,  B64D7/08 ,  B64D17/64 ,  B64D25/00 ,  F41A19/58 ,  F41B7/00 ,  F41F1/00

Abstract: The object of this invention is a method to shoot an object from a flying apparatus. Into an flying apparatus, into certain part of it, like a container that consists at least of a bottom and a shell a spring will be placed, like a push spring that has been loaded in a tense state and that is locked in this position using a fixing organ and further there will be put as an extension of the spring an object to be shot out from the flying apparatus. The fixing organ is thread, metal cord, bar, strip, rope, line, or some combination of these and tension strength (T) is greater than the tension load of the push force (F) to the mentioned fixing organ. the tension strength (T) of the fixing organ is weakened to be less than the mentioned tension load by heating, burning, or melting the mentioned fixing organ by electric energy when the fixing organ breaks, the spring expands into the direction of the object and the push force (F) pushes the object out of the container and off the flying apparatus. The apparatus that is used in the present method is also an object of the invention.

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：US20120175468A1

公开(公告)日：2012-07-12

申请号：US13026061

申请日：2011-02-11

Applicant: Eric Zerof

Inventor： Eric Zerof

IPC: B64C13/20 ,  B64C13/18 ,  H04N7/18 ,  G05D1/00 ,  B64D17/80 ,  B64D1/16 ,  B64D1/18

CPC classification number: B64D1/16 ,  A62C3/0228 ,  A62C3/0242 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/145 ,  B64C2201/185 ,  G05D1/101

Abstract: A system for delivering cooling water to building roofs by means of drone aircraft is disclosed. Control systems for navigation and precisely targeting a water spray are disclosed.

Abstract translation: 公开了一种通过无人驾驶飞机将冷却水输送到建筑物屋顶的系统。 公开了用于导航和精确瞄准喷水的控制系统。