WO2018094824A1 - 固定卡扣和具有该固定卡扣的无人机 - Google Patents

固定卡扣和具有该固定卡扣的无人机 Download PDF

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Publication number
WO2018094824A1
WO2018094824A1 PCT/CN2016/113250 CN2016113250W WO2018094824A1 WO 2018094824 A1 WO2018094824 A1 WO 2018094824A1 CN 2016113250 W CN2016113250 W CN 2016113250W WO 2018094824 A1 WO2018094824 A1 WO 2018094824A1
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WO
WIPO (PCT)
Prior art keywords
buckle
limiting
fixing
sensor
support
Prior art date
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Ceased
Application number
PCT/CN2016/113250
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English (en)
French (fr)
Inventor
吴旭民
吴晓龙
周乐
韩振
关毅骏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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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Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680088505.5A priority Critical patent/CN109562842A/zh
Publication of WO2018094824A1 publication Critical patent/WO2018094824A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • 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
    • B64D43/00—Arrangements or adaptations of instruments
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C17/00—Compasses; Devices for ascertaining true or magnetic north for navigation or surveying purposes

Definitions

  • the present invention relates to a fixed buckle and a drone having the same.
  • the drone is controlled by a radio remote control device.
  • the current sensing components such as the compass sensor fixing method, are mostly fixed with or without magnetic screws, and require fixtures for auxiliary assembly positioning during assembly, and the assembly is complicated.
  • the sensing component is damaged, it is difficult for the customer to repair it by itself, and the damaged tripod is usually connected during the process of adhesive damage, resulting in greater loss.
  • the adhesive is likely to fail in harsh environments, causing displacement of the sensing components, such as the compass sensor, which can seriously affect the flight control of the drone and easily cause the drone to blow.
  • a fixing buckle for fixing a sensor to a support member comprising: a buckle body and a limiting portion disposed on a surface of the buckle body, the buckle body having a fitting groove for receiving And positioning the sensor, the limiting portion being connectable with the support member to fix the sensor relative to the support member.
  • the limiting portion is a limiting protrusion, and the limiting protrusion protrudes from the surface of the buckle body in a normal state, and can be contracted toward the buckle body and received in the card in a pressing state. Buckle inside the body.
  • the limiting portion has a cylindrical limiting protrusion.
  • the number of the limiting portions is two.
  • the buckle body has spaced apart sheet-like extensions, the limiting portions are respectively disposed on the extending portion, and the extending portions have elasticity, and the extending portions may be close to or away from each other.
  • a clip between the mounting groove and the direction perpendicular to the top of the buckle body The angle is at a predetermined angle and is not zero.
  • the two opposite side walls of the mounting groove are different structures.
  • a middle portion of a side wall of the mounting groove has a relief structure, and a width of the mounting groove above the relief structure is greater than a width of the bottom of the mounting groove.
  • a fixing frame is further included, and the fixing frame is disposed on the top of the buckle body.
  • the end of the fixing frame has a protruding bone position, and the number of the protruding bone positions is four, and two sides of the fixing frame are respectively provided with two protruding bone positions, and each side protrudes A relatively concave groove-like structure is formed between the bone sites.
  • An unmanned aerial vehicle includes a main body portion, a tripod assembly, a fixed buckle and a sensor, wherein the tripod is disposed at a bottom of the main body portion for supporting the main body portion, and the fixed buckle is disposed In the tripod assembly, the sensor card is placed in the fixed buckle, and the fixed buckle is a fixed buckle as described above.
  • first stand and the second stand each include a support bar assembly, a beam, a connecting part assembly and a supporting leg, and the cross beam is disposed between the support bar assemblies and performs the support bar Limiting, an end of the support rod assembly is coupled to the connection assembly, and the support leg is coupled to the connection assembly.
  • the support rod assembly includes a first support rod and a second support rod, and the first support rod has a receiving space therein, and the fixed buckle is received in the receiving space inside the first support rod.
  • the middle portion of the first support rod has a limiting hole, and the limiting hole is disposed in cooperation with the limiting portion of the fixed buckle, and the limiting portion is stuck in the limiting hole.
  • the senor is a compass sensor.
  • the unmanned aerial vehicle provided by the embodiment of the present invention is provided with a fixing buckle for mounting the sensor, and the fixing buckle has a limiting protrusion and the limiting hole cooperate with the locking hole, so that the A snap card is placed in the first support bar.
  • No special jig is required for positioning during the installation process, and the positioning is more precise.
  • the design of the fixed buckle can greatly simplify the assembly process, facilitate replacement, reduce the difficulty of user maintenance, and increase the adaptability of the aircraft in harsh environments.
  • FIG. 1 is a perspective view of a drone according to an embodiment of the present invention.
  • Figure 2 is a perspective view showing a portion of the structure of the drone of Figure 1.
  • Figure 3 is a cross-sectional view of a portion of the structure of the drone of Figure 2 taken along line III-III.
  • Figure 4 is an exploded view of a portion of the structure of the drone of Figure 2;
  • Figure 5 is a partial enlarged view of a portion of the mechanism of the drone of Figure 4.
  • a component when referred to as being "fixed” to another component, it can be directly on the other component or the component can be present.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a group A piece is considered to be “set to” another component, which can be placed directly on another component or possibly with a centered component.
  • the compass sensor assembly method of the drone is mostly fixed with or without a magnetic screw. Since the installation position needs to be away from the magnetic field interference position, it is installed at the foot of the unmanned aerial vehicle.
  • the installation of the compass sensor requires precise determination of the positions of the X, Y, and Z axes, and the installation does not allow for large angular errors, so precise positioning and mounting angle during installation are particularly important. Fixture positioning is required for the assembly with adhesive fixing.
  • the glue will damage the tripod when it is damaged, causing greater damage.
  • gluing may fail in harsh environments, causing the compass to shift, which may cause a drone bomber accident. Therefore, the inventors made major improvements in the way the compass sensor was fixed.
  • the fixing buckle for fixing the sensor provided by the embodiment of the invention adopts elastic boss positioning.
  • FIG. 1 is a schematic structural view of a drone provided by the present invention.
  • the drone 100 includes a main body portion 10, a tripod assembly 30, a fixed buckle 50, and a sensor 70.
  • the tripod 30 is disposed at the bottom of the main body portion 10, the fixing buckle 50 is disposed in the tripod assembly 30, and the sensor 70 is fixed to the tripod assembly 30 by the fixing buckle 50.
  • the tripod assembly 30 includes a first stand 31 and a second stand 32 .
  • the tripod assembly 30 can also include other numbers of tripods, which are not limited by the present invention.
  • the structures of the first stand 31 and the second stand 32 are substantially the same. Therefore, the structure of the first stand 31 is specifically described below by taking the first stand 31 as an example. description of.
  • the first stand 31 includes a support bar assembly 311, a cross member 312, a connector assembly 313, and a support leg 314.
  • the beam 312 is disposed between the support rod assemblies 311, and the end of the support rod assembly 311 is connected to the connection assembly 313, and the support legs 314 Connected to the connector assembly 313.
  • the support rod assembly 311 includes a first support rod 3111 and the second support rod 3112. Of course, in other embodiments, the support rod assembly 311 may further include other numbers of support rods. Make a limit.
  • the first support rod 3111 has a receiving space therein, and the first support rod 3111 has a limiting hole 3113 and a limiting slot 3114.
  • the limiting hole 3113 is disposed in the middle of the first supporting rod 3111.
  • the limiting hole 3113 is a circular through hole, and the number is two, and the two of the limiting positions
  • the holes 3113 are oppositely disposed.
  • the limiting hole 3113 can also be other numbers, which is not limited in the present invention.
  • the limiting slot 3114 is disposed at an end of the first supporting rod 3111 facing the supporting leg 314. In the embodiment, the limiting slot 3114 extends from the end surface of the first supporting rod 3111 to the first A support plate 3111 faces the end surface of the support leg 314.
  • the cross member 312 is disposed between the first support rod 3111 and the second support rod 3112 for limiting and fixing the first support rod 3111 and the second support rod 3112.
  • the cross member 312 The strength of the first stand 31 can be increased, and the first stand 31 can be prevented from being subjected to an external force to cause an unexpected twist/swing.
  • the beam 312 includes a connecting beam 3121 and a sleeve 3122 respectively disposed at two ends of the connecting beam 3121.
  • the two ends of the connecting beam 3121 are respectively connected to the two sleeves 3122.
  • the connecting beam 3121 is in a parallel state with the horizontal plane.
  • the number of the sleeves 3122 is two, and the two sleeves 3122 are tightly sleeved respectively in the middle of the corresponding first support rods 3111 and the second support rods 3112. Specifically, the sleeve 3122 corresponding to the first support rod 3111 is sleeved at the limiting hole 3113 of the first support rod 3111 and covers the limiting hole 3113. It can be understood that the two sleeves 3122 are respectively disposed at the same height of the first support rod 3111 and the second support rod 3112. In other words, the angle between the connecting beam 3121 and the first support rod 3111 and the second support rod 3112 is the same.
  • the connecting portion assembly 313 is coupled to the support bar assembly 311 and the support leg 314, respectively, to connect the support bar assembly 311 and the support leg 314.
  • the connecting portion assembly 313 includes a first connecting portion 3131 and a second connecting portion 3132.
  • the first connecting portion 3131 is connected to the first supporting rod 3111
  • the second connecting portion 3132 is connected to the second supporting rod 3112.
  • the first connecting portion 3131 includes a support rod sleeve 3133 and a support foot sleeve 3134.
  • the support rod sleeve 3133 is fixedly disposed at a middle portion of the support foot sleeve 3134, and the two are not connected to each other.
  • the support rod sleeve 3133 is sleeved at the end of the first support rod 3111 and connected to the end of the first support rod 3111.
  • the bottom of the support sleeve 3133 has a limiting protrusion 3135.
  • the limiting protrusion 3135 is disposed in cooperation with the limiting slot 3114 and is locked in the limiting slot 3114, thereby realizing the support rod sleeve.
  • the relative position of the first support rod 3111 is defined by 3133.
  • the limiting protrusions 3135 are substantially strip-shaped.
  • the support leg sleeve 3134 is sleeved on the support leg 314 and fixedly disposed with the support leg 314. Thereby, the first support rod 3111 and the support leg 314 are connected together.
  • the second connecting portion 3132 is connected to the second support rod 3112 and the support leg 314, respectively.
  • the structure of the second connecting portion 3132 is substantially similar to that of the first connecting portion 3131, and details are not described herein.
  • the support leg 314 is disposed at a bottom end of the first stand 31 for supporting the drone 100 and increasing the stability of the support of the first stand 31.
  • the second stand 32 is used in conjunction with the first stand 31.
  • the structure of the second leg frame 32 is similar to that of the first leg frame 31, except that the orientation of the second leg frame 32 is different with respect to the main body portion 10, and details are not described herein.
  • the fixing buckle 50 is received in the receiving space of the first support rod 3111 .
  • the fixing buckle 50 includes a buckle body 51 and a fixing frame 52 , and the fixing frame 52 is disposed on the top of the buckle body 51 .
  • the fixing buckle 50 is made of a hard plastic material, which does not interfere with the sensor 70, so that the stability of the operation of the sensor 70 can be ensured.
  • the buckle body 51 is matched with the receiving space of the first support rod 3111 , and includes a limiting portion 511 and a receiving groove 512 .
  • the number of the limiting portions 511 is two, and the limiting portion 511 is a limiting protrusion. Further, the limiting protrusion is a cylindrical shape. Of course, the limiting portion 511 can also be other shapes and other quantities, which are not limited by the present invention.
  • the two limiting portions 511 are disposed on two sides of the buckle body 51 .
  • the two limiting portions 511 are respectively disposed corresponding to the two limiting holes 3113, and the two limiting portions 511 are respectively respectively inserted into the corresponding two limiting holes. Within 3113.
  • the two limiting portions 511 are normally located on both sides of the buckle body 51, and are also elastically received in the buckle body 51 when needed.
  • the buckle body 51 has spaced apart sheet-like extensions 513 , and the limiting portions 511 are respectively located on the extensions 513 .
  • the extending portion 513 has elasticity, and the extending portion 513 can be relatively close to or away from each other to adjust the distance between the limiting portions 511. The assembly and disassembly between the fixed buckle 50 and the tripod assembly 30 are facilitated.
  • the mounting groove 512 is disposed inside the buckle body 51.
  • the opposite sidewall structures of the mounting groove 512 are different, that is, a foolproof structure is formed to prevent the sensor 70 from being inserted backward.
  • the middle portion of one side wall of the mounting groove 512 has a relief structure 5121.
  • the relief structure 5121 is a groove formed on a sidewall surface of the mounting groove 512.
  • the fixing frame 52 is substantially strip-shaped and extends from the top of the buckle body 51 by a predetermined distance.
  • the end of the fixing frame 52 is formed with a protruding bone position 521 at intervals to facilitate fixing the sensor 40. Cable.
  • the protruding bone positions 521 are four, and the two protruding bone positions 521 are disposed on two sides of the fixing frame 521, and the convex bone positions 521 on each side form a relatively concave shape. Grooved structure.
  • the sensor 70 is stuck in the mounting groove 512 and is disposed in cooperation with the mounting groove 512.
  • the sensor 70 includes a substrate 71, an electronic sensing element 72, and an extraction lead 73.
  • the electronic sensing element 72 is disposed on one surface of the substrate 71, and one end of the wire 73 is connected to the substrate 71.
  • the sensor 70 is a compass that can use the earth's magnetic field to discern the direction and convert it into an analog signal to be transmitted to the controller of the drone 100.
  • the substrate 71 may be a printed circuit board, and a printed circuit is disposed on the surface thereof to electrically connect the electronic sensing element 72.
  • the number of the electronic sensing elements 72 is plural, and the plurality of electronic sensing elements are disposed on the same side of the substrate 71.
  • the lead wire 73 is disposed on the fixing frame 52.
  • the lead wire 73 can be wound on the fixing frame 52; of course, the lead wire 73 can also be fixedly disposed on the fixing frame 52 by other connecting and fixing components, for example, by taking out the wire.
  • a lead 72 is tied between the protruding bone positions 521.
  • the lead wire 73 is electrically connected to the substrate 71, and transmits information detected by the sensor 70 to the drone 100 Controller.
  • the sensor 70 has a side wall with the electronic component 72 facing the mounting slot 512 with a relief structure 5121. Because the inner wall of the avoidance structure 5121 is located on one side of the fitting groove 512, the sensor 70 can only be inserted into the fitting groove 5121 in a specific manner, so the fitting groove 512 also has a foolproof function, if The reverse assembly does not allow the sensor 70 to fit within the mounting slot 512.
  • the unmanned aerial vehicle provided by the embodiment of the present invention is provided with a fixing buckle for mounting the sensor, and the fixing buckle has a limiting protrusion and the limiting hole cooperate with the locking hole, so that the A snap card is placed in the first support bar.
  • No special jig is required for positioning during the installation process, and the positioning is more precise.
  • the design of the fixed buckle can greatly simplify the assembly process, facilitate replacement, reduce the difficulty of user maintenance, and increase the adaptability of the aircraft in harsh environments.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Measurement And Recording Of Electrical Phenomena And Electrical Characteristics Of The Living Body (AREA)

Abstract

一种固定卡扣(50) 和具有固定卡扣（50）的无人机（100），固定卡扣（50）用于将传感器(70)固定于支撑件上，其包括卡扣主体(51)和设置于卡扣主体(51)表面的限位部(511)，卡扣主体(51)具有装配槽(512)，装配槽(512)用于收容并定位传感器（70），限位部(511)能够与支撑件相连接进而将传感器（70）相对于支撑件固定设置。固定卡扣（50）的设计可以极大简化装配工艺，更换方便，降低了用户维护难度，增加了飞机在恶劣环境的适应能力。

Description

固定卡扣和具有该固定卡扣的无人机 技术领域
本发明涉及一种固定卡扣和具有该固定卡扣的无人机。
背景技术
无人机是通过无线电遥控设备进行控制的。目前的感测元件，比如指南针传感器固定方式多采用胶粘固定或者不带磁螺丝，并且在装配时需要治具进行辅助装配定位，装配较为复杂。
此外，感测元件如果损坏，客户很难自己进行修理，在胶粘损坏的过程中通常会连接损坏脚架，造成更大的损失。同时，胶粘在恶劣环境中很可能会失效，从而造成感测元件的位移，比如指南针传感器，这种情况会严重影响无人机的飞行控制，容易造成无人机炸机。
发明内容
有鉴于此，有必要提供一种装配简单、定位精确、无附带损伤以及稳定可靠的固定卡扣。
一种固定卡扣，用于将传感器固定于支撑件上，包括卡扣主体和设置于所述卡扣主体表面的限位部，所述卡扣主体具有装配槽，所述装配槽用于收容并定位所述传感器，所述限位部能够与所述支撑件相连接进而将所述传感器相对于所述支撑件固定设置。
进一步地，所述限位部为限位凸起，所述限位凸起在正常状态突出于所述卡扣主体表面，在按压状态能够向所述卡扣主体方向收缩并收容于所述卡扣主体内。
进一步地，所述限位部圆柱形限位凸起。
进一步地，所述限位部的个数为两个。
进一步地，所述卡扣主体具有间隔设置的片状延伸部，所述限位部分别设置于所述延伸部，且所述延伸部具有弹性，所述延伸部可以相互靠近或远离。
进一步地，所述装配槽与所述垂直于所述卡扣主体顶部的方向之间的夹 角呈预定角度，且不为零。
进一步地，所述装配槽两个相对的侧壁为相异结构。
进一步地，所述装配槽的一侧壁中部具有避让结构，所述避让结构上方的装配槽宽度大于所述装配槽底部的宽度。
进一步地，还包括固定架，所述固定架设置于所述卡扣主体顶部。
进一步地，所述固定架的末端具有突出骨位，所述突出骨位的个数为四个，所述固定架的两侧各设置有两个所述凸出骨位，每一侧的突出骨位之间形成相对凹陷的槽状结构。
一种无人机，所述无人机包括主体部、脚架组件、固定卡扣和传感器，所述脚架设置于所述主体部底部用于支撑所述主体部，所述固定卡扣设置于所述脚架组件内，所述传感器卡置于所述固定卡扣内，所述固定卡扣为如上所述的固定卡扣。
进一步地，所述第一脚架和所述第二脚架均包括支撑杆组件、横梁、连接部组件和支撑脚，所述横梁设置于所述支撑杆组件之间并对所述支撑杆进行限位，所述支撑杆组件的末端与所述连接部组件连接，所述支撑脚与所述连接部组件连接。
进一步地，所述支撑杆组件包括第一支撑杆和第二支撑杆，所述第一支撑杆内部具有收容空间，所述固定卡扣收容于所述第一支撑杆内部的收容空间内。
进一步地，所述第一支撑杆中部具有限位孔，所述限位孔与所述固定卡扣的限位部配合设置，所述限位部卡置于所述限位孔内。
进一步地，所述传感器为指南针传感器。
本发明的实施方式提供的无人机设有用于安装所述传感器的固定卡扣，所述固定卡扣具有的限位凸起与所述限位孔配合卡置，从而很方便的将所述卡扣卡置于所述第一支撑杆内。在安装过程中不需要专用治具进行定位，定位更加精准。此外，固定卡扣的设计可以极大简化装配工艺，更换方便，降低了用户维护难度，增加了飞机在恶劣环境的适应能力。
附图说明
图1是本发明实施方式提供的无人机的立体图。
图2是图1中的无人机的部分结构立体图。
图3是图2中的无人机的部分结构沿III-III的剖视图。
图4是图2中的无人机的部分结构的分解图。
图5是图4的无人机的部分机构的局部放大图。
主要元件符号说明
无人机                       100
主体部                       10
脚架组件                     30
第一脚架                     31
支撑杆组件                   311
第一支撑杆                   3111
第二支撑杆                   3112
横梁                         312
连接横梁                     3121
套筒                         3122
连接部组件                   313
第一连接部                   3131
第二连接部                   3132
支撑杆套筒                   3133
支撑脚套筒                   3134
支撑脚                         314
第二脚架                       32
固定卡扣                       50
卡扣主体                       51
限位部                         511
装配槽                         512
延伸部                         513
避让结构                       5121
固定架                         52
凸出骨位                       521
传感器                         70
基板                           71
电子感应元件                   72
引出导线                       73
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，都属于本发明保护的范围。
需要说明的是，当组件被称为“固定于”另一个组件，它可以直接在另一个组件上或者也可以存在居中的组件。当一个组件被认为是“连接”另一个组件，它可以是直接连接到另一个组件或者可能同时存在居中组件。当一个组 件被认为是“设置于”另一个组件，它可以是直接设置在另一个组件上或者可能同时存在居中组件。
除非另有定义，本文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。本文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，不是旨在于限制本发明。本文所使用的术语“及/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。
在实现本发明的过程中，发明人发现了如下问题：
目前无人机的指南针传感器装配方式多为胶粘或者不带磁性的螺丝固定，因安装位置需要远离磁场干扰的位置，所以其多安装于无人机脚架处。指南针传感器安装需要精确确定X、Y、Z三个轴的位置，且安装不允许有较大的角度误差，因此安装时精确定位和安装角度尤为重要。采用胶粘固定装配时需要治具辅助定位。同时胶粘在损坏时会连带损坏脚架，造成更大的损失。此外，在恶劣的环境中胶粘可能会失效，造成指南针移位，可能会造成无人机炸机事故。因此发明人在指南针传感器的固定方式上做了重点改进。
本发明实施例提供的用于固定传感器的固定卡扣采用弹性凸台定位。下面，通过具体实施例，对固定卡扣以及固定卡扣与无人机的装配
请同时参阅图1和图4，图1是本发明提供的无人机的结构示意图。所述无人机100包括主体部10、脚架组件30、固定卡扣50和传感器70。所述脚架30设置于所述主体部10底部，所述固定卡扣50设置于所述脚架组件30内，所述传感器70通过所述固定卡扣50固定于所述脚架组件30。
请参阅图2，在本实施方式中，所述脚架组件30包括第一脚架31和第二脚架32。当然，在其他实施方式中，所述脚架组件30还可以包括其他数量的脚架，本发明对此不做限定。此外，本实施方式中，所述第一脚架31和所述第二脚架32的结构大致相同，因此下面以第一脚架31为例，对所述第一脚架31的结构进行具体的描述。
请结合参阅图3和图4，所述第一脚架31包括支撑杆组件311，横梁312、连接部组件313和支撑脚314。所述横梁312设置于所述支撑杆组件311之间，所述支撑杆组件311的末端与所述连接部组件313连接，所述支撑脚314 与所述连接部组件313连接。
所述支撑杆组件311包括第一支撑杆3111和所述第二支撑杆3112，当然，在其他的实施方式中，所述支撑杆组件311还可以包括其他数量的支撑杆，本发明对此不做限定。
所述第一支撑杆3111内部具有收容空间，所述第一支撑杆3111的具有限位孔3113和限位槽3114。其中，所述限位孔3113设置于所述第一支撑杆3111的中部，在本实施方式中，所述限位孔3113为圆形通孔，且数量为两个，两个所述限位孔3113相对设置。当然，所述限位孔3113还可以为其他个数，本发明对此不做限定。所述限位槽3114设置于所述第一支撑杆3111朝向所述支撑脚314的末端，本实施方式中，所述限位槽3114自所述第一支撑杆3111的端面贯穿至所述第一支撑板3111朝向所述支撑脚314的端面。
所述横梁312设置于所述第一支撑杆3111和所述第二支撑杆3112之间，用于所述第一支撑杆3111和所述第二支撑杆3112进行限位固定，所述横梁312能够增加所述第一脚架31的强度，并能够防止所述第一脚架31受到外力而产生非预期的扭动/摆动。具体地，所述横梁312包括连接横梁3121和分别设置于所述连接横梁3121两端的套筒3122。
所述连接横梁3121两端分别与所述两个套筒3122连接。在所述无人机100处于正常飞行状态时，所述连接横梁3121与水平面处于平行状态。
其中所述套筒3122的个数为两个，所述两个套筒3122分别紧密套设于对应的所述第一支撑杆3111和所述第二支撑杆3112中部。具体地，与所述第一支撑杆3111相对应的套筒3122套设于所述第一支撑杆3111的限位孔3113处，且覆盖所述限位孔3113。可以理解，所述两个套筒3122套分别设于所述第一支撑杆3111和所述第二支撑杆3112的相同高度处。换句话说，所述连接横梁3121与所述第一支撑杆3111和所述第二支撑杆3112之间的夹角相同。
所述连接部组件313分别与所述支撑杆组件311和支撑脚314连接，从而将所述支撑杆组件311和所述支撑脚314连接。所述连接部组件313包括第一连接部3131和第二连接部3132。其中所述第一连接部3131对应与所述第一支撑杆3111连接，所述第二连接部3132对应与所述第二支撑杆3112连接。
所述第一连接部3131包括支撑杆套筒3133和支撑脚套筒3134，所述支撑杆套筒3133固定设置于所述支撑脚套筒3134的中部，且所述二者内部互不连通。
所述支撑杆套筒3133套设于所述第一支撑杆3111末端，并与所述第一支撑杆3111末端连接。所述支撑套筒3133底部具有限位凸起3135，所述限位凸起3135与所述限位槽3114配合设置且卡置于所述限位槽3114内，从而实现所述支撑杆套筒3133与所述第一支撑杆3111的相对位置进行限定。本实施方式中，所述限位凸起3135大致呈条状。
所述支撑脚套筒3134套设于所述支撑脚314上并与所述支撑脚314固定设置。从而实现所述第一支撑杆3111和所述支撑脚314连接在一起。
所述第二连接部3132分别连接所述第二支撑杆3112和所述支撑脚314。在本实施方式中，所述第二连接部3132与所述第一连接部3131的结构大致类似，在此不再进行赘述。
所述支撑脚314设置于所述第一脚架31的底端，用于对所述无人机100进行支撑，并增加所述第一脚架31支撑的稳固性。
所述第二脚架32与所述第一脚架31配合使用。在本实施方式中，所述第二脚架32与所述第一脚架31的结构类似，只是相对于所述主体部10的朝向不同，在此不再进行赘述。
请参阅图5，所述固定卡扣50收容于所述第一支撑杆3111的收容空间内。所述固定卡扣50包括卡扣主体51和固定架52，所述固定架52设置于所述卡扣主体51顶部。在本实施方式中，所述固定卡扣50为硬质塑料材质，其不会对所述传感器70产生干扰，因而可以保证所述传感器70工作的稳定性。
所述卡扣主体51与所述第一支撑杆3111的收容空间匹配设置，其包括限位部511和收容槽512。
在本实施方式中，所述限位部511的个数为两个，且所述限位部511为限位凸起。进一步地，所述限位凸起为类圆柱形。当然，所述限位部511还可以为其他形状和其他数量，本发明对此不做限定。所述两个限位部511设置于所述卡扣主体51的两侧。所述两个限位部511与所述两个限位孔3113分别对应设置，所述两个限位部511分别卡置于各自对应的所述两个限位孔 3113内。为了方便装配，所述两个限位部511正常状态位于所述卡扣主体51的两侧，在需要的时候也可弹性的收容于所述卡扣主体51内。
图示的实施方式中，所述卡扣主体51的具有间隔设置的片状延伸部513，所述限位部511分别位于所述延伸部513上。本实施方式中，所述延伸部513具有弹性，所述延伸部513可以相对靠近或者远离，以调整所述限位部511之间的距离。以便于所述固定卡扣50与所述脚架组件30之间的组装及拆卸。
所述装配槽512设置于所述卡扣主体51内部。所述装配槽512相对的两个侧壁结构相异，即形成防呆结构，防止传感器70插反。具体地，所述装配槽512的一侧壁的中部具有避让结构5121，本实施方式中，所述避让结构5121为形成于所述装配槽512一侧壁表面的凹槽。
所述固定架52大致呈条状，其自所述卡扣主体51的顶部延伸预定距离，所述固定架52的末端形成有间隔设置有凸出骨位521，以便于固定所述传感器40的线缆。具体地，所述凸出骨位521为四个，所述固定架521的两侧各设置两个所述凸出骨位521，每一侧所述凸出骨位521之间形成相对凹陷的槽状结构。
请再参阅图5，所述传感器70卡置于所述装配槽512内，且其与所述装配槽512配合设置。所述传感器70包括基板71、电子感应元件72和引出导线73。所述电子感应元件72设置于所述基板71的一侧表面，所述导线73一端与所述基板71连接。本实施方式中，所述传感器70为指南针，其可以利用地球磁场辨别方向，并将其转换为模拟信号传送至所述无人机100的控制器。
在本实施方式中，所述基板71可以为印刷电路板，且其表面设置有印制电路从而电连接电子感应元件72。
所述电子感应元件72的个数为多个，所述多个电子感应元件设置于所述基板71的同一侧。所述引出导线73设置于所述固定架52上。其中，所述引出导线73可以缠绕设置于所述固定架52上；当然，所述引出导线73也可以通过其他连接固定部件固定设置于所述固定架52上，例如通过扎线将所述引出导线72绑缚于所述凸出骨位521之间。所述引出导线73与所述基板71电连接，并且将所述传感器70检测到的信息传送至所述无人机100 的控制器。
在所述传感器70的具体装配过程中，所述传感器70具有电子元件72的一侧朝向所述装配槽512具有避让结构5121的侧壁。因为避让结构5121的位于所述装配槽512的一侧内壁，使得所述传感器70只能以特定的方式插入所述装配槽5121，因此所述装配槽512也具有防呆功能，如果将所述反向装配则不能将所述传感器70装配与所述装配槽512内。
本发明的实施方式提供的无人机设有用于安装所述传感器的固定卡扣，所述固定卡扣具有的限位凸起与所述限位孔配合卡置，从而很方便的将所述卡扣卡置于所述第一支撑杆内。在安装过程中不需要专用治具进行定位，定位更加精准。此外，固定卡扣的设计可以极大简化装配工艺，更换方便，降低了用户维护难度，增加了飞机在恶劣环境的适应能力。
另外，本技术领域的普通技术人员应当认识到，以上的实施方式仅是用来说明本发明，而并非用作为对本发明的限定，只要在本发明的实质精神范围之内，对以上实施例所作的适当改变和变化都落在本发明要求保护的范围之内。

Claims (15)

  1. 一种固定卡扣，用于将传感器固定于支撑件上，其特征在于：包括卡扣主体和设置于所述卡扣主体表面的限位部，所述卡扣主体具有装配槽，所述装配槽用于收容并定位所述传感器，所述限位部能够与所述支撑件相连接进而将所述传感器相对于所述支撑件固定设置。
  2. 如权利要求1所述的固定卡扣，其特征在于：所述限位部为限位凸起，所述限位凸起在正常状态突出于所述卡扣主体表面，在按压状态能够向所述卡扣主体方向收缩并收容于所述卡扣主体内。
  3. 如权利要求2所述的固定卡扣，其特征在于：所述限位部圆柱形限位凸起。
  4. 如权利要求3所述的固定卡扣，其特征在于：所述限位部的个数为两个。
  5. 如权利要求4所述的固定卡扣，其特征在于：所述卡扣主体具有间隔设置的片状延伸部，所述限位部分别设置于所述延伸部，且所述延伸部具有弹性，所述延伸部可以相互靠近或远离。
  6. 如权利要求1所述的固定卡扣，其特征在于：所述装配槽与所述垂直于所述卡扣主体顶部的方向之间的夹角呈预定角度，且不为零。
  7. 如权利要求6所述的固定卡扣，其特征在于：所述装配槽两个相对的侧壁为相异结构。
  8. 如权利要求7所述的固定卡扣，其特征在于：所述装配槽的一侧壁中部具有避让结构，所述避让结构上方的装配槽宽度大于所述装配槽底部的宽度。
  9. 如权利要求1所述的固定卡扣，其特征在于：还包括固定架，所述固定架设置于所述卡扣主体顶部。
  10. 如权利要求9所述的固定卡扣，其特征在于：所述固定架的末端具有突出骨位，所述突出骨位的个数为四个，所述固定架的两侧各设置有两个所述凸出骨位，每一侧的突出骨位之间形成相对凹陷的槽状结构。
  11. 一种无人机，其特征在于：所述无人机包括主体部、脚架组件、固 定卡扣和传感器，所述脚架设置于所述主体部底部用于支撑所述主体部，所述固定卡扣设置于所述脚架组件内，所述传感器卡置于所述固定卡扣内，所述固定卡扣为权利要求1-10任意一项所述的固定卡扣。
  12. 如权利要求11所述的无人机，其特征在于：所述第一脚架和所述第二脚架均包括支撑杆组件、横梁、连接部组件和支撑脚，所述横梁设置于所述支撑杆组件之间并对所述支撑杆进行限位，所述支撑杆组件的末端与所述连接部组件连接，所述支撑脚与所述连接部组件连接。
  13. 如权利要求12所述的无人机，其特征在于：所述支撑杆组件包括第一支撑杆和第二支撑杆，所述第一支撑杆内部具有收容空间，所述固定卡扣收容于所述第一支撑杆内部的收容空间内。
  14. 如权利要求13所述的无人机，其特征在于：所述第一支撑杆中部具有限位孔，所述限位孔与所述固定卡扣的限位部配合设置，所述限位部卡置于所述限位孔内。
  15. 如权利要求11所述的无人机，其特征在于：所述传感器为指南针传感器。
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