公开(公告)号：EP2540623A3

公开(公告)日：2015-10-28

申请号：EP12173757.1

申请日：2012-06-27

Applicant: Aerovel Corporation

Inventor： McGeer, Brian T. ,  Coatney, Robert S.

IPC: B64C39/02 ,  B64F1/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/182 ,  B64F1/04 ,  B64F1/22

Abstract: An aircraft 1, 101 capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for a small vessel. For retrieval, the aircraft hovers over a base apparatus 6 having one or more rails 5, 105 which bound a space into which the aircraft can safely descend. When the aircraft's measured position and velocity are appropriate, the aircraft descends promptly such that a spanwise component 4, 104 on the aircraft engages the rails. The teeth 8, 108 restrain the aircraft in position and orientation, while the rails bring the aircraft to rest. Articulation of the rails is used to park the aircraft in a servicing station 14. Connections for refueling, recharging, and/or functional checks are made in preparation for launch. Launch is effected by removing connections and restraints and articulating the rails to put the aircraft in an appropriate position and orientation. The aircraft uses its own thrust to climb out of the apparatus into free flight.

公开(公告)号：EP2927122A1

公开(公告)日：2015-10-07

申请号：EP15151731.5

申请日：2015-01-20

Applicant: The Boeing Company

Inventor： Newman, Daniel Ira ,  Lacy, Roger W. ,  Preator, Robin M. ,  Gianopulos, Elia N. ,  Ziegenbein, Perry

IPC: B64C29/00

CPC classification number: B64C27/26 ,  B64C27/28 ,  B64C29/0008 ,  B64C29/0025 ,  B64C29/0033 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An aircraft (10) takes off, lands, or hovers with at least one wing-mounted thrust-producing device (12) attached to at least one wing (16) of the aircraft and at least two fuselage-mounted thrust-producing devices (18) attached to a fuselage of the aircraft both providing vertical thrust. The aircraft (10) is flown while the at least one wing-mounted thrust-producing device (12) provides horizontal thrust and with the at least two fuselage-mounted thrust-producing devices (18) not providing any thrust.

Abstract translation: 飞机（10）起飞，降落或悬停，其中至少有一个安装在飞行器的至少一个翼（16）上的机翼安装推力产生装置（12）和至少两个机身安装的推力产生装置 18）附在机身的机身上，提供垂直推力。 飞行器（10）飞行，而至少一个机翼安装的推力产生装置（12）提供水平推力并且至少两个机身安装的推力产生装置（18）不提供任何推力。

公开(公告)号：EP2800688A2

公开(公告)日：2014-11-12

申请号：EP12813773.4

申请日：2012-10-23

Applicant: Desaulniers, Jean-Marc (Joseph)

Inventor： Desaulniers, Jean-Marc (Joseph)

IPC: B64C27/20 ,  B64C29/02 ,  B64C39/00 ,  B64C39/02

CPC classification number: B64C39/024 ,  B63G8/001 ,  B63G8/16 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64G1/002 ,  B64G1/24 ,  B64G1/40

Abstract: The invention relates to an active geometric exoskeleton device (FIG. l) for a multi environment, multi mode, vertical or horizontal take off and landing gyropendular piloted craft or drone with compensatory propulsion and fluidic gradient collimation capable of moving in the following various physical environments: on land, in the air, in or under the sea or in space, comprising an active pseudo-rhombohedral annular fairing which 1) protects the various propulsion units and the payload by absorbing impacts, 2) corrects the trim and reorientates the trajectory upon collisions with any obstacle in the physical environment or the terrain, such a craft being provided with upper, intermediate and lower propulsion units, and with a hollow annular vertebral structure incorporating a payload containing the application functions suited to various domains: 1) civil defence emergency preparedness in the context of search and rescue activities, 2) exploration, navigation, transport, surveillance, 3) detection of deposits of hydrocarbons or ores, of boreholes or pump holes on land, under water or in space, 4) supporting and stabilizing a mobile, free or tethered submerged pontoon for a wind turbine or a water turbine, 5) maintenance work, 6) endovascular or intra-cavity navigation and intravention during surgery, 7) land, aerial, underwater or space telecommunications, and 8) deployment of telecommunications infrastructure in free space.

公开(公告)号：EP2760739A1

公开(公告)日：2014-08-06

申请号：EP12835896.7

申请日：2012-09-14

Applicant: Singapore Technologies Aerospace Ltd

Inventor： CHAN, Keen Ian

IPC: B64C29/02 ,  B64C25/32 ,  B64C27/08 ,  B64C39/08 ,  B64C39/10 ,  B64C99/00 ,  B64C11/46 ,  A63H27/133 ,  A63H27/127 ,  A63H27/18

CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C13/24 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  G05D1/0669 ,  Y10T29/49826

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.

公开(公告)号：EP2688800A2

公开(公告)日：2014-01-29

申请号：EP12772138.9

申请日：2012-03-23

Applicant: Page, Mark, Allan

Inventor： MCCUE, Matthew, Robert ,  GODLASKY, Robert, Anthony

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为飞行器以固定翼飞行模式提供动力。

公开(公告)号：EP2147858A3

公开(公告)日：2012-04-11

申请号：EP09160870.3

申请日：2009-05-21

Applicant: Honeywell International Inc.

Inventor： Collette, Daniel Ross

IPC: B64C27/20 ,  B64C39/02

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

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame (190), attached to which are an engine (120), gearbox assembly, fan, and a plurality of control vanes (130). A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods (240) carrying various payloads. 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：EP2247500B1

公开(公告)日：2012-04-04

申请号：EP09705453.0

申请日：2009-02-02

Applicant: Bryant, Ashley Christopher

Inventor： Bryant, Ashley Christopher

IPC: B64C29/00 ,  B64C39/02 ,  B64C39/10

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：EP2244941A2

公开(公告)日：2010-11-03

申请号：EP09700087.1

申请日：2009-01-02

Applicant: Pruzina, Marian

Inventor： Pruzina, Marian

IPC: B64C39/06

CPC classification number: B64C39/064 ,  B64C2201/027 ,  B64C2201/088

Abstract: The Spring flying device (1) preferably of circular, oval or polygon shape, capable of vertical take-off and landing, comprises the source (5) of flowing medium (6), which flows through chamber (2) consisting of curved bottom face generating buoyancy during flow (3) and curved top medium attracting face (4). The faces (3) and (4) making up chamber (2) have adequate spacing from each other which allows their interaction still; control is provided by deflection (9) and swivelling (10) flaps, pivot-mounted in chamber (2) and acting upon the flowing medium (6). The device (1 ) may carry missile ramp (18) with protective guide shield (14) with horizontal (15) and radial (16) deflection flaps which streamline the missile exhaust gases (17) to outer top buoyancy face (12), while the missile exhaust gases (17) may be streamlined to apertures (19) of the chamber simultaneously.

公开(公告)号：EP2147858A2

公开(公告)日：2010-01-27

申请号：EP09160870.3

申请日：2009-05-21

Applicant: Honeywell International Inc.

Inventor： Collette, Daniel Ross

IPC: B64C27/20 ,  B64C39/02

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

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame (190), attached to which are an engine (120), gearbox assembly, fan, and a plurality of control vanes (130). A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods (240) carrying various payloads. 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.

Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风管风扇芯包括附接到发动机（120），齿轮箱组件，风扇和多个控制叶片（130）的框架（190）。 框架上的第一表面包括多个连接或电迹线。 多个连接件用于可移除地附接承载各种有效载荷的各种吊舱（240）。 因此，简单地通过将不同的荚移除并附接到固定的车辆核心，可以使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚被附接到框架时，它们增强了车辆的空气动力学。

公开(公告)号：EP1995174A2

公开(公告)日：2008-11-26

申请号：EP08101858.2

申请日：2008-02-21

Applicant: Honeywell International Inc.

Inventor： Hursig, David C. ,  Martinez, Steven D.

IPC: B64C27/20 ,  B64C39/02 ,  B64D45/04 ,  G05D1/08

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64D45/04 ,  G05D1/0653 ,  G05D1/0858

Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takcoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

Abstract translation: 起飞和着陆模式被添加到垂直起飞和着陆（VTOL）无人机（UAV）的飞行控制系统。 起飞和着陆模式使用可用于飞行控制系统和VTOL UAV现有控制面和节气门控制的数据。 因此，VTOL无人机可以在倾斜的表面上进行夯实和降落，而不需要使用设计成在倾斜表面上对无人机进行平坦化的起落架机构。