WO2021078162A1 - 一种无人机 - Google Patents

一种无人机 Download PDF

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Publication number
WO2021078162A1
WO2021078162A1 PCT/CN2020/122539 CN2020122539W WO2021078162A1 WO 2021078162 A1 WO2021078162 A1 WO 2021078162A1 CN 2020122539 W CN2020122539 W CN 2020122539W WO 2021078162 A1 WO2021078162 A1 WO 2021078162A1
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WO
WIPO (PCT)
Prior art keywords
connecting portion
wing
aerial vehicle
unmanned aerial
locking member
Prior art date
Application number
PCT/CN2020/122539
Other languages
English (en)
French (fr)
Inventor
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 EP20878980.0A priority Critical patent/EP4046906A4/en
Publication of WO2021078162A1 publication Critical patent/WO2021078162A1/zh
Priority to US17/659,683 priority patent/US11999465B2/en

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/26Attaching the wing or tail units or stabilising surfaces
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for
    • B64C39/02Aircraft not otherwise provided for characterised by special use
    • B64C39/024Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10Wings
    • B64U30/12Variable or detachable wings, e.g. wings with adjustable sweep
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2211/00Modular constructions of airplanes or helicopters
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00Type of UAV
    • B64U10/25Fixed-wing aircraft

Definitions

  • the invention relates to the field of aircraft, in particular to an unmanned aerial vehicle.
  • the rapid integration and separation of the wing and the fuselage of the UAV can facilitate the packaging and transportation of the UAV.
  • This requires the connection of the fuselage and the wing to meet the strength, rigidity and reliability without affecting the flight performance. Disassembly and assembly are simple and fast.
  • the purpose of the present invention is to provide a drone.
  • An unmanned aerial vehicle includes a fuselage and a wing.
  • One of the fuselage and the wing is provided with a first connecting portion, and the other is provided with a second connecting portion.
  • the connecting portion and the second connecting portion are detachably connected; the first connecting portion is engaged with the second connecting portion and the fuselage and the wing are connected by rotating or sliding the second connecting portion locking.
  • the first connecting portion includes a latch member and a protrusion provided on the latch member, the cross-sectional width of the protrusion is greater than the cross-sectional width of the latch member;
  • the second connecting portion includes a lock
  • the locking member is provided with a guide groove for sliding the pin member and an installation groove for mating with the protrusion, the guide groove and the installation groove communicate with each other, and the The width of the guide groove is smaller than the cross-sectional width of the plug member.
  • first connecting portion is provided on the fuselage
  • second connecting portion is provided on the wing
  • the wing is provided with a through hole
  • the locking member is rotatably installed in the through hole
  • a side wall of the through hole is provided with a mounting hole that matches the mounting groove.
  • the shape of the locking member is columnar.
  • the second connecting portion further includes a first limiting member provided on the locking member, and the through hole is provided with a first limiting member that cooperates with the first limiting member to restrict the locking member The second limit of the rotation range.
  • the second connecting portion further includes a pressure block provided at one end of the through hole to restrict the locking member from moving out of the through hole.
  • the wing includes a wing body and a connecting bracket installed on the wing body, and the through hole is provided on the connecting bracket.
  • a sliding groove is provided on the wing, and the locking member is a sliding block slidably installed in the sliding groove.
  • the second connecting portion further includes an elastic member arranged in the sliding groove, one end of the elastic member is in contact with the inner side of the sliding groove, and the other end of the elastic member is in contact with the locking groove. Pieces conflict.
  • the shape of the protrusion is spherical.
  • a first electrical connector is provided on the fuselage, and a second electrical connector mated with the first electrical connector is provided on the wing.
  • one of the fuselage and the wing is provided with a support member, and the other is provided with a slot for inserting and fitting with the support member.
  • the shape of the support member is tubular, and the cross section of the support member is rectangular.
  • the number of the first connecting portion and the second connecting portion are both two, the two first connecting portions are respectively provided on both sides of the supporting member, and the two second connecting portions They are respectively arranged on both sides of the support.
  • the present invention has the beneficial effect that by providing a first connecting portion on one of the fuselage and wing, and a second connecting portion on the other, the first connecting portion is engaged with the first connecting portion.
  • the second connecting part realizes the locking of the fuselage and the wing by rotating or sliding the second connecting part, thereby facilitating the disassembly and assembly of the fuselage and the wing, and the connecting part meets the reliability of strength and rigidity without affecting the flight performance.
  • Figure 1 is a schematic diagram of a drone provided by an embodiment of the present invention.
  • Figure 2 is an exploded view of a drone provided by an embodiment of the present invention.
  • Figure 3 is an enlarged view of A shown in Figure 2;
  • FIG. 4 is a schematic diagram of a first connecting portion and a second connecting portion provided by an embodiment of the present invention
  • Figure 5 is a schematic diagram of a wing in an embodiment of the present invention.
  • Fig. 6 is a schematic diagram of the cooperation between the wing and the locking member in another embodiment of the present invention.
  • the drone provided by the embodiment of the present invention includes a fuselage 1 and a wing 2.
  • One of the fuselage 1 and the wing 2 is provided with a first connecting portion 10, and the other
  • the second connecting portion 20 is provided on the second connecting portion 10, and the first connecting portion 10 and the second connecting portion 20 are detachably connected; the first connecting portion 10 is engaged with the second connecting portion 20 and the machine is realized by rotating or sliding the second connecting portion 20.
  • the body 1 and the wing 2 are locked, rotating or sliding the second connecting part 20 and separating the first connecting part 10 and the second connecting part 20 to realize the unlocking of the fuselage 1 and the wing 2, which is convenient for disassembly and assembly, and can meet the strength, The reliability of rigidity does not affect the flight performance.
  • the first connecting portion 10 includes a plug member 11 and a protrusion 12 provided on the plug member 11.
  • the cross-sectional width of the protrusion 12 is greater than the cross-sectional width of the plug member 11;
  • the second connecting portion 20 It includes a locking member 21.
  • the locking member 21 is provided with a guide groove 211 for sliding the pin member 11 and a mounting groove 212 for snap-fitting with the protrusion 12.
  • the guide groove 211 and the mounting groove 212 communicate with each other, and the guide groove The width of 211 is smaller than the cross-sectional width of the latch member 11.
  • the locking member 21 When the locking member is moved until the mounting groove 212 is aligned with the protrusion 12, the protrusion 12 extends into the locking member 21 through the mounting groove 212, and the locking member 21 is moved to slide the latch member 11 into the guide groove 211, so that The latch member 11 is locked with the locking member 21 so as to lock the first connecting portion 10 and the second connecting portion 20.
  • the locking member 21 is moved and the latch member 11 slides in the guide groove 211 to align the protrusion 12 with the installation groove 212, the latch member 11 is pulled out, thereby unlocking the first connecting portion 10 and the second connecting portion 20.
  • the first connecting portion 10 is provided on the fuselage 1, and the second connecting portion 20 is provided on the wing 2, that is, the latch member 11 is protrudingly provided on the fuselage 1, and is locked.
  • the piece 21 is movably mounted on the wing 2.
  • the wing 2 is provided with a through hole 22, the locking member 21 is cylindrical in shape, and the locking member 21 is rotatably installed in the through hole 22.
  • the side wall is provided with a mounting hole 221 adapted to the mounting groove 212, and the shape of the protrusion 12 is spherical, which reduces the friction on the second connecting portion 20 during mounting and dismounting.
  • the second connecting portion 20 further includes a first limiting member 23 provided on the locking member 21, and a first limiting member 23 that cooperates with the first limiting member 23 to limit the rotation range of the locking member 21 is provided in the through hole 22
  • the two limiting members 222 make the first connecting portion 10 and the second connecting portion 20 more securely fixed.
  • the second connecting portion 20 further includes a pressure block 24 arranged at one end of the through hole 22 to restrict the locking member 21 from moving out of the through hole 22, wherein the pressure block 24 is fixed to the wing 2 by bolts.
  • the wing 2 includes a wing body 25 and a connecting bracket 26 installed on the wing body 25.
  • the through hole 22 is provided on the connecting bracket 26.
  • the connecting bracket 26 can be inserted into the wing body 25 or glued. It is connected to the wing body 25, and can also be fixed to the wing body 25 by bolts.
  • the wing 2 is provided with a sliding groove 27, the locking member 21 is a sliding block slidably installed in the sliding groove 27, and the locking member 21 is provided with a sliding groove for pushing and locking.
  • the push-torque 28 of the member 21 pushes the push-torque 28 to slide the locking member 21 until the mounting groove 212 is aligned with the protrusion 12, the protrusion 12 extends into the locking member 21 through the mounting groove 212, and the locking member 21 is slid to make the latch
  • the piece 11 slides into the guide groove 211 to achieve locking. Slide the locking member 21 to align the mounting groove 212 with the protrusion 12, and pull out the pin member 11 to achieve unlocking.
  • the second connecting portion 20 further includes an elastic member 29 arranged in the sliding groove 27.
  • One end of the elastic member 29 is in contact with the inner side of the sliding groove 27, and the other end of the elastic member 29 is in contact with the locking member 21.
  • the member 29 is used to provide a restoring force for the locking member 21 to ensure the reliability of the connection between the first connecting portion 10 and the second connecting portion 20.
  • one of the fuselage 1 and the wing 2 is provided with a support 3, and the other is provided with a card slot 4 for inserting and fitting with the support 3 .
  • one end of the support 3 is fixed to the fuselage 1, and the wing 2 is provided with a slot 4.
  • the wing 2 is first installed on the support 3 through the slot 4 , To achieve coarse positioning, make the installation faster, and at the same time the support 3 plays the role of supporting the wing 2 to make the connection part stronger.
  • the shape of the support 3 is tubular, and the cross section of the support 3 is rectangular, which reduces the weight of the drone.
  • the number of the first connecting portion 10 and the second connecting portion 20 connecting each wing 2 and the fuselage 1 are both two, and the two first connecting portions 10 are respectively provided on two of the supports 3 On the side, two second connecting portions 20 are respectively provided on both sides of the support 3.
  • first connecting portion 10 is provided on the wing 2 and the second connecting portion 20 is provided on the fuselage 1, that is, the latch member 11 is protrudingly provided on the wing 2, and the locking member 21
  • the movable installation is on the fuselage 1.
  • the fuselage 1 is provided with a first electrical connector 5, and the wing 2 is provided with a second electrical connector 6 mated with the first electrical connector 5, and the wing 2 passes through The second electrical connector 6 is electrically connected with the first electrical connector 5 to obtain a control command.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Forklifts And Lifting Vehicles (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)

Abstract

一种无人机,包括机身(1)和机翼(2),机身和机翼中的其中一者上设有第一连接部(10),另一者上设有第二连接部(20),第一连接部和第二连接部可拆卸连接;第一连接部卡合于第二连接部并通过旋转或滑动第二连接部实现机身与机翼的锁定。方便机身与机翼的拆装,连接部分满足强度、刚性的可靠性,不影响飞行性能。

Description

一种无人机
本申请要求于2019年10月21日提交中国专利局、申请号为201911001523.7、申请名称为“一种无人机”的中国专利申请的优先权,其全部内容通过引用结合在本申请中。
技术领域
本发明涉及飞行器领域,尤其涉及一种无人机。
背景技术
目前,无人机的机翼与机身的快速整合与分离,可以方便无人机的包装及运输,这就要求机身与机翼的连接满足强度、刚性的可靠性,不影响飞行性能,拆装简单、快速。
发明内容
为了实现无人机机身与机翼的连接满足强度、刚性的可靠性,不影响飞行性能,方便拆装,本发明的目的在于提供一种无人机。
为了实现上述目的,本发明采用如下技术方案:
一种无人机,包括机身和机翼,所述机身和所述机翼中的其中一者上设有第一连接部,另一者上设有第二连接部,所述第一连接部和所述第二连接部可拆卸连接;所述第一连接部卡合于所述第二连接部并通过旋转或滑动所述第二连接部实现所述机身与所述机翼的锁定。
进一步地,所述第一连接部包括插销件和设于所述插销件上的凸起,所述凸起的横截面宽度大于所述插销件的横截面宽度;所述第二连接部包括锁紧件,所述锁紧件上设有用于供所述插销件滑动的导向槽和用于与所述凸起卡插配合的安装槽,所述导向槽和所述安装槽连通,且所述导向槽的宽度小于所述插销 件的横截面宽度。
进一步地,所述第一连接部设于所述机身上,所述第二连接部设于所述机翼上。
进一步地,所述机翼上设有通孔,所述锁紧件转动安装于所述通孔内,所述通孔的侧壁上设有与所述安装槽相适配的安装孔。
进一步地,所述锁紧件的形状为柱状。
进一步地,所述第二连接部还包括设于所述锁紧件上的第一限位件,所述通孔内设有与所述第一限位件相配合以限制所述锁紧件转动范围的第二限位件。
进一步地,所述第二连接部还包括设于所述通孔一端以限制所述锁紧件移出所述通孔的压块。
进一步地,所述机翼包括机翼本体和安装于所述机翼本体上的连接支架,所述通孔设于所述连接支架上。
进一步地,所述机翼上设有滑槽,所述锁紧件为滑动安装于所述滑槽内的滑块。
进一步地,所述第二连接部还包括设于所述滑槽内的弹性件,所述弹性件的一端与所述滑槽的内侧相抵触,所述弹性件的另一端与所述锁紧件相抵触。
进一步地,所述凸起的形状为球状。
进一步地,所述机身上设有第一电连接器,所述机翼上设有与所述第一电连接器插接配合的第二电连接器。
进一步地,所述机身和所述机翼中的其中一者上设有支撑件,另一者上设有与所述支撑件卡插配合的卡槽。
进一步地,所述支撑件的形状为管状,所述支撑件的横截面为矩形。
进一步地,所述第一连接部和所述第二连接部的数量均为两个,两个所述第一连接部分别设于所述支撑件的两侧,两个所述第二连接部分别设于所述支撑件的两侧。
相比现有技术,本发明的有益效果在于:通过在机身和机翼中的其中一者上设置第一连接部,另一者上设置第二连接部,第一连接部卡合于第二连接部并通过旋转或滑动第二连接部实现机身与机翼的锁定,从而方便机身与机翼的拆装,连接部分满足强度、刚性的可靠性,不影响飞行性能。
附图说明
图1为本发明实施例提供的无人机的示意图;
图2为本发明实施例提供的无人机的爆炸图;
图3为图2所示A处的放大图;
图4为本发明实施例提供的第一连接部和第二连接部的示意图;
图5为本发明一种实施方式中的机翼的示意图;
图6为本发明另一实施方式中机翼与锁紧件的配合示意图。
1、机身;10、第一连接部;11、插销件;12、凸起;2、机翼;20、第二连接部;21、锁紧件;211、导向槽;212、安装槽;22、通孔;221、安装孔;222、第二限位件;23、第一限位件;24、压块;25、机翼本体;26、连接支架;27、滑槽;28、推扭;29、弹性件;3、支撑件;4、卡槽;5、第一电连接器;6、第二电连接器。
具体实施方式
为了便于理解本发明,下面结合附图和具体实施例,对本发明进行更详细的说明。需要说明的是,当元件被表述“固定于”另一个元件,它可以直接在 另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件,它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”以及类似的表述只是为了说明的目的。
除非另有定义,本说明书所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本说明书中在本发明的说明书中所使用的术语只是为了描述具体的实施例的目的,不是用于限制本发明。本说明书所使用的术语“和/或”包括一个或多个相关的所列项目的任意的和所有的组合。
下面,结合附图以及具体实施方式,对本发明做进一步描述,需要说明的是,在不相冲突的前提下,以下描述的各实施例之间或各技术特征之间可以任意组合形成新的实施例。
如图1-3所示,本发明实施例提供的无人机,包括机身1和机翼2,机身1和机翼2中的其中一者上设有第一连接部10,另一者上设有第二连接部20,第一连接部10和第二连接部20可拆卸连接;第一连接部10卡合于第二连接部20并通过旋转或滑动第二连接部20实现机身1与机翼2的锁定,旋转或滑动第二连接部20并分离第一连接部10和第二连接部20实现机身1与机翼2的解锁,方便拆装,且能满足强度、刚性的可靠性,不影响飞行性能。
如图2-4所示,第一连接部10包括插销件11和设于插销件11上的凸起12,凸起12的横截面宽度大于插销件11的横截面宽度;第二连接部20包括锁紧件21,锁紧件21上设有用于供插销件11滑动的导向槽211和用于与凸起12卡插配合的安装槽212,导向槽211和安装槽212连通,且导向槽211的宽度小于插销件11的横截面宽度。当移动锁紧件至安装槽212对准凸起12时,凸起12通 过安装槽212伸入锁紧件21内部,移动锁紧件21以使插销件11滑动至导向槽211内,从而使插销件11与锁紧件21锁定,从而锁定第一连接部10和第二连接部20。移动锁紧件21,使插销件11在导向槽211内滑动以使凸起12对准安装槽212时,拔出插销件11,从而使第一连接部10和第二连接部20解锁。
如图3所示,在一实施例中,第一连接部10设于机身1上,第二连接部20设于机翼2上,即插销件11凸设于机身1上,锁紧件21活动安装于机翼2上。
如图3-5所示,在一种实施方式中,机翼2上设有通孔22,锁紧件21的形状为柱状,锁紧件21转动安装于通孔22内,通孔22的侧壁上设有与安装槽212相适配的安装孔221,凸起12的形状为球状,减少安装和拆卸过程中对第二连接部20的摩擦。当转动锁紧件21使安装槽212对准安装孔221,凸起12伸入安装槽212内,转动锁紧件21使插销件11滑动值导向槽211内实现锁定。
进一步地,第二连接部20还包括设于锁紧件21上的第一限位件23,通孔22内设有与第一限位件23相配合以限制锁紧件21转动范围的第二限位件222,使第一连接部10和第二连接部20固定更牢固。
进一步地,第二连接部20还包括设于通孔22一端以限制锁紧件21移出通孔22的压块24,其中,压块24通过螺栓固定于机翼2上。
进一步地,机翼2包括机翼本体25和安装于机翼本体25上的连接支架26,通孔22设于连接支架26上,连接支架26可以插接于机翼本体25内,也可以粘接于机翼本体25内,也可以通过螺栓固定于机翼本体25上。
如图6所示,在另一实施方式中,机翼2上设有滑槽27,锁紧件21为滑动安装于滑槽27内的滑块,锁紧件21上设有用于推动锁紧件21的推扭28,推动推扭28使锁紧件21滑动至安装槽212对准凸起12时,凸起12通过安装槽212伸入锁紧件21内,滑动锁紧件21使插销件11滑动至导向槽211内,实现锁定。 滑动锁紧件21使安装槽212对准凸起12,拔出插销件11,实现解锁。
进一步地,第二连接部20还包括设于滑槽27内的弹性件29,弹性件29的一端与滑槽27的内侧相抵触,弹性件29的另一端与锁紧件21相抵触,弹性件29用于为锁紧件21提供回复力,保证第一连接部10和第二连接部20连接的可靠性。
如图2-5所示,在一实施例中,机身1和机翼2中的其中一者上设有支撑件3,另一者上设有与支撑件3卡插配合的卡槽4。如图3所示,支撑件3的一端固定于机身1上,机翼2上设有卡槽4,当安装机翼2时,先通过卡槽4将机翼2安装于支撑件3上,实现粗定位,使安装更快速,同时支撑件3起到支撑机翼2的作用,使连接部分更牢固。其中,支撑件3的形状为管状,支撑件3的横截面为矩形,减小无人机的重量。
如图3所示,连接每个机翼2与机身1的第一连接部10和第二连接部20的数量均为两个,两个第一连接部10分别设于支撑件3的两侧,两个第二连接部20分别设于支撑件3的两侧。
可以理解,在另一实施例中,第一连接部10设于机翼2上,第二连接部20设于机身1上,即插销件11凸设于机翼2上,锁紧件21活动安装于机身1上。
如图3和图5所示,机身1上设有第一电连接器5,机翼2上设有与第一电连接器5插接配合的第二电连接器6,机翼2通过第二电连接器6与第一电连接器5电连接获得控制指令。
上述实施方式仅为本发明的优选实施方式,不能以此来限定本发明保护的范围,本领域的技术人员在本发明的基础上所做的任何非实质性的变化及替换均属于本发明所要求保护的范围。

Claims (15)

  1. 一种无人机,其特征在于,包括机身和机翼,所述机身和所述机翼中的其中一者上设有第一连接部,另一者上设有第二连接部,所述第一连接部和所述第二连接部可拆卸连接;所述第一连接部卡合于所述第二连接部并通过旋转或滑动所述第二连接部实现所述机身与所述机翼的锁定。
  2. 根据权利要求1所述的无人机,其特征在于,所述第一连接部包括插销件和设于所述插销件上的凸起,所述凸起的横截面宽度大于所述插销件的横截面宽度;所述第二连接部包括锁紧件,所述锁紧件上设有用于供所述插销件滑动的导向槽和用于与所述凸起卡插配合的安装槽,所述导向槽和所述安装槽连通,且所述导向槽的宽度小于所述插销件的横截面宽度。
  3. 根据权利要求2所述的无人机,其特征在于,所述第一连接部设于所述机身上,所述第二连接部设于所述机翼上。
  4. 根据权利要求3所述的无人机,其特征在于,所述机翼上设有通孔,所述锁紧件转动安装于所述通孔内,所述通孔的侧壁上设有与所述安装槽相适配的安装孔。
  5. 根据权利要求4所述的无人机,其特征在于,所述锁紧件的形状为柱状。
  6. 根据权利要求4所述的无人机,其特征在于,所述第二连接部还包括设于所述锁紧件上的第一限位件,所述通孔内设有与所述第一限位件相配合以限制所述锁紧件转动范围的第二限位件。
  7. 根据权利要求4所述的无人机,其特征在于,所述第二连接部还包括设于所述通孔一端以限制所述锁紧件移出所述通孔的压块。
  8. 根据权利要求4所述的无人机,其特征在于,所述机翼包括机翼本体和安 装于所述机翼本体上的连接支架,所述通孔设于所述连接支架上。
  9. 根据权利要求3所述的无人机,其特征在于,所述机翼上设有滑槽,所述锁紧件为滑动安装于所述滑槽内的滑块。
  10. 根据权利要求9所述的无人机,其特征在于,所述第二连接部还包括设于所述滑槽内的弹性件,所述弹性件的一端与所述滑槽的内侧相抵触,所述弹性件的另一端与所述锁紧件相抵触。
  11. 根据权利要求2-10任一项所述的无人机,其特征在于,所述凸起的形状为球状。
  12. 根据权利要求1-10任一项所述的无人机,其特征在于,所述机身上设有第一电连接器,所述机翼上设有与所述第一电连接器插接配合的第二电连接器。
  13. 根据权利要求1-10任一项所述的无人机,其特征在于,所述机身和所述机翼中的其中一者上设有支撑件,另一者上设有与所述支撑件卡插配合的卡槽。
  14. 根据权利要求13所述的无人机,其特征在于,所述支撑件的形状为管状,所述支撑件的横截面为矩形。
  15. 根据权利要求13所述的无人机,其特征在于,所述第一连接部和所述第二连接部的数量均为两个,两个所述第一连接部分别设于所述支撑件的两侧,两个所述第二连接部分别设于所述支撑件的两侧。
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