WO2016065512A1 - 航模机及其电调组装结构 - Google Patents

航模机及其电调组装结构 Download PDF

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Publication number
WO2016065512A1
WO2016065512A1 PCT/CN2014/089577 CN2014089577W WO2016065512A1 WO 2016065512 A1 WO2016065512 A1 WO 2016065512A1 CN 2014089577 W CN2014089577 W CN 2014089577W WO 2016065512 A1 WO2016065512 A1 WO 2016065512A1
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WIPO (PCT)
Prior art keywords
fixing member
esc
positioning
positioning plate
assembly structure
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PCT/CN2014/089577
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English (en)
French (fr)
Inventor
陈瑞
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深圳市尚腾影科技有限公司
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Application filed by 深圳市尚腾影科技有限公司 filed Critical 深圳市尚腾影科技有限公司
Priority to PCT/CN2014/089577 priority Critical patent/WO2016065512A1/zh
Priority to CN201480001180.3A priority patent/CN106458321A/zh
Publication of WO2016065512A1 publication Critical patent/WO2016065512A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • the invention relates to a nautical model structure, in particular to a multi-rotor aircraft model machine and an electric adjustment assembly structure thereof.
  • the present invention provides a model aircraft and an ESC assembly structure thereof for externally placing an electric adjustment device on a body of a model aircraft to solve the above technical problems.
  • Embodiments of the present invention provide an ESC assembly structure for externally mounted on a motor of a model aircraft.
  • the ESC assembly structure includes: a positioning plate fixedly connected to the motor; a fixing member fixedly connected to the motor through the positioning plate; an ESC main member received in the fixing member; and a heat sink fixed on the The bottom of the ESC main component; the motor external wiring and the ESC external wiring are fixed at the bottom of the heat sink, one end of the external wiring of the motor is connected to the motor, and the other end is connected to the electric through the external wiring Adjust the main parts to electrical connection.
  • Another embodiment of the present invention provides a model aircraft, the model machine including at least one pair of rotors, A motor system and the above-described ESC assembly structure.
  • the motor system is disposed below the rotor, and the ESC assembly structure is disposed below or adjacent to the motor system.
  • the aircraft model machine and the ESC assembly structure thereof of the invention can adopt the above structure, so that the electric adjustment device can be directly externally mounted on the motor system, which is convenient for assembly and wiring, convenient for disassembly and assembly of parts during production and maintenance, and avoiding large area. Disassembly and assembly damage to the hardware, and can improve the cooling effect, improve the drone's working efficiency and ESC life.
  • FIG. 1 is an exploded view of an electrical adjustment assembly structure of a model aircraft according to an embodiment of the present invention
  • FIG. 2 is an assembled view of a first perspective view of an electrical adjustment assembly structure of a model aircraft according to an embodiment of the present invention
  • FIG. 3 is an assembled view of a second perspective view of an electrical adjustment assembly structure of a model aircraft according to an embodiment of the present invention
  • FIG. 4 is an assembled view of a third perspective view of an electrical adjustment assembly structure of a model aircraft according to an embodiment of the present invention.
  • FIG. 1 is an exploded view of an electrical adjustment assembly structure 10 of a model aircraft according to an embodiment of the present invention.
  • the aircraft model machine is a multi-rotor aircraft model machine.
  • the aircraft model machine includes at least a plurality of rotors 20, a plurality of motor systems 30 corresponding to the rotors 20, and a plurality of the ESC assembly structures 10, wherein the plurality of the ESC assembly structures 10 correspond to each other. It is provided in the motor system 30.
  • the motor system 30 is disposed below the rotor 20 for driving the rotor 20 to rotate.
  • the ESC assembly structure 10 is disposed below or adjacent to the motor system 30 for providing a control voltage to the motor system 30 to control the speed of the motor system 30.
  • each of the motor systems 30 includes a motor.
  • the bottom of the motor is provided with a plurality of threaded interfaces (not shown). In this embodiment, the number of the threaded interfaces is four.
  • the ESC assembly structure 10 includes a positioning plate 11, a fixing member 12, an ESC main member 13, a heat sink 14, a motor outer wiring 15, and an ESC external wiring 16.
  • the positioning plate 11 is provided with four flange-shaped positioning portions 111. Each of the positioning portions 111 defines an outer positioning hole 112 for mounting on the fixing member 112. It can be understood that the positioning plate 11 can also be circular, and it is not necessary to open the flange-shaped positioning portion 111 as long as the outer positioning hole 112 is opened.
  • a through hole 113 is defined in the middle of the positioning plate 11, and four inner positioning holes 114 are defined in the periphery of the through hole 113, and the inner positioning holes 114 correspond to the threaded interfaces on the motor.
  • the positioning plate 11 is fixed to the bottom of the motor system 30 by means of four screws passing through the inner positioning holes 114 to be screwed to the threaded interface on the motor.
  • the positioning plate 11 is a carbon fiber board, the positioning portion 111 is in the shape of a fan, and the inner positioning hole 114 is elliptical, but not limited thereto, the inner positioning hole 114 may be circular. .
  • the positioning plate 11 is not limited to being positioned to the bottom of the motor, and may be positioned at a side or top position of the motor according to specific needs.
  • the fixing member 12 is substantially in the form of a hollow ring, and a sleeve 121 is formed on the outer side wall thereof, and the sleeve 121 is used for inserting with a carbon fiber tube (not labeled) to pass through the carbon fiber tube and other models of the aircraft model machine.
  • the parts are connected.
  • the inner diameter of the fixing member 12 is smaller than the maximum outer diameter of the positioning plate 11.
  • the material of the fixing member 12 is aluminum. It can be understood that in other embodiments, the fixing member 12 can be other materials such as plastics, alloys, and the like.
  • the fixing member 12 further includes an upper surface 123 facing the motor and four screw holes corresponding to the outer positioning holes 112 on the positioning plate 11.
  • the lower surface 125 faces the heat sink 14.
  • the lower surface 125 is also provided with a plurality of screw holes (not shown) and is formed with at least one notch 127 extending upward along the side wall.
  • the ESC 13 includes an ESC PCB and other electronic components.
  • Four through holes 131 are defined in the edge of the ESC PCB.
  • the heat sink 14 has a rectangular shape, and is provided with four external positioning holes 141 and four internal control deep positioning holes 143.
  • the external positioning hole 141 is disposed at the bottom of the heat sink 14 .
  • the four internal controlled deep positioning holes 143 correspond to the through holes 131 on the ESC PCB.
  • the ESC needs to connect three devices. In addition to connecting the motor system and the power supply, it also needs a signal control line to connect the throttle channel of the receiver (not shown). When obtaining the throttle information of the remote control, Power the servos of the receiver and other channels. Therefore, in the embodiment, the motor outer wiring 15 and the external electrical wiring 16 are respectively three. Specifically, one end of the motor outer wire 15 is connected to the motor, the other end is connected through one wire buckle 151 and one end of the electrical external wire 16 , and the other end of the ESC wire 16 is electrically connected to the ESC PCB.
  • a wiring buckle 151 having four screw holes is used, and the two wires are fixed to the four external positioning holes 141 at the bottom of the heat sink 14.
  • the wire buckle 151 is fixedly connected to the heat sink 14 through the external positioning hole 141 and a screw (not labeled), but is not limited thereto.
  • the wire clip 151 can be integrally formed with the heat sink 14 to eliminate the step of opening the external positioning hole 141.
  • the positioning plate 11 is flatly pressed against the upper surface 123 of the fixing member 12, and is fixed to the fixing member 12 by four screws.
  • the motor is then fixed to the positioning plate 11 by the four inner positioning holes 114 by means of another four screws.
  • the fixing member 12 is fixedly connected.
  • a carbon fiber tube is inserted into the boss 121 of the fixing member 12, and the carbon fiber tube is fastened to the boss 121 with a screw 4.
  • the wiring clip 151 is fixed to the heat sink 14, and the motor outer wiring 15 and the electrical external wiring 16 are inserted into the wiring buckle 151, and are electrically connected to each other in the wiring buckle 151. Then, one end of the motor external wiring 15 is electrically connected to the motor system 30, and the remaining end of the ESC external wiring 16 is electrically connected to the ESC through a notch 127 on the fixing member 12. Thereby completing the assembly.
  • the order of the above assembly is not fixed, and the assembly order can be arbitrarily adjusted according to the preference of the user. For example, it can be adjusted to fix the heat sink 14 to the fixing member 12 after assembling the wiring buckle 151 to the heat sink 14, and finally connect the fixing member 12 with the positioning plate 11 and the motor, and the like.
  • the inner diameter of the fixing member 12 may also be set to be slightly larger than or equal to the outer diameter of the positioning plate 11 such that the positioning plate 11 can be received in the fixing member 12.
  • the edge of the upper surface 123 of the fixing member 12 has a plurality of flanges extending radially inward. Group When the loading plate 11 is received in the fixing member 12 and rotated in a certain direction, the positioning portion 111 of the positioning plate 11 is fitted to the flange, and the positioning plate 11 is It is defined in the fixing member 12. Thereby, the positioning of the positioning plate 11 and the fixing member 12 is completed.
  • the positioning plate 11 or the fixing member 12 When it is necessary to separate the positioning plate 11 from the fixing member 12, the positioning plate 11 or the fixing member 12 is rotated in the opposite direction, so that the locking portion of the positioning portion 111 and the flange of the fixing member 12 can be released. Thereby achieving disassembly. In this way, the motor fixed on the positioning plate 11 and the fixing member 12 can be connected by rotation to facilitate disassembly and assembly.
  • the electric adjustment device can be directly externally mounted on the motor system, which not only facilitates assembly and wiring, but also facilitates disassembly and assembly of parts during production and maintenance, avoids damage to hardware by large-area disassembly, and can improve heat dissipation.
  • the effect is to improve the working performance and ESC life of the drone.

Abstract

一种电调组装结构（10），用于外置在航模机的电机（30）上，该电调组装结构（10）包括：定位板（11），与所述电机（30）固定连接；固定件（12），通过所述定位板（11）与所述电机（30）固定连接；电调主件（13），收容在所述固定件（12）内；散热片（14），固定在所述电调主件（13）底部；电机外接线（15）以及电调外接线（16），固定在所述散热片（14）底部，所述电机外接线（15）的一端连接所述电机（30），另一端通过所述电调外接线（16）与所述电调主件（13）电连接。还提供一种具有该电调组装结构的航模机。

Description

航模机及其电调组装结构 技术领域
本发明涉及航模结构，尤其涉及一种多旋翼航模机及其电调组装结构。
背景技术
传统的多旋翼航模(也叫无人机)的马达电调装置通常都是内置在主机体内部。此结构需要将电调线从机体内部沿着旋翼轴连接到旋翼下方的马达上，以使得电调装置能够将控制信号传输到马达上，从而控制马达的转速以及进行换向。
这种结构存在三个弊端：一是不利于散热。由于电调装置在工作状态下发热量大，内置于机体中会导致机体散热困难，从而大大降低无人机的工作效能和电调使用寿命。二是不利于维护。由于电调装置集中内置在机体中，用户在需要维修调试和更换电调时，必须对机体进行全面拆装，不仅操作难度大，而且很容易造成机体和其他硬件的损害。三是走线混乱。电调与其他电子元件集中于机体主体内部，走线混乱，对生产组装和检修的操作要求很高，而且影响美观。
发明内容
有鉴于此，本发明提供一种航模机及其电调组装结构，用于将电调装置外置于航模机的机体，以解决上述技术问题。
本发明实施例提供一种电调组装结构，用于外置在航模机的电机上。该电调组装结构包括：定位板，与所述电机固定连接；固定件，通过所述定位板与所述电机固定连接；电调主件，收容在所述固定件内；散热片，固定在所述电调主件底部；电机外接线以及电调外接线，固定在所述散热片底部，所述电机外接线的一端连接所述电机，另一端通过所述电调外接线与所述电调主件电连接。
本发明另一实施例提供一种航模机，所述航模机至少包括至少一对旋翼、 一电机系统以及上述的电调组装结构。所述电机系统设置在所述旋翼下方，所述电调组装结构设置在所述电机系统下方或临近的周边。
本发明的航模机及其电调组装结构通过采用上述的结构，使得电调装置能够直接外置在电机系统上，不仅组装和接线方便，方便生产和检修过程中的零件拆装，避免大面积拆装对硬件的损害，而且能够提升散热效果，提升无人机工作效能和电调寿命。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。
图1是根据本发明实施例的航模机的电调组装结构的分解图；
图2是本发明实施例提供的航模机的电调组装结构第一视角的组装图；
图3是本发明实施例提供的航模机的电调组装结构第二视角的组装图；
图4是本发明实施例提供的航模机的电调组装结构第三视角的组装图。
具体实施方式
下面结合附图和具体实施方式对本发明的技术方案作进一步更详细的描述。显然，所描述的实施例仅仅是本发明的一部分实施例，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的前提下所获得的所有其他实施例，都应属于本发明保护的范围。
请参阅图1，其是本发明一实施例提供的航模机的电调组装结构10的分解图。本实施例中，所述航模机为多旋翼航模机。所述航模机至少包括多个旋翼20、对应于所述旋翼20设置的多个电机系统30，以及多个所述电调组装结构10，所述多个所述电调组装结构10一一对应于所述电机系统30设置。具体的，所述电机系统30设置在所述旋翼20下方，用于驱动所述旋翼20旋转。所述电调组装结构10设置在所述电机系统30下方或临近的周边，用于提供控制电压给所述电机系统30，以控制所述电机系统30的转速。
本实施例中，每个所述电机系统30包括马达。为了与所述电调组装结构10 固定连接，所述马达底部设置有多个螺纹接口(图未示)。本实施例中，所述螺纹接口的数量是4个。
所述电调组装结构10包括定位板11、固定件12、电调主件13、散热片14、电机外接线15以及电调外接线16。
所述定位板11边缘开设有四个凸缘状定位部111，每个定位部111上开设有一个外定位孔112，以方便安装在所述固定件112上。可以理解，所述定位板11也可以呈圆形，无需开设凸缘状的定位部111，只要开设有所述外定位孔112即可。所述定位板11的中间位置开设有一个通孔113，所述通孔113周边开设有4个内定位孔114，所述内定位孔114与所述马达上的螺纹接口相对应。通过4个螺钉穿过所述内定位孔114与所述马达上的螺纹接口螺接，所述定位板11固定到所述电机系统30的底部。
本实施例中，所述定位板11为碳纤维板，所述定位部111呈扇形，所述内定位孔114呈椭圆形，但均不以此为限，所述内定位孔114可以是圆形。此外，所述定位板11也不限于定位到马达的底部，根据具体需要，可以定位在马达的侧边或者顶部合适位置。
所述固定件12大致呈中空环装，其外侧壁上形成有一个轴套121，所述轴套121用于与一碳纤维管(未标号)插接，以通过该碳纤维管和航模机的其他部件相连接。本实施例中，所述固定件12的内径小于所述定位板11的最大外径。本实施例中，所述固定件12的材料为铝。可以理解，在其他实施例中，所述固定件12可以是其他材料，如塑胶、合金等等。所述固定件12还包括上表面123和下表面125，所述上表面123面向所述马达，并开设有4个螺孔与所述定位板11上的外定位孔112对应。所述下表面125面向散热片14，所述下表面125也开设有多个螺孔(图未示)，并形成有至少一个沿侧壁向上延伸的缺口127。
所述电调主件13包括电调PCB以及其他电子器件。所述电调PCB的边缘开设有4个通孔131。
所述散热片14呈长方形，其开设有4个外接定位孔141和4个内控深定位孔143。所述外接定位孔141设置在所述散热片14的底部。所述4个内控深定位孔143与所述电调PCB上的通孔131对应。当需要将所述散热片14安装到所述电调主件13上时，通过螺钉穿过所述散热片14上的内控深定位孔143以及电调PCB的通孔131，而与所述固定件12的下表面125的螺孔螺接，从而完成 固定。
通常情况下，电调装置需要连接三个设备，除了连接电机系统和电源外，还需要一根信号控制线接接收机(图未示)的油门通道，在获得遥控器油门信息的同时，也给接收机和其它通道的舵机供电。因此，本实施例中，所述电机外接线15和电调外接线16分别为3条。具体的，所述电机外接线15的一端和马达相连，另一端通过一接线卡扣151和电调外接线16的一端相连，而电调外接线16另一端则和电调PCB电连接。更具体的，在电机外接线15和电调外接线16相接的地方，使用具有4个螺孔的接线卡扣151，将两种线固定在散热片14底部的4个外接定位孔141上。本实施例中，所述接线卡扣151通过所述外接定位孔141以及螺钉(未标号)与所述散热片14固定连接，但不限于此。在其他实施例中，所述接线卡扣151可以与所述散热片14一体成型，从而省去了开设外接定位孔141的步骤。
请结合图2至图4，组装时，首先，将定位板11平整压合在所述固定件12的上表面123，并利用4个螺钉固定在所述固定件12上。然后利用另外4个螺钉，通过所述4个内定位孔114将马达与定位板11固定。将电调PCB固定在铝管夹5上，再利用螺钉通过所述散热片14上的内控深定位孔143以及电调PCB的螺孔，从而将所述散热片14以及电调PCB与所述固定件12固定连接。然后，将碳纤维管插入到所述固定件12的轴套121内，并用螺钉4将碳纤维管紧固在所述轴套121上。将接线卡扣151固定在散热片14上，以及将电机外接线15和电调外接线16插入接线卡扣151，并在所述接线卡扣151内相互电连接。然后，将电机外接线15的一端与所述电机系统30电连接，以及将所述电调外接线16的剩余一端通过所述固定件12上的缺口127，与所述电调PCB电连接，从而完成组装。
可以理解，上述组装的顺序并非是固定不变的，根据使用者的偏好，可对组装顺序进行任意调整。例如，可以调整为先将接线卡扣151组装到散热片14上之后，再将散热片14固定在固定件12上，最后再将固定件12与定位板11和马达连接等等。
此外，在一些实施例中，所述固定件12的内径尺寸还可设置稍大于或等于所述定位板11的外径尺寸，使得所述定位板11能够收容在所述固定件12内。此种结构中，所述固定件12的上表面123边缘沿径向向内延伸有多个凸缘。组 装时，将所述定位板11收容在所述固定件12内，并通过某一方向的旋转，使得所述定位板11的定位部111与所述凸缘贴合，所述定位板11被限定在所述固定件12内。由此，完成定位板11与固定件12的定位。当需要将定位板11与固定件12分离是，沿着相反的方向旋转所述定位板11或固定件12，即可解除所述定位部111与所述固定件12的凸缘的锁和，从而实现拆解。通过此种方式，可使得固定在所述定位板11上的马达与所述固定件12通过旋转的方式连接，方便拆装。
通过采用上述的结构，使得电调装置能够直接外置在电机系统上，不仅组装和接线方便，方便生产和检修过程中的零件拆装，避免大面积拆装对硬件的损害，而且能够提升散热效果，提升无人机工作效能和电调寿命。
以上所揭露的仅为本发明实施例中的较佳实施例而已，当然不能以此来限定本发明之权利范围，因此依本发明权利要求所作的等同变化，仍属本发明所涵盖的范围。

Claims (10)

  1. 一种电调组装结构，用于外置在航模机的电机上，该电调组装结构包括：
    定位板，与所述电机固定连接；
    固定件，通过所述定位板与所述电机固定连接；
    电调主件，收容在所述固定件内；
    散热片，固定在所述电调主件底部；
    电机外接线以及电调外接线，固定在所述散热片底部，所述电机外接线的一端连接所述电机，另一端通过所述电调外接线与所述电调主件电连接。
  2. 如权利要求1所述的电调组装结构，其特征在于，所述定位板开设有多个外定位孔以及多个内定位孔，所述定位板通过所述内定位孔与对应的定位元件连接而固定在所述电机上；所述固定件通过所述外定位孔与所述定位板固定连接。
  3. 如权利要求2所述的电调组装结构，其特征在于，所述固定件包括一上表面，所述上表面开设有螺孔与所述定位板的多个外定位孔对应，通过螺钉穿过所述定位板的外定位孔与所述固定件的螺孔螺接，来固定连接所述定位板和所述固定件。
  4. 如权利要求3所述的电调组装结构，其特征在于，所述固定件呈中空环形状，所述定位板的外径大于所述固定件的内径。
  5. 如权利要求1所述的电调组装结构，其特征在于，所述定位板的边缘开设有多个凸缘状定位部，所述定位板收容在所述固定件内，所述固定件包括一上表面，所述上表面的边缘沿径向向内延伸有多个凸缘，当沿第一方向旋转所述定位板时，所述定位板的定位部与所述固定件的凸缘贴合，所述定位板被所述凸缘限定在所述固定件内，当沿第二方向旋转所述定位板时，所述定位板的定位部与所述固定件的凸缘分离。
  6. 如权利要求1所述的电调组装结构，其特征在于，所述固定件的下表面开设有多个螺孔，所述电调主件上开设有多个通孔对应于所述下表面上的螺孔，所述散热片开设有多个内控深定位孔与所述通孔对应，通过螺钉穿过所述内控深定位孔以及电调主件上的通孔而与所述下表面上的螺孔螺接，从而将散热片和电调主件固定在所述固定件上。
  7. 如权利要求1所述的电调组装结构，其特征在于，所述散热片的底部设置有多个外接定位孔，所述电调组装结构还包括一个接线卡扣，所述接线卡扣通过所述外接定位孔以及螺钉与所述散热片固定连接，所述电机外接线和电调外接线通过所述接线卡扣固定在所述散热片底部。
  8. 如权利要求6所述的电调组装结构，其特征在于，所述接线卡扣与所述散热片一体成型。
  9. 如权利要求1所述的电调组装结构，其特征在于，所述固定件的侧壁上形成有向上延伸的缺口，所述电调外接线通过所述缺口与所述电调PCB电连接。
  10. 一种航模机，所述航模机至少包括至少一对旋翼、一电机系统以及如权利要求1～9项任一项所述的电调组装结构，所述电机系统设置在所述旋翼下方，所述电调组装结构设置在所述电机系统下方或临近的周边。
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