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    AIRCRAFT DATA TRANSFER
    2.
    发明公开
    AIRCRAFT DATA TRANSFER 审中-公开
    FLUGZEUGDATENÜBERTRAGUNG

    公开(公告)号：EP3093242A1

    公开(公告)日：2016-11-16

    申请号：EP15167163.3

    申请日：2015-05-11

    Applicant: BAE Systems PLC

    Inventor： The designation of the inventor has not yet been filed

    IPC: B64D39/00 ,  H04B7/185 ,  B64C39/02

    CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/063

    Abstract: Disclosed is a data transfer method comprising: performing a refuelling process including receiving, by an aircraft (104), aircraft fuel from a first entity (for example, a tanker aircraft (102)), the first entity being remote from the aircraft (104); and, during the refuelling process, sending data between the aircraft (104) and a second entity (for example, the tanker aircraft (102)), the second entity being remote from the aircraft (104). The data is sent as a radio frequency signal having a frequency in the range 50GHz to 70GHz. Preferably, the data is sent as a radio frequency signal having a frequency in the range 57GHz to 66GHz, for example 60GHz.

    Abstract translation: 公开了一种数据传送方法，包括：执行加油处理，包括由飞机（104）接收来自第一实体（例如，油船飞机（102））的飞机燃料，所述第一实体远离飞机（104 ）; 并且在加油过程期间，在飞机（104）和第二实体（例如，油轮飞行器（102））之间发送数据，第二实体远离飞行器（104）。 数据作为频率在50GHz至70GHz范围内的射频信号发送。 优选地，数据作为具有在57GHz至66GHz范围内的频率（例如60GHz）的射频信号发送。

    MODULAR AIRCRAFT SYSTEM
    3.
    发明申请
    MODULAR AIRCRAFT SYSTEM 审中-公开
    模块化飞机系统

    公开(公告)号：WO2017180392A1

    公开(公告)日：2017-10-19

    申请号：PCT/US2017/026146

    申请日：2017-04-05

    Applicant: AL-SABAH, Nasser M. ,  33100.81 PATENT TRUST

    Inventor： AL-SABAH, Nasser M.

    IPC: B64C3/38 ,  B64C3/34 ,  B64C9/00 ,  B64C9/32 ,  B64C13/00 ,  B64C13/20 ,  B64C39/02 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14

    CPC classification number: B64C3/38 ,  B64C1/26 ,  B64C3/34 ,  B64C5/06 ,  B64C9/00 ,  B64C9/326 ,  B64C13/00 ,  B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/063 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/16 ,  B64C2201/165 ,  B64C2211/00 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D37/00 ,  B64D39/00 ,  B64D47/08 ,  Y02T50/32

    Abstract: The modular aircraft system includes a single fuselage (10) having a permanently installed empennage (12) and plural sets of wing modules (46a, 46b, 66a, 66b, 68a, 68b) and engine modules (56, 60, 64), with each wing and engine module optimized for different flight conditions and missions. The fuselage (10) and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings (46a, 46b) having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings (68a, 68b) having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module (66a, 66b) is also provided. Turboprop (56), single turbojet (60), and dual turbojet (64) engine modules are provided for installation depending upon mission requirements.

    Abstract translation: 模块化飞行器系统包括具有永久安装的尾翼（12）和多组翼模块（46a，46b，66a，66b，68a，68b）的单个机身（10）和发动机模块 56,60,64），每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身（10）和每个模块被配置为用于模块的快速移除和安装以最小化飞行器的停机时间。 当高度耐力和/或重量承载能力不受重视时，提供具有相对低纵横比的短翼（46a，46b）用于相对高速飞行。 提供具有高纵横比的长翼（68a，68b）用于速度不是绝对重要的较长距离和耐力飞行。 还提供了中跨翼模块（66a，66b）。 根据任务要求，提供涡轮螺旋桨发动机（56），单涡轮喷气发动机（60）和双涡轮喷气发动机（64）发动机模块用于安装。

    AIRCRAFT DATA TRANSFER
    4.
    发明申请
    AIRCRAFT DATA TRANSFER 审中-公开
    飞机数据传输

    公开(公告)号：WO2016181116A1

    公开(公告)日：2016-11-17

    申请号：PCT/GB2016/051313

    申请日：2016-05-09

    Applicant: BAE SYSTEMS PLC

    Inventor： PESCOD, Christopher Ralph ,  SMITH, Andrew James

    IPC: B64D39/00 ,  H04B7/185 ,  B64C39/02

    CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/063

    Abstract: Disclosed is a data transfer method comprising: performing a refuelling process including receiving, by an aircraft (104), aircraft fuel from a first entity (for example, a tanker aircraft (102)), the first entity being remote from the aircraft (104); and, during the refuelling process, sending data between the aircraft (104) and a second entity (for example, the tanker aircraft (102)), the second entity being remote from the aircraft (104). The data is sent as a radio frequency signal having a frequency in the range 50GHz to 70GHz. Preferably, the data is sent as a radio frequency signal having a frequency in the range 57GHz to 66GHz, for example 60GHz.

    Abstract translation: 公开了一种数据传输方法，包括：执行加油过程，包括由飞机（104）接收来自第一实体（例如，油轮飞机（102））的飞行器燃料，所述第一实体远离飞机（104 ）; 并且在加油过程期间，在飞机（104）和第二实体（例如，油罐飞机（102））之间发送数据，第二实体远离飞行器（104）。 该数据作为具有在50GHz至70GHz范围内的频率的射频信号发送。 优选地，数据作为具有在57GHz至66GHz范围内的频率（例如60GHz）的射频信号发送。

    System and method of automatic piloting for in-flight refuelling of aircraft, and aircraft comprising said system
    6.
    发明授权
    System and method of automatic piloting for in-flight refuelling of aircraft, and aircraft comprising said system 有权
    系统和方法，用于飞机的飞行期间飞机自动控制Auftankoperationen，以及含有该平面的系统。

    公开(公告)号：EP2338793B8

    公开(公告)日：2017-01-11

    申请号：EP10195529.2

    申请日：2010-12-16

    Applicant: LEONARDO S.P.A.

    Inventor： Pepicelli, Geremia ,  Portaro, Gaetano ,  Bava, Renzo

    IPC: B64D39/00

    CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/063 ,  G05D1/104

    Abstract: An automatic-piloting system (15) configured for being set on a receiver aircraft (1) and for controlling operations of in-flight refuelling of said receiver aircraft (1), comprising: first detection means (8), set on the receiver aircraft (1) and configured for acquiring first geometrical information associated to a first detection area (22) and a second detection area (24) belonging to a tanker aircraft (20), the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system (15); processing means (14), configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft (1) with respect to the tanker aircraft (20); and an automatic-pilot device (2) coupled to the processing means (14) and configured for varying flight parameters of the receiver aircraft (1) on the basis of the first position information.

    MICRO HYBRID GENERATOR SYSTEM DRONE
    10.
    发明申请
    MICRO HYBRID GENERATOR SYSTEM DRONE 有权
    微型混合发电机系统

    公开(公告)号：US20160137304A1

    公开(公告)日：2016-05-19

    申请号：US14942600

    申请日：2015-11-16

    Applicant: TOP FLIGHT TECHNOLOGIES, INC.

    Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

    IPC: B64D27/02 ,  B64D33/08 ,  B64C39/02 ,  B64C27/00 ,  B64C27/08

    CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

    Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

    Abstract translation: 一种包括至少一个转子电动机的无人驾驶飞行器。 转子电机由微型混合发电系统供电。 微型混合发电机系统包括被配置为向至少一个转子电动机提供电力的可再充电电池，被配置为产生机械功率的小型发动机，耦合到小型发动机的发电机电动机，并且被配置为使用由 小型发动机，桥式整流器，被配置为将由发电电动机产生的交流电力转换为直流电力，并将DC电力提供给可再充电电池和至少一个转子电动机中的一个或两者;以及电子控制单元， 所述小型发动机的节气门至少部分地基于至少一个负载的功率需求，所述至少一个负载包括所述至少一个转子电动机。

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