WO2017202223A1 - 一种飞行器及其动力装置、动力组件 - Google Patents

一种飞行器及其动力装置、动力组件 Download PDF

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Publication number
WO2017202223A1
WO2017202223A1 PCT/CN2017/084327 CN2017084327W WO2017202223A1 WO 2017202223 A1 WO2017202223 A1 WO 2017202223A1 CN 2017084327 W CN2017084327 W CN 2017084327W WO 2017202223 A1 WO2017202223 A1 WO 2017202223A1
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Prior art keywords
aircraft
driving member
disposed
power unit
mounting plate
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PCT/CN2017/084327
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English (en)
French (fr)
Inventor
胡华智
靳洪胜
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亿航智能设备（广州）有限公司
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Application filed by 亿航智能设备（广州）有限公司 filed Critical 亿航智能设备（广州）有限公司
Publication of WO2017202223A1 publication Critical patent/WO2017202223A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes

Definitions

  • the present application relates to the field of drone technology, and in particular, to an aircraft, a power device thereof, and a power component.
  • the purpose of the present application is to provide an aircraft, a power unit thereof, and a power assembly, which can improve the heat dissipation efficiency of the aircraft and simplify the installation process of the aircraft.
  • a power device comprising: a driving member, a propeller driven by the driving member, and an electric adjusting module connected to the driving member, wherein the electric adjusting module and the propeller are respectively disposed on the driving member end.
  • a mounting plate is disposed between the ESC module and the driving component, the driving component is fixed on the mounting board side, and a mounting area is disposed on a lower side of the mounting board, and the ESC module Fixed to the mounting area.
  • thermoelectric spacer disposed between the mounting area and the ESC module.
  • the heat dissipating gasket is a silicone heat dissipating gasket.
  • a heat dissipating portion is disposed on the periphery of the mounting board, and the heat dissipating portion is integrally formed with the mounting board.
  • a power assembly includes a mounting base and any one of the above-mentioned power devices disposed on the mounting seat, the upper end of the mounting seat is provided with an upper receiving portion, and the lower end is provided with a lower receiving portion, each of which houses the power Device.
  • a recessed portion is recessed in a middle portion of the outer wall of the mounting seat.
  • annular light bar is disposed between the lower receiving portion and the mounting plate, and the annular light bar includes an annular light strip and an annular light cover covering the annular light strip.
  • An aircraft includes an aircraft body, an arm disposed on the aircraft body, and a power assembly of any of the foregoing disposed on the arm.
  • a connector is included to connect the mount and the arm.
  • the present application separates the ESC module from the flight control module, disperses the heat source of the aircraft, and improves the heat dissipation effect of the ESC module and the flight control module, as opposed to the ESC.
  • the aircraft integrated with the module and the flight control module, the aircraft of the embodiment has better heat dissipation effect, and integrates the ESC module and the driving component, and has good heat dissipation effect between the ESC module and the driving component.
  • the silicone heat sink and aluminum mounting plate can further improve the heat dissipation of the aircraft and simplify the installation process of the aircraft.
  • Figure 1 is a schematic view of an aircraft of the present application
  • Figure 2 is an exploded view of a power assembly of the present application
  • Figure 3 is an exploded view of a power unit of the present application
  • FIG. 4 is a schematic view of a ring light strip of the present application.
  • the present application also provides an aircraft 30 including an aircraft main body 31 , an arm 32 disposed on the aircraft main body 31 , and a power assembly 20 disposed on the arm 32 .
  • the aircraft body includes a fuselage, a flight control module disposed inside the fuselage, and a battery module.
  • the power assembly 20 includes a mounting base 21, and a power unit 10 disposed on the mounting base 21.
  • the upper end of the mounting seat 21 is provided with an upper receiving portion 22, and the lower end is provided with a lower receiving portion 23, each of which houses a power unit. .
  • the power unit 10 includes a driving member 11 , a propeller 12 driven by the driving member 11 , and an electric adjusting module 13 connected to the driving member 11 .
  • the electric adjusting module 13 and the propeller 12 are respectively disposed at two ends of the driving member 11 .
  • the driving member 11 is a motor.
  • a heat dissipating pad 14 and a mounting plate 15 are disposed between the ESC module 13 and the driving member 11.
  • the driving member 11 is fixed on the upper side of the mounting plate 15.
  • the mounting plate 15 is provided with a mounting area 16 on the lower side thereof, and the heat dissipating pad 14 is disposed on the mounting surface. Between the area 16 and the ESC module 13, the ESC module 13 is fixedly disposed on the mounting area 16.
  • the heat sink 14 is preferably a silicone heat sink. Further, a heat dissipating portion 17 is integrally provided on the periphery of the mounting plate 15, and the heat dissipating portion 17 is integrally formed with the mounting plate 15, and the mounting plate 15 is preferably an aluminum mounting plate. Since the ESC module and the flight control module are the main heating sources of the aircraft, the ESC module is separated from the flight control module, which can disperse the heat source of the aircraft and improve the heat dissipation effect of the ESC module and the flight control module, compared with the ESC module.
  • the aircraft with integrated flight control module the aircraft of the embodiment has better heat dissipation effect, and integrates the ESC module and the driving component, and uses the silica gel with good heat dissipation effect between the ESC module and the driving component.
  • the heat sink and the aluminum mounting plate can further improve the heat dissipation of the aircraft and simplify the installation process of the aircraft.
  • a recess 24 is recessed in the outer wall of the mounting seat 21.
  • the weight of the mount can be reduced, thereby reducing the load on the drive member.
  • the aircraft in this embodiment further includes a connecting member 26, and the connecting member 26 is directed from the outer wall of the mounting seat.
  • the outer extension is formed to connect the mount 21 and the above-mentioned arm.
  • the connector and the 26 mount 21 may be integrally formed or assembled.
  • a plurality of bosses are protruded from the mounting region 16, and a screw hole is disposed on the boss.
  • the heat dissipation pad 14 is disposed in a limiting interval formed by the plurality of bosses, and the ESC module 13 is placed.
  • the ESC module 13 is fixedly disposed on the mounting area 16 by screws.
  • the above-mentioned limiting interval serves to locate the heat dissipating pad 14 and maximize the contact area between the heat dissipating pad 14 and the ESC module 13, thereby improving the heat dissipating effect of the ESC module 13.
  • the center of the mounting area 16 is also provided with a through hole to reduce the weight of the mounting plate, thereby reducing the load on the driving member.
  • the driving member 11 is fixed to the upper side of the mounting board 15 by screws.
  • the mounting plate 15 is fixedly disposed on the upper housing portion 22 and the lower housing portion 23 by screws, respectively. Wherein, the ESC module is completely received by the accommodating portion, and the driving component portion is exposed outside the accommodating portion.
  • annular light bar 25 is further disposed between the lower receiving portion 23 and the mounting plate 15.
  • the ring light bar 25 includes an annular light strip 25a and an annular light cover 25b covering the annular light strip 25a.
  • the ring light strip is connected to the lower receiving portion and the mounting plate by snapping.
  • the above-mentioned ring light bar is arranged on the aircraft to serve as a warning for the operator to locate the position of the aircraft.
  • the utility model has the beneficial effects that the heat dissipation source of the aircraft is dispersed, the heat source of the aircraft is dispersed, and the heat dissipation effect of the electronic control module and the flight control module is improved, and the power module is integrated with the flight control module.
  • the aircraft of the embodiment has a better heat dissipation effect, and the ESC module and the driving component are integrated, and the silicone heat dissipating gasket with good heat dissipation effect between the ESC module and the driving component is utilized.
  • the aluminum mounting plate can further improve the heat dissipation of the aircraft and simplify the installation process of the aircraft.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Arrangement Of Elements, Cooling, Sealing, Or The Like Of Lighting Devices (AREA)
  • Road Signs Or Road Markings (AREA)
  • Cooling Or The Like Of Electrical Apparatus (AREA)

Abstract

本申请提供一种飞行器及其动力装置、动力组件，其中，动力装置包括驱动件、受驱动件驱动的螺旋桨、与驱动件连接的电调模块，电调模块和螺旋桨分别设置于驱动件两端。本申请还提供一种包括上述动力装置的动力组件及其飞行器。由于电调模块和飞控模块是飞行器的主要发热源，将电调模块与飞控模块分离，可以分散飞行器的发热源，提高电调模块和飞控模块的散热效果，将电调模块与驱动件整合在一起，利用设置于电调模块和驱动件之间的具有良好散热效果的硅胶散热垫片和铝制安装板，可以进一步提高飞行器的散热效果，同时可以简化飞行器的安装过程。

Description

一种飞行器及其动力装置、动力组件 技术领域
本申请涉及无人机技术领域，特别涉及一种飞行器及其动力装置、动力组件。
背景技术
近几年来，不断兴起的多旋翼飞行器因其具有的成本低、易操作、具有高度灵活性和可以超低空飞行等特点越来越受到各行各业的广泛使用，现有的大多数飞行器主要应用于科学研究、地理探测、农业浇灌及视频拍摄等领域。目前，由于电池、动力系统以及电调系统等工作时产生大量热量的问题，导致飞行器损耗大，从而影响飞行器的寿命。另外，由于电调系统与飞控系统一起组装在飞行器主体上，安装复杂。
因此，如何提高飞行器的散热效率以及简化飞行器的安装成为本行业的研究热点。
技术问题
问题的解决方案
技术解决方案
本申请的目的在于提供一种飞行器及其动力装置、动力组件，能够提高飞行器的散热效率以及简化飞行器的安装过程。
为实现本申请的目的，采取的技术方案是：
一种动力装置，其特征在于，包括驱动件、受所述驱动件驱动的螺旋桨、与所述驱动件连接的电调模块，所述电调模块和所述螺旋桨分别设置于所述驱动件两端。
进一步的是，所述电调模块与所述驱动件之间设有安装板，所述驱动件固定于所述安装板上侧，所述安装板下侧设有安装区域，所述电调模块固定于所述安装区域上。
进一步的是，它还进一步地包括有散热垫片，所述散热垫片设置于所述安装区域与所述电调模块之间。
进一步的是，所述散热垫片为硅胶散热垫片。
进一步的是，所述安装板外围设有散热部，所述散热部与安装板一体成型。
一种动力组件，包括安装座、设置于所述安装座上的任意一项上述的动力装置，所述安装座上端设有上收容部，下端设有下收容部，分别各收容有一所述动力装置。
进一步的是，所述安装座外壁中部凹设一凹陷部。
进一步的是，所述下收容部和所述安装板之间设有一环形灯条，所述环形灯条包括一环形灯带、以及包覆所述环形灯带的环形灯罩。
一种飞行器，包括飞行器主体、设置于飞行器主体上的机臂、以及设置于所述机臂上任意一项上述的动力组件。
进一步的是，包括一连接件，连接所述安装座和所述机臂。
发明的有益效果
有益效果
与现有技术相比，本申请具有以下有益效果：
由于飞控模块和电调模块是飞行器的主要发热源，本申请通过将电调模块与飞控模块分离，分散飞行器的发热源，提高电调模块和飞控模块的散热效果，相对于电调模块与飞控模块整合在一起的飞行器，本实施例的飞行器具有更加优良的散热效果，将电调模块与驱动件整合在一起，利用设置于电调模块和驱动件之间的具有良好散热效果的硅胶散热垫片和铝制安装板，可以进一步提高飞行器的散热效果，同时可以简化飞行器的安装过程。
对附图的简要说明
附图说明
图1是本申请的一种飞行器示意图；
图2是本申请的一种动力组件爆炸图；
图3是本申请的一种动力装置爆炸图；
图4是本申请的环形灯条示意图。
附图标记说明：
10.动力装置，11.驱动件，12.螺旋桨，13.电调模块，14.散热垫片，15.安装板 ，16.安装区域，17.散热部，20.动力组件，21.安装座，22.上收容部，23.下收容部，24.凹陷部，25.环形灯条，25a.环形灯带，25b.环形灯罩，26.连接件，30.飞行器，31.飞行器主体，32.机臂。
发明实施例
本发明的实施方式
下面结合附图对本申请的实施例进行详细说明：
如图1所示，本申请还提供一种飞行器30，包括飞行器主体31、设置于飞行器主体31上的机臂32、以及设置于机臂32上的动力组件20。其中，飞行器主体包括机身、设置于机身内部的飞控模块和电池模块。
如图2所示，动力组件20包括安装座21，设置于安装座21上的动力装置10，安装座21上端设有上收容部22，下端设有下收容部23，分别各收容有一动力装置。
如图3所示，动力装置10包括驱动件11、受驱动件11驱动的螺旋桨12、与驱动件11连接的电调模块13，电调模块13和螺旋桨12分别设置于驱动件11两端。其中，驱动件11是电机。电调模块13与驱动件11之间设有散热垫片14和安装板15，驱动件11固定于安装板15上侧，安装板15下侧设有安装区域16，散热垫片14设置于安装区域16和电调模块13之间，电调模块13固定设置于安装区域16上。其中，散热垫片14优选为硅胶散热垫片。进一步地，安装板15外围设有散热部17，散热部17与安装板15一体成型，安装板15优选为铝制安装板。由于电调模块和飞控模块是飞行器的主要发热源，将电调模块与飞控模块分离，可以分散飞行器的发热源，提高电调模块和飞控模块的散热效果，相对于电调模块与飞控模块整合在一起的飞行器，本实施例的飞行器具有更加优良的散热效果，将电调模块与驱动件整合在一起，利用设置于电调模块和驱动件之间的具有良好散热效果的硅胶散热垫片和铝制安装板，可以进一步提高飞行器的散热效果，同时可以简化飞行器的安装过程。
如图2所示，安装座21外壁凹设有一凹陷部24。通过设置凹陷部24，可以减轻安装座的重量，从而减轻驱动件的负载。
进一步地，本实施例中的飞行器还包括一连接件26，连接件26自安装座外壁向 外延伸形成，连接安装座21和上述机臂。连接件与26安装座21可以是一体成型或是组装而成。
如图3所示，安装区域16的凸设多个凸台，凸台上设有螺孔，散热垫片14设置于上述多个凸台围绕形成的限位区间内，电调模块13安放在凸台上，通过螺丝使电调模块13固定设置于安装区域16上。上述限位区间起到定位散热垫片14的作用，同时使散热垫片14与电调模块13的接触面积最大化，提高电调模块13的散热效果。安装区域16中心还设有一通孔，可以减轻安装板的重量，从而减轻驱动件的负载。驱动件11通过螺丝固定设置于安装板15上侧。
安装板15通过螺丝分别固定设置于上收容部22和下收容部23上。其中，电调模块完全被收容部收容，驱动件部分裸露于收容部外。
进一步地，如图2所示，下收容部23和安装板15之间还设有一环形灯条25。如图4所示，环形灯条25包括一环形灯带25a、以及包覆环形灯带25a的环形灯罩25b。上述环形灯条通过卡接的方式连接所述下收容部和所述安装板。在飞行器上设置上述环形灯条可以起到提示警示的作用，方便操作者定位飞行器的位置。
本申请的有益效果在于通过将飞行器的主要发热源电调模块和飞控模块分离，分散飞行器的发热源，提高电调模块和飞控模块的散热效果，相对于电调模块与飞控模块整合在一起的飞行器，本实施例的飞行器具有更加优良的散热效果，将电调模块与驱动件整合在一起，利用设置于电调模块和驱动件之间的具有良好散热效果的硅胶散热垫片和铝制安装板，可以进一步提高飞行器的散热效果，同时可以简化飞行器的安装过程。
以上所述实施例的各技术特征可以进行任意的组合，为使描述简洁，未对上述实施例中的各个技术特征所有可能的组合都进行描述，然而，只要这些技术特征的组合不存在矛盾，都应当认为是本说明书记载的范围。
以上所述实施例仅表达了本申请的几种实施方式，其描述较为具体和详细，但并不能因此而理解为对本申请保护范围的限制。应当指出的是，对于本领域的普通技术人员来说，在不脱离本申请构思的前提下，还可以做出如果干变形和改进，这些都属于本申请的保护范围。因此，本申请专利的保护范围应以所附权利要求为准。

Claims (10)

  1. 一种动力装置，其特征在于，包括驱动件、受所述驱动件驱动的螺旋桨、与所述驱动件连接的电调模块，所述电调模块和所述螺旋桨分别设置于所述驱动件两端。
  2. 根据权利要求1的动力装置，其特征在于，所述电调模块与所述驱动件之间设有安装板，所述驱动件固定于所述安装板上侧，所述安装板下侧设有安装区域，所述电调模块固定于所述安装区域上。
  3. 根据权利要求2的动力装置，其特征在于，它还进一步地包括有散热垫片，所述散热垫片设置于所述安装区域与所述电调模块之间。
  4. 根据权利要求3的动力装置，其特征在于，所述散热垫片为硅胶散热垫片。
  5. 根据权利要求2或3的动力装置，其特征在于，所述安装板外围设有散热部，所述散热部与所述安装板一体成型。
  6. 一种动力组件，其特征在于，包括安装座、设置于所述安装座上的如权利要求1至5任意一项的动力装置，所述安装座上端设有上收容部，下端设有下收容部，分别各收容有一所述动力装置。
  7. 根据权利要求6的动力组件，其特征在于，所述安装座外壁中部凹设一凹陷部。
  8. 根据权利要求7动力组件，其特征在于，所述下收容部和所述安装板之间设有一环形灯条，所述环形灯条包括一环形灯带、以及包覆所述环形灯带的环形灯罩。
  9. 一种飞行器，其特征在于，包括飞行器主体、设置于所述飞行器主体上的机臂、以及设置于所述机臂上的如权利要求6至8任意一项的动力组件。
  10. 根据权利要求9的飞行器，其特征在于，包括一连接件，连接所述安装座和所述机臂。
PCT/CN2017/084327 2016-05-25 2017-05-15 一种飞行器及其动力装置、动力组件 WO2017202223A1 (zh)

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CN201620491491.9 2016-05-25

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CN115258170A (zh) * 2022-09-28 2022-11-01 北京瀚科智翔科技发展有限公司 用于共轴双桨无人机的一体化电机电调结构

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