公开(公告)号：EP3168567A1

公开(公告)日：2017-05-17

申请号：EP16197881.2

申请日：2016-11-09

Applicant: MBDA Deutschland GmbH

Inventor： MAIER, Franz

IPC: F42B10/14 ,  F42B10/62 ,  F42B10/48

CPC classification number: F42B10/14 ,  B64C3/38 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/165 ,  F42B10/48 ,  F42B10/62 ,  Y02T50/14

Abstract: Ein unbemannter Flugkörper (1) mit einem Rumpf (2) und zumindest einer am Rumpf (2) um zumindest eine Tragflügelschwenkachse (Z) schwenkbar gelagerten Tragflügeleinrichtung (3) zeichnet sich dadurch aus, dass die zumindest eine schwenkbare Tragflügeleinrichtung (3) eine erste Tragfläche (30; 30') und eine von dieser in Richtung der Gierachse (z) beabstandete zweite Tragfläche (34; 34') aufweist und dass sich zwischen dem freien Ende der ersten Tragfläche (30; 30') und dem freien Ende der zweiten Tragfläche (34; 34') zumindest eine Verbindungsfläche (33, 37; 33', 33"; 37'; 37") erstreckt, mit der die jeweiligen freien Enden der Tragflächen (30, 34; 30', 34') miteinander verbunden oder verbindbar sind.

公开(公告)号：EP3124379A1

公开(公告)日：2017-02-01

申请号：EP15178886.6

申请日：2015-07-29

Applicant: Airbus Defence and Space GmbH

Inventor： STEINWANDEL, Jürgen ,  WANG, Ning ,  JUDAS, Michael ,  VAN TOOR, Jan

IPC: B64C29/00

CPC classification number: B64D35/08 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24 ,  B64D2027/026

Abstract: Die Erfindung betrifft ein senkrechtstartfähiges Fluggerät (10) mit einem Schubantrieb (31) zum Erzeugen einer in eine Horizontalrichtung (1) wirkenden Antriebskraft und einem Hubantrieb (32) zum Erzeugen einer in eine Vertikahichtung wirkenden Auftriebskraft. Das Fluggerät weist ferner einen Motor (12) zum Bereitstellen von mechanischer Energie für den Schubantrieb (31) und einen ersten Generator (11) zum Bereitstellen von elektrischer Energie für den Hubantrieb (32) auf. Zudem weist das Fluggerät einen Abgasturbolader (40) für den Motor (12) mit einer von einem Abgasstrom (44) des Motors (12) angetriebenen ersten Turbine (41) auf, die dazu ausgeführt ist, mechanische Energie für den Schubantrieb (31) bereitzustellen.

Abstract translation: 具有用于产生在水平方向上有效的驱动力的推进驱动器的垂直起飞飞机和用于产生在垂直方向上有效的提升力的提升驱动装置包括用于为推进驱动提供机械能的马达和 用于为升降机驱动提供电能的第一发电机。 此外，该飞行器包括用于马达的废气涡轮增压器，其中第一涡轮机由马达的排气流驱动，其中第一涡轮机构造成为推进驱动提供机械能。

公开(公告)号：EP2899128A1

公开(公告)日：2015-07-29

申请号：EP15152248.9

申请日：2015-01-23

Applicant: NEXTER Systems

Inventor： Sautet, Jean-Yves ,  Possidente, Dominique

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/208 ,  B64F1/04

Abstract: L'invention porte sur un dispositif d'accueil (1) pour drone (10) destiné à être embarqué à bord d'un véhicule (100) caractérisé en ce que le dispositif d'accueil (1) comporte:
un support (12) destiné à supporter un drone (10),
un moyen d'élévation (20) du support (12) destiné à déplacer le support (12) entre une position basse située au voisinage d'une base du moyen d'élévation (20) et une position élevée,
au moins un plot aimanté solidaire de la base du moyen d'élévation (20), plot aimanté destiné à coopérer avec un élément d'arrimage magnétique (22) solidaire d'un drone pour assurer l'arrimage de ce dernier en position basse.
L'invention vise également un véhicule associé à un tel dispositif.

公开(公告)号：EP2814735A1

公开(公告)日：2014-12-24

申请号：EP13710309.9

申请日：2013-02-13

Applicant: Reiter, Johannes

Inventor： Reiter, Johannes

IPC: B64C29/02 ,  B64C39/02 ,  B64C29/00

CPC classification number: B64C27/00 ,  B64C3/385 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0075 ,  B64C29/02 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

公开(公告)号：EP2274204B1

公开(公告)日：2014-10-15

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 ,  F04D29/30

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

公开(公告)号：EP2103518A3

公开(公告)日：2012-02-29

申请号：EP09153384.4

申请日：2009-02-21

Applicant: Honeywell International Inc.

Inventor： Goossen, Emray R. ,  Sheoran, Yogendra Y.

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

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64C2201/208 ,  B64F1/04

Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster (104) and a duct (106) configured to direct airflow generated by the thruster includes a capture plate (120) and an extension (122). The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

公开(公告)号：EP1982914A3

公开(公告)日：2011-07-06

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.

公开(公告)号：EP1851109B1

公开(公告)日：2011-01-05

申请号：EP06734600.7

申请日：2006-02-09

Applicant: Honeywell International Inc.

Inventor： GOOSSEN, Emray, R.

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components (203), engine (10), and avionics/payload pods (300, 302) are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan (201 ), stator (102), and control vane design. Assembly connections between ducted fans (203) and electronic modules are also identical. An engine (10) or APU drives the dual ducted fans (203) through a splined shaft (601) to a differential (600) or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator (102) hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms (603) on each of the splined shafts (601) between the differential (600) and ducted fans (203). In the electric motor case relative speed is through electronic speed control. The fans (201 ) are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

公开(公告)号：EP2236417A1

公开(公告)日：2010-10-06

申请号：EP10151453.7

申请日：2010-01-22

Applicant: Honeywell International Inc.

Inventor： Fitzpatrick, David

IPC: B64C39/02 ,  G01R33/02 ,  G05D1/08

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  G01R33/0206 ,  G05D1/0858

Abstract: Measurement of only one axis of a three-axis magnetometer is used to control the performance of at least one corrective action on an unmanned aerial vehicle ("UAV"). In one example, a method includes receiving from a three-axis magnetometer a measurement representative of an attitude of a UAV, wherein the measurement is of only one axis of the magnetometer, comparing the measurement to an allowable range of attitudes, determining that the measurement is not within the allowable range of attitudes, and performing at least one corrective action on the UAV.

Abstract translation: 仅一个三轴磁力计的轴的测量值用于在无人驾驶飞行器（“UAV”），以控制上的至少一个校正动作的性能。 在一个实施例中，一种方法包括：从一个三轴磁力计接收测量代表一个UAV的姿势的，worin测量是磁力的仅一个轴的，测量在态度容许范围进行比较来的，确定性的挖掘做了测量 不是态度在容许范围内，以及对所述UAV至少一个校正动作。

公开(公告)号：EP1851109A2

公开(公告)日：2007-11-07

申请号：EP06734600.7

申请日：2006-02-09

Applicant: Honeywell International Inc.

Inventor： GOOSSEN, Emray, R.

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components (203), engine (10), and avionics/payload pods (300, 302) are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan (201 ), stator (102), and control vane design. Assembly connections between ducted fans (203) and electronic modules are also identical. An engine (10) or APU drives the dual ducted fans (203) through a splined shaft (601) to a differential (600) or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator (102) hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms (603) on each of the splined shafts (601) between the differential (600) and ducted fans (203). In the electric motor case relative speed is through electronic speed control. The fans (201 ) are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.