子分类：
| 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 | 一种带有四个辅助翼的混合动力无人机及其控制方法 | CN201610350995.3 | 2016-05-25 | CN105882954A | 2016-08-24 | 孟光磊; 潘海兵; 梁宵; 田丰; 喻勇涛; 薛继佳; 朱琳琳 |
| 一种带有四个辅助翼的混合动力无人机及其控制方法。本发明综合直升机与四旋翼的优势，综合油动与电动的优势，设计了一款以直升机架构为主体，以四旋翼架构为辅助的油、电混合动力系统的垂直起降无人机。此架构无人机包括主旋翼、垂直尾翼、左前辅助旋翼、右前辅助旋翼、左后辅助旋翼和右后辅助旋翼，共六个旋翼。无人机整体上采用直升机的基本架构，但将传统的直升机主旋翼的浆距可调浆叶换为普通的固定浆距浆叶，此种变动虽然使主旋翼失去了控制飞行方向的功能，但却有效降低了制造成本。而无人机飞行方向和机动动作的控制，则由垂直尾翼和四个辅助旋翼完成。本发明的主旋翼采用内燃机为动力，以增强无人机的续航能力，其他旋翼采用无刷电机为动力，以提高无人机的稳定性和机动性。 | ||||||
| 2 | 基于合成射流技术的小型喷气飞行器 | CN201710541384.1 | 2017-07-05 | CN107364583A | 2017-11-21 | 方剑; 蔡乐 |
| 基于合成射流技术的小型喷气飞行器。本发明涉及一种基于合成射流技术的小型喷气飞行器。所述的动力腔室（6）设置在球形外壳体（1）的内部下端，所述的球形外壳体（1）的内部上端设置支撑板Ⅰ（10）与支撑板Ⅱ（11），所述的支撑板Ⅰ（10）上设置电池（3），所述的支撑板Ⅰ（10）的下方设置支撑板Ⅱ（11），所述的支撑板Ⅱ（11）上从左至右依次设置振荡模块（4）、调速器（5）与飞控模块（2）。本发明用于小型喷气飞行器。 | ||||||
| 3 | 涵道推进器及小型无人飞机 | CN201710854482.0 | 2017-09-20 | CN107472523A | 2017-12-15 | 杨冰; 鄢胜峰; 陶恕; 陈风虎; 余士雄; 喻畅; 陈浩; 匡昊盾; 张冬林; 曾小玉; 吴倩 |
| 本发明公开了一种涵道推进器及小型无人飞机，装配于小型无人飞机的机壳上，用于提供飞行动力；所述机壳包括上表面及下表面，涵道推进器包括两端贯通的涵道壳体、固定座、动力件以及螺旋桨；涵道壳体装配于机壳上且形成贯通上表面和下表面的涵道腔，固定座设置于涵道腔内，动力件装配于固定座上且收容于涵道腔内，螺旋桨收容于涵道腔内且与动力件传动连接。上述小型无人飞机中，通过设置涵道推进器作为整机的动力来源，而设置于涵道推进器上的螺旋桨被收容于涵道腔内，即隐形设置而非暴露于机壳外，使得小型无人飞机在飞行过程中，避免因螺旋桨与外界物体碰撞，从而有效提高整机的安全性和可靠性。 | ||||||
| 4 | 气动飞行器 | CN201610027627.5 | 2016-01-07 | CN105711836A | 2016-06-29 | 孙秀文 |
| 本发明公开了用压缩空气作为动力的遥控无人飞行器，用空气压缩机压缩空气输送到无人机轻质储气罐里面作为飞行原动力，通过气动马达带动单轴或者多轴螺旋桨转动，实现无人机飞行，本系统由纤维储气罐1、气流开关2、智能减压阀3、蓄电池4、航电系统5、充气口6、机架7、螺旋桨8、气动马达9、安全气囊10、降落伞11、输气管12组成，各个部件全部固定在机架上，另外还有外置充气机和遥控器以及挂载负重，蓄电池4给气流开关2和智能减压阀3的电动马达供电，智能减压阀3在航电系统5的控制下单独控制每个轴的气动马达9，并通过重力感应调节输入每个轴的气动马达9的气流，可以使无人机平稳飞行。 | ||||||
| 5 | 一种混合动力的无人机 | CN201610159972.4 | 2016-03-18 | CN105711825A | 2016-06-29 | 吴李海 |
| 本发明适用于遥控机器人技术领域，提供了一种混合动力的无人机，该无人机包括飞行装置、遥控装置、燃料发动机、同轴正反转齿轮箱及同轴上下正反转螺旋桨，所述飞行装置通过无线通信连接所述飞行装置，所述燃料发动机设于所述飞行装置的顶面中心点，所述同轴正反转齿轮箱设于所述燃料发动机上，所述燃料发动机的极轴置于所述同轴正反转齿轮箱内与所述同轴正反转齿轮箱内的齿轮连接，所述同轴上下正反转螺旋桨的正反转旋转轴设于所述同轴正反转齿轮箱上，所述同轴上下正反转螺旋桨的正反转旋转轴分别连接所述同轴正反转齿轮箱内的正反转旋转齿轮，所述燃料发动机的发电机输出端连接所述供电装置。结构简单，操作方便，维护方便，成本低廉。 | ||||||
| 6 | マルチロータ航空機 | JP2017543702 | 2015-10-28 | JP2017533863A | 2017-11-16 | アンダース ユング |
| マルチロータ航空機(1、1’、1''、1'''、1''''、1'''''、1'''''')は、少なくとも三つの油圧モータ(11、21、31)と、それぞれが前記少なくとも三つの油圧モータ(11、21、31)の一つにより回転可能な少なくとも三つのロータ(10、20、30)と、少なくとも一つのパワーユニット(2)と、それぞれが前記少なくとも三つの油圧モータ(11、21、31)の一つに加圧流体を供給して駆動することにより前記少なくとも三つのロータ(10、20、30)の一つを回転させるための少なくとも三つの第一油圧ポンプ(12、22、32)と、前記少なくとも三つの油圧モータ(11、21、31)へ分配される加圧流体の流れを変更することによって、前記マルチロータ航空機の動作制御を行なう制御ユニット(6)とを備えている。前記少なくとも三つの油圧ポンプ(12、22、32)から前記少なくとも三つの油圧モータ(11、21、31)への加圧流体の流れのそれぞれを制御する少なくとも一つの制御弁(13、23、33)によって、前記少なくとも三つの油圧モータ(11、21、31)へ分配される加圧流体の流れが個別に制御可能である。【選択図】図2 | ||||||
| 7 | Aerial Vehicle Refueling System incorporating a Universal Refueling Interface | US15160071 | 2016-05-20 | US20170334581A1 | 2017-11-23 | Michael White; Miles Austin |
| A system for autonomously replacing batteries or fuel cells on small aerial vehicles such as Unmanned Aerial Vehicles (UAVs) or radio-controlled aircraft (RC) is described. At the core of this system is a “universal battery receptacle” that can be added to a variety of unmanned aircraft platforms and provides a uniform interface for battery or fuel cell replacement in the form of a commensurately designed “universal fuel cell”.Additionally, a system is described through which an aerial vehicle can be accepted, manipulated, the batteries replaced, and the vehicle re-launched, all without direct user intervention. Such systems can be deployed across a geographic area to increase the range of aerial vehicles without extensive ground support personnel. | ||||||
| 8 | Unmanned aerial vehicle angular reorientation | US14947871 | 2015-11-20 | US09776709B2 | 2017-10-03 | Carlos Thomas Miralles |
| A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | ||||||
| 9 | Aircraft with a plurality of engines driving a common driveshaft | US15204547 | 2016-07-07 | US09688397B2 | 2017-06-27 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 10 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION | US14947871 | 2015-11-20 | US20160185447A1 | 2016-06-30 | Carlos Thomas Miralles |
| A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | ||||||
| 11 | Long range hybrid electric airplane | US11703362 | 2007-02-07 | US20080184906A1 | 2008-08-07 | Joseph B. Kejha |
| An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe. | ||||||
| 12 | DISPOSITIF AEROPORTE | EP15759845.9 | 2015-07-15 | EP3172435A1 | 2017-05-31 | LOZANO, Rogelio |
| The invention concerns an airborne device (10) comprising at least three supporting wings (12) and a linking device (18), the wings being linked to each other by first flexible cables (16), each wing being further linked to the linking device (18) by a second flexible cable (20), the linking device being linked to a third flexible cable (22) intended to be linked to a base (46, 48), the first, second and third cables being tensioned when the airborne device is carried in the wind. | ||||||
| 13 | Multi-Hybrid Aircraft Engine | US16326717 | 2017-08-28 | US20190186418A1 | 2019-06-20 | Orlorunfemi Jacob Azundah |
| A multi-hybrid aircraft engine that includes a primary compressor 1, a multiplier 199 comprising a drive block, a driven block, driven block pistons 54, and primary shafts 78 and 41; an output shaft 105, and a speed regulator 167. The multi-hybrid aircraft engine is configured such that the primary compressor 1 is fluidly connected to the drive block 46 which is mechanically connected to the driven block 57. The primary compressor 1 pumps compressible fluid to the drive block 46 through the speed regulator 167 to drive the drive block 46, which in turn, drives the primary shafts 78 and 41. The primary shafts 78 and 41 drive the driven block 57, which pumps fluid via the driven block pistons 54, to the drive block 46 through the speed regulator 167 to increase the flow rate of compressible fluid within the multi-hybrid aircraft engine. Furthermore, the driven block 57 provides a shaft 68 that is connected to sets of planetary gears 62 connected to an output shaft 105 that drives a propeller 186. | ||||||
| 14 | MULTI-ROTOR AERIAL VEHICLE | US15523244 | 2015-10-28 | US20180016022A1 | 2018-01-18 | Anders Ljung |
| Multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″), wherein the control of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31. | ||||||
| 15 | ROTARY-WING VEHICLE AND SYSTEM | US15056408 | 2016-02-29 | US20170247107A1 | 2017-08-31 | Istvan Hauer; Cyril Blank; Allan Vaitses |
| An apparatus comprising a body defining a first vertical axis, two or more frame members each having a longitudinal axis and having an inner-end and an outer-end connected to the body at the inner-end and where a first horizontal geometrical plane is generally coincident with the longitudinal axis of each of the two or more frame members and where the first horizontal geometrical plane is generally orthogonal to the first vertical axis, two or more rotary-wings each comprising one or more blades whose rotation defines a first rotational axis which is configurable to be nearly parallel with the first vertical axis and comprising a second rotational axis which is configurable to be approximately parallel first horizontal geometrical plane where a first of the two or more rotary-wings having a blade-inner-end and a first blade-outer-end rotatably connected by its blade-inner-end to a first transmission is disposed substantially on the outer-end of a first of the two or more frame members, a second of the two or more rotary-wings having a blade-inner-end and a blade-outer-end rotatably connected by its blade-inner-end to a second transmission is disposed substantially on the outer-end of a second of the two or more frame members, where each of the first rotational axes is disposed on the opposite side of plane which is coincident with the first vertical axis, where the direction of rotation of a first of the two or more rotary-wings about its first rotational axis is opposite of that of the second of the two or more rotary-wings about its first rotational axis, and, where the rotational disk defined by the rotation of the blade-outer-end of the first of the two or more rotary-wings is at least partially coincident with rotational disk defined by the rotation of the blade-outer-end of the second of the two or more rotary-wings. | ||||||
| 16 | HYBRID PROPULSION POWER SYSTEM FOR AERIAL VEHICLES | US15163499 | 2016-05-24 | US20170088277A1 | 2017-03-30 | Ankita Ghoshal |
| This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles which includes a thermoelectric generator. The thermoelectric generator includes a first heat exchanger disposed within an exhaust duct of an unmanned aerial vehicle. The thermoelectric generator further includes a first ceramic layer disposed on the first heat exchanger and a first and second metal tab bonded to the first ceramic layer. The thermoelectric generator further includes a second metal tab bonded to a second ceramic layer. At least one N-type thermoelectric leg is disposed between the first metal tab bonded to the first ceramic layer and the metal tab bonded to the second ceramic layer. Further, at least one P-type thermoelectric leg is disposed between the second metal tab bonded to the first ceramic layer and the metal tab bonded to the second ceramic layer. | ||||||
| 17 | Aircraft With A Plurality Of Engines Driving A Common Driveshaft | US15204547 | 2016-07-07 | US20160311530A1 | 2016-10-27 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 18 | HYBRID PROPULSION POWER SYSTEM FOR AERIAL VEHICLES | US14867152 | 2015-09-28 | US20160090184A1 | 2016-03-31 | Ankita Ghoshal |
| This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles. The hybrid propulsion system includes a combustor, a thermophotovoltaic generator, and a thermoelectric generator. The combustor burns a chemical based fuel to produce radiation and heat that are converted into electricity used to power the aerial vehicle. The thermophotovoltaic generator is positioned to receive radiation and remnant heat generated by flames in the combustor while the thermoelectric generator receives heat from exhausted flue gases from the combustor. | ||||||
| 19 | Aircraft with freewheeling engine | US13442544 | 2012-04-09 | US08720814B2 | 2014-05-13 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 20 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION | US15689945 | 2017-08-29 | US20180093755A1 | 2018-04-05 | Carlos Thomas Miralles |
| A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | ||||||
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