CN112770972A - 由涡轮发电机驱动的模块化的多旋翼无人机 - Google Patents
由涡轮发电机驱动的模块化的多旋翼无人机 Download PDFInfo
- Publication number
- CN112770972A CN112770972A CN201980058019.2A CN201980058019A CN112770972A CN 112770972 A CN112770972 A CN 112770972A CN 201980058019 A CN201980058019 A CN 201980058019A CN 112770972 A CN112770972 A CN 112770972A
- Authority
- CN
- China
- Prior art keywords
- drone
- flight
- units
- frame
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000007788 liquid Substances 0.000 claims abstract description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract 2
- 239000000446 fuel Substances 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims 1
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- 239000004917 carbon fiber Substances 0.000 claims 1
- 239000002828 fuel tank Substances 0.000 abstract 1
- 230000008878 coupling Effects 0.000 description 5
- 238000010168 coupling process Methods 0.000 description 5
- 238000005859 coupling reaction Methods 0.000 description 5
- 239000003380 propellant Substances 0.000 description 5
- 239000000178 monomer Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/40—Modular UAVs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/24—Coaxial rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2211/00—Modular constructions of airplanes or helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/60—UAVs characterised by the material
- B64U20/65—Composite materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/10—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
本发明涉及一种大型的多旋翼的旋翼无人机,其能够通过连接器连接至相同的无人机以便增加载荷能力和飞行时间。其具有推进系统,该推进系统包括由8个电动马达组成的4个同轴的旋翼,电动马达以液体燃料为燃料的涡轮发电机(APU)驱动。机架包括:作为螺旋桨保护系统和无人机的诸如电子设备、燃料箱、发电机等各种部件的容器的中空的碳纤维结构;不朝无人机中心会聚而朝各个发动机会聚以保证机架中心有空间的方形的发动机支撑系统。能够模块化的可能性允许能够增加有用的有效载荷、自主性和可靠性的无限的装载配置。
Description
技术领域
本发明涉及一种具有高载荷能力、自主性、便于运输和使用的多旋翼无人机,其具有连接至其他单体单元以增加其诸如载荷、自主性和可靠性等能力的独特特征。
具体涉及航空领域,尤其涉及具有远程控制或自动飞行能力的无人航空载具(UAV,Unmanned Aerial Vehicle)。
背景技术
在现有技术中,与旋翼无人机的使用有关的一些问题尚未解决或没有充分解决。
特别是存在与载荷能力、自主性、可运输性和可靠性相关的问题。
特别是多旋翼机在设计阶段即具有预先确定的尺寸和重量的,其基于以下各项之间的比率来确定载荷能力和自主性:螺旋桨尺寸、马达、载具重量和电池容量。通常,较大的无人机尺寸意味着较高的可运输载荷能力和通常较大的飞行自主性。
然而,另一方面,由于尺寸和现场组装的原因,无人机的大尺寸会导致可运输性问题。
当前,多旋翼机被构造为运载小载荷(例如,大约几千克)并且保持飞行几十分钟(例如,40-60分钟)。为了运输大载荷,多旋翼机必须很大,具有大型的发动机、螺旋桨以及大而重的电池,以产生足够用于起飞的能量。
发明内容
本发明的目的是通过由涡轮发电机驱动的模块化的多旋翼无人机的创新系统来解决所有上述问题,该创新系统容许单体单元连接至其他相同单元以便增加载荷能力、自主性、可靠性,始终保持系统的运输便利性,并且容许供能系统由以液体燃料为燃料的涡轮发电机驱动的电动机组成。
特别是通过:
·具有中空结构的碳纤维机架,该机架构造简单,从而减少了部件总数,减轻了重量,赋予了整个系统更大的强度,并且该机架能够用作航空电子设备和控制系统、推进剂和布线的容器;
·方形的旋翼承载系统,与其他旋翼承载系统不同,方形的旋翼承载系统不在多旋翼机的中心处会聚为连接点,从而提供了用于安装发电机的空间,并且还在整个机架上提供了良好的重量分布(图2.2)
·多旋翼无人机的宽度在220到300厘米之间,以便能够将它们放置在卡车的装载平台上,或者可以将它们堆叠起来以在标准运输容器上运输和存放;
·在双马达四旋翼机配置中使用带有大直径螺旋桨(40至50英寸)的8个无刷电动马达,对于每个轴,无刷电动马达都叠加在相反的螺旋桨上(4个同轴的旋翼),能够获得200至400kg的推力(图l);
·具有涡轮发电机的电动推进系统,涡轮发电机具有能够安装在机架内部或外部的推进剂箱,能够产生30/50KW的能量;
·通过无人机各侧面上的物理连接系统将多架无人机接合在一起以便创建多样化飞行和装载配置:
o该系统容许通过多个单体模块的连接以便增加载荷能力;
o在运输期间保持恒定的飞行范围和有限度的体积变大(limited bulkiness)的同时使载荷能力可变(见图5)的1、2、2×2、2×3、2×4、3×3、2×5、3×4、3×5、4×4等配置的无限可能性(见图4);
·耦合系统,其容许在多个单体模块之间连接数据线和能量线(见图2.1);
·在各个模块之间联合的情况下,系统变得冗余,因为在发生发电机故障的情况下,马达将能够使用所连接的其他发电机的能量;
·每个单个单元中的冗余的航空电子设备和控制系统(AVIONICS),以及每个单元都能够作为其他单元的备用电子设备:
o仅使用一个模块时,该单元将被定义为主导单元(MASTER);
o使用多个单元时,只有一个单元将成为主导单元并且作为所有其他单元的飞行控制器。其他单元将成为辅助单元(SLAVE)并且由系统自动配置用于与主导单元相关的飞行,只有在主导单元发生故障的情况下,辅助单元才会变为主导单元并控制其他单元;
·该系统将配备有全球定位传感器的系统,其可以校正定位误差(RTK-实时动态(Real Time Chinematik)),防撞和检测障碍物,进行传输数据和立体导航和定位摄像机;
·能够使用单体单元系统的可能性将容许以便利的方式运输堆叠在卡车或运输容器中的单体单元系统,并且仅在实际使用它们的地方才能将它们连接成型(见图5)
附图说明
现在参照以举例而非限制的方式给出的附图说明本发明,在附图中:
·图1:特别是描述无人机的特殊形状和主要部件及其定位:
o 1.1由诸如陀螺仪、加速度计、定位系统等各种传感器组成的冗余航空电子设备和控制系统,
o 1.2液体推进剂箱
o 1.3无人机之间的连接和联接系统
o 1.4缓冲电池
o 1.5无人机之间的连接和联接系统
o 1.6无人机之间的连接和联接系统
o 1.7液体推进剂箱
o 1.8无人机之间的连接和联接系统
o 1.9缓冲电池
o 1.10液体推进剂涡轮发电机
·图2:描述了使系统模块化的机架的特性和两架无人机之间的连接系统o 2.1可实现单独单元之间的物理连接、数据传输和电力的无人机之间的对接板
o 2.2用于马达支撑的方形马达的支撑机架的结构以及模块之间的连接系统的结构
·图3:通过四个连接板的使用描述了四架无人机之间的连接系统。
·图4:描述了可以通过将多架无人机彼此连接而获得的一些配置
o 4.1单模块
o 4.2双模块配置
o 4.3成直线的三个模块(3×l)
o 4.4成直线的四个模块(4×1)
o 4.5四个模块(2×2)
o 4.6六个模块(3×2)
o 4.7八个模块(4×2)
o 4.8九个模块(3×3)
o 4.9十个模块(5×2)
·图5:描述了装载系统和通过容器运输的可能性。实际上,单独的模块是可堆叠的,并且具有适于插入容器内的尺寸。特别是在图中可以看到,在40英尺的容器中,可以通过分成5组、每组7个模块来储存35个单个单元。
o 5.1一组堆叠的7个单体单元
o 5.2 40英尺的顶部敞开的标准容器。
单架无人机由复合材料和轻质材料制成;在每个载具中,安装采用燃料的涡轮发电机,以产生足够保证机载电子设备和所有电机机的运行的电力。
载荷能力和自主性将取决于机上螺旋桨的量以及将使用的单独单元的数量。
所产生的电能将直接由电机使用,并且还将用于保持缓冲备用电池系统,以确保在发生发电机故障的情况下UAV运行几分钟并足以进行紧急降落。
无人机将配备自主学习式飞行控制器,该飞行控制器适应于系统基于物理连接的单体模块数量能够采用的多样化配置。
a.该系统配备有航空电子设备和控制系统和飞行控制器,其能够基于所连接的单体单元的数量及其定位来修改飞行参数。
b.配置中将只有一架无人机控制其他单元,并被定义为主导控制器(MASTERCONTROLLER);将重新配置数据发送到被称为辅助控制器(SLAVE CONTROLLER)的其他单元;
c.辅助控制器将保持备用状态,将控制权留给主导控制器。只有在主导控制器可能发生故障的情况下,辅助控制器才会基于自分配的优先级成为主导控制器;
d.该系统将能够基于连接模块的数量来管理飞行、传感器、马达和电源控制器的故障;
e.该系统配备有特殊的遥测系统(地面/空中/地面),以连续监控系统和飞行数据。
该系统被设计为容许连接的单体无人机,从而形成由多个单体单元构成的较大的无人机,以便通过使用物理上接合在一起的相同类型的多架无人机来增加无人机的载荷能力。
无人机可用于替代飞行员的生命可能处于危险之中的情景,或狭窄的空间内需要高载荷能力、自主性、起飞和降落将物品从A点运输到B点的所有情况;
一些实际使用的例子可以总结为:
·高海拔运输;
·各种尺寸和重量的物品或物体的运输,其中无人机可以适应要运输的物体的尺寸和重量;
·在困难和/或危险的环境中的搜索和救援行动;
·在敌对环境中的物体的运输和/或科学研究;
·几乎无限的民防行动。
Claims (6)
1.一种旋翼无人机,其具有:
·具有中空结构的碳纤维机架,所述碳纤维机架能够容纳飞行所需的部件并且保护旋翼;
·所述机架的特性,在所述机架中发动机支撑臂不朝内部会聚并形成用作安装发动机的支撑件的方形结构,所述发动机安装在的所述方形结构各边的中心,从而留出自由机架的中央部分的空间,所述中央部分也用作所述部件的装载空间以及用作各个单元之间的连接系统的结构支撑件;
·4个同轴的旋翼,每个旋翼由定位在支撑所述机架的所述机架的四个边的中心的2个电动马达和对转螺旋桨组成;
·用于供应足够飞行的电力的APU(辅助动力单元)涡轮发电机配置器;
··介于最小220×220cm和最大300×300cm之间的宽度;
·能够物理连接至其他同类型单元以创建具有不同的飞行配置的组合体以增加有效载荷。
2.根据权利要求1所述的无人机,其特征在于,所述无人机具有保护所述旋翼和所有飞行部件的碳纤维机架以及由4个橡胶垫组成的保障其免受地面影响的起落架,并且能够通过将各个单元彼此上下叠置地定位或在侧面竖直地定位所述机架将其堆叠以便于运输。
3.根据权利要求1所述的无人机,其特征在于,所述无人机通过能够保证两个或更多个单元之间的刚性物理连接的特殊的连接器能够在每一个侧面物理地连接至其他单元以创建多样化配置,从而增加载荷能力。
4.根据权利要求1所述的无人机,其特征在于,所述无人机具有推进系统,所述推进系统使用由涡轮驱动的APU(辅助动力单元,auxiliary power unit)产生的能量,所述APU由液体燃料驱动,并产生足够驱动所述飞行系统和发动机的能量。
5.根据权利要求3所述的无人机,其特征在于,所述横向连接系统容许彼此连接的各无人机之间共享电能和信息。
6.根据前述任一项权利要求所述的无人机,其特征在于,所述无人机具有飞行控制器,所述飞行控制器基于所连接的无人机的数量及它们的定位(无人机的形状)适应所述系统的多样化配置并因此来改变飞行特性。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT201800008376 | 2018-09-06 | ||
IT102018000008376 | 2018-09-06 | ||
PCT/IT2019/050197 WO2020049604A1 (en) | 2018-09-06 | 2019-09-05 | Modular multi-rotary wing drone powered by electric turbine generator |
Publications (1)
Publication Number | Publication Date |
---|---|
CN112770972A true CN112770972A (zh) | 2021-05-07 |
Family
ID=65496791
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201980058019.2A Pending CN112770972A (zh) | 2018-09-06 | 2019-09-05 | 由涡轮发电机驱动的模块化的多旋翼无人机 |
Country Status (2)
Country | Link |
---|---|
CN (1) | CN112770972A (zh) |
WO (1) | WO2020049604A1 (zh) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20200094965A1 (en) | 2018-07-27 | 2020-03-26 | California Institute Of Technology | Modular and dynamically reconfigurable flying systems encompassing flying vehicle modules |
CN111645855B (zh) * | 2020-05-28 | 2023-03-07 | 西南交通大学 | 两轴模组及使用该组件的无人机 |
US11673689B2 (en) * | 2021-04-27 | 2023-06-13 | Verizon Patent And Licensing Inc. | Command center for drone management |
CN113104213B (zh) * | 2021-05-06 | 2022-07-05 | 北京理工大学 | 一种模块化可变形无人机的结构 |
US12006076B2 (en) * | 2022-02-24 | 2024-06-11 | Microavia International Limited | Packaging system for drones |
WO2024079769A1 (en) * | 2022-10-14 | 2024-04-18 | Antonio Terribile | Hybrid locomotion robotic device for plant inspection |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090145998A1 (en) * | 2008-01-11 | 2009-06-11 | Salyer Ival O | Aircraft using turbo-electric hybrid propulsion system |
EP2818406A1 (en) * | 2013-06-24 | 2014-12-31 | The Boeing Company | Modular vehicle lift system |
WO2016134193A1 (en) * | 2015-02-19 | 2016-08-25 | Amazon Technologies, Inc. | Collective unmanned aerial vehicle configurations |
US20160272316A1 (en) * | 2015-01-17 | 2016-09-22 | Brian Dale Nelson | Multicopter with Detachable Wing |
US20160311529A1 (en) * | 2013-12-18 | 2016-10-27 | Neva Aerospace, Ltd. | Modular Electric VTOL Aircraft |
CN106394910A (zh) * | 2015-07-29 | 2017-02-15 | 空中客车防务和空间有限责任公司 | 用于垂直起降无人机的混合电动驱动系 |
WO2017184095A1 (en) * | 2016-04-22 | 2017-10-26 | Gozluklu Burak | Three dimensional scalable and modular aircraft |
WO2017197316A1 (en) * | 2016-05-13 | 2017-11-16 | Top Flight Technologies, Inc. | Passenger carrying unmanned aerial vehicle powered by a hybrid generator system |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10139838B2 (en) * | 2016-09-27 | 2018-11-27 | International Business Machines Corporation | Methods and systems for multiple drone delivery system |
US9957045B1 (en) * | 2017-09-03 | 2018-05-01 | Brehnden Daly | Stackable drones |
-
2019
- 2019-09-05 WO PCT/IT2019/050197 patent/WO2020049604A1/en active Application Filing
- 2019-09-05 CN CN201980058019.2A patent/CN112770972A/zh active Pending
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090145998A1 (en) * | 2008-01-11 | 2009-06-11 | Salyer Ival O | Aircraft using turbo-electric hybrid propulsion system |
EP2818406A1 (en) * | 2013-06-24 | 2014-12-31 | The Boeing Company | Modular vehicle lift system |
US20160311529A1 (en) * | 2013-12-18 | 2016-10-27 | Neva Aerospace, Ltd. | Modular Electric VTOL Aircraft |
US20160272316A1 (en) * | 2015-01-17 | 2016-09-22 | Brian Dale Nelson | Multicopter with Detachable Wing |
WO2016134193A1 (en) * | 2015-02-19 | 2016-08-25 | Amazon Technologies, Inc. | Collective unmanned aerial vehicle configurations |
CN106394910A (zh) * | 2015-07-29 | 2017-02-15 | 空中客车防务和空间有限责任公司 | 用于垂直起降无人机的混合电动驱动系 |
WO2017184095A1 (en) * | 2016-04-22 | 2017-10-26 | Gozluklu Burak | Three dimensional scalable and modular aircraft |
US20190127063A1 (en) * | 2016-04-22 | 2019-05-02 | Burak Gozluklu | Three dimensional scalable and modular aircraft |
WO2017197316A1 (en) * | 2016-05-13 | 2017-11-16 | Top Flight Technologies, Inc. | Passenger carrying unmanned aerial vehicle powered by a hybrid generator system |
Also Published As
Publication number | Publication date |
---|---|
WO2020049604A1 (en) | 2020-03-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10689102B2 (en) | Vertical take-off and landing aircraft | |
CN112770972A (zh) | 由涡轮发电机驱动的模块化的多旋翼无人机 | |
CN109018320B (zh) | X形倾转翼飞行器 | |
US11492116B2 (en) | Tiltrotor aircraft having tiltable forward and aft rotors | |
KR102655609B1 (ko) | 고정익 및 회전익 구성을 가진 vtol 항공기 | |
ES2842977T3 (es) | Sistema de propulsión para una aeronave y método para suministrar potencia de propulsión para una aeronave | |
US20160311529A1 (en) | Modular Electric VTOL Aircraft | |
US9878786B2 (en) | System and method for operation and management of reconfigurable unmanned aircraft | |
US20180273158A1 (en) | Multi-Architecture Modular Unmanned Aerial System | |
US11565813B2 (en) | Swarm-based firefighting drone and mass aerial drop system and method | |
US8660712B2 (en) | Reconfigurable aircraft | |
US9527597B1 (en) | Unmanned aerial vehicle with twin-engine fore/AFT configuration and associated systems and methods | |
US20160159472A1 (en) | Reconfigurable unmanned aircraft system | |
CN112368208A (zh) | 电动动力系统架构和使用该架构的容错vtol飞行器 | |
CN112912310A (zh) | 具有分布式电池的无人驾驶运输飞行器及其供电方法 | |
CN117550120A (zh) | 具有可配置燃料电池电力系统的uav | |
De Wagter et al. | Design and testing of a vertical take-off and landing UAV optimized for carrying a hydrogen fuel cell with a pressure tank | |
US11742500B2 (en) | Structural gaseous material storage tank | |
Rajendran et al. | The development of a small solar powered electric unmanned aerial vehicle systems | |
CN113727910A (zh) | 具有可配置燃料电池电力系统的uav | |
CN115477019A (zh) | 一种模块化氢能源无人机 | |
CN116923695A (zh) | 组合式多旋翼无人机系统及其控制方法 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
RJ01 | Rejection of invention patent application after publication | ||
RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210507 |