WO2017185487A1 - 一种可自卸电池式无人机电池固定安装结构 - Google Patents

一种可自卸电池式无人机电池固定安装结构 Download PDF

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Publication number
WO2017185487A1
WO2017185487A1 PCT/CN2016/085190 CN2016085190W WO2017185487A1 WO 2017185487 A1 WO2017185487 A1 WO 2017185487A1 CN 2016085190 W CN2016085190 W CN 2016085190W WO 2017185487 A1 WO2017185487 A1 WO 2017185487A1
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WO
WIPO (PCT)
Prior art keywords
battery
battery cover
unmanned aerial
aerial vehicle
mounting structure
Prior art date
Application number
PCT/CN2016/085190
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English (en)
French (fr)
Inventor
鲍静云
王威
殷兰兰
Original Assignee
深圳市龙云创新航空科技有限公司
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.)
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Application filed by 深圳市龙云创新航空科技有限公司 filed Critical 深圳市龙云创新航空科技有限公司
Publication of WO2017185487A1 publication Critical patent/WO2017185487A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/32—Severable or jettisonable parts of fuselage facilitating emergency escape
    • 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
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • B64D27/40—

Definitions

  • the invention relates to a mounting structure in the field of unmanned aerial vehicles, in particular to a fixed installation structure of a self-unloading battery type unmanned aerial vehicle.
  • the present invention provides a fixed installation structure of a self-unloading battery type unmanned aerial vehicle, which solves the technical defect that the existing unmanned aerial vehicle product is likely to cause serious damage to the unmanned aerial vehicle in the event of an accident.
  • a self-unloading battery type unmanned aerial vehicle battery mounting structure comprises a drone main body and a battery cover, wherein a bottom of the main body of the drone is provided with a battery chamber for accommodating a battery, and one side of the battery chamber is provided with a hinge a corresponding one side of the battery cover is provided with a hinge post that is coupled to the hinge hole, the hinge column is hinged in the hinge hole and the battery cover is hingedly disposed on the drone body, and the battery cavity is The other end of the battery cover is provided with a battery cover female buckle, and the free end of the battery cover is provided with a battery cover male buckle that is coupled to the battery cover female buckle, and the battery cover male buckle can be fastened to the unmanned
  • the battery cover on the main body of the machine body and the battery is restrained inside the battery cavity, the battery cover male buckle and/or the battery cover female buckle are deformable members, and the battery cover male buckle and/or the battery cover female buckle are subjected to After the impact force exceeds the preset value, deformation may
  • the battery cover is an integrally formed piece, and the battery cover includes a reinforcing rib.
  • the main body of the drone includes a frame, a casing and a landing gear disposed at a bottom of the frame, the frame having an arm extending toward the periphery, the arm A motor and a propeller driven by the motor are provided, the motor being powered by a battery in the battery cavity.
  • the front end of the main body of the drone is provided with a camera assembly.
  • the invention provides a fixed installation structure of a self-unloading battery type unmanned aerial vehicle battery, and the battery cover female buckle and the battery cover male buckle of the fixed installation structure of the battery can mutually Disengagement further causes the battery of the drone to fall out of the battery cavity, reducing the impact inertia of the entire drone, avoiding damage to the frame or internal components of the drone, and effectively reducing the accident of the drone in a hard landing.
  • the damage caused by the situation can further extend the service life of the drone.
  • the self-unloading battery type drone battery fixed installation structure solves the technical defect that the existing drone product is likely to cause serious damage to the drone when an accident occurs.
  • Figure 1 is a structural split view of the present invention
  • Figure 2 is a state diagram of the present invention before assembling the battery
  • Figure 3 is a state diagram of the present invention in the process of assembling a battery
  • Fig. 4 is a view showing the state of the present invention after the battery is assembled.
  • a self-unloading battery type unmanned aerial vehicle battery mounting structure comprises a UAV main body 1 and a battery cover 2, and a bottom of the UAV main body 1 is provided with a battery chamber 10 for accommodating a battery 4, the battery chamber 10
  • One side of the battery cover 2 is provided with a hinge hole, and a corresponding side of the battery cover 2 is provided with a hinge post fitted to the hinge hole, the hinge column is hinged in the hinge hole and the battery cover 2 is hingedly arranged on the drone
  • the battery chamber 10 is provided with a battery cover female buckle on the other side thereof away from the hinge hole, and the free end of the battery cover 2 is provided with a battery cover male buckle 21 fitted to the battery cover female buckle.
  • the battery cover male buckle 21 can be fastened on the battery cover female buckle on the main body 1 of the drone and the battery 4 is restrained inside the battery cavity 10.
  • the battery cover male buckle 21 and/or the battery cover female buckle are The deformable member, the battery cover male snap 21 and/or the battery cover female snap can be deformed after being subjected to an impact force exceeding a preset value and the battery cover male snap 21 and the battery cover female snap are separated from each other.
  • the battery cover male buckle 21 and/or the battery cover female buckle are deformable members, when the drone is hard landing or subjected to a large impact exceeding a preset value, the battery cover male buckle 21 and the battery cover female buckle will Separated from each other, at this time, the battery 4 in the battery chamber 10 will fall out of the battery chamber 10, thereby reducing the mass and inertia of the entire drone, and avoiding damage caused by the drone during a large impact process, contributing to Protect the drone and indirectly extend the life of the drone.
  • the battery cover 2 is an integrally formed member, and the battery cover 2 includes a reinforcing rib.
  • the UAV main body 1 comprises a frame 11, a casing 12 and a landing gear 13 disposed at the bottom 11 of the frame, the frame 11 having an arm 14 extending toward the periphery, the machine
  • the arm 14 is provided with a motor 15 and a propeller 16 driven by the motor 15, which is powered by a battery 4 in the battery chamber 10.
  • the front end of the UAV main body 1 is provided with a camera assembly 17.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Battery Mounting, Suspending (AREA)
  • Toys (AREA)

Abstract

一种可自卸电池式无人机电池固定安装结构，包括无人机主体（1）和电池盖（2），所述无人机主体（1）底部开设有用于容纳电池（4）的电池腔（10），电池腔（10）的一侧设置有铰接孔，所述电池盖（2）上对应的一侧设置有配合于所述铰接孔的铰接柱，所述铰接柱铰接在铰接孔中并使得电池盖（2）铰接设置在无人机主体（1）上，所述电池腔（10）在其远离铰接孔的另一侧设置有电池盖母扣，所述电池盖（2）的自由端设置有配合于所述电池盖母扣的电池盖公扣（21），所述电池盖公扣（21）可扣紧在无人机主体（1）上的电池盖母扣上并将电池（4）限位在电池腔（10）内部，电池盖公扣（21）和/或电池盖母扣为可变形构件。该种可自卸电池式无人机电池固定安装结构具有结构简单、实施方便、可保护无人机主体安全、有效延长无人机寿命等优点。

Description

一种可自卸电池式无人机电池固定安装结构
技术领域
本发明涉及一种无人机领域的安装结构，特别是一种自卸电池式无人机电池固定安装结构。
背景技术
近年来，随着无人机应用范围的推广，无人机控制技术得到了迅猛发展，市面上出现了各种功能的无人机产品。但是，现有的以锂电池为动力的无人机，均是用螺丝或者魔术带紧固于机身中，电池与无人机是固定的，在飞行全过程中电池均与机身结为一体，在意外硬着陆过程中也不会从飞机上脱落，因此，大质量电池在此过程中由于自身的惯性可能会对机身和起落架造成严重损坏，影响无人机的使用寿命。
有鉴于此，本发明的目的在于提供一种新的技术方案以解决现存的技术问题。
发明内容
为了克服现有技术的不足，本发明提供一种自卸电池式无人机电池固定安装结构，解决了现有无人机产品在发生意外时电池容易对无人机造成严重损坏的技术缺陷。
本发明解决其技术问题所采用的技术方案是：
一种可自卸电池式无人机电池固定安装结构，包括无人机主体和电池盖，所述无人机主体底部开设有用于容纳电池的电池腔，所述电池腔的一侧设置有铰接孔，所述电池盖上对应的一侧设置有配合于所述铰接孔的铰接柱，所述铰接柱铰接在铰接孔中并使得电池盖铰接设置在无人机主体上，所述电池腔在其远离铰接孔的另一侧设置有电池盖母扣，所述电池盖的自由端设置有配合于所述电池盖母扣的电池盖公扣，所述电池盖公扣可扣紧在无人机主体上的电池盖母扣上并将电池限位在电池腔内部，所述电池盖公扣和/或电池盖母扣为可变形构件，电池盖公扣和/或电池盖母扣在受到超过预设值的冲击力后可发生变形并使得电池盖公扣和电池盖母扣相互分离。
作为上述技术方案的改进，所述电池盖为一体成型件，电池盖包括有加强筋。
作为上述技术方案的进一步改进，所述无人机主体包括机架、机壳和设置在所述机架底部的起落架，所述机架具有向着四周延伸设置的机臂，所述机臂上设置有电机及由所述电机驱动的螺旋桨，所述电机由所述电池腔中的电池提供电源。
作为上述技术方案的进一步改进，所述无人机主体前端设置有摄像头组件。
本发明的有益效果是：本发明提供了一种自卸电池式无人机电池固定安装结构，电池所述固定安装结构的电池盖母扣和电池盖公扣在无人机发生意外时可相互脱离，进一步使得无人机的电池从电池腔中掉出，缩小整个无人机的冲击惯性，避免电池对无人机的框架或内部零部件造成损坏，有效降低无人机在硬着陆等意外情况中造成的损失，进一步可延长无人机的使用寿命。该种自卸电池式无人机电池固定安装结构，解决了现有无人机产品在发生意外时电池容易对无人机造成严重损坏的技术缺陷。
附图说明
下面结合附图和实施例对本发明进一步说明。
图1是本发明的结构拆分图；
图2是本发明在装配电池前的状态图；
图3是本发明在装配电池过程中的状态图；
图4是本发明在装配电池后的的状态图。
具体实施方式
以下将结合实施例和附图对本发明的构思、具体结构及产生的技术效果进行清楚、完整地描述，以充分地理解本发明的目的、特征和效果。显然，所描述的实施例只是本发明的一部分实施例，而不是全部实施例，基于本发明的实施例，本领域的技术人员在不付出创造性劳动的前提下所获得的其他实施例，均属于本发明保护的范围。另外，专利中涉及到的所有联接/连接关系，并非单指构件直接相接，而是指可根据具体实施情况，通过添加或减少联接辅件，来组成更优的联接结构。本发明创造中的各个技术特征，在不互相矛盾冲突的前提下可以交互组合，参照图1-4。
一种可自卸电池式无人机电池固定安装结构，包括无人机主体1和电池盖2，所述无人机主体1底部开设有用于容纳电池4的电池腔10，所述电池腔10的一侧设置有铰接孔，所述电池盖2上对应的一侧设置有配合于所述铰接孔的铰接柱，所述铰接柱铰接在铰接孔中并使得电池盖2铰接设置在无人机主体1上，所述电池腔10在其远离铰接孔的另一侧设置有电池盖母扣，所述电池盖2的自由端设置有配合于所述电池盖母扣的电池盖公扣21，所述电池盖公扣21可扣紧在无人机主体1上的电池盖母扣上并将电池4限位在电池腔10内部，所述电池盖公扣21和/或电池盖母扣为可变形构件，电池盖公扣21和/或电池盖母扣在受到超过预设值的冲击力后可发生变形并使得电池盖公扣21和电池盖母扣相互分离。
由于上述的电池盖公扣21和/或电池盖母扣为可变形构件，当无人机在硬着陆或受到超过预设值的较大冲击时，电池盖公扣21与电池盖母扣会相互分离，这时候，电池腔10内的电池4会从电池腔10中掉出，从而减小整个无人机的质量及惯性，避免无人机在较大冲击过程中产生损伤，有助于保护无人机，间接延长无人机的使用寿命。
优选地，所述电池盖2为一体成型件，电池盖2包括有加强筋。
优选地，所述无人机主体1包括机架11、机壳12和设置在所述机架底部11的起落架13，所述机架11具有向着四周延伸设置的机臂14，所述机臂14上设置有电机15及由所述电机15驱动的螺旋桨16，所述电机15由所述电池腔10中的电池4提供电源。
优选地，所述无人机主体1前端设置有摄像头组件17。
以上是对本发明的较佳实施进行了具体说明，但本发明创造并不限于所述实施例，熟悉本领域的技术人员在不违背本发明精神的前提下还可做出种种的等同变形或替换，这些等同的变形或替换均包含在本申请权利要求所限定的范围内。

Claims (4)

  1. 一种可自卸电池式无人机电池固定安装结构，其特征在于：包括无人机主体（1）和电池盖（2），所述无人机主体（1）底部开设有用于容纳电池（4）的电池腔（10），所述电池腔（10）的一侧设置有铰接孔，所述电池盖（2）上对应的一侧设置有配合于所述铰接孔的铰接柱，所述铰接柱铰接在铰接孔中并使得电池盖（2）铰接设置在无人机主体（1）上，所述电池腔（10）在其远离铰接孔的另一侧设置有电池盖母扣，所述电池盖（2）的自由端设置有配合于所述电池盖母扣的电池盖公扣（21），所述电池盖公扣（21）可扣紧在无人机主体（1）上的电池盖母扣上并将电池（4）限位在电池腔（10）内部，所述电池盖公扣（21）和/或电池盖母扣为可变形构件，电池盖公扣（21）和/或电池盖母扣在受到超过预设值的冲击力后可发生变形并使得电池盖公扣（21）和电池盖母扣相互分离。
  2. 根据权利要求1所述的一种可自卸电池式无人机电池固定安装结构，其特征在于：所述电池盖（2）为一体成型件，电池盖（2）包括有加强筋。
  3. 根据权利要求2所述的一种可自卸电池式无人机电池固定安装结构，其特征在于：所述无人机主体（1）包括机架（11）、机壳（12）和设置在所述机架底部（11）的起落架（13），所述机架（11）具有向着四周延伸设置的机臂（14），所述机臂（14）上设置有电机（15）及由所述电机（15）驱动的螺旋桨（16），所述电机（15）由所述电池腔（10）中的电池（4）提供电源。
  4. 根据权利要求3所述的一种可自卸电池式无人机电池固定安装结构，其特征在于：所述无人机主体（1）前端设置有摄像头组件（17）。
PCT/CN2016/085190 2016-04-28 2016-06-08 一种可自卸电池式无人机电池固定安装结构 WO2017185487A1 (zh)

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CN201620383316.8 2016-04-28

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WO2019143255A1 (en) * 2018-01-17 2019-07-25 Griff Aviation As An unmanned aerial vehicle
WO2021242113A1 (en) * 2020-05-28 2021-12-02 Griff Aviation As A battery connector

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CN203638088U (zh) * 2013-10-24 2014-06-11 深圳一电科技有限公司 旋翼飞行器
CN204341403U (zh) * 2014-10-12 2015-05-20 西北工业大学 一种节能环保的飞行器
CN204937508U (zh) * 2015-09-11 2016-01-06 东莞市瑞科五金塑胶制品有限公司 一种无人机

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US20040195438A1 (en) * 2003-01-09 2004-10-07 Chamberlain Mark Spencer Electric powered flying wing toy
DE102006020508A1 (de) * 2006-04-20 2007-10-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Fahrzeug und Verfahren zum Betrieb eines Fahrzeugs
CN203638088U (zh) * 2013-10-24 2014-06-11 深圳一电科技有限公司 旋翼飞行器
CN204341403U (zh) * 2014-10-12 2015-05-20 西北工业大学 一种节能环保的飞行器
CN204937508U (zh) * 2015-09-11 2016-01-06 东莞市瑞科五金塑胶制品有限公司 一种无人机

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019143255A1 (en) * 2018-01-17 2019-07-25 Griff Aviation As An unmanned aerial vehicle
KR20200106197A (ko) * 2018-01-17 2020-09-11 그리프 에이비에이션 에이에스 무인 항공기
JP2021512002A (ja) * 2018-01-17 2021-05-13 グリフ アビエーション エーエスＧｒｉｆｆ Ａｖｉａｔｉｏｎ Ａｓ 無人航空機
JP7285847B2 (ja) 2018-01-17 2023-06-02 グリフ アビエーション エーエス 無人航空機
KR102652241B1 (ko) * 2018-01-17 2024-03-28 그리프 에이비에이션 에이에스 무인 항공기
WO2021242113A1 (en) * 2020-05-28 2021-12-02 Griff Aviation As A battery connector

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