公开(公告)号：US09132916B2

公开(公告)日：2015-09-15

申请号：US13664323

申请日：2012-10-30

Applicant: The Boeing Company

Inventor： Mark Hanna ,  David R. Poling

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/082 ,  B64C2201/126 ,  B64C2201/182 ,  B64C2201/206

Abstract: An aircraft system incorporates a first aircraft having a grappling device including a first gripper with a first actuator and a second gripper with a second actuator. The first gripper and the second gripper are movable between an open and a closed position to engage a hooking device and pivot together to change a capture angle. A first controller receives a command and operates the actuators in response to open and close the first and second grippers of the grappling device. The controller also receives a second command and operates the first and second actuators to pivot the grippers and provide grappling at a range of capture angles. A second aircraft, which may be a UAV, incorporates the hooking device. The hooking device includes a ring rotatable from the surface and a third actuator to rotate the ring between a stowed and an extended position.

Abstract translation: 飞行器系统包括具有抓斗装置的第一飞行器，该抓斗装置包括具有第一致动器的第一夹持器和具有第二致动器的第二夹持器。 第一夹持器和第二夹持器可在打开位置和关闭位置之间移动以接合钩挂装置并枢转在一起以改变捕获角度。 响应于打开和关闭抓斗装置的第一和第二夹持器，第一控制器接收命令并操作致动器。 控制器还接收第二命令并且操作第一和第二致动器以枢转夹持器并且在捕获角度范围内提供抓斗。 可能是UAV的第二架飞机结合了挂钩装置。 挂钩装置包括从表面可旋转的环和第三致动器，以在收起和伸出位置之间旋转环。

公开(公告)号：US20150115096A1

公开(公告)日：2015-04-30

申请号：US14564775

申请日：2014-12-09

Applicant: The Boeing Company

Inventor： Glenn T. Rossi

IPC: B64C27/26 ,  B64D5/00 ,  B64C29/02 ,  B64C39/00 ,  B64C39/02

CPC classification number: B64C27/26 ,  B64C27/28 ,  B64C29/0033 ,  B64C29/02 ,  B64C37/02 ,  B64C39/003 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/206 ,  B64D5/00

Abstract: A compound rotorcraft including a rotary wing aircraft having a fuselage and at least one rotor and a fixed-wing aircraft coupled to the rotary wing aircraft, wherein the rotary wing aircraft can fly on the rotor or the fixed-wing aircraft, and wherein the fixed-wing aircraft is detachable from the rotary wing aircraft to fly independently.

Abstract translation: 一种复合旋翼航空器，其包括具有机身的旋翼飞机和至少一个转子以及耦合到旋转翼飞行器的固定翼飞行器，其中所述旋翼飞机可以在所述转子或所述固定翼飞行器上飞行，并且其中所述固定 飞机可以从旋翼飞机上拆下来独立飞行。

公开(公告)号：US20120292444A1

公开(公告)日：2012-11-22

申请号：US13574457

申请日：2011-01-19

Applicant: Benoit Jaurand

Inventor： Benoit Jaurand

IPC: B64D1/10 ,  B64C1/22

CPC classification number: B64D1/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/201 ,  B64C2201/206

Abstract: The system comprises an outer container which is fixed, directly and fully, in the hold of the transport aeroplane (AC), and in which there is an inner container that can be moved longitudinally and brought from a first carrying position (AC) in which it is situated fully inside said outer container into a second off-loading position (P2), position (P2) in which it is longitudinally offset towards the rear of the aircraft (AC) so that a part of said inner container is then situated outside the transport aeroplane (AC).

Abstract translation: 该系统包括直接和完全固定在运输飞机（AC）的保持件中的外部容器，并且其中存在能够纵向移动并从第一运送位置（AC）带动的内部容器 它完全位于所述外部容器内部进入第二卸载位置（P2），位置（P2）中，其朝向飞行器（AC）的后部纵向偏移，使得所述内部容器的一部分然后位于外部 运输飞机（AC）。

公开(公告)号：US07789339B2

公开(公告)日：2010-09-07

申请号：US11475085

申请日：2006-06-27

Applicant: Geoffrey S. Sommer

Inventor： Geoffrey S. Sommer

IPC: B64D5/00

CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

公开(公告)号：US20080105112A1

公开(公告)日：2008-05-08

申请号：US11766343

申请日：2007-06-21

Applicant: Michael Grabmeier

Inventor： Michael Grabmeier

IPC: B64D1/12

CPC classification number: B64D1/12 ,  B64C2201/206

Abstract: A device for launching unmanned missiles from an aircraft with a pallet, on which at least one container is provided to receive a missile. The container has an upper container section that has a pylori for the suspended, detachable support of the missile. The container has a lower container section that is embodied as a support area for the missile.

Abstract translation: 用于从具有托盘的飞机发射无人导弹的装置，其上提供至少一个容器以接收导弹。 容器具有上部容器部分，其具有用于导弹的悬挂的可分离支撑件的幽门。 容器具有较低的容器部分，其被实施为导弹的支撑区域。

公开(公告)号：US20180257780A1

公开(公告)日：2018-09-13

申请号：US15454359

申请日：2017-03-09

Applicant: Jeffrey Sassinsky

Inventor： Jeffrey Sassinsky

IPC: B64D5/00 ,  B64C39/02 ,  G08G5/00 ,  B64D47/08 ,  B64D7/00 ,  F41H13/00 ,  F41B13/10 ,  F41H9/00 ,  F41H11/02

CPC classification number: F41H11/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/12 ,  B64C2201/182 ,  B64C2201/206 ,  B64D7/00 ,  B64D47/08 ,  B64F1/02 ,  F41B13/10 ,  F41H9/00 ,  F41H9/04 ,  F41H11/04 ,  F41H13/00 ,  F41H13/0012 ,  F41H13/0062

Abstract: The present invention is a device, system(s) and/or method(s) for disrupting, capturing, and/or disabling and unmanned aerial vehicle(s) in flight, on the ground, or preparing for flight that may or may not be under the control of the invention operator. In certain embodiments, the invention is supported and carried by an unmanned aerial vehicle that is controlled by a ground operator, a computer process and associate hardware, or any combination thereof. In other embodiments, the invention contains physical destruction devices such as projectiles, explosives, spikes, electric shock generators, etc. The invention is manipulated to track, intercept, capture, disrupt, disable and/or move a target unmanned aerial vehicle. In certain embodiments, the invention includes materials able to contain, at least in part, hazardous materials and/or conditions caused by the target unmanned aerial vehicle. In certain embodiments, the invention interfaces with external unmanned aerial vehicle detection/tracking systems. A unique design element in certain embodiments is the ability to limit the potential of the captured aerial vehicle escaping the device and/or falling to the ground. Another unique design element in certain embodiments is the ability of the invention to limit collateral damage caused by the captured unmanned aerial vehicle or apparatuses contained thereon. Another unique design element is the ability of the invention to interface with external unmanned aerial vehicle detection/tracking systems.

公开(公告)号：US10035597B2

公开(公告)日：2018-07-31

申请号：US15238200

申请日：2016-08-16

Applicant: Douglas Desrochers ,  David Desrochers

Inventor： Douglas Desrochers ,  David Desrochers

IPC: B64C25/00 ,  B64D1/08 ,  B64C39/02 ,  B64D17/80 ,  B64C1/30

CPC classification number: B64D1/08 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/206 ,  B64D1/10 ,  B64D1/12 ,  B64D17/38 ,  B64D17/80

Abstract: An unmanned aerial system (UAS) including a sonotube deployable multicopter (SDM) having a plurality of rotors for propulsion, a plurality of extension arms, and a central pivot device. Each extension arm supports at least one of the plurality of rotors. The central pivot device supports the plurality of extension arms radially extending from the central pivot device. Pivotal movement of a first arm-support structure of the central pivot device relative to a second arm-support structure of the central pivot device rotates a first pair of the plurality of extension arms in unison relative to a second pair of the plurality of extension arms. The pivotal movement is biased to rotate the plurality of extension arms from a compact configuration to an expanded configuration while the UAS is airborne. The SDM configured to be held inside a sonoshell in the compact configuration.

公开(公告)号：US20170369169A1

公开(公告)日：2017-12-28

申请号：US15375590

申请日：2016-12-12

Applicant: KOREA INSTITUTE OF SCIENCE AND TECHNOLOGY

Inventor： Taikjin LEE ,  Suk Woo NAM ,  Chang Won YOON ,  Hyun Seo PARK ,  Young Min JHON ,  Seok LEE ,  Min-Jun CHOI

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/206

Abstract: The present invention relates to an unmanned aerial vehicle system having a multi-rotor type rotary wing. The unmanned aerial vehicle system having a multi-rotor type rotary wing includes a first unmanned aerial vehicle, at least one second unmanned aerial vehicle, and a bridge that connects the first unmanned aerial vehicle and the at least one second unmanned aerial vehicle to be separable from each other, wherein the at least one second unmanned aerial vehicle is moveable by the first unmanned aerial vehicle in a state where the at least one second unmanned aerial vehicle is coupled to the first unmanned aerial vehicle by the bridge without being driven, and the at least one second unmanned aerial vehicle is separable from the first unmanned aerial vehicle which is in flight.

公开(公告)号：US09849983B2

公开(公告)日：2017-12-26

申请号：US15535431

申请日：2015-12-04

Applicant: ALFRED-WEGENER-INSTITUT

Inventor： Andreas Herber ,  Dirk Kalmbach ,  Ruediger Gerdes ,  Hans-Joerg Bayer

IPC: B64D3/02 ,  B64C39/02 ,  B64C3/16 ,  F41J9/10 ,  B64C1/00

CPC classification number: B64D3/02 ,  B64C3/16 ,  B64C39/022 ,  B64C2001/0045 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/206 ,  F41J9/10

Abstract: An aerodynamically shaped, active towed body includes a fuselage curved along its vertical and horizontal longitudinal plane. The fuselage has a unit chamber and a load chamber. A transverse plane of the fuselage is triangular, two upper corners being located on an upper face of the fuselage and a lower corner being located on a lower face of the fuselage. Each of two wings is subdivided into a small and a large segment. The small segment points downwards and is attached to the fuselage in a region of the lower corner and the large segment points upwards and is attached to the small segment. Each of the small segments comprise an additional load chamber. The towed body further includes a tail fin, rudders that are each adjustable by the control device and a coupling for the towing cable.

公开(公告)号：US20170297445A1

公开(公告)日：2017-10-19

申请号：US15132255

申请日：2016-04-19

Applicant: SHENZHEN FLYEAH INTELLIGENT TECHNOLOGY CO., LTD.

Inventor： Junxiong ZHENG ,  Daniel Yin LIU ,  Hongyu RAN

IPC: B60L11/18 ,  B64F1/36 ,  B64C39/02 ,  B64D5/00

CPC classification number: B64D5/00 ,  B60L53/14 ,  B60L53/37 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/206 ,  B64D2203/00

Abstract: A cone shaped docking and releasing mechanism provides rigid connection between a parent UAV and a sub UAV to form a spliced double unmanned aerial vehicle system with improved cruising duration ability by providing sub UAV battery with charging function. It comprises a parent UAV, a sub UAV and a docking mechanism with charging ports. The parent UAV and the sub UAV are connected with each other through the docking mechanism to form a double UAV system, the docking mechanism is a cone structure and comprises a charging output component connected with the parent UAV internal control system, a charging circuit connected with a sub UAV control system and a charging input component connected with the charging circuit.