公开(公告)号：EP2414238A1

公开(公告)日：2012-02-08

申请号：EP10707317.3

申请日：2010-01-19

Applicant: DCNS

Inventor： AFFRE DE SAINT ROME, Ronan

IPC: B64F1/12 ,  F16B21/16

CPC classification number: F16B21/16 ,  B64C2201/182 ,  B64F1/125

Abstract: The invention relates to an anchoring harpoon intended in particular for an aircraft, capable of cooperating with an anchoring grate of a platform, comprising jack means including cylinder means containing mobile piston means provided with a rod that extends beyond the cylinder means, the free end of which includes a harpoon head (7) that is hooked in the grate and comprises retaining fingers (8, 13, 14) that can be moved between a retracted position and an active position by control means (9). The invention is characterised in that the means (9) for controlling the movements of the fingers comprise a control piston (18) which can slide inside the rod of the jack and which is associated with a bistable actuator (19) of the fingers, capable of moving between a retracted position and an active position in which the fingers are deployed with the application of successive pressure pulses in the jack means.

公开(公告)号：EP1952488A4

公开(公告)日：2011-10-05

申请号：EP06836088

申请日：2006-07-15

Applicant: PHYSICAL OPTICS CORP

Inventor： LEE KANG ,  FORRESTER THOMAS ,  JANNSON TOMASZ ,  KOSTRZEWSKI ANDREW ,  SAVANT GAJENDRA

IPC: H01R13/24 ,  B64C39/02 ,  G05D1/00

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/182 ,  H01R13/005 ,  H01R13/2421 ,  H01R35/04 ,  H01R39/64 ,  Y10T403/32606

公开(公告)号：EP2218642A2

公开(公告)日：2010-08-18

申请号：EP10250229.1

申请日：2010-02-11

Applicant: Aerovel Corporation

Inventor： McGeer, Brian T. ,  von Flotow, Andreas H.

IPC: B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/12

CPC classification number: B64F1/12 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64F1/125 ,  B64F1/28 ,  B64F5/00

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a weighted cable (2,3), and pulls it at low relative speed into a broad aperture ( l a ,Ψ a ) of a base apparatus (5). Continued translation of the aircraft may pull the cable clear of the apparatus, in which case it can continue in free flight and return for another retrieval attempt. Alternatively, the cable will be dragged along guiding surfaces (4) of the apparatus into and through a slot (6) or similar channel, until its free end is captured. The aircraft, having thus become anchored to the base station, is then pulled down by the cable into a receptacle (9). Guiding surfaces of the receptacle adjust the position and orientation of a probe (8) on the aircraft, while directing the probe to mate with a docking fixture. Once mated to the fixture, the cable can be released and stored aboard the aircraft; the aircraft can be automatically shut down; and fueling or other servicing can be completed through appropriate connectors in the docking fixture. The aircraft can remain docked as needed, and when desired, be automatically started and tested in preparation for launch. It can then be released into free flight. A full ground-handling cycle can thus accomplished with simple and economical apparatus. It can be used with low risk of damage, and only moderate piloting accuracy.

公开(公告)号：EP2025594A1

公开(公告)日：2009-02-18

申请号：EP06743478.7

申请日：2006-05-11

Applicant: Aerovision Vehiculos Aereos, S.L.

Inventor： TURRILLAS LAS HERAS, Arturo

IPC: B64F1/02 ,  B64C39/02

CPC classification number: B64F1/02 ,  B64C2201/182

Abstract: The invention relates to a device for recovering unmanned airborne vehicles comprising support means connected to the ground and retention means connected to the support means, it being possible for the device to occupy a non-operational position and an operational position in which the retention means are interposed in the path of the unmanned airborne vehicle. The support means consist of at least one inflatable element (1) comprising a part which, in the inflated position, has two vertical branches, and the retention means (5) are joined to the mentioned part of the at least one inflatable element (1) by sliding means (2), (4), (6), (7), such that the retention means (5), by the thrust of the unmanned airborne vehicle, move and at least partially surround the mentioned airborne vehicle, which is confined in the mentioned retention means.

Abstract translation: 本发明涉及一种用于恢复无人机载车辆的装置，包括连接到地面的支撑装置和连接到支撑装置的保持装置，该装置可能占据非操作位置和操作位置，在该位置中保持装置 插在无人机载路上。 所述支撑装置包括至少一个可充气元件（1），所述至少一个可膨胀元件（1）包括在膨胀位置具有两个垂直分支的部分，并且所述保持装置（5）与所述至少一个可充气元件（1 ）通过滑动装置（2），（4），（6），（7），使得保持装置（5）由无人驾驶飞行器的推力移动并且至少部分地围绕所提及的空中飞行器， 被限制在上述保留手段中。

公开(公告)号：EP1602576A3

公开(公告)日：2008-11-26

申请号：EP05090154.5

申请日：2005-05-30

Applicant: RAFAEL - ARMAMENT DEVELOPMENT AUTHORITY LTD.

Inventor： Rom, Hanan

IPC: B64C39/02 ,  B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/182 ,  B64F1/02

Abstract: A system (10) for slowing an air vehicle (12), including an independently supported aerodynamic drag device (14) designed so that, after contact is made between the flying air vehicle and the aerodynamic drag device (14), one or more parts of the aerodynamic drag device are carried along by the air vehicle (12) thereby decelerating the air vehicle (12), so that a majority of a kinetic energy dissipation of a combination of the air vehicle (12) and the aerodynamic drag device (14) is due to an aerodynamic drag of the aerodynamic drag device

公开(公告)号：EP1767453B1

公开(公告)日：2008-06-18

申请号：EP06121033.2

申请日：2006-09-21

Applicant: Honeywell International Inc.

Inventor： Horak, Dan T.

IPC: B64C39/02 ,  B64F1/04 ,  A63H27/14

CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

公开(公告)号：EP0629164A4

公开(公告)日：1995-07-12

申请号：EP93907455

申请日：1993-03-12

Applicant: SCHMITTLE HUGH J

Inventor： SCHMITTLE HUGH J

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).

公开(公告)号：KR101831679B1

公开(公告)日：2018-02-23

申请号：KR1020137000536

申请日：2011-05-03

Applicant: 에이에이아이 코포레이션

Inventor： 밀러,스티븐,더블유. ,  폭스,스티븐,제이. ,  쉴,그레이엄,더블유. ,  아스케,브라이언,에이.

IPC: B64F1/02 ,  B64C39/02 ,  F16F9/00 ,  F16F1/36 ,  F16F15/02

CPC classification number: B64F1/02 ,  B64C2201/182 ,  F41H11/02 ,  F41J13/00

Abstract: 항공기회복장치는포획장치와제 1 및제 2 버팀대쌍을포함한다. 제 1 및제 2 버팀대쌍은각각상부및 하부버팀대를포함한다. 제 1 버팀대쌍은상기버팀대쌍이상기항공기를포획하기위하여상기포획장치를개방위치에서지지하는제 1 위치로부터, 상기버팀대쌍이상기포획장치에상기항공기가충돌한이후에포획된상기항공기를보유하기위하여상기포획장치를폐쇄위치에서지지하는제 2 위치로움직인다. 제 2 버팀대쌍 또한상기제 1 위치로부터제 2 위치로움직인다. 일단이상기포획장치의각 상부영역또는하부영역과각각연결되고타 단이각 상부버팀대또는하부버팀대와각각연결되는에너지요소들은상기항공기의충돌력을흡수한다.

公开(公告)号：KR1020170040103A

公开(公告)日：2017-04-12

申请号：KR1020160125254

申请日：2016-09-29

Applicant: 인시투, 인크.

Inventor： 앤드류로이즈헤이즈 ,  제임스스테이텔러맥그류 ,  웨인데이비드굿리치 ,  제프리휴냅 ,  찰스로렌스거스리 ,  브래들리루이스슈릭 ,  달시린데이비슨 ,  피터조셉쿤즈 ,  롤프테오도르리스디크

IPC: B64C39/02 ,  B64D5/00 ,  B64D47/00 ,  B64C27/10 ,  B64C27/12 ,  B64D27/24

CPC classification number: B64D5/00 ,  B63B21/50 ,  B64C27/08 ,  B64C29/0025 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/182

Abstract: 무인항공기에대한공중발사및/또는회수, 그리고이와관련된시스템및 방법. 무인항공기(UAV) 시스템을작동하는대표적인방법은제1 다중로터운반항공기가제2 적재된항공기를하늘위로운반하고, 내장배터리로제1 항공기에전원을공급하면서제2 항공기를비행을위해분리시키는단계를포함한다. 방법은제1 항공기가제2 항공기를포획하기위해제2 항공기의비행경로에포획줄을위치시키는방법을추가로포함할수 있다.

Abstract translation: 空中发射和/或返回无人机，以及与之相关的系统和方法。 操作无人飞行器（UAV）系统的典型方法如下：第一多转子运输飞机运输第二拖运飞机的头顶，为内部电池运输飞机提供动力， 它包括。 该方法可以进一步包括一种方法，通过该方法，第一飞机将捕获物放置在第二飞机的飞行路径上以捕获第二飞机。

公开(公告)号：KR101681348B1

公开(公告)日：2016-11-30

申请号：KR1020117027894

申请日：2010-04-23

Applicant: 인시투, 인크.

Inventor： 길크리스트로버트3세 ,  스태퍼드존 ,  데니스브라이언디. ,  스미스알렌 ,  맥제이미 ,  슬리와스티븐엠. ,  슈릭브래들리 ,  휴즈로버트

IPC: B64F1/02 ,  A63H27/32

CPC classification number: B64F1/02 ,  B64C2201/182

Abstract: 무인항공기회수및 항공기회수후의동작제어시스템및 방법이본원에개시된다. 본발명의일 실시예에따른무인항공기를처리하는항공기회수시스템은베이스부분(102)과, 베이스부분에이동가능하게결합되는제1 단부(106) 및제1 단부반대편의제2 자유단부를갖는긴 항공기포획부재(104)를포함한다. 항공기포획부재는제1 부분(110)과, 제1 부분의말단단부의제2 부분(112)을포함하고비행중인무인항공기를도중포획하도록위치된다. 제1 부분및/또는제2 부분은대체로가요적이다. 상기시스템은항공기포획부재에작동가능하게결합되고항공기로부터의착륙력의적어도일부를수용하도록위치되는에너지포획및 소산조립체(108)를더 포함한다.

Abstract translation: 本文公开了用于恢复无人飞机并控制飞行器的恢复后运动的系统和方法。 根据本公开的一个实施例的用于处理无人飞行器的飞机恢复系统包括基部和细长的飞行器捕获构件，其具有可移动地联接到基部的第一端和与第一端相对的第二自由端。 飞机捕获构件包括在第一部分的远端处的第一部分和第二部分，并且定位成拦截飞行中的无人飞行器。 第一和/或第二部分通常是柔性的。 该系统还包括能量捕获和耗散组件，其可操作地联接到飞行器捕获构件并被定位成接收来自飞行器的着陆力的至少一部分。