WO2017091948A1 - 电池容纳装置及无人飞行器、电子装置 - Google Patents

电池容纳装置及无人飞行器、电子装置 Download PDF

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Publication number
WO2017091948A1
WO2017091948A1 PCT/CN2015/095990 CN2015095990W WO2017091948A1 WO 2017091948 A1 WO2017091948 A1 WO 2017091948A1 CN 2015095990 W CN2015095990 W CN 2015095990W WO 2017091948 A1 WO2017091948 A1 WO 2017091948A1
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WO
WIPO (PCT)
Prior art keywords
battery
substrate
locking structure
elastic piece
fixing frame
Prior art date
Application number
PCT/CN2015/095990
Other languages
English (en)
French (fr)
Inventor
张永生
陈泽杰
段玉琴
肖文龙
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201580003652.3A priority Critical patent/CN105939933B/zh
Priority to PCT/CN2015/095990 priority patent/WO2017091948A1/zh
Publication of WO2017091948A1 publication Critical patent/WO2017091948A1/zh

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Classifications

    • 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
    • H01M50/249—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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • 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
    • H01M50/204—Racks, modules or packs for multiple batteries or multiple cells
    • H01M50/207—Racks, modules or packs for multiple batteries or multiple cells characterised by their shape
    • H01M50/209—Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for prismatic or rectangular cells
    • 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
    • H01M50/244—Secondary casings; Racks; Suspension devices; Carrying devices; Holders characterised by their mounting method
    • 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
    • H01M50/264—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders with fastening means, e.g. locks for cells or batteries, e.g. straps, tie rods or peripheral frames
    • 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
    • H01M50/271—Lids or covers for the racks or secondary casings
    • 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
    • H01M50/50—Current conducting connections for cells or batteries
    • 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

  • the present invention relates to the field of battery assembly technology, and in particular, to a battery receiving device and an unmanned aerial vehicle and an electronic device using the battery receiving device.
  • a battery receiving device comprising:
  • a plurality of battery fixing frames are radially disposed and supported between the first substrate and the second substrate, and each of the battery fixing frames is formed with a receiving cavity for inserting a battery.
  • the plurality of battery fixing frames are evenly arranged between the first substrate and the second substrate; or
  • the plurality of battery fixing frames are arranged symmetrically between the first substrate and the second substrate.
  • the plurality of battery fixing frames are arranged along the same plane; or the plurality of battery fixing frames are disposed between the first substrate and the second substrate in a stacked manner.
  • a first locking structure is disposed on the inner wall of the receiving cavity, and the first locking structure is configured to cooperate with the second locking structure on the battery when the battery is inserted into the receiving cavity. Thereby the battery is locked in the receiving cavity.
  • the battery receiving device further includes a plurality of partitions radially disposed and supported between the first substrate and the second substrate, each of the battery fixing frames being disposed
  • the receiving cavity on the battery fixing frame is a through hole opened at both ends between adjacent end portions of the two adjacent partition plates, and the adjacent two of the partition plates are close to each other One end of the battery is respectively abutted against an end of the battery passing through the receiving cavity when the battery is inserted into the receiving cavity.
  • a plurality of through holes are respectively formed in the partition plate and/or the battery fixing frame.
  • the spacers are detachably connected to the first substrate and the second substrate, respectively.
  • the spacer is provided with a connection hole
  • the first substrate and the second substrate are respectively provided with connection holes opposite to the connection holes on the spacer, the first substrate and the first substrate
  • the partitions are fixed together by a joint of the connecting members with the opposite connecting holes of the first substrate and the partition, and the second substrate and the partition are passed through the connecting member and the second The substrate and the opposing connecting holes on the spacer are fixed together.
  • the spacer further has a support rod perpendicular to the spacer on a side contacting the first substrate or the second substrate, the support rod and the first substrate or the a second substrate detachably connected to prevent the spacer from twisting between the first substrate or the second substrate, and to enhance the spacer on the first substrate and the second substrate The support provided between the two.
  • the battery fixing frame is detachably connected to the first substrate and the second substrate, respectively.
  • the battery fixing frame is provided with a connecting hole
  • the first substrate and the second substrate are respectively provided with connecting holes opposite to the connecting holes on the battery fixing frame
  • the first substrate and the first substrate are fixed together by a cooperation of the connecting members with the connecting holes of the first substrate and the battery fixing frame, and the connecting between the second substrate and the battery fixing frame It is fixed together with the cooperation of the second substrate and the opposite connecting holes on the battery fixing frame.
  • the connecting hole is a threaded hole
  • the connecting member is a screw
  • An unmanned aerial vehicle comprising a battery receiving device as described above, the battery receiving device constituting a fuselage of the unmanned aerial vehicle.
  • the UAV further includes a plurality of batteries
  • the battery includes a battery body, a spring piece, and a second locking structure
  • the elastic piece is disposed at a side of one end of the battery body, and the elastic piece is in a natural state a distance from the battery body
  • the second locking structure is disposed on the elastic piece, and the elastic piece abuts against the inner wall of the receiving cavity of the battery receiving device when the battery is inserted into the receiving cavity of the battery receiving device And engaging the second locking structure on the elastic piece with the first locking structure on the battery receiving device to lock the battery in the receiving cavity.
  • the elastic piece is elastically deformed by an external force and moves toward a direction of the battery body, and the second locking structure on the elastic piece is separated from the battery receiving device by following the movement of the elastic piece.
  • the first locking structure releases the battery from the receiving cavity of the battery receiving device.
  • the elastic piece extends from at least one side of the battery body toward the end of the battery body inserted into the end of the receiving cavity, and the extended end is separated from the battery body, and the second locking structure is provided. At the free end of the shrapnel; or,
  • the elastic piece protrudes from at least one side of one end of the battery body, and the second locking structure is disposed at a position where the elastic piece is away from the battery body.
  • first locking structure on the battery fixing frame is a rib or a card slot
  • second locking structure on the battery is a hook structure
  • the first locking structure on the battery fixing frame is a convex structure, and the second locking structure on the battery is a groove structure;
  • the first locking structure on the battery fixing frame is a groove structure
  • the second locking structure on the battery is a convex structure
  • two or more of the batteries are integrally formed by splicing and then housed in the receiving cavity of the battery fixing frame.
  • each of the batteries is housed in a battery case, or the battery is integrally formed with the battery case, and a side of the battery case is provided with a splicing structure, and the battery case passes through the splicing structure and One or more battery cases are spliced together.
  • first substrate and the second substrate of the battery receiving device respectively constitute an upper cover and a lower cover of the body of the UAV.
  • the UAV further includes a plurality of arms respectively mounted between adjacent two battery fixing frames of the battery receiving device; and/or
  • the UAV further includes a landing gear mounted on the second substrate of the battery receiving device; and/or
  • the UAV further includes a load connection mechanism mounted to an outer surface of the second substrate of the battery receiving device.
  • An electronic device includes a body and a battery receiving device as described above, the battery receiving device being mounted to a central portion of the body and constituting a part of the body.
  • the electronic device further includes a plurality of batteries
  • the battery includes a battery body, a spring piece, and a second locking structure
  • the elastic piece is disposed at a side of one end of the battery body, and the elastic piece is away from the natural state
  • the battery body; the second locking structure is disposed on the elastic piece, and the elastic piece abuts against the inner wall of the receiving cavity of the battery receiving device when the battery is inserted into the receiving cavity of the battery receiving device And engaging a second locking structure on the elastic piece with the first locking structure on the battery receiving device to lock the battery in the receiving cavity.
  • the elastic piece is elastically deformed by an external force and moves toward a direction of the battery body, and the second locking structure on the elastic piece is separated from the battery receiving device by following the movement of the elastic piece.
  • the first locking structure releases the battery from the receiving cavity of the battery receiving device.
  • the elastic piece extends from at least one side of the battery body toward the end of the battery body inserted into the end of the receiving cavity, and the extended end is separated from the battery body, and the second locking structure is provided. At the free end of the shrapnel; or,
  • the elastic piece protrudes from at least one side of one end of the battery body, and the second locking structure is disposed at a position where the elastic piece is away from the battery body.
  • first locking structure on the battery fixing frame is a rib or a card slot
  • second locking structure on the battery is a hook structure
  • the first locking structure on the battery fixing frame is a convex structure, and the second locking structure on the battery is a groove structure;
  • the first locking structure on the battery fixing frame is a groove structure
  • the second locking structure on the battery is a convex structure
  • two or more of the batteries are integrally formed by splicing and then housed in the receiving cavity of the battery fixing frame.
  • each of the batteries is housed in a battery case, or the battery is integrally formed with the battery case, and a side of the battery case is provided with a splicing structure, and the battery case passes through the splicing structure and One or more battery cases are spliced together.
  • the electronic device is a remote controller or a remote control vehicle.
  • first substrate and/or the second substrate of the battery receiving device adopt an upper cover and/or a lower cover of the body.
  • the battery accommodating device of the present invention replaces a plurality of battery fixing frames radially in the middle of the fuselage by replacing a current single battery with a large capacity of the aircraft for a battery life with a relatively small capacity.
  • the battery accommodating device of the present invention replaces a plurality of battery fixing frames radially in the middle of the fuselage by replacing a current single battery with a large capacity of the aircraft for a battery life with a relatively small capacity.
  • the number of used batteries can be increased or decreased according to actual needs, while reducing the weight of the whole machine, the balance of the center of gravity of the body is also ensured, and the applied to the A carrier, such as the flight performance of the UAV or the mobility of the electronic device.
  • FIG. 1 is a perspective view of a battery housing device in accordance with an embodiment of the present invention.
  • Fig. 2 is a view showing the internal structure of the battery housing device of Fig. 1.
  • Fig. 3 is an exploded perspective view showing the battery housing device of Fig. 1;
  • Fig. 4 is a perspective view of a battery according to an embodiment of the present invention.
  • Fig. 5 is a perspective view showing a battery housed in a battery case according to an embodiment of the present invention.
  • Figure 6 is a perspective view of a plurality of batteries spliced together through a battery case in accordance with an embodiment of the present invention.
  • FIG. 7 is a perspective view of an unmanned aerial vehicle according to an embodiment of the present invention, the unmanned aerial vehicle including the battery receiving device of FIG. 1.
  • FIG. 8 is a partial cross-sectional view of an electronic device including the battery receiving device of FIG. 1 in accordance with an embodiment of the present invention.
  • the battery housing device 20 includes a first substrate 21, a second substrate 22, and a plurality of battery fixing frames 24.
  • the plurality of battery fixing frames 24 are radially disposed and supported between the first substrate 21 and the second substrate 22.
  • each of the battery fixing frames 24 is formed with a receiving cavity 241 (shown in FIG. 3) for inserting the battery 30, and the receiving cavity 241 is for receiving the battery 30.
  • the plurality of battery fixing frames 24 are evenly arranged between the first substrate 21 and the second substrate 22. In other embodiments, the plurality of battery fixing frames 24 may be arranged symmetrically between the first substrate 21 and the second substrate 22 in a center.
  • the plurality of battery fixing frames 24 are arranged along the same plane so as to reduce the spacing between the first substrate 21 and the second substrate 22, thereby reducing the overall capacity of the battery receiving device 20. thickness.
  • the plurality of battery fixing frames 24 may also be disposed between the first substrate 21 and the second substrate 22 in a stacked manner, that is, a part of the plurality of battery fixing frames 24 are the same.
  • the other portions are arranged in a plane, and the other portions are arranged along the other plane, and the two portions of the battery fixing frame 24 are stacked in the direction from the first substrate 21 to the second substrate 22.
  • the two portions of the battery fixing frame 24 may completely overlap in the direction from the first substrate 21 to the second substrate 22, or may partially overlap.
  • the battery fixing frame 24 may be stacked in three or more layers.
  • a first locking structure 242 is disposed on an inner wall of the receiving cavity 241 , and the first locking structure 242 is configured to insert the battery 30 into the receiving cavity 241 .
  • the battery 30 includes a battery body 31 , a spring piece 32 , and a second locking structure 33 .
  • the elastic piece 32 is disposed on a side surface of one end of the battery body 31, and the elastic piece 32 is away from the battery body 31 in a natural state.
  • the second locking structure 33 is disposed on the elastic piece 32.
  • the elastic piece 32 When the battery 30 is inserted into the receiving cavity 241, the elastic piece 32 can be elastically deformed by an external force and moved toward the battery body 31. After the external force disappears, the elastic piece 32 recovers and resists against the inner wall of the receiving cavity 241 by the resilience force, and the second locking structure 33 on the elastic piece 32 and the first A locking structure 242 mates to lock the battery 30 in the receiving cavity 241.
  • the elastic piece 32 can be deformed by an external force and moved toward the battery body 31, and the second locking structure 33 on the elastic piece 32 follows the same. The movement of the elastic piece 32 is released from the first locking structure 242 on the battery housing device 20, so that the battery 30 is disengaged from the housing cavity 241 of the battery housing device 20.
  • the elastic piece 32 extends from at least one side surface of the battery body 31 toward the end of the battery body 31 inserted into the receiving cavity 241, and the extended end is separated from the battery body 31.
  • the second locking structure 33 is disposed at a free end of the elastic piece 32.
  • the elastic piece 32 may protrude from at least one side of one end of the battery body 31 , and the second locking structure 33 is disposed at a position where the elastic piece 32 is away from the battery body 31 .
  • the first locking structure 242 on the battery fixing frame 24 is a rib
  • the second locking structure 33 on the battery 30 is a hook structure
  • the first locking structure 242 on the battery fixing frame 24 can be a card slot
  • the second locking structure 33 on the battery 30 can be a hook structure
  • the first locking structure 242 on the battery fixing frame 24 may be a convex structure
  • the second locking structure 33 on the battery 30 may be a groove structure
  • the first locking structure 242 on the battery fixing frame 24 may be a groove structure.
  • the second locking structure 33 on the battery 30 may be a convex structure.
  • two or more of the batteries 30 may be integrally formed by splicing and then received into the receiving cavity 241 of the battery fixing frame 24.
  • each of the batteries 30 can be housed in a battery case 34, or the battery 30 can be integrally formed with the battery case 34.
  • a splicing structure (not shown) is disposed on a side of the battery case 34.
  • the battery case 34 can be spliced together with one or more battery cases 34 through the splicing structure.
  • the battery housing device 20 further includes a plurality of partitions 23 that are radially disposed and supported between the first substrate 21 and the second substrate 22.
  • each of the battery fixing frames 24 is disposed between the two adjacent ends of the two partition plates 23, and the receiving cavity 241 of the battery fixing frame 24 is two.
  • the open end opening, the shortest distance between the two adjacent partitions 23 is less than or equal to the width of the battery 30, such that the adjacent two of the partitions 23 are closer to each other.
  • the battery accommodating device 20 of the present invention is provided with a corresponding locking structure on the battery fixing frame 24 and the battery 30, and is abutted against the near end by two adjacent spacers 23
  • the battery 30 is inserted into the end of the receiving cavity 241, so that the stability of the battery 30 after insertion into the receiving cavity 241 can be ensured, and the battery 30 can be prevented from being generated from the receiving cavity 241 during movement or flight. An accident that came out.
  • the spacers 23 are detachably connected to the first substrate 21 and the second substrate 22, respectively.
  • the partition plate 23 is provided with a connecting hole 231
  • the first substrate 21 and the second substrate 22 are respectively provided with connecting holes opposite to the connecting holes 231 of the partition plate 23.
  • 211, 221 the first substrate 21 and the partition plate 23 are coupled with the opposite connecting holes 211, 231 of the first substrate 21 and the partition plate 23 by a connecting member (not shown).
  • the second substrate 22 and the partition plate 23 are coupled with the opposite connecting holes 221, 231 of the second substrate 22 and the partition plate 23 by a connecting member (not shown). Fixed together.
  • the battery fixing frame 24 is detachably connected to the first substrate 21 and the second substrate 22, respectively.
  • the battery fixing frame 24 is provided with a connecting hole 243, and the first substrate 21 and the second substrate 22 are respectively disposed opposite to the connecting hole 243 of the battery fixing frame 24.
  • the connection holes 212 and 222, the first substrate 21 and the battery fixing frame 24 are connected to the first substrate 21 and the battery fixing frame 24 via a connecting member (not shown),
  • the 243 is fixed together, and the second substrate 22 and the battery fixing frame 24 are connected to the second substrate 22 and the battery fixing frame 24 through a connecting member (not shown).
  • the cooperation of 222 and 243 is fixed together.
  • the connecting holes 211, 212, 221, 222, 231, and 243 are respectively threaded holes, and the connecting member is a screw.
  • a plurality of through holes 232, 244 are respectively defined in the partition plate 23 and the battery fixing frame 24, thereby ensuring provision between the first substrate 21 and the second substrate 22.
  • the overall weight of the battery receiving device 20 is alleviated on the premise of sufficient supporting force.
  • the partition plate 23 is further provided with a support rod 233 substantially perpendicular to the partition plate 23 on a side contacting the first substrate 21 or the second substrate 22, the support The rod 233 is detachably connected to the first substrate 21 or the second substrate 22 for preventing the spacer 23 from twisting between the first substrate 21 or the second substrate 22, and enhancing the The supporting force provided between the first substrate 21 and the second substrate 22 is described in the separator 23.
  • the support rod 233 may also be omitted.
  • the battery housing device 20 can be applied to an unmanned aerial vehicle 1.
  • the UAV 1 further includes a plurality of the batteries 30.
  • the battery housing device 20 constitutes the body of the UAV 1 and is used to house the battery 30.
  • the first substrate 21 and the second substrate 22 of the battery receiving device 20 can be used as the upper cover and the lower cover of the body of the UAV 1 respectively, thereby alleviating the unmanned The overall weight of the aircraft 1.
  • the UAV 1 further includes, but is not limited to, an arm 101, a landing gear 102, and a load connecting mechanism 103.
  • the number of the arm 101 may be multiple and installed in the same.
  • the landing gear 102 can be mounted on the second substrate 22 of the battery receiving device 20, and the load connection mechanism 103, such as a pan/tilt, can be mounted on the outer surface of the second substrate 22 of the battery receiving device 20.
  • the battery fixing frame 24 can also serve as a carrier for other functional hardware of the UAV 1, for example, an outer surface of the first substrate 21 of the battery fixing frame 24 can be used to mount the antenna 104 of the UAV 1 .
  • the batteries 30 accommodated in the battery fixing frame 24 are also arranged in a radial uniform or centrally symmetric manner.
  • the UAV 1 is mounted on the fuselage to ensure that the center of gravity of the UAV 1 coincides with the center of the UAV 1 to improve flight stability.
  • the battery accommodating device 20 of the present invention replaces the manner in which the current aircraft 1 uses a single battery 30 having a large capacity to maintain the battery life of a plurality of batteries 30 having a relatively small capacity, and radiates the plurality of battery fixing frames 24 Provided in the middle of the fuselage, the rigidity of the battery 30 and the battery fixing frame 24 itself can enhance the structural strength of the aircraft 1 as a whole, and make full use of the internal space of the UAV 1 for the absence of The human aircraft 1 expands the external components to reserve space.
  • the number of used batteries can be increased or decreased according to actual needs, while reducing the weight of the whole machine, the balance of the center of gravity of the body is also ensured, and the Flight performance of the human aircraft 1.
  • the battery housing device 20 can also be applied to an electronic device 2.
  • the electronic device 2 can be a remote device, or a mobile device such as a remote control vehicle.
  • the electronic device 2 further includes a body 12 and a plurality of the batteries 30.
  • the battery receiving device 20 is mounted in the middle of the body 12 and constitutes a part of the body 12, that is, the first substrate 21 and/or the second substrate 22 of the battery receiving device 20 can adopt the The upper cover and/or the lower cover of the body 12 reduce the overall weight of the electronic device 2.
  • the battery housing device 20 is for housing the battery 30.
  • the internal space of the electronic device 2 can be fully utilized, and a space is reserved for the external components of the electronic device 2.
  • the loaded battery 30 can be reduced according to actual needs, so as to reduce the weight of the whole machine, and ensure the balance of the center of gravity of the whole machine, and improve the moving performance of the electronic device 2.

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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)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Battery Mounting, Suspending (AREA)

Abstract

一种电池容纳装置（20），包括第一基板（21）、第二基板（22）以及多个电池固定框架（24）。所述多个电池固定框架（24）呈辐射状设置并支撑于所述第一基板（21）和第二基板（22）之间。每一所述电池固定框架（24）上形成有供电池（30）插入的收容腔（241）。本发明还涉及一种使用所述电池容纳装置（20）的飞行器以及电子装置。

Description

电池容纳装置及无人飞行器、电子装置 技术领域
本发明涉及电池装配技术领域，特别涉及一种电池容纳装置以及使用所述电池容纳装置的无人飞行器和电子装置。
背景技术
现有飞行器的电池安装方案多半是通过魔术贴将电池粘接在飞行器的顶部或底部，但这样的粘接方式会使电池与飞行器之间连接不牢靠，导致电池在飞行器飞行过程中容易从飞行器中脱出。其次，为了延长飞行器的飞行时间，通常要增大电池容量，从而导致电池体积过大，在机身内安装不便，造成了机身空间浪费，又占用了顶部、底部空间，导致外部扩展件没有安装位置。同时，为了增强机身刚性，又需要在机身内增加许多结构连接件，从而增加了额外的重量，降低了飞行器的续航能力。此外，通过粘接方式粘接的电池无法保证每次粘接的重复精度，导致机身重心经常发生变化，影响了飞行器的飞行性能。
发明内容
有鉴于此，有必要提出一种电池容纳装置以及使用所述电池容纳装置的无人飞行器和电子装置，以解决上述问题。
一种电池容纳装置，包括：
第一基板和第二基板；
多个电池固定框架，呈辐射状设置并支撑于所述第一基板和第二基板之间，每一所述电池固定框架上形成有供电池插入的收容腔。
进一步地，所述多个电池固定框架均匀地排布在所述第一基板和所述第二基板之间；或者，
所述多个电池固定框架呈中心对称排布在所述第一基板和所述第二基板之间。
进一步地，所述多个电池固定框架沿同一平面排布；或者，所述多个电池固定框架采用叠置的方式设置于所述第一基板与所述第二基板之间。
进一步地，所述收容腔内壁上设有第一锁紧结构，所述第一锁紧结构用于在所述电池插入所述收容腔时与所述电池上的第二锁紧结构相配合，从而将所述电池锁紧在所述收容腔中。
进一步地，所述电池容纳装置还包括多个隔板，所述多个隔板呈辐射状设置并支撑于所述第一基板和所述第二基板之间，每一所述电池固定框架设置在相邻的两个所述隔板相距较远的端部之间，所述电池固定框架上的所述收容腔为两端开口的通孔，相邻的两个所述隔板相距较近的一端在所述电池插入所述收容腔时分别抵持于所述电池穿过所述收容腔的端部。
进一步地，所述隔板及/或所述电池固定框架上分别开设有多个通孔。
进一步地，所述隔板分别与所述第一基板和所述第二基板可拆卸连接。
进一步地，所述隔板上设有连接孔，所述第一基板以及所述第二基板上分别设有与所述隔板上的连接孔相对的连接孔，所述第一基板与所述隔板之间通过连接件与所述第一基板和所述隔板上相对的连接孔的配合而固定在一起，所述第二基板与所述隔板之间通过连接件与所述第二基板和所述隔板上相对的连接孔的配合而固定在一起。
进一步地，所述隔板在与所述第一基板或所述第二基板接触的一侧上还设有与所述隔板垂直的支撑杆，所述支撑杆与所述第一基板或所述第二基板可拆卸连接，用于避免所述隔板在所述第一基板或所述第二基板之间扭动，并增强所述隔板在所述第一基板和所述第二基板之间提供的支撑力。
进一步地，所述电池固定框架分别与所述第一基板和所述第二基板可拆卸连接。
进一步地，所述电池固定框架上设有连接孔，所述第一基板以及所述第二基板上分别设有与所述电池固定框架上的连接孔相对的连接孔，所述第一基板与所述电池固定框架之间通过连接件与所述第一基板和所述电池固定框架上相对的连接孔的配合而固定在一起，所述第二基板与所述电池固定框架之间通过连接件与所述第二基板和所述电池固定框架上相对的连接孔的配合而固定在一起。
进一步地，所述连接孔为螺纹孔，所述连接件为螺钉。
一种无人飞行器，包括如上所述的电池容纳装置，所述电池容纳装置构成所述无人飞行器的机身。
进一步地，所述无人飞行器还包括多个电池，所述电池包括电池本体、弹片以及第二锁紧结构，所述弹片设置于所述电池本体的一端的侧面，所述弹片在自然状态下远离所述电池本体；所述第二锁紧结构设置于所述弹片上，所述弹片在所述电池插入所述电池容纳装置的收容腔时抵持于所述电池容纳装置的收容腔的内壁上，并使所述弹片上的第二锁紧结构与所述电池容纳装置上的第一锁紧结构相配合，从而将所述电池锁紧在所述收容腔中。
进一步地，所述弹片在外力的作用下发生弹性形变并向靠近所述电池本体的方向移动，所述弹片上的第二锁紧结构跟随所述弹片的移动而脱离所述电池容纳装置上的第一锁紧结构，使所述电池从所述电池容纳装置的收容腔中脱出。
进一步地，所述弹片自所述电池本体的至少一个侧面向所述电池本体插入所述收容腔的端部的方向延伸，且延伸末端与所述电池本体分离，所述第二锁紧结构设于所述弹片的自由端；或者，
所述弹片凸设于所述电池本体一端的至少一个侧面，所述第二锁紧结构设于所述弹片远离所述电池本体之处。
进一步地，所述电池固定框架上的第一锁紧结构为肋条或卡槽，所述电池上的第二锁紧结构为卡钩结构；或者，
所述电池固定框架上的第一锁紧结构为凸起结构，所述电池上的第二锁紧结构为凹槽结构；或者，
所述电池固定框架上的第一锁紧结构为凹槽结构，所述电池上的第二锁紧结构为凸起结构。
进一步地，两个或两个以上的所述电池通过拼接的方式构成一个整体之后再收容至所述电池固定框架的收容腔中。
进一步地，每一所述电池收容至一电池盒中，或者，所述电池与所述电池盒一体成型，所述电池盒的侧面上设有拼接结构，所述电池盒通过所述拼接结构与一个或一个以上的电池盒拼接在一起。
进一步地，所述电池容纳装置的第一基板以及第二基板分别构成所述无人飞行器的机身的上盖板以及下盖板。
进一步地，所述无人飞行器还包括多个机臂，所述多个机臂分别安装于所述电池容纳装置的相邻两个电池固定框架之间；及/或，
所述无人飞行器还包括起落架，所述起落架安装于所述电池容纳装置的第二基板上；及/或，
所述无人飞行器还包括负载连接机构，所述负载连接机构安装于所述电池容纳装置的第二基板的外表面。
一种电子装置，包括机身以及如上所述的电池容纳装置，所述电池容纳装置安装于所述机身的中部，并构成所述机身的一部分。
进一步地，所述电子装置还包括多个电池，所述电池包括电池本体、弹片以及第二锁紧结构，所述弹片设置于所述电池本体的一端的侧面，所述弹片在自然状态下远离所述电池本体；所述第二锁紧结构设置于所述弹片上，所述弹片在所述电池插入所述电池容纳装置的收容腔时抵持于所述电池容纳装置的收容腔的内壁上，并使所述弹片上的第二锁紧结构与所述电池容纳装置上的第一锁紧结构相配合，从而将所述电池锁紧在所述收容腔中。
进一步地，所述弹片在外力的作用下发生弹性形变并向靠近所述电池本体的方向移动，所述弹片上的第二锁紧结构跟随所述弹片的移动而脱离所述电池容纳装置上的第一锁紧结构，使所述电池从所述电池容纳装置的收容腔中脱出。
进一步地，所述弹片自所述电池本体的至少一个侧面向所述电池本体插入所述收容腔的端部的方向延伸，且延伸末端与所述电池本体分离，所述第二锁紧结构设于所述弹片的自由端；或者，
所述弹片凸设于所述电池本体一端的至少一个侧面，所述第二锁紧结构设于所述弹片远离所述电池本体之处。
进一步地，所述电池固定框架上的第一锁紧结构为肋条或卡槽，所述电池上的第二锁紧结构为卡钩结构；或者，
所述电池固定框架上的第一锁紧结构为凸起结构，所述电池上的第二锁紧结构为凹槽结构；或者，
所述电池固定框架上的第一锁紧结构为凹槽结构，所述电池上的第二锁紧结构为凸起结构。
进一步地，两个或两个以上的所述电池通过拼接的方式构成一个整体之后再收容至所述电池固定框架的收容腔中。
进一步地，每一所述电池收容至一电池盒中，或者，所述电池与所述电池盒一体成型，所述电池盒的侧面上设有拼接结构，所述电池盒通过所述拼接结构与一个或一个以上的电池盒拼接在一起。
进一步地，所述电子装置为遥控器或遥控战车。
进一步地，所述电池容纳装置的第一基板及/或第二基板采用所述机身的上盖板及/或以及下盖板。
本发明的电池容纳装置通过将现行的飞行器使用容量较大的单一电池续航的方式替换为采用容量相对较小的多个电池续航的方式，将多个电池固定框架呈辐射状设置在机身中部，通过电池以及电池固定框架自身的刚性，可加强飞行器整体的结构强度，并充分利用了所述无人飞行器的内部空间，为所述无人飞行器扩展外部组件预留出了空间。此外，通过将多个电池固定框架呈辐射状设置，在实际应用中可根据实际需要增减使用电池的数量，在减轻整机重量的同时，还保证了机身重心平衡，增强所应用到的载体，例如所述无人飞行器的飞行性能或所述电子装置的移动性能。
 附图说明
图1是本发明一实施例的一种电池容纳装置的立体图。
图2是图1的电池容纳装置的内部结构图。
图3是图1的电池容纳装置的结构分解图。
图4是本发明一实施例的电池的立体图。
图5是本发明一实施例的电池收容至电池盒的立体图。
图6是本发明一实施例的多个电池通过电池盒而拼接在一起的立体图。
图7是本发明一实施例的无人飞行器的立体图，所述无人飞行器包括图1的电池容纳装置。
图8是本发明一实施例的电子装置的局部剖视图，所述电子装置包括图1的电池容纳装置。
主要元件符号说明
电池容纳装置 20
第一基板 21
连接孔 211
第二基板 22
连接孔 221
隔板 23
连接孔 231
通孔 232
支撑杆 233
电池固定框架 24
收容腔 241
第一锁紧结构 242
连接孔 243
通孔 244
电池 30
电池本体 31
弹片 32
第二锁紧结构 33
电池盒 34
飞行器 1
机臂 101
起落架 102
负载连接机构 103
天线 104
电子装置 2
机身 12
如下具体实施方式将结合上述附图进一步说明本发明。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
请一并参阅图1-2，为本发明一实施例的一种电池容纳装置20的立体图。所述电池容纳装置20包括第一基板21、第二基板22、以及多个电池固定框架24。其中，所述多个电池固定框架24呈辐射状设置并支撑于所述第一基板21和第二基板22之间。在本实施方式中，每一所述电池固定框架24上形成有供电池30插入的收容腔241（如图3所示），所述收容腔241用于收容所述电池30。
在本实施方式中，所述多个电池固定框架24均匀地排布在所述第一基板21和所述第二基板22之间。在其他实施方式中，所述多个电池固定框架24可呈中心对称排布在所述第一基板21和所述第二基板22之间。
在本实施方式中，所述多个电池固定框架24沿同一平面排布，以便减小所述第一基板21与第二基板22之间的间距，从而减小所述电池容纳装置20的整体厚度。在其他实施方式中，所述多个电池固定框架24也可采用叠置的方式设置于第一基板21与第二基板22之间，即，所述多个电池固定框架24中的一部分沿同一平面排布，另一部分沿另一平面排布，两部分所述电池固定框架24沿自第一基板21向第二基板22的方向叠置。两部分所述电池固定框架24可以沿自第一基板21向第二基板22的方向完全重叠，亦可以部分重叠。在其他的实施方式中，所述电池固定框架24可以叠置为三层或者三层以上。
请参阅图3，在本实施方式中，所述收容腔241的内壁上设有第一锁紧结构242，所述第一锁紧结构242用于在所述电池30插入所述收容腔241时与所述电池30上的第二锁紧结构33（见图4所示）相配合，从而将所述电池30锁紧在所述收容腔241中。
请参阅图4，所述电池30包括电池本体31、弹片32以及第二锁紧结构33。所述弹片32设置于所述电池本体31的一端的侧面，所述弹片32在自然状态下远离所述电池本体31。所述第二锁紧结构33设置于所述弹片32上。
当所述电池30插入所述收容腔241时，所述弹片32在外力的作用下可发生弹性形变并向靠近所述电池本体31的方向移动。当所述外力消失后，所述弹片32在回弹力的作用下恢复形变并抵持于所述收容腔241的内壁上，并使所述弹片32上的第二锁紧结构33与所述第一锁紧结构242配合，从而将所述电池30锁紧在所述收容腔241中。
同样地，当需要取出所述电池30时，所述弹片32在外力的作用下可发生形变并向靠近所述电池本体31的方向移动，所述弹片32上的第二锁紧结构33跟随所述弹片32的移动而脱离所述电池容纳装置20上的第一锁紧结构242，使所述电池30从所述电池容纳装置20的收容腔241中脱出。
在本实施方式中，所述弹片32自所述电池本体31的至少一个侧面向所述电池本体31插入所述收容腔241的端部的方向延伸，且延伸末端与所述电池本体31分离，所述第二锁紧结构33设于所述弹片32的自由端。
在其他实施方式中，所述弹片32可凸设于所述电池本体31一端的至少一个侧面，所述第二锁紧结构33设于所述弹片32远离所述电池本体31之处。
在本实施方式中，所述电池固定框架24上的第一锁紧结构242为肋条，所述电池30上的第二锁紧结构33为卡钩结构。在其他实施方式中，所述电池固定框架24上的第一锁紧结构242可为卡槽，所述电池30上的第二锁紧结构33可为卡钩结构。或者，所述电池固定框架24上的第一锁紧结构242可为凸起结构，相应地，所述电池30上的第二锁紧结构33可为凹槽结构。或者，所述电池固定框架24上的第一锁紧结构242可为凹槽结构，相应地，所述电池30上的第二锁紧结构33可为凸起结构。
在其他实施方式中，两个或两个以上的所述电池30还可通过拼接的方式构成一个整体之后再收容至所述电池固定框架24的收容腔241中。在所述其他实施方式中，如图5所示，每一所述电池30可收容至一电池盒34中，或者，所述电池30可与所述电池盒34一体成型。所述电池盒34的侧面上设有拼接结构（图未示），如图6所示，所述电池盒34可通过所述拼接结构与一个或一个以上的电池盒34拼接在一起。
请再次参阅图3，所述电池容纳装置20还包括多个隔板23，所述多个隔板呈辐射状设置并支撑于所述第一基板21和所述第二基板22之间。在本实施方式中，每一所述电池固定框架24设置在相邻的两个所述隔板23相距较远的端部之间，所述电池固定框架24上的所述收容腔241为两端开口的通孔，相邻的两个所述隔板23之间的最短距离小于或等于所述电池30的宽度，使得相邻的两个所述隔板23相距较近的一端在所述电池30插入所述收容腔时分别抵持于所述电池30穿过所述收容腔241的端部，从而使所述电池30更加牢靠地固定在所述收容腔内。
本发明的电池容纳装置20通过在所述电池固定框架24与所述电池30上设置相应的锁紧结构，以及通过相邻的两个所述隔板23相距较近的一端抵持于所述电池30插入所述收容腔241的端部，从而能够保证所述电池30插入所述收容腔241后的稳定可靠性，有效地避免在移动或飞行过程中发生电池30从所述收容腔241中脱出的事故。
在本实施方式中，所述隔板23分别与所述第一基板21和所述第二基板22可拆卸连接。在本实施方式中，所述隔板23上设有连接孔231，所述第一基板21以及所述第二基板22上分别设有与所述隔板23上的连接孔231相对的连接孔211、221，所述第一基板21与所述隔板23之间通过连接件（图未示）与所述第一基板21和所述隔板23上相对的连接孔211、231的配合而固定在一起，所述第二基板22与所述隔板23之间通过连接件（图未示）与所述第二基板22和所述隔板23上相对的连接孔221、231的配合而固定在一起。
在本实施方式中，所述电池固定框架24分别与所述第一基板21和所述第二基板22可拆卸连接。在本实施方式中，所述电池固定框架24上设有连接孔243，所述第一基板21以及所述第二基板22上分别设有与所述电池固定框架24上的连接孔243相对的连接孔212、222，所述第一基板21与所述电池固定框架24之间通过连接件（图未示）与所述第一基板21和所述电池固定框架24上相对的连接孔212、243的配合而固定在一起，所述第二基板22与所述电池固定框架24之间通过连接件（图未示）与所述第二基板22和所述电池固定框架24上相对的连接孔222、243的配合而固定在一起。
在本实施方式中，所述连接孔211、212、221、222、231、243分别为螺纹孔，所述连接件为螺钉。
在本实施方式中，所述隔板23以及所述电池固定框架24上分别开设有多个通孔232、244，从而在保证在所述第一基板21与所述第二基板22之间提供足够的支撑力的前提下，减轻所述电池容纳装置20的整体重量。
在本实施方式中，所述隔板23在与所述第一基板21或所述第二基板22接触的一侧上还设有大致与所述隔板23垂直的支撑杆233，所述支撑杆233与所述第一基板21或所述第二基板22可拆卸连接，用于避免所述隔板23在所述第一基板21或所述第二基板22之间扭动，并增强所述隔板23在所述第一基板21和所述第二基板22之间提供的支撑力。在其他实施方式中，所述支撑杆233也可以省略。
在本实施方式中，如图7所示，所述电池容纳装置20可应用于一种无人飞行器1中。其中，所述无人飞行器1还包括多个所述电池30。在本实施方式中，所述电池容纳装置20构成所述无人飞行器1的机身，并用于收容所述电池30。在本实施方式中，所述电池容纳装置20的第一基板21以及第二基板22可分别作为所述无人飞行器1的机身的上盖板以及下盖板使用，从而减轻所述无人飞行器1的整体重量。
在本实施方式中，所述无人飞行器1还包括但不限于，机臂101、起落架102以及负载连接机构103，其中，所述机臂101的数量可为多个，并分别安装于所述电池容纳装置20的相邻两个所述电池固定框架24之间。所述起落架102可安装于所述电池容纳装置20的第二基板22上，所述负载连接机构103，例如云台，可安装于所述电池容纳装置20的第二基板22的外表面。
所述电池固定框架24还可作为所述无人飞行器1的其他功能硬件的载体，例如，所述电池固定框架24的第一基板21的外表面可用于安装所述无人飞行器1的天线104。
由于所述多个电池固定框架24呈辐射状均匀排布或呈中心对称排布，使得收容于所述电池固定框架24中的所述电池30也呈辐射状均匀或呈中心对称地设置在所述无人飞行器1机身上，从而可保证所述无人飞行器1的重心与所述无人飞行器1的中心重合，提高飞行的稳定性。
可以理解的是，当所述无人飞行器1只需要较短的滞空时间时，不需要将所述电池容纳装置20的所有收容腔241都同时装载所述电池30，以便减轻所述无人飞行器1的整体重量，延长续航时间。
本发明的电池容纳装置20通过将现行的飞行器1使用容量较大的单一电池30续航的方式替换为采用容量相对较小的多个电池30续航的方式，且将多个电池固定框架24呈辐射状设置在机身中部，通过所述电池30以及所述电池固定框架24自身的刚性，可加强飞行器1整体的结构强度，并充分利用了所述无人飞行器1的内部空间，为所述无人飞行器1扩展外部组件预留出了空间。此外，通过将多个电池固定框架24呈辐射状设置，在实际应用中可根据实际需要增减使用电池的数量，在减轻整机重量的同时，还保证了机身重心平衡，增强所述无人飞行器1的飞行性能。
在其他实施方式中，如图8所示，所述电池容纳装置20还可应用于一种电子装置2中。其中，所述电子装置2可为遥控器、或遥控战车等可移动装置，所述电子装置2还包括机身12以及多个所述电池30。所述电池容纳装置20安装于所述机身12的中部，并构成所述机身12的一部分，即，所述电池容纳装置20的第一基板21及/或第二基板22可采用所述机身12的上盖板及/或以及下盖板，从而减轻所述电子装置2的整体重量。所述电池容纳装置20用于收容所述电池30。通过将多个电池固定框架24呈辐射状设置在所述电子装置2的机身12中部，可充分利用所述电子装置2的内部空间，为所述电子装置2扩展外部组件预留出了空间。此外，还可根据实际需要减少装载的电池30，以便减轻整机重量，并保证了整机重心平衡，提高所述电子装置2的移动性能。
最后应说明的是，以上实施例仅用以说明本发明的技术方案而非限制，尽管参照较佳实施例对本发明进行了详细说明，本领域的普通技术人员应当理解，可以对本发明的技术方案进行修改或等同替换，而不脱离本发明技术方案的精神和范围。

Claims (30)

  1. 一种电池容纳装置，包括：
    第一基板和第二基板；
    多个电池固定框架，呈辐射状设置并支撑于所述第一基板和第二基板之间，每一所述电池固定框架上形成有供电池插入的收容腔。
  2. 如权利要求1所述的电池容纳装置，其特征在于，所述多个电池固定框架均匀地排布在所述第一基板和所述第二基板之间；或者，
    所述多个电池固定框架呈中心对称排布在所述第一基板和所述第二基板之间。
  3. 如权利要求2所述的电池容纳装置，其特征在于，所述多个电池固定框架沿同一平面排布；或者，所述多个电池固定框架采用叠置的方式设置于所述第一基板与所述第二基板之间。
  4. 如权利要求2所述的电池容纳装置，其特征在于，所述收容腔内壁上设有第一锁紧结构，所述第一锁紧结构用于在所述电池插入所述收容腔时与所述电池上的第二锁紧结构相配合，从而将所述电池锁紧在所述收容腔中。
  5. 如权利要求2所述的电池容纳装置，其特征在于，所述电池容纳装置还包括多个隔板，所述多个隔板呈辐射状设置并支撑于所述第一基板和所述第二基板之间，每一所述电池固定框架设置在相邻的两个所述隔板相距较远的端部之间，所述电池固定框架上的所述收容腔为两端开口的通孔，相邻的两个所述隔板相距较近的一端在所述电池插入所述收容腔时分别抵持于所述电池穿过所述收容腔的端部。
  6. 如权利要求5所述的电池容纳装置，其特征在于，所述隔板及/或所述电池固定框架上分别开设有多个通孔。
  7. 如权利要求5所述的电池容纳装置，其特征在于，所述隔板分别与所述第一基板和所述第二基板可拆卸连接。
  8. 如权利要求7所述的电池容纳装置，其特征在于，所述隔板上设有连接孔，所述第一基板以及所述第二基板上分别设有与所述隔板上的连接孔相对的连接孔，所述第一基板与所述隔板之间通过连接件与所述第一基板和所述隔板上相对的连接孔的配合而固定在一起，所述第二基板与所述隔板之间通过连接件与所述第二基板和所述隔板上相对的连接孔的配合而固定在一起。
  9. 如权利要求5所述的电池容纳装置，其特征在于，所述隔板在与所述第一基板或所述第二基板接触的一侧上还设有与所述隔板垂直的支撑杆，所述支撑杆与所述第一基板或所述第二基板可拆卸连接，用于避免所述隔板在所述第一基板或所述第二基板之间扭动，并增强所述隔板在所述第一基板和所述第二基板之间提供的支撑力。
  10. 如权利要求1所述的电池容纳装置，其特征在于，所述电池固定框架分别与所述第一基板和所述第二基板可拆卸连接。
  11. 如权利要求10所述的电池容纳装置，其特征在于，所述电池固定框架上设有连接孔，所述第一基板以及所述第二基板上分别设有与所述电池固定框架上的连接孔相对的连接孔，所述第一基板与所述电池固定框架之间通过连接件与所述第一基板和所述电池固定框架上相对的连接孔的配合而固定在一起，所述第二基板与所述电池固定框架之间通过连接件与所述第二基板和所述电池固定框架上相对的连接孔的配合而固定在一起。
  12. 如权利要求8或11所述的电池容纳装置，其特征在于，所述连接孔为螺纹孔，所述连接件为螺钉。
  13. 一种无人飞行器，包括：
    如权利要求1-11任意一项所述的电池容纳装置，所述电池容纳装置构成所述无人飞行器的机身。
  14. 如权利要求13所述的无人飞行器，其特征在于，所述无人飞行器还包括多个电池，所述电池包括电池本体、弹片以及第二锁紧结构，所述弹片设置于所述电池本体的一端的侧面，所述弹片在自然状态下远离所述电池本体；所述第二锁紧结构设置于所述弹片上，所述弹片在所述电池插入所述电池容纳装置的收容腔时抵持于所述电池容纳装置的收容腔的内壁上，并使所述弹片上的第二锁紧结构与所述电池容纳装置上的第一锁紧结构相配合，从而将所述电池锁紧在所述收容腔中。
  15. 如权利要求14所述的无人飞行器，其特征在于，所述弹片在外力的作用下发生弹性形变并向靠近所述电池本体的方向移动，所述弹片上的第二锁紧结构跟随所述弹片的移动而脱离所述电池容纳装置上的第一锁紧结构，使所述电池从所述电池容纳装置的收容腔中脱出。
  16. 如权利要求15所述的无人飞行器，其特征在于，所述弹片自所述电池本体的至少一个侧面向所述电池本体插入所述收容腔的端部的方向延伸，且延伸末端与所述电池本体分离，所述第二锁紧结构设于所述弹片的自由端；或者，
    所述弹片凸设于所述电池本体一端的至少一个侧面，所述第二锁紧结构设于所述弹片远离所述电池本体之处。
  17. 如权利要求14所述的无人飞行器，其特征在于，所述电池固定框架上的第一锁紧结构为肋条或卡槽，所述电池上的第二锁紧结构为卡钩结构；或者，
    所述电池固定框架上的第一锁紧结构为凸起结构，所述电池上的第二锁紧结构为凹槽结构；或者，
    所述电池固定框架上的第一锁紧结构为凹槽结构，所述电池上的第二锁紧结构为凸起结构。
  18. 如权利要求14所述的无人飞行器，其特征在于，两个或两个以上的所述电池通过拼接的方式构成一个整体之后再收容至所述电池固定框架的收容腔中。
  19. 如权利要求18所述的无人飞行器，其特征在于，每一所述电池收容至一电池盒中，或者，所述电池与所述电池盒一体成型，所述电池盒的侧面上设有拼接结构，所述电池盒通过所述拼接结构与一个或一个以上的电池盒拼接在一起。
  20. 如权利要求13所述的无人飞行器，其特征在于，所述电池容纳装置的第一基板以及第二基板分别构成所述无人飞行器的机身的上盖板以及下盖板。
  21. 如权利要求13或20所述的无人飞行器，其特征在于，所述无人飞行器还包括多个机臂，所述多个机臂分别安装于所述电池容纳装置的相邻两个电池固定框架之间；及/或，
    所述无人飞行器还包括起落架，所述起落架安装于所述电池容纳装置的第二基板上；及/或，
    所述无人飞行器还包括负载连接机构，所述负载连接机构安装于所述电池容纳装置的第二基板的外表面。
  22. 一种电子装置，包括：
    机身；以及
    如权利要求1-11任意一项所述的电池容纳装置，所述电池容纳装置安装于所述机身的中部，并构成所述机身的一部分。
  23. 如权利要求22所述的电子装置，其特征在于，所述电子装置还包括多个电池，所述电池包括电池本体、弹片以及第二锁紧结构，所述弹片设置于所述电池本体的一端的侧面，所述弹片在自然状态下远离所述电池本体；所述第二锁紧结构设置于所述弹片上，所述弹片在所述电池插入所述电池容纳装置的收容腔时抵持于所述电池容纳装置的收容腔的内壁上，并使所述弹片上的第二锁紧结构与所述电池容纳装置上的第一锁紧结构相配合，从而将所述电池锁紧在所述收容腔中。
  24. 如权利要求23所述的电子装置，其特征在于，所述弹片在外力的作用下发生弹性形变并向靠近所述电池本体的方向移动，所述弹片上的第二锁紧结构跟随所述弹片的移动而脱离所述电池容纳装置上的第一锁紧结构，使所述电池从所述电池容纳装置的收容腔中脱出。
  25. 如权利要求24所述的电子装置，其特征在于，所述弹片自所述电池本体的至少一个侧面向所述电池本体插入所述收容腔的端部的方向延伸，且延伸末端与所述电池本体分离，所述第二锁紧结构设于所述弹片的自由端；或者，
    所述弹片凸设于所述电池本体一端的至少一个侧面，所述第二锁紧结构设于所述弹片远离所述电池本体之处。
  26. 如权利要求23所述的电子装置，其特征在于，所述电池固定框架上的第一锁紧结构为肋条或卡槽，所述电池上的第二锁紧结构为卡钩结构；或者，
    所述电池固定框架上的第一锁紧结构为凸起结构，所述电池上的第二锁紧结构为凹槽结构；或者，
    所述电池固定框架上的第一锁紧结构为凹槽结构，所述电池上的第二锁紧结构为凸起结构。
  27. 如权利要求22所述的电子装置，其特征在于，两个或两个以上的所述电池通过拼接的方式构成一个整体之后再收容至所述电池固定框架的收容腔中。
  28. 如权利要求27所述的电子装置，其特征在于，每一所述电池收容至一电池盒中，或者，所述电池与所述电池盒一体成型，所述电池盒的侧面上设有拼接结构，所述电池盒通过所述拼接结构与一个或一个以上的电池盒拼接在一起。
  29. 如权利要求22所述的电子装置，其特征在于，所述电子装置为遥控器或遥控战车。
  30. 如权利要求22所述的电子装置，其特征在于，所述电池容纳装置的第一基板及/或第二基板采用所述机身的上盖板及/或以及下盖板。
PCT/CN2015/095990 2015-11-30 2015-11-30 电池容纳装置及无人飞行器、电子装置 WO2017091948A1 (zh)

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