WO2018006439A1 - Integrated power multi-axis unmanned aerial vehicle - Google Patents

Integrated power multi-axis unmanned aerial vehicle Download PDF

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Publication number
WO2018006439A1
WO2018006439A1 PCT/CN2016/090571 CN2016090571W WO2018006439A1 WO 2018006439 A1 WO2018006439 A1 WO 2018006439A1 CN 2016090571 W CN2016090571 W CN 2016090571W WO 2018006439 A1 WO2018006439 A1 WO 2018006439A1
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WIPO (PCT)
Prior art keywords
unit
aerial vehicle
flight control
unmanned aerial
power generation
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PCT/CN2016/090571
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French (fr)
Chinese (zh)
Inventor
鲍静云
范晋红
王威
殷兰兰
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深圳市龙云创新航空科技有限公司
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Publication of WO2018006439A1 publication Critical patent/WO2018006439A1/en

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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/31—Supply or distribution of electrical power generated by photovoltaics
    • 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

Definitions

  • the invention relates to the technical field of drones, in particular to an integrated power multi-axis drone.
  • the existing power solutions mainly include the following: (1) Polymer rechargeable lithium battery, which is the power mode adopted by most multi-axis rotary wing drones. The flight control response is fast, the structure is simple, and the light is short. It is short flight time and long charging time. (2) Two-stroke or four-stroke fuel engines, when used in multi-axis drones, have the disadvantages of being complicated, cumbersome, prone to failure, and difficult to maintain. (3) Turbojet engines have the same disadvantages as before, and are expensive, difficult to debug, and short in service life.
  • an object of the present invention is to provide an integrated power multi-axis unmanned aerial vehicle with simple structure and long flight stability.
  • an integrated power multi-axis unmanned aerial vehicle comprising a drone body, wherein the unmanned aerial vehicle body is provided with a power generating unit, a power storage unit, a flight control unit and an electric drive unit, An output end of the flight control unit is connected to an input end of the electric drive unit, the flight control unit is connected to the power generation unit, the power generation unit is connected to the power storage unit, and an output end of the power generation unit and an input of the electric drive unit End connection, an output end of the power storage unit is respectively connected to an input end of the electric drive unit and an input end of the flight control unit;
  • the power generation system includes an internal combustion engine, a fuel tank, a cooling fan, a generator, and a rectification module, and the internal combustion engine passes The oil pipe is connected to the fuel tank, the output torque of the internal combustion engine is connected to the generator input torque; the heat dissipation fan is used for heat dissipation of the power generation module, and the input end thereof is connected to the output end
  • the power storage unit includes a lithium battery and a balance charge, and an output end of the power generation unit is connected by a balanced charge and an input end of the lithium battery.
  • the power storage unit further includes a solar power generation module, the solar power generation module is laid on the unmanned aerial vehicle body, and an output end of the solar power generation module is connected to an input end of the lithium battery through a balance charge.
  • the power generating unit further includes a throttle servo and a tachometer, wherein the tachometer is configured to detect and display the engine speed, the throttle servo is used to control the engine speed, and the output end of the tachometer and the flight control unit The input terminal is connected, and the input end of the throttle servo is connected to the output end of the flight control unit.
  • the power generating unit further includes a temperature sensor disposed on the surface of the generator, and an output end thereof is connected to the flight control module.
  • the electric drive unit includes an electric motor and a propeller, and an output torque of the electric motor is coupled to the propeller.
  • the invention has the beneficial effects that the invention is provided with an internal combustion engine, an electric motor, a power storage unit and an electric drive unit, and the internal combustion engine drives the generator to generate electricity for the electric drive unit and the electric storage unit, because the energy density ratio of the fuel is high;
  • the flight of the aircraft does not require complicated mechanical structure, which reduces the weight of the aircraft;
  • the organic combination of the power supply modes of the oil and electricity system greatly extends the range of the drone, and the present invention also has a cooling fan, which can be used to dissipate the generator through the cooling fan. The heat dissipation prevents the generator from being overheated and damaged.
  • the invention realizes stable and reliable long-distance flight of the drone.
  • Figure 1 is a schematic view showing the structure of an embodiment of the present invention.
  • an integrated power multi-axis unmanned aerial vehicle includes a drone body, and the unmanned aerial vehicle body is provided with a power generating unit, a power storage unit, a flight control unit and an electric drive unit, and the fly An output end of the control unit is connected to an input end of the electric drive unit, the flight control unit is connected to the power generation unit, the power generation unit is connected to the power storage unit, and an output end of the power generation unit is connected to an input end of the electric drive unit.
  • An output end of the power storage unit is respectively connected to an input end of the electric drive unit and an input end of the flight control unit;
  • the power generation system includes an internal combustion engine, a fuel tank, a cooling fan, a generator, and a rectifier module, and the internal combustion engine passes through the oil pipe and the fuel tank Connected, the output torque of the internal combustion engine is connected to the generator input torque;
  • the cooling fan is used to dissipate heat to the power generation module, and the input end thereof is connected to the output end of the flight control system; the output end of the generator passes through the rectifier module and the power The input of the drive unit is connected.
  • the invention also has a cooling fan, which can dissipate heat from the generator through the cooling fan to prevent the generator from overheating and damage.
  • the power supply unit can be used as a backup power source in a special case by connecting with the electric drive unit, and can also be used as an internal combustion engine starting energy source when connected to the generator.
  • the power storage unit includes a lithium battery and a balance charge, and an output end of the power generation unit is connected by a balanced charge and an input end of the lithium battery. Battery life can be extended by charging the battery with a balanced charge.
  • the power storage unit further includes a solar power generation module, the solar power generation module is laid on the unmanned aerial vehicle body, and the output end of the solar power generation module is connected to the input end of the lithium battery through the balance charge.
  • the lithium battery can be charged by the solar power generation module, so that the flying cost of the drone is reduced, and the environment is energy-saving.
  • the power generating unit further includes a throttle servo for detecting and displaying the engine speed, the throttle servo for controlling the engine speed, and an output end of the tachometer.
  • a throttle servo for detecting and displaying the engine speed
  • the throttle servo for controlling the engine speed
  • an output end of the tachometer Connected to the input of the flight control unit, the input of the throttle servo is connected to the output of the flight control unit.
  • the internal combustion engine is turned by the system components such as its own tank throttle servo to provide the motive force.
  • the tachometer can detect the engine speed, then feed the speed information to the flight control unit, and send the control signal to the throttle servo through the flight control unit to control the engine speed.
  • the power generating unit further includes a temperature sensor, the temperature sensor is disposed on the surface of the generator, and the output end thereof is connected to the flight control module, and the temperature information of the generator is detected by the temperature sensor and transmitted to the flight control unit.
  • the flight control unit can control the speed of the cooling fan to enhance the heat dissipation to prevent the generator from being damaged due to overheating.
  • the electric drive unit includes an electronic governor, an electric motor and a propeller, and the output torque of the electric motor and the propeller are connected to drive the propeller to provide lift for the drone, and the electric motor is adjusted by the electronic governor. speed.
  • the flight control unit is the central nervous system of the whole scheme, and its function is to collect data collected by each sensing unit, and output various control commands to plan and execute various flight tasks.
  • the sensor unit in the flight controller measures the flight attitude of the aircraft and outputs a trim command to the electronic speed governor and the throttle servo to maintain the aircraft's power motor at the required speed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Secondary Cells (AREA)

Abstract

An integrated power multi-axis unmanned aerial vehicle, which comprises an internal combustion engine, an electric motor, an electricity storage unit, and an electric drive unit. The internal combustion engine is employed to drive an electric generator to generate electricity so as to provide power to the electric drive unit and the electricity storage unit. Because the energy density ratio of a fuel is high, the employment of electricity for driving the aerial vehicle in flight obviates the need for a complex mechanical structure, thus reducing the weight of the aerial vehicle. The organic combination of fuel-electricity integrated power supply mode greatly extends the range of the unmanned aerial vehicle; at the same time, a cooling fan is provided, and the electric generator can be cooled by the cooling fan, thus preventing the electric generator from being damaged due to overheating. In sum of the above, the integrated power multi-axis unmanned aerial vehicle implements stable, reliable, long-range flight of the unmanned aerial vehicle and is broadly applicable in the technical field of unmanned aerial vehicles.

Description

一种集成式动力多轴无人机  Integrated power multi-axis drone
技术领域Technical field
本发明涉及无人机技术领域，尤其涉及一种集成式动力多轴无人机。The invention relates to the technical field of drones, in particular to an integrated power multi-axis drone.
背景技术Background technique
近年来，随着无人机应用的推广，应用领域不断拓展，不同行业不同领域对无人机性能需求不尽相同，但都希望飞行时间能尽可能的长，受限于目前主流无人机动力方案的各种技术瓶颈，飞行时间都达不到人们的期望值。现有动力解决方案主要有如下几种：(1)聚合物可充电锂电池，这是目前绝大多数多轴旋翼无人机采用的动力方式，飞行控制响应快、结构简单、轻便，其缺点是飞行时间短，充电时间长。(2)两冲程或四冲程燃油发动机，用于多轴无人机时其缺点是机构复杂、笨重、易出故障、难以维护保养。(3)涡轮喷气发动机，其缺点同前，另价格昂贵、调试难度大、使用寿命短。 In recent years, with the promotion of drone applications, the application field has been expanding, and the performance requirements of drones in different industries and different fields are not the same, but they all hope that the flight time can be as long as possible, limited by the current mainstream drones. The various technical bottlenecks of the power plan, flight time can not meet people's expectations. The existing power solutions mainly include the following: (1) Polymer rechargeable lithium battery, which is the power mode adopted by most multi-axis rotary wing drones. The flight control response is fast, the structure is simple, and the light is short. It is short flight time and long charging time. (2) Two-stroke or four-stroke fuel engines, when used in multi-axis drones, have the disadvantages of being complicated, cumbersome, prone to failure, and difficult to maintain. (3) Turbojet engines have the same disadvantages as before, and are expensive, difficult to debug, and short in service life.
发明内容Summary of the invention
为了解决上述技术问题，本发明的目的是提供一种结构简单、长航稳定安全的集成式动力多轴无人机。In order to solve the above technical problems, an object of the present invention is to provide an integrated power multi-axis unmanned aerial vehicle with simple structure and long flight stability.
本发明所采用的技术方案是：一种集成式动力多轴无人机，包括无人机本体，所述无人机本体内设置有发电单元、储电单元、飞控单元和电力驱动单元，所述飞控单元的输出端与电力驱动单元的输入端连接，所述飞控单元与发电单元连接，所述发电单元与储电单元连接，所述发电单元的输出端与电力驱动单元的输入端连接，所述储电单元的输出端分别与电力驱动单元的输入端和飞控单元的输入端连接；所述发电系统包括内燃机、油箱、散热风扇、发电机和整流模块，所述内燃机通过油管与油箱连接、所述内燃机的输出扭矩与发电机输入扭矩连接；所述散热风扇用于给发电模块散热、其输入端与飞控系统的输出端连接；所述发电机的输出端通过整流模块与电力驱动单元的输入端连接。The technical solution adopted by the present invention is: an integrated power multi-axis unmanned aerial vehicle comprising a drone body, wherein the unmanned aerial vehicle body is provided with a power generating unit, a power storage unit, a flight control unit and an electric drive unit, An output end of the flight control unit is connected to an input end of the electric drive unit, the flight control unit is connected to the power generation unit, the power generation unit is connected to the power storage unit, and an output end of the power generation unit and an input of the electric drive unit End connection, an output end of the power storage unit is respectively connected to an input end of the electric drive unit and an input end of the flight control unit; the power generation system includes an internal combustion engine, a fuel tank, a cooling fan, a generator, and a rectification module, and the internal combustion engine passes The oil pipe is connected to the fuel tank, the output torque of the internal combustion engine is connected to the generator input torque; the heat dissipation fan is used for heat dissipation of the power generation module, and the input end thereof is connected to the output end of the flight control system; the output end of the generator is rectified The module is connected to the input of the electric drive unit.
进一步，所述储电单元包括锂电池和平衡充，所述发电单元的输出端通过平衡充和锂电池的输入端连接。Further, the power storage unit includes a lithium battery and a balance charge, and an output end of the power generation unit is connected by a balanced charge and an input end of the lithium battery.
进一步，所述的储电单元还包括太阳能发电模块，所述太阳能发电模块铺设于无人机本体上，所述太阳能发电模块的输出端通过平衡充与锂电池的输入端连接。Further, the power storage unit further includes a solar power generation module, the solar power generation module is laid on the unmanned aerial vehicle body, and an output end of the solar power generation module is connected to an input end of the lithium battery through a balance charge.
进一步，所述发电单元还包括油门舵机和转速表，所述转速表用于检测与显示内燃机转速，所述油门舵机用于控制内燃机转速，所述转速表的输出端与飞控单元的输入端连接，所述油门舵机的输入端与飞控单元的输出端连接。Further, the power generating unit further includes a throttle servo and a tachometer, wherein the tachometer is configured to detect and display the engine speed, the throttle servo is used to control the engine speed, and the output end of the tachometer and the flight control unit The input terminal is connected, and the input end of the throttle servo is connected to the output end of the flight control unit.
进一步，所述的发电单元还包括温度传感器，所述温度传感器设置于发电机表面，其输出端与飞控模块连接。Further, the power generating unit further includes a temperature sensor disposed on the surface of the generator, and an output end thereof is connected to the flight control module.
进一步，所述电力驱动单元包括电动机与螺旋桨，所述电动机的输出扭矩与螺旋桨连接。Further, the electric drive unit includes an electric motor and a propeller, and an output torque of the electric motor is coupled to the propeller.
本发明的有益效果是：本发明设有内燃机、电动机、储电单元以及电力驱动单元，采用内燃机驱动发电机发电为电力驱动单元和储电单元提供能量，由于燃油的能量密度比高；采用电力驱动飞机飞行不需复杂的机械结构，减轻了飞机重量；油电一体的供能方式的有机结合，大大延长了无人机航程，同时本发明还设有散热风扇，通过散热风扇可对发电机散热，防止发电机过热损坏，综上所述，本发明实现了无人机稳定可靠远航飞行。The invention has the beneficial effects that the invention is provided with an internal combustion engine, an electric motor, a power storage unit and an electric drive unit, and the internal combustion engine drives the generator to generate electricity for the electric drive unit and the electric storage unit, because the energy density ratio of the fuel is high; The flight of the aircraft does not require complicated mechanical structure, which reduces the weight of the aircraft; the organic combination of the power supply modes of the oil and electricity system greatly extends the range of the drone, and the present invention also has a cooling fan, which can be used to dissipate the generator through the cooling fan. The heat dissipation prevents the generator from being overheated and damaged. In summary, the invention realizes stable and reliable long-distance flight of the drone.
附图说明DRAWINGS
下面结合附图对本发明的具体实施方式作进一步说明：The specific embodiments of the present invention are further described below in conjunction with the accompanying drawings:
图1是本发明一具体实施例的结构示意图。BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a schematic view showing the structure of an embodiment of the present invention.
具体实施方式detailed description
需要说明的是，在不冲突的情况下，本申请中的实施例及实施例中的特征可以相互组合。It should be noted that the embodiments in the present application and the features in the embodiments may be combined with each other without conflict.
如图1所示，一种集成式动力多轴无人机，包括无人机本体，所述无人机本体内设置有发电单元、储电单元、飞控单元和电力驱动单元，所述飞控单元的输出端与电力驱动单元的输入端连接，所述飞控单元与发电单元连接，所述发电单元与储电单元连接，所述发电单元的输出端与电力驱动单元的输入端连接，所述储电单元的输出端分别与电力驱动单元的输入端和飞控单元的输入端连接；所述发电系统包括内燃机、油箱、散热风扇、发电机和整流模块，所述内燃机通过油管与油箱连接、所述内燃机的输出扭矩与发电机输入扭矩连接；所述散热风扇用于给发电模块散热、其输入端与飞控系统的输出端连接；所述发电机的输出端通过整流模块与电力驱动单元的输入端连接。As shown in FIG. 1 , an integrated power multi-axis unmanned aerial vehicle includes a drone body, and the unmanned aerial vehicle body is provided with a power generating unit, a power storage unit, a flight control unit and an electric drive unit, and the fly An output end of the control unit is connected to an input end of the electric drive unit, the flight control unit is connected to the power generation unit, the power generation unit is connected to the power storage unit, and an output end of the power generation unit is connected to an input end of the electric drive unit. An output end of the power storage unit is respectively connected to an input end of the electric drive unit and an input end of the flight control unit; the power generation system includes an internal combustion engine, a fuel tank, a cooling fan, a generator, and a rectifier module, and the internal combustion engine passes through the oil pipe and the fuel tank Connected, the output torque of the internal combustion engine is connected to the generator input torque; the cooling fan is used to dissipate heat to the power generation module, and the input end thereof is connected to the output end of the flight control system; the output end of the generator passes through the rectifier module and the power The input of the drive unit is connected.
其工作原理为：采用内燃机驱动发电机发电为电力驱动单元和储电单元提供能量，由于燃油的能量密度比高；采用电力驱动飞机飞行不需复杂的机械结构，减轻了飞机重量；油电一体的供能方式的有机结合，因此大大延长了无人机航程，同时本发明还设有散热风扇，通过散热风扇可对发电机散热，防止发电机过热损坏。所述供电单元通过与电力驱动单元连接不仅可以在特殊情况下作为备用的动力能源，同时与发电机连接还可以作为内燃机启动能源。The working principle is as follows: the internal combustion engine drives the generator to generate electricity for the electric drive unit and the storage unit, because the energy density ratio of the fuel is high; the electric-driven aircraft flight does not require complicated mechanical structure, which reduces the weight of the aircraft; The organic combination of the energy supply modes greatly extends the drone voyage. At the same time, the invention also has a cooling fan, which can dissipate heat from the generator through the cooling fan to prevent the generator from overheating and damage. The power supply unit can be used as a backup power source in a special case by connecting with the electric drive unit, and can also be used as an internal combustion engine starting energy source when connected to the generator.
进一步作为优选的实施方式，所述储电单元包括锂电池和平衡充，所述发电单元的输出端通过平衡充和锂电池的输入端连接。通过平衡充对电池充电可延长电池的使用寿命。Further as a preferred embodiment, the power storage unit includes a lithium battery and a balance charge, and an output end of the power generation unit is connected by a balanced charge and an input end of the lithium battery. Battery life can be extended by charging the battery with a balanced charge.
进一步作为优选的实施方式，所述的储电单元还包括太阳能发电模块，所述太阳能发电模块铺设于无人机本体上，所述太阳能发电模块的输出端通过平衡充与锂电池的输入端连接，通过太阳能发电模块可对锂电池充电，使得无人机飞行成本降低，环保节能。Further, as a preferred embodiment, the power storage unit further includes a solar power generation module, the solar power generation module is laid on the unmanned aerial vehicle body, and the output end of the solar power generation module is connected to the input end of the lithium battery through the balance charge. The lithium battery can be charged by the solar power generation module, so that the flying cost of the drone is reduced, and the environment is energy-saving.
进一步作为优选的实施方式，所述发电单元还包括油门舵机和转速表，所述转速表用于检测与显示内燃机转速，所述油门舵机用于控制内燃机转速，所述转速表的输出端与飞控单元的输入端连接，所述油门舵机的输入端与飞控单元的输出端连接。通过自身的油箱油门舵机等系统组件让内燃机机转起来提供原动力。其转速表可检测发动机转速，然后把转速信息反馈到飞控单元，通过飞控单元，把控制信号给油门舵机，进而控制内燃机机转速。Further, as a preferred embodiment, the power generating unit further includes a throttle servo for detecting and displaying the engine speed, the throttle servo for controlling the engine speed, and an output end of the tachometer. Connected to the input of the flight control unit, the input of the throttle servo is connected to the output of the flight control unit. The internal combustion engine is turned by the system components such as its own tank throttle servo to provide the motive force. The tachometer can detect the engine speed, then feed the speed information to the flight control unit, and send the control signal to the throttle servo through the flight control unit to control the engine speed.
进一步作为优选的实施方式，所述的发电单元还包括温度传感器，所述温度传感器设置于发电机表面，其输出端与飞控模块连接，通过温度传感器检测发电机温度信息传输给飞控单元，当温度过高时，飞控单元可通过控制散热风扇的转速，加强散热力度以防止发电机因过热而损坏。Further, as a preferred embodiment, the power generating unit further includes a temperature sensor, the temperature sensor is disposed on the surface of the generator, and the output end thereof is connected to the flight control module, and the temperature information of the generator is detected by the temperature sensor and transmitted to the flight control unit. When the temperature is too high, the flight control unit can control the speed of the cooling fan to enhance the heat dissipation to prevent the generator from being damaged due to overheating.
进一步作为优选的实施方式，所述电力驱动单元包括电子调速器、电动机与螺旋桨，所述电动机的输出扭矩与螺旋桨连接带动螺旋桨转动为无人机提供升力，通过电子调速器，对电动机调速。Further, as a preferred embodiment, the electric drive unit includes an electronic governor, an electric motor and a propeller, and the output torque of the electric motor and the propeller are connected to drive the propeller to provide lift for the drone, and the electric motor is adjusted by the electronic governor. speed.
所述飞控单元是整个方案的中枢神经系统，它的作用是收集各传感单元采集的数据，并输出各种控制指令，规划和执行各种飞行任务。 飞控中的传感器单元测量飞机的飞行姿态并输出修整指令给电子调速其和油门舵机使飞机的动力电动机保持在需要的转速上。The flight control unit is the central nervous system of the whole scheme, and its function is to collect data collected by each sensing unit, and output various control commands to plan and execute various flight tasks. The sensor unit in the flight controller measures the flight attitude of the aircraft and outputs a trim command to the electronic speed governor and the throttle servo to maintain the aircraft's power motor at the required speed.
以上是对本发明的较佳实施进行了具体说明，但本发明创造并不限于所述实施例，熟悉本领域的技术人员在不违背本发明精神的前提下还可做作出种种的等同变形或替换，这些等同的变形或替换均包含在本申请权利要求所限定的范围内。The above is a detailed description of the preferred embodiments of the present invention, but the present invention is not limited to the embodiments, and those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the invention. Such equivalent modifications or alternatives are intended to be included within the scope of the claims.

Claims (6)

  1. 一种集成式动力多轴无人机，包括无人机本体，其特征在于：所述无人机本体内设置有发电单元、储电单元、飞控单元和电力驱动单元，所述飞控单元的输出端与电力驱动单元的输入端连接，所述飞控单元与发电单元连接，所述发电单元与储电单元连接，所述发电单元的输出端与电力驱动单元的输入端连接，所述储电单元的输出端分别与电力驱动单元的输入端和飞控单元的输入端连接； An integrated power multi-axis unmanned aerial vehicle includes a drone body, wherein: the unmanned aerial vehicle body is provided with a power generating unit, a power storage unit, a flight control unit and an electric drive unit, and the flight control unit The output end is connected to the input end of the electric drive unit, the flight control unit is connected to the power generation unit, the power generation unit is connected to the power storage unit, and the output end of the power generation unit is connected to the input end of the electric drive unit, An output end of the power storage unit is respectively connected to an input end of the electric drive unit and an input end of the flight control unit;
    所述发电系统包括内燃机、油箱、散热风扇、发电机和整流模块，所述内燃机通过油管与油箱连接、所述内燃机的输出扭矩与发电机输入扭矩连接；所述散热风扇用于给发电模块散热、其输入端与飞控系统的输出端连接；所述发电机的输出端通过整流模块与电力驱动单元的输入端连接。 The power generation system includes an internal combustion engine, a fuel tank, a heat dissipation fan, a generator, and a rectification module, the internal combustion engine is connected to a fuel tank through a fuel pipe, and an output torque of the internal combustion engine is connected to a generator input torque; the cooling fan is used to dissipate heat from a power generation module. The input end thereof is connected to the output end of the flight control system; the output end of the generator is connected to the input end of the electric drive unit through the rectifier module.
  2. 根据权利要求1所述的集成式动力多轴无人机，其特征在于：所述储电单元包括锂电池和平衡充，所述发电单元的输出端通过平衡充和锂电池的输入端连接。The integrated power multi-axis drone according to claim 1, wherein the power storage unit comprises a lithium battery and a balance charge, and an output end of the power generation unit is connected by an input terminal of the balance charge lithium battery.
  3. 根据权利要求2所述的集成式动力多轴无人机，其特征在于：所述的储电单元还包括太阳能发电模块，所述太阳能发电模块铺设于无人机本体上，所述太阳能发电模块的输出端通过平衡充与锂电池的输入端连接。The integrated power multi-axis drone according to claim 2, wherein the power storage unit further comprises a solar power generation module, the solar power generation module is laid on the unmanned aerial vehicle body, and the solar power generation module The output is connected to the input of the lithium battery through a balanced charge.
  4. 根据权利要求3所述的集成式动力多轴无人机，其特征在于：所述发电单元还包括油门舵机和转速表，所述转速表用于检测与显示内燃机转速，所述油门舵机用于控制内燃机转速，所述转速表的输出端与飞控单元的输入端连接，所述油门舵机的输入端与飞控单元的输出端连接。The integrated power multi-axis drone according to claim 3, wherein said power generating unit further comprises a throttle servo and a tachometer, said tachometer for detecting and displaying the engine speed, said throttle servo For controlling the engine speed, the output of the tachometer is connected to the input of the flight control unit, and the input of the throttle servo is connected to the output of the flight control unit.
  5. 根据权利要求4所述的集成式动力多轴无人机，其特征在于：所述的发电单元还包括温度传感器，所述温度传感器设置于发电机表面，其输出端与飞控模块连接。The integrated power multi-axis drone according to claim 4, wherein the power generating unit further comprises a temperature sensor, the temperature sensor is disposed on the surface of the generator, and the output end thereof is connected to the flight control module.
  6. 根据权利要求5所述的集成式动力多轴无人机，其特征在于：所述电力驱动单元包括电动机与螺旋桨，所述电动机的输出扭矩与螺旋桨连接。The integrated power multi-axis drone according to claim 5, wherein said electric drive unit comprises an electric motor and a propeller, and an output torque of said electric motor is coupled to the propeller.
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