WO2018161193A1 - Four-axis aerial vehicle provided with lights - Google Patents

Four-axis aerial vehicle provided with lights Download PDF

Info

Publication number
WO2018161193A1
WO2018161193A1 PCT/CN2017/075672 CN2017075672W WO2018161193A1 WO 2018161193 A1 WO2018161193 A1 WO 2018161193A1 CN 2017075672 W CN2017075672 W CN 2017075672W WO 2018161193 A1 WO2018161193 A1 WO 2018161193A1
Authority
WO
WIPO (PCT)
Prior art keywords
module
fuselage
loop
spiral
control circuit
Prior art date
Application number
PCT/CN2017/075672
Other languages
French (fr)
Chinese (zh)
Inventor
肖丽芳
Original Assignee
肖丽芳
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 肖丽芳 filed Critical 肖丽芳
Priority to PCT/CN2017/075672 priority Critical patent/WO2018161193A1/en
Publication of WO2018161193A1 publication Critical patent/WO2018161193A1/en

Links

Classifications

    • 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
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/006—Safety devices
    • 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
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/10—Simultaneous control of position or course in three dimensions
    • G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
    • G05D1/102—Simultaneous control of position or course in three dimensions specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00—UAVs characterised by their flight controls

Definitions

  • the utility model belongs to the field of machines, and in particular relates to a four-axis light aircraft.
  • the communication between the UAV and the ground terminal is mostly wirelessly transmitted, that is, the flight state of the UAV is transmitted to the ground terminal through a wireless signal.
  • the unmanned aerial vehicle flight state is not intuitive enough, and it is relatively lagging. In the user's control of the unmanned aerial vehicle flight, the unmanned aircraft can not notice the flight state of the unmanned aerial vehicle. It may cause an accident and is therefore not reliable enough. Therefore, how to get rid of a single wirelessly transmitted signal transmission method, a new device or method for knowing the flight state of an unmanned aerial vehicle has become a goal pursued by those skilled in the art.
  • a four-axis light aircraft comprising a control circuit, a wireless transceiver module, an electric motor, a battery, a fuselage and a top bumper: voltage input of the control circuit with a Bluetooth module, a test program module, a four-axis drive module and a barometric sensor module
  • the wireless transceiver module is composed of a filtering portion, a decoder, and the like, and is connected to an antenna and a power source; the motor is symmetrically distributed under the spiral spiral wing in front, rear, and left and right directions of the body; the battery is embedded in the body.
  • the control circuit is composed of a control loop, a power loop, a main loop, and an auxiliary loop; wherein the control loop is composed of a power loop, a button switch, a protection switch, a relay coil, and an auxiliary thereof.
  • the power supply circuit is composed of a photoresistor R, a magnetron switch L, a fixed value resistor R0, a power source Ul, and the like.
  • the wireless transceiver The module and the receiving module are directly connected to the decoder; the decoder is further connected to the single chip by the encoding module and the high frequency transmitting module; and the receiving portion is composed of the high frequency frequency selecting module and the demodulating module.
  • a four-axis light aircraft wherein: the motor is composed of a stationary locating and a rotatable rotor; the stator is mainly composed of a stator core The stator winding resistance and the base are composed of three parts; the rotor is connected to the spiral wing by a shaft, and the spiral wings are symmetrically distributed in the front, rear, and left and right directions of the body; the spiral wings are at the same height plane and the structure is The radii are all the same, the motor is symmetrically mounted on the bracket end of the aircraft; the intermediate space of the bracket end houses the flight control computer and external equipment.
  • the utility model has the advantages of dexterous structure and low energy consumption, and the monitoring personnel of the monitoring room can realize wireless remote control of the aircraft through Bluetooth, etc., when the aircraft flies to the scene after the disaster. In the sky, the image data can be wirelessly transmitted to the monitoring room through the carried camera, which provides convenience for on-site decision-making.
  • 1 is a front view showing the structure of the present invention.
  • the top anti-collision bar 2, charging interface; 3, U SB interface; 4, control circuit; 5, wireless transceiver module; 6, base; 7, laser transmitter; 8, laser; 9, battery; 10, the fuselage; 11, the motor; 12, the spiral wing.
  • a four-axis light aircraft includes a control circuit (4), a wireless transceiver module (5), an electric motor (11), a battery (9), a fuselage (10) and a top bumper (1).
  • the control circuit (4) is connected to a voltage input end of the Bluetooth module, the test program module, the four-axis drive module, and the air pressure sensor module;
  • the wireless transceiver module (5) is composed of a filter part, a decoder, and the like, and an antenna and a power supply.
  • the control circuit (4) is controlled
  • the circuit, the power circuit, the main circuit and the auxiliary circuit are composed of: the control circuit is composed of a power circuit, a button switch, a protection switch, a relay coil and an auxiliary contact thereof; the power circuit is composed of a photoresistor R and a magnetic control
  • the switch module (5) and the receiving module are directly connected to the decoder; the decoder is connected to the single chip microcomputer and is composed of an encoding module and a high frequency transmitting module; The receiving portion is composed of a high frequency frequency selective module and a demodulation module; the motor (11) is composed of a stationary locating and a rotatable rotor; the stat
  • the rotor is connected to the spiral helix (12) through a shaft, and the spiral wing (12) is symmetrically distributed in the front, rear, and left and right directions of the body; the spiral wing (12) is in the same A height plane, and the same structure and radius, the motor (11) has four symmetrical mountings on the support end of the aircraft, and the flight control computer and external equipment are placed in the middle space of the bracket.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

A four-axis aerial vehicle provided with lights comprises a control circuit (4), a wireless transceiver module (5), motors (11), a battery (9), a fuselage (10), and a top anti-collision rod (1). The control circuit (4) is connected to voltage input ends of a Bluetooth module, a test program module, a four-axis drive module and an air pressure sensor module. The wireless transceiver module (5) consists of a filter part, a decoder and the like, and is connected to an antenna and a power supply. The motors (11) are located below a propeller (12), and are symmetrically distributed in the front, rear, left and right directions. The aerial vehicle has an ingenious structure and low energy consumption.

Description

一种四轴灯光飞行器 技术领域  Four-axis light aircraft
[0001] 本实用新型属于机器领域， 具体涉及一种四轴灯光飞行器。  [0001] The utility model belongs to the field of machines, and in particular relates to a four-axis light aircraft.
背景技术  Background technique
[0002] 目前， 无人飞行器与地面终端的通信大都是通过无线传播的， 即通过无线信号 将无人飞行器的飞行状态发送至地面终端。 但是， 这种无线传输的方式仍存在 一些问题： 无人飞行器飞行状态不够直观， 也比较滞后， 在使用者控制无人飞 行器飞行中， 有吋不能够及吋的注意到无人飞行器的飞行状态， 有可能会造成 事故， 因此不够可靠。 因此， 如何摆脱单一的无线传播的信号传输方式、 一种 新的获知无人飞行器飞行状态的装置或方法成为了本领域技术人员追求的目标 。 综上述我设计了一种四轴灯光飞行器。  [0002] At present, the communication between the UAV and the ground terminal is mostly wirelessly transmitted, that is, the flight state of the UAV is transmitted to the ground terminal through a wireless signal. However, there are still some problems in the way of wireless transmission: The unmanned aerial vehicle flight state is not intuitive enough, and it is relatively lagging. In the user's control of the unmanned aerial vehicle flight, the unmanned aircraft can not notice the flight state of the unmanned aerial vehicle. It may cause an accident and is therefore not reliable enough. Therefore, how to get rid of a single wirelessly transmitted signal transmission method, a new device or method for knowing the flight state of an unmanned aerial vehicle has become a goal pursued by those skilled in the art. In summary, I designed a four-axis light aircraft.
技术问题  technical problem
[0003] 当无人飞行器在光线不足、 视野模糊的环境下作业吋， 地面终端无法直观判断 无人飞行器的飞行状态的信息。  [0003] When an unmanned aerial vehicle is operated in an environment with insufficient light and blurred vision, the ground terminal cannot intuitively judge the information of the flight state of the unmanned aerial vehicle.
问题的解决方案  Problem solution
技术解决方案  Technical solution
[0004] 本实用新型是通过以下技术方案实现。 一种四轴灯光飞行器， 包括控制电路， 无线收发模块， 电动机， 电池， 机身和顶部防撞杆： 所述控制电路与蓝牙模块 、 测试程序模块、 四轴驱动模块和气压传感器模块的电压输入端连接； 所述无 线收发模块由滤波部分、 解码器等组成与天线、 电源连接； 所述电动机在螺螺 旋翼的下方对称分布在机体的前后、 左右四个方向； 所述电池镶嵌在机身内部 与充电接口相连； 所述顶部防撞杆插入机身的正上方并且在机身上表面的中心 。 作为本实用新型的进一步优化方案， 所述控制电路由控制回路、 电源回路、 主回路、 辅助回路组成； 所述控制回路中则由电源回路、 按钮幵关、 保护幵关 、 继电器线圈及其辅助触点组成； 所述电源回路由光敏电阻 R、 磁控幵关 L、 定 值电阻 R0、 电源 Ul等组成。 作为本实用新型的进一步优化方案， 所述无线收发 模块与接收模块直接和解码器相连； 所述解码器再和单片机相连由编码模块和 高频发射模块组成； 接收部分则是由高频选频模块和解调模块组成。 作为本实 用新型的进一步优化方案， 根据权利要求 1所述的一种四轴灯光飞行器， 其特征 在于： 所述电动机由静止的定字和可以转动的转子组成； 所述定子主要由定子 铁芯、 定子绕组电阻和基座三部分组成； 所述转子则通过轴与螺螺旋翼相连， 所螺旋翼对称分布在机体的前后、 左右四个方向； 所述螺螺旋翼处于同一高度 平面且结构和半径都相同， 所述电动机对称的安装在飞行器的支架端； 所述支 架端中间空间安放飞行控制计算机和外部设备。 [0004] The utility model is realized by the following technical solutions. A four-axis light aircraft, comprising a control circuit, a wireless transceiver module, an electric motor, a battery, a fuselage and a top bumper: voltage input of the control circuit with a Bluetooth module, a test program module, a four-axis drive module and a barometric sensor module The wireless transceiver module is composed of a filtering portion, a decoder, and the like, and is connected to an antenna and a power source; the motor is symmetrically distributed under the spiral spiral wing in front, rear, and left and right directions of the body; the battery is embedded in the body. The interior is connected to the charging interface; the top bumper is inserted directly above the fuselage and at the center of the upper surface of the fuselage. As a further optimization scheme of the present invention, the control circuit is composed of a control loop, a power loop, a main loop, and an auxiliary loop; wherein the control loop is composed of a power loop, a button switch, a protection switch, a relay coil, and an auxiliary thereof. The power supply circuit is composed of a photoresistor R, a magnetron switch L, a fixed value resistor R0, a power source Ul, and the like. As a further optimization scheme of the present invention, the wireless transceiver The module and the receiving module are directly connected to the decoder; the decoder is further connected to the single chip by the encoding module and the high frequency transmitting module; and the receiving portion is composed of the high frequency frequency selecting module and the demodulating module. As a further optimization of the present invention, a four-axis light aircraft according to claim 1, wherein: the motor is composed of a stationary locating and a rotatable rotor; the stator is mainly composed of a stator core The stator winding resistance and the base are composed of three parts; the rotor is connected to the spiral wing by a shaft, and the spiral wings are symmetrically distributed in the front, rear, and left and right directions of the body; the spiral wings are at the same height plane and the structure is The radii are all the same, the motor is symmetrically mounted on the bracket end of the aircraft; the intermediate space of the bracket end houses the flight control computer and external equipment.
发明的有益效果  Advantageous effects of the invention
有益效果  Beneficial effect
[0005] 与现有的技术相比， 本实用新型的有益效果是： 本实用新型结构灵巧， 耗能低 ， 监控室的监控人员可以通过蓝牙等对飞行器实现无线遥控， 当飞行器飞行到 灾后现场上空吋， 可以通过所携带的摄像头将图像资料无线传输给监控室， 为 现场决策提供了方便。  Compared with the prior art, the utility model has the following beneficial effects: The utility model has the advantages of dexterous structure and low energy consumption, and the monitoring personnel of the monitoring room can realize wireless remote control of the aircraft through Bluetooth, etc., when the aircraft flies to the scene after the disaster. In the sky, the image data can be wirelessly transmitted to the monitoring room through the carried camera, which provides convenience for on-site decision-making.
对附图的简要说明  Brief description of the drawing
附图说明  DRAWINGS
[0006] 图 1是本实用新型的结构主视图。 图中： 1、 顶部防撞杆； 2、 充电接口； 3、 U SB接口； 4、 控制电路； 5、 无线收发模块； 6、 底座； 7、 激光发射头； 8、 激光 ； 9、 电池； 10、 机身； 11、 电动机； 12、 螺旋翼。  1 is a front view showing the structure of the present invention. In the figure: 1, the top anti-collision bar; 2, charging interface; 3, U SB interface; 4, control circuit; 5, wireless transceiver module; 6, base; 7, laser transmitter; 8, laser; 9, battery; 10, the fuselage; 11, the motor; 12, the spiral wing.
本发明的实施方式 Embodiments of the invention
[0007] 下面结合附图与具体实施方式对本实用新型作进一步详细描述。 如图 1所示， 一种四轴灯光飞行器， 包括控制电路 （4) ， 无线收发模块 （5) ， 电动机 （11 ) ， 电池 （9) ， 机身 （10) 和顶部防撞杆 （1) ： 所述控制电路 （4) 与蓝牙模 块、 测试程序模块、 四轴驱动模块和气压传感器模块的电压输入端连接； 所述 无线收发模块 （5) 由滤波部分、 解码器等组成与天线、 电源连接； 所述电动机 在螺螺旋翼 （12) 的下方对称分布在机体的前后、 左右四个方向； 所述电池 （9 ) 镶嵌在机身内部与充电接口 （2) 相连； 所述顶部防撞杆 （1) 插入机身的正 上方并且在机身 （10) 上表面的中心： 所述控制电路 （4) 由控制回路、 电源回 路、 主回路、 辅助回路组成： 所述控制回路中则由电源回路、 按钮幵关、 保护 幵关、 继电器线圈及其辅助触点组成； 所述电源回路由光敏电阻 R、 磁控幵关 L 、 定值电阻 R0、 电源 U1等组成； 所述无线收发模块 （5) 与接收模块直接和解码 器相连； 所述解码器再和单片机相连由编码模块和高频发射模块组成； 所述接 收部分则是由高频选频模块和解调模块组成； 所述电动机 （11) 由静止的定字 和可以转动的转子组成； 所述定子主要由定子铁芯、 定子绕组电阻和基座三部 分组成； 所述转子则通过轴与螺螺旋翼 （12) 相连， 所螺旋翼 （12) 对称分布 在机体的前后、 左右四个方向； 所述螺旋翼 （12) 处于同一高度平面， 且结构 和半径都相同， 所述电动机 （11) 有四个对称的安装在飞行器的支架端， 支架 中间空间安放飞行控制计算机和外部设备。 以上显示和描述了本实用新型的基 本原理、 主要特征和优点。 本行业的技术人员应该了解， 本实用新型不受上述 实施例的限制， 上述实施例和说明书中描述的只是说明本实用新型的原理， 在 不脱离本实用新型精神和范围的前提下， 本实用新型还会有各种变化和改进， 这些变化和改进都落入要求保护的本实用新型范围内。 本实用新型要求保护范 围由所附的权利要求书及其等效物界定。 The present invention will be further described in detail below in conjunction with the drawings and specific embodiments. As shown in Figure 1, a four-axis light aircraft includes a control circuit (4), a wireless transceiver module (5), an electric motor (11), a battery (9), a fuselage (10) and a top bumper (1). The control circuit (4) is connected to a voltage input end of the Bluetooth module, the test program module, the four-axis drive module, and the air pressure sensor module; the wireless transceiver module (5) is composed of a filter part, a decoder, and the like, and an antenna and a power supply. Connecting; the motor is symmetrically distributed under the spiral spiral wing (12) in front, rear, and left and right directions of the body; the battery (9) ) is mounted inside the fuselage and connected to the charging interface (2); the top anti-collision bar (1) is inserted directly above the fuselage and at the center of the upper surface of the fuselage (10): the control circuit (4) is controlled The circuit, the power circuit, the main circuit and the auxiliary circuit are composed of: the control circuit is composed of a power circuit, a button switch, a protection switch, a relay coil and an auxiliary contact thereof; the power circuit is composed of a photoresistor R and a magnetic control The switch module (5) and the receiving module are directly connected to the decoder; the decoder is connected to the single chip microcomputer and is composed of an encoding module and a high frequency transmitting module; The receiving portion is composed of a high frequency frequency selective module and a demodulation module; the motor (11) is composed of a stationary locating and a rotatable rotor; the stator is mainly composed of a stator core, a stator winding resistor and a base. The rotor is connected to the spiral helix (12) through a shaft, and the spiral wing (12) is symmetrically distributed in the front, rear, and left and right directions of the body; the spiral wing (12) is in the same A height plane, and the same structure and radius, the motor (11) has four symmetrical mountings on the support end of the aircraft, and the flight control computer and external equipment are placed in the middle space of the bracket. The basic principles, main features and advantages of the present invention have been shown and described above. It should be understood by those skilled in the art that the present invention is not limited by the foregoing embodiments. The foregoing embodiments and the description are merely illustrative of the principles of the present invention, without departing from the spirit and scope of the present invention. There are various changes and modifications in the novel types which fall within the scope of the claimed invention. The scope of the invention is defined by the appended claims and their equivalents.

Claims

权利要求书 Claim
[权利要求 1] 一种四轴灯光飞行器， 包括控制电路， 无线收发模块， 电动机， 电池 [Claim 1] A four-axis light aircraft, including a control circuit, a wireless transceiver module, an electric motor, a battery
， 机身和顶部防撞杆： 所述控制电路与蓝牙模块、 测试程序模块、 四 轴驱动模块和气压传感器模块的电压输入端连接； 所述无线收发模块 由滤波部分、 解码器等组成与天线、 电源连接； 所述电动机在螺螺旋 翼的下方对称分布在机体的前后、 左右四个方向； 所述电池镶嵌在机 身内部与充电接口相连； 所述顶部防撞杆插入机身的正上方并且在机 身上表面的中心。 , the fuselage and the top bumper: the control circuit is connected with the voltage input end of the Bluetooth module, the test program module, the four-axis drive module and the air pressure sensor module; the wireless transceiver module is composed of a filter part, a decoder, etc. The electric motor is connected symmetrically under the spiral spiral wing in four directions of front and rear and left and right sides of the body; the battery is embedded in the interior of the fuselage and connected to the charging interface; the top anti-collision bar is directly inserted above the fuselage And at the center of the upper surface of the fuselage.
[权利要求 2] 根据权利要求 1所述的一种四轴灯光飞行器， 其特征在于： 所述控制 电路由控制回路、 电源回路、 主回路、 辅助回路组成； 所述控制回路 中则由电源回路、 按钮幵关、 保护幵关、 继电器线圈及其辅助触点组 成； 所述电源回路由光敏电阻 R、 磁控幵关！^、 定值电阻 R0、 电源 U1 等组成。  [Claim 2] A four-axis light aircraft according to claim 1, wherein: the control circuit is composed of a control loop, a power supply loop, a main loop, and an auxiliary loop; and the control loop is composed of a power loop , button switch, protection switch, relay coil and its auxiliary contacts; the power circuit is made up of photoresistor R, magnetron! ^, fixed value resistor R0, power supply U1 and so on.
[权利要求 3] 根据权利要求 1所述的一种四轴灯光飞行器， 其特征在于： 所述无线 收发模块与接收模块直接和解码器相连； 所述解码器再和单片机相连 由编码模块和高频发射模块组成； 接收部分则是由高频选频模块和解 调模块组成。  [Claim 3] A four-axis light aircraft according to claim 1, wherein: the wireless transceiver module and the receiving module are directly connected to the decoder; and the decoder is connected to the single chip by the encoding module and the high The frequency transmitting module is composed; the receiving part is composed of a high frequency frequency selective module and a demodulation module.
[权利要求 4] 根据权利要求 1所述的一种四轴灯光飞行器， 其特征在于： 所述电动 机由静止的定字和可以转动的转子组成； 所述定子主要由定子铁芯、 定子绕组电阻和基座三部分组成； 所述转子则通过轴与螺螺旋翼相连 [Claim 4] A four-axis light aircraft according to claim 1, wherein: said motor is composed of a stationary locating and a rotatable rotor; said stator is mainly composed of a stator core and a stator winding resistor. And the base is composed of three parts; the rotor is connected to the spiral wing by a shaft
； 所螺旋翼对称分布在机体的前后、 左右四个方向； 所述螺螺旋翼处 于同一高度平面且结构和半径都相同； 所述电动机对称的安装在飞行 器的支架端； 所述支架端中间空间安放飞行控制计算机和外部设备。 The spiral wings are symmetrically distributed in the front, rear, and left and right directions of the body; the spiral spiral wings are at the same height plane and have the same structure and radius; the motor is symmetrically mounted on the bracket end of the aircraft; Place the flight control computer and external equipment.
PCT/CN2017/075672 2017-03-05 2017-03-05 Four-axis aerial vehicle provided with lights WO2018161193A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/075672 WO2018161193A1 (en) 2017-03-05 2017-03-05 Four-axis aerial vehicle provided with lights

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2017/075672 WO2018161193A1 (en) 2017-03-05 2017-03-05 Four-axis aerial vehicle provided with lights

Publications (1)

Publication Number Publication Date
WO2018161193A1 true WO2018161193A1 (en) 2018-09-13

Family

ID=63447693

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/075672 WO2018161193A1 (en) 2017-03-05 2017-03-05 Four-axis aerial vehicle provided with lights

Country Status (1)

Country Link
WO (1) WO2018161193A1 (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102442424A (en) * 2011-10-21 2012-05-09 北京工业大学 System and method for controlling fixed-height flight of fixed-wing unmanned aerial vehicle
CN103365295A (en) * 2013-06-29 2013-10-23 天津大学 DSP (Digital Signal Processor)-based quad-rotor unmanned aerial vehicle autonomous hover control system and method
CN105700540A (en) * 2016-03-09 2016-06-22 哈尔滨工业大学深圳研究生院 FPGA-based unmanned plane flight control circuit
CN205787908U (en) * 2016-05-23 2016-12-07 湖北省超能超高压电力科技开发有限公司 A kind of based on power transmission and transforming equipment UAV system field intensity indicator obstacle avoidance system
JP6051327B1 (en) * 2016-05-26 2016-12-27 株式会社プロドローン Unmanned aerial vehicle
US20170015412A1 (en) * 2015-07-17 2017-01-19 iDrone LLC Thrust vectoring on a rotor-based remote vehicle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102442424A (en) * 2011-10-21 2012-05-09 北京工业大学 System and method for controlling fixed-height flight of fixed-wing unmanned aerial vehicle
CN103365295A (en) * 2013-06-29 2013-10-23 天津大学 DSP (Digital Signal Processor)-based quad-rotor unmanned aerial vehicle autonomous hover control system and method
US20170015412A1 (en) * 2015-07-17 2017-01-19 iDrone LLC Thrust vectoring on a rotor-based remote vehicle
CN105700540A (en) * 2016-03-09 2016-06-22 哈尔滨工业大学深圳研究生院 FPGA-based unmanned plane flight control circuit
CN205787908U (en) * 2016-05-23 2016-12-07 湖北省超能超高压电力科技开发有限公司 A kind of based on power transmission and transforming equipment UAV system field intensity indicator obstacle avoidance system
JP6051327B1 (en) * 2016-05-26 2016-12-27 株式会社プロドローン Unmanned aerial vehicle

Similar Documents

Publication Publication Date Title
CN105516691B (en) Long stagnant empty unmanned plane base station communication and monitoring system
CN112567171B (en) Unmanned aerial vehicle station
CN204808049U (en) Communication system with unmanned aerial vehicle
CN204925801U (en) Changeable communication mode's unmanned aerial vehicle control system
TW200835540A (en) Central control system of wireless remote-control model
CN111262293A (en) Battery management system
CN105292477A (en) Wrist type portable accompanying flight autonomous supervision unmanned aerial vehicle
CN105321317A (en) Intelligent Bluetooth control system with posture induction function
WO2018103203A1 (en) Ducted unmanned aerial vehicle
CN104071352A (en) Intelligent taking-off and landing platform system for micro aerial vehicle
CN106961577A (en) A kind of unmanned aerial vehicle control system and method
WO2018161193A1 (en) Four-axis aerial vehicle provided with lights
CN112034890B (en) Unmanned aerial vehicle man-machine cooperative control system
CN108928480A (en) A kind of unmanned plane being automatically separated storehouse with photographic equipment waterproof
CN203342370U (en) Mini-type four-rotor aircraft controlled by Bluetooth
CN105511455A (en) Control system and method for amphibious unmanned aircraft
CN206249103U (en) A kind of unmanned aerial vehicle control system
CN205221113U (en) Portable companion of wrist formula flies autonomic control unmanned aerial vehicle
CN214493340U (en) Flapping wing aircraft with parachute function
CN205293094U (en) Cut umbrella device and have device's unmanned aircraft
CN103977569A (en) Mobile phone vertical lifting aircraft
CN113371225A (en) Unmanned aerial vehicle leaves empty power supply system
CN204660017U (en) A kind of kite assisting in flying device
CN111522357A (en) Control method and system for unmanned aerial vehicle flight
CN107187589B (en) A kind of Intelligent unattended machine

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: 17899536

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

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 22/01/2020)

122 Ep: pct application non-entry in european phase

Ref document number: 17899536

Country of ref document: EP

Kind code of ref document: A1