公开(公告)号：EP3344534A1

公开(公告)日：2018-07-11

申请号：EP16842803.5

申请日：2016-08-30

Applicant: University of Maryland, College Park

Inventor： VALENTE, Evandro Gurgel do Amaral ,  WERELEY, Norman, M. ,  VALENTE, Eduardo Gurgel do, Amaral

IPC: B64C3/14 ,  B64C29/00

CPC classification number: B64C37/00 ,  B64C5/02 ,  B64C11/46 ,  B64C15/12 ,  B64C19/00 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/208 ,  B64C2211/00 ,  B64D29/00

Abstract: The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

公开(公告)号：EP3290334A1

公开(公告)日：2018-03-07

申请号：EP17188895.1

申请日：2017-08-31

Applicant: Sunlight Photonics Inc.

Inventor： Frolov, Sergey V. ,  Cyrus, Michael ,  Moussouris, John Peter

IPC: B64C27/28 ,  B64C29/00 ,  B64C11/00 ,  B64D27/24 ,  B64C39/02 ,  B64C27/24

CPC classification number: B64D27/24 ,  B64C11/001 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/208 ,  Y02T50/64

Abstract: Embodiments of the present invention provide an aircraft (200) for vertical take-off and landing. In various embodiments, an aircraft assembly includes at least one first wing portion (210) providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion (210) and at least one thruster (240) positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents (2030) positioned inside at least one of the wing openings. The air vents can further include louvres (2040) positioned over or under the air vents (2030) to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

Abstract translation: 本发明的实施例提供用于垂直起飞和降落的飞行器（200）。 在各种实施例中，飞机组件包括在水平飞行期间提供升力的至少一个第一机翼部分（210），设置在至少一个第一机翼部分（210）的竖直轴线上的至少一个机翼开口以及至少一个 一个推进器（240）位于所述至少一个翼开口内以在垂直飞行期间提供垂直推力。 飞机组件还可以包括定位在至少一个翼开口内的通气孔（2030）。 通风口还可以包括位于通风口（2030）上方或下方的百叶窗（2040）以打开和关闭翼部开口。 推进器可以进一步用于为飞机提供飞行控制。

公开(公告)号：EP3282334A1

公开(公告)日：2018-02-14

申请号：EP17182759.5

申请日：2017-07-24

Applicant: Parrot Drones

Inventor： RIMOUX, Ariel ,  PIRAT, Frédéric

IPC: G05D1/00 ,  G05D1/08

CPC classification number: G05D1/0088 ,  A63H27/12 ,  A63H30/04 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0016 ,  G05D1/0038 ,  G05D1/042 ,  G05D1/0653 ,  G05D1/0808

Abstract: Le drone comprend un système de pilotage automatique (24) qui reçoit des instructions internes et/ou externes de pilotage, ainsi que des données d'attitude (ϕ*, θ*), d'altitude (z*) et de vitesse (V*) instantanées délivrées par des capteurs (48, 50, 58, 60, 62, 68, 70). Des circuits de calcul de consignes (36, 38, 40) calculent, en fonction d'un modèle du comportement aérodynamique du drone en vol, des consignes d'angles de roulis (ϕ) et/ou de tangage (θ) et/ou des consignes de vitesse (V) et/ou des consignes d'altitude (z) correspondant aux instructions internes et/ou externes de pilotage reçues. Des circuits de correction et de contrôle (44, 44, 52, 54, 64) commandent le système de propulsion (28) et les servomécanismes (30) des gouvernes du drone. Un système (26) permet en outre de générer en interne des instructions de pilotage pour des modes de vol autonome tels que décollage automatique ou atterrissage automatique.

Abstract translation: 所述UAV包括接收指令的内部和/或外部控制，以及姿态数据（φ*，θ*），高度（Z *）和速度的自动转向系统（24）（V *）通过传感器（48,50,58,60,62,68,70）瞬时传送。 计算电路的指令（36，38，40）来计算，基于所述UAV在飞行的空气动力行为的模型，侧倾角（φ）和/或俯仰（θ）的指令和/或 速度设定点（V）和/或高度设定点（z）对应于所接收的内部和/或外部导频指令。 校正和控制电路（44,44,52,54,64）控制无人机的控制表面的推进系统（28）和伺服机构（30）。 系统（26）还在内部生成用于自动飞行模式的飞行指令，例如自动起飞或自动着陆。

公开(公告)号：EP3228537A1

公开(公告)日：2017-10-11

申请号：EP17163331.6

申请日：2017-03-28

Applicant: Lockheed Martin Corporation

Inventor： GAMBLE, Dustin Eli ,  CURRAN, Matthew

IPC: B64C3/38

CPC classification number: B64C3/42 ,  B64C1/26 ,  B64C1/28 ,  B64C3/38 ,  B64C3/385 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/028 ,  B64C2201/10

Abstract: An aerial vehicle (100) includes a fuselage (120), a wing (110), and a wing shift device (150). The wing shift device (150) is configured to be coupled to the fuselage (120). The wing shift device (150) comprises plurality of apertures (Fig. 2, 215, 305) for coupling the wing (110) to the aerial vehicle (100). The plurality of apertures (Fig. 2, 215, 305) are configured to permit the wing (110) to be shifted in a forward or aft direction along the fuselage (120) based on a center of gravity (160) of the aerial vehicle (100).

Abstract translation: 一种飞行器（100）包括机身（120），机翼（110）和机翼换档装置（150）。 机翼换挡装置（150）构造成联接到机身（120）。 机翼移位装置（150）包括用于将机翼（110）连接至飞行器（100）的多个孔（图2,215,305）。 基于飞行器的重心（160），多个孔（图2,215,305）构造成允许机翼（110）沿机身（120）沿向前或向后方向移动 （100）。

公开(公告)号：EP2403757B1

公开(公告)日：2014-04-16

申请号：EP10722158.2

申请日：2010-03-05

Applicant: Cranfield Aerospace Ltd

Inventor： THOMASSON, Peter, Geoffrey ,  JONES, Robert, Idris ,  POLL, David, Ian, Alistair

IPC: B64C13/16

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0094 ,  G05D1/0825

公开(公告)号：EP2277775B1

公开(公告)日：2012-05-09

申请号：EP10188051.6

申请日：2008-04-16

Applicant: GO SCIENCE LIMITED

Inventor： Gosling, Harry George Dennis

IPC: B64C39/06 ,  B64C39/02

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

公开(公告)号：EP2188176B1

公开(公告)日：2011-03-23

申请号：EP08857634.3

申请日：2008-09-11

Applicant: Altair

Inventor： LEHMANN, Benjamin

IPC: B64C39/02

CPC classification number: B64C39/024 ,  A63H27/02 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127

Abstract: The present invention relates to a modular drone (1) consisting of a flying structure (2) and image acquisition means, characterized in that said image acquisition means as well as the motorization are supported by a rigid platen (6) connected to the flying structure (2) by links that are detachable when the loadings between said platen (6) and said flying structure (2) exceed a wrenching threshold value, these links being constituted by one from among electromagnetic links (41, 42) and self-adhering tapes and materials. The present invention also relates to an airborne image acquisition system consisting of such a modular drone.

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：EP1257466A2

公开(公告)日：2002-11-20

申请号：EP01937143.4

申请日：2001-02-07

Applicant: Aerovironment Inc.

Inventor： MACCREADY, Paul ,  HIBBS, Bart, D. ,  COX, Earl, C. ,  LISOSKI, Derek, L. ,  KENDALL, Greg, T.

IPC: B64D27/24

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

公开(公告)号：EP1257465A2

公开(公告)日：2002-11-20

申请号：EP01934833.3

申请日：2001-02-12

Applicant: Aerovironment Inc.

Inventor： MACCREADY, Paul ,  HIBBS, Bart, D. ,  COX, Earl, C. ,  LISOSKI, Derek, L. ,  KENDALL, Greg T.

IPC: B64C39/02 ,  G05D1/00 ,  H04B7/185

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.