-
公开(公告)号：US20150285165A1
公开(公告)日：2015-10-08
申请号：US14439502
申请日：2013-10-22
Applicant: EADS DEUTSCHLAND GMBH
Inventor： Juergen Steinwandel , Florian Stagliano , Jan Van Toor
CPC classification number: F02D29/02 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/044 , B64C2201/066 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/16 , B64D27/02 , B64D27/24 , B64D31/00 , B64D41/00 , B64D2027/026 , Y02T50/44 , Y02T50/64
Abstract: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.
Abstract translation: 无人机包括具有柴油或煤油内燃机的推进系统和用于发动机充气的充电装置。 推进系统可以是混合推进系统或并联混合推进系统。
-
公开(公告)号：US20170341769A1
公开(公告)日：2017-11-30
申请号：US15606201
申请日：2017-05-26
Applicant: Neoex Systems, Inc.
Inventor： Mark Steven Haberbusch , Philip Travis Putman
CPC classification number: B64D39/06 , B64C39/024 , B64C2201/063 , B64C2201/16 , B64C2201/18 , B64D37/14 , B64D2041/005 , B64F1/28 , F17C5/007 , F17C5/02 , F17C2205/0355 , F17C2205/037 , F17C2221/012 , F17C2223/0161 , F17C2223/033 , F17C2225/0161 , F17C2225/033 , F17C2227/0107 , F17C2227/0135 , F17C2227/044 , F17C2260/032 , F17C2265/065 , F17C2270/0189
Abstract: A system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.
-
公开(公告)号：US20160214728A1
公开(公告)日：2016-07-28
申请号：US14917299
申请日：2014-09-05
Applicant: UNIVERSITA DEGLI STUDI DI FIRENZE
Inventor： Guglielmo ROSSI , Sandro MORETTI , Nicola CASAGLI
CPC classification number: B64D27/26 , B64C27/08 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/123 , B64C2201/16
Abstract: A structure of drone (100) comprises a frame (110) comprising an engagement portion (110′), said engagement portion (110′) being a strip having a predetermined geometry. The structure of drone (100) also comprises a plurality of propulsion elements (120). Each propulsion element (120) is arranged, in use, to be engaged in a removable way to the engagement portion (110′) at a any point of the strip, in such a way to easily change the number and the arrangement of the propulsion elements (120) present on the engagement portion (110′).
Abstract translation: 无人机（100）的结构包括具有接合部分（110'）的框架（110），所述接合部分（110'）是具有预定几何形状的条带。 无人机（100）的结构还包括多个推进元件（120）。 每个推进元件（120）在使用中被布置成以可移除的方式接合到条带的任何点处的接合部分（110'），以便容易地改变推进器的数量和布置 存在于接合部分（110'）上的元件（120）。
-
公开(公告)号：US20160096613A1
公开(公告)日：2016-04-07
申请号：US14849814
申请日：2015-09-10
Applicant: Jonathon Thomas Johnson , Elizabeth V.M. Johnson
Inventor： Jonathon Thomas Johnson , Elizabeth V.M. Johnson
CPC classification number: B64C39/024 , B64C25/32 , B64C29/04 , B64C2025/325 , B64C2201/021 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/16 , B64C2201/18
Abstract: Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.
Abstract translation: 目前的飞机技术包括固定翼，多转子和矢量引擎设计。 固定翼技术和矢量引擎技术的综合已经实施，但仅限于传统的固定翼设计飞机。 所提出的飞机设计具有机身预期的创新，改进的矢量引擎设计系统和起落架系统。
-
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。
-
Patent Agency Ranking
公开(公告)号：WO2014067506A1
公开(公告)日：2014-05-08
申请号：PCT/DE2013/000620
申请日：2013-10-22
Applicant: EADS DEUTSCHLAND GMBH
Inventor： STEINWANDEL, Jürgen , STAGLIANO, Florian , VAN TOOR, Jan
CPC classification number: F02D29/02 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/044 , B64C2201/066 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/16 , B64D27/02 , B64D27/24 , B64D31/00 , B64D41/00 , B64D2027/026 , Y02T50/44 , Y02T50/64
Abstract: Die Erfindung betrifft ein unbemanntes Luftfahrzeug (10), dessen Antrieb (12) einen als Diesel- und/oder Kerosinmotor ausgebildeten Verbrennungsmotor (28) mit Ladereinrichtung (30) zur Motoraufladung umfasst. Insbesondere ist als Antrieb (12) ein Hybridantrieb (32), mehr insbesondere ein Parallel-Hybridantrieb, vorgesehen.
Abstract translation: 本发明涉及无人驾驶飞行器（10），设计为柴油和/或煤油发动机燃烧发动机（28）与加载装置（30），用于强制吸气其驱动器（12）。 特别是，作为一个驱动器（12）是混合动力驱动（32），更具体地说，涉及并联式混合动力驱动，提供了。
-
公开(公告)号：WO2015036907A1
公开(公告)日：2015-03-19
申请号：PCT/IB2014/064278
申请日：2014-09-05
Applicant: UNIVERSITÀ DEGLI STUDI DI FIRENZE
Inventor： ROSSI, Guglielmo , MORETTI, Sandro , CASAGLI, Nicola
IPC: B64C39/02
CPC classification number: B64D27/26 , B64C27/08 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/123 , B64C2201/16
Abstract: A structure of drone (100) comprises a frame (110) comprising an engagement portion (110')/ said engagement portion (110') being a strip having a predetermined geometry. The structure of drone (100) also comprises a plurality of propulsion elements (120). Each propulsion element (120) is arranged, in use, to be engaged in a removable way to the engagement portion (110') at a any point of the strip, in such a way to easily change the number and the arrangement of the propulsion elements (120) present on the engagement portion (110').
Abstract translation: 无人机（100）的结构包括框架（110），其包括具有预定几何形状的条带的接合部分（110'）/所述接合部分（110'）。 无人机（100）的结构还包括多个推进元件（120）。 每个推进元件（120）在使用中被布置成以可移动的方式接合到条带的任何点处的接合部分（110'），以便容易地改变推进器的数量和布置 存在于接合部分（110'）上的元件（120）。
-
18.发明公开公开(公告)号：US20230259145A1
公开(公告)日：2023-08-17
申请号：US17747142
申请日：2022-05-18
Applicant: Skydio, Inc.
CPC classification number: G05D1/0646 , G05D1/106 , H04W4/021 , B64C39/024 , B64C2201/146 , B64C2201/16
Abstract: An unmanned aerial vehicle (UAV) comprises a flight control system and an electromechanical system directed by the flight control system. The flight control system is configured to track a position of a beacon that is in motion and monitor a difference between an actual position of the unmanned aerial vehicle and a desired position of the unmanned aerial vehicle relative to the position of the beacon. The flight control system configures one or more flight objectives based on one or more factors comprising whether the difference between the actual position and the desired position exceeds a threshold, wherein the flight objectives comprise a velocity objective and a position objective. The flight control system also commands the electromechanical system based at least on the one or more flight objectives.
-
公开(公告)号：US09735465B2
公开(公告)日：2017-08-15
申请号：US14804170
申请日：2015-07-20
Applicant: Qualcomm Incorporated
Inventor： Karoly Becze , Vincent Martin Kemler , Randy Edward Standke
CPC classification number: H01Q1/28 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/122 , B64C2201/16 , H01Q1/286 , H01Q1/46
Abstract: According to some embodiments, an unmanned vehicle includes a power supply configured to supply an electrical power signal to a motor for propelling the unmanned vehicle, a wireless communication device configured to transmit or receive a radio frequency (RF) signal, and a motor feed antenna coupled to the power supply and the wireless communication device, the motor feed antenna configured to conduct the electrical power signal from the power supply to the motor, and to transmit or receive RF signals as an antenna for the wireless communication device.
-
公开(公告)号：US09567079B2
公开(公告)日：2017-02-14
申请号：US14849814
申请日：2015-09-10
Applicant: Jonathon Thomas Johnson , Elizabeth V. M. Johnson
Inventor： Jonathon Thomas Johnson , Elizabeth V. M. Johnson
CPC classification number: B64C39/024 , B64C25/32 , B64C29/04 , B64C2025/325 , B64C2201/021 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/16 , B64C2201/18
Abstract: Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.
Abstract translation: 目前的飞机技术包括固定翼，多转子和矢量引擎设计。 固定翼技术和矢量引擎技术的综合已经实施，但仅限于传统的固定翼设计飞机。 所提出的飞机设计具有机身预期的创新，改进的矢量引擎设计系统和起落架系统。
-
-
-
-
-
-
-
-
-
Search Results
34
records
(took 0.038 seconds)
