公开(公告)号：WO2010031384A2

公开(公告)日：2010-03-25

申请号：PCT/DE2009/001286

申请日：2009-09-16

Applicant: GABLER MASCHINENBAU GMBH ,  VIERTEL, Christian ,  TENBERGEN, Martin

Inventor： VIERTEL, Christian ,  TENBERGEN, Martin

IPC: B64F1/06

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: Das Verfahren zum Starten einer Drohne (10) mittels eines die Startenergie aufbringenden Startkatapults (9) erfolgt derart, dass zunächst das Startkatapult (9) vor dem Starten ausgerichtet wird. Dabei ist das Startkatapult (9) mittels eines Sichtschutzes (4) verdeckt, wobei der Sichtschutz (4) erst nach dem Ausrichten und unmittelbar vor dem Starten zumindest teilweise entfernt wird.

Abstract translation: 由开始施加能量启动弹射器装置启动一个无人驾驶飞机（10）的方法，（9）是这样的，第一弹射器（9）之前开始对准。 在此，弹射器（9）通过可视屏幕（4）的装置被覆盖，其中筛选（4）对准之后，并立即启动之前至少部分地去除。

公开(公告)号：WO2008015663A1

公开(公告)日：2008-02-07

申请号：PCT/IL2007/000488

申请日：2007-04-18

Applicant: ELBIT SYSTEMS ELECTRO-OPTICS ELOP LTD. ,  KARIV, Amnon

Inventor： KARIV, Amnon

IPC: B64F1/02 ,  B64F1/04 ,  B64F1/08

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02

Abstract: A system for landing UAV's comprising a slingshot structure (25) that includes a central arm (26) and an axis means (45) installed along the central arm of the structure and wherein it enables the central arm to move around it in addition, the system comprises base means (50) connecting the axis means to a platform (20) at which the system is installable. The system also include a controlled pulling and braking means (55) that connects between lower end of the central arm of the structure and the platform upon which the system is installable and an assembly (35), essentially formed as a substantially "Y" shape part that is installable unto the top end of the central arm of the structure and a stretchable elastic means (30) installed in a stretched manner at a gap formed between the two arms of the assembly and set to connect with a landing UAV(15). At the landing phase, the controlled pulling and braking means of the system, essentially brakes the motion of the central arm of the structure that is propelled to revolve around the system's axis means, from a time that the UAV forms contact with the elastic means and with it propels the structure to move around the axis means.

Abstract translation: 一种用于着陆UAV的系统，其包括弹弓结构（25），该弹弓结构包括中心臂（26）和沿着所述结构的中心臂安装的轴线装置（45），并且其中使得所述中央臂能够围绕其运动， 系统包括将轴装置连接到可安装系统的平台（20）的基座装置（50）。 该系统还包括可控制的拉动和制动装置（55），其连接该结构的中心臂的下端和该系统可安装的平台以及基本上形成为基本上“Y”形的组件（35） 该部分可安装到该结构的中央臂的顶端，以及可拉伸的弹性装置（30），该伸缩弹性装置（30）以形成在组件的两个臂之间的间隙的方式安装，并设置成与着陆UAV（15）连接， 。 在着陆阶段，从无人机与弹性装置形成接触的时间起，系统的受控牵引和制动装置基本上制动被推进围绕系统轴装置旋转的结构的中心臂的运动， 随着它推动结构围绕轴线移动。

公开(公告)号：WO2007034468A1

公开(公告)日：2007-03-29

申请号：PCT/IL2005/001281

申请日：2005-11-30

Applicant: BlueBird Aero Systems Ltd. ,  NADIR, Ronen

Inventor： NADIR, Ronen

IPC: B64D17/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/80

Abstract: The disclosure provides a parachute release device which may include a connecting element capable of connecting to an aircraft and to a parachute and a locking mechanism capable of releasing the connecting element from the aircraft upon being actuated by an actuator, wherein the parachute may be connected to the connecting element by a multiplicity of points, wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator and wherein the device may be suitable for use in small weights aircrafts due to its small size and weight . The disclosure further provides a method for releasing a parachute from an aircraft, the method may include activating an actuator capable of releasing a locking mechanism, wherein the locking mechanism is adapted to release a connecting element from an aircraft upon being actuated, wherein the connecting element is adapted to connect a parachute and wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator.

Abstract translation: 本公开提供了一种降落伞释放装置，其可以包括能够连接到飞机和降落伞的连接元件，以及能够由致动器致动时能够从飞行器释放连接元件的锁定机构，其中降落伞可以连接到 所述连接元件由多个点组成，其中所述锁定机构适于阻止施加到所述致动器的力，并且其中所述装置由于其小的尺寸和重量而适合用于小型重量飞机。 本发明还提供了一种用于从飞行器释放降落伞的方法，所述方法可包括激活能够释放锁定机构的致动器，其中所述锁定机构适于在致动时从飞行器释放连接元件，其中所述连接元件 适于连接降落伞，并且其中所述锁定机构适于阻止施加在所述致动器上的力。

公开(公告)号：WO0232762A3

公开(公告)日：2004-01-08

申请号：PCT/US0131631

申请日：2001-10-11

Applicant: DRAPER LAB CHARLES S

Inventor： MARTORANA RICHARD T ,  ANDERSON JAMIE ,  SPEARING SIMON MARK ,  KESSLER SETH ,  APPLEBY BRENT ,  BERGMANN EDWARD ,  GEORGE SEAN ,  JACOBSON STEVEN ,  FLYER DONALD ,  DRELA MARK ,  KIRKOS GREGORY ,  MCFARLAND WILLIAM JR

IPC: B64C39/02 ,  F42B15/10 ,  B64C3/56

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly (10) is adapted for launching with, transit in, and deployment from an artillery shell (22). The flyer assembly (10) includes a jettisonable shroud (12) and a flyer (14). The flyer (14) is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer (14) is positionable within the shroud (12) with the flyer axis parallel to the shroud axis and the shell axis. The flyer (14) includes a body member disposed about the flyer axis, and a foldable wing assembly (20) mounted to the body member. THe wing assembly (20) is characterized by a plurality of nested wing segments (32) when the flyer is in the first state. THe wing assembly (20) is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly (10) is launched from an artillery cannon, and can thus reach a target quickly, without expending energy stored with theflyer. During launch, the flwyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along eht flyer axis.

Abstract translation: 传单组件（10）适用于从炮弹（22）发射，转运和展开。 传单组件（10）包括可喷射的护罩（12）和传单（14）。 飞翼（14）适于在处于第一状态时承受沿飞行器轴线的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单（14）可定位在护罩（12）内，飞翼轴线平行于护罩轴线和外壳轴线。 传单（14）包括围绕飞行器轴线设置的主体构件和安装到主体构件的可折叠翼组件（20）。 当翼片处于第一状态时，翼组件（20）的特征在于多个嵌套翼段（32）。 翼组件（20）可配置成展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件（10）从炮兵炮发射，并且因此能够快速地达到目标，而不会消耗与飞行器一起存储的能量。 在发射过程中，飞镖耦合到护罩上，以便在飞行器沿着飞行器轴线的加速期间将传单的一部分保持在张紧状态。

公开(公告)号：WO0232762A9

公开(公告)日：2003-02-20

申请号：PCT/US0131631

申请日：2001-10-11

Applicant: DRAPER LAB CHARLES S

Inventor： MARTORANA RICHARD T ,  ANDERSON JAMIE ,  SPEARING SIMON MARK ,  KESSLER SETH ,  APPLEBY BRENT ,  BERGMANN EDWARD ,  GEORGE SEAN ,  JACOBSON STEVEN ,  FLYER DONALD ,  DRELA MARK ,  KIRKOS GREGORY ,  MCFARLAND WILLIAM JR

IPC: B64C39/02 ,  F42B15/10 ,  B64C

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load an high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 机翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高温环境的高负载，并且可以承受大约16,000g的安装载荷。

公开(公告)号：US20180134412A1

公开(公告)日：2018-05-17

申请号：US15566603

申请日：2016-04-29

Applicant: Chung Kiak POH ,  Chung How POH

Inventor： Chung Kiak POH ,  Chung How POH

IPC: B64F1/12 ,  B64C39/02 ,  H02S20/30

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/02 ,  B64F1/222 ,  H02S20/30

Abstract: The present invention generally relates to a system and method of a docking system (1) for fixed wing unmanned aerial vehicle, or non-fixed wing unmanned aerial vehicle (2) such as rotorcraft, or combination thereof, comprising at least a docking and/or launching pad capable of being arranged in an array or staggered manner; said pad has a surface (6) for said vehicle docking and launching, said docking and launching surface (6) comprising moveable pads (31) which include electromagnets that can be energized to capture a docking vehicle (2); and another energy harvesting surface (4) has photovoltaic panel to harness solar energy to generate electricity or hydrogen fuel for a variety of on-board applications such as to charge said vehicle (2) and to power the docking system and providing a safe stowage and protected storage for the said vehicle (2).

公开(公告)号：US09957064B2

公开(公告)日：2018-05-01

申请号：US14707424

申请日：2015-05-08

Applicant: AAI Corporation

Inventor： Stephen W. Miller ,  Zachary J. Smith ,  Peter J. Helman

IPC: B64F1/06 ,  B64F1/02 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/025

Abstract: An unmanned aerial vehicle (UAV) platform includes a stationary base constructed and arranged to reside over a fixed location on a surface (e.g., a ground location, a ship's deck, a trailer or other vehicle, etc.). The UAV platform further includes a set of UAV interfaces constructed and arranged to interface directly with a UAV (e.g., a launcher, a net apparatus, etc.). The UAV platform further includes a turntable assembly which couples to the stationary base. The turntable assembly is constructed and arranged to couple to each UAV interface and control angular direction of that UAV interface over the fixed location. A method of operating a UAV platform includes deploying the UAV platform over a fixed location, preparing a UAV interface on a turntable assembly of the UAV platform, and rotating the turntable to control angular direction of the UAV interface over the fixed location.

公开(公告)号：US20170313442A1

公开(公告)日：2017-11-02

申请号：US15583226

申请日：2017-05-01

Applicant: CIRCOR AEROSPACE, INC.

Inventor： Russell S. SIRVIS ,  Christopher R. LOVASCO ,  Juan VASQUEZ ,  David W. GASS ,  Corey C. JORDAN ,  Liron DROR ,  John NELLIKUNNEL ,  Jeffrey HORNING ,  Christopher OLSEN

IPC: B64F1/06 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084

Abstract: An aerial vehicle launcher including a rail having a first end and a longitudinal axis and a piston movable in a passageway formed in the rail, the piston connected to a carriage by at least two elongate flexible members. The carriage having a support device for releasably engaging the aerial vehicle. Upon the carriage and the aerial vehicle approaching one end of the rail, the support device controllably disengaging the aerial vehicle, permitting the aerial vehicle to be launched. A device is connected to a pressurized gas source, the device controllably providing pressurized gas from the pressurized gas source to the passageway for drivingly moving the piston, the carriage, and aerial vehicle along the rail for launching the aerial vehicle. The device includes a reservoir for holding pressurized gas, the reservoir being a conduit, the pressurized gas in the reservoir providing the driving force for launching the aerial vehicle.

公开(公告)号：US20160347451A1

公开(公告)日：2016-12-01

申请号：US15113368

申请日：2015-01-27

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Michael Shepshelovich ,  Danny Abramov ,  Yonatan Klein

IPC: B64C39/02 ,  B64D43/02 ,  B64C15/12 ,  B64C3/14

CPC classification number: B64C39/024 ,  B64C3/14 ,  B64C13/16 ,  B64C15/12 ,  B64C29/00 ,  B64C2201/084 ,  B64C2201/104 ,  B64D43/02 ,  Y02T50/12

Abstract: Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated flow over the fixed wings and conditions of attached flow over the fixed wings. Such methods also include the step of using the operating map for guidance, causing the air vehicle to operate at least within a low Reynolds numbers range corresponding to the operating map, such as to avoid or minimize risk of causing the air vehicle to operate at conditions of separated flow over the fixed wings.

Abstract translation: 提供了用于操作具有固定翼的机动车辆的方法。 这样的方法包括提供与固定翼相关的迎角与雷诺数相关的操作图的步骤，包括在固定翼上分离的流动的条件以及固定翼上附着流的条件。 这种方法还包括使用操作图来进行引导的步骤，使得空中飞行器至少在对应于操作图的低雷诺数范围内操作，以避免或最小化导致飞行器在条件下操作的风险 分离流过固定翼。

公开(公告)号：US09470477B2

公开(公告)日：2016-10-18

申请号：US14281680

申请日：2014-05-19

Applicant: AeroVironment, Inc.

Inventor： Guan H Su ,  Marcos Henry Rodriguez

IPC: F41F3/00 ,  B64C39/02 ,  B64F1/06 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。