公开(公告)号：EP3147210A2

公开(公告)日：2017-03-29

申请号：EP16190742.3

申请日：2016-09-27

Applicant: Ewatt Technology Co., Ltd.

Inventor： ZHAO, Guocheng ,  LUO, Wei ,  QI, Pengcheng

IPC: B64C27/04 ,  B64C27/82 ,  B64C39/02 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08

CPC classification number: B64D33/02 ,  B64C27/82 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/141 ,  B64C2201/146 ,  B64D27/08 ,  B64D33/06 ,  B64D33/08 ,  B64D2033/0246 ,  B64D2033/028

Abstract: The present invention discloses an unmanned helicopter, and belongs to the technical field of unmanned aerial vehicles. The unmanned helicopter includes an air inlet system, an exhaust system, a cooling system and a dynamic balance system. The air inlet system is fixed on a second side; the exhaust system is fixed on a third side; and the cooling system is fixed on a first side, and the dynamic balance system is fixed on a tail. The airflow at the outside of the unmanned helicopter flows into the air inlet system smoothly, quickly and efficiently under the action of its own flow velocity relative to the unmanned helicopter, therefore the technical problem in the prior art that the air entering the fuselage with a unit volume is burnt insufficiently, which generates adverse effects on the normal flight of the unmanned helicopter, is solved.

Abstract translation: 本发明公开了一种无人直升机，属于无人驾驶飞行器技术领域。 无人直升机包括进气系统，排气系统，冷却系统和动平衡系统。 进气系统固定在第二侧; 排气系统固定在第三侧; 冷却系统固定在第一侧，动平衡系统固定在尾部。 无人直升机外部的气流在相对于无人驾驶直升机的自身流速的作用下，平稳，快速而有效地流入，因此现有技术中的技术问题是空气进入机身的空气 单位体积燃烧不足，对无人直升机的正常飞行产生不利影响，得到解决。

公开(公告)号：EP3107807A1

公开(公告)日：2016-12-28

申请号：EP15704564.2

申请日：2015-02-17

Applicant: IAT 21 Innovative Aeronautics Technologies GmbH

Inventor： SCHWAIGER, Meinhard

IPC: B64C3/38 ,  B64C3/56 ,  B64C29/00 ,  B64C39/00 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/56 ,  B64C27/026 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026 ,  B64D2211/00

Abstract: The invention relates to an aircraft comprising a fuselage (1), a plurality of propeller units (3) that can pivot in relation to the fuselage (1), and wings (5) that can pivot at least partially in relation to the fuselage (1) and independently of the propeller units (3).

Abstract translation: 本发明涉及一种飞机，其包括机身（1），可相对于机身（1）枢转的多个螺旋桨单元（3）和能够相对于机身至少部分地枢转的翼（5） 1）并且独立于螺旋桨单元（3）。

公开(公告)号：EP2914490A1

公开(公告)日：2015-09-09

申请号：EP13811348.5

申请日：2013-10-22

Applicant: AIRBUS DEFENCE AND SPACE GMBH

Inventor： STEINWANDEL, Jürgen ,  STAGLIANO, Florian ,  VAN TOOR, Jan

IPC: B64C39/02 ,  B64D27/02 ,  B64D27/24

CPC classification number: F02D29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/16 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

Abstract: The invention relates to an unmanned aircraft (10), the drive (12) of which comprises an internal combustion engine (28) designed as a diesel and/or kerosene engine and having a charging device (30) for charging the engine. In particular a hybrid drive (32), more especially a parallel hybrid drive, is provided as the drive (12).

公开(公告)号：EP1713689B1

公开(公告)日：2012-08-01

申请号：EP04821333.4

申请日：2004-03-25

Applicant: The Insitu Group

Inventor： MCGEER, Brian T. ,  ROESELER, Cory ,  VON FLOTOW, Andreas

IPC: B64F1/06 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft (150) can be launched from an apparatus that includes a launch carriage (120) that moves along a launch axis. A gripper (180) carried by the launch carriage can have at least one grip Portion (181) in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the fuselage of the aircraft as the launch carriage (120) decelerates, releasing the aircraft (150) for takeoff.

公开(公告)号：EP2196392A2

公开(公告)日：2010-06-16

申请号：EP09172360.1

申请日：2009-10-06

Applicant: Honeywell International Inc.

Inventor： Annati, Richard E. ,  O'Brien, Patrick L.

IPC: B64C27/20 ,  B64C39/02 ,  B64D27/24

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64D27/24 ,  Y02T50/64

Abstract: A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine (210), an electric motor (220) that comprises a motor generator, a motor drive (222) and a battery (224). The motor drive and battery are integrated into the aerial vehicle and provide power to the ducted fan aerial vehicle. The electric motor may comprise a ring motor generator. In operation, this dual propulsion system serves as a weight-efficient option to allow for two sources of power on a ducted fan unmanned aerial vehicle.

Abstract translation: 提供了一种用于垂直起飞和降落管道风扇飞行器的推进系统，该推进系统包括内燃机（210），电动机（220），其包括电动发电机，电动机驱动器（222）和 电池（224）。 电机驱动器和电池集成到飞行器中，并为管道风扇飞行器提供电力。 电动机可以包括环形电动发电机。 在运行中，这种双推进系统作为一种重量选择，允许在管道式风扇无人机上使用两个电源。

公开(公告)号：EP1687200A2

公开(公告)日：2006-08-09

申请号：EP04810203.2

申请日：2004-11-01

Applicant: The Insitu Group, Inc.

Inventor： SLIWA, Steven, M. ,  VON FLOTOW, Andreas, H. ,  DENNIS, Brian, D.

IPC: B63H1/00

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: Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine 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 between the fixture and the propeller.

公开(公告)号：EP1476354A1

公开(公告)日：2004-11-17

申请号：EP03713175.2

申请日：2003-02-19

Applicant: Singapore Technologies Aerospace Ltd

Inventor： BARRETT, Ronald, Martin

IPC: B64C29/02 ,  B64C39/02 ,  B64C39/06

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment (12) and a lower fuselage segment (14) that extend in opposite directions from a rotor guard assembly (16). A rotor (52) rotates within the rotor guard assembly (16) between the fuselage segments(12, 14). Plural turning vanes (28) extend from the rotor guard assembly (16) beneath the rotor (52). Moreover, plural grid fins (26) extend radially from the lower fuselage segment (14) below the turning vanes (28). The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins (26).

公开(公告)号：EP0861776B1

公开(公告)日：2002-11-27

申请号：EP97118254.8

申请日：1993-06-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hanson, Bruce D. ,  Kohlhepp, Frederick W. ,  Millea, Vincent F. ,  Cycon, James P.

IPC: B64C27/12 ,  B64D35/04

CPC classification number: B64C27/10 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025 ,  F16D3/06 ,  F16D3/185

公开(公告)号：EP1255673A1

公开(公告)日：2002-11-13

申请号：EP01907770.0

申请日：2001-02-13

Applicant: Bertin Technologies

Inventor： LEPRETRE, Marc ,  CHASTANG, Georges

IPC: B64C39/02 ,  B64C27/20

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud (40) integral with a cylindrical fairing (16) wherein rotates a propeller (10) powered by an engine (12) housed in a fuselage (18) secured to the fairing (16) with radial arms (28) and straightening vanes (30).

公开(公告)号：EP0629164B1

公开(公告)日：1999-05-26

申请号：EP93907455.5

申请日：1993-03-12

Applicant: SCHMITTLE, Hugh J.

Inventor： SCHMITTLE, Hugh J.

IPC: B64C3/38

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).