| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 设有使其成为两栖式的附件的旋翼无人机 | CN201510964554.8 | 2015-12-21 | CN105711824A | 2016-06-29 | G·拉法根; K·法戈; Y·贝纳塔 |
| 无人机(10)包括主体(12)和多个推进单元，每个推进单元设有由相应的马达驱动的推进器(18)，不同的马达能够以差异化的方式控制，以便在姿态和速度上操纵所述无人机，并且产生升力。所述附件包括轴(20)，轴(20)相对于所述无人机的主前进方向在横向取向(X)上可移除地紧固到无人机主体，并且在定位成与所述无人机的重心对齐且在该重心上方的点(22)处。所述附件包括两个环形元件(26)，所述两个环形元件(26)彼此独立地自由旋转地安装在轴(20)的相应的端部处且相对于无人机主体(12)对称。这些环形元件(26)相对于水的密度低于所述单元，并且环形元件(26)的直径高于所述无人机的总尺寸。 | ||||||
| 2 | 无人驾驶的飞机和用于无人驾驶的飞机的运行方法 | CN201380057222.0 | 2013-10-22 | CN104903192B | 2017-11-07 | J.施泰因旺德尔; F.施塔格利亚诺; J.范图尔 |
| 本发明涉及一种无人驾驶的飞机(10)，其驱动器(12)包括构造为柴油和/或煤油马达的带有用于马达增压的增压装置(30)的内燃机(28)。特别地混合驱动器(32)设置为驱动器(12)，更特别地将并联混合驱动器设置为驱动器(12)。 | ||||||
| 3 | 无人驾驶的飞机和用于无人驾驶的飞机的运行方法 | CN201380057222.0 | 2013-10-22 | CN104903192A | 2015-09-09 | J.施泰因旺德尔; F.施塔格利亚诺; J.范图尔 |
| 本发明涉及一种无人驾驶的飞机(10)，其驱动器(12)包括构造为柴油和/或煤油马达的带有用于马达增压的增压装置(30)的内燃机(28)。特别地混合驱动器(32)设置为驱动器(12)，更特别地将并联混合驱动器设置为驱动器(12)。 | ||||||
| 4 | 一种有线无人机用于桥墩面的检测装置 | CN201610079824.1 | 2016-02-05 | CN107042887A | 2017-08-15 | 蒋宗池 |
| 本发明公开了一种有线无人机用于桥墩面的检测装置，包括旋翼无人机、接触杆、电源和升降机构，其中升降机构还包括变频电机、传动轴、卷筒和机架，其中变频电机固定安装在机架上，变频电机的输出端与传动轴固定连接，而传动轴沿轴向依次固定有卷筒Ⅰ和卷筒Ⅱ，旋翼无人机连接的接触杆分别与电源的正负极输出端连接，所述升降机构卷筒上的绞绳分别与接触杆的同一端连接，通过升降机构在纵向上控制水平运行的旋翼无人机观测设备的升降，实现旋翼无人机既能沿着接触杆轴向水平巡航拍摄观测，填补了大型桥梁检测的技术空白。 | ||||||
| 5 | 一种救援飞行器 | CN201610585853.5 | 2016-07-22 | CN106005394A | 2016-10-12 | 黎欣 |
| 本发明提供一种救援飞行器，包括机体(1)、升力发动机(2)、姿态喷流器(3)、尾推发动机(4)、水平尾翼(5)、垂直尾翼(6)、起落架(7)、飞控设备舱(8)、救援收纳舱(9)，2台升力发动机(2)内置机体(1)航向方向两侧，4个姿态喷流器(3)成对内置机体(1)展向方向两侧，机体(1)航向方向机尾端安装有相互垂直的水平尾翼(5)和垂直尾翼(6)，垂直尾翼(6)上安装有尾推发动机(4)，机体(1)内的两侧升力发动机(2)之间安装有飞控设备舱(8)和救援收纳舱(9)。本发明所提供的救援飞行器，具有垂直起降能力，且桨叶内置机体中可在狭小空间中救援，具有快速高效、受地理空间限制少等优势。 | ||||||
| 6 | 一种无人运输机 | CN201610313051.9 | 2016-05-12 | CN105947172A | 2016-09-21 | 陈涛; 窦炳耀; 蒋彪; 邵运英 |
| 本发明公开了一种无人运输机。所述无人运输机包括机身(1)、第一发动机(2)、第二发动机(3)以及机翼(4)，所述机身(1)的中部至机头部分与所述机翼(4)融合；所述第一发动机(2)以及所述第二发动机(3)内埋至所述机翼(4)的翼根部；所述机身(1)的中部至机尾部分呈长条状；所述机身(1)的底部设置有投放舱门(11)，所述投放舱门(11)用于在所述飞机平飞过程中投放物品；机身中部的底部自所述投放舱门处向所述机身的尾部的顶部方向倾斜延伸，并与所述机身的尾部的顶部融合，该倾斜延伸部分上设置有倾斜投掷舱门(12)。本方案采用固定翼飞机设计，相较旋翼机/直升机等，具有飞行距离远，飞行速度快，载重能力强的特点。 | ||||||
| 7 | Motor feed antenna for vehicle | US14804170 | 2015-07-20 | US09735465B2 | 2017-08-15 | Karoly Becze; Vincent Martin Kemler; Randy Edward Standke |
| 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. | ||||||
| 8 | VTOL symmetric airfoil fuselage of fixed wing design | US14849814 | 2015-09-10 | US09567079B2 | 2017-02-14 | Jonathon Thomas Johnson; Elizabeth V. M. Johnson |
| 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. | ||||||
| 9 | MOTOR FEED ANTENNA FOR VEHICLE | US14804170 | 2015-07-20 | US20170025744A1 | 2017-01-26 | Karoly Becze; Vincent Martin Kemler; Randy Edward Standke |
| 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. | ||||||
| 10 | Unmanned Aircraft and Operation Method for the Same | US15953209 | 2018-04-13 | US20180283292A1 | 2018-10-04 | Juergen STEINWANDEL; Florian STAGLIANO; Jan VAN TOOR |
| 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. | ||||||
| 11 | Unmanned Aircraft and Operation Method for the Same | US14439502 | 2013-10-22 | US20150285165A1 | 2015-10-08 | Juergen Steinwandel; Florian Stagliano; Jan Van Toor |
| 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. | ||||||
| 12 | UNBEMANNTES LUFTFAHRZEUG UND BETRIEBSVERFAHREN | EP13811348.5 | 2013-10-22 | EP2914490B1 | 2017-05-24 | STEINWANDEL, Jürgen; STAGLIANO, Florian; VAN TOOR, Jan |
| 13 | Drone structure | US14917299 | 2014-09-05 | US10081432B2 | 2018-09-25 | Guglielmo Rossi; Sandro Moretti; Nicola Casagli |
| 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′). | ||||||
| 14 | Modular aircraft system | US15096216 | 2016-04-11 | US09505484B1 | 2016-11-29 | Nasser M. Al-Sabah |
| The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings 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 having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle. | ||||||
| 15 | AN IMPROVED DRONE STRUCTURE | US14917299 | 2014-09-05 | US20160214728A1 | 2016-07-28 | Guglielmo ROSSI; Sandro MORETTI; Nicola CASAGLI |
| 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′). | ||||||
| 16 | VTOL SYMMETRIC AIRFOIL FUSELAGE OF FIXED WING DESIGN | US14849814 | 2015-09-10 | US20160096613A1 | 2016-04-07 | Jonathon Thomas Johnson; Elizabeth V.M. Johnson |
| 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. | ||||||
| 17 | MOTOR FEED ANTENNA FOR VEHICLE | EP16728176.5 | 2016-05-23 | EP3326239A1 | 2018-05-30 | BECZE, Karoly; KEMLER, Vincent Martin; STANDKE, Randy Edward |
| 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. | ||||||
| 18 | UNBEMANNTES LUFTFAHRZEUG UND BETRIEBSVERFAHREN HIERFÜR | EP13811348.5 | 2013-10-22 | EP2914490A1 | 2015-09-09 | STEINWANDEL, Jürgen; STAGLIANO, Florian; VAN TOOR, Jan |
| The invention relates to an unmanned aircraft (10), the drive (12) of which comprises an internal combustion engine (28) designed as a diesel and/or kerosene engine and having a charging device (30) for charging the engine. In particular a hybrid drive (32), more especially a parallel hybrid drive, is provided as the drive (12). | ||||||
| 19 | 드론 | KR1020160079369 | 2016-06-24 | KR101804328B1 | 2017-12-04 | 이승재 |
| 본발명은조종사없이무선전파의유도에의해서비행및 조종이가능한비행체인드론에관한것으로서, 좀더 상세하게는, 종래드론본체의최외곽에구비되어드론추진체로사용되는다수의고속회전블레이드를생략하는대신흡입한공기를소정압력으로압축후, 고속으로분사시켜추진력을발생시키는무블레이드형추진체를가지는드론에관한것으로, 본발명에따른드론은, 외부로부터공기를흡입하여소정압력값으로압축시킨후 배출시키는압축공기생성부(10, 20); 중앙에상기압축공기생성부(10, 20)가구비되고, 외측면에는소정간격을두고다수의압축공기배출홀(32)이형성되며, 내부에는상기다수의압축공기배출홀(32)과각각연통되어상기압축공기생성부(10, 20)로부터발생되는압축공기를안내배출시키는다수의분기배출로(31)가형성되는몸체부(30); 및상측에서하측으로갈수록중공반경이점차확장되는내부중공의원통형태로형성되어외측이상기몸체부(30)에결합되고, 외측단에는상기압축공기배출홀(32)과연통되게입구홀(41)이구비되어상기압축공기배출홀(32)로부터배출된압축공기가상기입구홀(41)을통해유입되며, 상측내주면에는압축공기가하측으로분사되는분사노즐부(43)가내주면을따라형성되고, 내부에는상기입구홀(41)을통해유입된압축공기를상기분사노즐부(43)로안내배출시키는분사배출로(42)가구비되는추진체(40);를포함하여구성되고, 상기분사노즐부(43)의하측면에는, 압축공기가소정방향으로편향분사되게다수의편향돌기부(44)가소정간격을두고소정높이로구비되는것을특징으로한다. | ||||||
| 20 | 드론 | KR1020160044900 | 2016-04-12 | KR1020170116814A | 2017-10-20 | 이승재 |
| 본발명은조종사없이무선전파의유도에의해서비행및 조종이가능한비행체인드론에관한것으로서, 좀더 상세하게는, 종래드론본체의최외곽에구비되어드론추진체로사용되는다수의고속회전블레이드를생략하는대신압축공기를고속으로분사시켜추진력을발생시키는무블레이드형추진체를가지는드론에관한것으로, 본발명에따른드론(1)은, 외부로부터공기를흡입하여소정압력값으로압축시킨후 배출시키는압축공기생성부(10, 20); 중앙에상기압축공기생성부(10, 20)가구비되고, 외측면에는소정간격을두고다수의압축공기배출홀(32)이형성되며, 내부에는상기다수의압축공기배출홀(32)과각각연통되어상기압축공기생성부(10, 20)로부터발생되는압축공기를안내배출시키는다수의분기배출로(31)가형성되는몸체부(30); 및상측에서하측으로갈수록중공반경이점차확장되는내부중공의원통형태로형성되어외측이상기몸체부(30)에결합되고, 외측단에는상기압축공기배출홀(32)과연통되게입구홀(41)이구비되어상기압축공기배출홀(32)로부터배출된압축공기가상기입구홀(41)을통해유입되며, 상측내주면에는압축공기가하측으로분사되는분사노즐부(43)가내주면을따라형성되고, 내부에는상기입구홀(41)을통해유입된압축공기를상기분사노즐부(43)로안내배출시키는분사배출로(42)가구비되는추진체(40);를포함하여구성되는것을특징으로한다. | ||||||
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