WO2017071338A1 - 云台快速装拆装置以及具有其的无人机 - Google Patents

云台快速装拆装置以及具有其的无人机 Download PDF

Info

Publication number
WO2017071338A1
WO2017071338A1 PCT/CN2016/091778 CN2016091778W WO2017071338A1 WO 2017071338 A1 WO2017071338 A1 WO 2017071338A1 CN 2016091778 W CN2016091778 W CN 2016091778W WO 2017071338 A1 WO2017071338 A1 WO 2017071338A1
Authority
WO
WIPO (PCT)
Prior art keywords
assembly
pan
pedestal
fuselage
tilt
Prior art date
Application number
PCT/CN2016/091778
Other languages
English (en)
French (fr)
Inventor
梁智颖
邱龙学
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
Priority to EP16858777.2A priority Critical patent/EP3351845B1/en
Publication of WO2017071338A1 publication Critical patent/WO2017071338A1/zh
Priority to US15/958,530 priority patent/US10919645B2/en

Links

Images

Classifications

    • 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
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • 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
    • 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
    • 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
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • 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
    • 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

Definitions

  • the present application relates to the field of cloud platforms, and in particular to a cloud platform quick assembly and disassembly device and a drone having the same.
  • the gimbal is mounted on a carrier as a supporting device for installing and fixing an electric device such as a camera, and is widely used in the fields of photography, photography, monitoring, and the like.
  • the PTZ is usually fixed on the body of the UAV as a carrier, and the camera (such as a camera and camera) for aerial photography is mounted through the PTZ to obtain a specific type of environment.
  • Information (such as remote sensing images).
  • the pan/tilt in the prior art is directly connected to the drone, and most of the two are locked and fixed by screws.
  • the pan/tilt and camera equipment are installed on the drone before the task is performed, and only the shooting equipment equipped with the threaded holes of a specific specification can be used with the pan/tilt.
  • the assembly structure reduces the versatility of the gimbal.
  • the disassembly and assembly operation is complicated and the efficiency is low.
  • the thread is excessively worn and the durability is poor, which is disadvantageous for the rapid execution of the drone. task.
  • the technical problem to be solved by the present application is to overcome the technical problems of poor versatility of the pan/tilt in the prior art and complicated and inefficient operation of the disassembly and assembly operation of the photographing device.
  • the present application provides a pan/tilt quick assembly and disassembly device, including a fuselage base assembly, a cloud pedestal assembly, and a locking assembly, wherein the fuselage base assembly is fixedly mounted on the carrier; the cloud pedestal assembly is fixed.
  • the cloud pedestal assembly includes a cloud pedestal; the locking assembly is mounted on the fuselage mount assembly or the cloud pedestal assembly, and the locking assembly detachably mounts the cloud pedestal assembly and the fuselage mount assembly such that The gimbal is detachably mounted on the carrier.
  • the fuselage base assembly comprises a fuselage seat
  • the fuselage mount has a fuselage seat receiving slot opening toward the pan head
  • the pan rest is movably received in the fuselage seat receiving slot
  • the locking component is mounted on the fuselage On the seat.
  • the fuselage base assembly comprises a fuselage seat
  • the cloud mount has a cloud platform receiving slot opening toward the fuselage seat
  • the fuselage mount is movably received in the cloud platform receiving slot
  • the locking component is mounted on the cloud platform .
  • a side wall of the cloud pedestal receiving slot is provided with a button hole extending through the outer wall of the pedestal, and a fixing post is protruded outwardly from the inner wall of the pedestal receiving slot;
  • the locking component comprises a button and a torsion spring, and the button is movably inserted In the button hole, the torsion spring is sleeved on the fixing column, and the rotating arm at one end of the torsion spring abuts the top button, so that the button is pushed inward and then returned to the initial position by the action of the rotating arm.
  • the button has a vertical plate-shaped baffle, and a middle surface of the baffle surface protrudes horizontally outwardly to form a substrate, and the substrate is provided with a lock groove; the surface of the body frame facing the pan pedestal corresponds to the button convex outward
  • the utility model is provided with a lock core, and the lock core is slidably held in the lock groove, so that the fuselage seat is movably disassembled and assembled in the pedestal receiving groove.
  • the direction of the button pressing is the A direction
  • the opening direction of the locking slot is the B direction perpendicular to the moving direction of the button
  • the direction of the mounting of the pedestal is the same as the opening direction of the locking slot
  • the direction of the removal of the pedestal and the opening direction of the locking slot On the contrary, the disassembly direction of the pedestal is inconsistent with the pushing direction of the button.
  • the side wall of the cloud pedestal receiving slot mounting button and the side wall of the side wall protrude inwardly with a plurality of guiding blocks; the body seat protrudes outwardly corresponding to the position of the guiding block on the pedestal seat A plurality of guiding grooves are formed, and the guiding blocks slide in the guiding grooves to realize accurate sliding installation of the gimbal.
  • the body mount assembly further comprises a fuselage circuit adapter board, and the fuselage circuit adapter board is mounted on the fuselage mount;
  • the cloud mount component further comprises a pan/tilt circuit adapter board, and the pan/tilt circuit adapter board is mounted on the On the cloud pedestal, when the cloud pedestal component is mounted on the fuselage mount assembly, the fuselage circuit adapter board is in electrical contact with the pan-tilt circuit adapter board to achieve signal transmission.
  • the fuselage seat of the fuselage base assembly is recessed in the mounting surface of the mounting carrier to form a receiving slot, and the fuselage circuit adapter plate is received in the receiving slot; the cloud platform of the cloud platform assembly is located at the mounting platform The mounting surface is recessed to form a mounting slot, and the pan/tilt circuit adapter board is installed in the mounting slot.
  • the bottom wall of the accommodating groove is provided with a first through hole penetrating the outer surface of the body seat, and the bottom of the groove is installed a second through hole penetrating through the bottom wall of the gimbal receiving groove is formed in the wall, and when the cloud pedestal assembly is mounted on the body frame assembly, the fuselage circuit adapter plate and the pan/tilt circuit adapter plate pass through the first through hole and The second through hole is in electrical contact.
  • a plurality of conductive contacts are disposed on a side of the fuselage circuit adapter plate facing the pan-tilt circuit adapter board, and the side of the pan-tilt circuit adapter board facing the fuselage circuit adapter board corresponds to the body circuit
  • the conductive contact piece of the board is provided with a plurality of touch type elastic pieces. When the cloud pedestal assembly is mounted on the body seat assembly, the touch type elastic piece is in electrical contact with the conductive contact piece.
  • the fuselage base assembly further comprises a cable cover plate, the cable cover plate is mounted on the fuselage base, and is covered on the outer side of the fuselage circuit adapter plate, and the hook plate is provided with a hook for carrying The cable on the piece is connected to the external radar through the hook.
  • the present application further provides a drone, comprising the pan/tilt quick assembly and disassembly device of any of the above, and a photographing device, wherein the photographing device is disposed on the pan/tilt, and the carrier is a fuselage of the drone.
  • the gimbal quick assembly and disassembly device uses a locking component to detachably mount the cloud pedestal assembly and the fuselage seat assembly, thereby enabling the pylon to be detachably mounted on the carrier, thereby improving the previous cloud.
  • the platform is fixedly mounted on the carrier, which causes the disassembly and assembly operation to be complicated and low in efficiency, thereby realizing the quick assembly and disassembly of the gimbal and the carrier, and the structure design is simple, the operation is convenient, and the continuous performance is reliable.
  • the PTZ quick-installation and disassembly device provided by the present application, when the gimbal is quickly assembled and disassembled on the carrier, the lock cylinder cooperates with the torsion spring sliding latch to enter and exit the lock slot to lock and disassemble the cloud pedestal assembly, and at the same time, the pedestal
  • the guiding block slides in the guiding groove of the fuselage seat, so that the fuselage seat is movably disassembled and assembled in the receiving seat of the cloud platform, thereby realizing the purpose of quick disassembly and assembly of the gimbal.
  • the fuselage circuit adapter plate is provided with a plurality of conductive contacts
  • the PTZ circuit adapter plate is provided with a plurality of touch-type shrapnels corresponding to the conductive contacts of the fuselage circuit adapter plate.
  • the UAV uses the PTZ quick assembly and disassembly device to fix the fuselage base assembly on the main body of the UAV, and the cloud pedestal assembly is fixedly mounted on the PTZ, and the locking component will be Cloud pedestal group
  • the detachable assembly of the components and the fuselage seat assembly enables the pylon to be detachably mounted on the drone, thereby improving the conventional installation of the gimbal on the unmanned aerial vehicle, resulting in complicated disassembly and assembly operations and low efficiency.
  • the utility model realizes the quick assembly and disassembly between the cloud platform and the drone, and has the advantages of simple structure design, convenient operation and reliable continuous performance.
  • FIG. 1 is a schematic view showing the fuse holder assembly and the cloud pedestal assembly of the PTZ quick assembly and disassembly device installed on the carrier and the pan/tilt, respectively.
  • FIG. 2 is a perspective view of an embodiment of the quick loading and unloading device of the gimbal shown in FIG. 1.
  • FIG. 3 is a perspective view of another angle of the quick-installing and disassembling device of the gimbal shown in FIG. 2.
  • FIG. 4 is an exploded view of the quick-installing and disassembling device of the gimbal shown in FIG. 3.
  • FIG. 5 is a schematic view of the gimbal quick assembly and disassembly device shown in FIG. 2 mounting the gimbal on the carrier.
  • FIG. 6 is a schematic view showing the relative position of the pan/tilt head of the gimbal quick assembly and disassembly device shown in FIG. 5 when it is not locked on the fuselage seat.
  • Fig. 7 is a schematic view showing the relative position of the pan/tilt head of the pan/tilt quick-mounting and disassembling device shown in Fig. 5 when it is locked on the fuselage seat.
  • 120-cloud pedestal component 21-cloud pedestal; 211-cloud pedestal receiving slot; 212-button hole;
  • 22-PTZ circuit adapter board 2221-touch type shrapnel; 222-connector; 30-locking assembly;
  • connection are to be understood broadly, and may be, for example, a fixed connection, a detachable connection, or an integral, unless otherwise explicitly defined and defined. Ground connection.
  • the PTZ quick-installation and disassembly device provided in this embodiment is suitable for the assembly and disassembly of the PTZ 300 on the carrier 200, for example, on the UAV, to realize quick assembly and disassembly between the PTZ and the UAV.
  • the PTZ quick-release device can also be used on other devices, such as automobiles and security devices, and there is no limitation.
  • the pan/tilt quick assembly and disassembly device includes a fuselage base assembly 10, a cloud pedestal assembly 20, and a locking assembly 30, wherein the fuselage mount assembly 10 is fixedly mounted on the carrier 200.
  • the cloud pedestal assembly 20 is fixedly mounted on the cloud platform 300, and the cloud pedestal assembly 20 includes a cloud pedestal 21; the locking assembly 30 is mounted on the fuselage base assembly 10 or the cloud pedestal assembly 20, and is locked.
  • the assembly 30 detachably mounts the cloud pedestal assembly 20 and the fuselage mount assembly 10 such that the pan/tilt head 300 is detachably mounted on the carrier 200.
  • the pan/tilt quick assembly and disassembly device detachably mounts the cloud pedestal assembly 20 and the fuselage base assembly 10 by using a locking assembly 30, so that the pan/tilt head 300 is detachably mounted on the carrier 200
  • the fixed installation of the gimbal 300 on the carrier 200 has been improved, resulting in complicated disassembly and assembly operations and low efficiency, thereby realizing quick assembly and disassembly of the gimbal 300 and the carrier 200, and having simple structure design, convenient operation and continuous operation. Reliable performance.
  • the fuselage base assembly 10 includes a fuselage base 11 having a cavity facing the pedestal receiving slot 211 of the fuselage mount 11.
  • the seat 11 is movably received in the pedestal receiving slot 211, and the locking assembly 30 is mounted on the pedestal 21.
  • the pedestal 21 is housed in the body mount 11
  • the fuselage base 11 has a fuselage seat receiving slot with an opening facing the pan head 21, and the pan head 21 is movably received in the fuselage seat receiving slot, and the locking assembly 30 is mounted on the body mount. 11 on.
  • a side wall of the cloud pedestal receiving slot 211 defines a button hole 212 extending through the outer wall of the pedestal 21 , and the inner wall of the pedestal receiving slot 211 is outwardly protruded.
  • the locking assembly 30 includes a button 31 and a torsion spring 32.
  • the button 31 is movably inserted into the button hole 212.
  • the torsion spring 32 is sleeved on the fixing post 213, and the torsion spring 32 is at one end.
  • the rotating arm 321 abuts the button 31 so that the button 31 is pushed inward and is returned to the initial position by the action of the rotating arm 321.
  • the button 31 has a vertical plate-shaped baffle 311.
  • the bottom surface of the baffle 311 is horizontally outwardly convexly formed to form a substrate 312, and the substrate 312 is provided with a lock.
  • the slot 3121 has an L-shape.
  • the surface of the body of the pedestal 11 facing the pedestal 21 is outwardly convexly disposed with a lock core 111 corresponding to the button 31.
  • the lock core 111 is slidably held in the lock groove 3121, so that the body frame 11 is detachably attached to the body.
  • the cloud pedestal is accommodated in the slot 211.
  • the locking assembly 30 and the lock cylinder 111 may also be an integral locking device for unlocking and locking functions.
  • the button 31 and the torsion spring 32 are provided.
  • Other variations or modifications of the various forms may be made on the basis of the lock cylinder 111, and all embodiments are not required and cannot be exhaustive.
  • the surface of the fuselage base 11 facing the cloud pedestal 21 is marked with a mounting mark 112, and the bottom wall of the pedestal receiving groove 211 of the pedestal 21 corresponds to the fuselage seat.
  • the installation indicator 112 on the 11 is also marked with the installation indicator 214.
  • the side wall of the pedestal receiving groove 211 of the pedestal 21 protrudes inwardly in the direction in which the lock core 111 slides out of the locking groove 3121.
  • the direction in which the button 31 is pressed is the A direction
  • the opening direction of the lock slot 3121 is the B direction perpendicular to the moving direction of the button 31.
  • the direction in which the pan head 21 is mounted is the direction of the lock slot 3121.
  • the direction of the opening is the same, and the direction in which the pedestal 21 is detached is opposite to the opening direction of the lock groove 3121, that is, the detachment direction of the pedestal 21 does not coincide with the urging direction of the button 31.
  • the side wall of the button 301 is mounted on the side wall of the button 31 and the side wall of the side wall is protruded inwardly with respect to the side wall of the side wall.
  • the guiding block 215 is arranged in the B direction. As shown in FIG. 3, the body frame 11 protrudes outwardly corresponding to the position of the guiding block 215 on the cloud pedestal 21 to form a plurality of guiding grooves 113. When the pedestal 21 is assembled and detached, the guiding block 215 slides in the guiding slot 113 to accurately align the sliding of the pan/tilt head 300.
  • the fuselage seat 11 and the pedestal 21 are first placed oppositely according to the installation designation 111 of the fuselage base 11 and the mounting indicator 214 on the pedestal 21, as shown in FIG. 6. Then, the button 31 on the pedestal 21 is pressed in the direction A, the pedestal 21 is covered on the body frame 11, and the pedestal 21 is slid in the B direction, so that the guiding block 215 on the pedestal 21 is slid into the body. The guide groove 113 of 11 is as shown in FIG. Finally, the button 31 is released, and the end of the substrate 312 of the button 31 is returned to the initial position by the action of the rotating arm 321 of the torsion spring 32. At this time, the lock cylinder 111 is held in the lock groove 3121.
  • the pan/tilt quick assembly and disassembly device of the embodiment removes the pan/tilt head 300, it is opposite to the above-mentioned installation step.
  • the button 31 on the pedestal 21 is pressed in the direction A, and the end of the substrate 312 of the button 31 abuts against the rotating arm 321 of the torsion spring 32, and at the same time, the lock cylinder 111 slides to the opening of the lock groove 3121.
  • the pedestal 21 is slid in the opposite direction of the B direction, and the lock core 111 slides out of the lock slot 3121 through the lock slot 3121 of the button 31.
  • the guide block 215 slides out of the guide slot 113 in the B direction, thereby realizing The separation of the pedestal 21 from the fuselage seat 11 enables rapid disassembly of the gimbal 300.
  • the body mount assembly 10 further includes a body.
  • the circuit adapter board 12 and the cable cover 13 are mounted on the body mount 11 with the body circuit adapter plate 12 and the cable cover 13.
  • the cloud pedestal assembly 20 further includes a pan/tilt circuit adapter plate 22 mounted on the cloud pedestal 21.
  • the fuselage circuit adapter plate 12 is in electrical contact with the pan/tilt circuit adapter plate 22 to effect signal transmission.
  • the fuselage base 11 of the fuselage mount assembly 10 is recessed in the mounting surface of the mounting carrier 200 to form a receiving slot 114, and the bottom wall of the receiving slot 114 is opened.
  • the pedestal 21 of the cloud pedestal assembly 20 is recessed in the mounting surface of the mounting platform 300 to form a mounting slot 216.
  • the bottom wall of the mounting slot 216 defines a second through hole 217 extending through the bottom wall of the pedestal receiving slot 211.
  • the fuselage circuit adapter plate 12 and the cable cover 13 are received in the receiving slot 114, and the cable cover 13 is covered outside the fuselage circuit adapter plate 12.
  • the pan/tilt circuit adapter plate 22 is mounted in the mounting slot 216.
  • the fuselage circuit adapter plate 12 and the pan/tilt circuit adapter plate 22 The first through hole 115 and the second through hole 217 are electrically contacted.
  • a plurality of conductive contacts 121 are disposed on a side of the airframe circuit adapter plate 12 facing the pan-tilt circuit adapter plate 22, and the pan-tilt circuit adapter plate
  • the conductive contact piece 121 corresponding to the body circuit adapter plate 12 on one side of the body circuit board 12 is provided with a plurality of touch type elastic pieces 221, and when the cloud pedestal assembly 20 is mounted on the body seat assembly 10
  • the touch type elastic piece 221 is in electrical contact with the conductive contact piece 121.
  • the manner in which the fuselage circuit adapter plate 12 and the pan-tilt circuit adapter plate 22 are electrically connected is a conductive contact piece 121 and a touch-type elastic piece 221, and a spring piece connection and a conductive terminal connection may also be adopted. Or connector connection, etc.
  • the fuselage circuit adapter plate 12 is provided with a connector 122 facing the surface of the carrier 200 for the fuselage circuit adapter plate 12 and the carrier 200. The signal is transmitted between.
  • the card cover 13 is provided with a hook 131. The remaining wires on the carrier 200 are stored by the hooks 131 and then connected to the external radar.
  • the platform circuit adapter plate 22 is provided with a connector 222 facing the surface of the platform 300 for realizing signals between the pan-tilt circuit board 22 and the platform 300. transfer.
  • the embodiment provides a drone, which comprises the pan/tilt quick-release device according to any one of the first embodiments, and a photographing device, wherein the photographing device is disposed on the pan/tilt (300).
  • the carrier (200) is the body of the drone.
  • the above-mentioned UAV is fixedly mounted on the main body of the drone by using the PTZ quick-installing and disassembling device in the first embodiment, and the cloud pedestal assembly 20 is fixedly mounted on the PTZ 300.
  • the locking assembly 30 detachably mounts the cloud pedestal assembly 20 and the body mount assembly 10, thereby detachably mounting the pan/tilt head 300 on the drone, improving the conventional installation of the pan/tilt head 300 in the absence of On the man-machine, the disassembly and assembly operation is complicated and the efficiency is low, thus realizing the quick assembly and disassembly between the gimbal 300 and the drone, the structure design is simple, the operation is convenient, and the continuous performance is reliable.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Remote Sensing (AREA)
  • Accessories Of Cameras (AREA)
  • Pivots And Pivotal Connections (AREA)
  • Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
  • Seats For Vehicles (AREA)

Abstract

一种云台快速装拆装置，包括机身座组件（10）、云台座组件（20）以及锁紧组件（30），其中机身座组件（10）固定装设于承载件（200）上；云台座组件（20）固定装设于云台（300）上，云台座组件（20）包括云台座（21）；锁紧组件（30）装设于机身座组件（10）或者云台座组件（20）上，锁紧组件（30）将云台座组件（20）和机身座组件（10）可拆卸地安装在一起，以使云台（300）可拆卸地安装在承载件（200）上。还提供了一种无人机，包括云台快速装拆装置以及拍摄装置，该拍摄装置设置于云台（300）上，承载件（200）为无人机的机身。云台（300）可拆卸地安装在无人机上，实现了云台（300）与无人机的快速装拆。

Description

云台快速装拆装置以及具有其的无人机 技术领域
本申请涉及云台领域，尤其涉及一种云台快速装拆装置以及具有其的无人机。
背景技术
云台作为安装、固定摄像机等电器设备的支撑设备安装于承载件上，其广泛应用于摄影、照相、监控等领域。在无人机技术应用领域，通常将云台固定在作为承载件的无人机的机身上，并通过云台搭载用于航拍的拍摄设备(比如照相机和摄像机)，以获取特定类型的环境信息(例如遥感图像)。
通常情况下，现有技术中的云台直接与无人机固定连接，两者之间大多采用螺钉进行锁紧固定。为了运输方便，云台及摄像设备都是在执行任务前才安装在无人机上，并且只有配置了特定规格的螺纹孔的拍摄设备才能与云台配套使用。这种装配结构一方面降低了云台的通用性，另一方面拆装操作复杂、效率低，同时经过多次拆装后还会导致螺纹过度磨损，耐用性差，因此不利于无人机快速执行任务。
申请内容
为此，本申请要解决的技术问题在于克服现有技术的云台通用性差以及拍摄设备拆装操作复杂、效率低的技术问题。
为了实现上述目的，本申请提供一种云台快速装拆装置，包括机身座组件、云台座组件以及锁紧组件，其中，机身座组件固定装设于承载件上；云台座组件固定装设于云台上，云台座组件包括云台座；锁紧组件装设于机身座组件或者云台座组件上，锁紧组件将云台座组件和机身座组件可拆卸的安装在一起，以使云台可拆卸的安装在承载件上。
作为优选，机身座组件包括机身座，机身座具有一开口朝向云台座的机身座收容槽，云台座可活动地收容于机身座收容槽内，锁紧组件装设于机身座上。
作为优选，机身座组件包括机身座，云台座具有一开口朝向机身座的云台座收容槽，机身座可活动地收容于云台座收容槽内，锁紧组件装设于云台座上。
作为优选，云台座收容槽的一侧壁向外开设有贯穿云台座外壁的按键孔，云台座收容槽内壁向外凸设有一固定柱；锁紧组件包括按键以及扭簧，按键活动地插设于按键孔中，扭簧套设于固定柱上，扭簧一端的转臂抵顶按键，以使按键向里推动后受到转臂的作用可以回到初始位置。
作为优选，按键具有一竖直板状的挡板，挡板一侧表面中部水平向外凸伸形成一基板，基板上开设有锁槽；机身座朝向云台座的表面对应于按键向外凸设有一锁芯，锁芯可滑动的卡持于锁槽内，以使机身座活动地拆装于云台座收容槽内。
作为优选，按键按压的方向为A方向，锁槽的开口方向为垂直于按键活动方向的B方向，云台座安装的方向与锁槽的开口方向相同，云台座拆卸的方向与锁槽的开口方向相反，即云台座的拆装方向与按键的推动方向不一致。
作为优选，云台座收容槽安装按键的侧壁以及相对于该侧壁的侧壁上向内凸伸有若干导引块；机身座对应于云台座上的导引块位置向外凸伸以形成若干导引槽，导引块在导引槽中滑动，以实现云台的滑动准确安装。
作为优选，机身座组件还包括机身电路转接板，机身电路转接板安装于机身座上；云台座组件还包括有云台电路转接板，云台电路转接板安装于云台座上，当云台座组件安装在机身座组件上时，机身电路转接板与云台电路转接板电性接触，以实现信号的传递。
作为优选，机身座组件的机身座位于安装承载件的安装面向里凹设形成有容置槽，机身电路转接板收容于容置槽内；云台座组件的云台座位于安装云台的安装面向里凹设形成一安装槽，云台电路转接板安装于安装槽内。
作为优选，容置槽底壁上开设有贯穿机身座外表面的第一通孔，安装槽底 壁上开设有贯穿云台座收容槽底壁的第二通孔，当云台座组件安装在机身座组件上时，机身电路转接板与云台电路转接板透过第一通孔和第二通孔电性接触。
作为优选，机身电路转接板朝向云台电路转接板的一侧上设置有若干导电触片，云台电路转接板朝向机身电路转接板的一侧上对应于机身电路转接板的导电触片设置有若干触动式弹片，当云台座组件安装在机身座组件上时，触动式弹片与导电触片电性接触。
作为优选，机身座组件还包括卡线盖板，卡线盖板安装于机身座上，并盖合在机身电路转接板外，卡线盖板上设置有卡钩，以供承载件上的排线通过卡钩后与外接的雷达连接。
为了实现上述目的，本申请还提供一种无人机，包括上述任一项的云台快速装拆装置，以及拍摄装置，拍摄装置设置于云台上，承载件为无人机的机身。
本申请提供的云台快速装拆装置以及具有其的无人机具有如下优点：
1.本申请提供的云台快速装拆装置，采用锁紧组件将云台座组件和机身座组件可拆卸的安装在一起，进而使云台可拆卸的安装在承载件上，改善了以往云台固定安装在承载件上，造成拆装操作复杂、效率低的情况，从而实现了云台与承载件的快速装拆，结构设计简单、操作便捷、连续性能可靠。
2.本申请提供的云台快速装拆装置，当云台快速装拆于承载件上时，锁芯配合扭簧滑动的卡持进出锁槽来锁紧和拆卸云台座组件，同时，云台座的导引块在机身座的导引槽中滑动，以使机身座活动地拆装于云台座收容槽内，进而实现云台快速拆装的目的。
3.本申请提供的云台快速装拆装置，机身电路转接板设置有若干导电触片，云台电路转接板对应于机身电路转接板的导电触片设置有若干触动式弹片，当云台座组件安装在机身座组件上时，触动式弹片与导电触片电性接触，以实现云台座组件和机身座组件之间信号的传递。
4.本申请提供的无人机，由于采用了云台快速装拆装置，将机身座组件固定装设于无人机主体上，云台座组件固定装设于云台上，锁紧组件将云台座组 件和机身座组件可拆卸的安装在一起，进而使云台可拆卸的安装在无人机上，改善了以往云台固定安装在无人机上，造成拆装操作复杂、效率低的情况，从而实现了云台与无人机之间的快速装拆，结构设计简单、操作便捷、连续性能可靠。
附图说明
为了更清楚地说明本申请具体实施方式的技术方案，下面根据本申请的具体实施例并结合附图，对申请作进一步详细说明。
图1为本申请云台快速装拆装置的机身座组件和云台座组件分别安装在承载件和云台上的示意图。
图2为图1所示云台快速装拆装置一种实施方式的立体图。
图3为图2所示云台快速装拆装置的另一角度的立体图。
图4为图3所示云台快速装拆装置的爆炸图。
图5为图2所示云台快速装拆装置将云台安装到承载件上的示意图。
图6为图5所示云台快速装拆装置的云台座未锁紧在机身座上时的相对位置的示意图。
图7为图5所示云台快速装拆装置的云台座锁紧在机身座上时的相对位置的示意图。
图中各附图标记说明如下。
10-机身座组件；11-机身座；111-锁芯；112-安装标示；
113-导引槽；114-容置槽；115-第一通孔；12-机身电路转接板；
121-导电触片；122-连接器；13-卡线盖板；31-卡钩；
120-云台座组件；21-云台座；211-云台座收容槽；212-按键孔；
213-固定柱；14-安装标示；215-导引块；216-安装槽；217-第二通孔；
22-云台电路转接板；221-触动式弹片；222-连接器；30-锁紧组件；
31-按键；311-挡板；312-基板；3121-锁槽；32-扭簧；321-转臂；
200-承载件；300-云台。
具体实施方式
下面将结合附图对本申请的技术方案进行清楚、完整地描述，显然，所描述的实施例是本申请一部分实施例，而不是全部的实施例。基于本申请中的实施例，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，都属于本申请保护的范围。
在本申请的描述中，需要说明的是，术语“上”、“竖直”、“水平”、“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申请和简化描述，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申请的限制。此外，术语“第一”、“第二”、仅用于描述目的，而不能理解为指示或暗示相对重要性。
在本申请的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接。对于本领域的普通技术人员而言，可以具体情况理解上述术语在本申请中的具体含义。
此外，下面所描述的本申请不同实施方式中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
实施例1
本实施例提供的云台快速装拆装置，适用于承载件200上云台300的装拆，比如用在无人机上，以实现云台与无人机之间的快速装拆。当然，该云台快速装拆装置也可用在其他设备上，比如汽车、安防设备等，对此不作限制。如1和图2所示，所述云台快速装拆装置包括机身座组件10、云台座组件20以及锁紧组件30，其中，所述机身座组件10固定装设于承载件200上；所述云台座组件20固定装设于云台300上，所述云台座组件20包括云台座21；所述锁紧组件30装设于机身座组件10或者云台座组件20上，锁紧组件30将所述云台座组件20和机身座组件10可拆卸的安装在一起，以使所述云台300可拆卸的安装在所述承载件200上。
上述云台快速装拆装置采用锁紧组件30将所述云台座组件20和机身座组件10可拆卸的安装在一起，进而使所述云台300可拆卸的安装在所述承载件200 上，改善了以往云台300固定安装在承载件200上，造成拆装操作复杂、效率低的情况，从而实现了云台300与承载件200的快速装拆，结构设计简单、操作便捷、连续性能可靠。
如图1和图3所示，在本实施例中，所述机身座组件10包括机身座11，云台座21具有一开口朝向所述机身座11的云台座收容槽211，机身座11可活动地收容于云台座收容槽211内，锁紧组件30装设于云台座21上。
作为变形的实施方式，还可以采用云台座21收容于机身座11的方式。具体的，所述机身座11具有一开口朝向云台座21的机身座收容槽，云台座21可活动地收容于机身座收容槽内，所述锁紧组件30装设于机身座11上。
作为优选的实施方式，如图3和图4所示，所述云台座收容槽211的一侧壁向外开设有贯穿云台座21外壁的按键孔212，云台座收容槽211内壁向外凸设有一固定柱213。所述锁紧组件30包括按键31以及扭簧32，所述按键31活动地插设于所述按键孔212中，所述扭簧32套设于所述固定柱213上，扭簧32一端的转臂321抵顶所述按键31，以使按键31向里推动后受到转臂321的作用可以回到初始位置。
作为优选的实施方式，如图4所示，所述按键31具有一竖直板状的挡板311，挡板311一侧表面中部水平向外凸伸形成一基板312，基板312上开设有锁槽3121，该锁槽呈L型。所述机身座11朝向云台座21的表面对应于按键31向外凸设有一锁芯111，锁芯111可滑动的卡持于锁槽3121内，以使机身座11活动地拆装于云台座收容槽211内。
作为变形的实施方式，所述锁紧组件30以及锁芯111还可以是一体式的锁器件，以实现开锁、锁紧功能，对于所属领域的普通技术人员来说，在按键31、扭簧32以及锁芯111的基础上还可以做出其它不同形式的变化或变动，这里无需也无法对所有的实施方式予以穷举。
作为优选的实施方式，如图2和图3所示，机身座11朝向云台座21的表面上标示有安装标示112，云台座21的云台座收容槽211的底壁对应于机身座 11上的安装标示112也标示有安装标示214，当使用者安装时，只需要对应机身座11的安装标示111和云台座21上的安装标示214即可明白机身座11与云台座21的相对安装位置关系，方便了使用者的使用。
作为优选的实施方式，如图4所示，云台座21的云台座收容槽211的侧壁根据锁芯111滑出锁槽3121的方向向内凸伸有若干导引块215。如图4和图5所示，按键31按压的方向为A方向，锁槽3121的开口方向为垂直于按键31活动方向的B方向，所述云台座21安装的方向与所述锁槽3121的开口方向相同，所述云台座21拆卸的方向与所述锁槽3121的开口方向相反，即云台座21的拆装方向与按键31的推动方向不一致。云台座收容槽211安装按键31的侧壁以及相对于该侧壁的侧壁上向内凸伸有若干的所述导引块215，所述导引块215沿B方向排列。如图3所示，机身座11对应于云台座21上的导引块215位置向外凸伸以形成若干导引槽113。当装拆云台座21时，导引块215在导引槽113中滑动，以实现云台300的滑动准确装拆。
本实施例的云台快速装拆装置安装时，首先根据机身座11的安装标示111和云台座21上的安装标示214相对放置机身座11和云台座21，如图6所示。然后沿A方向按压云台座21上的按键31，使云台座21盖合在机身座11上，沿B方向滑动云台座21，进而使云台座21上的导引块215滑入机身座11的导引槽113中，如图7所示。最后放开按键31，按键31的基板312的末端受到扭簧32的转臂321的作用回到初始位置，此时，锁芯111卡持于锁槽3121中。
本实施例的云台快速装拆装置拆卸云台300时，与上述安装时步骤相反。首先沿A方向按压云台座21上的按键31，按键31的基板312的末端抵顶扭簧32的转臂321，同时，锁芯111滑动到锁槽3121的开口处。再沿B方向的反方向滑动所述云台座21，锁芯111通过按键31的锁槽3121开口滑出锁槽3121，所述导引块215沿B方向滑出导引槽113，进而实现了云台座21与机身座11的分离，从而实现了云台300的快速拆卸。
作为优选的实施方式，如图2和图3所示，所述机身座组件10还包括机身 电路转接板12以及卡线盖板13，所述机身电路转接板12以及卡线盖板13安装于机身座11上。所述云台座组件20还包括有云台电路转接板22，所述云台电路转接板22安装于云台座21上。当云台座组件20安装在机身座组件10上时，机身电路转接板12与云台电路转接板22电性接触，以实现信号的传递。
具体的，如图2至图4所示，所述机身座组件10的机身座11位于安装承载件200的安装面向里凹设形成有容置槽114，容置槽114底壁上开设有贯穿机身座11外表面的第一通孔115。所述云台座组件20的云台座21位于安装云台300的安装面向里凹设形成一安装槽216，安装槽216底壁上开设有贯穿云台座收容槽211底壁的第二通孔217。所述机身电路转接板12和卡线盖板13收容于容置槽114内，卡线盖板13盖合在机身电路转接板12外。所述云台电路转接板22安装于所述安装槽216内，当云台座组件20安装在机身座组件10上时，所述机身电路转接板12与云台电路转接板22透过第一通孔115和第二通孔217电性接触。
作为优选的实施方式，如图2和图3所示，所述机身电路转接板12朝向云台电路转接板22的一侧上设置有若干导电触片121，云台电路转接板22朝向机身电路转接板12的一侧上对应于所述机身电路转接板12的导电触片121设置有若干触动式弹片221，当云台座组件20安装在机身座组件10上时，所述触动式弹片221与所述导电触片121电性接触。
作为变形的实施方式，上述机身电路转接板12与云台电路转接板22电性连接的方式采用导电触片121与触动式弹片221的方式，还可以采用弹片连接、导电端子的连接或者连接器连接等方式。
作为优选的实施方式，如图2和图4所示，所述机身电路转接板12朝向承载件200的表面设置有连接器122，以供机身电路转接板12与承载件200之间实现信号的传递。所述卡线盖板13上设置有卡钩131，承载件200上其余的排线通过卡钩131收纳整理后与外接的雷达连接。云台电路转接板22朝向云台300的表面设置有连接器222，以供云台电路转接板22与云台300之间实现信号的 传递。
实施例2
本实施例提供一种无人机，其包括实施例1中记载的任一项所述云台快速装拆装置，以及拍摄装置，所述拍摄装置设置于所述云台(300)上，所述承载件(200)为所述无人机的机身。
上述无人机由于采用了实施例1中的云台快速装拆装置，将机身座组件10固定装设于无人机主体上，所述云台座组件20固定装设于云台300上，锁紧组件30将所述云台座组件20和机身座组件10可拆卸的安装在一起，进而使所述云台300可拆卸的安装在无人机上，改善了以往云台300固定安装在无人机上，造成拆装操作复杂、效率低的情况，从而实现了云台300与无人机之间的快速装拆，结构设计简单、操作便捷、连续性能可靠。
显然，上述实施例仅仅是为清楚地说明所作的举例，而并非对实施方式的限定。对于所属领域的普通技术人员来说，在上述说明的基础上还可以做出其它不同形式的变化或变动。这里无需也无法对所有的实施方式予以穷举。而由此所引伸出的显而易见的变化或变动仍处于本申请创造的保护范围之中。

Claims (13)

  1. 一种云台快速装拆装置，其特征在于：包括机身座组件(10)、云台座组件(20)以及锁紧组件(30)，其中，所述机身座组件(10)固定装设于承载件(200)上；所述云台座组件(20)固定装设于云台(300)上，所述云台座组件(20)包括云台座(21)；所述锁紧组件(30)装设于机身座组件(10)或者云台座组件(20)上，锁紧组件(30)将所述云台座组件(20)和机身座组件(10)可拆卸的安装在一起，以使所述云台(300)可拆卸的安装在所述承载件(200)上。
  2. 根据权利要求1所述的云台快速装拆装置，其特征在于：所述机身座组件(10)包括机身座(11)，所述机身座(11)具有开口朝向所述云台座(21)的机身座收容槽，所述云台座(21)可活动地收容于所述机身座收容槽内，所述锁紧组件(30)装设于所述机身座(11)上。
  3. 根据权利要求1所述的云台快速装拆装置，其特征在于：所述机身座组件(10)包括机身座(11),所述云台座(21)具有开口朝向所述机身座(11)的云台座收容槽(211)，所述机身座(11)可活动地收容于所述云台座收容槽(211)内，所述锁紧组件(30)装设于所述云台座(21)上。
  4. 根据权利要求3所述的云台快速装拆装置，其特征在于：所述云台座收容槽(211)的一侧壁向外开设有贯穿云台座(21)外壁的按键孔(212)，云台座收容槽(211)内壁向外凸设有固定柱(213)；所述锁紧组件(30)包括按键(31)以及扭簧(32)，所述按键(31)活动地插设于所述按键孔(212)中，所述扭簧(32)套设于所述固定柱(213)上，扭簧(32)一端的转臂(321)抵顶所述按键(31)，以使按键(31)向里推动后受到转臂(321)的作用可以回到初始位置。
  5. 根据权利要求4所述的云台快速装拆装置，其特征在于：所述按键(31)具有竖直板状的挡板(311)，所述挡板(311)一侧表面中部水平向外凸伸形成 基板(312)，所述基板(312)上开设有锁槽(3121)；所述机身座(11)朝向云台座(21)的表面对应于所述按键(31)向外凸设有锁芯(111)，所述锁芯(111)可滑动的卡持于所述锁槽(3121)内，以使所述机身座(11)活动地拆装于所述云台座收容槽(211)内。
  6. 根据权利要求5所述的云台快速装拆装置，其特征在于：所述按键(31)按压的方向为A方向，所述锁槽(3121)的开口方向为垂直于按键(31)活动方向的B方向，所述云台座(21)安装的方向与所述锁槽(3121)的开口方向相同，所述云台座(21)拆卸的方向与所述锁槽(3121)的开口方向相反，即云台座(21)的拆装方向与按键(31)的推动方向不一致。
  7. 根据权利要求4-6其中任一项所述的云台快速装拆装置，其特征在于：所述云台座收容槽(211)安装所述按键(31)的侧壁以及相对于该侧壁的侧壁上向内凸伸有若干导引块(215)；所述机身座(11)对应于所述云台座(21)上的所述导引块(215)位置向外凸伸以形成若干导引槽(113)，所述导引块(215)在所述导引槽(113)中滑动，以实现所述云台(300)的滑动准确安装。
  8. 根据权利要求3-6其中任一项所述的云台快速装拆装置，其特征在于：所述机身座组件(10)还包括机身电路转接板(12)，所述机身电路转接板(12)安装于机身座(11)上；所述云台座组件(20)还包括有云台电路转接板(22)，所述云台电路转接板(22)安装于云台座(21)上，当云台座组件(20)安装在机身座组件(10)上时，所述机身电路转接板(12)与云台电路转接板(22)电性接触，以实现信号的传递。
  9. 根据权利要求8所述的云台快速装拆装置，其特征在于：所述机身座组件(10)的机身座(11)位于安装承载件(200)的安装面向里凹设形成有容置槽(114)，所述机身电路转接板(12)收容于容置槽(114)内；所述云台座组件(20)的云台座(21)位于安装云台(300)的安装面向里凹设形成安装槽(216)，所述云台电路转接板(22)安装于所述安装槽(216)内。
  10. 根据权利要求9所述的云台快速装拆装置，其特征在于：所述容置槽 (114)底壁上开设有贯穿机身座(11)外表面的第一通孔(115)，所述安装槽(216)底壁上开设有贯穿云台座收容槽(211)底壁的第二通孔(217)，当云台座组件(20)安装在机身座组件(10)上时，所述机身电路转接板(12)与云台电路转接板(22)透过第一通孔(115)和第二通孔(217)电性接触。
  11. 根据权利要求9或10所述的云台快速装拆装装置，其特征在于：所述机身电路转接板(12)朝向云台电路转接板(22)的一侧上设置有若干导电触片(121)，所述云台电路转接板(22)朝向机身电路转接板(12)的一侧上对应于所述机身电路转接板(12)的导电触片(121)设置有若干触动式弹片(221)，当云台座组件(20)安装在机身座组件(10)上时，所述触动式弹片(221)与所述导电触片(121)电性接触。
  12. 根据权利要求8所述的云台快速装拆装置，其特征在于：所述机身座组件(10)还包括卡线盖板(13)，所述卡线盖板(13)安装于机身座(11)上，并盖合在机身电路转接板(12)外，所述卡线盖板(13)上设置有卡钩(131)，所述承载件(200)上其余的排线通过卡钩(131)收纳整理后与外接的雷达连接。
  13. 一种无人机，其特征在于：包括权利要求1-12中任一项所述的云台快速装拆装置，以及拍摄装置，所述拍摄装置设置于所述云台(300)上，所述承载件(200)为所述无人机的机身。
PCT/CN2016/091778 2015-10-28 2016-07-26 云台快速装拆装置以及具有其的无人机 WO2017071338A1 (zh)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP16858777.2A EP3351845B1 (en) 2015-10-28 2016-07-26 Quick assembly/disassembly apparatus for unmanned aerial vehicle
US15/958,530 US10919645B2 (en) 2015-10-28 2018-04-20 Gimbal quick assembly/disassembly apparatus and unmanned aerial vehicle having the same

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201520845452.X 2015-10-28
CN201520845452.XU CN205076056U (zh) 2015-10-28 2015-10-28 云台快速装拆装置以及具有其的无人机

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US15/958,530 Continuation US10919645B2 (en) 2015-10-28 2018-04-20 Gimbal quick assembly/disassembly apparatus and unmanned aerial vehicle having the same

Publications (1)

Publication Number Publication Date
WO2017071338A1 true WO2017071338A1 (zh) 2017-05-04

Family

ID=55428479

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/091778 WO2017071338A1 (zh) 2015-10-28 2016-07-26 云台快速装拆装置以及具有其的无人机

Country Status (4)

Country Link
US (1) US10919645B2 (zh)
EP (1) EP3351845B1 (zh)
CN (1) CN205076056U (zh)
WO (1) WO2017071338A1 (zh)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107176290A (zh) * 2017-05-31 2017-09-19 温州市通翔智能科技有限公司 一种无人机
CN109367804A (zh) * 2018-09-28 2019-02-22 国网浙江省电力有限公司 一种沟道巡检无人机

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN205076056U (zh) 2015-10-28 2016-03-09 深圳市道通智能航空技术有限公司 云台快速装拆装置以及具有其的无人机
WO2017096546A1 (en) * 2015-12-09 2017-06-15 SZ DJI Technology Co., Ltd. Imaging system and method for unmanned vehicles
CN209146617U (zh) * 2018-08-20 2019-07-23 深圳市大疆创新科技有限公司 一种云台连接结构、云台装置及摄影设备
CN109707961B (zh) * 2018-12-26 2020-10-09 成都优艾维智能科技有限责任公司 一种云台快拆连接结构
CN109973941A (zh) * 2019-05-08 2019-07-05 上汽大众汽车有限公司 汽车灯具的吸湿装置
USD956856S1 (en) * 2019-10-30 2022-07-05 Autel Intelligent Technology Corp., Ltd. Extension support
CN114408156B (zh) * 2022-04-01 2022-07-08 沃飞长空科技(成都)有限公司 一种拆装结构、拆装方法和无人机
CN114572409B (zh) * 2022-05-07 2022-07-29 北京卓翼智能科技有限公司 一种用于无人机载荷的安装装置以及无人机

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN203099236U (zh) * 2013-03-04 2013-07-31 南京元鼎机电有限公司 多功能可拆卸可调角度稳定器
US20140336848A1 (en) * 2013-05-10 2014-11-13 Palo Alto Research Center Incorporated System and method for detecting, tracking and estimating the speed of vehicles from a mobile platform
CN104386249A (zh) * 2014-11-17 2015-03-04 马鞍山市靓马航空科技有限公司 一种快速测绘多旋翼无人机及其测绘方法
CN204494013U (zh) * 2015-03-19 2015-07-22 庄金昌 自拍附件支架
CN205076056U (zh) * 2015-10-28 2016-03-09 深圳市道通智能航空技术有限公司 云台快速装拆装置以及具有其的无人机

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7374351B2 (en) * 2005-08-10 2008-05-20 Logitech Europe S.A. Spring loaded attachment mechanism for camera and base
CN203259882U (zh) 2013-05-23 2013-10-30 北方天途航空技术发展（北京）有限公司 新型三轴全角度云台
US9736376B1 (en) * 2014-04-03 2017-08-15 The Tiffen Company, Llc Tilt head, camera stage, multi-post monitor mount and camera stabilizer encompassing the same
EP3926299A1 (en) * 2014-04-28 2021-12-22 SZ DJI Technology Co., Ltd. Interchangeable mounting platform
CN203996915U (zh) 2014-06-07 2014-12-10 珠海羽人飞行器有限公司 三轴自稳定云台
CN104981644B (zh) * 2014-06-27 2017-06-30 深圳市大疆灵眸科技有限公司 锁紧装置及其使用的云台
JP6132983B2 (ja) * 2014-09-24 2017-05-24 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 雲台とそれを用いる画像形成装置、及び無人機
CN204250379U (zh) * 2014-09-24 2015-04-08 深圳市大疆创新科技有限公司 云台及其使用的成像装置、以及无人机
CN104696690B (zh) 2015-03-18 2017-05-24 零度智控（北京）智能科技有限公司 机载云台
CN204592779U (zh) 2015-03-18 2015-08-26 零度智控（北京）智能科技有限公司 机载云台
CN105042299B (zh) 2015-04-22 2017-05-31 零度智控（北京）智能科技有限公司 无人飞行器机载云台
US10437136B2 (en) * 2015-05-22 2019-10-08 Timothy P. Lajoie Modular video attachment with vibration dampening
US20160352992A1 (en) * 2015-05-27 2016-12-01 Gopro, Inc. Image Stabilization Mechanism
WO2017000316A1 (en) * 2015-07-02 2017-01-05 SZ DJI Technology Co., Ltd. Gimbal for image capturing
WO2017035840A1 (zh) * 2015-09-06 2017-03-09 深圳市大疆创新科技有限公司 云台、成像装置及无人飞行器
JP6811336B2 (ja) * 2017-02-24 2021-01-13 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 マルチジンバル組立体
WO2018152770A1 (zh) * 2017-02-24 2018-08-30 深圳市大疆创新科技有限公司 云台组件及机架

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN203099236U (zh) * 2013-03-04 2013-07-31 南京元鼎机电有限公司 多功能可拆卸可调角度稳定器
US20140336848A1 (en) * 2013-05-10 2014-11-13 Palo Alto Research Center Incorporated System and method for detecting, tracking and estimating the speed of vehicles from a mobile platform
CN104386249A (zh) * 2014-11-17 2015-03-04 马鞍山市靓马航空科技有限公司 一种快速测绘多旋翼无人机及其测绘方法
CN204494013U (zh) * 2015-03-19 2015-07-22 庄金昌 自拍附件支架
CN205076056U (zh) * 2015-10-28 2016-03-09 深圳市道通智能航空技术有限公司 云台快速装拆装置以及具有其的无人机

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP3351845A4 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107176290A (zh) * 2017-05-31 2017-09-19 温州市通翔智能科技有限公司 一种无人机
CN107176290B (zh) * 2017-05-31 2023-09-05 温州市通翔智能科技有限公司 一种无人机
CN109367804A (zh) * 2018-09-28 2019-02-22 国网浙江省电力有限公司 一种沟道巡检无人机
CN109367804B (zh) * 2018-09-28 2024-02-06 国网浙江省电力有限公司 一种沟道巡检无人机

Also Published As

Publication number Publication date
EP3351845B1 (en) 2019-09-18
EP3351845A1 (en) 2018-07-25
EP3351845A4 (en) 2018-09-26
CN205076056U (zh) 2016-03-09
US10919645B2 (en) 2021-02-16
US20180237158A1 (en) 2018-08-23

Similar Documents

Publication Publication Date Title
WO2017071338A1 (zh) 云台快速装拆装置以及具有其的无人机
TWI423536B (zh) 用來連接板卡之連接器機構
US9451133B2 (en) Spring-loaded mounting housing for a camera
WO2018113202A1 (zh) 一种可拆卸云台连接装置及无人飞行器
JP2012517685A (ja) バヨネット係止装置を含む電気コネクタ
JP2012516543A (ja) ヘルメット装着用暗視システムの電気コネクタ
US7985091B1 (en) Locking mechanism and information handling system using the same
WO2018066817A1 (ko) 플렉시블 커넥터를 포함하는 전자 장치
US20230375170A1 (en) Quick mount apparatus and method of using same
WO2020107552A1 (zh) 摇杆结构及手持云台
US20120242211A1 (en) Support frame and housing and support assembly
WO2017206434A1 (zh) 保护壳、电子装置、电子调速器及无人机
CN106657469A (zh) 一种移动终端
CN212473485U (zh) 一种应用于接触网检测车的综合定位装置
CN110858869B (zh) 相机模组及具有该相机模组的电子装置
US20120325760A1 (en) Mounting apparatus for power supply
JP2004032141A (ja) カメラモジュール
JP2019149631A (ja) 撮像装置
CN211124348U (zh) 一种无人机地面信号器
US11974410B1 (en) Electronic device with connector interface for rotating external connector
US20240003749A1 (en) Electronic device for monitoring vehicle environments
JPH11274758A (ja) 小型電子機器の着脱装置
CN100410840C (zh) 主机
US9338912B2 (en) Electronic device holder
CN216672101U (zh) 扩展坞及转换器

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16858777

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 2016858777

Country of ref document: EP

NENP Non-entry into the national phase

Ref country code: DE