公开(公告)号：EP2601100A2

公开(公告)日：2013-06-12

申请号：EP11729582.4

申请日：2011-04-20

Applicant: Desaulniers, Jean-Marc (Joseph)

Inventor： Desaulniers, Jean-Marc (Joseph)

IPC: B64C39/02

CPC classification number: B64C29/00 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: The invention relates to a vertical take-off and landing gyropendular craft or drone device (FIG. 18) able to move around in the following different physical environments: in the air, on land, at sea, underwater or in space, comprising upper and lower propulsion units, equipped with an annular fairing accommodating a certain number of electronically slaved wing or gas-powered drive or propulsion units situated in the continuation of the axis of this device, mounted on 3-D swivels at the ends of a certain number of telescopic rods, for example set at 120° apart at the periphery of the platform and orientable about the three axes according to the plane of flight of the multimodal multi-environment craft, a vertebral structure by way of a 3-D articulated central body of solid or hollow cylindrical shape for forming a stabilized function of stabilizing, maintaining the position and heading, and of an inertial rotary disc platform equipped underneath with a cabin of hemispherical shape extending from the vertebral structure, accommodating a payload or a useful application, designed for various fields of application e.g. the sector of defence or civil security, so as to perform functions of search and rescue, exploration, navigation, transport, surveillance and telecommunications infrastructure deployment in free space.

公开(公告)号：EP2274204A4

公开(公告)日：2012-10-31

申请号：EP09741589

申请日：2009-05-07

Applicant: ENTECHO PTY LTD

Inventor： CHAPMAN GREG ,  KAWKA JAKUB ,  SCHLUNKE CHRISTOPHER KIM

IPC: B64C29/02 ,  B64C7/00 ,  B64C15/02 ,  B64C27/20 ,  B64C39/00 ,  B64D33/04 ,  F04D29/30

CPC classification number: B64C27/20 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108

公开(公告)号：EP2151379A3

公开(公告)日：2012-04-11

申请号：EP09161737.3

申请日：2009-06-02

Applicant: Honeywell International Inc.

Inventor： Collette, Daniel Ross ,  Helsing, JR., Joseph Scott

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2211/00

Abstract: A pod (240) for an unmanned aerial vehicle is provided that may be removed and reattached to the vehicle. The pod comprises an outer shell, within which a variety of payloads may be carried. A first surface on the vehicle frame comprises a plurality of connects or electrical traces. The plurality of attachments are used to removably attach the pods to the first surface. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

公开(公告)号：EP2274204A1

公开(公告)日：2011-01-19

申请号：EP09741589.7

申请日：2009-05-07

Applicant: Entecho Pty.Ltd.

Inventor： CHAPMAN, Greg ,  KAWKA, Jakub ,  SCHLUNKE, Christopher, Kim

IPC: B64C29/02 ,  B64C15/02 ,  B64C39/00 ,  B64C7/00 ,  B64C27/20 ,  B64D33/04

CPC classification number: B64C27/20 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108

Abstract: A fluid dynamic device (100) for directing fluid flow to generate thrust comprising a thrust control shroud (130) disposed about a central axis (210) of said fluid dynamic device (100) for directing a fluid flow between an upstream fluid intake region (220) and a downstream fluid exit region (222), forming a fluid exit area, of said shroud (130) to generate thrust wherein a displacement of said fluid exit region (222) of said shroud (130) with respect to said central axis (210) results in a translation of said fluid exit area (222) such that the level of shear stress induced in that part of the shroud (130) disposed laterally to the direction of translation of the shroud (130) is minimised.

公开(公告)号：EP2253536A1

公开(公告)日：2010-11-24

申请号：EP08767003.0

申请日：2008-01-09

Applicant: Zubkov, Sergey Gennadievich ,  Reznichenko, Vycheslav Ivanovich ,  Khmel, Dmitry Sergeevich

Inventor： KHMEL, Dmitry Sergeevich

IPC: B64C27/57 ,  B64C27/80

CPC classification number: B64C11/306 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

Abstract: The invention relates to aeronautical engineering, in particular to methods of flight due to creating of forces on air propellers, namely using thrust vectoring of direction and amount of force created by air propellers of opposite rotation with the axis, mainly in the direction of flight, in the expanded range of speeds, from 50 m/s to high near-sonic speed of flight. The invention may be applied for horizontal flight and maneuvering in flight on vertical take-off aircrafts using rotation of main rotors from the vertical stand of rotor axes during the take-off to almost horizontal position of rotor axes in horizontal flight, thus both the rotation of rotors and the change of position of an aircraft together with its rotors may be applied, and it may be also used in the horizontal take-off aircrafts with almost horizontal position of axes during the horizontal flight, including the planes with airscrew propellers.

Abstract translation: 本发明涉及航空工程，尤其是的飞行的方法由于对空气螺旋桨的力的产生，即使用方向，并通过与轴相反旋转的空气推进器产生的力的大小的推力矢量，主要以飞行方向， 在速度的范围扩大，50米/秒至的飞行高近音速。 本发明可以适用于在使用从转子轴的起飞期间的垂直直立主转子的旋转垂直起飞飞行器飞行水平飞行和操纵在水平飞行中的转子轴的大致水平位置，因此，这两个旋转 转子和与它一起的转子的飞行器的位置的变化可被施加，并且可以在与轴的基本水平位置的水平起飞飞行器水平飞行期间如此使用，包括与螺旋桨推进器的计划。

公开(公告)号：EP2247500A2

公开(公告)日：2010-11-10

申请号：EP09705453.0

申请日：2009-02-02

Applicant: Bryant, Ashley Christopher

Inventor： Bryant, Ashley Christopher

IPC: B64C29/00 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A VTOL flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored manoeuvring of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. Where propulsion units (52-55) are pivoted to arms (56), the arms (56) of fore and aft propulsion units (52, 54; 53, 55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Just one propulsion unit (21) may be mounted at each extremity of the wing-structure (22), and additional fan units (48, 83) may be used for augmenting lift and for yaw control.

公开(公告)号：EP1476354B1

公开(公告)日：2008-11-05

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：EP1982914A2

公开(公告)日：2008-10-22

申请号：EP08007263.0

申请日：2008-04-12

Applicant: LFK-Lenkflugkörpersysteme GmbH

Inventor： Gleich, Peter ,  Maier, Franz

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146

Abstract: Verwendung eines Fluggerätes (10), dessen Vortrieb mittels eines von einem batterieberiebenen Elektromotor (30) angetriebenen Propeller (13) erfolgt, als ferngesteuerte "Mini-Drohne", deren Rumpfstruktur (11) als Träger eines über Fernsteuersignale beeinflussbaren Autopiloten (34) über Steckgelenke lösbar mit der Rumpfstruktur verbundenen aerodynamischen Flächen (15) und Ruder (17), sowie von Rudermaschinen (36) einer Sende- und Empfangselektronik (33) und von Fernsehkameras (23) zur Aufnahme des vom Fluggerät überflogenen Geländes dient, welches Fluggerät (10) mittels vorprogrammierter Steuersignale sowie von Lenksignalen in Abhängigkeit der auf eine die Leitstelle (38) übertragenen Fernsehbilder betätigbar ist.

Abstract translation: 飞机（10）具有使用电池驱动的电动机（30）驱动的前侧螺旋桨（13），其中使用前侧螺旋桨执行飞行器的推进。 机身结构（11）设置用于可分离的接收空气动力学表面（15）。 机身结构设计为由塑料制成的管状体，其中管状体的前窄侧带有螺旋桨。

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：EP1628878B1

公开(公告)日：2007-03-07

申请号：EP04734053.4

申请日：2004-05-20

Applicant: QinetiQ Limited

Inventor： KELLEHER, Christopher C., Cody Technology Park

IPC: B64C37/02 ,  B64D5/00

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.