WO2018113202A1 - 一种可拆卸云台连接装置及无人飞行器 - Google Patents

一种可拆卸云台连接装置及无人飞行器 Download PDF

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Publication number
WO2018113202A1
WO2018113202A1 PCT/CN2017/087434 CN2017087434W WO2018113202A1 WO 2018113202 A1 WO2018113202 A1 WO 2018113202A1 CN 2017087434 W CN2017087434 W CN 2017087434W WO 2018113202 A1 WO2018113202 A1 WO 2018113202A1
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WO
WIPO (PCT)
Prior art keywords
pan
tilt
assembly
alignment
uav
Prior art date
Application number
PCT/CN2017/087434
Other languages
English (en)
French (fr)
Inventor
胡亮军
Original Assignee
深圳市道通智能航空技术有限公司
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 深圳市道通智能航空技术有限公司 filed Critical 深圳市道通智能航空技术有限公司
Publication of WO2018113202A1 publication Critical patent/WO2018113202A1/zh
Priority to US16/454,634 priority Critical patent/US11543071B2/en

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Classifications

    • 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
    • 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
    • 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
    • F16M11/12—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting in more than one direction
    • F16M11/121—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting in more than one direction constituted of several dependent joints
    • F16M11/123—Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting in more than one direction constituted of several dependent joints the axis of rotation intersecting in a single point, e.g. by using 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
    • F16M11/18—Heads with mechanism for moving the apparatus relatively to the stand
    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
    • H01R13/631—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for engagement only
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/639—Additional means for holding or locking coupling parts together, after engagement, e.g. separate keylock, retainer strap
    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/627—Snap or like fastening
    • H01R13/6278—Snap or like fastening comprising a pin snapping into a recess

Definitions

  • Embodiments of the present application relate to the field of drones, and more particularly to a circuit protection device for a detachable cloud platform and a corresponding unmanned aerial vehicle.
  • the gimbal is integrated with the drone fuselage.
  • the gimbal and drone fuselage are detachable in more drone designs.
  • the pan/tilt fixture used on the unmanned aerial vehicle generally adopts a three-axis structure that is fastened to the pan/tilt, which is inconvenient for the user to use, is not easy to assemble and disassemble, and often is inserted laterally when the circuit is connected between the terminals because of the mechanical
  • the use of worn contacts makes the connection terminals susceptible to damage, which causes problems such as the gimbal being inoperable.
  • China Patent Application No.: 201610107361.5 discloses a detachable UAV that includes a fuselage and a pan/tilt head.
  • the camera unit is provided with a camera unit, and the body and the head are detachably connected.
  • the installation of the pan/tilt and the fuselage is such that the casing 102 is provided with a through slot 112 at a position corresponding to the fixed portion 110.
  • the slot 112 forms a segmented slide rail 106.
  • the clamping device includes a block 206, and the casing 102 is provided with a groove 109, the block 206 and the groove 109 cooperation.
  • the pan/tilt is fixed to the body by the latch 206 being clamped to the recess 109.
  • the slider 205 is first slid into position, the block 206 is embedded in the groove 109, and the card block 206 is clamped to the groove 109, and the side of the pan/tilt 201 with the card block 206 is clamped to the casing.
  • the cooperation between the slider 205 on the pan/tilt 201 and the slide rail 106 on the casing 102 is coupled to connect the pan/tilt 201 to the casing 102 (page 4 of the manual).
  • the slider 205 when the gimbal is disassembled and installed, the slider 205 is required to slide in the slide rail 106 every time, and the circuit connection terminal on the slider 205 is prone to wear during disassembly, affecting the gimbal diagram. Like the transmission of data, or eventually the gimbal can not work.
  • the technical problem to be solved by the embodiments of the present application is to provide a circuit protection device for a detachable cloud platform and a corresponding detachable cloud platform and an unmanned aerial vehicle.
  • the pan/tilt head using the pan/tilt connection device can ensure the electrical connection between the unmanned aerial vehicle and the pan/tilt head while being mounted to the fuselage, and the alignment between the circuit connection terminals between the unmanned aerial vehicle and the pan/tilt head is placed in the first place. Fixing after alignment reduces the mechanical use of the circuit connection terminals and improves the service life of the UAV.
  • the pre-installation assembly and the locking assembly are easy to operate and can be fixed and disassembled by simply rotating or pressing and rotating.
  • a technical solution provided by an embodiment of the present application is:
  • a detachable pan/tilt connection device including:
  • the alignment mechanism is configured to align the UAV circuit connection terminal with the PTZ circuit connection terminal;
  • pre-installation assembly disposed on the alignment assembly, the pre-installation assembly securing the pan-tilt connection to the fuselage of the UAV relative to the alignment assembly;
  • a locking assembly disposed on the pre-installation assembly that locks the pre-installed assembly when the pre-mounted assembly is moved relative to the alignment assembly to a predetermined position.
  • an unmanned aerial vehicle comprising a fuselage, an unmanned aerial vehicle circuit connection terminal, a pan/tilt head and a pan-tilt circuit connection terminal, comprising a pan-tilt connection device for detachably connecting the unmanned aerial vehicle and the pan/tilt, the pan-tilt connection device include:
  • the alignment component is fixed on the platform for aligning the UAV circuit connection terminal with the PTZ circuit connection terminal;
  • a pre-installed component disposed on the alignment assembly, the pre-installed component being shipped relative to the alignment assembly Fixing the pan/tilt connection to the fuselage;
  • a locking assembly disposed on the pre-installation assembly that locks the pre-installed assembly when the pre-mounted assembly is moved relative to the alignment assembly to a predetermined position.
  • a detachable cloud platform comprising a pan/tilt connection device for detachably connecting an unmanned aerial vehicle and a cloud platform, the pan-tilt connection device comprising:
  • the alignment component is fixed on the platform for aligning the UAV circuit connection terminal with the PTZ circuit connection terminal;
  • pre-installation assembly disposed on the alignment assembly, the pre-installation assembly securing the pan-tilt connection to the fuselage relative to the alignment assembly movement;
  • a locking assembly disposed on the pre-installation assembly that locks the pre-installed assembly when the pre-mounted assembly is moved relative to the alignment assembly to a predetermined position.
  • the beneficial effects of the embodiments of the present application are: the pan-tilt connection device provided in the embodiment, and the detachable cloud platform and the unmanned aerial vehicle, and the alignment component is disposed to preferentially ensure the electrical connection of the circuit connection terminal between the unmanned aerial vehicle and the cloud platform.
  • the connection makes the circuit connection terminals between the UAV and the PTZ only need to maintain electrical contact to avoid repeated friction during disassembly, reduce the mechanical loss of the circuit connection terminals, and improve the service life of the UAV.
  • the pre-installed components and locking components are easy to operate, and can be fixed and disassembled by simple rotation or pressing and rotating operations.
  • FIG. 1 is a schematic perspective view showing the structure of an unmanned aerial vehicle according to an embodiment of the present application
  • FIG. 2 is a disassembled state diagram of a head of an unmanned aerial vehicle according to an embodiment of the present application
  • FIG. 3 is an exploded perspective view of the detachable pan/tilt connection device of the embodiment of the present application.
  • FIG. 4 is an assembled perspective view of a detachable pan/tilt connection device according to an embodiment of the present application
  • FIG 5 is another assembled perspective view of the detachable pan/tilt connection device of the embodiment of the present application.
  • FIG. 6 is a perspective structural view of a button of a detachable pan/tilt connection device locking assembly according to an embodiment of the present application
  • FIG. 7 is a perspective view showing another perspective view of a button of the detachable pan/tilt connection locking assembly of the embodiment of the present application.
  • the present application relates to a connection device of a detachable cloud platform and a corresponding detachable cloud platform and unmanned aerial vehicle.
  • the pan/tilt head of the pan/tilt connection device firstly ensures the electrical connection between the unmanned aerial vehicle and the pan/tilt head while being detachably mounted to the unmanned aircraft fuselage, and prioritizes the unmanned aerial vehicle and the gimbal by setting the alignment components.
  • the electrical connection between the circuit connection terminals and the operation of the pre-installation component and the locking component does not affect the alignment component, which substantially reduces the mechanical loss of repeated friction during the installation and disassembly of the gimbal, and improves the service life of the UAV.
  • the pre-installation assembly and the locking assembly provided in the embodiment of the present application are convenient and simple to operate, and can be fixed and disassembled by simple rotation or pressing and rotating operations.
  • the pan/tilt connection device 300 of the present application is inserted into a fuselage connecting plate fixed on the unmanned aerial vehicle by a pre-installed component fixed on the pan/tilt, and rotated by a certain angle by pre-installing the component.
  • the locking assembly locks the pre-installation assembly so that it cannot rotate to secure the platform 200 to the UAV 100.
  • the pre-installation assembly and the locking assembly are easy to operate and can be fixed and disassembled by simply rotating the pre-mounted assembly or pressing the locking assembly while rotating the pre-mounted assembly.
  • the finger presses the button of the locking component with a certain force to rotate the rotating ring of the pre-installed component, and then the pan-tilt 200 can be directly pulled out, and the pan-tilt 200 can be simply and stably completed without tools.
  • the assembly and disassembly work with the unmanned aircraft body 110 can also protect and dissipate the circuit to ensure the normal operation of the gimbal and the unmanned aerial vehicle.
  • the unmanned aerial vehicle 100 includes a fuselage 110, a propeller 102 and a propeller 104 mounted on the fuselage 110, an unmanned aerial vehicle circuit connection terminal, a pan/tilt head 200, and a detachable connection.
  • the UAV 100 in this embodiment employs a quadrotor UAV.
  • the UAV uses four small propellers with flexible flight safety controls to achieve six degrees of freedom.
  • the fuselage 110 is provided with a fuselage connection plate 120, and the fuselage connection plate 120 includes an alignment groove 124 and a buckle 122 that cooperates with the pre-fixing device.
  • the buckle 122 has a set angle of inclination.
  • the fuselage connecting plate 120 is provided with three pairs of alignment grooves 124 and buckles 122.
  • the fuselage connecting plate 120 is fixedly provided with a buffer layer 132.
  • the buffer layer 132 is a silica gel layer or a buffering elastic material layer.
  • the buffer layer 132 is interposed on the body connecting plate 120 via the buffer fixing plate 130.
  • the buffer layer may have other embodiments, such as being fixed on the pan/tilt connection device 300 of the pan/tilt head 200, and only the pan/tilt head 200 and the body 110 are assembled, and the pan/tilt head and the body are firmly fastened.
  • the pan-tilt connection device 300 includes an alignment assembly, a pre-installation assembly disposed on the alignment assembly, and a locking assembly.
  • the alignment assembly is fixed on the platform 200 for aligning the UAV circuit connection terminal with the PTZ circuit connection terminal.
  • a pre-installation assembly disposed on the alignment assembly that secures the pan-tilt connection to the fuselage connection plate 120 of the fuselage 110 relative to the alignment assembly movement.
  • a locking assembly disposed on the pre-installation assembly that locks the pre-installed assembly when the pre-mounted assembly is moved relative to the alignment assembly to a predetermined position.
  • the alignment assembly includes a pan-tilt connection plate 70 fixed to the pan/tilt head 200, and a fixed cover 30 fixed to the pan-tilt connection plate 70, and at least one slide path is formed between the pan-tilt connection plate and the fixed cover. In the present embodiment, three slides are formed.
  • the pan/tilt connection plate 70 is provided with a plurality of circular friction ribs 73 on the side facing the fixed cover 30.
  • the pre-installation assembly is a rotating ring 40.
  • the rotating ring 40 is rotatably mounted in a slide formed between the pan-tilt connecting plate 70 and the fixed cover 30, and is rotatable relative to the pan-tilt connecting plate 70 and the fixed cover 30.
  • the inner wall of the rotating ring 40 corresponds to the three pairs of alignment grooves 124 and the buckles 122 provided by the fuselage connecting plate 120 to form three buckles 42.
  • the rotating ring 40 is rotatably mounted on the pan/tilt connection plate 70 When the cover 30 is fixed, the three buckles 42 are each located in the corresponding three slides. When the rotating ring 40 is rotated, the plurality of snaps 42 slide along the rotating ring 40 in the slide.
  • a pair of alignment marks are disposed on the rotation ring 40 and the fuselage connection plate 120.
  • the three pairs of alignment grooves 124 and the buckles 122 provided on the body 110 correspond to the three buckles 42 provided on the rotating ring 40.
  • the pre-fixing process is entered after the alignment of the pan/tilt 200 with the fuselage 110 is completed.
  • the buckle 42 of the rotating ring 40 has partially protruded into the alignment groove 124 of the body connecting plate 120.
  • the rotating ring 40 is rotated such that the plurality of buckles 42 on the inner side of the rotating ring 40 slide in the slide, and the buckle 42 climbs from the alignment groove 124 to the buckle 122 on the side of the alignment groove 124.
  • the angle of inclination of the contact surface of the buckle 122 and the buckle 42 ensures that the buckle 42 is fastened to the buckle 122 of the fuselage connection plate 120 after the end of the rotation of the slide.
  • the locking assembly is disposed within the rotating ring 40 .
  • the disassembly button 50, the spring 58, the stroke control structure, and the locking structure are included.
  • the pan/tilt connection plate 70 is provided with a mounting groove 71 for mounting a locking assembly.
  • the detaching button 50 of the locking assembly is provided with a mounting shaft 56, and the spring 58 is sleeved on the mounting shaft 56, and the end abuts in the mounting groove 71.
  • the stroke of the disassembly button 50 that is elastically disposed in the mounting groove 71 is limited by the control structure.
  • the stroke control structure includes two guide grooves 52 formed on one side of the detaching button 50 and two limit posts (not shown) provided in the mounting groove 71.
  • the locking structure includes a guide groove 60 formed on the other side of the detaching button and a buckle 64 protruding from the detaching button 50. The end of the guiding groove 60 is twisted back to form a receiving cavity 62, and the inlet of the guiding groove 60 is a flared wide opening.
  • pan/tilt connection device 300 Please refer to the pan/tilt connection device 300 shown in FIG. 2 at the same time, wherein the mounting groove 71 of the pan-tilt connection plate 70 is further provided with a fixing rod 66.
  • the fixing rod 66 in the mounting groove 71 is located at the flared inlet of the guiding groove 60, and before the stroke of the buckle 42 of the rotating ring 40 is completed, the fixing rod 66 has a certain distance from the flared inlet of the guide groove 60; when the buckle 42 When the fastening stroke of the buckle edge 122 reaches a predetermined position, the fixing rod 66 enters the flared inlet of the guide groove 60; when the buckle 42 is completed during the fastening stroke of the buckle edge 122, the fixing rod 66 guides The flared inlet of the slot 60 passes over the buckle 64 into the receiving cavity 62 and is within the receiving cavity 62 at the lower limit of the blocking of the buckle 64.
  • the pan/tilt connection plate 70 is provided with a plurality of friction ribs 73 on the fixed cover 30.
  • the purpose of the friction ribs 73 is to increase the frictional force of the rotation of the rotating ring 40 to make the rotating ring 40 have a more stable hand when rotating, and to prevent the rotating ring from rotating to avoid affecting the pre-fixing step of the operation.
  • the pan/tilt connection device of the present application integrally forms a wind guiding cavity.
  • heat is generated between the UAV circuit connection terminal and the PTZ circuit connection terminal, and heat accumulation affects product performance.
  • a fan is installed at one end of the air guiding cavity, and a bottom-up adsorption force is generated inside the UAV body 110 and the PTZ 200.
  • the detachable head of the present application makes full use of the air.
  • the adsorption force forms a heat dissipation air passage in the gimbal connection device, extracts the heat generated by the cloud platform, optimizes the working environment of the circuit, and improves the service life of the cloud platform and the unmanned aerial vehicle.
  • the structure of the heat dissipating air passage is composed of the following: the fixing cover 30 is provided with an opening 31, the buffer layer 132 is provided with an opening 133, and the buffer fixing plate 130 is provided with an opening 131, and the body connecting plate 120 is provided with an opening 125.
  • the center of the rotating ring 40 forms an opening 41.
  • a heat dissipating air passage for the UAV circuit and the PTZ circuit is formed.
  • the heat dissipation air passage is from the periphery of the rotating ring 40, through the opening 41 of the rotating ring 40, the opening 31 of the fixing cover 30, the opening 131 of the buffer fixing plate 130, the opening 133 of the buffer layer 132, and the opening from the body connecting plate 120. Scattered around 125.
  • the head mounted with the pan-tilt connection device 300 is aligned with the fuselage connecting plate 120 installed under the fuselage 110, so that the UAV circuit is connected.
  • the terminal is aligned with the pan-tilt circuit connection terminal to complete the alignment step.
  • the buckle 42 of the rotating ring 40 of the rotating ring 40 is partially extended into the alignment groove 124 of the fuselage connecting plate 120.
  • the rotating ring 40 is rotated, so that the plurality of buckles 42 on the inner side of the rotating ring 40 slide in the slide, and the buckle 42 climbs up from the alignment groove 124.
  • the buckle 122 on one side of the groove 124.
  • the angle of inclination of the contact surface of the buckle 122 and the buckle 42 ensures that the buckle 42 is fastened to the buckle 122 of the fuselage connection plate 120 after the end of the rotation of the slide.
  • the locking assembly prevents the rotation ring 40 from retreating to loosen the buckle 42 and the buckle 122, and the fixing rod 66 slides in.
  • the receiving cavity 62 of the button guide groove 60 is disassembled to lock the fastening between the pan/tilt and the body.
  • the fixing rod 66 enters the flared inlet of the guide groove 60, and as the buckle 42 is further rotated on the buckle edge 122, The fixing rod 66 enters the receiving cavity 62 from the flared inlet of the guiding groove 60 beyond the buckle 64 and is located in the receiving cavity 62 at the lower limit of the blocking of the buckle 64, while the spring end of the locking assembly dismounting button 58 is pressed against Between the inner wall surface of the mounting groove 71 and the detaching button, the rotating ring 40 and the pan/tilt head 200 are locked by the elastic force thereof.
  • the disassembly button 50 When disassembling, only one hand presses the disassembly button 50, and the other hand holds the gimbal 200 at a certain angle to directly pull out the gimbal 200. Specifically, when the button 50 is detached, the inwardly moving detachment button 50 compresses the spring, and the fixed lever 66 disengages from the accommodating cavity 62 while rotating the rotating ring 40, which is detached from the flared inlet over the buckle 64. At the same time, the three buckles 42 of the rotating ring 40 are also returned from the buckle edge 122 to the alignment groove 124, and the removal of the pan/tilt is completed.
  • the connecting terminal only needs to maintain electrical contact without repeated friction when disassembling, which reduces the mechanical loss of the circuit connecting terminal and improves the service life of the unmanned aerial vehicle.
  • the pre-installation assembly and the locking assembly are easy to operate, and can be fixed and disassembled by simple rotation or pressing and rotating operations.
  • the pan/tilt connection plate 70 is provided with a plurality of friction ribs 73 to provide a more delicate hand for the user to operate the rotary ring 40.
  • the detachable cloud platform of the present application, the fixed cover 30 or the fuselage connecting plate 110 is provided with a buffer layer, which reduces the influence of the vibration of the unmanned aerial vehicle on the circuit and the device during take-off and landing.
  • the pan-tilt connection device 300 integrally forms a wind guide cavity to prevent heat accumulation between the UAV circuit connection terminal and the PTZ circuit connection terminal from affecting product performance
  • the PTZ connection of the present application is A heat dissipation air duct is formed in the device to set a fan, and the heat generated by the pan/tilt circuit is extracted, and optimized
  • the circuit working environment has improved the service life of the gimbal and the unmanned aerial vehicle.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)
  • Accessories Of Cameras (AREA)
  • Casings For Electric Apparatus (AREA)
  • Automatic Assembly (AREA)
  • Toys (AREA)

Abstract

一种可拆卸云台连接装置(300)以及无人飞行器(100)，该可拆卸云台连接装置(300)包括：对准组件，该对准组件用于对准无人飞行器(100)电路连接端子与云台(200)电路连接端子；设置在对准组件上的预安装组件(40)，该预安装组件(40)相对于该对准组件运动将该云台(200)连接固定至该无人飞行器(100)的机身(110)；以及设置在预安装组件(40)上的锁紧组件，该预安装组件(40)相对于对准组件运动至预设位置时该锁紧组件锁紧该预安装组件(40)。使用该云台连接装置(300)的云台(200)在安装至机身(110)的同时能够保证无人飞行器(100)和云台(200)的电性连接，将无人飞行器(100)和云台(200)之间电路连接端子之间的对准放在首位，对准后再固定减少了电路连接端子的机械使用，提高了无人飞行器(100)的使用寿命。

Description

一种可拆卸云台连接装置及无人飞行器 技术领域
本申请实施方式涉及无人机领域，特别是涉及一种可拆卸云台的电路保护装置与相应的无人飞行器。
背景技术
随着无线互联和图像处理技术的发展，无人机的功能越来越强大也得到更多用户的青睐。为了实现无人机的图像获取，需要在无人机上搭载安装摄像头组的云台。云台与无人机机身一体成型。更多无人机设计中该云台与无人机机身是可拆卸的。
目前无人飞行器上采用的云台固定装置一般采用是紧固云台的三轴结构，用户在使用时很不方便，不易组装和拆卸，且经常侧向插入时，电路连接端子之间因为机械使用磨损接触使得连接端子容易损坏导致云台无法工作等问题。
中国专利申请号：201610107361.5披露了一种云台可拆卸的无人机，包括机身和云台，云台上设置有摄像组件，机身与云台可拆卸连接。其中，云台与机身的安装为：机壳102在对应固定部110的位置设置有通槽112。通槽112形成分段式滑轨106，安装云台时，滑块205在轨106滑动到位后，卡紧装置包括卡块206，机壳102上设置有凹槽109，卡块206与凹槽109配合。通过卡块206卡紧于凹槽109将云台固定在机身上。卡紧装置在工作时，首先滑块205滑动到位，卡块206嵌入凹槽109，通过卡块206卡紧于凹槽109，将云台201设有卡块206的一侧卡紧于机壳102上，再配合云台201上的滑块205与机壳102上的滑轨106之间的配合，从而将云台201地与机壳102连接(说明书第4页)。
但是该种云台在拆卸安装时，每次需要滑块205在滑轨106中滑行到位，滑块205上的电路连接端子在拆卸中容易出现磨损，影响云台图 像数据的传输，或者最终导致云台无法工作。
因此，现有无人机机身与云台的固定连接技术还有待于改进和发展。
发明内容
本申请实施方式主要解决的技术问题是提供一种可拆卸云台的电路保护装置与相应的可拆卸云台和无人飞行器。使用该云台连接装置的云台在安装至机身的同时能够保证无人飞行器和云台的电性连接，将无人飞行器和云台之间电路连接端子之间的对准放在首位，对准后再固定减少了电路连接端子的机械使用，提高了无人飞行器的使用寿命。并且预安装组件和锁紧组件操作方便简单，只需简单旋转或者按压和旋转操作即可实现固定和拆卸。
为解决上述技术问题，第一方面，本申请实施方式提供的一个技术方案是：
提供一种可拆卸云台连接装置，包括：
对准组件，该对准机构用于对准无人飞行器电路连接端子与云台电路连接端子；
设置在对准组件上的预安装组件，该预安装组件相对于对准组件运动将该云台连接固定至该无人飞行器的机身；以及
设置在预安装组件上的锁紧组件，该预安装组件相对于对准组件运动至预设位置时该锁紧组件锁紧该预安装组件。
为解决上述技术问题，第二方面，本申请实施方式采用的另一个技术方案是：
提供一种无人飞行器，包括机身、无人飞行器电路连接端子、云台以及云台电路连接端子，包括用于可拆卸连接无人飞行器和云台的云台连接装置，该云台连接装置包括：
对准组件，该对准组件固定在该云台上，用于对准无人飞行器电路连接端子与云台电路连接端子；
设置在对准组件上的预安装组件，该预安装组件相对于对准组件运 动将该云台连接固定至该机身；以及
设置在预安装组件上的锁紧组件，该预安装组件相对于对准组件运动至预设位置时该锁紧组件锁紧该预安装组件。
为解决上述技术问题，第三方面，本申请实施方式采用的再一个技术方案是：
提供一种拆卸式云台，包括用于可拆卸连接无人飞行器和云台的云台连接装置，该云台连接装置包括：
对准组件，该对准组件固定在该云台上，用于对准无人飞行器电路连接端子与云台电路连接端子；
设置在对准组件上的预安装组件，该预安装组件相对于对准组件运动将该云台连接固定至该机身；以及
设置在预安装组件上的锁紧组件，该预安装组件相对于对准组件运动至预设位置时该锁紧组件锁紧该预安装组件。
本申请实施方式的有益效果是：本实施例中提供的云台连接装置以及可拆卸云台和无人飞行器，设置对准组件，优先保证无人飞行器和云台之间电路连接端子的电性连接，使得无人飞行器和云台之间电路连接端子只需保持电性接触避免了拆卸时的反复摩擦，减少了电路连接端子的机械损耗，提高了无人飞行器的使用寿命。并且设置的预安装组件和锁紧组件操作方便简单，只需简单旋转或者按压和旋转操作即可实现固定和拆卸。
附图说明
图1是本申请实施方式的无人飞行器的立体结构示意图；
图2是本申请实施方式的无人飞行器的云台拆卸状态图；
图3是本申请实施方式的可拆卸云台连接装置的立体分解图；
图4是本申请实施方式的可拆卸云台连接装置的组装立体图；
图5是本申请实施方式的可拆卸云台连接装置的另一组装立体图；
图6是本申请实施方式的可拆卸云台连接装置锁紧组件的按钮立体结构图；以及
图7是本申请实施方式的可拆卸云台连接装置锁紧组件的按钮另一视角立体结构图。
具体实施方式
为使本申请实施例的目的、技术方案和优点更加清楚明白，下面结合附图对本申请实施例做进一步详细说明。在此，本申请的示意性实施例及其说明用于解释本申请，但并不作为对本申请的限定。
本申请涉及一种可拆卸云台的连接装置与相应的可拆卸云台和无人飞行器。
设置该云台连接装置的云台在可拆卸安装至无人飞行器机身的同时首先保证无人飞行器和云台的电性连接，并通过设置对准组件，优先保证无人飞行器和云台之间电路连接端子的电性连接，并且预安装组件和锁紧组件的工作不影响对准组件，充分减少了云台安装拆卸过程中的反复摩擦的机械损耗，提高了无人飞行器的使用寿命。并且，本申请实施例设置的预安装组件和锁紧组件操作方便简单，只需简单旋转或者按压和旋转操作即可实现固定和拆卸。
请参考图1，本申请的云台连接装置300通过固定在云台上的预安装组件部份插入固定在无人飞行器上的机身连接板，并通过将预安装组件旋转一定的角度再由锁紧组件锁住预安装组件，使其不能转动从而将云台200固定在无人飞行器100。该预安装组件和锁紧组件操作方便简单，只需简单旋转预安装组件或者按压锁紧组件同时旋转预安装组件的操作即可实现固定和拆卸云台。具体来说，取出云台时，手指用一定的力按下锁紧组件的按键，旋转预安装组件的旋转环，然后可直接拔出云台200，无需工具即可简单稳固地完成云台200与无人飞行器机身110之间的装配与拆卸工作，同时能对电路起到保护和散热的作用，以保障云台和无人飞行器的正常工作。
请一并参考图2和图3，所示无人飞行器100包括机身110、安装在机身110上的螺旋桨102和螺旋桨104、无人飞行器电路连接端子、云台200、用于可拆卸连接无人飞行器和云台的连接装置300以及云台 电路连接端子。
本实施例中的无人飞行器100采用四旋翼无人机。无人飞行器采用四个小巧的螺旋桨，具有飞行安全控制灵活等特点，能够实现六个自由度的飞行。
为了与云台连接装置300实现安装固定，该机身110上装设机身连接板120，该机身连接板120包括对位槽124以及与预固定装置配合的扣边122。该扣边122具有设定的倾斜角。本申请实施例中，该机身连接板120设置三对对位槽124和扣边122。
为了减少无人飞行器在起降中产生的震动冲击，该机身连接板120固定设置有缓冲层132，本申请实施例中，该缓冲层132为硅胶层，或者具有缓冲作用的弹性材料层。该缓冲层132通过缓冲固定板130夹设在该机身连接板120上。
该缓冲层也可以有其它实施方式，比如固定在云台200的云台连接装置300上，只须保证云台200与机身110组装后云台与机身稳固扣合。
云台连接装置300的具体结构请参考图3，该云台连接装置300包括对准组件、设置在对准组件上的预安装组件以及锁紧组件。该对准组件固定在该云台200上，用于对准无人飞行器电路连接端子与云台电路连接端子。设置在对准组件上的预安装组件，该预安装组件相对于对准组件运动将该云台连接固定至该机身110的机身连接板120上。设置在预安装组件上的锁紧组件，该预安装组件相对于对准组件运动至预设位置时该锁紧组件锁紧该预安装组件。
该对准组件包括固定在云台200的云台连接板70、以及固定在云台连接板70的固定盖30，该云台连接板和固定盖之间形成至少一滑道。本实施方式中，形成三个滑道。该云台连接板70面对固定盖30一侧设置若干圆形摩擦筋73。
该预安装组件为旋转环40。该旋转环40可转动安装在云台连接板70与固定盖30之间形成的滑道内，并可相对于云台连接板70和固定盖30转动。该旋转环40内壁对应机身连接板120设置的三对对位槽124和扣边122形成三个卡扣42。该旋转环40转动安装在云台连接板70与 固定盖30之间时，该三个卡扣42各自位于对应的三个滑道内。旋转该旋转环40时，多个卡扣42随着旋转环40在滑道内滑动。
为了准确与无人飞行器10的机身连接板120对准同时对准无人飞行器电路连接端子与云台电路连接端子，该旋转环40和机身连接板120上设置一对对准标识。
当该旋转环40的对准标识对齐该机身连接板120的对准标识时，此时无人飞行器电路连接端子与云台电路连接端子准确对准。
该机身110上设置的三对对位槽124以及扣边122，与旋转环40设置的三个卡扣42对应。
在完成云台200与机身110的对准之后进入预固定过程。完成对准以后，旋转环40的卡扣42已部分伸入机身连接板120的对位槽124内。转动旋转环40，使得旋转环40内侧的多个卡扣42在滑道内滑动，同时卡扣42从对位槽124爬上对位槽124一侧的扣边122。该扣边122与卡扣42的接触面设定的倾斜角保证卡扣42在滑道的转动行程结束后，正好扣紧在该机身连接板120的扣边122上。
请参考图6以及图7，该锁紧组件设置在旋转环40内。包括拆卸按钮50、弹簧58、行程控制结构以及锁紧结构。
该云台连接板70设置用于安装锁紧组件的安装槽71。该锁紧组件的拆卸按钮50设置安装轴56，该弹簧58套设在该安装轴56上，末端抵靠在组装在该安装槽71内。弹性设置在安装槽71的拆卸按钮50的行程由控制结构进行限位。该行程控制结构包括形成在拆卸按钮50一侧的两导槽52以及设置在安装槽71的两限位柱(图未示)。该锁紧结构包括形成在拆卸按钮另一侧的导槽60和凸设在拆卸按钮50的挡扣64。该导槽60末端迂回形成一收容腔62，导槽60的入口为喇叭形阔口。
请同时参考图2所示的云台连接装置300，其中，该云台连接板70的安装槽71内还设置有固定杆66。
该锁紧组件安装在安装槽71后，安装槽71内的固定杆66正好位于导槽60的喇叭形入口处，在旋转环40的卡扣42在该扣边122行程完成之前，该固定杆66与导槽60的喇叭形入口有一定距离；当卡扣42 在该扣边122的扣合行程到预定位置时，该固定杆66进入导槽60的喇叭形入口；当卡扣42在该扣边122的扣合行程完成过程中，该固定杆66从导槽60的喇叭形入口越过挡扣64进入收容腔62并在挡扣64的阻挡下限位在该收容腔62内。
本申请实施例中，该云台连接板70面对固定盖30上设置若干摩擦筋73。
该摩擦筋73设置的目的是为了增加旋转环40转动的摩擦力使旋转环40在转动时有更稳定的手感，并且防止旋转环回转以免影响操作完成的预固定步骤。
请参考图5，本申请的云台连接装置，整体中空形成一导风腔。在无人飞行器工作过程中，无人飞行器电路连接端子与云台电路连接端子之间会产生热量，热量积聚影响产品性能。本申请实施例中，该导风腔的一端安装风扇，在无人机机身110和云台200内部产生一股自下而上的吸附力，本申请的可拆卸云台充分利用该种空气吸附力，在云台连接装置内形成散热风道，抽出云台产生的热量，优化了电路工作环境，提高了云台以及无人飞行器的使用寿命。
该散热风道的结构由以下组成：该固定盖30设置开口31，该缓冲层132设置开口133，该缓冲固定板130设置开口131，该机身连接板120设置开口125。该旋转环40中心形成开口41。结合该旋转环40的开口41共同形成对无人飞行器电路和云台电路的散热风道。该散热风道为从旋转环40外围起，经过旋转环40的开口41、固定盖30的开口31、缓冲固定板130的开口131、缓冲层132的开口133并从机身连接板120的开口125四周散出。
安装时，根据旋转环40和机身连接板120上设置对准标识，将组装有云台连接装置300的云台对准机身110下方安装的机身连接板120，使得无人飞行器电路连接端子与云台电路连接端子对准，完成对准步骤。对准以后旋转环40的旋转环40的卡扣42已部分伸入机身连接板120的对位槽124内。开始预固定步骤，转动旋转环40，使得旋转环40内侧的多个卡扣42在滑道内滑动，同时卡扣42从对位槽124爬上对位 槽124一侧的扣边122。该扣边122与卡扣42的接触面设定的倾斜角保证卡扣42在滑道的转动行程结束后，正好扣紧在该机身连接板120的扣边122上。在预固定步骤过程中，卡扣42在的扣边122滑动到扣紧位置时，该锁紧组件为防止旋转环40后退使卡扣42与扣边122之间固定松动，固定杆66滑入拆卸按钮导槽60的收容腔62内，锁紧云台与机身之间的扣合。具体来说，当卡扣42在扣边122的接触面上转动到预定位置时，该固定杆66进入导槽60的喇叭形入口，并随着卡扣42在扣边122上的进一步转动，该固定杆66从导槽60的喇叭形入口越过挡扣64进入收容腔62并在挡扣64的阻挡下限位在该收容腔62内，同时锁紧组件拆卸按钮58上的弹簧末端抵紧在安装槽71内壁面和拆卸按钮之间，利用其弹性力锁住旋转环40和云台200。
拆卸时，只需一手按压拆卸按钮50，另一只手托住云台200旋转一定的角度即可直接拔出云台200。具体来说，当压拆卸按钮50时，向内移动的拆卸按钮50压缩弹簧，该固定杆66脱离收容腔62，同时转动旋转环40，该固定杆66越过挡扣64从喇叭形入口退出。同时旋转环40的三个卡扣42也从扣边122退回到对位槽124处，此时即完成云台的拆卸。
本申请的云台连接装置以及可拆卸云台和无人飞行器，该对准组件可优先保证无人飞行器和云台之间电路连接端子的电性连接，使得无人飞行器和云台之间电路连接端子只需保持电性接触不需要拆卸时的反复摩擦，减少了电路连接端子的机械损耗，提高了无人飞行器的使用寿命。并且该预安装组件和锁紧组件操作方便简单，只需简单旋转或者按压和旋转操作即可实现固定和拆卸。同时，该云台连接板70上设置若干摩擦筋73，为用户在操作旋转环40提供更细腻的手感。本申请的可拆卸云台，该固定盖30或者机身连接板110上设置缓冲层，减少了无人飞行器在起降时震动对电路和设备的影响。在进一步的改进中，该云台连接装置300整体中空形成导风腔，以避免无人飞行器电路连接端子与云台电路连接端子之间产生的热量积聚影响产品性能，本申请的在云台连接装置内形成散热风道设置风扇，抽出云台电路产生的热量，优化 了电路工作环境，提高了云台以及无人飞行器的使用寿命。
以上所述仅为本申请的实施方式，并非因此限制本申请的专利范围，凡是利用本申请说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本申请的专利保护范围内。

Claims (21)

  1. 一种可拆卸云台连接装置，其特征在于，包括：
    对准组件，所述对准机构用于对准无人飞行器电路连接端子与云台电路连接端子；
    设置在对准组件上的预安装组件，所述预安装组件相对于对准组件运动将所述云台连接固定至所述无人飞行器的机身；以及
    设置在预安装组件上的锁紧组件，所述预安装组件相对于对准组件运动至预设位置时所述锁紧组件锁紧所述预安装组件。
  2. 根据权利要求1所述的可拆卸云台连接装置，其特征在于，所述对准组件包括固定在云台的云台连接板、以及固定在云台连接板的固定盖，所述云台连接板和固定盖之间形成至少一滑道。
  3. 根据权利要求2所述的可拆卸云台连接装置，其特征在于，所述云台连接板上设置若干摩擦筋。
  4. 根据权利要求3所述的可拆卸云台连接装置，其特征在于，所述预安装组件包括安装在所述至少一滑道内并可相对于云台连接板和固定盖转动的旋转环，所述旋转环对应滑道设置至少一可扣合在无人飞行器机身的卡扣，其中，所述旋转环上设置对准标识。
  5. 根据权利要求4所述的可拆卸云台连接装置，其特征在于，所述旋转环设置用于安装锁紧组件的安装槽，所述锁紧组件包括通过弹簧组装在所述安装槽内的拆卸按钮、拆卸按钮的行程控制结构以及锁紧结构，其中，所述行程控制结构包括形成在拆卸按钮一侧的两导槽以及设置在安装槽的两限位柱，所述锁紧结构包括形成在拆卸按钮另一侧的导槽和挡扣。
  6. 根据权利要求1-5任一项所述的可拆卸云台连接装置，其特征在于，所述固定盖上设置缓冲层。
  7. 根据权利要求6所述的可拆卸云台连接装置，其特征在于，所述固定盖和缓冲层均设置开口，结合所述旋转环的开口共同形成对无人飞行器电路和云台电路的散热风道。
  8. 一种无人飞行器，包括机身、无人飞行器电路连接端子、云台以及云台电路连接端子，其特征在于，包括用于可拆卸连接无人飞行器和云台的云台连接装置，所述云台连接装置包括：
    对准组件，所述对准组件固定在所述云台上，用于对准无人飞行器电路连接端子与云台电路连接端子；
    设置在对准组件上的预安装组件，所述预安装组件设置相对于对准组件运动将所述云台连接固定至所述机身；以及
    设置在预安装组件上的锁紧组件，所述预安装组件相对于对准组件运动至预设位置时所述锁紧组件锁紧所述预安装组件。
  9. 根据权利要求8所述的无人飞行器，其特征在于，所述对准组件包括固定在云台的云台连接板、以及固定在云台连接板的固定盖，所述云台连接板和固定盖之间形成至少一滑道。
  10. 根据权利要求9所述的无人飞行器，其特征在于，所述云台连接板上设置若干摩擦筋。
  11. 根据权利要求9所述的无人飞行器，其特征在于，所述固定盖上设置缓冲层。
  12. 根据权利要求10所述的无人飞行器，其特征在于，所述预安装组件包括安装在所述至少一滑道内并可相对于云台连接板和固定盖转动的旋转环，所述旋转环对应滑道设置至少一可扣合在无人飞行器机身的卡扣，其中，所述旋转环上设置对准标识。
  13. 根据权利要求12所述的无人飞行器，其特征在于，所述机身上装设机身连接板，所述机身连接板设置用于导入卡扣的对位槽以及与卡扣配合的扣边，所述扣边与卡扣的接触面具有设定的倾斜角。
  14. 根据权利要求13所述的无人飞行器，其特征在于，所述机身连接板固定设置有缓冲层，所述缓冲层通过缓冲固定板夹设在所述机身连接板上。
  15. 根据权利要求14所述的无人飞行器，其特征在于，所述旋转环设置用于安装锁紧组件的安装槽，所述锁紧组件包括通过弹簧组装在所述安装槽内的拆卸按钮、拆卸按钮的行程控制结构以及锁紧结构，其中， 所述行程控制结构包括形成在拆卸按钮一侧的两导槽以及设置在安装槽的两限位柱，所述锁紧结构包括形成在拆卸按钮另一侧的导槽和挡扣。
  16. 根据权利要求15所述的无人飞行器，其特征在于，所述固定盖、缓冲层、缓冲固定板以及机身固定板均设置开口，结合所述旋转环的开口共同形成对无人飞行器电路和云台电路的散热风道。
  17. 一种拆卸式云台，其特征在于，包括用于可拆卸连接无人飞行器和云台的云台连接装置，所述云台连接装置包括：
    对准组件，所述对准组件固定在所述云台上，用于对准无人飞行器电路连接端子与云台电路连接端子；
    设置在对准组件上的预安装组件，所述预安装组件相对于对准组件运动将所述云台连接固定至所述机身；以及
    设置在预安装组件上的锁紧组件，所述预安装组件相对于对准组件运动至预设位置时所述锁紧组件锁紧所述预安装组件。
  18. 根据权利要求17所述的拆卸式云台，其特征在于，所述对准组件包括固定在云台的云台连接板、以及固定在云台连接板的固定盖，所述云台连接板和固定盖之间形成至少一滑道。
  19. 根据权利要求18所述的拆卸式云台，其特征在于，所述预安装组件包括安装在所述至少一滑道内并可相对于云台连接板和固定盖转动的旋转环，所述旋转环对应滑道设置至少一可扣合在无人飞行器机身的卡扣，其中，所述旋转环上设置对准标识。
  20. 根据权利要求17-19所述的拆卸式云台，其特征在于，所述固定盖上设置缓冲层。
  21. 根据权利要求20所述的拆卸式云台，其特征在于，所述固定盖和缓冲层设置开口，结合所述旋转环的开口共同形成对无人飞行器电路和云台电路的散热风道。
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