WO2019047429A1 - 一种基于多旋翼无人机的涵道推进系统 - Google Patents
一种基于多旋翼无人机的涵道推进系统 Download PDFInfo
- Publication number
- WO2019047429A1 WO2019047429A1 PCT/CN2017/118524 CN2017118524W WO2019047429A1 WO 2019047429 A1 WO2019047429 A1 WO 2019047429A1 CN 2017118524 W CN2017118524 W CN 2017118524W WO 2019047429 A1 WO2019047429 A1 WO 2019047429A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ducted
- uav
- rotor
- lift module
- drone
- Prior art date
Links
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
Definitions
- the invention belongs to the technical field of drones, and particularly relates to a ducted propulsion system based on a multi-rotor UAV.
- Existing four-rotor (or multi-rotor) aircraft employ four (or more) rotors as a direct source of power for flight.
- the rotors are symmetrically distributed in the front, rear, and left and right directions of the body.
- the four rotors are in the same height plane, and the four rotors have the same structure and radius.
- the four motors are symmetrically mounted on the aircraft.
- the space in the middle of the bracket houses the flight control computer and external equipment.
- the above-mentioned aircraft is driven by a small brushless motor and a rotor (propeller), and the current small brushless motor for multi-rotor drones has a maximum pulling force of 800g-2000g/axis and is expensive, and is mostly used in industrial-grade multi-rotor drones. .
- the tensile force of the consumer-grade UAV is only 350g-400g/axis. Due to the low pulling force, the load capacity is insufficient, and because of the inherent aerodynamic problem of the propeller, the propeller speed is increased when the fixed-diameter propeller provides a large thrust. However, the efficiency of the propeller will also decrease.
- the existing consumer-grade quadrotor (multi-rotor) has significantly reduced flight time and flight radius of the drone and can not carry mission loads exceeding its own thrust in the case of carrying heavy task loads due to cost and design problems.
- the ratio of the effective power of the propeller to the output power of the engine is called the propeller efficiency.
- Patent name a tilting double-ducted drone (application number: 20160382189.4)
- the patent is a tilting double-ducted drone, and the structure includes: a central wing and a flight control device inside the central wing, avionics equipment, electrical equipment, and ducted tilting control mechanism; avionics equipment, electrical equipment, and culvert
- the track tilting control mechanism is respectively connected to the flight control device.
- the ducted drone uses the ducted road as the power system of the unmanned aerial vehicle as a whole.
- the ducted control system and the power supply system are placed inside the flight control of the drone, and are integrally connected with the unmanned, and the design cost and the manufacturing cost are high. It is not convenient for repair and replacement.
- Patent name an electric ducted rotorcraft drone (application number: 201610872892)
- This patent is an electric ducted rotor drone that relates to a drone.
- a plurality of first plastic rings and a plurality of second plastic rings are coaxially arranged and alternately connected to form a duct body, and a plurality of axial brackets are disposed on the duct body, the top and the top of each axial bracket
- the support frames are connected, and the propeller, the baffle bracket and the steering gear bracket are respectively arranged on the output shaft of the motor from top to bottom, and the plurality of baffles are arranged on the baffle bracket, and each of the baffles
- the two ends are respectively detachably connected with the guide vane bracket and the inner wall of the duct body, and the plurality of rudder blades are disposed on the steering gear bracket, and the two ends of each rudder piece respectively correspond to the steering bracket and the inner wall of the duct body Removable connection.
- the patent puts the control system and the power system inside the duct, and uses the ducted fan as the external structure of the whole body.
- the ducted road is integrated with the drone, which is difficult to design, technically difficult, design cost and manufacturing cost. It is too high and it is not convenient to repair and replace the duct.
- the technical problem to be solved by the present invention is that the existing ducted propulsion system cannot be applied to the consumer multi-rotor UAV on the market.
- the present invention adds a separate ducted lift module under the conventional multi-rotor aircraft, and utilizes the same propeller fan with the same diameter to produce greater thrust at the same power. Integrating the ducted fan and its power and control system in a ducted lift module as an external accessory to the consumer-grade multi-rotor drone, providing additional lift and increasing the flight time and flight distance of the drone
- Existing consumer-grade multi-rotor aircraft can carry heavier mission load execution tasks.
- a ducted propulsion system based on a multi-rotor UAV includes a multi-rotor UAV 10, a PTZ interface I20, a ducted lift module 30, and a PTZ interface II40.
- the ducted lift module 30 and the multi-rotor drone 10 are mutually independent modules.
- the multi-rotor UAV 10 and the PTZ interface I20 are rigidly connected, and the lower part of the PTZ interface I20 is rigidly connected with the duct lift module 30; the upper part of the PTZ interface II40 is rigidly connected with the duct lift module 30, and the PTZ interface
- the lower part of the II40 has a reserved interface, and the reserved interface can be connected to the mounted PTZ or other devices.
- the ducted lift module 30 is composed of a battery 3010, a power switch 3020, a left ducted fan 3030, a right ducted fan 3040, a left electronic governor 3050, a right electronic governor 3060, an ESC server 3070, and a remote control signal receiving unit.
- the machine 3080 is composed of a mode controller 3090.
- the battery 3010 provides power to the left ducted fan 3030, the right ducted fan 3040, the left electronic governor 3050, the right electronic governor 3060, the ESC server 3070, the remote control signal receiver 3080, and the mode controller 3090.
- the power switch 3020 is a single pole single throw switch for controlling the breaking of the battery 3010.
- the left ducted fan 3030 and the right ducted fan 3040 are a pair of positive and negative propeller ducted fans and are disposed on both sides of the multi-rotor drone 10, and the left ducted fan 3030 and the right ducted fan 3040 are ducted lifts. Module 30 provides thrust.
- the left electronic governor 3050 is connected to the left ducted fan 3030
- the right electronic governor 3060 is connected to the right ducted fan 3040
- the left electronic governor 3050 and the right electronic governor 3060 are passed through the ESC server 3070 or
- the remote control signal receiver 3080 adjusts the rotational speed of the left ducted fan 3030 and the right ducted fan 3040 to adjust the thrust.
- the ESC server 3070 has a gear position adjustment function, and the ESC server 3070 is connected to the electronic governor 3050 and the right electronic governor 3060, respectively, and controls the left electronic governor 3050 and the right electron through the ESC server 3070.
- the governor 3060 further controls the rotational speeds of the left ducted fan 3030 and the right ducted fan 3040.
- the remote control signal receiver 3080 is connected to the left electronic governor 3050 and the right electronic governor 3060, and the remote control signal receiver 3080 receives the radio signal transmitted by the external bypass remote controller of the multi-rotor drone 10, and transmits the radio signal.
- the left electronic governor 3050 and the right electronic governor 3060 further control the rotational speeds of the left ducted fan 3030 and the right ducted fan 3040.
- the mode controller 3090 is a single pole double throw switch for controlling the opening and closing of the ESC server 3070 and the remote control signal receiver 3080.
- the rigid connection is a screw connection, a ⁇ connection or a slide connection.
- the control takeoff flow of the multi-rotor UAV 10 is as follows:
- the multi-rotor UAV 10 takes off as follows: first, after turning on the power of the multi-rotor UAV 10, the multi-rotor is unlocked by the UAV remote controller. The machine 10 sends a take-off command to the multi-rotor drone 10 through the drone remote controller, and the multi-rotor drone 10 propeller speed is increased to provide lift, and the multi-rotor drone 10 takes off.
- the multi-rotor UAV 10 When it is necessary to increase the load, the multi-rotor UAV 10 is provided with a ducted lift module 30, and the specifications of the duct lift module 30 vary according to different loads.
- the takeoff process is as follows:
- Step 1 The drone flying hand turns on the multi-rotor drone 10 power supply.
- Step 2 The drone flying hand opens the power switch 3020 of the communication duct lift module 30 to open the duct lift module 30.
- Step 3 The drone flying hand selects the relevant mode of the ducted lift module 30 by using the mode selector 3090, such as the switch up to the manual mode and the switch down to the remote mode.
- the mode selector 3090 such as the switch up to the manual mode and the switch down to the remote mode.
- Step 4A-1 If the manual mode is selected, the drone flying hand manually adjusts the gear position on the ESC server 3070 to cause the ducted lift module 30 to generate lift according to the selected gear position.
- Step 4A-2 The UAV flying hand unlocks the multi-rotor UAV 10 through the UAV remote control, and the UAV fly control UAV remote control sends a take-off command to the multi-rotor UAV 10
- the machine 10 receives the takeoff command to start the propeller, at which time the multi-rotor drone 10 takes off under the combined action of the lift provided by the ducted lift module 30 and its own propeller.
- Step 4B-1 If the remote control mode is selected, the drone flying hand opens the external ducted remote controller to send an instruction to the ducted lift module 30, and the ducted lift module 30 receives the command of the external ducted remote controller. Lift.
- Step 4B-2 The UAV flying hand unlocks the multi-rotor UAV 10 through the UAV remote control to control the UAV remote control to send a take-off command to the multi-rotor UAV 10, and the multi-rotor UAV 10 starts the propeller At this time, the multi-rotor UAV 10 drone takes off under the combined action of the duct lift module 30 and the lift provided by the propeller itself.
- the utility model uses a universal pan/tilt interface, and can be rigidly mechanically combined with various types of consumer-grade multi-rotor UAVs available on the market, and can be equipped with different ducts or batteries according to different load requirements to increase the maximum lift. There is no need to install a complicated ducted control system, and there is a large conversion potential and design margin, which saves a lot of cost compared to redesigning a ducted drone.
- Figure 1 is a block diagram of a drone based on a ducted propulsion module.
- Figure 2 is a schematic view of the structure of the ducted lift module.
- Figure 3 is a top view of a drone based on a ducted propulsion module.
- Figure 4 is a schematic diagram of the take-off operation flow of the drone when the ducted lift module is not installed.
- Figure 5 shows the schematic diagram of the take-off operation of the drone when the ducted lift module is installed.
- a ducted propulsion system based on a multi-rotor UAV includes a multi-rotor UAV 10, a PTZ interface I20, a ducted lift module 30, and a PTZ interface II40.
- the multi-rotor UAV 10 and the PTZ interface I20 are rigidly connected, and the lower part of the PTZ interface I20 is rigidly connected with the duct lift module 30; the upper part of the PTZ interface II40 is rigidly connected with the duct lift module 30, and the PTZ interface
- the lower part of the II40 has a reserved interface, and the reserved interface can be connected to the mounted PTZ or other devices.
- the ducted lift module 30 is composed of a battery 3010, a power switch 3020, a left ducted fan 3030, a right ducted fan 3040, a left electronic governor 3050, a right electronic governor 3060, an ESC server 3070, and a remote control signal receiving unit.
- the machine 3080 is composed of a mode controller 3090.
- the battery 3010 provides power to the left ducted fan 3030, the right ducted fan 3040, the left electronic governor 3050, the right electronic governor 3060, the ESC server 3070, the remote control signal receiver 3080, and the mode controller 3090.
- the power switch 3020 is a single pole single throw switch for controlling the breaking of the battery 3010.
- the left ducted fan 3030 and the right ducted fan 3040 are a pair of positive and negative propeller ducted fans and are disposed on both sides of the multi-rotor drone 10, and the left ducted fan 3030 and the right ducted fan 3040 are ducted lifts. Module 30 provides thrust.
- the left electronic governor 3050 is connected to the left ducted fan 3030
- the right electronic governor 3060 is connected to the right ducted fan 3040
- the left electronic governor 3050 and the right electronic governor 3060 are passed through the ESC server 3070 or
- the remote control signal receiver 3080 adjusts the rotational speed of the left ducted fan 3030 and the right ducted fan 3040 to adjust the thrust.
- the ESC server 3070 has a gear position adjustment function, and the ESC server 3070 is connected to the electronic governor 3050 and the right electronic governor 3060, respectively, and controls the left electronic governor 3050 and the right electron through the ESC server 3070.
- the governor 3060 further controls the rotational speeds of the left ducted fan 3030 and the right ducted fan 3040.
- the remote control signal receiver 3080 is connected to the left electronic governor 3050 and the right electronic governor 3060, and the remote control signal receiver 3080 receives the radio signal transmitted by the external bypass remote controller of the multi-rotor drone 10, and transmits the radio signal.
- the left electronic governor 3050 and the right electronic governor 3060 further control the rotational speeds of the left ducted fan 3030 and the right ducted fan 3040.
- the mode controller 3090 is a single pole double throw switch for controlling the opening and closing of the ESC server 3070 and the remote control signal receiver 3080.
- the rigid connection is a screw connection, a ⁇ connection or a slide connection.
- the multi-rotor UAV 10 takes off as follows: first, after turning on the power of the multi-rotor UAV 10, the multi-rotor is unlocked by the UAV remote controller. The machine 10 sends a take-off command to the multi-rotor drone 10 through the drone remote controller, and the multi-rotor drone 10 propeller speed is increased to provide lift, and the multi-rotor drone 10 takes off.
- the multi-rotor UAV 10 When it is necessary to increase the load, the multi-rotor UAV 10 is provided with a ducted lift module 30, and the specifications of the duct lift module 30 vary according to different loads.
- the takeoff process is as follows:
- Step 1 The drone flying hand turns on the multi-rotor drone 10 power supply.
- Step 2 The drone flying hand opens the power switch 3020 of the communication duct lift module 30 to open the duct lift module 30.
- Step 3 The drone flying hand selects the relevant mode of the ducted lift module 30 by using the mode selector 3090, such as the switch up to the manual mode and the switch down to the remote mode.
- the mode selector 3090 such as the switch up to the manual mode and the switch down to the remote mode.
- Step 4A-1 If the manual mode is selected, the drone flying hand manually adjusts the gear position on the ESC server 3070 to cause the ducted lift module 30 to generate lift according to the selected gear position.
- Step 4A-2 The UAV flying hand unlocks the multi-rotor UAV 10 through the UAV remote control, and the UAV fly control UAV remote control sends a take-off command to the multi-rotor UAV 10
- the machine 10 receives the takeoff command to start the propeller, at which time the multi-rotor drone 10 takes off under the combined action of the lift provided by the ducted lift module 30 and its own propeller.
- Step 4B-1 If the remote control mode is selected, the drone flying hand opens the external ducted remote controller to send an instruction to the ducted lift module 30, and the ducted lift module 30 receives the command of the external ducted remote controller. Lift.
- Step 4B-2 The UAV flying hand unlocks the multi-rotor UAV 10 through the UAV remote control to control the UAV remote control to send a take-off command to the multi-rotor UAV 10, and the multi-rotor UAV 10 starts the propeller At this time, the multi-rotor UAV 10 drone takes off under the combined action of the duct lift module 30 and the lift provided by the propeller itself.
- the multi-rotor UAV 10 is composed of a power system, an avionics control system, a pan-tilt interface, and a drone remote controller.
- the type and specification of the ducted lift module 30 can be varied according to different load requirements. For example, when carrying a load of 1 kg, a pair of 50 mm ducts with a single thrust of 900 g can be selected as the power source of the duct lift module 30. For example, when carrying a 5 kg class load, a pair of 90 mm ducts with a single thrust of 3.5 kg can be selected as the power source for the duct lift module 30. And the same ducted lift module can provide different sizes of thrust.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
Description
Claims (3)
- 一种基于多旋翼无人机的涵道推进系统,其特征在于:该系统包括多旋翼无人机(10)、云台接口Ⅰ(20)、涵道升力模块(30)和云台接口Ⅱ(40);涵道升力模块(30)与多旋翼无人机(10)为相互独立的模块;多旋翼无人机(10)与云台接口Ⅰ(20)通过刚性连接,云台接口Ⅰ(20)的下部与涵道升力模块(30)通过刚性连接;云台接口Ⅱ(40)的上部与涵道升力模块(30)通过刚性连接,云台接口Ⅱ(40)的下部设有预留接口,预留接口能够与所搭载的云台连接;所述涵道升力模块(30)由电池(3010)、电源开关(3020)、左涵道风扇(3030)、右涵道风扇(3040)、左电子调速器(3050)、右电子调速器(3060)、电调伺服器(3070)、遥控信号接收机(3080)和模式控制器(3090)组成;所述电池(3010)为左涵道风扇(3030)、右涵道风扇(3040)、左电子调速器(3050)、右电子调速器(3060)、电调伺服器(3070)、遥控信号接收机(3080)和模式控制器(3090)提供电力;所述电源开关(3020)为单刀单掷开关,用以控制电池(3010)的开断;所述左涵道风扇(3030)和右涵道风扇(3040)为一对正反桨涵道风扇并设置在多旋翼无人机(10)的两侧,左涵道风扇(3030)和右涵道风扇(3040)为涵道升力模块(30)提供推力;所述左电子调速器(3050)与左涵道风扇(3030)连接,右电子调速器(3060)与右涵道风扇(3040)连接,左电子调速器(3050)和右电子调速器(3060)通过电调伺服器(3070)或遥控信号接收机(3080)调节左涵道风扇(3030)与右涵道风扇(3040)的转速,进而调节推力;所述电调伺服器(3070)具有档位调节功能,电调伺服器(3070)分别和电子调速器3050、右电子调速器(3060)连接,通过电调伺服器(3070)控制左电子调速器(3050)及右电子调速器(3060),进而控制左涵道风扇(3030)及右涵道风扇(3040)的转速;遥控信号接收机(3080)均与左电子调速器(3050)及右电子调速器(3060)连接,遥控信号接收机(3080)接收多旋翼无人机(10)的外部涵道遥控器发送的无线电信号,并将无线电信号发送至左电子调速器(3050)及右电子调速器(3060),进而控制左涵道风扇(3030)及右涵道风扇(3040)的转速;所述模式控制器(3090)为单刀双掷开关,用以控制电调伺服器(3070)和所述遥控信号接收机(3080)的开闭。
- 根据权利要求1所述的一种基于多旋翼无人机的涵道推进系统,其特征在于:刚性连接为螺丝连接、榫卯连接或滑轨连接。
- 根据权利要求1所述的一种基于多旋翼无人机的涵道推进系统,其特征在于:多旋翼无人机(10)的控制起飞流程如下:当多旋翼无人机(10)未加装涵道升力模块(30)时,多旋翼无人机(10)起飞流程如下:首先接通多旋翼无人机(10)电源后,通过无人机遥控器解锁多旋翼无人机(10),通过无人机遥控器向多旋翼无人机(10)发送起飞指令,多旋翼无人机(10)螺旋桨转速加快,提供升力,多旋翼无人机(10)起飞;当需要增加载重时,给多旋翼无人机(10)加装涵道升力模块(30),涵道升力模块(30)的规格根据不同载重而变化;此时起飞流程如下:步骤1:无人机飞手接通多旋翼无人机(10)电源;步骤2:无人机飞手打开连通涵道升力模块(30)的电源开关(3020),使涵道升力模块(30)处于开启状态;步骤3:无人机飞手利用模式选择器3090选择涵道升力模块(30)的相关模式,如开关向上为手动模式,开关向下为遥控模式;步骤4A-1:如果选择手动模式的情况下,无人机飞手手动调节电调伺服器(3070)上的档位,使涵道升力模块(30)根据所选档位产生升力;步骤4A-2:无人机飞手通过无人机遥控器解锁多旋翼无人机(10),无人机飞手控制无人机遥控器向多旋翼无人机(10)发送起飞指令,多旋翼无人机(10)接收起飞指令启动螺旋桨,此时多旋翼无人机(10)在所述涵道升力模块(30)和自身螺旋桨提供的升力的共同作用下起飞;步骤4B-1::如果选择遥控模式的情况下,无人机飞手打开外部涵道遥控器向所述涵道升力模块(30)发送指令,涵道升力模块(30)接收外部涵道遥控器的指令产生升力;步骤4B-2:无人机飞手通过无人机遥控器解锁多旋翼无人机(10),以控制无人机遥控器向多旋翼无人机(10)发送起飞指令,多旋翼无人机(10)启动螺旋桨,此时多旋翼无人机(10)无人机在所述涵道升力模块(30)和自身螺旋桨 提供的升力的共同作用下起飞。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201710790821.3 | 2017-09-05 | ||
CN201710790821.3A CN107458593B (zh) | 2017-09-05 | 2017-09-05 | 一种基于多旋翼无人机的涵道推进系统 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2019047429A1 true WO2019047429A1 (zh) | 2019-03-14 |
Family
ID=60551934
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CN2017/118524 WO2019047429A1 (zh) | 2017-09-05 | 2017-12-26 | 一种基于多旋翼无人机的涵道推进系统 |
Country Status (2)
Country | Link |
---|---|
CN (1) | CN107458593B (zh) |
WO (1) | WO2019047429A1 (zh) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107458593B (zh) * | 2017-09-05 | 2023-09-12 | 北京工业大学 | 一种基于多旋翼无人机的涵道推进系统 |
CN109159633A (zh) * | 2018-08-31 | 2019-01-08 | 长春工程学院 | 一种两栖无人机 |
CN114954930A (zh) * | 2022-06-16 | 2022-08-30 | 南京大学 | 一种基于电动涵道风扇的双旋翼尾座式无人机 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103332293A (zh) * | 2013-06-13 | 2013-10-02 | 上海大学 | 倾转式双涵道超小型无人机 |
WO2016112124A2 (en) * | 2015-01-08 | 2016-07-14 | Vantage Robotics, Llc | Unmanned aerial vehicle with propeller protection and high impact survivability |
CN105947201A (zh) * | 2016-04-27 | 2016-09-21 | 乐视控股(北京)有限公司 | 一种模块化无人机及其使用方法 |
CN206243467U (zh) * | 2016-11-18 | 2017-06-13 | 中国航空工业集团公司沈阳飞机设计研究所 | 一种四涵道旋翼无人机 |
CN107042883A (zh) * | 2017-03-27 | 2017-08-15 | 上海珞鹏航空科技有限公司成都研发分公司 | 一种二级传动发动机纵列式可发电和载物的双涵道无人机 |
CN107458593A (zh) * | 2017-09-05 | 2017-12-12 | 北京工业大学 | 一种基于多旋翼无人机的涵道推进系统 |
CN207157519U (zh) * | 2017-09-05 | 2018-03-30 | 北京工业大学 | 一种基于多旋翼无人机的涵道推进系统 |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6561455B2 (en) * | 1997-12-10 | 2003-05-13 | Franco Capanna | Vertical take-off and landing, aerodynamically self-sustained horizontal flight hybrid aircraft |
US7658346B2 (en) * | 2005-02-25 | 2010-02-09 | Honeywell International Inc. | Double ducted hovering air-vehicle |
GB201322401D0 (en) * | 2013-12-18 | 2014-02-05 | Geola Technologies Ltd | Modular electric VTOL aircraft |
DE202014009436U1 (de) * | 2014-06-17 | 2015-01-08 | Flairics Gmbh & Co. Kg | Modularer Multikopter |
US10059437B2 (en) * | 2015-01-08 | 2018-08-28 | Robert Stanley Cooper | Multi-rotor safety shield |
CN204822069U (zh) * | 2015-06-19 | 2015-12-02 | 中国船舶工业系统工程研究院 | 一种涵道四旋翼无人机构型 |
CN205203397U (zh) * | 2015-11-24 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | 一种垂直起降无人机油电混合动力系统 |
CN105752320A (zh) * | 2016-04-01 | 2016-07-13 | 陈方平 | 一种涵道式无人机及其控制方法 |
-
2017
- 2017-09-05 CN CN201710790821.3A patent/CN107458593B/zh active Active
- 2017-12-26 WO PCT/CN2017/118524 patent/WO2019047429A1/zh active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103332293A (zh) * | 2013-06-13 | 2013-10-02 | 上海大学 | 倾转式双涵道超小型无人机 |
WO2016112124A2 (en) * | 2015-01-08 | 2016-07-14 | Vantage Robotics, Llc | Unmanned aerial vehicle with propeller protection and high impact survivability |
CN105947201A (zh) * | 2016-04-27 | 2016-09-21 | 乐视控股(北京)有限公司 | 一种模块化无人机及其使用方法 |
CN206243467U (zh) * | 2016-11-18 | 2017-06-13 | 中国航空工业集团公司沈阳飞机设计研究所 | 一种四涵道旋翼无人机 |
CN107042883A (zh) * | 2017-03-27 | 2017-08-15 | 上海珞鹏航空科技有限公司成都研发分公司 | 一种二级传动发动机纵列式可发电和载物的双涵道无人机 |
CN107458593A (zh) * | 2017-09-05 | 2017-12-12 | 北京工业大学 | 一种基于多旋翼无人机的涵道推进系统 |
CN207157519U (zh) * | 2017-09-05 | 2018-03-30 | 北京工业大学 | 一种基于多旋翼无人机的涵道推进系统 |
Also Published As
Publication number | Publication date |
---|---|
CN107458593B (zh) | 2023-09-12 |
CN107458593A (zh) | 2017-12-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US11505314B2 (en) | Vertical takeoff and landing aircraft with tiltable rotors | |
CN110035954B (zh) | 用于私人飞机的通风旋翼安装臂架 | |
CN108367803B (zh) | 混合动力推进式垂直起降航空器 | |
EP2928772B1 (en) | Vertical takeoff and landing aircraft | |
CN107074366B (zh) | 直升机 | |
EP3564122B1 (en) | Hybrid tiltrotor drive system | |
KR101895366B1 (ko) | 개량형 하이브리드 드론 | |
US20190084684A1 (en) | Hybrid aircraft | |
WO2016081041A1 (en) | Muiti-propulsion design for unmanned aerial systems | |
WO2016066131A1 (zh) | 一种复合式垂直起降飞行器 | |
WO2020107373A1 (zh) | 动力组件、动力系统及无人机 | |
CN208746231U (zh) | 一种分布式涵道螺旋桨动力垂直起降无人机 | |
WO2019047429A1 (zh) | 一种基于多旋翼无人机的涵道推进系统 | |
CN110626495A (zh) | 小型共轴双旋翼式无人机 | |
WO2020250029A1 (en) | Method and convertible vtol or evtol aircraft for transition from helicopter mode to gyroplane mode and vice versa | |
CN113636072A (zh) | 一种基于可倾转涵道螺旋桨的跨介质无人机 | |
WO2024035711A1 (en) | Aircraft with hybrid parallel and series propulsion system | |
CN207157519U (zh) | 一种基于多旋翼无人机的涵道推进系统 | |
EP3849899A1 (en) | Apparatus for aerial transportation of payload | |
CN211468751U (zh) | 一种飞行器 | |
CN108216612A (zh) | 无人机 | |
CN108313263A (zh) | 用于固定翼无人机的机身动力系统 | |
CN215399323U (zh) | 一种基于可倾转涵道螺旋桨的跨介质无人机 | |
CN108454843A (zh) | 用于固定翼无人机的动力机身装置 | |
CN208470105U (zh) | 用于固定翼无人机的可调式旋翼机尾装置 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 17924040 Country of ref document: EP Kind code of ref document: A1 |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 17924040 Country of ref document: EP Kind code of ref document: A1 |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 17924040 Country of ref document: EP Kind code of ref document: A1 |
|
32PN | Ep: public notification in the ep bulletin as address of the adressee cannot be established |
Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205A DATED 03/12/2020) |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 17924040 Country of ref document: EP Kind code of ref document: A1 |