WO2023142702A1 - 一种锁定装置及无人机 - Google Patents

一种锁定装置及无人机 Download PDF

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Publication number
WO2023142702A1
WO2023142702A1 PCT/CN2022/137318 CN2022137318W WO2023142702A1 WO 2023142702 A1 WO2023142702 A1 WO 2023142702A1 CN 2022137318 W CN2022137318 W CN 2022137318W WO 2023142702 A1 WO2023142702 A1 WO 2023142702A1
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WIPO (PCT)
Prior art keywords
fuselage
wing
auxiliary
main
locking device
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PCT/CN2022/137318
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English (en)
French (fr)
Inventor
陈建国
司亮
李金鸣
余敏
李隽卿
段先楚
Original Assignee
航天时代飞鸿技术有限公司
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Application filed by 航天时代飞鸿技术有限公司 filed Critical 航天时代飞鸿技术有限公司
Publication of WO2023142702A1 publication Critical patent/WO2023142702A1/zh

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    • 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

Definitions

  • the invention relates to the field of unmanned aerial vehicles, in particular to a locking device and an unmanned aerial vehicle.
  • the purpose of the present invention is to solve the shortcomings in the prior art.
  • the present invention aims to provide a locking device and a drone for solving the above-mentioned problems in the prior art.
  • a locking device for connecting the wing and the fuselage of the drone comprising: at least two first connecting parts and at least two corresponding second connecting parts;
  • the at least two first connectors are telescopically/rotatably arranged on the wing/fuselage;
  • the at least two second connectors are arranged on the fuselage/wing,
  • the at least two first connectors are respectively correspondingly connected to the at least two second connectors.
  • the at least two first connecting parts include a main wing/fuselage pin and a secondary wing/fuselage pin.
  • the at least two second connectors include a fuselage/wing main box corresponding to the wing/fuselage main pin , and the fuselage/wing auxiliary box corresponding to the wing/fuselage auxiliary pin.
  • the locking device further includes a main quick release pin and a secondary quick release pin, the main quick release pin connects the main bolt and the main sleeve box; the secondary quick release pin connects the secondary latch and the secondary sleeve.
  • an implementation mode is further provided, the upper end of the main quick release pin and the auxiliary quick release pin are provided with a circular boss, and the lower end is provided with a through hole, and the The distance from the circular boss to the through hole is the same as the thickness of the wing at the installation position of the main quick release pin and the auxiliary quick release pin.
  • the main bolt and the auxiliary bolt are provided with cylindrical holes, correspondingly, on the main casing and the auxiliary casing Each is provided with a circular hole corresponding to the cylindrical hole.
  • an implementation mode which further includes two spring bayonet pins, and the two spring bayonet pins are respectively installed on the main quick release pin and the secondary quick release pin. on the through hole at the lower end.
  • an implementation mode is further provided, the length of the main quick release pin and the auxiliary quick release pin is longer than the length of the main bolt and the main sleeve, and the length of the auxiliary bolt and the auxiliary sleeve The height of the wing at the location of the box.
  • the present invention also provides an unmanned aerial vehicle, the unmanned aerial vehicle comprises the locking device described in the present invention, a wing and a fuselage, and the locking device is used to connect the wing and the fuselage.
  • the locking device includes at least two sets, which are respectively arranged between the fuselage of the drone and the wings on the left and right sides.
  • the locking device provided by the embodiment of the present invention is used to connect the wing and the fuselage of the drone, and the locking device includes at least two first connecting parts and at least two corresponding second connecting parts; wherein, the at least The two first connectors are telescopically/rotatably arranged on the wing/fuselage; correspondingly, the at least two second connectors are arranged on the fuselage/wing, and the at least two The first connecting pieces are respectively correspondingly connected to the at least two second connecting pieces.
  • the locking device of the present invention can realize convenient disassembly and assembly of the wing and the fuselage without tools, simple operation and reliable locking.
  • Fig. 1 is a schematic exploded view of a locking device in an embodiment of the present invention
  • Fig. 2 is a schematic diagram of the docking process of the wing and the fuselage in an embodiment of the present invention
  • Fig. 3 is a schematic diagram of the upper surface effect after the wing and the fuselage are docked in an embodiment of the present invention
  • Fig. 4 is a schematic diagram of the effect of the lower surface of the wing after it is docked with the fuselage in the embodiment of the present invention.
  • the locking device in the present invention is used for the wing and fuselage of the drone, and the locking device includes at least two first connectors and at least two corresponding second connectors; wherein, The at least two first connectors are telescopically/rotatably arranged on the wing/fuselage; correspondingly, the at least two second connectors are arranged on the fuselage/wing, and the At least two first connectors are respectively connected to the at least two second connectors correspondingly.
  • the locking device in the embodiment of the present invention includes a main wing pin 1, a main fuselage box 2, an auxiliary wing pin 3, an auxiliary fuselage box 4, a main quick release pin 5, and an auxiliary quick release pin 6, spring bayonet 7,
  • main latch 1 and auxiliary latch 3 can be set on the fuselage, correspondingly main cover box 2 and auxiliary cover box 4 are set on the wing.
  • the main pin 1 and the secondary pin 3 in the embodiment of the present invention are telescopically/rotatably arranged on the wing/fuselage, specifically, a cavity is provided on the corresponding wing/fuselage,
  • a cavity is provided on the corresponding wing/fuselage,
  • the main pin 1 and the auxiliary pin 3 shrink into the corresponding cavity, which is convenient for the wing and the fuselage to be packed and transported separately; or when the main pin 1 and the auxiliary pin 3 are connected to the wing
  • a rotation axis is set between the fuselage and the main pin 1 and the secondary pin 3 are rotated to the side of the wing/fuselage when locking is not required, which is convenient for placement or transportation.
  • the main quick release pin 5 connects the main pin 1 and the main casing 2; the secondary quick release pin 6 connects the secondary pin 3 and the secondary casing 4,
  • the main wing pin 1 is inserted into the fuselage main box 2
  • the wing auxiliary pin 3 is inserted into the fuselage auxiliary box 4, and the two actions are performed simultaneously.
  • the fuselage end surface and the wing The end faces are aligned, and the assembly process is shown in Figure 2; wherein, the upper ends of the main quick release pin 5 and the auxiliary quick release pin 6 are provided with a circular boss, and the lower ends of the main quick release pin 5 and the auxiliary quick release pin 6 are provided with a through hole
  • the shape of the through hole can be circular, square or elliptical, etc., and its shape is not limited. of the same thickness.
  • cylindrical holes are provided on the main bolt 1 and the auxiliary bolt 3, and the cylindrical holes are in the vertical direction.
  • a circular hole is provided, which is also in the vertical direction.
  • the length of the main quick release pin 5 and the auxiliary quick release pin 6 in the embodiment of the present invention is greater than the height at the wing where the main latch 1 and the main sleeve box 2, the auxiliary latch 3 and the auxiliary sleeve box 4 are located, thereby ensuring The complete alignment and locking of the wing and the fuselage, after locking, the surfaces of the two are the same plane, and the through holes provided at the lower ends of the main quick release pin 5 and the auxiliary quick release pin 6, the axes of the two through holes are respectively in line with the The axes of the main quick release pin 5 and the auxiliary quick release pin 6 are perpendicular; in the locking device of the present invention, two spring bayonet pins 7 are also arranged, and the main quick release pin 5 and the auxiliary quick release pin 6 pass through the After overlapping and aligning the cylindrical hole and the round hole, the lower end provided with the through hole protrudes from the lower surface of the fuselage at the corresponding joint, and the two spring latches 7 pass through
  • the process of dismantling a wing of the locking device is as follows: firstly, the spring bayonet 7 is sequentially pulled out from the through holes of the main quick release pin 5 and the auxiliary quick release pin 6 respectively, and the main quick release pin 5 and the auxiliary quick release pin 6 are completed.
  • main quick release pin 5 and the auxiliary quick release pin 6 are pulled out from the fuselage in turn to complete the main wing pin 1 and the fuselage main box 2, the wing auxiliary pin 3 and the fuselage auxiliary box 4 At the same time, retract or rotate the main pin 1 and the auxiliary pin 3; finally, pull out the wing from the fuselage to complete the separation and disassembly of the wing and the fuselage, and use the same method to quickly disassemble and unlock the other wing.
  • the present invention also provides an unmanned aerial vehicle.
  • the unmanned aerial vehicle includes a locking device, a wing and a fuselage.
  • the locking device includes at least two sets, which are respectively arranged on the unmanned fuselage and the two sides of the fuselage. between the wings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Forklifts And Lifting Vehicles (AREA)

Abstract

一种锁定装置和无人机，其中锁定装置用于无人机的机翼和机身，锁定装置包括至少两个第一连接件（1,3）及对应的至少两个第二连接件（2,4）；其中，至少两个第一连接件可伸缩/旋转地设置于所述机翼/机身上；对应地，至少两个第二连接件设置于所述机身/机翼上，至少两个第一连接件分别对应连接所述至少两个第二连接件。锁定装置可实现机翼与机身无工具便捷拆装，操作简单，锁定可靠。

Description

一种锁定装置及无人机 技术领域
本发明涉及无人机领域，尤其涉及一种锁定装置及无人机。
 背景技术
目前大多数无人机为满足道路运输条件，都采用将无人机的各个部分进行拆卸，将拆卸的部件分别装箱进行运输，从而将无人机运输到需要的地方。当无人机需要执行任务时，通过组装的方式，将装箱的无人机的各个部件，按照无人机的设计方案完成无人机各个组件的装配，将这些装箱的各个部件装配完整后，无人机才可进行飞行，从而执行预定的任务。机翼与机身对接机构广泛应用于具有固定翼的无人机，而常规的无人机的机翼和机身一般直接用螺栓固连接，但这种连接方式在装配与运输过程中在对机翼和机身进行拆装时比较麻烦，而且频繁的拆装容易对机翼造成损害，影响机翼的结构，且对机翼和机身装在一起后的无人机的飞行性能也会带来一定的影响。因此，研究一种对各种无人机的机翼和机身均适用的连接锁定装置成为目前亟待解决的问题。
 技术问题
本发明的目的是为了解决现有技术中存在的缺点，本发明旨在提供一种锁定装置及无人机，用于解决现有技术中存在的上述问题。
 技术解决方案
本发明的上述技术目的将通过以下所述的技术方案予以实现。
一种锁定装置，用于连接无人机的机翼和机身，所述锁定装置包括：至少两个第一连接件及对应的至少两个第二连接件；
 其中，所述至少两个第一连接件可伸缩/旋转地设置于所述机翼/机身上；
对应地，所述至少两个第二连接件设置于所述机身/机翼上，
所述至少两个第一连接件分别对应连接所述至少两个第二连接件。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述至少两个第一连接件包括机翼/机身主插销和机翼/机身副插销。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述至少两个第二连接件包括与所述机翼/机身主插销对应的机身/机翼主套箱，及与所述机翼/机身副插销对应的机身/机翼副套箱。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述锁定装置还包括主快卸销和副快卸销，所述主快卸销连接所述主插销和主套箱；所述副快卸销连接所述副插销和所述副套箱。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述主快卸销和所述副快卸销的上端设置有圆形凸台，下端设置有贯通孔，且所述圆形凸台至贯通孔的间距与所述主快卸销和副快卸销的安装位置处的机翼的厚度相同。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述主插销和所述副插销上均设置有圆柱孔，相应地，在所述主套箱和副套箱上均设置有与所述圆柱孔对应的圆孔。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，还包括两个弹簧卡销，所述两个弹簧卡销分别穿设在所述主快卸销和副快卸销下端的所述贯通孔上。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述主快卸销和副快卸销的长度大于所述主插销与主套箱、所述副插销与副套箱所在位置处机翼的高度。
本发明还提供了一种无人机，所述无人机包括本发明所述的锁定装置、机翼和机身，所述锁定装置用于连接所述机翼与机身。
如上所述的方面和任一可能的实现方式，进一步提供一种实现方式，所述锁定装置至少包括两套，分别设置于所述无人机的机身与左右两侧的机翼之间。
 有益效果
本发明的有益技术效果
本发明实施例提供的锁定装置，用于连接无人机的机翼和机身，所述锁定装置包括至少两个第一连接件及对应的至少两个第二连接件；其中，所述至少两个第一连接件可伸缩/旋转地设置于所述机翼/机身上；对应地，所述至少两个第二连接件设置于所述机身/机翼上，所述至少两个第一连接件分别对应连接所述至少两个第二连接件。本发明的锁定装置，可以实现机翼与机身无工具便捷拆装，操作简单，锁定可靠。
 附图说明
以下，结合附图来详细说明本发明的实施例，其中：
图1为本发明的实施例中的锁定装置爆炸视示意图；
图2 为本发明的实施例中机翼与机身对接过程示意图；
图3 为本发明的实施例中机翼与机身对接后上表面效果示意图；
图4为本发明的实施例中机翼与机身对接后下表面效果示意图。
 本发明的实施方式
为使本发明要解决的技术问题、技术方案和优点更加清楚，下面将结合附图及具体实施例进行详细描述，但本发明的实施方式不限于此。
如图1所示，本发明中的锁定装置，用于无人机的机翼和机身，所述锁定装置包括至少两个第一连接件及对应的至少两个第二连接件；其中，所述至少两个第一连接件可伸缩/旋转地设置于所述机翼/机身上；对应地，所述至少两个第二连接件设置于所述机身/机翼上，所述至少两个第一连接件分别对应连接所述至少两个第二连接件。
具体地，本发明中的实施例中的锁定装置包括机翼主插销1、机身主套箱2、机翼副插销3、机身副套箱4、主快卸销5、副快卸销6、弹簧卡销7，插销和套箱的位置不作限定，也可以在机身上设置主插销1和副插销3，相应地在机翼上设置主套箱2和副套箱4。
优选地，本发明中的实施例中的主插销1和副插销3可伸缩/旋转地设置于所述机翼/机身上，具体来说在相应的机翼/机身上设置空腔，在机翼和机身分离时，所述主插销1和副插销3收缩至相应的该空腔内，方便机翼和机身分别装箱运输；或者在主插销1和副插销3与机翼/机身之间设置旋转轴，在无需锁定时，将主插销1和副插销3旋转至机翼/机身的侧边，方便放置或运输。
优选地，本发明中的实施例中所述主快卸销5连接所述主插销1和主套箱2；所述副快卸销6连接所述副插销3和所述副套箱4，在具体锁定时，机翼主插销1插入机身主套箱2中，机翼副插销3插入机身副套箱4中，且两个动作同时进行，完成上述动作后机身端面和机翼端面贴齐，装配过程如图2所示；其中，主快卸销5和副快卸销6的上端设置有圆形凸台，主快卸销5和副快卸销6的下端设置有贯通孔，贯通孔的形状可为圆形、方形或椭圆形等，其形状不限，圆形凸台至贯通孔的间距与主快卸销5和副快卸销6的安装位置处的机翼的厚度相同。
优选地，本发明的实施例中在所述主插销1和副插销3上均设置有圆柱孔，圆柱孔为竖直方向，相应地，在主套箱2和副套箱4上相应位置处设置有圆孔，也为竖直方向，在机翼和机身安装时，所述主插销1插入机身主套箱2中以后，使所述主插销1上的圆柱孔与主套箱2上的圆孔对齐；同样地，所述副插销3插入机身副套箱4中以后使所述副插销3上的圆柱孔与副套箱4上的圆孔对齐。也就是说，在主插销1与主套箱2、副插销3与副套箱4插入连接时，上述的圆柱孔与圆孔处于重合对齐的状态，在这种情况下，主快卸销5和副快卸销6分别穿过所述重合对齐的圆柱孔与圆孔，实现方便快速拆装，安装完成后的效果如图3所示。
优选地，本发明的实施例中的主快卸销5和副快卸销6的长度大于主插销1与主套箱2、副插销3与副套箱4所在机翼处的高度，从而保证机翼与机身的完全对齐锁定，锁定后二者的表面为同一平面，在主快卸销5和副快卸销6的下端设置的贯通孔，两个所述贯通孔的轴线分别与所述主快卸销5和副快卸销6的轴线相垂直；在本发明的锁定装置中还设置有两个弹簧卡销7，主快卸销5和副快卸销6在穿过所述重合对齐的圆柱孔与圆孔后，其设置有贯通孔的下端伸出于相应连接处的机身的下表面，两个弹簧卡销7分别穿过贯通孔，完成锁定安装，安装完成后的效果如图4所示。
锁定装置拆解一个机翼的过程为：首先，将弹簧卡销7依次分别从主快装销5和副快装销6的贯通孔中抽出，完成主快装销5和副快装销6的解锁；然后将主快装销5和副快装销6依次分别从机身上抽出，完成机翼主插销1和机身主套箱2、机翼副插销3和机身副套箱4的解锁，同时将主插销1和副插销3进行收缩或旋转；最后将机翼从机身中抽出，完成机翼和机身的分离拆卸，同时采用相同方式快拆解锁另外一个机翼。
本发明还提供了一种无人机，所述无人机包括锁定装置、机翼和机身，所述锁定装置至少包括两套，分别设置于所述无人的机身与机身两侧的机翼之间。
上述说明示出并描述了本发明的若干优选实施例，但如前所述，应当理解本发明并非局限于本文所披露的形式，不应看作是对其他实施例的排除，而可用于各种其他组合、修改和环境，并能够在本发明所述申请构想范围内，通过上述教导或相关领域的技术或知识进行改动。而本领域人员所进行的改动和变化不脱离本发明的精神和范围，则都应在本发明所附权利要求书的保护范围内。

Claims (10)

  1. 一种锁定装置，用于连接无人机的机翼和机身，其特征在于，所述锁定装置包括至少两个第一连接件及对应的至少两个第二连接件；
     其中，所述至少两个第一连接件可伸缩/旋转地设置于所述机翼/机身上；
    对应地，所述至少两个第二连接件设置于所述机身/机翼上，
    所述至少两个第一连接件分别对应连接所述至少两个第二连接件。
  2. 根据权利要求1所述的锁定装置，其特征在于，所述至少两个第一连接件包括机翼/机身主插销和机翼/机身副插销。
  3. 根据权利要求2所述的锁定装置，其特征在于，所述至少两个第二连接件包括与所述机翼/机身主插销对应的机身/机翼主套箱及与所述机翼/机身副插销对应的机身/机翼副套箱。
  4. 根据权利要求3所述的锁定装置，其特征在于，所述锁定装置还包括主快卸销和副快卸销，所述主快卸销连接所述主插销和主套箱；所述副快卸销连接所述副插销和所述副套箱。
  5. 根据权利要求4所述的锁定装置，其特征在于，所述主快卸销和所述副快卸销的上端设置有圆形凸台，下端设置有贯通孔，且所述圆形凸台至贯通孔的间距与所述主快卸销和副快卸销的安装位置处的机翼的厚度相同。
  6. 根据权利要求4所述的锁定装置，其特征在于，所述主插销和所述副插销上均设置有圆柱孔，相应地，在所述主套箱和副套箱上均设置有与所述圆柱孔对应的圆孔。
  7. 根据权利要求5所述的锁定装置，其特征在于，还包括两个弹簧卡销，所述两个弹簧卡销分别穿设在所述主快卸销和副快卸销下端的所述贯通孔上。
  8. 根据权利要求7所述的锁定装置，其特征在于，所述主快卸销和副快卸销的长度分别大于所述主插销与主套箱、所述副插销与副套箱所在位置处机翼的高度。
  9. 一种无人机，其特征在于，所述无人机包括权利要求1-8任一项所述的锁定装置、机翼和机身，所述锁定装置用于连接所述机翼与机身。
  10. 根据权利要求9所述的无人机，其特征在于，所述锁定装置至少包括两套，分别设置于所述无人机的机身与左右两侧的机翼之间。
PCT/CN2022/137318 2022-01-25 2022-12-07 一种锁定装置及无人机 WO2023142702A1 (zh)

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