WO2021043335A2 - 机翼拆卸组件和飞行器 - Google Patents

机翼拆卸组件和飞行器 Download PDF

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Publication number
WO2021043335A2
WO2021043335A2 PCT/CN2020/123359 CN2020123359W WO2021043335A2 WO 2021043335 A2 WO2021043335 A2 WO 2021043335A2 CN 2020123359 W CN2020123359 W CN 2020123359W WO 2021043335 A2 WO2021043335 A2 WO 2021043335A2
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WO
WIPO (PCT)
Prior art keywords
wing
pressing
fuselage
fixed
connecting portion
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PCT/CN2020/123359
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English (en)
French (fr)
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WO2021043335A3 (zh
Inventor
杜元源
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.)
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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 EP20859994.4A priority Critical patent/EP4043337A4/en
Publication of WO2021043335A2 publication Critical patent/WO2021043335A2/zh
Publication of WO2021043335A3 publication Critical patent/WO2021043335A3/zh
Priority to US17/653,525 priority patent/US20220185445A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • 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
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2211/00—Modular constructions of airplanes or helicopters

Definitions

  • the utility model relates to the technical field of aircraft, in particular to a wing disassembly assembly and an aircraft.
  • Aircraft can provide people with entertainment or perform tasks, such as being used as an important tool for high-altitude shooting.
  • an aircraft includes wings and a fuselage. Because the wings are relatively long, the space occupied by the aircraft is relatively large; therefore, aircraft with detachable wings came into being. However, the existing disassembly and assembly solutions of the wings of the aircraft are more troublesome and require special disassembly and assembly tools.
  • the main purpose of the present invention is to provide a wing disassembly assembly and an aircraft, which aims to solve the technical problem of the troublesome disassembly and assembly scheme of the wing of the existing aircraft.
  • the present invention provides a wing disassembly assembly for detachably connecting the wing of the aircraft to the fuselage of the aircraft.
  • the wing disassembly assembly includes a first connecting portion and a second connecting portion,
  • the first connecting part includes a fixing seat, a pressing part and a fastening part, one of the fixing seat and the second connecting part is fixed on the wing, and the other is fixed on the fuselage;
  • a mounting groove is defined on the second connecting portion, and the notch of the mounting groove faces away from the first connecting portion;
  • the pressing part is rotatably connected with the fixing seat, the buckling part is rotatably connected with the pressing part, one end of the buckling part is buckled in the mounting groove, and the pressing part is used for When being pressed, the fastener is driven to move away from the notch of the installation groove as a whole, so that the fastener is buckled in the installation groove.
  • the buckle member includes a buckle connecting rod and a buckle body provided at one end of the buckle connecting rod, and the other end of the buckle connecting rod is rotatably connected with the pressing member.
  • the buckling body has a spherical shape or a cylindrical shape.
  • the middle part of the pressing member is rotatably connected with the fastening member.
  • the pressing member includes a pressing connecting rod and a pressing handle, one end of the pressing connecting rod is rotatably connected to the fixing seat, and the other end of the pressing connecting rod is fixed to the pressing handle Connected, the pressing connecting rod and the pressing handle are located on different straight lines.
  • the installation groove includes a groove bottom and a groove wall, and the groove bottom and the groove wall are connected to form an arc surface.
  • the wing detachment assembly further includes a buckle for fixing the pressing member, and when the buckle is buckled in the installation groove, the buckle fixes the pressing Pieces.
  • the first connecting portion further includes a first connecting plate, and the first connecting plate and the fixing base are fixedly connected;
  • the first connecting plate is fixed on the inner wall of the housing of the fuselage, and the fixing seat passes through the housing of the fuselage and is rotatably connected with the pressing member ;
  • the first connecting plate is fixed on the inner wall of the outer shell of the wing, and the fixing seat passes through the outer shell of the wing and is rotatably connected to the pressing member .
  • the second connecting portion includes a connecting seat and a second connecting plate, the mounting groove is opened on the connecting seat, the second connecting plate and the connecting seat are fixedly connected, and the second connecting plate is used for Fixed on the inner wall of the outer shell of the fuselage or wing;
  • the connecting seat passes through the shell of the fuselage so that the mounting groove is exposed to the shell of the fuselage;
  • the connecting seat passes through the outer shell of the wing so that the mounting groove is exposed to the outer shell of the wing.
  • the present invention also provides an aircraft including a fuselage, a wing, and the above-mentioned wing detachment assembly, and the wing is detachably connected to the fuselage through the wing detachment assembly .
  • the second connecting part of the present invention is provided with a mounting groove, and the notch of the mounting groove faces away from the first connecting part;
  • the first connecting part includes a fixing seat, a pressing member and Fastening member, the fixing seat is used to be fixed on the fuselage or the wing, the pressing member and the fixing seat are rotatably connected, the buckle member and the pressing member are rotatably connected, the One end of the fastening member is used for fastening in the installation groove, and the pressing member is used for being compressed to drive the fastening member as a whole away from the notch of the installation groove, so that the fastening member By being fastened in the installation slot, the wing can be quickly installed on the fuselage, and the wing can be quickly disassembled from the fuselage. It can be completed manually without special disassembly and assembly tools, and the disassembly and assembly are simple.
  • Figure 1 is a schematic diagram of the structure of the wing disassembly assembly of the utility model.
  • Figure 2 is a schematic diagram of the structure of the first connecting part of the present invention.
  • Fig. 3 is a schematic diagram of the three-dimensional structure of the first connecting plate of the present invention.
  • Figure 4 is a schematic diagram of the structure of the pressing piece of the present invention.
  • Figure 5 is a schematic diagram of the structure of the fastening element of the present invention.
  • Figure 6 is a schematic diagram of the structure of the snap fastener of the present invention.
  • Fig. 7 is a schematic diagram of the structure of the second connecting part of the present invention.
  • Figure 8 is a schematic diagram of the structure of the utility model aircraft.
  • FIG. 9 is a schematic diagram of an enlarged structure at A in FIG. 8.
  • the present invention provides a wing detachment assembly 1 for detachably connecting the wing of the aircraft to the fuselage of the aircraft.
  • the wing disassembly assembly 1 includes a first connecting portion 10 and a second connecting portion 20, and the first connecting portion 10 and the second connecting portion 20 can be quickly detached and connected.
  • One of the first connecting portion 10 and the second connecting portion 20 is fixed on the wing, and the other is fixed on the fuselage.
  • the first connecting portion 10 is fixed on the fuselage, and the second connecting portion 20 is fixed on the wing for description.
  • the first connecting portion 10 includes a first connecting plate 11, a fixing seat 12, a pressing member 13, a buckling member 14 and a buckle member 15.
  • the first connecting plate 11 is fixedly connected to the fixing seat 12 and pressed together
  • the piece 13 is rotatably connected with the fixing base 12, and the fastening piece 14 is rotatably connected with the pressing piece 13.
  • the first connecting plate 11 is used to be fixed on the fuselage, one end of the buckle 14 is used to buckle on the second connecting portion 20, and the pressing piece 13 is used to be pressed by an external force to drive the buckle 14 away from the whole body.
  • the second connecting portion 20 is used to fix the buckle 14 to the second connecting portion 20, and the buckle 15 is used to fix the pressing piece 13, that is, to fix the pressing piece 13 on the body to make
  • the first connecting portion 10 and the second connecting portion 20 are more stable when connected. It can be understood that the fastener 15 can be omitted.
  • the shape of the first connecting plate 11 is not limited, for example, the shape of the first connecting plate 11 is a circle or a quadrilateral.
  • the first connecting plate 11 is fixed on the inner wall of the casing of the fuselage, wherein the fixing seat 12 passes through the casing of the fuselage and is rotatably connected with the pressing member 13.
  • the first connecting plate 11 is fixed on the inner wall of the housing, and the fixing is firm and not easy to fall.
  • the first connecting plate 11 may be glued to the inner wall of the casing of the fuselage.
  • the area of the first connecting plate 11 is set as required.
  • the first connecting plate 11 When the area of the first connecting plate 11 is large, the pressure on the shell of the fuselage can be made smaller, and the shell of the fuselage does not need to be made too thick. It can be understood that the first connecting plate 11 may also be fixed on the outer wall of the fuselage shell, or embedded in the fuselage shell.
  • the specific structure of the rotational connection between the fixing base 12 and the pressing member 13 is not limited.
  • it can adopt hinged connection, rotating shaft structure or bolt structure.
  • the fixing base 12 and the first connecting plate 11 may be integrally formed. It can be understood that the structure of the rotational connection of the other two components is not limited. It can be understood that the first connecting plate 11 can be omitted, so that the fixing base 12 is fixed on the fuselage.
  • one end of the pressing member 13 is rotatably connected with the fixing base 12, and the middle part of the pressing member 13 is rotatably connected with the fastening member 14.
  • the distance between the position on the middle of the pressing piece 13 and one end of the pressing piece 13 is greater than one-third of the length of the pressing piece 13, and the distance from the other end of the pressing piece 13 is less than one-third of the length of the pressing piece 13 two.
  • the pressing member 13 includes a pressing connecting rod 131 and a pressing handle 132.
  • One end of the pressing connecting rod 131 is rotatably connected to the fixing base 12, and the other end of the pressing connecting rod 131 is fixedly connected to the pressing handle 132.
  • the pressing connecting rod 131 and the pressing handle 132 are located on different straight lines.
  • the pressing handle 132 is convenient for the user to apply force to the pressing part 13 when disassembling and assembling the wing.
  • the pressing connecting rod 131 and the pressing handle 132 may be integrally formed.
  • the fastening member 14 includes a fastening connecting rod 141 and a fastening body 142 provided at one end of the fastening connecting rod 141, and the other end of the fastening connecting rod 141 is rotatably connected with the pressing part 13.
  • the buckling connecting rod 141 and the buckling body 142 are located on different planes, so that the buckling body 142 can be buckled on the second connecting portion 20.
  • the buckling connecting rod 141 is rod-shaped, and the shape of its cross-sectional area is not limited, for example, it may be circular or quadrilateral.
  • the buckle body 142 is spherical or cylindrical, and the buckle body 142 can contact the second connecting portion 20 better.
  • the buckling body 142 is cylindrical, one end of the cylindrical shape is connected to the side wall of the buckling connecting rod 141.
  • the buckle 15 is U-shaped, the middle part of the buckle 15 is used for buckling the pressing member 13, and the two ends of the buckle 15 are used for fixing on the body.
  • the two ends of the buckle 15 are used for fixing on the body.
  • holes or slots can be opened on the fuselage for fixing.
  • the outer sides of both ends of the U-shaped buckle 15 may be provided with protrusions 151 to engage with the body.
  • the second connecting portion 20 includes a second connecting portion 20 including a connecting seat 21 and a second connecting plate 22.
  • the connecting seat 21 is fixedly connected to the second connecting plate 22.
  • the second connecting plate 22 is used for fixing on the wing, and the connecting seat 21 is used for fixing the fastener 14.
  • the shape of the second connecting plate 22 is not limited.
  • the shape of the second connecting plate 22 is a circle or a quadrilateral.
  • the second connecting plate 22 is fixed on the inner wall of the outer shell of the wing, and the connecting seat 21 passes through the outer shell of the fuselage and is connected to the fastener 14.
  • the second connecting plate 22 is fixed on the inner wall of the outer shell of the wing, which is firmly fixed and not easy to fall.
  • the second connecting plate 22 may be glued to the inner wall of the outer shell of the wing.
  • the area of the second connecting plate 22 is set as required. When the area of the second connecting plate 22 is large, the pressure on the wing shell can be made smaller, and the wing shell does not need to be made too thick. It can be understood that the second connecting plate 22 may also be fixed on the outer wall of the wing shell, or embedded in the wing shell.
  • a mounting groove 211 is defined on the connecting seat 21, and the notch of the mounting groove 211 faces away from the first connecting portion 10.
  • the pressing member 13 is pressed to drive the entire buckling member 14 away from the notch of the mounting groove 211, so that the buckling body 142 of the buckling member 14 is buckled in the mounting groove 211, That is, the buckle body 142 is fixed in the installation groove 211.
  • the second connecting plate 22 can be omitted, so that the connecting seat 21 is fixed on the wing.
  • the installation groove 211 includes a groove bottom and a groove wall, and the groove bottom and the groove wall are connected to form an arc surface, which facilitates the fastening body 142 to be fixed in the installation groove 211 more easily.
  • the shape of the mounting groove 211 is not limited to this, and the shape of the mounting groove 211 is not limited in this application.
  • the mounting groove 211 may also be a V-shaped groove.
  • the first connecting plate 11 of the first connecting portion 10 is fixed on the inner wall of the outer shell of the fuselage
  • the second connecting plate 22 of the second connecting portion 20 is fixed on the inner wall of the outer shell of the wing.
  • Rotate the pressing piece 13 to place the buckling body 142 of the buckling piece 14 in the mounting groove 211, and then rotate the pressing piece 13 to move the buckling piece 14 away from the slot of the mounting groove 211 as a whole, so that the buckling body 142 is pressed
  • the fastening member 14 is fastened in the mounting groove 211
  • the fastening member 15 fixes the pressing member 13 on the fuselage, so that the wing can be installed on the fuselage.
  • the present invention also provides an aircraft 2.
  • the aircraft 2 includes a fuselage 30, a wing 40, and the aforementioned wing disassembly assembly 1, and the wing 40 passes through the wing disassembly assembly 1. It is detachably connected to the main body 30.
  • the aircraft 2 may be a flying device such as a drone.
  • the second connecting part of the present invention is provided with a mounting groove, and the notch of the mounting groove faces away from the first connecting part;
  • the first connecting part includes a fixing seat, a pressing member and Fastening member, the fixing seat is used to be fixed on the fuselage or the wing, the pressing member is rotatably connected with the fixing seat, the buckling member is rotatably connected with the pressing member, the One end of the fastening member is used for fastening in the installation groove, and the pressing member is used for being compressed to drive the fastening member as a whole away from the notch of the installation groove, so that the fastening member By being fastened in the installation slot, the wing can be quickly installed on the fuselage, and the wing can be quickly disassembled from the fuselage. It can be completed manually without special disassembly tools, and the disassembly is simple.

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

本实用新型涉及飞行器技术领域，尤其涉及一种机翼拆卸组件和飞行器。所述机翼拆卸组件包括第一连接部和第二连接部，所述第一连接部包括固定座、压合件和扣合件，所述固定座和所述第二连接部中的其中一者固定在机翼上，另一者固定在机身上；所述第二连接部上开设一安装槽，所述安装槽的槽口背离所述第一连接部；所述压合件和所述固定座转动连接，所述扣合件和所述压合件转动连接，所述扣合件的一端扣合在所述安装槽内，所述压合件用于在被压合时带动所述扣合件整体远离所述安装槽的槽口，以使所述扣合件扣合在所述安装槽内。飞行器包括了上述的机翼拆卸组件。该机翼拆卸组件和飞行器具有方便拆装机翼的优点。

Description

机翼拆卸组件和飞行器 技术领域
本实用新型涉及飞行器技术领域，尤其涉及一种机翼拆卸组件和飞行器。
背景技术
飞行器可以为人们提供娱乐或执行任务，如可以作为高空拍摄等的重要工具。通常，飞行器包括机翼和机身，由于机翼相对较长，会使飞行器占据的空间较大；于是，可拆卸机翼的飞行器应运而生。然而，现有的飞行器的机翼的拆装方案较为麻烦，需要专门的拆装工具。
因此，如何提供一种方便拆装飞行器机翼的方案，就成了现有技术的需求。
实用新型内容
本实用新型的主要目的在于提供一种机翼拆卸组件和飞行器，旨在解决现有的飞行器的机翼的拆装方案较为麻烦的技术问题。
第一方面，本实用新型提供了一种机翼拆卸组件，用于将飞行器的机翼可拆卸的连接于飞行器的机身，所述机翼拆卸组件包括第一连接部和第二连接部，所述第一连接部包括固定座、压合件和扣合件，所述固定座和所述第二连接部中的其中一者固定在机翼上，另一者固定在机身上；
所述第二连接部上开设一安装槽，所述安装槽的槽口背离所述第一连接部；
所述压合件和所述固定座转动连接，所述扣合件和所述压合件转动连接，所述扣合件的一端扣合在所述安装槽内，所述压合件用于在被压合时带动所述扣合件整体远离所述安装槽的槽口，以使所述扣合件扣合在所述安装槽内。
优选地，所述扣合件包括扣合连接杆和设于所述扣合连接杆一端的扣合体，所述扣合连接杆的另一端与所述压合件转动连接。
优选地，所述扣合体呈球体形或圆柱形。
优选地，所述压合件的中部与所述扣合件转动连接。
优选地，所述压合件包括压合连接杆和压合把手，所述压合连接杆的一端与所述固定座转动连接，所述压合连接杆的另一端与所述压合把手固定连接，所述压合连接杆和所述压合把手位于不同的直线上。
优选地，所述安装槽包括槽底和槽壁，所述槽底和所述槽壁连接形成弧面。
优选地，所述机翼拆卸组件还包括用于固定所述压合件的卡扣件，在所述扣合件扣合在所述安装槽内时，所述卡扣件固定所述压合件。
优选地，所述第一连接部还包括第一连接板，所述第一连接板和所述固定座固定连接；
当所述固定座固定在机身上时，所述第一连接板固定在所述机身的外壳的内壁上，所述固定座穿过所述机身的外壳与所述压合件转动连接；或
当所述固定座固定在机翼上时，所述第一连接板固定在所述机翼的外壳的内壁上，所述固定座穿过所述机翼的外壳与所述压合件转动连接。
优选地，所述第二连接部包括连接座和第二连接板，所述安装槽开设在所述连接座上，所述第二连接板和连接座固定连接，所述第二连接板用于固定在所述机身或机翼的外壳的内壁上；
当所述第二连接部固定在机身上时，所述连接座穿过所述机身的外壳以使所述安装槽外露于所述机身的外壳；或
当所述第二连接部固定在机翼上时，所述连接座穿过所述机翼的外壳以使所述安装槽外露于所述机翼的外壳。
第二方面，本实用新型还提供一种飞行器，所述飞行器包括机身、机翼和上述的机翼拆卸组件，所述机翼通过所述机翼拆卸组件可拆卸地连接于所述机身。
与现有技术相比，本实用新型的第二连接部上开设一安装槽，所述安装槽的槽口背离所述第一连接部；所述第一连接部包括固定座、压合件和扣合件，所述固定座用于固定在所述机身或机翼上，所述压合件和所述固定座转动连接，所述扣合件和所述压合件转动连接，所述扣合件的一端用于扣合在所述安装槽内，所述压合件用于被压合以带动所述扣合件整体远离所述安装槽的槽口，以使所述扣合件扣合在所述安装槽内，能把机翼快速安装在机身上，也能把机翼快速从机身上拆卸下来，不用专门的拆装工具，手动即可完 成，拆装简单。
附图说明
图1为本实用新型的机翼拆卸组件的结构示意图。
图2为本实用新型的第一连接部的结构示意图。
图3为本实用新型的第一连接板的立体结构示意图。
图4为本实用新型的压合件的结构示意图。
图5为本实用新型的扣合件的结构示意图。
图6为本实用新型的卡扣件的结构示意图。
图7为本实用新型的第二连接部的结构示意图。
图8为本实用新型的飞行器的结构示意图。
图9为图8中A处的放大结构示意图。
具体实施方式
为了使本实用新型的目的、技术方案及优点更加清楚明白，以下结合附图及实施例，对本实用新型进行进一步详细说明。应当理解，此处所描述的具体实施例仅用以解释本实用新型，并不用于限定本实用新型。基于本实用新型中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本实用新型保护的范围。
本申请的说明书和权利要求书及上述附图中的术语“第一”、“第二”、“第三”、“第四”等(如果存在)是用于区别类似的对象，而不必用于描述特定的顺序或先后次序。应该理解这样使用的数据在适当情况下可以互换，以便这里描述的实施例能够以除了在这里图示或描述的内容以外的顺序实施。此外，术语“包括”和“具有”以及他们的任何变形，意图在于覆盖不排他的包含，例如，包含了一系列步骤或单元的过程、方法、系统、产品或设备不必限于清楚地列出的那些步骤或单元，而是可包括没有清楚地列出的或对于这些过程、方法、产品或设备固有的其它步骤或单元。
另外，各个实施例之间的技术方案可以相互结合，但是必须是以本领域普通技术人员能够实现为基础，当技术方案的结合出现相互矛盾或无法实现时应当认为这种技术方案的结合不存在，也不在本实用新型要求的保护范围 之内。
请参阅图1，本实用新型提供一种机翼拆卸组件1，用于将飞行器的机翼可拆卸地连接于飞行器的机身。机翼拆卸组件1包括第一连接部10和第二连接部20，第一连接部10与第二连接部20能快速拆卸连接。第一连接部10和第二连接部20的中其中一者固定在机翼上，另一者固定在机身上。本实施例中，以第一连接部10固定在机身上，第二连接部20固定在机翼上进行说明。
请参阅图2，第一连接部10包括第一连接板11、固定座12、压合件13、扣合件14和卡扣件15，第一连接板11与固定座12固定连接，压合件13与和固定座12转动连接，扣合件14与压合件13转动连接。第一连接板11用于固定在机身上，扣合件14的一端用于扣合在第二连接部20，压合件13用于受外力作用被压合以带动扣合件14整体远离所述第二连接部20，以使扣合件14固定在第二连接部20，卡扣件15用于固定所述压合件13，即把压合件13固定在机身上，以使第一连接部10与第二连接部20连接时更稳固。可以理解，卡扣件15可以省略设置。
请参阅图3，第一连接板11的形状不做限定，例如，第一连接板11的形状为圆形或四边形。本实施例中，第一连接板11固定在所述机身的外壳的内壁上，其中固定座12穿过所述机身的外壳与压合件13转动连接。第一连接板11固定在外壳的内壁上，固定牢固，不易掉落。第一连接板11可以粘合在机身的外壳的内壁上。第一连接板11的面积根据需要进行设置，在第一连接板11的面积大时，能使机身的外壳的所受的压强较小，机身的外壳就不必做的过厚。可以理解，第一连接板11也可以固定在机身外壳的外壁上，或嵌入机身的外壳。
固定座12与压合件13转动连接的具体结构不做限定。如可以采用如可通过铰接、转轴结构或插销结构。固定座12和第一连接板11可以一体成型。可以理解，其他两个元器件转动连接的结构也不做限定。可以理解，第一连接板11可省略设置，使固定座12固定在所述机身上。
请一并参阅图2和图4，压合件13的一端与固定座12转动连接，压合件13的中部与扣合件14转动连接。压合件13的中部上的位置距压合件13的一端的距离大于压合件13长度的三分之一，距压合件13的另一端的距离小于 压合件13长度的三分之二。压合件13包括压合连接杆131与压合把手132，压合连接杆131的一端与所述固定座12转动连接，压合连接杆131的另一端与压合把手132固定连接，所述压合连接杆131和所述压合把手132位于不同的直线上。压合把手132便于用户拆装机翼时，向压合件13施力。压合连接杆131和压合把手132可以一体成型设置。
请一并参阅图2和图5，扣合件14包括扣合连接杆141和设于扣合连接杆141一端的扣合体142，扣合连接杆141的另一端与压合件13转动连接。扣合连接杆141和所述扣合体142位于不同的平面上，以使扣合体142能扣合在第二连接部20上。
扣合连接杆141为杆状，其横截面积的形状不做限定，如可以为圆形，或四边形。
扣合体142呈球体形或圆柱形，扣合体142能和第二连接部20接触的更好。扣合体142为圆柱形时，圆柱形的一端部与扣合连接杆141的侧壁连接。
请参阅图6，卡扣件15呈U形，卡扣件15的中部用于卡设压合件13，卡扣件15的两端用于固定在机身上。如机身上可以开设孔或槽以进行固定。作为一种选择，U形的卡扣件15的两端的外侧可以分别设置凸起151，以和机身卡合。
请一并参阅图2和图7，第二连接部20包括第二连接部20包括连接座21和第二连接板22。连接座21与第二连接板22固定连接。第二连接板22用于固定在机翼上，连接座21用于供扣合件14固定。
第二连接板22的形状不做限定，例如，第二连接板22的形状为圆形或四边形。本实施例中，第二连接板22固定在所述机翼的外壳的内壁上，其中连接座21座穿过所述机身的外壳与扣合件14连接。第二连接板22固定在机翼的外壳的内壁上，固定牢固，不易掉落。第二连接板22可以粘合在机翼的外壳的内壁上。第二连接板22的面积根据需要进行设置，在第二连接板22的面积大时，能使机翼的外壳的所受的压强较小，机翼的外壳就不必做的过厚。可以理解，第二连接板22也可以固定在机翼外壳的外壁上，或嵌入机翼的外壳。
连接座21上开设一安装槽211，所述安装槽211的槽口背离所述第一连接部10。压合件13在被压合以带动所述扣合件14的整体远离所述安装槽211 的槽口，以使所述扣合件14的扣合体142扣合在所述安装槽211内，即扣合体142固定在安装槽211内。可以理解，第二连接板22可以省略设置，使连接座21固定在所述机翼上。
安装槽211包括槽底和槽壁，所述槽底与所述槽壁连接形成弧面，便于扣合体142更容易固定在安装槽211内。可以理解，安装槽211的形状并不以此为限，本申请中并不限定安装槽211的形状，如安装槽211也可以是V形槽。
在使用时，把第一连接部10的第一连接板11固定在机身的外壳的内壁上，第二连接部20的第二连接板22固定在机翼的外壳的内壁上。转动压合件13，把扣合件14的扣合体142能放置在安装槽211内，再转动压合件13，使扣合件14整体远离安装槽211的槽口，使扣合体142压在安装槽211的槽底。在扣合件14扣合在所述安装槽211内时，卡扣件15把压合件13固定在机身上，即可使机翼安装在机身上。可以理解，一个飞行器有2个机翼时，需要使用2个机翼拆卸组件1，以快速拆卸每一个机翼。可以理解，对上述操作进行反向操作，即可拆卸机翼。
可以理解，当第一连接部10的固定座12固定在机翼上，当第二连接部20固定在机身上时，所述第一连接板11固定在所述机翼的外壳的内壁上，固定座12穿过所述机翼的外壳与所述压合件13转动连接，所述第二连接部20的连接座21穿过机身的外壳以使所述安装槽211外露于所述机身的外壳。
请一并参阅图8和图9，本实用新型还提供一种飞行器2，所述飞行器2包括机身30、机翼40和前述的机翼拆卸组件1，机翼40通过机翼拆卸组件1可拆卸地连接于机身30。飞行器2可以是无人机等用于飞行的装置。
与现有技术相比，本实用新型的第二连接部上开设一安装槽，所述安装槽的槽口背离所述第一连接部；所述第一连接部包括固定座、压合件和扣合件，所述固定座用于固定在所述机身或机翼上，所述压合件与所述固定座转动连接，所述扣合件与所述压合件转动连接，所述扣合件的一端用于扣合在所述安装槽内，所述压合件用于被压合以带动所述扣合件整体远离所述安装槽的槽口，以使所述扣合件扣合在所述安装槽内，能把机翼快速安装在机身上，也能把机翼快速从机身上拆卸下来，不用专门的拆卸工具，手动即可完成，拆卸简单。
需要说明的是，上述本实用新型实施例序号仅仅为了描述，不代表实施例的优劣。并且本文中的术语“包括”、“包含”或者其任何其他变体意在涵盖非排他性的包含，从而使得包括一系列要素的过程、装置、物品或者方法不仅包括那些要素，而且还包括没有明确列出的其他要素，或者是还包括为这种过程、装置、物品或者方法所固有的要素。在没有更多限制的情况下，由语句“包括一……”限定的要素，并不排除在包括该要素的过程、装置、物品或者方法中还存在另外的相同要素。
以上仅为本实用新型的优选实施例，并非因此限制本实用新型的专利范围，凡是利用本实用新型说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本实用新型的专利保护范围内。

Claims (10)

  1. 一种机翼拆卸组件，用于将飞行器的机翼可拆卸的连接于飞行器的机身，其特征在于：所述机翼拆卸组件包括第一连接部和第二连接部，所述第一连接部包括固定座、压合件和扣合件，所述固定座和所述第二连接部中的其中一者固定在机翼上，另一者固定在机身上；
    所述第二连接部上开设一安装槽，所述安装槽的槽口背离所述第一连接部；
    所述压合件和所述固定座转动连接，所述扣合件和所述压合件转动连接，所述扣合件的一端扣合在所述安装槽内，所述压合件用于在被压合时带动所述扣合件整体远离所述安装槽的槽口，以使所述扣合件扣合在所述安装槽内。
  2. 如权利要求1所述的机翼拆卸组件，其特征在于：所述扣合件包括扣合连接杆和设于所述扣合连接杆一端的扣合体，所述扣合连接杆的另一端与所述压合件转动连接。
  3. 如权利要求2所述的机翼拆卸组件，其特征在于：所述扣合体呈球体形或圆柱形。
  4. 如权利要求1所述的机翼拆卸组件，其特征在于：所述压合件的中部与所述扣合件转动连接。
  5. 如权利要求1所述的机翼拆卸组件，其特征在于：所述压合件包括压合连接杆和压合把手，所述压合连接杆的一端与所述固定座转动连接，所述压合连接杆的另一端与所述压合把手固定连接，所述压合连接杆和所述压合把手位于不同的直线上。
  6. 如权利要求1所述的机翼拆卸组件，其特征在于：所述安装槽包括槽底和槽壁，所述槽底和所述槽壁连接形成弧面。
  7. 如权利要求1所述的机翼拆卸组件，其特征在于：所述机翼拆卸组件还包括用于固定所述压合件的卡扣件，在所述扣合件扣合在所述安装槽内时，所述卡扣件固定所述压合件。
  8. 如权利要求1所述的机翼拆卸组件，其特征在于：所述第一连接部还包括第一连接板，所述第一连接板和所述固定座固定连接；
    当所述固定座固定在机身上时，所述第一连接板固定在所述机身的外壳的内壁上，所述固定座穿过所述机身的外壳与所述压合件转动连接；或
    当所述固定座固定在机翼上时，所述第一连接板固定在所述机翼的外壳的内壁上，所述固定座穿过所述机翼的外壳与所述压合件转动连接。
  9. 如权利要求1所述的机翼拆卸组件，其特征在于：所述第二连接部包括连接座和第二连接板，所述安装槽开设在所述连接座上，所述第二连接板和连接座固定连接，所述第二连接板用于固定在所述机身或机翼的外壳的内壁上；
    当所述第二连接部固定在机身上时，所述连接座穿过所述机身的外壳以使所述安装槽外露于所述机身的外壳；或
    当所述第二连接部固定在机翼上时，所述连接座穿过所述机翼的外壳以使所述安装槽外露于所述机翼的外壳。
  10. 一种飞行器，其特征在于，所述飞行器包括机身、机翼和权利要求1～9任一项所述的机翼拆卸组件，所述机翼通过所述机翼拆卸组件可拆卸地连接于所述机身。
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