WO2017147764A1 - 电源组件、无人飞行器及遥控移动装置 - Google Patents

电源组件、无人飞行器及遥控移动装置 Download PDF

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Publication number
WO2017147764A1
WO2017147764A1 PCT/CN2016/074915 CN2016074915W WO2017147764A1 WO 2017147764 A1 WO2017147764 A1 WO 2017147764A1 CN 2016074915 W CN2016074915 W CN 2016074915W WO 2017147764 A1 WO2017147764 A1 WO 2017147764A1
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WO
WIPO (PCT)
Prior art keywords
circuit board
disposed
power supply
casing
mobile device
Prior art date
Application number
PCT/CN2016/074915
Other languages
English (en)
French (fr)
Inventor
唐尹
冯建刚
农贵升
Original Assignee
深圳市大疆创新科技有限公司
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 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to PCT/CN2016/074915 priority Critical patent/WO2017147764A1/zh
Priority to CN201680004579.6A priority patent/CN107223108B/zh
Publication of WO2017147764A1 publication Critical patent/WO2017147764A1/zh
Priority to US16/110,756 priority patent/US11034446B2/en
Priority to US17/346,191 priority patent/US20210300558A1/en

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Classifications

    • 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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/08—Arrangements of cameras
    • 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
    • B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
    • B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U60/00—Undercarriages
    • B64U60/50—Undercarriages with landing legs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements

Definitions

  • the present invention relates to a power supply assembly and an unmanned aerial vehicle and a remote control mobile device using the same.
  • Remotely controlled mobile devices such as unmanned aerial vehicles or unmanned vehicles, generally include a host mounting structure and control, powering, and powering devices respectively coupled to the host mounting structure.
  • the user remotely controls the control device through a control device such as a remote controller, so that the control device controls the power device to drive the remote mobile device to travel as a whole.
  • the energizing device is for providing a source of energy to the power unit.
  • the above-mentioned host installation structure is generally: integrating as many functional modules as possible on one circuit board, and placing the circuit board in the casing of the remote control mobile device . However, since all the functional modules are integrated on the circuit board, assembly, disassembly, or maintenance of the above-described host mounting structure is inconvenient.
  • An unmanned aerial vehicle includes a fuselage and a power supply assembly disposed on the fuselage.
  • the power supply assembly includes a polyhedral mount, an energizing device, and at least two functional modules, the mounting bracket being disposed on the fuselage, the at least two functional modules being disposed separately from each other differently from the mounting bracket Sideways and electrically connected to each other.
  • the power supply device is disposed on the mounting frame, and the at least two functional modules are electrically connected to the power supply device.
  • the airframe is a casing, and the power component is housed in the casing.
  • the air body includes an upper case and a lower case that are engaged with each other, and the power component is disposed between the upper case and the lower case.
  • the power component is fixedly disposed on the upper casing to form an upper casing assembly with the upper casing.
  • the unmanned aerial vehicle further includes at least one control member fixed to the lower casing and corresponding to the mounting bracket.
  • the at least one control member includes a first control member fixedly stacked on the lower case, and the first control member is a circuit board.
  • the at least one control component further includes a second control component, the second control component is stacked on the first control component, and the second control component is a circuit board.
  • the at least one control member is electrically connected to a load mounted on the UAV and is used to control the load operation.
  • the unmanned aerial vehicle further includes a heat dissipating member disposed on the lower casing adjacent to the control member.
  • the at least one control member and the heat dissipating member are respectively fixed to the lower case to form a lower case assembly with the lower case.
  • the lower case includes a first housing and a second housing, the first housing is detachably coupled to the upper housing, and the second housing is detachably mounted to the first housing On the housing.
  • the at least one control member and the heat dissipating member are respectively fixed on the second housing to facilitate integrated assembly of the at least one control member and the heat dissipating member.
  • the first housing is provided with a mounting opening, the mounting opening extends through the first housing and communicates with the inner cavity of the fuselage, and the second housing is disposed on the mounting opening .
  • the heat sink is a heat dissipation fan.
  • the lower case includes a first case and a second case, the first case is engaged with the upper case, and the second case is detachably mounted on the first case Physically.
  • the first housing is provided with a mounting opening, the mounting opening extends through the first housing and communicates with the inner cavity of the fuselage, and the second housing is disposed on the mounting opening .
  • the unmanned aerial vehicle is provided with an image acquisition device, and the image acquisition device is connected to the second casing of the fuselage.
  • the unmanned aerial vehicle further includes a cloud platform, the cloud platform is adjustably disposed on the second housing, and the image acquisition device is disposed on the cloud platform.
  • the UAV further includes a landing gear disposed on the first casing of the fuselage and extending away from the fuselage.
  • the UAV further includes a motor disposed on the body and a propeller disposed on the motor.
  • the at least two functional modules are respectively boards for performing different functions.
  • the at least two functional modules are at least one of the following: a speed sensing module, a gravity sensing module, a visual sensing module, a magnetic field sensing module, and a control module.
  • the at least two functional modules include a first circuit board and a second circuit board, and the first circuit board and the second circuit board are respectively disposed on opposite sides of the mounting frame.
  • the energy supply device is disposed in the mounting frame, and the first circuit board and the second circuit board are respectively stacked on outer peripheral surfaces of opposite sides of the mounting frame.
  • the power supply assembly further includes an adapter disposed at one end of the mounting bracket and electrically connected to the power supply device.
  • the adapter is stacked on an outer circumferential surface of the mounting frame, and opposite sides of the adapter are adjacent to the first circuit board and the second circuit board, respectively.
  • a standard interface is disposed on the adapter, and the standard interface is used for electrical connection with the power supply device.
  • the at least two functional modules further include a third circuit board disposed on the mounting bracket and spaced apart from the second circuit board and the first circuit board, respectively.
  • the third circuit board is electrically connected to the energy supply device.
  • the third circuit board is stacked on an outer peripheral surface of the mounting frame, and three sides of the third circuit board are adjacent to the first circuit board, the second circuit board, and the Adapter.
  • the power component further includes a controller disposed on a side of the third circuit board facing away from the mounting frame, and the controller is electrically connected to the power supply device.
  • two ends of the controller respectively extend from opposite ends of the third circuit board, and are respectively electrically connected to the power supply device.
  • controller is a flight controller or a travel controller.
  • the power supply assembly further includes a controller connected to the mounting bracket, and the controller is a flight controller or a travel controller.
  • a remote control mobile device includes a body and a power component disposed on the body.
  • the power supply assembly includes a polyhedral mount, an energizing device, and at least two functional modules, the mounting bracket being disposed on the fuselage, the at least two functional modules being disposed separately from each other differently from the mounting bracket Sideways and electrically connected to each other.
  • the power supply device is disposed on the mounting frame, and the at least two functional modules are electrically connected to the power supply device.
  • the airframe is a casing, and the power component is housed in the casing.
  • the air body includes an upper case and a lower case that are engaged with each other, and the power component is disposed between the upper case and the lower case.
  • the power component is fixedly disposed on the upper casing to form an upper casing assembly with the upper casing.
  • the unmanned aerial vehicle further includes at least one control member fixed to the lower casing and corresponding to the mounting bracket.
  • the at least one control member includes a first control member fixedly stacked on the lower case, and the first control member is a circuit board.
  • the at least one control component further includes a second control component, the second control component is stacked on the first control component, and the second control component is a circuit board.
  • the at least one control member is electrically connected to a load mounted on the UAV and is used to control the load operation.
  • the unmanned aerial vehicle further includes a heat dissipating member disposed on the lower casing adjacent to the control member.
  • the at least one control member and the heat dissipating member are respectively fixed to the lower case to form a lower case assembly with the lower case.
  • the lower case includes a first housing and a second housing, the first housing is detachably coupled to the upper housing, and the second housing is detachably mounted to the first housing On the housing.
  • the at least one control member and the heat dissipating member are respectively fixed on the second housing to facilitate integrated assembly of the at least one control member and the heat dissipating member.
  • the first housing is provided with a mounting opening, the mounting opening extends through the first housing and communicates with the inner cavity of the fuselage, and the second housing is disposed on the mounting opening .
  • the heat sink is a heat dissipation fan.
  • the lower case includes a first case and a second case, the first case is engaged with the upper case, and the second case is detachably mounted on the first case Physically.
  • the first housing is provided with a mounting opening, the mounting opening extends through the first housing and communicates with the inner cavity of the fuselage, and the second housing is disposed on the mounting opening .
  • the unmanned aerial vehicle is provided with an image acquisition device, and the image acquisition device is connected to the second casing of the fuselage.
  • the unmanned aerial vehicle further includes a cloud platform, the cloud platform is adjustably disposed on the second housing, and the image acquisition device is disposed on the cloud platform.
  • the UAV further includes a landing gear disposed on the first casing of the fuselage and extending away from the fuselage.
  • the UAV further includes a motor disposed on the body and a propeller disposed on the motor.
  • the at least two functional modules are respectively boards for performing different functions.
  • the at least two functional modules are at least one of the following: a speed sensing module, a gravity sensing module, a visual sensing module, a magnetic field sensing module, and a control module.
  • the at least two functional modules include a first circuit board and a second circuit board, and the first circuit board and the second circuit board are respectively disposed on opposite sides of the mounting frame.
  • the energy supply device is disposed in the mounting frame, and the first circuit board and the second circuit board are respectively stacked on outer peripheral surfaces of opposite sides of the mounting frame.
  • the power supply assembly further includes an adapter disposed at one end of the mounting bracket and electrically connected to the power supply device.
  • the adapter is stacked on an outer circumferential surface of the mounting frame, and opposite sides of the adapter are adjacent to the first circuit board and the second circuit board, respectively.
  • a standard interface is disposed on the adapter, and the standard interface is used for electrical connection with the power supply device.
  • the at least two functional modules further include a third circuit board disposed on the mounting bracket and spaced apart from the second circuit board and the first circuit board, respectively.
  • the third circuit board is electrically connected to the energy supply device.
  • the third circuit board is stacked on an outer peripheral surface of the mounting frame, and three sides of the third circuit board are adjacent to the first circuit board, the second circuit board, and the Adapter.
  • the power component further includes a controller disposed on a side of the third circuit board facing away from the mounting frame, and the controller is electrically connected to the power supply device.
  • two ends of the controller respectively extend from opposite ends of the third circuit board, and are respectively electrically connected to the power supply device.
  • controller is a flight controller or a travel controller.
  • the power supply assembly further includes a controller connected to the mounting bracket, and the controller is a flight controller or a travel controller.
  • the remote control mobile device is an unmanned vehicle or an unmanned ship.
  • a power supply assembly includes a polyhedral mounting bracket, an energizing device, and at least two functional modules, the at least two functional modules being disposed separately from each other on different sides of the mounting bracket and electrically connected to each other;
  • the energy device is disposed on the mounting frame, and the at least two functional modules are respectively electrically connected to the power supply device.
  • the at least two functional modules are respectively boards for performing different functions.
  • the at least two functional modules are at least one of the following: a speed sensing module, a gravity sensing module, a visual sensing module, a magnetic field sensing module, and a control module.
  • the at least two functional modules include a first circuit board and a second circuit board, and the first circuit board and the second circuit board are respectively disposed on opposite sides of the mounting frame.
  • the energy supply device is disposed in the mounting frame, and the first circuit board and the second circuit board are respectively stacked on outer peripheral surfaces of opposite sides of the mounting frame.
  • the power supply assembly further includes an adapter disposed at one end of the mounting bracket and electrically connected to the power supply device.
  • the adapter is stacked on an outer circumferential surface of the mounting frame, and opposite sides of the adapter are adjacent to the first circuit board and the second circuit board, respectively.
  • a standard interface is disposed on the adapter, and the standard interface is used for electrical connection with the power supply device.
  • the at least two functional modules further include a third circuit board disposed on the mounting bracket and spaced apart from the second circuit board and the first circuit board, respectively.
  • the third circuit board is electrically connected to the energy supply device.
  • the third circuit board is stacked on an outer peripheral surface of the mounting frame, and three sides of the third circuit board are adjacent to the first circuit board, the second circuit board, and the Adapter.
  • the power component further includes a controller disposed on a side of the third circuit board facing away from the mounting frame, and the controller is electrically connected to the power supply device.
  • two ends of the controller respectively extend from opposite ends of the third circuit board, and are respectively electrically connected to the power supply device.
  • controller is a flight controller or a travel controller.
  • the power supply assembly further includes a controller connected to the mounting bracket, and the controller is a flight controller or a travel controller.
  • a plurality of the functional modules are disposed separately from each other on different sides of the mounting frame, so that installation and debugging of the plurality of functional modules can be separated from each other, which facilitates debugging and maintenance of the power component.
  • the disassembly and assembly of the power component is more convenient.
  • the layout of the power supply component is more rationalized, the overall volume of the remote control mobile device is reduced, and the assembly, disassembly or maintenance of the power supply component in the remote control mobile device is more convenient.
  • FIG. 1 is a schematic perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 2 is a partially exploded perspective view of the unmanned aerial vehicle of FIG. 1.
  • FIG. 3 is a perspective exploded view of the unmanned aerial vehicle of FIG. 1.
  • Unmanned aerial vehicle 1 body 100 Upper shell assembly 20 Upper shell twenty one Mount twenty three First installation 231 Second installation 233 Third installation department 235 Fourth installation department 237 Containing space 239 Energy supply device 25 functional module 27 First board 271 Second circuit board 273 Third circuit board 275 Controller 28 Adapter 29 interface 291 Lower shell assembly 40 Lower case 41 First housing 411 Mounting port 4111 Second housing 413 Containment chamber 42 Control 43 First control 431 Second control 433 Heat sink 45 landing gear 60 powerplant 300 Motor 310 PTZ camera 400 Yuntai 410 Image acquisition device 430
  • a component when referred to as being “fixed” to another component, it can be directly on the other component or the component can be present.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a component When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • the terms “vertical,” “horizontal,” “left,” “right,” and the like, as used herein, are for illustrative purposes only.
  • an embodiment of the present invention provides a remote control mobile device, which may be, but is not limited to, an unmanned aerial vehicle, an unmanned vehicle, an unmanned vehicle, etc., in this embodiment,
  • the remote mobile device is described by taking the unmanned aerial vehicle 1 as an example.
  • the UAV 1 includes a fuselage 100 and a power unit 300 disposed on the body 100 and configured to provide flight power to the UAV 1 .
  • the unmanned aerial vehicle 1 is used to mount a pan-tilt camera 400 to perform a photographing operation, and the pan-tilt camera 400 may include a pan-tilt head 410 and an image acquiring device 430 disposed on the pan-tilt head 410.
  • the body 100 includes an upper casing assembly 20, a lower casing assembly 40, and a landing gear 60.
  • the upper casing assembly 20 and the lower casing assembly 40 are fastened to each other to form a casing of the UAV 1
  • the landing gear 60 is disposed on the lower casing assembly 40 . And used as a support for the UAV 1 when landing.
  • the lower case assembly 40 includes a lower case 41, a control member 43 and a heat sink 45.
  • the control member 43 and the heat sink 45 are disposed on the lower casing 41 and located between the lower casing 41 and the upper casing assembly 20.
  • the lower case 41 has a substantially concave housing shape, and a receiving cavity 42 is formed thereon.
  • the lower case 41 is configured to receive the components of the UAV 1 in cooperation with the upper case assembly 20.
  • the lower case 41 includes a first housing 411 and a second housing 413 connected to the first housing 411.
  • a mounting portion 4111 is defined in a substantially central portion of the first housing 411, and the mounting opening 4111 is in communication with the receiving cavity 42.
  • the second housing 413 is disposed on the mounting opening 4111 and closes the mounting opening 4111. By disassembling and mounting the second housing 413, the mounting opening 4111 can be conveniently opened or closed, so that the user can conveniently view or maintain the components inside the body 100.
  • the second housing 413 is also used to mount the pan-tilt camera 400.
  • the pan/tilt head 410 is disposed on a side of the second casing 413 facing away from the receiving cavity 42
  • the image acquiring device 430 is disposed on the pan/tilt head 410 . It can be understood that the pan/tilt head 410 can be omitted, and the image acquiring device 430 is directly connected to the second casing 413.
  • the control member 43 is disposed on a side of the second housing 413 facing the receiving cavity 42.
  • the control unit 43 is electrically connected to the pan-tilt camera 400 and is used to control the movement of the pan-tilt camera 400 to adjust the image acquisition device 430 to a desired angle for shooting.
  • the control member 43 is a control circuit board, and the number thereof is two.
  • the two control members 43 are respectively a first control member 431 and a second control member 433.
  • the first control member 431 is fixedly stacked on the second housing 413, and the second control member 433 is stacked.
  • the grounding member 431 is disposed on the first control member 431.
  • control members 43 may be one, three, four or more.
  • the control member 43 is directly mounted on the second casing 413 of the lower casing 41 without additionally providing a mounting bracket dedicated to the control member 43 to simplify the internal structure of the fuselage 100 and remaining The space is relatively large and the overall weight of the fuselage 100 is relatively light.
  • the heat sink 45 is disposed on one side of the control member 43 and is fixed to the second housing 413.
  • the heat dissipating member 45 is a heat dissipating fan for promoting air circulation inside the casing of the UAV 1 to prevent the UAV 1 from overheating during operation.
  • the landing gear 60 is disposed on the first casing 411 and located on a side of the first casing 411 facing away from the receiving cavity 42.
  • the number of the landing gears 60 is two, and the two landing gears 60 are spaced apart from each other.
  • the landing gear 60 is a stationary landing gear. It can be understood that in other embodiments, the landing gear 60 can also be a retractable landing gear, and is not limited to the embodiment.
  • the upper casing assembly 20 is disposed on the first casing 411 and located on a side of the first casing 411 facing away from the landing gear 60.
  • the upper casing assembly 20 includes an upper casing 21, a mounting bracket 23, an energizing device 25, a functional module 27, and a controller 28.
  • the mounting bracket 23 is disposed between the upper casing 21 and the first casing 411, the energy supply device 25, the functional module 27, and the controller 28 Both are connected within the mounting bracket 23.
  • the upper casing 21 is substantially in the shape of a casing, and is disposed on the lower casing 41 and is configured to cooperate with the lower casing 41 to receive components of the UAV 1 .
  • the mounting bracket 23 is disposed between the upper casing 21 and the lower casing 41 and is connected to the upper casing 21, and the mounting bracket 23 is disposed corresponding to the control member 43.
  • the mounting bracket 23 is used to mount the energy supply device 25 and the function module 27.
  • the mounting bracket 23 is a polyhedral mounting bracket.
  • the mounting frame 23 has a rectangular frame shape, which is a hollow structure.
  • the mounting bracket 23 is provided with a plurality of mounting portions, and the plurality of mounting portions include, but are not limited to, a first mounting portion 231 , a second mounting portion 233 , a third mounting portion 235 , and a fourth mounting portion 237 .
  • the first mounting portion 231 and the second mounting portion 233 are spaced apart from each other and substantially parallel to each other.
  • the third mounting portion 235 is disposed on a side of the first mounting portion 231 and the second mounting portion 233 adjacent to the lower case 41, and opposite sides of the third mounting portion 235 are respectively
  • the first mounting portion 231 and the second mounting portion 233 are connected to each other.
  • the fourth mounting portion 237 is disposed on a side of the third mounting portion 235 adjacent to the upper casing 21, and the three sides of the fourth mounting portion 237 are respectively associated with the first mounting portion 231
  • the second mounting portion 233 and the third mounting portion 235 are connected to each other.
  • the connection between the first mounting portion 231, the second mounting portion 233, the third mounting portion 235, and the fourth mounting portion 237 is such that the mounting frame 23 has a drawer shape and four
  • the mounting portions collectively form a receiving space (not shown) for accommodating the energy supply device 25.
  • the energy supply device 25 is a battery assembly.
  • the energizing device 25 is disposed in the receiving space of the mounting bracket 23.
  • the plurality of functional modules 27 are plural, and a plurality of the functional modules 27 are disposed apart from each other on the outer circumference of the mounting bracket 23.
  • a plurality of the functional modules 27 are electrically connected to the power supply device 25, and a plurality of the functional modules 27 are electrically connected to each other.
  • the function module 27 is a circuit board, and the number thereof is three, and the three function modules 27 are respectively a first circuit board 271, a second circuit board 273, and a third circuit board 275.
  • the first circuit board 271, the second circuit board 273, and the third circuit board 275 are respectively mounted on the first mounting portion 231, the second mounting portion 233, and the third mounting portion 235.
  • the first circuit board 271 and the second circuit board 273 are stacked on the outer peripheral surfaces of opposite sides of the mounting frame 23, respectively.
  • the third circuit board 275 is disposed on the mounting frame 23 and spaced apart from the first circuit board 271 and the second circuit board 273, respectively. The opposite sides of the third circuit board 275 are adjacent to the first circuit board 271 and the second circuit board 273, respectively.
  • a plurality of the function modules 27 are respectively boards for performing different functions. It can be understood that, in other implementations, the function module 27 may be two, three, five, seven or more; and the function module 27 may also be any two or more of the following two or more Combination of functional modules: speed sensing module, gravity sensing module, visual sensing module, magnetic field sensing module, control module.
  • the controller 28 is disposed on a side of the third circuit board 275 facing away from the mounting bracket 23 and is fixedly coupled to the mounting bracket 23.
  • the length of the controller 28 is greater than the length of the third circuit board 275.
  • the two ends of the controller 28 are respectively extended from opposite ends of the third circuit board 275 and electrically connected to the power supply device 25 respectively.
  • the controller 28 is a flight controller for controlling the UAV 1 to perform a flight mission.
  • the upper casing assembly 20 further includes an adapter 29 disposed at one end of the mounting bracket 23.
  • the adapter 29 is used for electrical connection with the energy supply device 25 .
  • the adapter 29 is stacked on the fourth mounting portion 237 and located outside the mounting bracket 23.
  • the adapter 29 is provided with an interface 291 for electrically connecting to the energy supply device 25.
  • the interface 291 is a standard data interface for transmitting power or/and transmitting data.
  • the opposite sides of the adapter 29 are adjacent to the first circuit board 271 and the second circuit board 273, respectively.
  • the power unit 300 is disposed on the body 100.
  • the power unit 300 is a rotor assembly.
  • the UAV 1 is a quadrotor, ie an aircraft having four rotor assemblies.
  • the power unit 300 includes a motor 310 and a propeller (not shown) coupled to the motor 310.
  • the propeller of the power unit 300 is not shown, but does not mean that the power unit 300 can dispense with the propeller.
  • the motor 310 is capable of driving the propeller to rotate to provide the unmanned aerial vehicle 1 with the power to fly.
  • the UAV 1 can also be a six-rotor aircraft, an eight-rotor aircraft, a twelve-rotor aircraft, etc., and even the UAV 1 can be a single-rotor aircraft; in addition, in other embodiments, The UAV 1 can be a fixed wing aircraft or a fixed wing-rotor hybrid aircraft.
  • the mounting bracket 23, the energizing device 25 and the functional module 27 provided by the embodiments of the present invention together constitute a power component of the UAV 1 .
  • the mounting bracket 23 is a polyhedral mounting bracket, and a plurality of the functional modules 27 are disposed on different sides of the mounting bracket 23 separately from each other to install and debug a plurality of the functional modules 27 The separation from each other facilitates the debugging and maintenance of the power component, and also facilitates the disassembly and assembly of the power component.
  • the above-mentioned separation function module 27 is arranged in such a manner that the inner cavity space of the body 100 is utilized reasonably, so that the structure of the power supply component is relatively more compact, and the inner cavity of the body 100 is simultaneously More remaining space is reserved, which provides an effective channel for the flow of air, which is beneficial to the heat dissipation of the unmanned aerial vehicle 1.
  • the power module is detachably mounted in the upper casing 21 to form the upper casing assembly 20, and the control member 43 and the heat dissipation member 45 are mounted on the lower casing 41 to form the lower portion.
  • the shell assembly 40 makes the structure of the UAV 1 more compact, facilitating modular assembly and disassembly and assembly of the UAV 1 .
  • the UAV 1 is configured such that the controller, the power supply device, and the plurality of functional modules are respectively designed as independent modules, and are mounted on the mounting frame to make the power component
  • the layout is more rationalized, the overall volume of the UAV 1 is reduced, and the assembly, disassembly or maintenance of the power components in the UAV 1 is more convenient.
  • the structure of the mounting bracket 23 is not limited to the rectangular frame structure described above, but may be other polyhedral structures.
  • the mounting bracket 23 may be a tetrahedral mounting structure, a hexahedral mounting structure, an octahedron mounting structure, or the like, and a plurality of the functional modules 27 are disposed separately from each other on different sides of the mounting bracket 23.
  • the UAV 1 can be applied to other fields than aerial photography, such as map mapping, disaster inspection, spraying pesticides, etc. Accordingly, the load on the UAV 1 can be in addition to the above-described PTZ camera 400. Other loads than detectors, spray equipment, etc.
  • the remote mobile device may be a mobile device other than an unmanned aerial vehicle.
  • the remote control mobile device may be an unmanned vehicle.
  • the controller 28 is a travel controller
  • the energy supply device 25 may be a battery assembly or a fuel assembly
  • the power device 300 is a wheel assembly.
  • the remote mobile device may be an unmanned ship, an unmanned submarine, or the like.

Abstract

一种电源组件、无人飞行器（1）及遥控移动装置无人飞行器，所述无人飞行器（1）包括机身（100）以及设置于所述机身（100）上的电源组件，所述电源组件包括多面体状安装架（23）、供能装置（25）以及至少两个功能模块（27），所述安装架（23）设置在所述机身（100）上，所述至少两个功能模块（27）彼此分离地设置于所述安装架（23）的不同侧面，并相互电性连接，所述供能装置（25）设置于所述安装架（23）上，所述至少两个功能模块（27）分别与所述供能装置（25）电性连接。

Description

电源组件、无人飞行器及遥控移动装置 技术领域
本发明涉及一种电源组件及使用该电源组件的无人飞行器和遥控移动装置。
背景技术
遥控移动装置，例如无人飞行器或者无人驾驶车辆等，一般包括主机安装结构以及分别连接于所述主机安装结构上的控制装置、供能装置和动力装置。用户通过遥控器等控制设备遥控所述控制装置，使所述控制装置控制所述动力装置带动所述遥控移动装置整体行进。所述供能装置用于为所述动力装置提供能量来源。由于所述遥控移动装置的小型化设计需要，上述的主机安装结构通常为：将尽量多的功能模块集成于一个电路板上，并将所述电路板设置于所述遥控移动装置的机壳内。然而，由于所述电路板上集成有所有的功能模块，使上述的主机安装结构的组装、拆卸或维修不便利。
发明内容
鉴于以上内容，有必要提供一种体积相对较小且拆装便利的遥控移动装置及其电源组件。
一种无人飞行器，其包括机身以及设置于所述机身上的电源组件。所述电源组件包括多面体状安装架、供能装置以及至少两个功能模块，所述安装架设置在所述机身上，所述至少两个功能模块彼此分离地设置于所述安装架的不同侧面，并相互电性连接。所述供能装置设置于所述安装架上，所述至少两个功能模块分别与所述供能装置电性连接。
进一步地，所述机身为机壳，所述电源组件收容在所述机壳内。
进一步地，所述机身包括相互扣合的上壳及下壳，所述电源组件设置在所述上壳及所述下壳之间。
进一步地，所述电源组件固定设置于所述上壳上，以与所述上壳形成上壳组件。
进一步地，所述无人飞行器还包括至少一个控制件，所述至少一个控制件固定于所述下壳上，并对应于所述安装架。
进一步地，所述至少一个控制件包括固定地叠置于所述下壳上的第一控制件，所述第一控制件为电路板。
进一步地，所述至少一个控制件还包括第二控制件，所述第二控制件叠置于所述第一控制件上，所述第二控制件为电路板。
进一步地，所述至少一个控制件与搭载在所述无人飞行器上的负载电性连接，并用于控制所述负载工作。
进一步地，所述无人飞行器还包括散热件，所述散热件邻近所述控制件设置于所述下壳上。
进一步地，所述至少一个控制件、所述散热件分别地固定于所述下壳上，以与所述下壳形成下壳组件。
进一步地，所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合连接，所述第二壳体可拆卸地装设于所述第一壳体上。
进一步地，所述至少一个控制件、所述散热件分别地固定于所述第二壳体上，以便于所述至少一个控制件及所述散热件的集成组装。
进一步地，所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
进一步地，所述散热件为散热风扇。
进一步地，所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合，所述第二壳体可拆卸地装设于所述第一壳体上。
进一步地，所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
进一步地，所述无人飞行器上设置有图像获取装置，所述图像获取装置连接于所述机身的所述第二壳体上。
进一步地，所述无人飞行器还包括云台，所述云台能够调节地设置于所述第二壳体上，所述图像获取装置设置于所述云台上。
进一步地，所述无人飞行器还包括起落架，所述起落架设置于所述机身的所述第一壳体上，并朝远离所述机身的方向延伸。
进一步地，所述无人飞行器还包括设置于所述机身上的电机以及设置于所述电机上的螺旋桨。
进一步地，所述至少两个功能模块分别为用于执行不同功能的电路板。
进一步地，所述至少两个功能模块为以下几种中的至少一种：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
进一步地，所述至少两个功能模块包括第一电路板及第二电路板，所述第一电路板及所述第二电路板分别设置在所述安装架的相对两侧。
进一步地，所述供能装置设置在所述安装架内，所述第一电路板及所述第二电路板分别叠置在所述安装架的相对两侧的外周表面上。
进一步地，所述电源组件还包括转接件，所述转接件设置在所述安装架的一端，并与所述供能装置电性连接。
进一步地，所述转接件叠置在所述安装架的外周表面上，且所述转接件的相对两个侧边分别邻近所述第一电路板及所述第二电路板。
进一步地，所述转接件上设置有标准接口，所述标准接口用于与所述供能装置电性连接。
进一步地，所述至少两个功能模块还包括第三电路板，所述第三电路板设置在所述安装架上并分别与所述第二电路板及所述第一电路板彼此间隔，所述第三电路板与所述供能装置电性连接。
进一步地，所述第三电路板叠置在所述安装架的外周表面上，且所述第三电路板的三个侧边分别邻近所述第一电路板、所述第二电路板以及所述转接件。
进一步地，所述电源组件还包括控制器，所述控制器设置于所述第三电路板的背离所述安装架的一侧，所述控制器与所述供能装置电性连接。
进一步地，所述控制器的两端分别相对所述第三电路板的对应两端延伸出，并分别与所述供能装置电性连接。
进一步地，所述控制器为飞行控制器或者行驶控制器。
进一步地，所述电源组件还包括连接于所述安装架上的控制器，所述控制器为飞行控制器或者行驶控制器。
一种遥控移动装置，其包括机身以及设置于所述机身上的电源组件。所述电源组件包括多面体状安装架、供能装置以及至少两个功能模块，所述安装架设置在所述机身上，所述至少两个功能模块彼此分离地设置于所述安装架的不同侧面，并相互电性连接。所述供能装置设置于所述安装架上，所述至少两个功能模块分别与所述供能装置电性连接。
进一步地，所述机身为机壳，所述电源组件收容在所述机壳内。
进一步地，所述机身包括相互扣合的上壳及下壳，所述电源组件设置在所述上壳及所述下壳之间。
进一步地，所述电源组件固定设置于所述上壳上，以与所述上壳形成上壳组件。
进一步地，所述无人飞行器还包括至少一个控制件，所述至少一个控制件固定于所述下壳上，并对应于所述安装架。
进一步地，所述至少一个控制件包括固定地叠置于所述下壳上的第一控制件，所述第一控制件为电路板。
进一步地，所述至少一个控制件还包括第二控制件，所述第二控制件叠置于所述第一控制件上，所述第二控制件为电路板。
进一步地，所述至少一个控制件与搭载在所述无人飞行器上的负载电性连接，并用于控制所述负载工作。
进一步地，所述无人飞行器还包括散热件，所述散热件邻近所述控制件设置于所述下壳上。
进一步地，所述至少一个控制件、所述散热件分别地固定于所述下壳上，以与所述下壳形成下壳组件。
进一步地，所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合连接，所述第二壳体可拆卸地装设于所述第一壳体上。
进一步地，所述至少一个控制件、所述散热件分别地固定于所述第二壳体上，以便于所述至少一个控制件及所述散热件的集成组装。
进一步地，所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
进一步地，所述散热件为散热风扇。
进一步地，所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合，所述第二壳体可拆卸地装设于所述第一壳体上。
进一步地，所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
进一步地，所述无人飞行器上设置有图像获取装置，所述图像获取装置连接于所述机身的所述第二壳体上。
进一步地，所述无人飞行器还包括云台，所述云台能够调节地设置于所述第二壳体上，所述图像获取装置设置于所述云台上。
进一步地，所述无人飞行器还包括起落架，所述起落架设置于所述机身的所述第一壳体上，并朝远离所述机身的方向延伸。
进一步地，所述无人飞行器还包括设置于所述机身上的电机以及设置于所述电机上的螺旋桨。
进一步地，所述至少两个功能模块分别为用于执行不同功能的电路板。
进一步地，所述至少两个功能模块为以下几种中的至少一种：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
进一步地，所述至少两个功能模块包括第一电路板及第二电路板，所述第一电路板及所述第二电路板分别设置在所述安装架的相对两侧。
进一步地，所述供能装置设置在所述安装架内，所述第一电路板及所述第二电路板分别叠置在所述安装架的相对两侧的外周表面上。
进一步地，所述电源组件还包括转接件，所述转接件设置在所述安装架的一端，并与所述供能装置电性连接。
进一步地，所述转接件叠置在所述安装架的外周表面上，且所述转接件的相对两个侧边分别邻近所述第一电路板及所述第二电路板。
进一步地，所述转接件上设置有标准接口，所述标准接口用于与所述供能装置电性连接。
进一步地，所述至少两个功能模块还包括第三电路板，所述第三电路板设置在所述安装架上并分别与所述第二电路板及所述第一电路板彼此间隔，所述第三电路板与所述供能装置电性连接。
进一步地，所述第三电路板叠置在所述安装架的外周表面上，且所述第三电路板的三个侧边分别邻近所述第一电路板、所述第二电路板以及所述转接件。
进一步地，所述电源组件还包括控制器，所述控制器设置于所述第三电路板的背离所述安装架的一侧，所述控制器与所述供能装置电性连接。
进一步地，所述控制器的两端分别相对所述第三电路板的对应两端延伸出，并分别与所述供能装置电性连接。
进一步地，所述控制器为飞行控制器或者行驶控制器。
进一步地，所述电源组件还包括连接于所述安装架上的控制器，所述控制器为飞行控制器或者行驶控制器。
进一步地，所述遥控移动装置为无人驾驶车辆或无人驾驶船舶。
一种电源组件，包括多面体状安装架、供能装置以及至少两个功能模块，所述至少两个功能模块彼此分离地设置于所述安装架的不同侧面，并相互电性连接；所述供能装置设置于所述安装架上，所述至少两个功能模块分别与所述供能装置电性连接。
进一步地，所述至少两个功能模块分别为用于执行不同功能的电路板。
进一步地，所述至少两个功能模块为以下几种中的至少一种：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
进一步地，所述至少两个功能模块包括第一电路板及第二电路板，所述第一电路板及所述第二电路板分别设置在所述安装架的相对两侧。
进一步地，所述供能装置设置在所述安装架内，所述第一电路板及所述第二电路板分别叠置在所述安装架的相对两侧的外周表面上。
进一步地，所述电源组件还包括转接件，所述转接件设置在所述安装架的一端，并与所述供能装置电性连接。
进一步地，所述转接件叠置在所述安装架的外周表面上，且所述转接件的相对两个侧边分别邻近所述第一电路板及所述第二电路板。
进一步地，所述转接件上设置有标准接口，所述标准接口用于与所述供能装置电性连接。
进一步地，所述至少两个功能模块还包括第三电路板，所述第三电路板设置在所述安装架上并分别与所述第二电路板及所述第一电路板彼此间隔，所述第三电路板与所述供能装置电性连接。
进一步地，所述第三电路板叠置在所述安装架的外周表面上，且所述第三电路板的三个侧边分别邻近所述第一电路板、所述第二电路板以及所述转接件。
进一步地，所述电源组件还包括控制器，所述控制器设置于所述第三电路板的背离所述安装架的一侧，所述控制器与所述供能装置电性连接。
进一步地，所述控制器的两端分别相对所述第三电路板的对应两端延伸出，并分别与所述供能装置电性连接。
进一步地，所述控制器为飞行控制器或者行驶控制器。
进一步地，所述电源组件还包括连接于所述安装架上的控制器，所述控制器为飞行控制器或者行驶控制器。
综上所述，多个所述功能模块彼此分离地设置在所述安装架的不同侧面，使多个所述功能模块的安装与调试能够彼此分离进行，有利于所述电源组件的调试和维修，也使得所述电源组件的拆装更为方便。同时，电源组件的布局更为合理化，减小了所述遥控移动装置整体积，使所述遥控移动装置内电源组件的组装、拆卸或维修更为方便。
 附图说明
图1为本发明实施方式提供的无人飞行器的立体示意图。
图2为图1所示无人飞行器的部分结构分解示意图。
图3为图1所示无人飞行器的立体分解示意图。
主要元件符号说明
无人飞行器 1
机身 100
上壳组件 20
上壳 21
安装架 23
第一安装部 231
第二安装部 233
第三安装部 235
第四安装部 237
收容空间 239
供能装置 25
功能模块 27
第一电路板 271
第二电路板 273
第三电路板 275
控制器 28
转接件 29
接口 291
下壳组件 40
下壳 41
第一壳体 411
安装口 4111
第二壳体 413
收容腔 42
控制件 43
第一控制件 431
第二控制件 433
散热件 45
起落架 60
动力装置 300
电机 310
云台相机 400
云台 410
图像获取装置 430
如下具体实施方式将结合上述附图进一步说明本发明。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
需要说明的是，当组件被称为“固定于”另一个组件，它可以直接在另一个组件上或者也可以存在居中的组件。当一个组件被认为是“连接”另一个组件，它可以是直接连接到另一个组件或者可能同时存在居中组件。当一个组件被认为是“设置于”另一个组件，它可以是直接设置在另一个组件上或者可能同时存在居中组件。本文所使用的术语“垂直的”、“水平的”、“左”、“右”以及类似的表述只是为了说明的目的。
除非另有定义，本文所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本文中在本发明的说明书中所使用的术语只是为了描述具体的实施例的目的，不是旨在于限制本发明。本文所使用的术语“及／或”包括一个或多个相关的所列项目的任意的和所有的组合。
下面结合附图，对本发明的一些实施方式作详细说明。在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
请参阅图1及图2，本发明实施方式提供一种遥控移动装置，所述遥控移动装置可以为但并不限于为无人飞行器、无人车或无人船等，本实施例中，所述遥控移动装置以无人飞行器1为例。所述无人飞行器1包括机身100以及动力装置300，所述动力装置300设置于所述机身100上，并用于为所述无人飞行器1提供飞行的动力。在本实施方式中，所述无人飞行器1用于搭载云台相机400进行拍摄作业，所述云台相机400可以包括云台410以及设置于所述云台410上的图像获取装置430。
所述机身100包括上壳组件20、下壳组件40以及起落架60。具体在图示的实施方式中，所述上壳组件20及所述下壳组件40相互扣合以形成所述无人飞行器1的机壳，所述起落架60设置在所述下壳组件40上，并用作所述无人飞行器1降落时的支撑。
请同时参阅图3，所述下壳组件40包括下壳41、控制件43以及散热件45。具体在图示的实施例中，所述控制件43及所述散热件45均设置在所述下壳41上，并位于所述下壳41与所述上壳组件20之间。
所述下壳41大致呈凹陷的壳体状，其上形成收容腔42。所述下壳41用于与所述上壳组件20相配合收容所述无人飞行器1的零部件。在本实施方式中，所述下壳41包括第一壳体411以及与所述第一壳体411相连接的第二壳体413。所述第一壳体411的大致中部位置开设有安装口4111，所述安装口4111与所述收容腔42相连通。所述第二壳体413设置在所述安装口4111上，并封闭所述安装口4111。通过拆卸及安装所述第二壳体413，可以方便地开启或关闭所述安装口4111，使用户能够方便地查看或维护所述机身100内部的零部件。
在本实施方式中，所述第二壳体413还用于装设所述云台相机400。具体而言，所述云台410设置在所述第二壳体413背离所述收容腔42的一侧，所述图像获取装置430设置在所述云台410上。可以理解，所述云台410可以省略，而直接将所述图像获取装置430连接在所述第二壳体413上。
所述控制件43设置在所述第二壳体413上朝向所述收容腔42的一侧。所述控制件43与所述云台相机400电性连接，并用于控制所述云台相机400运动，以将所述图像获取装置430调整至拍摄所需角度。在本实施方式中，所述控制件43为控制电路板，其数量为两个。两个所述控制件43分别为第一控制件431以及第二控制件433，所述第一控制件431固定地叠置于所述第二壳体413上，所述第二控制件433层叠地设置于所述第一控制件431上。
可以理解，在其他的实施方式中，所述控制件43可以为一个、三个、四个或多个。所述控制件43直接装设在所述下壳41的所述第二壳体413上，而无需额外设置专用于所述控制件43的安装架，使所述机身100内部结构简化、剩余空间相对较大，且使所述机身100的整体重量相对较轻。
所述散热件45设置在所述控制件43的一侧，并固定于所述第二壳体413上。在本实施方式中，所述散热件45为散热风扇，其用于促进所述无人飞行器1的机壳内部的空气流通，以防止所述无人飞行器1在运行时过热。
所述起落架60设置在所述第一壳体411上，并位于所述第一壳体411背离所述收容腔42的一侧。在本实施方式中，所述起落架60的数量为两个，两个所述起落架60彼此间隔地设置。具体在图示的实施例中，所述起落架60为固定式起落架。可以理解，在其他的实施方式中，所述起落架60还可以为可收放式起落架，并不局限于本实施方式。
所述上壳组件20设置于所述第一壳体411上，并位于所述第一壳体411背离所述起落架60的一侧。所述上壳组件20包括上壳21、安装架23、供能装置25、功能模块27以及控制器28。具体在图示的实施例中，所述安装架23设置在所述上壳21及所述第一壳体411之间，所述供能装置25、所述功能模块27及所述控制器28均连接在所述安装架23内。
所述上壳21大致呈壳体状，其盖设于所述下壳41上，并用于与所述下壳41相配合以收容所述无人飞行器1的零部件。
所述安装架23设置在所述上壳21与所述下壳41之间，并与所述上壳21相连接，且所述安装架23与所述控制件43相对应设置。所述安装架23用于装设所述供能装置25及所述功能模块27。在本实施方式中，所述安装架23为多面体安装架。具体而言，所述安装架23为矩形的框体状，其为镂空结构。
所述安装架23上设置有多个安装部，多个所述安装部包括但不限于第一安装部231、第二安装部233、第三安装部235以及第四安装部237。具体在图示的实施例中，所述第一安装部231与所述第二安装部233彼此间隔设置，且大致相互平行。所述第三安装部235设置在所述第一安装部231及所述第二安装部233靠近所述下壳41的一侧，且所述第三安装部235的相对两个侧边分别与所述第一安装部231及所述第二安装部233相连接。所述第四安装部237设置在所述第三安装部235靠近所述上壳21的一侧，且所述第四安装部237的三个侧边分别与所述第一安装部231、所述第二安装部233及所述第三安装部235相连接。所述第一安装部231、所述第二安装部233、所述第三安装部235及所述第四安装部237的连接设置使所述安装架23呈屉形的结构，且四个所述安装部共同形成一个收容空间（图未标出），所述收容空间用于收容所述供能装置25。
在本实施方式中，所述供能装置25为电池组件。所述供能装置25设置在所述安装架23的所述收容空间内。
所述功能模块27为多个，多个所述功能模块27彼此分离地设置在所述安装架23的外周。多个所述功能模块27分别与所述供能装置25电性连接，且多个所述功能模块27之间相互电性连接。具体在本实施方式中，所述功能模块27为电路板，其数量为三个，三个所述功能模块27分别为：第一电路板271、第二电路板273以及第三电路板275。第一电路板271、所述第二电路板273及所述第三电路板275分别装设在所述第一安装部231、所述第二安装部233及所述第三安装部235上。具体在图示的实施方式中，所述第一电路板271及所述第二电路板273分别层叠地设置在所述安装架23的相对两侧的外周表面上。所述第三电路板275设置在所述安装架23上，并分别与所述第一电路板271及所述第二电路板273彼此间隔。所述第三电路板275的相对侧边分别邻近所述第一电路板271及所述第二电路板273。
进一步地，多个所述功能模块27分别为用于执行不同功能的电路板。可以理解，在其他的实施方式中，所述功能模块27可以为两个、三个、五个、七个或更多；且所述功能模块27还可以为以下任两种或两种以上的功能模块的组合：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
所述控制器28设置在所述第三电路板275背离所述安装架23的一侧，并与所述安装架23固定连接。具体在图示的实施方式中，所述控制器28的长度大于所述第三电路板275的长度。所述控制器28的两端分别相对所述第三电路板275的对应两端延伸出，并分别与所述供能装置25电性连接。在本实施方式中，所述控制器28为飞行控制器，其用于控制所述无人飞行器1执行飞行任务。
所述上壳组件20进一步地包括转接件29，所述转接件29设置于所述安装架23的一端。所述转接件29用于与所述供能装置25电性连接。具体而言，所述转接件29叠置在所述第四安装部237上，并位于所述安装架23的外侧。所述转接件29上设置有接口291，所述接口291用于与所述供能装置25电性连接。在本实施方式中，所述接口291为标准数据接口，其用于传输电力或/及传输数据。所述转接件29上的相对两个侧边分别邻近所述第一电路板271及所述第二电路板273。
所述动力装置300设置在所述机身100上。在本实施方式中，所述动力装置300为旋翼组件。具体在图示的实施例中，所述无人飞行器1为四旋翼飞行器，即具有四个旋翼组件的飞行器。所述动力装置300包括电机310以及与所述电机310相连的螺旋桨（图未示出）。具体在图示的实施方式中，所述动力装置300的螺旋桨并未示出，但并不表示所述动力装置300可以省去所述螺旋桨。所述电机310能够驱动所述螺旋桨转动，以为所述无人飞行器1提供飞行的动力。可以理解，所述无人飞行器1也可以为六旋翼飞行器、八旋翼飞行器、十二旋翼飞行器等，甚至，所述无人飞行器1可以为单旋翼飞行器；另外，在其他实施方式中，所述无人飞行器1可以为固定翼飞行器，或者固定翼-旋翼混合的飞行器。
本发明实施例提供的所述安装架23、所述供能装置25以及所述功能模块27，共同构成所述无人飞行器1的电源组件。在所述电源组件中，所述安装架23为多面体安装架，多个所述功能模块27彼此分离地设置在所述安装架23的不同侧面，使多个所述功能模块27的安装与调试能够彼此分离进行，有利于所述电源组件的调试和维修，也使得所述电源组件的拆装更为方便。同时，上述的分离式的功能模块27的设置方式，合理利用了所述机身100的内腔空间，使所述电源组件的结构相对更为紧凑的同时，为所述机身100的内腔预留了较多的剩余空间，为空气的流动提供了有效通道，有利于所述无人飞行器1的散热。
另外，所述电源组件可拆卸地装设于所述上壳21内组成所述上壳组件20，所述控制件43及所述散热件45装设于所述下壳41上组成所述下壳组件40，使所述无人飞行器1的结构更为紧凑，便于所述无人飞行器1的模块化组装以及拆装调试。
综上所述，所述无人飞行器1将所述控制器、所述供能装置及多个所述功能模块分别设计为相互独立的模块安装于所述安装架上，使所述电源组件的布局更为合理化，减小了所述无人飞行器1整体体积，使所述无人飞行器1内电源组件的组装、拆卸或维修更为方便。
可以理解，所述安装架23的结构不局限于上文所描述的矩形框架结构，其还可以为其他的多面体结构。例如，所述安装架23可以为四面体安装结构、六面体安装结构、八面体安装结构等，并将多个所述功能模块27彼此分离地设置在所述安装架23的不同侧面。
可以理解，所述无人飞行器1可以应用于航拍以外的其他领域，例如地图测绘、灾情巡查、喷洒农药等，相应地，所述无人飞行器1上的负载可以为除了上述的云台相机400以外的其他负载，如探测器、喷洒设备等。
可以理解，所述遥控移动装置可以为除无人飞行器以外的移动装置。例如，所述遥控移动装置可以为无人驾驶车辆，此时，控制器28为行驶控制器，供能装置25可以为电池组件或者燃料组件等，动力装置300为车轮组件。或者，所述遥控移动装置可以为无人驾驶船舶、无人驾驶潜艇等。
以上实施方式仅用以说明本发明的技术方案而非限制，尽管参照以上实施方式对本发明进行了详细说明，本领域的普通技术人员应当理解，可以对本发明的技术方案进行修改或等同替换都不应脱离本发明技术方案的精神和范围。

Claims (81)

  1. 一种无人飞行器，其包括机身以及设置于所述机身上的电源组件，其特征在于：所述电源组件包括多面体状安装架、供能装置以及至少两个功能模块，所述安装架设置在所述机身上，所述至少两个功能模块彼此分离地设置于所述安装架的不同侧面，并相互电性连接；所述供能装置设置于所述安装架上，所述至少两个功能模块分别与所述供能装置电性连接。
  2. 如权利要求1所述的无人飞行器，其特征在于：所述机身为机壳，所述电源组件收容在所述机壳内。
  3. 如权利要求1所述的无人飞行器，其特征在于：所述机身包括相互扣合的上壳及下壳，所述电源组件设置在所述上壳及所述下壳之间。
  4. 如权利要求3所述的无人飞行器，其特征在于：所述电源组件固定设置于所述上壳上，以与所述上壳形成上壳组件。
  5. 如权利要求3所述的无人飞行器，其特征在于：所述无人飞行器还包括至少一个控制件，所述至少一个控制件固定于所述下壳上，并对应于所述安装架。
  6. 如权利要求5所述的无人飞行器，其特征在于：所述至少一个控制件包括固定地叠置于所述下壳上的第一控制件，所述第一控制件为电路板。
  7. 如权利要求6所述的无人飞行器，其特征在于：所述至少一个控制件还包括第二控制件，所述第二控制件叠置于所述第一控制件上，所述第二控制件为电路板。
  8. 如权利要求5所述的无人飞行器，其特征在于：所述至少一个控制件与搭载在所述无人飞行器上的负载电性连接，并用于控制所述负载工作。
  9. 如权利要求5所述的无人飞行器，其特征在于：所述无人飞行器还包括散热件，所述散热件邻近所述控制件设置于所述下壳上。
  10. 如权利要求9所述的无人飞行器，其特征在于：所述至少一个控制件、所述散热件分别地固定于所述下壳上，以与所述下壳形成下壳组件。
  11. 如权利要求9所述的无人飞行器，其特征在于：所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合连接，所述第二壳体可拆卸地装设于所述第一壳体上。
  12. 如权利要求9所述的无人飞行器，其特征在于：所述至少一个控制件、所述散热件分别地固定于所述第二壳体上，以便于所述至少一个控制件及所述散热件的集成组装。
  13. 如权利要求12所述的无人飞行器，其特征在于：所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
  14. 如权利要求9所述的无人飞行器，其特征在于：所述散热件为散热风扇。
  15. 如权利要求3所述的无人飞行器，其特征在于：所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合，所述第二壳体可拆卸地装设于所述第一壳体上。
  16. 如权利要求15所述的无人飞行器，其特征在于：所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
  17. 如权利要求15所述的无人飞行器，其特征在于：所述无人飞行器上设置有图像获取装置，所述图像获取装置连接于所述机身的所述第二壳体上。
  18. 如权利要求17所述的无人飞行器，其特征在于：所述无人飞行器还包括云台，所述云台能够调节地设置于所述第二壳体上，所述图像获取装置设置于所述云台上。
  19. 如权利要求15所述的无人飞行器，其特征在于：所述无人飞行器还包括起落架，所述起落架设置于所述机身的所述第一壳体上，并朝远离所述机身的方向延伸。
  20. 如权利要求1所述的无人飞行器，其特征在于：所述无人飞行器还包括设置于所述机身上的电机以及设置于所述电机上的螺旋桨。
  21. 如权利要求1所述的无人飞行器，其特征在于：所述至少两个功能模块分别为用于执行不同功能的电路板。
  22. 如权利要求21所述的无人飞行器，其特征在于：所述至少两个功能模块为以下几种中的至少一种：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
  23. 如权利要求21所述的无人飞行器，其特征在于：所述至少两个功能模块包括第一电路板及第二电路板，所述第一电路板及所述第二电路板分别设置在所述安装架的相对两侧。
  24. 如权利要求23所述的无人飞行器，其特征在于：所述供能装置设置在所述安装架内，所述第一电路板及所述第二电路板分别叠置在所述安装架的相对两侧的外周表面上。
  25. 如权利要求24所述的无人飞行器，其特征在于：所述电源组件还包括转接件，所述转接件设置在所述安装架的一端，并与所述供能装置电性连接。
  26. 如权利要求25所述的无人飞行器，其特征在于：所述转接件叠置在所述安装架的外周表面上，且所述转接件的相对两个侧边分别邻近所述第一电路板及所述第二电路板。
  27. 如权利要求25所述的无人飞行器，其特征在于：所述转接件上设置有标准接口，所述标准接口用于与所述供能装置电性连接。
  28. 如权利要求24所述的无人飞行器，其特征在于：所述至少两个功能模块还包括第三电路板，所述第三电路板设置在所述安装架上并分别与所述第二电路板及所述第一电路板彼此间隔，所述第三电路板与所述供能装置电性连接。
  29. 如权利要求28所述的无人飞行器，其特征在于：所述第三电路板叠置在所述安装架的外周表面上，且所述第三电路板的三个侧边分别邻近所述第一电路板、所述第二电路板以及所述转接件。
  30. 如权利要求29所述的无人飞行器，其特征在于：所述电源组件还包括控制器，所述控制器设置于所述第三电路板的背离所述安装架的一侧，所述控制器与所述供能装置电性连接。
  31. 如权利要求30所述的无人飞行器，其特征在于：所述控制器的两端分别相对所述第三电路板的对应两端延伸出，并分别与所述供能装置电性连接。
  32. 如权利要求30所述的无人飞行器，其特征在于：所述控制器为飞行控制器或者行驶控制器。
  33. 如权利要求1所述的无人飞行器，其特征在于：所述电源组件还包括连接于所述安装架上的控制器，所述控制器为飞行控制器或者行驶控制器。
  34. 一种遥控移动装置，其包括机身以及设置于所述机身上的电源组件，其特征在于：所述电源组件包括多面体状安装架、供能装置以及至少两个功能模块，所述安装架设置在所述机身上，所述至少两个功能模块彼此分离地设置于所述安装架的不同侧面，并相互电性连接；所述供能装置设置于所述安装架上，所述至少两个功能模块分别与所述供能装置电性连接。
  35. 如权利要求34所述的遥控移动装置，其特征在于：所述机身为机壳，所述电源组件收容在所述机壳内。
  36. 如权利要求34所述的遥控移动装置，其特征在于：所述机身包括相互扣合的上壳及下壳，所述电源组件设置在所述上壳及所述下壳之间。
  37. 如权利要求36所述的遥控移动装置，其特征在于：所述电源组件固定设置于所述上壳上，以与所述上壳形成上壳组件。
  38. 如权利要求36所述的遥控移动装置，其特征在于：所述无人飞行器还包括至少一个控制件，所述至少一个控制件固定于所述下壳上，并对应于所述安装架。
  39. 如权利要求38所述的遥控移动装置，其特征在于：所述至少一个控制件包括固定地叠置于所述下壳上的第一控制件，所述第一控制件为电路板。
  40. 如权利要求39所述的遥控移动装置，其特征在于：所述至少一个控制件还包括第二控制件，所述第二控制件叠置于所述第一控制件上，所述第二控制件为电路板。
  41. 如权利要求38所述的遥控移动装置，其特征在于：所述至少一个控制件与搭载在所述无人飞行器上的负载电性连接，并用于控制所述负载工作。
  42. 如权利要求38所述的遥控移动装置，其特征在于：所述无人飞行器还包括散热件，所述散热件邻近所述控制件设置于所述下壳上。
  43. 如权利要求42所述的遥控移动装置，其特征在于：所述至少一个控制件、所述散热件分别地固定于所述下壳上，以与所述下壳形成下壳组件。
  44. 如权利要求42所述的遥控移动装置，其特征在于：所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合连接，所述第二壳体可拆卸地装设于所述第一壳体上。
  45. 如权利要求42所述的遥控移动装置，其特征在于：所述至少一个控制件、所述散热件分别地固定于所述第二壳体上，以便于所述至少一个控制件及所述散热件的集成组装。
  46. 如权利要求45所述的遥控移动装置，其特征在于：所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
  47. 如权利要求42所述的遥控移动装置，其特征在于：所述散热件为散热风扇。
  48. 如权利要求36所述的遥控移动装置，其特征在于：所述下壳包括第一壳体及第二壳体，所述第一壳体与所述上壳相扣合，所述第二壳体可拆卸地装设于所述第一壳体上。
  49. 如权利要求48所述的遥控移动装置，其特征在于：所述第一壳体上设置有安装口，所述安装口贯穿所述第一壳体并与所述机身的内腔连通，所述第二壳体盖设于所述安装口上。
  50. 如权利要求48所述的遥控移动装置，其特征在于：所述无人飞行器上设置有图像获取装置，所述图像获取装置连接于所述机身的所述第二壳体上。
  51. 如权利要求50所述的遥控移动装置，其特征在于：所述无人飞行器还包括云台，所述云台能够调节地设置于所述第二壳体上，所述图像获取装置设置于所述云台上。
  52. 如权利要求48所述的遥控移动装置，其特征在于：所述无人飞行器还包括起落架，所述起落架设置于所述机身的所述第一壳体上，并朝远离所述机身的方向延伸。
  53. 如权利要求34所述的遥控移动装置，其特征在于：所述无人飞行器还包括设置于所述机身上的电机以及设置于所述电机上的螺旋桨。
  54. 如权利要求34所述的遥控移动装置，其特征在于：所述至少两个功能模块分别为用于执行不同功能的电路板。
  55. 如权利要求54所述的遥控移动装置，其特征在于：所述至少两个功能模块为以下几种中的至少一种：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
  56. 如权利要求54所述的遥控移动装置，其特征在于：所述至少两个功能模块包括第一电路板及第二电路板，所述第一电路板及所述第二电路板分别设置在所述安装架的相对两侧。
  57. 如权利要求56所述的遥控移动装置，其特征在于：所述供能装置设置在所述安装架内，所述第一电路板及所述第二电路板分别叠置在所述安装架的相对两侧的外周表面上。
  58. 如权利要求57所述的遥控移动装置，其特征在于：所述电源组件还包括转接件，所述转接件设置在所述安装架的一端，并与所述供能装置电性连接。
  59. 如权利要求58所述的遥控移动装置，其特征在于：所述转接件叠置在所述安装架的外周表面上，且所述转接件的相对两个侧边分别邻近所述第一电路板及所述第二电路板。
  60. 如权利要求58所述的遥控移动装置，其特征在于：所述转接件上设置有标准接口，所述标准接口用于与所述供能装置电性连接。
  61. 如权利要求57所述的遥控移动装置，其特征在于：所述至少两个功能模块还包括第三电路板，所述第三电路板设置在所述安装架上并分别与所述第二电路板及所述第一电路板彼此间隔，所述第三电路板与所述供能装置电性连接。
  62. 如权利要求61所述的遥控移动装置，其特征在于：所述第三电路板叠置在所述安装架的外周表面上，且所述第三电路板的三个侧边分别邻近所述第一电路板、所述第二电路板以及所述转接件。
  63. 如权利要求62所述的遥控移动装置，其特征在于：所述电源组件还包括控制器，所述控制器设置于所述第三电路板的背离所述安装架的一侧，所述控制器与所述供能装置电性连接。
  64. 如权利要求63所述的遥控移动装置，其特征在于：所述控制器的两端分别相对所述第三电路板的对应两端延伸出，并分别与所述供能装置电性连接。
  65. 如权利要求63所述的遥控移动装置，其特征在于：所述控制器为飞行控制器或者行驶控制器。
  66. 如权利要求34所述的遥控移动装置，其特征在于：所述电源组件还包括连接于所述安装架上的控制器，所述控制器为飞行控制器或者行驶控制器。
  67. 如权利要求34所述的遥控移动装置，其特征在于：所述遥控移动装置为无人驾驶车辆或无人驾驶船舶。
  68. 一种电源组件，其特征在于：包括多面体状安装架、供能装置以及至少两个功能模块，所述至少两个功能模块彼此分离地设置于所述安装架的不同侧面，并相互电性连接；所述供能装置设置于所述安装架上，所述至少两个功能模块分别与所述供能装置电性连接。
  69. 如权利要求68所述的电源组件，其特征在于：所述至少两个功能模块分别为用于执行不同功能的电路板。
  70. 如权利要求69所述的电源组件，其特征在于：所述至少两个功能模块为以下几种中的至少一种：速度感测模块，重力感测模块，视觉感测模块，磁场感测模块，控制模块。
  71. 如权利要求69所述的电源组件，其特征在于：所述至少两个功能模块包括第一电路板及第二电路板，所述第一电路板及所述第二电路板分别设置在所述安装架的相对两侧。
  72. 如权利要求71所述的电源组件，其特征在于：所述供能装置设置在所述安装架内，所述第一电路板及所述第二电路板分别叠置在所述安装架的相对两侧的外周表面上。
  73. 如权利要求72所述的电源组件，其特征在于：所述电源组件还包括转接件，所述转接件设置在所述安装架的一端，并与所述供能装置电性连接。
  74. 如权利要求73所述的电源组件，其特征在于：所述转接件叠置在所述安装架的外周表面上，且所述转接件的相对两个侧边分别邻近所述第一电路板及所述第二电路板。
  75. 如权利要求73所述的电源组件，其特征在于：所述转接件上设置有标准接口，所述标准接口用于与所述供能装置电性连接。
  76. 如权利要求72所述的电源组件，其特征在于：所述至少两个功能模块还包括第三电路板，所述第三电路板设置在所述安装架上并分别与所述第二电路板及所述第一电路板彼此间隔，所述第三电路板与所述供能装置电性连接。
  77. 如权利要求76所述的电源组件，其特征在于：所述第三电路板叠置在所述安装架的外周表面上，且所述第三电路板的三个侧边分别邻近所述第一电路板、所述第二电路板以及所述转接件。
  78. 如权利要求77所述的电源组件，其特征在于：所述电源组件还包括控制器，所述控制器设置于所述第三电路板的背离所述安装架的一侧，所述控制器与所述供能装置电性连接。
  79. 如权利要求78所述的电源组件，其特征在于：所述控制器的两端分别相对所述第三电路板的对应两端延伸出，并分别与所述供能装置电性连接。
  80. 如权利要求78所述的电源组件，其特征在于：所述控制器为飞行控制器或者行驶控制器。
  81. 如权利要求68所述的电源组件，其特征在于：所述电源组件还包括连接于所述安装架上的控制器，所述控制器为飞行控制器或者行驶控制器。
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Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018053837A1 (zh) * 2016-09-26 2018-03-29 深圳市大疆创新科技有限公司 无人机的机架组件及具有该机架组件的无人机
WO2018082004A1 (en) * 2016-11-04 2018-05-11 XDynamics Limited An unmanned aerial vehicle
DE102016221829A1 (de) * 2016-11-08 2018-05-09 Audi Ag Energieversorgungsfahrzeug zum Versorgen eines elektrisch antreibbaren Kraftfahrzeugs mit elektrischer Energie
CN208530829U (zh) * 2018-06-26 2019-02-22 深圳市大疆创新科技有限公司 无人机扩展系统及其无人机、扩展模块
WO2020061838A1 (zh) * 2018-09-26 2020-04-02 深圳市大疆创新科技有限公司 无人飞行器
CN109455291A (zh) * 2018-12-25 2019-03-12 拓攻（南京）机器人有限公司 一种用于无人机的机架及无人机
EP3821480B1 (en) * 2019-09-11 2022-05-18 SZ DJI Technology Co., Ltd. Power supply mounting position detecting device, method, and power supply

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8235324B1 (en) * 2009-03-03 2012-08-07 Orbital Research Inc. Rotorcraft with electrically driven blade control
CN203047531U (zh) * 2012-11-15 2013-07-10 深圳市大疆创新科技有限公司 多旋翼无人飞行器
CN203740115U (zh) * 2014-01-24 2014-07-30 深圳一电科技有限公司 无人机
CN204121762U (zh) * 2014-09-23 2015-01-28 彭信泉 一种多旋翼飞行器
CN204297110U (zh) * 2014-12-05 2015-04-29 广东澄星航模科技股份有限公司 一种具有gps装置的四轴飞行器
CN204688429U (zh) * 2015-05-20 2015-10-07 深圳市大疆创新科技有限公司 主机结构总成及使用该主机结构总成的遥控移动装置
CN105035312A (zh) * 2014-04-24 2015-11-11 鹦鹉股份有限公司 用于旋翼无人机的通用安装板
CN205469856U (zh) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 电源组件、无人飞行器及遥控移动装置

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9456185B2 (en) * 2009-08-26 2016-09-27 Geotech Environmental Equipment, Inc. Helicopter
GB2491129B (en) * 2011-05-23 2014-04-23 Blue Bear Systems Res Ltd Air vehicle
TWI500204B (zh) * 2012-03-21 2015-09-11 Simplo Technology Co Ltd 電池模組
US10569868B2 (en) * 2013-04-02 2020-02-25 Hood Technology Corporation Multicopter-assisted system and method for launching and retrieving a fixed-wing aircraft
US8991758B2 (en) * 2013-05-13 2015-03-31 Precisionhawk Inc. Unmanned aerial vehicle
US9611038B2 (en) * 2014-06-03 2017-04-04 Working Drones, Inc. Mobile computing device-based guidance navigation and control for unmanned aerial vehicles and robotic systems
JP6527153B2 (ja) * 2014-07-31 2019-06-05 エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ 無人航空機のドック
CN204144349U (zh) * 2014-08-29 2015-02-04 深圳市大疆创新科技有限公司 电动装置、电池模块以及电池单元
CA2911998A1 (en) * 2014-11-26 2016-05-26 Gilles Daigle Unmanned aerial vehicle
US10220954B2 (en) * 2015-01-04 2019-03-05 Zero Zero Robotics Inc Aerial system thermal control system and method
CN204568055U (zh) * 2015-02-05 2015-08-19 深圳雷柏科技股份有限公司 一种模块化无人飞行器
JP6614556B2 (ja) * 2015-06-01 2019-12-04 エスゼット ディージェイアイ テクノロジー カンパニー リミテッド 無人航空機
CN205022853U (zh) * 2015-08-14 2016-02-10 湖北易瓦特科技股份有限公司 多旋翼飞行设备
CN204937492U (zh) * 2015-08-27 2016-01-06 蔡强 一种模块组合式四轴飞行器
US9945828B1 (en) * 2015-10-23 2018-04-17 Sentek Systems Llc Airborne multispectral imaging system with integrated navigation sensors and automatic image stitching
FR3043337A1 (fr) * 2015-11-10 2017-05-12 Parrot Drone ayant un support de propulsion couple.
US11851174B2 (en) * 2015-11-20 2023-12-26 FlightWave Aerospace Systems Gimbaled thruster configuration for use with unmanned aerial vehicle
US20200225684A1 (en) * 2016-03-24 2020-07-16 Flir Detection, Inc. Persistent aerial communication and control system
US10780970B2 (en) * 2016-04-06 2020-09-22 Harris Aerial Llc Folding heavy-lift unmanned vehicle frame
US9981743B2 (en) * 2016-04-14 2018-05-29 Qualcomm Incorporated Electronic speed controller arm for vehicle
US20170305537A1 (en) * 2016-04-20 2017-10-26 Tenshi Technologies, LLC (A Utah, LLC) Un-manned aerial vehicle
WO2017197325A1 (en) * 2016-05-13 2017-11-16 Top Flight Technologies, Inc. Data center powered by a hybrid generator system
WO2018010122A1 (en) * 2016-07-13 2018-01-18 SZ DJI Technology Co., Ltd. Vehicle chassis and vehicle,method,and kit relating to the same
US20180086472A1 (en) * 2016-09-25 2018-03-29 Impossible Aerospace Corporation Aircraft Battery Systems and Aircraft Including Same
US10850838B2 (en) * 2016-09-30 2020-12-01 Sony Interactive Entertainment Inc. UAV battery form factor and insertion/ejection methodologies
CN206552279U (zh) * 2016-10-25 2017-10-13 深圳市大疆创新科技有限公司 无人飞行器及电池仓组件与电池仓
CN110021723B (zh) * 2016-11-02 2022-06-14 深圳市大疆创新科技有限公司 一种电池收纳装置及无人机
WO2018152785A1 (zh) * 2017-02-24 2018-08-30 深圳市大疆创新科技有限公司 无人飞行器
US10427790B2 (en) * 2017-06-12 2019-10-01 David A. Verkade Adaptive aerial vehicle
AU2018308963A1 (en) * 2017-08-01 2020-03-19 Zipline International Inc. Unmanned aircraft system with swappable components
US20190061970A1 (en) * 2017-08-29 2019-02-28 Qualcomm Incorporated Multi-rotor aerial drone with thermal energy harvesting
WO2019041174A1 (zh) * 2017-08-30 2019-03-07 深圳市大疆创新科技有限公司 无人机
US11046443B2 (en) * 2017-11-07 2021-06-29 Intel Corporation Safety systems for unmanned vehicles
CN110300705A (zh) * 2018-01-19 2019-10-01 深圳市大疆创新科技有限公司 机身及包括该机身的无人机

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8235324B1 (en) * 2009-03-03 2012-08-07 Orbital Research Inc. Rotorcraft with electrically driven blade control
CN203047531U (zh) * 2012-11-15 2013-07-10 深圳市大疆创新科技有限公司 多旋翼无人飞行器
CN203740115U (zh) * 2014-01-24 2014-07-30 深圳一电科技有限公司 无人机
CN105035312A (zh) * 2014-04-24 2015-11-11 鹦鹉股份有限公司 用于旋翼无人机的通用安装板
CN204121762U (zh) * 2014-09-23 2015-01-28 彭信泉 一种多旋翼飞行器
CN204297110U (zh) * 2014-12-05 2015-04-29 广东澄星航模科技股份有限公司 一种具有gps装置的四轴飞行器
CN204688429U (zh) * 2015-05-20 2015-10-07 深圳市大疆创新科技有限公司 主机结构总成及使用该主机结构总成的遥控移动装置
CN205469856U (zh) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 电源组件、无人飞行器及遥控移动装置

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