WO2019134406A1 - 无人机 - Google Patents

无人机 Download PDF

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Publication number
WO2019134406A1
WO2019134406A1 PCT/CN2018/107944 CN2018107944W WO2019134406A1 WO 2019134406 A1 WO2019134406 A1 WO 2019134406A1 CN 2018107944 W CN2018107944 W CN 2018107944W WO 2019134406 A1 WO2019134406 A1 WO 2019134406A1
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WO
WIPO (PCT)
Prior art keywords
battery
drone
limiting portion
main body
frame body
Prior art date
Application number
PCT/CN2018/107944
Other languages
English (en)
French (fr)
Inventor
孙亮
郭晓凯
金时润
Original Assignee
深圳市大疆创新科技有限公司
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Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Publication of WO2019134406A1 publication Critical patent/WO2019134406A1/zh

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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H01M50/249—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H01M50/202—Casings or frames around the primary casing of a single cell or a single battery
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H01M50/262—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders with fastening means, e.g. locks
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries

Definitions

  • Embodiments of the present invention relate to the field of drone technology, and in particular, to a drone that improves a battery fixing manner.
  • drones are increasingly being used in people's production and life, such as power inspection, map mapping, traffic security, advertising celebrations and many other fields.
  • the flight of the drone is basically powered by the battery.
  • the energy that the battery can provide is limited.
  • the battery needs to be replaced for the drone to make the drone sustainable.
  • it is necessary to manually press the elastic member disposed on the battery or press the elastic member disposed on the body of the drone with the finger to unlock the battery from the body. It is cumbersome and affects the user experience.
  • setting the elastic element on the battery or the body affects the appearance of the battery or the body.
  • the embodiment of the present invention provides an unmanned aerial vehicle with improved battery fixing manner to solve the above technical problem.
  • a drone including: a rack body and a battery, the rack body including a battery receiving cavity for accommodating the battery, located in the battery receiving cavity An elastic body, and a limiting portion disposed on the elastic body, wherein the battery is provided with a lock fitting that cooperates with the limiting portion;
  • the limiting portion when the battery is assembled in the battery receiving cavity, the limiting portion cooperates with the lock fitting to lock to restrict movement of the battery.
  • the limiting portion is a through hole or a groove
  • the lock fitting is a protrusion
  • the limiting portion is a protrusion
  • the lock fitting is a through hole or a groove.
  • the protrusion includes a first guiding surface for the battery to enter the battery receiving cavity, and a second guiding surface for moving the battery out of the battery receiving cavity.
  • the limiting portion includes a first guiding mating surface adapted to the first guiding surface and a second guiding mating surface adapted to the second guiding surface.
  • the frame body further includes a machine arm and a mounting portion disposed at a free end of the arm, the mounting portion for mounting a power device that provides flight power to the drone.
  • the frame body is integrally formed.
  • the battery further includes a grip portion provided to the battery body for applying an external force.
  • the rack body further includes a cover for closing the battery receiving cavity; wherein, when the battery is assembled in the battery receiving cavity, the battery has an activity between the cover and the cover spacing.
  • the drone further includes an upper casing and a lower casing assembled to the frame body; wherein the upper casing and the frame body, the lower casing and the lower casing The accommodating spaces of the functional modules of the drone are respectively formed between the main bodies of the rack.
  • the technical solution provided by the embodiment of the present invention may include the following beneficial effects: in the unmanned aerial vehicle of the embodiment of the present invention, an elastic body and a limiting portion are disposed in the battery receiving cavity of the main body of the rack, and the battery is provided with a limit.
  • the battery is assembled with the main body of the rack, the user only needs to insert the battery into the battery receiving cavity. At this time, the lock fitting and the limiting portion are locked to ensure that the battery is locked in the battery receiving cavity.
  • the operation method is simple and the user experience is improved.
  • FIG. 1 is a schematic diagram of an overall structure of a drone according to an embodiment of the present invention.
  • FIG. 2 is a schematic cross-sectional view of a drone according to an embodiment of the present invention.
  • Figure 3 is a partial enlarged view of Figure 2;
  • FIG. 4 is a schematic structural view of a main body of a rack according to an embodiment of the present invention.
  • FIG. 5 is a partially enlarged schematic view of a main body of a rack according to an embodiment of the present invention.
  • FIG. 6 is a schematic structural diagram of a battery according to an embodiment of the present invention.
  • FIG. 7 is a side view of a battery according to an embodiment of the present invention.
  • FIG. 8 is a schematic structural view of a battery assembled in a main body of a rack according to an embodiment of the present invention.
  • FIG. 9 is a schematic structural view of a battery removed from a rack main body according to an embodiment of the present invention.
  • the drone 100 of the embodiment of the present invention includes a rack main body 10 and a battery 20 mounted on the rack main body 10, and the rack main body 10 includes a battery receiving chamber 11 for accommodating the battery 20.
  • the rack body 10 further includes an elastic body 12 located in the battery receiving cavity 11 and a limiting portion 13 disposed on the elastic body 12, and the battery 20 is provided with the limiting portion 13
  • the fitting 22 is locked so that the battery 20 can be locked in the battery housing chamber 11.
  • the battery 20 can be assembled into the battery receiving cavity 11 under the action of an external force.
  • the limiting portion 13 is locked with the lock fitting 22.
  • the battery 20 is assembled on the frame body 10 while the battery 20 is electrically connected to the functional modules disposed on the frame body 10; as shown in FIG. 5 in conjunction with FIG.
  • the locking of the stopper portion 13 and the lock fitting 22 is released by the external force to move the battery 20 out of the battery accommodating chamber 11, thereby stopping the supply of power to the drone 100.
  • the elastic property of the elastic body 12 on the frame body 10 can be used to lock and unlock the limiting portion 13 and the lock fitting 22 under the elastic cooperation of the elastic body 12, so that the battery 20 is fixed.
  • the disassembly method is more convenient. In this way, it is possible to eliminate the need to provide elastic elements on the body or the battery 20 of the drone 100 to lock and unlock the battery 20 and the body, thereby improving the aesthetics of the body and the battery 20.
  • the user can directly lock the battery 20 by pushing the battery 20 into the battery accommodating cavity 11 , and the user can directly unlock the battery 20 by pulling the battery 20 to optimize the operation mode.
  • the lock fitting 22 and the limiting portion 13 can be released due to the elastic vibration of the elastic body 12, thereby disconnecting the battery 20 from the functional module on the frame main body 10.
  • the connection further serves to protect the drone 100 from power failure.
  • the elastic body 12 is a resilient arm.
  • the elastic body 12 and the limiting portion 13 are disposed on any side cavity wall of the rack main body 10 constituting the battery accommodating cavity 11.
  • the position of the lock fitting 22 disposed on the battery 20 is matched with the position of the limiting portion 13 to satisfy the battery. 20 is assembled in the battery accommodating cavity 11 and the limiting portion 13 is locked and locked with the lock fitting 22 .
  • the elastic body 12 and the limiting portion 13 are disposed on the upper side wall of the rack main body 10 constituting the battery accommodating cavity 11, and correspondingly, the lock fitting 22 is disposed on the upper surface of the battery 20.
  • the arrangement of the elastic body 12 and the limiting portion 13 is not limited to the upper side wall of the battery housing 11 , and the elastic body 12 and the limiting portion 13 may be multiple.
  • the frame body 10 is disposed on any side wall of the battery housing chamber 11.
  • the battery 20 includes a battery body 21 and an electrical connection portion (not shown) provided on the battery body 21, and the frame body 10 is provided with an electrical connection portion.
  • An electrical matching portion (not shown) that is electrically connected.
  • the electrical connection portion is electrically connected to the electrical mating portion to realize power supply for the functional module disposed on the rack main body 10.
  • the end of the battery 20 that first enters the battery accommodating chamber 11 is the tip end, and the other end opposite to the top end of the battery 20 is the tail end of the battery 20.
  • the electrical connection portion is provided on a top end surface of the battery body 21.
  • the electrical connection portion may also be disposed on the circumferential side of the battery body 21 or at any other position.
  • the battery 20 further includes a grip portion 23 for receiving an applied external force, so that the user can be easily applied to the battery 20 so that the battery 20 can be withdrawn from the battery accommodating chamber 11.
  • the grip portion 23 is disposed at the tail end of the battery main body 21, wherein the grip portion 23 is located at the fitting opening of the battery receiving chamber 11 when the battery 20 is completely assembled in the battery accommodating chamber 11.
  • the two grip portions 23 are disposed on the upper and lower sides or the left and right sides of the rear end of the battery body 21, so that the user can hold the handle.
  • the limiting portion 13 can be a through hole or a groove
  • the lock fitting 22 is a protrusion.
  • the protrusion is inserted into the through hole or the groove, so that the movement of the battery 20 can be restricted, that is, the battery 20 is assembled to the frame body 10 while An electrical connection of the battery 20 to a functional module disposed on the rack body 10 is achieved.
  • the battery 20 is deformed by the external force and the elastic body 12 is deformed to remove the protrusion from the through hole or the groove, the locking of the battery 20 and the frame body 10 is released, so that the battery 20 can be removed from the battery receiving chamber 11 Move out.
  • the protrusion further includes a first guiding surface 221 for the battery 20 to enter the battery housing chamber 11, and a second guiding surface 222 for moving the battery 20 out of the battery housing chamber 11.
  • the first guiding surface 221 and the second guiding surface 222 are oppositely disposed, wherein the first guiding surface 221 and the second guiding surface 222 may be planar or curved surfaces.
  • the limiting portion 13 includes a first guiding mating surface 131 adapted to the first guiding surface 221 and a second guiding mating surface 132 adapted to the second guiding surface 222, so as to satisfy the battery 20 It is fixed on the frame main body 10, and is easily unlocked from the rack main body 10 under a certain external force, so that the battery 20 is easily unlocked and disconnected from the rack main body 10 when the drone 100 accidentally falls or is hit.
  • the electrical connection to the functional modules on the rack main body 10 makes it possible to protect the drone 100, and the safety of the user can be ensured by stopping the drone 100 from operating.
  • the protrusion on the battery 20 abuts against the elastic body 12 to make the elastic body 12 deform and avoid until convex.
  • the first guiding surface 221 of the protrusion is adapted to the first guiding mating surface 131 of the limiting portion 13 so that the protrusion is limited to the through hole In the hole, the battery 20 is locked in the battery receiving chamber 11, and the electrical connection portion of the battery 20 is electrically connected to the electrical mating portion on the frame body 10.
  • the user pulls the battery 20 out of the battery accommodating chamber 11 by applying a force to the grip portion 23 of the battery 20, and the raised second guiding surface 222 is opposite to the first
  • the guiding engagement surface 132 is slid, and the elastic body 12 is deformed under the urging force of the protrusion to remove the protrusion from the through hole.
  • the battery 20 is electrically disconnected from the function module disposed on the frame body 10, This allows the user to easily detach the battery 20 from the rack main body 10.
  • the limiting portion may also be a protrusion
  • the locking fitting is a through hole or a groove, that is, a replacement of the mating structure.
  • the manner in which the protrusions are engaged with the through holes or the grooves is the same as that of the above embodiment, and will not be described herein.
  • the gantry main body 10 further includes an arm 14 and a mounting portion 15 disposed at a free end of the arm 14 for mounting the power for providing power to the drone 100.
  • the arm 14 is plural and is provided on the circumferential side of the drone 100.
  • the rack main body 10 is integrally formed, that is, the rack main body 10 of the fuselage portion of the drone 100, the arm 14, the mounting portion 15, and the plurality of wall surfaces constituting the battery receiving chamber 11 are integrally formed.
  • the frame body further includes a cover (not shown) for closing the battery receiving cavity; wherein when the battery is assembled in the battery receiving cavity, there is a movable spacing between the battery and the cover.
  • the battery is integrally assembled in the battery receiving cavity, and the cover body can be used to protect the battery.
  • the grip portion can be disposed on the tail end surface of the battery body, so that the battery can be easily unlocked and disconnected from the frame body when the drone accidentally falls or is hit.
  • the electrical connection of the functional modules on the main body of the rack protects the drone and ensures the safety of the user by stopping the drone.
  • the drone 100 further includes an upper casing 101 and a lower casing 102 assembled to the frame main body 10; wherein the upper casing 101 and the frame main body 10 and the lower casing
  • the accommodation space between the 102 and the rack main body 10 constitutes a functional module of the drone 100.
  • the rack main body 10 may be provided with a mounting portion (not shown) for mounting the functional module.
  • a mounting portion for attaching a visual sensor or an imaging device to the front end surface of the rack main body may be provided.
  • an elastic body and a limiting portion are disposed in the battery accommodating cavity of the frame body, and a lock fitting matched with the limiting portion is disposed on the battery, when the battery is assembled with the frame body
  • the user only needs to insert the battery into the battery accommodating cavity.
  • the lock fitting and the limiting portion cooperate with the lock to ensure that the battery is locked in the battery accommodating cavity, and the operation mode is simple, thereby improving the user experience.
  • it is possible to eliminate the need to provide elastic elements on the body or battery of the drone to lock and unlock the battery and the body, thereby improving the aesthetics of the body and the battery.
  • the user can directly lock the battery by pushing the battery into the battery receiving cavity, and the user can directly unlock the battery by pulling the battery, thereby optimizing the operation mode.
  • the battery can be easily locked to the frame body, and can be easily detached from the frame body under a certain external force, and the operation mode is simple, and After the drone is impacted, the battery and the main body of the rack are disconnected from the functional modules on the main body of the rack to realize the power failure protection drone.

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Battery Mounting, Suspending (AREA)

Abstract

一种无人机(100)，该无人机(100)包括：机架主体(10)以及电池(20)，所述机架主体(10)包括供容置所述电池(20)的电池容纳腔(11)、位于所述电池容纳腔(11)内的弹性主体(12)、以及设置于所述弹性主体(12)上的限位部(13)，所述电池(20)上设有与所述限位部(13)配合的锁配件(22)；其中，当所述电池(20)装配于所述电池容纳腔(11)中时，所述限位部(13)与锁配件(22)配合锁定以限制所述电池(20)的移动。本发明实施例的无人机(100)中，在机架主体(10)的电池容纳腔(11)内设有弹性主体(12)以及限位部(13)，并在电池(20)上设有与限位部(13)配合的锁配件(22)，在电池(20)装配机架主体(10)时，用户仅需通过将电池(20)插入电池容纳腔(11)内即可，此时通过该锁配件(22)与限位部(13)配合锁定，可以确保电池(20)锁定在电池容纳腔(11)内，操作方式简捷，从而提高用户的使用体验。

Description

无人机 技术领域
本发明实施例涉及无人机技术领域，尤其涉及一种改进电池固定方式的无人机。
背景技术
随着无人机技术的发展，无人机正日益广泛地应用于人们的生产生活之中，例如电力巡检、地图测绘、交管安防、广告庆典等诸多领域。目前无人机的飞行基本上是通过电池提供能量，然而电池可以提供的能量是有限的，在电池电量不足时，需要为无人机更换电池，以使无人机可持续续航。现有无人机中，在更换电池时，需要用手持按压设置在电池上的弹性元件或者用手指按压设置在无人机的机身上的弹性元件以使电池从机身上解锁，操作较为繁琐，影响用户体验，另外，在电池或者机身上设置弹性元件影响电池或者机身的外观。
发明内容
有鉴于此，本发明实施例提出一种改进电池固定方式的无人机以解决上述技术问题。
为达到上述目的，本发明实施例所采用的技术方案为：
根据本发明实施例的实施例，提供了一种无人机，包括：机架主体以及电池，所述机架主体包括供容置所述电池的电池容纳腔、位于所述电池容纳腔内的弹性主体、以及设置于所述弹性主体上的限位部，所述电池上设有与所述限位部配合的锁配件；
其中，当所述电池装配于所述电池容纳腔中时，所述限位部与锁配件配合锁定以限制所述电池的移动。
进一步地，所述限位部为通孔或者凹槽，所述锁配件为凸起。
进一步地，所述限位部为凸起，所述锁配件为通孔或者凹槽。
进一步地，所述凸起包括供所述电池进入所述电池容纳腔内的第一引导面、以及将所述电池移出所述电池容纳腔的第二引导面。
进一步地，所述限位部包括与所述第一引导面适配的第一引导配合面、以及与所述第二引导面适配的第二引导配合面。
进一步地，所述机架主体还包括机臂以及设置于所述机臂自由端的安装部，所述安装部用于安装为所述无人机提供飞行动力的动力装置。
进一步地，所述机架主体一体成型设置。
进一步地，所述电池还包括设置于所述电池主体以供施加外力的握持部。
进一步地，所述机架主体还包括用于封闭所述电池容纳腔的盖体；其中，当所述电池装 配于所述电池容纳腔内后，所述电池与所述盖体之间具有活动间距。
进一步地，所述无人机还包括装配于所述机架主体的上壳体和下壳体；其中，所述上壳体与所述机架主体之间、所述下壳体与所述机架主体之间分别构成所述无人机的功能模块的容纳空间。
本发明实施例提供的技术方案可以包括以下有益效果：本发明实施例的无人机中，在机架主体的电池容纳腔内设有弹性主体以及限位部，并在电池上设有与限位部配合的锁配件，在电池装配机架主体时，用户仅需通过将电池插入电池容纳腔内即可，此时通过该锁配件与限位部配合锁定，可以确保电池锁定在电池容纳腔内，操作方式简捷，从而提高用户的使用体验。
应当理解的是，以上的一般描述和后文的细节描述仅是示例性和解释性的，并不能限制本发明实施例。
附图说明
图1是本发明实施例提供的一种无人机的整体结构示意图；
图2是本发明实施例提供的一种无人机的截面示意图；
图3是图2中的部分放大示意图；
图4是本发明实施例提供的一种机架主体的结构示意图；
图5是本发明实施例提供的一种机架主体的部分放大示意图；
图6是本发明实施例提供的一种电池的结构示意图；
图7是本发明实施例提供的一种电池的侧面示意图；
图8是本发明实施例提供的一种机架主体中装配电池的结构示意图；
图9是本发明实施例提供的电池从机架主体中拆卸出的结构示意图。
具体实施方式
以下将结合附图所示的具体实施方式对本发明实施例进行详细描述。但这些实施方式并不限制本发明实施例，本领域的普通技术人员根据这些实施方式所做出的结构、方法、或功能上的变换均包含在本发明实施例的保护范围内。
在本发明实施例使用的术语是仅仅出于描述特定实施例的目的，而非旨在限制本发明实施例。在本发明实施例和所附权利要求书中所使用的单数形式的“一种”、“所述”和“该”也旨在包括多数形式，除非上下文清楚地表示其他含义。还应当理解，本文中使用的术语“和/或”是指并包含一个或多个相关联的列出项目的任何或所有可能组合。
下面结合附图，对本发明实施例的一些实施方式作详细说明，在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
如图1至图4所示，本发明实施例的无人机100包括机架主体10以及装配于机架主体10的电池20，该机架主体10包括供容置电池20的电池容纳腔11。在本实施例中，该机架主体10还包括位于电池容纳腔11内的弹性主体12、以及设置于弹性主体12上的限位部13，该电池20上设有与限位部13配合的锁配件22，以使电池20可以锁定于电池容纳腔11内。
其中，如图2结合图8所示，电池20可以在外力的作用下，装配到电池容纳腔11中，当电池20装配于电池容纳腔11中时，限位部13与锁配件22配合锁定以限制电池20的移动，即该电池20实现装配于机架主体10上，同时电池20与设置在机架主体10上的功能模块实现电气连接；如图5结合图9所示，当电池20在外力的作用下解除限位部13与锁配件22的锁定以将电池20移出电池容纳腔11，从而停止为无人机100供电。
本实施例中，利用机架主体10上的弹性主体12的弹性属性，可以满足限位部13与锁配件22在弹性主体12的弹性配合下锁定及解除锁定，如此以使电池20的固定方式及拆卸方式更加便捷，通过这种方式，可以无需在无人机100的机身或者电池20上设置弹性元件以实现电池20与机身的锁定与解锁，提高了机身和电池20的美观程度。另外，用户可以直接通过将电池20推入电池容纳腔11以实现电池20的锁定，用户可以直接通过抽拉电池20以实现电池20的解锁，优化了操作方式。并且该无人机100在意外坠落或者受到撞击时，由于弹性主体12的弹性震动，可以使锁配件22与限位部13解除，从而使电池20与机架主体10上的功能模块断开电气连接，进而起到断电保护无人机100的作用。可选地，该弹性主体12为弹性臂。
弹性主体12及限位部13设置于机架主体10构成电池容纳腔11的任一侧腔壁上，锁配件22设置于电池20上的位置则与限位部13所在的位置配合，满足电池20装配于电池容纳腔11中限位部13与锁配件22配合锁定即可。本实施例中，该弹性主体12及限位部13设置于机架主体10构成电池容纳腔11的上侧壁上，相对应地，锁配件22设置于电池20的上表面。当然，弹性主体12及限位部13的设置并不限于仅在机架主体10构成电池容纳腔11的上侧壁上，弹性主体12及限位部13可以为多个，可以根据设计需求，设置于机架主体10构成电池容纳腔11的任一侧腔壁上。
如图6和图7结合图4和图5所示，电池20包括电池主体21、以及设于电池主体21上的电连接部(未图示)，机架主体10上设有与电连接部配合电性连接的电配合部(未图示)。其中，当电池20完成装配于电池容纳腔11中，电连接部与电配合部对应电性连接以实现为设置在机架主体10上的功能模块供电。本实施例中，在电池20装配于电池容纳腔11的方向 上，电池20最先进入电池容纳腔11的一端为顶端，与电池20的顶端相对的另一端为电池20的尾端。该电连接部设置于电池主体21的顶端面上。当然，在其他实施例中，该电连接部也可以设置于电池主体21的周侧面上或其他任意位置。
进一步地，该电池20还包括用于接收被施加的外力的握持部23，从而可以便于用户施力于该电池20，以使电池20可以从电池容纳腔11中退出。本实施例中，该握持部23设置于电池主体21的尾端，其中，当电池20完成装配于电池容纳腔11中，该握持部23位于电池容纳腔11的装配口处。在一可选实施例中，该握持部23为两个，分设于电池主体21尾端的上下两侧面或者左右两侧面，如此可以便于用户握持。
在一实施例中，该限位部13可以为通孔或者凹槽，锁配件22为凸起。其中，当电池20装配于电池容纳腔11中时，该凸起插置入通孔内或凹槽内，从而可以限制电池20的移动，即该电池20实现装配于机架主体10上，同时实现电池20与设置在机架主体10上的功能模块的电气连接。当电池20在外力的作用下，弹性主体12发生形变以使凸起从通孔或者凹槽内移出后，则解除电池20与机架主体10的锁定，从而可以将电池20从电池容纳腔11中移出。
如图5至图7所示，进一步地，该凸起包括供电池20进入电池容纳腔11内的第一引导面221、以及将电池20移出电池容纳腔11的第二引导面222。该第一引导面221和第二引导面222相对设置，其中，该第一引导面221和第二引导面222可以为平面或者弧形面。当该第一引导面221和第二引导面222为平面时，在凸起朝向限位部13的方向上，第一引导面221与第二引导面222之间的间距沿限位部13的方向逐渐减小。
相对应地，该限位部13包括与第一引导面221适配的第一引导配合面131、以及与第二引导面222适配的第二引导配合面132，如此即可以满足将电池20固定在机架主体10上，且在一定外力作用下容易与机架主体10解除锁定，从而在无人机100意外坠落时或者受到撞击时，电池20容易与机架主体10解除锁定并断开与机架主体10上的功能模块的电气连接，从而可以保护该无人机100，而且通过使无人机100停止运行可以保证用户的安全。
具体地，如图1至图9所示，在电池20装配于机架主体10的电池容纳腔11时，电池20上的凸起抵持于弹性主体12以使弹性主体12形变避让，直至凸起对应于通孔(该示例中以通孔为例说明)时，该凸起的第一引导面221与限位部13的第一引导配合面131适配，以使该凸起限定于通孔内，即实现了电池20锁定于电池容纳腔11内，此时电池20的电连接部与机架主体10上的电配合部电性连接。在电池20从机架主体10上拆卸下来时，用户通过施力于电池20的握持部23，以将电池20从电池容纳腔11内拔出，该凸起的第二引导面222相对第二引导配合面132滑动，弹性主体12在凸起的抵持力下形变，以使凸起从通孔内移出， 此时电池20与设置在机架主体10上的功能模块断开电气连接，如此可以使用户轻松地将电池20从机架主体10上拆卸出。
在又一实施例中，限位部还可以为凸起，锁配件为通孔或者凹槽，即配合结构的置换。在该实施例中，该凸起与通孔或者凹槽的配合方式与上述实施例相同，在此就不再赘述。
进一步地，如图1和图4所示，机架主体10还包括机臂14以及设置于机臂14自由端的安装部15，该安装部15用于安装为无人机100提供飞行动力的动力装置30。该机臂14为多个，分设于无人机100的周侧面上。其中，该机架主体10一体成型设置，即无人机100的机身部分的机架主体10、机臂14、安装部15、以及构成电池容纳腔11的多个壁面均一体成型制成。
在又一实施例中，该机架主体还包括用于封闭电池容纳腔的盖体(未图示)；其中，当电池装配于电池容纳腔中，电池与盖体之间具有活动间距。该实施例中，电池整体装配于电池容纳腔内，盖体可以用于保护该电池，该电池装配于电池容纳腔中后，电池与盖体之间具有间距，该间距大于锁配件在电池与机架主体装配方向上的尺寸，握持部可以设置于电池主体的尾部端面上，如此同样可以满足在无人机意外坠落时或者受到撞击时，电池容易与机架主体解除锁定并断开与机架主体上的功能模块的电气连接，从而可以保护该无人机，而且通过使无人机停止运行可以保证用户的安全。
如图1和图2所示，无人机100还包括装配于机架主体10的上壳体101和下壳体102；其中，该上壳体101与机架主体10之间、下壳体102与机架主体10之间分别构成无人机100的功能模块的容纳空间。另外，该机架主体10上也可以设有供安装功能模块的装配部(未标示)，例如：在机架主体的前端面设有装配视觉传感器、或者拍摄装置等的装配部。
本发明实施例的无人机中，在机架主体的电池容纳腔内设有弹性主体以及限位部，并在电池上设有与限位部配合的锁配件，在电池装配机架主体时，用户仅需通过将电池插入电池容纳腔内即可，此时通过该锁配件与限位部配合锁定，可以确保电池锁定在电池容纳腔内，操作方式简捷，从而提高用户的使用体验。通过这种方式，可以无需在无人机的机身或者电池上设置弹性元件以实现电池与机身的锁定与解锁，提高了机身和电池的美观程度。另外，用户可以直接通过将电池推入电池容纳腔以实现电池的锁定，用户可以直接通过抽拉电池以实现电池的解锁，优化了操作方式。进一步地，通过对锁配件及限位部的结构特征的限定，可以使电池便于锁定于机架主体上，在一定外力下可以便于从机架主体内拆卸出，操作方式简便，而且还可以在无人机受到撞击后以使电池与机架主体断开与机架主体上的功能模块的电气连接，从而实现断电保护无人机。
本领域技术人员在考虑说明书及实践这里公开的发明实施例后，将容易想到本发明实施 例的其它实施方案。本申请旨在涵盖本发明实施例的任何变型、用途或者适应性变化，这些变型、用途或者适应性变化遵循本发明实施例的一般性原理并包括本发明实施例未公开的本技术领域中的公知常识或惯用技术手段。说明书和实施例仅被视为示例性的，本发明实施例的真正范围和精神由本申请的权利要求指出。
应当理解的是，本发明实施例并不局限于上面已经描述并在附图中示出的精确结构，并且可以在不脱离其范围进行各种修改和改变。本发明实施例的范围仅由所附的权利要求来限制。

Claims (10)

  1. 一种无人机，其特征在于，包括：机架主体以及电池，所述机架主体包括供容置所述电池的电池容纳腔、位于所述电池容纳腔内的弹性主体、以及设置于所述弹性主体上的限位部，所述电池上设有与所述限位部配合的锁配件；
    其中，当所述电池装配于所述电池容纳腔中时，所述限位部与锁配件配合锁定以限制所述电池的移动。
  2. 根据权利要求1所述的无人机，其特征在于，所述限位部为通孔或者凹槽，所述锁配件为凸起。
  3. 根据权利要求1所述的无人机，其特征在于，所述限位部为凸起，所述锁配件为通孔或者凹槽。
  4. 根据权利要求2所述的无人机，其特征在于，所述凸起包括供所述电池进入所述电池容纳腔内的第一引导面、以及将所述电池移出所述电池容纳腔的第二引导面。
  5. 根据权利要求4所述的无人机，其特征在于，所述限位部包括与所述第一引导面适配的第一引导配合面、以及与所述第二引导面适配的第二引导配合面。
  6. 根据权利要求1所述的无人机，其特征在于，所述机架主体还包括机臂以及设置于所述机臂自由端的安装部，所述安装部用于安装为所述无人机提供飞行动力的动力装置。
  7. 根据权利要求1至6中任一项所述的无人机，其特征在于，所述机架主体一体成型设置。
  8. 根据权利要求1所述的无人机，其特征在于，所述电池还包括设置于所述电池主体以供施加外力的握持部。
  9. 根据权利要求1所述的无人机，其特征在于，所述机架主体还包括用于封闭所述电池容纳腔的盖体；其中，当所述电池装配于所述电池容纳腔内后，所述电池与所述盖体之间具有活动间距。
  10. 根据权利要求1所述的无人机，其特征在于，所述无人机还包括装配于所述机架主体的上壳体和下壳体；其中，所述上壳体与所述机架主体之间、所述下壳体与所述机架主体之间分别构成所述无人机的功能模块的容纳空间。
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