公开(公告)号：EP2858898A4

公开(公告)日：2016-03-02

申请号：EP13832668

申请日：2013-06-07

Applicant: AEROVIRONMENT INC

Inventor： ANDRYUKOV OLEKSANDR

IPC: B64C39/00

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201

公开(公告)号：EP2838796A2

公开(公告)日：2015-02-25

申请号：EP13816392.8

申请日：2013-04-16

Applicant: Wintec Arrowmaker Inc.

Inventor： JONES, John, Charles ,  GRIGORYEV, Artem, Igorevich ,  ESPINOSA, Luis, Carlos

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

公开(公告)号：EP2720948A4

公开(公告)日：2015-02-11

申请号：EP11867771

申请日：2011-06-17

Applicant: SING ROBERT L

Inventor： SING ROBERT L

IPC: B64F1/22 ,  B64C13/18 ,  B64D9/00 ,  B64D45/00 ,  B64F1/28

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

公开(公告)号：EP2766260A1

公开(公告)日：2014-08-20

申请号：EP11874051.3

申请日：2011-10-12

Applicant: Saab AB

Inventor： DANIELSSON, Torkel

IPC: B64F1/02 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64C2201/201

Abstract: The present invention relates to a system and method for automatic launch and landing UAVs (Unmanned Aerial Vehicles). The system comprises a ground station adapted for automatic UAV launching and landing. The ground station comprises: means for communication with UAVs present within a range from the ground station; an arrangement adapted for launching UAVs and for capturing in-flight UAVs, said arrangement having at least one controllable arm; a computing unit arranged to compute a meeting point between the at least one controllable arm and one in-flight UAV based on data communicated between the UAV and the ground station by means of said means for communication; and a control unit arranged to control the at least one arm to capture an in-flight UAV at the meeting point or to launch one UAV. The system is characterized in that the control unit is arranged to control the at least one arm to move a UAV between the meeting point and at least one storage position.

公开(公告)号：EP2218642B1

公开(公告)日：2014-04-09

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 ,  B64F1/06

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 ,¨ 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：EP1963185A4

公开(公告)日：2012-04-04

申请号：EP06838485

申请日：2006-11-29

Applicant: ITT MFG ENTERPRISES INC

Inventor： PAGE GREGORY S

IPC: B64F1/10 ,  B64C39/02 ,  F42B15/36

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  F42B15/36

公开(公告)号：EP2046644B1

公开(公告)日：2011-10-05

申请号：EP07736228.3

申请日：2007-04-18

Applicant: ELBIT SYSTEMS LTD.

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.

公开(公告)号：EP2342129A1

公开(公告)日：2011-07-13

申请号：EP09822561.8

申请日：2009-10-20

Applicant: AAI Corporation

Inventor： MILLER, Stephen William

IPC: B64F1/04

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

Abstract: An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame.

公开(公告)号：EP2212198A1

公开(公告)日：2010-08-04

申请号：EP08845839.3

申请日：2008-10-31

Applicant: Raytheon Company

Inventor： KINSEY, Lloyd, E. ,  KRANKING, Patrick, D.

IPC: B64C29/02

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

公开(公告)号：EP1827972B8

公开(公告)日：2008-10-22

申请号：EP05813078.2

申请日：2005-11-30

Applicant: Israel Aerospace Industries Ltd.

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，其中执行反转操纵，使得飞机的背面朝向地面，并且飞机的底面背离地面。 在开始或完成这种机动之后，引起深度失速，并且飞机几乎垂直下降以落在其上侧，从而最小化撞击载荷或其下侧的损坏。 在构造成用于执行该方法的特定空气动力学布置中，可以在正常飞行期间收起的襟翼（24）以诸如在空气动力学上引起飞行器上的负俯仰力矩和深度失速的方式展开。