公开(公告)号：WO2006123048A1

公开(公告)日：2006-11-23

申请号：PCT/FR2006/001097

申请日：2006-05-16

Applicant: SAGEM DEFENSE SECURITE ,  SOUTIF, Christophe ,  TREMBLAIS, Anthony

Inventor： SOUTIF, Christophe ,  TREMBLAIS, Anthony

IPC: B64D25/00 ,  B64C39/02

CPC classification number: B64D25/00 ,  B64C39/024 ,  B64C2201/146 ,  B64C2201/185 ,  B64C2201/201 ,  B64D2201/00

Abstract: L'invention concerne un dispositif de contact d'un aéronef avec une aire de réception (100), comprenant au moins un sac gonflable (5) associé à des moyens d'admission et d'échappement (15) d'un fluide de gonflage et à des moyens de fixation (7) du sac (5) sous l'aéronef, une cloison (8) divisant le sac gonflable en un premier compartiment (9) auquel sont reliés les moyens d'admission et d'échappement et un deuxième compartiment (10) relié au premier compartiment par un organe de passage unidirectionnel (11) fixé à la cloison pour laisser passer le fluide de gonflage du premier compartiment vers le deuxième compartiment. L'invention a également pour objet un aéronef équipé d'un tel dispositif.

Abstract translation: 本发明涉及一种用于建立飞机和接收表面（100）之间的接触的装置。 本发明的装置包括：至少一个充气袋（5），其与用于充气流体的进入和排出装置（15）相关联，以及用于将袋（5）固定到飞行器的下侧的装置（7） （8），其将所述可充气袋分成具有连接到其的进排气装置的第一隔室（9）和通过固定的单向流动元件（11）连接到所述第一隔室的第二隔室（10） 以使得充气流体可以从第一隔室流到第二隔室。 本发明还涉及一种装有一个这种装置的飞行器。

公开(公告)号：WO2005042342A3

公开(公告)日：2006-06-29

申请号：PCT/US2004036349

申请日：2004-11-01

Applicant: INSITU GROUP ,  SLIWA STEVEN M ,  VON FLOTOW ANDREAS H ,  DENNIS BRIAN D

Inventor： SLIWA STEVEN M ,  VON FLOTOW ANDREAS H ,  DENNIS BRIAN D

IPC: B64D47/00 ,  B63H20060101 ,  B64C11/00 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/02 ,  B64D41/00 ,  B64F1/02 ,  F02K5/02 ,  H02J7/00

CPC classification number: B64C11/003 ,  A63H27/02 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/206 ,  B64D41/007 ,  F02K5/023 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/672

Abstract: Method and systems for starting propeller driven aircraft and other devices. A system in accordance with one embodiment of the invention includes a removable fixture (130) that is coupled to the propeller (120) and has at least one portion (131a) exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine (110) begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link (132) between the fixture and the propeller.

Abstract translation: 启动螺旋桨飞机和其他设备的方法和系统。 根据本发明的一个实施例的系统包括联接到螺旋桨（120）并且具有暴露于流动流以在发动机起动期间旋转螺旋桨的至少一个部分（131a）的可拆卸固定装置（130）。 发动机（110）开始翻转（例如在发动机起动和/或旋转高于阈值速率之后），该固定装置构造成与螺旋桨分离。 因此，系统可以包括夹具和螺旋桨之间的可释放的连杆（132）。

公开(公告)号：WO2005023642A3

公开(公告)日：2005-11-10

申请号：PCT/US2004004720

申请日：2004-02-19

Applicant: AAI CORP ,  MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

Inventor： MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

IPC: B64B20060101 ,  B64B1/00 ,  B64C3/56 ,  B64C39/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract translation: 提供了一种便携式无人飞行器和发射器系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于容纳发射气体的发射气体储存器; 发射管，可操作地连接到发射气体储存器并且具有定位在飞行器的压力管中的自由端; 位于发射管内的自由活塞; 和一个自由活塞止动件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中并且迫使自由活塞从初始位置移动到自由活塞通过自由活塞止挡而停止的终点位置。

公开(公告)号：WO2005014390A2

公开(公告)日：2005-02-17

申请号：PCT/US2004/001033

申请日：2004-01-17

Applicant: THE INSITU GROUP ,  DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

Inventor： DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

IPC: B64B

CPC classification number: B64F1/02 ,  B63B27/26 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了组装，发射，恢复，拆卸，捕获和存储无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞行器部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：WO2004106156A1

公开(公告)日：2004-12-09

申请号：PCT/GB2004/002209

申请日：2004-05-20

Applicant: QINETIQ LIMITED ,  KELLEHER, Christopher, Charles

Inventor： KELLEHER, Christopher, Charles

IPC: B64C37/02

CPC classification number: B64C37/02 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/101 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/201 ,  B64D5/00

Abstract: A heavier-than-air air vehicle (1), particularly a long endurance, solar powered, unmanned aerial vehicle (UAV) intended for "perpetual" flight within the stratosphere, is carried to its operational altitude suspended on a tether (14) from a helium balloon (16). The tether is attached at or towards a tip of the UAV's wing (3) so that it is carried in effectively a 90° banked attitude. At the desired altitude the UAV's powerplant is started and it flies on its tether in an upwardly-spiralling path relative to the balloon until a level or near level attitude is attained, when the tether is released and the UAV is permitted to assume free flight.

Abstract translation: 一架重型空中飞行器（1），特别是用于在平流层内“永久”飞行的长寿命的太阳能无人驾驶飞行器（UAV）被运载到悬挂在系绳（14）上的操作高度 氦气球（16）。 系绳连接在无人机翼（3）的尖端处或朝向无人机翼（3）的尖端，使得其有效地承载90度的组合姿态。 在所需的高度，UAV的动力装置启动，并且相对于气球以相对于气球的向上螺旋方式飞行，直到达到水平或近似水平的姿态时，系绳被释放并且UAV被允许进行自由飞行。

公开(公告)号：WO2004060743A2

公开(公告)日：2004-07-22

申请号：PCT/US2003/039332

申请日：2003-12-09

Applicant: UNIVERSITY OF FLORIDA ,  IFJU, Peter ,  LEE, Kyu-Ho ,  ALBERTANI, Roberto ,  MITRYK, Shawn, J. ,  BORIA, Frank, J. ,  ABDULRAHIM, Mujahid

Inventor： IFJU, Peter ,  LEE, Kyu-Ho ,  ALBERTANI, Roberto ,  MITRYK, Shawn, J. ,  BORIA, Frank, J. ,  ABDULRAHIM, Mujahid

IPC: B64B

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过简单地从管中释放微型飞行器而从管展开。

公开(公告)号：WO02032762A2

公开(公告)日：2002-04-25

申请号：PCT/US2001/031631

申请日：2001-10-11

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：EP3157811B1

公开(公告)日：2018-08-29

申请号：EP14898651.6

申请日：2014-07-31

Applicant: SZ DJI Technology Co., Ltd.

Inventor： WANG, Mingxi ,  LIN, Yuan ,  LI, Hongju

IPC: B64C39/02 ,  H02J7/00

CPC classification number: B60S5/06 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/182 ,  B64C2201/201 ,  H02J7/0045

Abstract: A unmanned aerial vehicle (UAV) base station for automated battery pack exchange and methods for manufacturing and using the same. The UAV base station includes a battery-exchange system disposed within a housing having a top-plate. The housing contains a battery array having a plurality of UAV battery packs and a mechanical mechanism for automatically removing an expended battery pack from a UAV that lands on the top-plate and replacing the expended battery pack with a charged battery pack. Thereby, the UAV base station system advantageously enables extended and autonomous operation of the UAV without the need for user intervention for exchanging UAV battery packs.

公开(公告)号：EP3253654A4

公开(公告)日：2018-07-11

申请号：EP16746225

申请日：2016-01-28

Applicant: AIROBOTICS LTD

Inventor： KRAUSS RAN ,  KLINER MEIR

IPC: B64F1/00 ,  B64F1/02 ,  B64F1/12 ,  B64F1/18 ,  G05D1/10 ,  H04B7/185

CPC classification number: B64F1/00 ,  B64C39/024 ,  B64C2201/066 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/02 ,  B64F1/12 ,  B64F1/18 ,  G05D1/102

Abstract: A system for homing and recharging an unmanned vehicle comprises a plurality of homing layers operative along the radius of an imaginary circle that has the homing target at its center, each homing layer consisting of a sub-system provided with location means of increasing accuracy relative to that of a sub-system that operates along said radius farther away, from the center of said circle.

公开(公告)号：EP3330176A1

公开(公告)日：2018-06-06

申请号：EP17203694.9

申请日：2017-11-27

Applicant: The Boeing Company

Inventor： NEWMAN, Daniel I.

IPC: B64C27/08 ,  B64C1/30 ,  B64C27/50 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C1/30 ,  B64C27/08 ,  B64C27/50 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/201 ,  B64D9/003

Abstract: An aerial vehicle includes one or more rotors and a cargo container. The one or more rotors are configured to propel the aerial vehicle. The cargo container defines a cargo volume and is configured to travel with the aerial vehicle during propulsion by the one or more rotors. The cargo container is further configured to contain, at least, the one or more rotors, when the aerial vehicle is not configured for moving cargo.