WO2016095837A1 - 飞行器系统 - Google Patents

飞行器系统 Download PDF

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Publication number
WO2016095837A1
WO2016095837A1 PCT/CN2015/097804 CN2015097804W WO2016095837A1 WO 2016095837 A1 WO2016095837 A1 WO 2016095837A1 CN 2015097804 W CN2015097804 W CN 2015097804W WO 2016095837 A1 WO2016095837 A1 WO 2016095837A1
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WO
WIPO (PCT)
Prior art keywords
aircraft
pan
tilt
motor
communication circuit
Prior art date
Application number
PCT/CN2015/097804
Other languages
English (en)
French (fr)
Inventor
田瑜
江文彦
Original Assignee
优利科技有限公司
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Filing date
Publication date
Application filed by 优利科技有限公司 filed Critical 优利科技有限公司
Priority to US15/529,779 priority Critical patent/US10053229B2/en
Publication of WO2016095837A1 publication Critical patent/WO2016095837A1/zh

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Classifications

    • G—PHYSICS
    • G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
    • G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
    • G03B17/00—Details of cameras or camera bodies; Accessories therefor
    • G03B17/56—Accessories
    • G03B17/561—Support related camera accessories
    • 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
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/02—Heads
    • F16M11/04—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand
    • F16M11/041—Allowing quick release of the apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/02—Heads
    • F16M11/04—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand
    • F16M11/06—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting
    • F16M11/08—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting around a vertical axis, e.g. panoramic heads
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/02—Heads
    • F16M11/04—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand
    • F16M11/06—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting
    • F16M11/10—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting around a horizontal axis
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/20—Undercarriages with or without wheels
    • F16M11/2007—Undercarriages with or without wheels comprising means allowing pivoting adjustment
    • F16M11/2035—Undercarriages with or without wheels comprising means allowing pivoting adjustment in more than one direction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M11/00—Stands or trestles as supports for apparatus or articles placed thereon ; Stands for scientific apparatus such as gravitational force meters
    • F16M11/20—Undercarriages with or without wheels
    • F16M11/2007—Undercarriages with or without wheels comprising means allowing pivoting adjustment
    • F16M11/2035—Undercarriages with or without wheels comprising means allowing pivoting adjustment in more than one direction
    • F16M11/2071—Undercarriages with or without wheels comprising means allowing pivoting adjustment in more than one direction for panning and rolling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
    • F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
    • G—PHYSICS
    • G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
    • G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
    • G03B15/00—Special procedures for taking photographs; Apparatus therefor
    • G03B15/006—Apparatus mounted on flying objects
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
    • H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
    • H04N23/60—Control of cameras or camera modules
    • H04N23/63—Control of cameras or camera modules by using electronic viewfinders
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
    • H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
    • H04N23/60—Control of cameras or camera modules
    • H04N23/66—Remote control of cameras or camera parts, e.g. by remote control devices
    • H04N23/661—Transmitting camera control signals through networks, e.g. control via the Internet
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
    • H04N7/00—Television systems
    • H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
    • H04N7/00—Television systems
    • H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
    • H04N7/183—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source
    • H04N7/185—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source from a mobile camera, e.g. for remote control
    • G—PHYSICS
    • G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
    • G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
    • G03B2206/00—Systems for exchange of information between different pieces of apparatus, e.g. for exchanging trimming information, for photo finishing

Definitions

  • the invention relates to an aircraft system.
  • an aircraft is usually capable of realizing an aerial photography function, and an image acquired by an aircraft needs to be displayed through a separate display device, making it inconvenient for the user to observe the image.
  • the image signal obtained by the aircraft is easily interfered during transmission, and the signal transmission between the aircraft and the remote controller is not stable and reliable.
  • the technical problem to be solved by the present invention is to overcome the defects that the user observes the image acquired by the aircraft in the prior art, and the transmission of the image signal obtained by the aircraft is not stable and reliable, and provides an aircraft system that is convenient for the user to view and has stable signal transmission. .
  • an aircraft system includes an aircraft provided with an imaging device and a remote controller, wherein the remote controller includes a display and a device for a first communication circuit for transmitting an aircraft control signal by the aircraft and a second communication circuit for receiving an image signal of the camera device, the display for displaying the image signal.
  • the remote controller of the present application is provided with a display capable of displaying an image signal, and the operator can intuitively observe the image captured by the camera device when using the remote controller to control the aircraft, thereby providing convenience for the operator.
  • the remote controller of the present application utilizes two communication circuits and can be equipped with two antennas and flying The device communicates with the camera device, and the transmission of the control signal and the image signal are independent of each other and do not interfere with each other, and the signal transmission is more stable and reliable.
  • the aircraft includes a pan/tilt, and the aircraft is connected to the camera device through the pan/tilt.
  • the aircraft includes a power supply circuit, and the aircraft supplies power to the camera device through the power supply circuit.
  • the first communication circuit is a 2.4 GHz communication circuit
  • the second communication circuit is a 5.8 GHz communication circuit.
  • the pan/tilt head is connected to the aircraft through a pan/tilt adapter, and the pan/tilt head includes an adapter body, and the front and rear sides of the adapter body respectively extend outwardly
  • the buckle portion is configured to be engaged with a cloud platform to restrict movement of the cloud platform in a vertical direction and a front-rear direction, and the adapter body is further provided with a plurality of fixing portions.
  • an upper damper plate is further disposed between the pan/tilt adapter and the pan/tilt, and two top surfaces of the upper damper plate are disposed corresponding to the two buckle portions. And the two bayonet ports are respectively engaged with the corresponding latching portions.
  • the top surface of the upper damper plate is provided with two channels near the two bayonet ports, and the cross-sectional shapes of the two bayonet ports are all L-shaped, and the two channels are located at Directly below the corresponding bayonet, the front and rear sides of the right end of the adapter body respectively extend outwardly with a first limiting portion, and the two first limiting portions respectively abut against the corresponding a accommodating slot is disposed on a left end of the accommodating body, a second limiting portion is disposed on the left end surface of the accommodating slot, and the second limiting portion is located at the right end of the accommodating body The second limiting portion abuts against the left end surface of the upper damper plate
  • the aircraft includes an aircraft control circuit
  • the pan/tilt includes a first motor, a second motor, a third motor, a picture transmitting unit and an inertial measurement unit, the first motor, the first
  • the two motors and the third motor are respectively used to control three axial rotations of the three-dimensional coordinate system
  • the aircraft control circuit is configured to respectively communicate with the first motor and the second motor through three-phase lines
  • the third motor is electrically connected
  • the aircraft control circuit is further configured to be electrically connected to the inertial measurement unit through a communication line.
  • the second communication circuit is a 5.8 GHz Wi-Fi communication circuit.
  • the positive progress of the present invention is that in the aircraft system of the present application, the control signal of the aircraft and the image signal transmitted by the camera device do not interfere with each other and the transmission is more stable, and the display can directly display the image signal to provide convenience for the user.
  • the image signal is transmitted through the 5.8 GHz communication circuit, and the image displayed on the display screen is smoother.
  • FIG. 1 is a schematic structural view of an aircraft system according to an embodiment of the present invention.
  • FIG. 2 is a schematic perspective structural view of a PTZ adapter according to an embodiment of the present invention.
  • Fig. 3 is a bottom view corresponding to Fig. 2.
  • FIG. 4 is a schematic perspective structural view of a portion of an aircraft pan/tilt head according to an embodiment of the present invention.
  • FIG. 5 is a schematic exploded view of a portion of an aircraft pan/tilt head according to an embodiment of the present invention.
  • FIG. 6 is another schematic structural diagram of an aircraft system according to an embodiment of the present invention.
  • the embodiment provides an aircraft system including an aircraft 31 provided with an imaging device 33 and a remote controller 32.
  • the remote controller includes a display 321 and a system for transmitting to the aircraft.
  • the first communication circuit 322 is a 2.4 GHz communication circuit
  • the second communication circuit 323 is a 5.8 GHz Wi-Fi communication circuit.
  • the aircraft control signal of the remote control is transmitted to the aircraft control circuit of the aircraft via a 2.4 GHz communication signal 41, which communicates with the camera device via a 5.8 GHz Wi-Fi communication signal 42.
  • the aircraft control circuit and power supply circuit 34 of the aircraft communicate with the camera 33 via wires 43.
  • the aircraft further includes a cloud platform 1 and a power supply circuit 34 through which the aircraft is connected to the camera device and supplies power to the camera device through the power supply circuit.
  • the pan/tilt head 1 is connected to the aircraft 31 via a pan/tilt adapter 2, and an upper damper plate 11 is further disposed between the pan/tilt adapter and the pan/tilt.
  • the two bayonet ports 111 have an L-shaped cross-sectional shape, and both of the bayonet ports 111 are disposed along the longitudinal direction of the pan-tilt adapter 2, that is, in the left-right direction. At the same time, the lengths of the two bayonet ports 111 are equal and opposite.
  • the pan/tilt adapter 2 includes an adapter body 21.
  • a latching portion 22 is defined on the front and rear sides of the adapter body 21, and the latching portion 22 is configured to be engaged with the pan/tilt head to limit the pan/tilt head in a vertical direction. And movement in the front and rear direction.
  • the two latching portions 22 are respectively disposed corresponding to the two latching ports 111, and the two latching portions 22 are respectively engaged with the corresponding latching ports 111. This enables the pan/tilt to be easily snapped onto the pan/tilt adapter 2, and the pan/tilt can be easily detached from the pan-tilt adapter 2.
  • the shape of the left end surface of the adapter body 21 is set to an arc shape, and the shape of the right end surface surface is also set to an arc shape.
  • the width of the left end portion of the adapter body 21 is greater than the width of the right end portion of the adapter body 21.
  • the latching portion 22 is provided at a right end portion of the adapter body 21 and integrally formed with the adapter body 21.
  • the adapter body 21 is provided with a fixing portion 23. Because the structure of the pan/tilt adapter 2 is simple, its volume is small and the weight is light, the pan/tilt adapter 2 can be conveniently fixed to different devices, such as an aircraft or a hand-held rack, through the fixing portion 23.
  • Two channels 112 are formed on the top surface of the upper damper plate 11 near the two bayonet ports 111.
  • the two portholes 111 have an L-shaped cross-sectional shape, and the two channels 112 are Located directly below the corresponding bayonet 111. This further reduces the contact area between the top surface of the gimbal and the bottom surface of the pan/tilt adapter 2, so that assembly or disassembly between the gimbal and the pan/tilt adapter 2 is more convenient.
  • a first limiting portion 25 extends outwardly from the front and rear sides of the right end portion of the adapter body 21, respectively.
  • the first limiting portion 25 is configured to abut the right end portion of the corresponding bayonet 111 to restrict the movement of the upper damping plate 11 of the pan/tilt in the longitudinal direction of the adapter body 21. .
  • the first limiting portion 25 abuts against the right end portion of the corresponding bayonet 111, and the first limiting portion 25 performs the advancing direction when the pan/tilt is inserted into the pan/tilt adapter 2
  • the restriction is to prevent the degree of advancement from slipping out of the bayonet 111 of the pan/tilt adapter 2, and cooperate with the latching portion 22 to play a limiting role in the vertical direction.
  • a accommodating groove 26 is disposed on the left end of the accommodating body 21, and a left end surface of the accommodating groove 26 is disposed on the left end surface of the accommodating groove 26 for limiting the length of the pylon in the longitudinal direction of the Adapter body 21.
  • the second limit portion 27 that moves. The second limiting portion 27 is located in the accommodating groove 26, and the second limiting portion 27 is bent upward when subjected to an upward force.
  • the second limiting portion 27 functions as a limit. When the pan/tilt is inserted into the adapter, the direction in which the head of the pan/tilt is reversed is restricted to prevent the pan/tilt from moving backward. Meanwhile, the second limiting portion 27 It can be bent upward when subjected to a certain upward force, so that the pan/tilt can be inserted into or removed from the pan/tilt adapter 2.
  • the second limiting portion 27 abuts against the left end surface of the upper damper plate 11. This restricts the movement of the upper damper plate 11 in the left-right direction, preventing the pan/tilt from being detached from the pan-tilt adapter 2 during the shooting.
  • An aircraft control circuit is included, the cloud platform includes a first motor, a second motor, a third motor, a picture transmission unit, and an inertial measurement unit, the first motor, the second motor, and the The third motor is configured to respectively control three axial rotations of the three-dimensional coordinate system, and the aircraft control circuit is configured to respectively electrically connect the first motor, the second motor, and the third motor through three-phase lines Connected, the aircraft control circuit is further configured to be electrically coupled to the inertial measurement unit via a communication line.
  • control signal of the aircraft and the image signal transmitted by the camera device do not interfere with each other and the transmission is more stable, and the display can directly display the image signal to provide convenience for the user.
  • the image signal is transmitted through the 5.8 GHz communication circuit, and the image displayed on the display screen is smoother.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Multimedia (AREA)
  • Signal Processing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Remote Sensing (AREA)
  • Studio Devices (AREA)
  • Details Of Aerials (AREA)

Abstract

一种飞行器系统(1)，其包括一设有摄像装置（33）的飞行器(31)以及一遥控器(32)，所述遥控器(32)包括一显示器(321)、一用于向所述飞行器(31)传输飞行器控制信号的第一通信电路(322)以及一用于接收所述摄像装置的影像信号的第二通信电路(323)，所述显示器(321)用于显示所述影像信号。

Description

飞行器系统
本申请要求申请日为2014年12月18日的中国专利申请CN201420814036.9的优先权。本申请引用上述中国专利申请的全文。
技术领域
本发明涉及一种飞行器系统。
背景技术
在现有技术中，飞行器通常能够实现航拍功能，利用飞行器获取的影像需要通过一个单独的显示装置进行显示，使用户不方便观察影像。而且飞行器获得的影像信号在传输过程中容易受到干扰，飞行器与遥控器之间的信号传输不够稳定可靠。
发明内容
本发明要解决的技术问题是为了克服现有技术中用户观察飞行器获取的影像不方便，且飞行器获得的影像信号的传输不够稳定可靠的缺陷，提供一种方便用户查看且信号传输稳定的飞行器系统。
本发明是通过下述技术方案来解决上述技术问题：一种飞行器系统，其包括一设有摄像装置的飞行器以及一遥控器，其特点在于，所述遥控器包括一显示器、一用于向所述飞行器传输飞行器控制信号的第一通信电路以及一用于接收所述摄像装置的影像信号的第二通信电路，所述显示器用于显示所述影像信号。
本申请的遥控器上设有能够显示影像信号的显示器，操作人员利用遥控器控制飞行器时能够直观的观察到摄像装置拍摄到的影像，为操作人员提供便利。另外，本申请的遥控器利用两个通信电路，可以配备两个天线与飞行 器和摄像装置进行通信，控制信号与影像信号的传输相互独立且彼此互不干扰，信号传输更加稳定可靠。
较佳地，所述飞行器包括一云台，所述飞行器通过所述云台与所述摄像装置连接。
较佳地，所述飞行器包括一供电电路，所述飞行器通过所述供电电路向所述摄像装置供电。
较佳地，所述第一通信电路为2.4GHz通信电路，所述第二通信电路为5.8GHz通信电路。
较佳地，所述云台通过一云台转接件与所述飞行器连接，所述云台转接件包括一转接本体，所述转接本体的前、后侧面上分别向外延伸有一卡扣部，所述卡扣部用于与一云台相卡接限制所述云台在竖直方向和前后方向上的移动，所述转接本体上还设置有若干固定部。
较佳地，所述云台转接件与所述云台之间还设有一上减震板，所述上减震板的顶面上设有与两个所述卡扣部对应设置的两个卡口，且两个所述卡口分别与相应的所述卡扣部卡接。
较佳地，所述上减震板的顶面上靠近两个所述卡口处开设有两个通道，两个所述卡口的横截面形状均为L形，且两个所述通道位于相应的所述卡口的正下方，所述转接本体的右端部的前、后侧面上分别向外延伸有一第一限位部，两个所述第一限位部分别抵靠于相应的所述卡口的右端部，所述转接本体的左端部上设有一容置槽，所述容置槽的左端面上设有一第二限位部，且所述第二限位部位于所述容置槽内，所述第二限位部抵靠于所述上减震板的左端面上
较佳地，飞行器包括一飞行器控制电路，所述云台包括一第一电机、一第二电机、一第三电机、一图传单元及一惯性测量单元，所述第一电机、所述第二电机及所述第三电机用于分别控制三维坐标系的三个轴向上的转动，所述飞行器控制电路用于通过三相线分别与所述第一电机、所述第二电机及 所述第三电机电连接，所述飞行器控制电路还用于通过通信线与所述惯性测量单元电连接。
较佳地，所述第二通信电路为5.8GHz的Wi-Fi通信电路。
本发明的积极进步效果在于：本申请的飞行器系统中，对飞行器的控制信号以及摄像装置传输的影像信号互不干扰且传输更加稳定，所述显示器能够直接显示影像信号为用户提供便利。影像信号通过5.8GHz通信电路进行传输，显示屏显示的影像更加流畅。
附图说明
图1为本发明实施例的飞行器系统的结构示意图。
图2为本发明实施例的云台转接件的立体结构示意图。
图3为与图2对应的仰视图。
图4为本发明实施例的飞行器云台部分的立体结构示意图。
图5为本发明实施例的飞行器云台部分的分解结构示意图。
图6为本发明实施例的飞行器系统的另一结构示意图。
具体实施方式
下面举个较佳实施例，并结合附图来更清楚完整地说明本发明。
在本发明的描述中，需要理解的是，术语“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。
参见图1至图5，本实施例提供一种飞行器系统，其包括一设有摄像装置33的飞行器31以及一遥控器32，所述遥控器包括一显示器321、一用于向所述飞行器传输飞行器控制信号的第一通信电路322以及一用于接收所述 摄像装置的影像信号的第二通信电路323，所述显示器用于显示所述影像信号。其中，所述第一通信电路322为2.4GHz通信电路，所述第二通信电路323为5.8GHz的Wi-Fi通信电路。
遥控器的飞行器控制信号通过2.4GHz通信信号41发送至所述飞行器的飞行器控制电路，遥控器与摄像装置通过5.8GHz的Wi-Fi通信信号42进行通信。飞行器的飞行器控制电路和供电电路34通过导线43与摄像装置33通信。
所述飞行器还包括一云台1以及一供电电路34，所述飞行器通过所述云台与所述摄像装置连接并通过所述供电电路向所述摄像装置供电。
所述云台1通过一云台转接件2与所述飞行器31连接，所述云台转接件与所述云台之间还设有一上减震板11，所述上减震板11的顶面上设有两个卡口111。两个卡口111的横截面形状均为L形，且两个卡口111均沿所述云台转接件2的长度方向上设置，即左右方向上设置。同时，两个卡口111的长度相等且相对设置。
如图1-3所示，云台转接件2包括一转接本体21。其中，所述转接本体21的前、后侧面上分别向外延伸有一卡扣部22，所述卡扣部22用于与所述云台相卡接从而限制所述云台在竖直方向和前后方向上的移动。两个所述卡扣部22分别与两个卡口111对应设置，且两个所述卡扣部22分别与相应的所述卡口111相卡接。这样使得云台能够方便的卡扣在云台转接件2上，且所述云台能够方便地从所述云台转接件2上拆卸。
当然，根据实际的需要，转接本体21的左端面的形状设置为弧形，右端面面的形状也设置为弧形。其中，转接本体21的左端部的宽度大于转接本体21的右端部的宽度。卡扣部22设置在转接本体21的右端部且与所述转接本体21一体成型。另外，转接本体21上设置有固定部23。因所述云台转接件2的结构简单，其体积较小以及重量较轻，可通过固定部23将云台转接件2方便地固定在不同的设备上，比如飞行器或手持架。
所述上减震板11的顶面上靠近两个所述卡口111处开设有两个通道112，两个所述卡口111的横截面形状均为L形，且两个所述通道112位于相应的所述卡口111的正下方。这样进一步减小了云台的顶面与云台转接件2的底面的接触面积，使得云台与云台转接件2之间的组装或拆卸更加方便。
所述转接本体21的右端部的前、后侧面上分别向外延伸有一第一限位部25。其中，所述第一限位部25用于抵靠于相应的所述卡口111的右端部从而限制所述云台的上减震板11在所述转接本体21的长度方向上的移动。
在本实施例中，第一限位部25分别抵靠于相应的所述卡口111的右端部，所述第一限位部25对云台插入云台转接件2时的前进方向进行限制，避免前进程度过多而滑出所述云台转接件2的卡口111，且与卡扣部22配合，起到竖直方向的限位作用。
另外，所述转接本体21的左端部上设有一容置槽26，所述容置槽26的左端面上设有一用于限制所述云台在所述转接本体21的长度方向上的移动的第二限位部27。且第二限位部27位于容置槽26内，所述第二限位部27受到一向上的作用力时可向上弯曲。
其中，第二限位部27起到限位作用，当云台插入转接件后，对其云台前进方向相反的方向进行限制，避免云台反向移动；同时，第二限位部27受到向上施加的一定作用力时可向上弯曲，从而方便云台插入或移出云台转接件2中。
此外，所述第二限位部27抵靠于所述上减震板11的左端面上。这样限制了所述上减震板11在左右方向上的移动，避免云台在拍摄过程中脱离所述云台转接件2。
包括一飞行器控制电路，所述云台包括一第一电机、一第二电机、一第三电机、一图传单元及一惯性测量单元，所述第一电机、所述第二电机及所述第三电机用于分别控制三维坐标系的三个轴向上的转动，所述飞行器控制电路用于通过三相线分别与所述第一电机、所述第二电机及所述第三电机电 连接，所述飞行器控制电路还用于通过通信线与所述惯性测量单元电连接。
本实施例的飞行器系统中飞行器的控制信号以及摄像装置传输的影像信号互不干扰且传输更加稳定，所述显示器能够直接显示影像信号为用户提供便利。影像信号通过5.8GHz通信电路进行传输，显示屏显示的影像更加流畅。
虽然以上描述了本发明的具体实施方式，但是本领域的技术人员应当理解，这些仅是举例说明，在不背离本发明的原理和实质的前提下，可以对这些实施方式做出多种变更或修改。因此，本发明的保护范围由所附权利要求书限定。

Claims (9)

  1. 一种飞行器系统，其包括一设有摄像装置的飞行器以及一遥控器，其特征在于，所述遥控器包括一显示器、一用于向所述飞行器传输飞行器控制信号的第一通信电路以及一用于接收所述摄像装置的影像信号的第二通信电路，所述显示器用于显示所述影像信号。
  2. 如权利要求1所述的飞行器系统，其特征在于，所述飞行器包括一云台，所述飞行器通过所述云台与所述摄像装置连接。
  3. 如权利要求1或2所述的飞行器系统，其特征在于，所述飞行器包括一供电电路，所述飞行器通过所述供电电路向所述摄像装置供电。
  4. 如权利要求1-3中至少一项所述的飞行器系统，其特征在于，所述第一通信电路为2.4GHz通信电路，所述第二通信电路为5.8GHz通信电路。
  5. 如权利要求2所述的飞行器系统，其特征在于，所述云台通过一云台转接件与所述飞行器连接，所述云台转接件包括一转接本体，所述转接本体的前、后侧面上分别向外延伸有一卡扣部，所述卡扣部用于与一云台相卡接限制所述云台在竖直方向和前后方向上的移动，所述转接本体上还设置有若干固定部。
  6. 如权利要求5所述的飞行器系统，其特征在于，所述云台转接件与所述云台之间还设有一上减震板，所述上减震板的顶面上设有与两个所述卡扣部对应设置的两个卡口，且两个所述卡口分别与相应的所述卡扣部卡接。
  7. 如权利要求6所述的飞行器系统，其特征在于，所述上减震板的顶面上靠近两个所述卡口处开设有两个通道，两个所述卡口的横截面形状均为L形，且两个所述通道位于相应的所述卡口的正下方，所述转接本体的右端部的前、后侧面上分别向外延伸有一第一限位部，两个所述第一限位部分别抵靠于相应的所述卡口的右端部，所述转接本体的左端部上设有一容置槽，所述容置槽的左端面上设有一第二限位部，且所述第二限位部位于所述容置 槽内，所述第二限位部抵靠于所述上减震板的左端面上。
  8. 如权利要求2所述的飞行器系统，其特征在于，飞行器包括一飞行器控制电路，所述云台包括一第一电机、一第二电机、一第三电机、一图传单元及一惯性测量单元，所述第一电机、所述第二电机及所述第三电机用于分别控制三维坐标系的三个轴向上的转动，所述飞行器控制电路用于通过三相线分别与所述第一电机、所述第二电机及所述第三电机电连接，所述飞行器控制电路还用于通过通信线与所述惯性测量单元电连接。
  9. 如权利要求4所述的飞行器系统，其特征在于，所述第二通信电路为5.8GHz的Wi-Fi通信电路。
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