公开(公告)号：EP3116781A4

公开(公告)日：2017-12-20

申请号：EP15762275

申请日：2015-03-05

Applicant: ENDURANT SYSTEMS LLC

Inventor： MCADOO GREGORY LEONARD

IPC: B64C39/02 ,  B64C27/08 ,  B64D27/04 ,  B64D27/24

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/26 ,  B64C29/0033 ,  B64C39/04 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/141 ,  B64D27/04 ,  B64D27/24 ,  B64D45/00 ,  B64D2027/026 ,  B64D2045/0085 ,  B64D2221/00 ,  H02J7/14 ,  H02J7/34 ,  H02K7/1815 ,  Y02T50/64

Abstract: UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

公开(公告)号：EP3243747A1

公开(公告)日：2017-11-15

申请号：EP17170907.4

申请日：2017-05-12

Applicant: Bell Helicopter Textron Inc.

Inventor： FENNY, Carlos Alexander ,  OLSON, Rohn Lee ,  ZAHASKY, Andrew James

IPC: B64C27/08 ,  B64C29/02 ,  B64C39/06 ,  B64C39/02 ,  B64C11/28 ,  B64C27/30 ,  B64D35/00 ,  B64C17/08 ,  B64C17/10

CPC classification number: B64C39/062 ,  B64C11/28 ,  B64C17/08 ,  B64C17/10 ,  B64C27/30 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2211/00 ,  B64D35/00

Abstract: VERTICAL TAKE OFF AND LANDING CLOSED WING AIRCRAFT
An aircraft (100) capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing (102) that provides lift whenever the aircraft (100) is in forward flight, a fuselage (104) at least partially disposed within a perimeter of the closed wing (102), and one or more spokes (106) coupling the closed wing (102) to the fuselage (104). The fuselage (104) can have a rear module substantially disposed within a perimeter of the distributed airframe (1002, Figure 11), and a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors (132) are disposed within or attached to the closed wing (102), fuselage (104) or spokes (106). Three or more propellers (120) are proximate to a leading edge of the closed wing (102) or the one or more spokes (106), distributed along the closed wing (102) or the one or more spokes (106), and operably connected to the one or more engines or motors (132). The propellers (120) provide lift whenever the aircraft (100) is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft (100) is in forward flight.

Abstract translation: 垂直起飞和着陆闭式翼飞机能够垂直起飞和着陆，静态飞行和向前飞行的飞机（100）包括闭合机翼（102），其在飞机（100）向前飞行时提供升力，机身（104 ）至少部分地设置在所述封闭翼（102）的周边内，以及一个或多个将所述封闭翼（102）连接到所述机身（104）的辐条（106）。 机身（104）可以具有基本上设置在分布式机身（1002，图11）的周边内的后部模块和可移除地连接至后部模块并与纵向轴线基本对齐的前部模块。 一个或多个发动机或马达（132）布置在封闭机翼（102），机身（104）或辐条（106）内或附接到封闭机翼（102）内。 三个或更多个螺旋桨（120）靠近沿着封闭翼（102）或一个或多个辐条（106）分布的封闭翼（102）或一个或多个辐条（106）的前缘，并且可操作地 连接到一个或多个发动机或电动机（132）。 每当飞机（100）处于垂直起飞和降落以及静止飞行时，螺旋桨（120）都提供升力，并且在飞机（100）向前飞行时提供推力。

公开(公告)号：EP3135583A1

公开(公告)日：2017-03-01

申请号：EP11761644.1

申请日：2011-06-20

Applicant: Wake Engineering, S.L.

Inventor： TURRILLAS LAS HERAS, Arturo

IPC: B64C25/56 ,  B64C35/00

CPC classification number: B64C25/56 ,  B64C35/00 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/123 ,  B64D2241/00

Abstract: The device comprises at least one folding, inflatable chamber (3), at least one runner (4) for landing on water, which is coupled to the aircraft (2) by means of the chamber (3), and at least one air intake (6) connected to the chamber. The intake (6) allows the entry of incident air into the chamber (3) in order to inflate and deploy the chamber (3), extending the runner (4) from a retracted-runner position into an extended-runner position

Abstract translation: 该装置包括至少一个折叠的可充气室（3），至少一个用于着陆在水面上的流道（4），其通过腔室（3）联接到飞行器（2），并且至少一个进气口 （6）连接到腔室。 入口（6）允许入口空气进入腔室（3），以便使空腔（3）膨胀和展开，从而将流道（4）从缩回流道位置延伸到延伸流道位置

公开(公告)号：EP1884463A1

公开(公告)日：2008-02-06

申请号：EP07106798.7

申请日：2007-04-24

Applicant: HONEYWELL INC.

Inventor： Goossen, Emray R ,  Mantych, Glen A. ,  Campbell, William T.

IPC: B64C39/02 ,  B64F1/04

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/201

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container (110) and a container lid (101) with the MAV (200) clamped to the lid. Also disposed on the container lid is a starting assembly (111). The lid (101) which doubles as a launching pad with the attached MAV (200) is removed from the container (110), placed on the ground, the MAV (200) is started with the starling mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Abstract translation: 微型飞行器（MAV）启动系统，提供组合功能：敏感车辆部件的包装保护，机械启动组件和发射台。 优选实施例包括容器（110）和容纳盖（101），其中MAV（200）夹在盖子上。 还设置在容器盖上的是起动组件（111）。 将具有连接的MAV（200）的作为发射台的盖（101）从容器（110）中取出，放置在地面上，MAV（200）以起落机构启动并启动。 这种安排可最大限度地减少操作者的身体风险，最大限度地减少总体MAV系统的重量，消耗操作员运输系统的最小空间，并消除对电池更换或充电的供电线路的依赖。

公开(公告)号：EP1767453A1

公开(公告)日：2007-03-28

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

Abstract: Autonomous micro air vehicles (102) surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad (120). The MAV has an engine (103) that is adapted to power the MAV. The launch pad has a starter (128) that is adapted to start the engine in the MAV when the MAV is resting on a launching surface (142) of the launch pad. The launch pad further has a battery (126) to power the starter.

Abstract translation: 提供自动微型飞行器（102）监视系统。 一个实施例的MAV系统包括MAV和发射台（120）。 MAV具有适于为MAV供电的发动机（103）。 所述发射台具有起动器（128），当所述MAV处于所述发射台的发射表面（142）上时，所述起动器适于在所述MAV中启动所述发动机。 发射台还具有用于为起动器供电的电池（126）。

公开(公告)号：EP1713689A2

公开(公告)日：2006-10-25

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

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：EP1590238A2

公开(公告)日：2005-11-02

申请号：EP04775727.3

申请日：2004-01-17

Applicant: The Insitu Group

Inventor： DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

IPC: B64B1/00

CPC classification number: B64F1/02 ,  B63B27/26 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft (140) and other flight devices or projectiles are described. In one embodiment, the aircraft (140) can be assembled from a container (111) with little or no manual engagement by an operator. The container (111) can include a guide structure to control motion of the aircraft components. The aircraft (140) can be launched from an apparatus that includes an extendable boom (103). The boom (103) can be extended to deploy a recovery line (853) to capture the aircraft (140) in flight. The aircraft (140) can then be returned to its launch platform, disassembled, and stored in the container (111), again with little or no direct manual contact between the operator and the aircraft (140).

公开(公告)号：EP1384662B1

公开(公告)日：2005-06-15

申请号：EP03016348.9

申请日：2003-07-18

Applicant: C.R.F. Società Consortile per Azioni

Inventor： Perlo, Piero ,  Bollea, Denis ,  Finizio, Roberto ,  Carvignese, Cosimo ,  Balocco, Elena

IPC: B64C39/02 ,  B64C29/02

CPC classification number: B64C29/02 ,  B64C27/20 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

公开(公告)号：EP1524189A1

公开(公告)日：2005-04-20

申请号：EP04023459.3

申请日：2004-10-01

Applicant: C.R.F. Società Consortile per Azioni

Inventor： Perlo, Piero ,  Pairetti, Bartolomeo ,  Finizio, Roberto ,  Carvignese, Cosimo ,  Repetto, Piermario ,  Bollea, Denis ,  Capello, Davide

IPC: B64C39/02 ,  B64C27/20 ,  A63H27/127 ,  H04M1/725

CPC classification number: B64C27/20 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  H04M1/21 ,  H04M1/72547

Abstract: The invention describes a microaircraft (2), which can be associated for instance to a cellular phone (1), provided with at least four microrotors (4) actuated with compressed fluid or by ring-shaped electric motors (7).

Abstract translation: 本发明描述了一种微型飞机（2），其可以例如与蜂窝电话（1）相关联，提供有至少四个由压缩流体致动的微电机（4）或由环形电动机（7）驱动。

公开(公告)号：EP1049623B1

公开(公告)日：2004-10-06

申请号：EP99905396.0

申请日：1999-01-25

Applicant: Avia Adviser HB

Inventor： HJELTE, Fritz

IPC: B64C27/06 ,  B64C29/02

CPC classification number: B64C39/024 ,  B64C27/52 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165

Abstract: An unmanned rotor carried aerial vehicle comprises a propulsion unit (5) and a carrier (7) suspended from the propulsion unit. The propulsion unit (5) is connected to the carrier (7) via a cardan-like joint (9) for permitting limited tilting of the propulsion unit relative to the carrier in two orthogonal directions corresponding to the roll and pitch directions of the vehicle and for preventing relative movement between the propulsion unit and the carrier in the yaw direction of the vehicle.