公开(公告)号：EP1370461B1

公开(公告)日：2004-09-22

申请号：EP02700439.9

申请日：2002-02-20

Applicant: BAE Systems PLC

Inventor： HARRISON, Richard George, Bae Systems plc

IPC: B64D5/00 ,  B64D3/00 ,  B64D39/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/206 ,  B64D3/00 ,  B64D5/00 ,  B64D39/02 ,  B64D39/06

Abstract: A system for launching, refuelling and recovering in flight an aircraft (10) such as an unmanned aerial vehicle (UAV) from a larger carrier aircraft (16) comprising a holder (22) on the carrier aircraft (16) to which the UAV (10) is detachably connectable and an extendable and retractable refuelling device (23, 24) on the carrier aircraft (16) detachably connectable to the UAV (10) whereby to launch the UAV it is disconnected from the holder (22), the refuelling device (23, 24) is extended with the UAV connected thereto to cause the UAV to trail behind the carrier aircraft and the UAV is then disconnected from the refuelling device.

公开(公告)号：WO2006069304A2

公开(公告)日：2006-06-29

申请号：PCT/US2005/046755

申请日：2005-12-22

Applicant: AURORA FLIGHT SCIENCES CORPORATION ,  PARKS, Robert

Inventor： PARKS, Robert

CPC classification number: F01D9/065 ,  B64C29/0075 ,  B64C29/0083 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/167 ,  B64D27/18 ,  B64D29/04 ,  B64D33/02 ,  F02C6/12 ,  F02C7/042 ,  F02K3/00 ,  F05D2220/90

Abstract: A system and method for tilting an engine in a vertical take-off and landing/short take-off and landing aircraft (VTOL/STOL A/C) is provided comprising a main control system, an engine tilting mechanism, and an air flow volume detector, which is located in the engine. The system and method tilt the engine to maximize engine performance based on a variety of parameters including the air flow volume so that forward and horizontal speeds are maximized at the appropriate times, and also to reduce radar cross section and infra-red visibility.

Abstract translation: 提供了一种用于在垂直起飞和着陆/短起飞和着陆飞机（VTOL / STOL A / C）中倾斜发动机的系统和方法，包括主控制系统，发动机倾斜机构和空气流量 检测器，位于发动机中。 该系统和方法基于包括空气流量的各种参数来倾斜发动机以使发动机性能最大化，使得在适当的时间使前进和水平速度最大化，并且还减少雷达截面和红外可见度。

公开(公告)号：WO2005025983A1

公开(公告)日：2005-03-24

申请号：PCT/IB2004/002940

申请日：2004-09-10

Applicant: POLITECNICO DI TORINO ,  QUAGLIOTTI, Fulvia ,  PRALIO, Barbara ,  GUGLIERI, Giorgio

Inventor： QUAGLIOTTI, Fulvia ,  PRALIO, Barbara ,  GUGLIERI, Giorgio

IPC: B64C39/02

CPC classification number: B64C5/08 ,  B64C23/069 ,  B64C39/024 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  Y02T50/12 ,  Y02T50/164

Abstract: Fixed wing micro aerial vehicle characterized in that it comprises an allowing platform (1) composed by two low aspect ratio semi-wings (2) with substantially trapezoidal planform, equipped with elevons (4) along their trailing edge and with outboard vertical fins (3) for lateral-directional stability.

Abstract translation: 固定翼微型飞行器，其特征在于，它包括由两个具有大致梯形平面的低纵横比半翼（2）构成的允许平台（1），沿着它们的后缘装备有升降（4）和外侧垂直翅片（3 ）用于横向稳定性。

公开(公告)号：WO2005014390A2

公开(公告)日：2005-02-17

申请号：PCT/US2004/001033

申请日：2004-01-17

Applicant: THE INSITU GROUP ,  DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

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

IPC: B64B

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 and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了组装，发射，恢复，拆卸，捕获和存储无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞行器部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：WO2004060743A2

公开(公告)日：2004-07-22

申请号：PCT/US2003/039332

申请日：2003-12-09

Applicant: UNIVERSITY OF FLORIDA ,  IFJU, Peter ,  LEE, Kyu-Ho ,  ALBERTANI, Roberto ,  MITRYK, Shawn, J. ,  BORIA, Frank, J. ,  ABDULRAHIM, Mujahid

Inventor： IFJU, Peter ,  LEE, Kyu-Ho ,  ALBERTANI, Roberto ,  MITRYK, Shawn, J. ,  BORIA, Frank, J. ,  ABDULRAHIM, Mujahid

IPC: B64B

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过简单地从管中释放微型飞行器而从管展开。

公开(公告)号：WO2003004352A1

公开(公告)日：2003-01-16

申请号：PCT/JP2002/006031

申请日：2002-06-17

Applicant: セイコーエプソン株式会社

Inventor： 赤堀 豊

IPC: B64B1/06

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system, comprising an airship (110), a base station (120), and at least three measurement points, wherein, when the airship (110) receiving an instruction from the base station (120) transmits ultrasonic wave, the measurement point units (S1 to S3) receive the ultrasonic wave to measure distances between the airship and the three measurement points and an MPU incorporated in the base station (120) calculates the position of the airship (110) and, according to the calculated position, the base station (120) transmits a navigation instruction to the airship (110) to control the route of the airship (110), whereby the operation of the airship by an operator can be eliminated, and the weight of loads mounted on the airship and the power consumption thereof can be reduced.

Abstract translation: 一种飞艇系统，包括飞艇（110），基站（120）和至少三个测量点，其中当接收到来自基站（120）的指令的飞艇（110）发射超声波时，测量点 单元（S1至S3）接收超声波以测量飞艇与三个测量点之间的距离，并且包含在基站（120）中的MPU计算飞艇（110）的位置，并且根据计算的位置， 基站（120）向飞艇（110）发送导航指令以控制飞艇（110）的路线，由此可以消除操作者的飞艇的操作，并且安装在飞艇上的载荷和 其功耗可以降低。

公开(公告)号：WO01085541A1

公开(公告)日：2001-11-15

申请号：PCT/EP2001/005066

申请日：2001-05-04

IPC: B64C39/02 ,  B64D27/02

CPC classification number: B64D27/023 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/165

Abstract: The invention relates to a propulsion system for aircraft, especially for high-flying and long-distance flying unmanned aircraft, to the aircraft itself and to a method for controlling aircraft. Said propulsion system has a first jet turbine engine and a second jet turbine engine (22, 24). The invention also provides that the first jet turbine engine is a turbine engine (22) and the second jet turbine engine is an airscrew turbine engine (24). Said airscrew turbine engine (24) remains non-operational at least during the process for starting the aircraft (10).

Abstract translation: 本发明涉及一种驱动系统，用于飞机，特别是用于高和进一步的飞行，无人驾驶飞机，飞机本身，以及用于控制飞行器的方法。 该驱动系统包括一个第一和一个第二发动机（22，24）。 还可以设想的是，第一发动机为喷气发动机（22）和所述第二推进器的螺旋桨式发动机（24），至少所述飞行器（10）的起动操作过程中，螺旋桨引擎（24）保持停止运转。

公开(公告)号：WO0068077B1

公开(公告)日：2001-01-25

申请号：PCT/US0007237

申请日：2000-03-16

Applicant: AEROVIRONMENT INC

Inventor： MACCREADY PAUL B JR

IPC: B64C29/02 ,  B64C39/02 ,  B64D1/08 ,  B64D1/22 ,  B64D9/00

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64D1/08 ,  B64D1/22

Abstract: Apparatus for transporting a load (24) between source and destination locations, comprising an aircraft having a body (11), power plant (12) carried by the body (11) to drive the aircraft both generally vertically and also generally horizontally, the aircraft also having a wing structure (14-15) that has a leading edge remaining presented in the direction of flight; and load pick-up, carry and set-down means (22) connected to the aircraft to elevate the load (24) from the source location, transport the elevated and air-borne load (24) generally horizontally, and set the load (24) down at the destination location, the body (11) and power plant (12) configured for vertical flight mode to elevate and set down the load (24), and for generally horizontal flight mode to transport the elevated load (24) generally horizontally below the level of the aircraft body (11).

Abstract translation: 用于在源和目的地之间运输负载（24）的设备，包括具有主体（11）的飞行器，由主体（11）承载的发电厂（12），以大致垂直地并且大致水平地驱动飞机 还具有翼片结构（14-15），其具有沿飞行方向保持的前缘; 以及连接到飞行器的负载拾取，携带和设置装置（22）以从源位置提升负载（24），大体水平地输送高空和空载负载（24），并设定负载（ 24）在目的地位置，主体（11）和配置用于垂直飞行模式的发电厂（12）升高和降低负载（24），并且为了大体上水平飞行模式通常运送升高的负载（24） 水平地低于飞机主体（11）的水平面。

公开(公告)号：WO2018027220A1

公开(公告)日：2018-02-08

申请号：PCT/US2017/045739

申请日：2017-08-07

Applicant: WILKINSON, Christopher

Inventor： WILKINSON, Christopher

IPC: B64C39/02 ,  G05B15/02

CPC classification number: B64C39/024 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22 ,  F41H3/00 ,  F41H13/0012 ,  F41H13/0093 ,  G01S7/38

Abstract: A law enforcement drone system is provided. The system features an unmanned aerial vehicle, having a wireless transceiver, an airframe, a propulsion system, a navigation mechanism, a processor, a memory, a power source, and at least one fuel tank. The system also features a control system having a wireless transceiver, an input device, capable of receiving a user's input and converting the user's input to electrical signals, a processor, and a memory. The control system is in wireless communication with the vehicle such that the control system is capable of utilizing the propulsion system in substantially real-time.

Abstract translation:

提供执法无人机系统。 该系统具有无人驾驶飞行器，具有无线收发器，机身，推进系统，导航机构，处理器，存储器，电源和至少一个燃料箱。 该系统还具有具有无线收发器，能够接收用户输入并将用户输入转换为电信号的输入设备，处理器和存储器的控制系统。 控制系统与车辆进行无线通信，使得控制系统能够基本上实时地利用推进系统。

公开(公告)号：WO2016114851A1

公开(公告)日：2016-07-21

申请号：PCT/US2015/060805

申请日：2015-11-16

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： ALBER, Mark R.

IPC: B64D27/06

CPC classification number: B64D35/04 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/088

Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

Abstract translation: 提供垂直起飞和着陆（VTOL）飞机，并且包括翼，每个翼上支撑的第一和第二机舱，第一和第二机舱中的每一个包括可驱动以产生飞机推力的螺旋桨，以及不对称发电单元 。 不对称发电单元包括仅设置在第一和第二机舱中的一个机舱中的单个发动机单元，以产生驱动第一和第二机舱的螺旋桨的动力。