WO2020135796A1 - 一种风扇组件、惯性测量组件以及无人飞行器 - Google Patents

一种风扇组件、惯性测量组件以及无人飞行器 Download PDF

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Publication number
WO2020135796A1
WO2020135796A1 PCT/CN2019/129561 CN2019129561W WO2020135796A1 WO 2020135796 A1 WO2020135796 A1 WO 2020135796A1 CN 2019129561 W CN2019129561 W CN 2019129561W WO 2020135796 A1 WO2020135796 A1 WO 2020135796A1
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Prior art keywords
fan assembly
bracket
fan
groove
assembly
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PCT/CN2019/129561
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English (en)
French (fr)
Inventor
梁智颖
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深圳市道通智能航空技术有限公司
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Publication of WO2020135796A1 publication Critical patent/WO2020135796A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D43/00—Arrangements or adaptations of instruments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for

Definitions

  • the invention relates to the field of aircraft, and in particular to a fan assembly, an inertial measurement assembly and an unmanned aerial vehicle.
  • Unmanned aerial vehicle or UAV for short, is a new concept equipment in rapid development, which has the advantages of flexible maneuverability, fast response, unmanned driving and low operation requirements.
  • UAVs are equipped with inertial measurement devices and fan assemblies.
  • the inertial measurement device is installed in the fuselage.
  • the inertial measurement device is used to measure the angular velocity and acceleration of the fuselage of the unmanned aerial vehicle. Safe navigation. For inertial measurement devices, measurement accuracy is one of the most critical indicators.
  • the fan component is used to dissipate the control circuit component.
  • the fan assembly usually generates vibration, which interferes with the inertial measurement device, which leads to a decrease in the accuracy of the inertial side beam device and frequent misjudgment.
  • An object of the embodiments of the present invention is to provide a fan assembly, an inertial measurement assembly, and an unmanned aerial vehicle to solve the technical problem of the fan assembly having a large interference with the inertial measurement device in the prior art.
  • a fan assembly which is installed on a fuselage of an unmanned aerial vehicle, the fan assembly includes: a bracket for connecting with the fuselage; a fixing seat, which is installed on the bracket; and a fan, which is installed on The fixing seat; and the shock absorber, abutting between the bracket and the fixing seat.
  • the bracket includes a bracket body and an air guide groove surrounded by the bracket body, and the fan is located in the air guide groove.
  • the bracket further includes a groove body provided on the bracket body, an opening of the groove body faces the wind guide groove, and the opening of the groove body communicates with the wind guide groove
  • the fixing base includes a fixing portion and an extending portion extending from the fixing portion, the fan is installed on the fixing portion, the extending portion is inserted into the groove body, the shock absorber abuts on the extension Between the part and the groove wall of the groove body.
  • the fan includes a motor and a fan blade connected to the motor, and a stator of the motor is connected to the fixed part.
  • the extension part is provided with a mounting hole, and the stator of the motor is connected to the mounting hole through a bolt.
  • the bracket further includes a bent portion, one end of the bent portion is connected to the groove body, and the other end of the bent portion is connected to the bracket body;
  • the other end of the bending portion connected to the bracket body may be bent relative to the bracket body in a direction away from the wind guide groove, so that the groove body is separated from the extension portion.
  • the bent portion is made of elastic material.
  • the groove body is further provided with a mounting portion, and the mounting portion is provided with a through hole.
  • the bracket is provided with a mounting portion, the mounting portion is located on a side of the trough away from the wind guide groove, and the mounting portion is located on a side of the bracket away from the wind guide groove ,
  • the mounting portion is provided with a through hole.
  • the shock absorber is provided with a receiving opening, an end of the extending portion away from the fixing portion is wrapped in the receiving opening by the damping member, and the extending portion is away from the fixing portion
  • One end of the and the shock absorber are both contained in the groove body.
  • the shock absorbing member includes two shock absorbing parts, and a connecting part connected between the two shock absorbing parts; an end of the extending part away from the fixing part is provided with a connecting hole, The connecting portion is accommodated in the connecting hole, and the two damping portions are respectively located on two opposite sides of the extending portion; any one of the two damping portions away from the connecting portion is The groove walls of the groove body abut against each other, so that the extending portion is separated from the groove wall of the groove body.
  • the number of the extending portions is plural, and the plurality of extending portions are evenly arranged around the fixing portion.
  • the number of extensions is three.
  • the shock absorber is made of rubber.
  • the shock absorber is a spring or a spring.
  • the bracket is integrally formed with the fixing base.
  • an inertial measurement assembly which is mounted on an unmanned aerial vehicle, and includes an installation plate for connecting to the fuselage of the unmanned aerial vehicle, an inertial measurement device provided on the installation plate, and the above-mentioned A fan assembly, the fan assembly is disposed close to the inertial measurement device.
  • an unmanned aerial vehicle including a fuselage and an arm connected to the fuselage, the unmanned aerial vehicle further includes an inertial measurement assembly as described above.
  • the fan assembly is installed on the fuselage of the unmanned aerial vehicle, and the fan assembly includes a bracket for The fuselage is connected; a fixed seat is installed on the bracket; a fan is installed on the fixed seat; and a shock absorber is abutted between the bracket and the fixed seat.
  • the shock absorbing member By abutting the shock absorbing member between the bracket and the fixing seat, the shock absorbing member can weaken the vibration transmitted by the fan to the fuselage, and has little effect on the inertial measurement device.
  • FIG. 1 is a perspective view of an unmanned aerial vehicle according to an embodiment of the invention.
  • FIG. 2 is an exploded view of the UAV shown in FIG. 1;
  • FIG. 3 is a perspective view of the fan assembly of the UAV shown in FIG. 2;
  • FIG. 4 is a rear view of the fan assembly shown in FIG. 3;
  • FIG. 5 is a front view of the fan assembly shown in FIG. 3;
  • FIG. 6 is an A-A cross-sectional view of the fan assembly shown in FIG. 5;
  • FIG. 7 is an exploded view of the fan assembly shown in FIG. 3;
  • FIG. 8 is a right side view of the fan assembly shown in FIG. 3;
  • FIG. 9 is a B-B sectional view of the fan assembly shown in FIG. 8, wherein the dotted line part is another state of the bracket;
  • FIG. 10 is a partial disassembly schematic diagram of the fan assembly shown in FIG. 3;
  • FIG. 11 is a schematic diagram of partial assembly of the fan assembly shown in 10;
  • FIG. 12 is a partial disassembly schematic diagram of another implementation manner of the fan assembly shown in FIG. 10;
  • FIG. 13 is a schematic diagram of the assembly of the shock absorber and the fixing seat of the fan assembly shown in FIG. 12;
  • FIG. 14 is a schematic diagram of the assembly of the fixing seat and the bracket of the fan assembly shown in FIG. 13.
  • FIG. 1 and FIG. 2 is an unmanned aerial vehicle 400 according to one embodiment of the present invention.
  • the unmanned aerial vehicle 400 can be divided into five major categories: micro, light, small, medium, and large according to factors such as weight and speed.
  • the UAV 400 with a smaller size is preferred.
  • the UAV 400 includes a fuselage 300, an arm connected to the fuselage 300, and an inertial measurement assembly 200 installed in the fuselage 300.
  • the inertial measurement assembly 200 includes a mounting plate, an inertial measurement device provided on the mounting plate, and a fan assembly 100 mounted on the fuselage.
  • the fan assembly 100 is disposed near the inertial measurement device.
  • the fuselage 300 includes a control circuit assembly composed of electronic components such as an MCU, and the control circuit assembly includes a plurality of control modules, for example, for controlling the operation of the power assembly to control the flying attitude of the UAV 400 A flight control module, a positioning module for navigating the unmanned aerial vehicle, a temperature control module for controlling the operation of the fan assembly 100, and a data processing module for processing environmental information acquired by related airborne equipment.
  • the drawings only show components related to the embodiments of the present invention.
  • the fan assembly 100 is applied to, but not limited to, the UAV 400, for example, in an unmanned boat or an unmanned vehicle.
  • the fan assembly 100 includes a bracket 10, a fixing base 20, a shock absorber 30, and a fan 40.
  • the fan 40 is installed on the fixed base 20.
  • the fixed base 20 is installed on the bracket 10.
  • the bracket 10 and the fixed base 20 are connected by the shock absorber 30.
  • the bracket 10 is connected to the body 300.
  • the vibration of the fan assembly 100 indirectly transmitted to the inertial measurement device through the body 300 can be effectively reduced, thereby ensuring the accuracy of the inertial measurement device.
  • the bracket 10 has a thin ring shape as a whole, the bracket 10 is provided with an air guide groove 11, and the inner ring surface of the bracket 10 forms a groove wall of the air guide groove 11, that is, the air guide groove 11 is a through slot.
  • the fan 40 is located in the air guide groove 11, and the air guide groove 11 is used to guide the direction of the airflow output by the fan 40.
  • the ring shape may be a closed ring or an incomplete ring that is not completely closed. The strength of the closed ring is higher than the two, but it is not limited in the present invention.
  • the groove wall of the air guiding groove 11 is provided with a slot 12 for installing the fixing base 20.
  • the number of the slots 12 is plural, and the plurality of slots 12 are distributed on the groove wall of the air guide slot 11 in a ring shape.
  • the plurality of slots 12 are evenly distributed, for example,
  • the three slots 12 are arranged in a zigzag shape, and the fixing seat 20 is inserted into the three slots 11 so that the fixing seat 20 is fixed relative to the bracket 10.
  • the bracket 10 includes a bracket main body 13, a bent portion 14 and a groove 15.
  • the bracket body 13, the bending portion 14 and the groove body 15 together surround the groove wall of the air guide groove 11.
  • the bracket body 13 may also surround the guide wall alone
  • the bending portion 14 can be elastically bent relative to the bracket body 13 in a direction away from the air guiding groove 11, so that the slot 12 and the fixing base 20
  • the separation can realize the convenient disassembly and assembly of the fixing seat 20 and the bracket 10.
  • the bracket body 13, the bent portion 14 and the groove body 15 can be formed by providing grooves on the bracket 10, however, according to the actual situation, the bracket 10 may be entirely It may be made of an elastic material, or only the bending portion 14 may be made of an elastic material.
  • the bracket 10 is fixed to the body 300 by bolts.
  • the bracket 10 is provided with a mounting portion 16, and the mounting portion 16 is provided with a through hole 17 for the bolt to pass through.
  • the mounting portion 16 is disposed on a side of the slot body 15 facing away from the slot 12.
  • the bracket 10 may also be integrally formed with the body 300.
  • the mounting portion 16 may also be provided at other positions of the bracket 10, for example, the mounting portion 16 is provided on the bracket body 13 and is located on the bracket body 13 away from the wind guide groove On the side of 11, the mounting portion 16 is connected to the bracket 10, and may be located on the side of the bracket facing away from the wind guide groove 11.
  • the bracket 10 and the fixing base 20 are two parts.
  • the fixed base 20 and the bracket 10 are two components, which can further reduce the transmission of the fan 40 to The vibration of the body 10.
  • bracket 10 and the fixing base 20 are integrally formed.
  • the fixing base 20 can be made of plastic material.
  • the fixing base 20 includes a fixing portion 21 and an extension portion 22.
  • the fixing portion 20 has the extension portion 22 extending toward the groove wall of the air guide groove 11.
  • the fixing portion 21 has a ring shape, and the fan 40 is mounted on the fixing portion 21. Specifically, the fixing portion 21 is sleeved on the fan 40.
  • the number of the extension portions 22 corresponds to the number of the slots 12.
  • a plurality of the extension portions 22 are distributed around the fixing portion 21 in a ring shape.
  • Each extension portion 22 is connected to one
  • the slots 12 correspond to each other.
  • the three extensions 22 are distributed in a zigzag shape, and the three extensions 22 are inserted into the three slots 12 respectively.
  • the extending portion 22 and the slot 12 may be provided with any shape of concave-convex mating structure.
  • the cross-section of the extending portion 22 and the slot 12 are substantially rectangular
  • the cross section of the extension portion 22 and the cross section of the slot 12 may be circular, triangular, etc., which is not limited in the present invention.
  • the edge of the end of the extending portion 22 facing away from the fixing portion 21 is provided with an arc transition 220 to facilitate the insertion of the extending portion 22 into the slot 12.
  • the extension portion 22 is further provided with a mounting hole 221 for mounting the fan 40.
  • the fan 40 is fixedly connected to the mounting hole 221 by a bolt.
  • the shock absorbing member 30 may be made of elastic rubber or plastic. In some other embodiments, the shock absorbing member 30 is a spring or an elastic sheet.
  • the shock absorber 30 is disposed between the groove wall of the slot 12 and the extension 22 so that the extension 22 is separated from the groove wall of the slot 12.
  • the number of the shock absorbers 30 corresponds to the number of the extensions 22, and each of the shock absorbers 30 corresponds to a corresponding extension 22.
  • the shock absorber 30 is provided with a receiving opening 31, and the shock absorber 30 wraps the extending portion 22 through the receiving opening 31 away from the fixing portion 21 At the end.
  • the shock absorber 30 is against the groove wall of the slot 12.
  • the shock absorbing member 30 includes two shock absorbing portions 32 and a connecting portion 31 connected between the two shock absorbing portions 32.
  • a connecting hole 222 is provided at an end of the extending portion 22 facing away from the fixing portion 21, an end of the connecting portion 31 is penetrated by the connecting hole 222, and the two shock-absorbing portions 32 are respectively located at the connecting portion 31
  • the shock absorber 30 may be directly injection molded on the extension 22. Any one of the two shock absorbing portions 32 is against the groove wall of the slot 12, so that the extending portion 22 is detached from the groove wall of the slot 12.
  • the fan 40 includes a motor 41, a fan blade 42, and a cable 43.
  • One end of the flat cable 43 is connected to the stator of the motor 41, the other end of the flat cable 43 is connected to the temperature control module, and the fan blade 42 is installed on the rotor of the motor 41.
  • the fixing portion 21 is sleeved on the stator of the motor 41, and the stator of the motor 41 and the mounting hole 221 are fixedly connected by bolts.
  • the fan assembly 100 is installed on the fuselage 300 of the UAV 400, and the fan assembly 100 includes : Bracket 10 for connecting to the fuselage 300; a fixed base 20, mounted on the bracket 10; a fan 40, mounted on the fixed base 20; and a shock absorber 30, abutting on the bracket 10 and Between the fixed seats 20.
  • the shock absorber 30 By abutting the shock absorber 30 between the bracket 10 and the fixing base 20, the shock absorber 30 can weaken the vibration transmitted by the fan 40 to the fuselage 300, which has little effect on the inertial measurement device .

Abstract

一种风扇组件（100）、惯性测量组件（200）以及无人飞行器（400），其中风扇组件（100）安装于无人飞行器（400）的机身（300），所述风扇组件（100）包括：支架（10），用于与所述机身（300）相连；固定座（20），安装于所述支架（10）；风扇（40）安装于所述固定座（20）；以及减震件（30），抵接于所述支架（10）与所述固定座（20）之间。通过将所述减震件（30）抵接于所述支架（10）与所述固定座（20）之间，所述减震件（30）可削弱风扇（40）传递至机身（300）的震动，对惯性测量装置的影响较小。

Description

一种风扇组件、惯性测量组件以及无人飞行器 【技术领域】
本发明涉及飞行器领域，尤其涉及一种风扇组件、惯性测量组件以及无人飞行器。
【背景技术】
无人驾驶飞机，简称无人飞行器(UAV)，是一种处在迅速发展中的新概念装备，其具有机动灵活、反应快速、无人驾驶、操作要求低的优点。
通常，无人飞行器搭载有惯性测量装置和风扇组件。
惯性测量装置最核心的传感器之一，安装于机身，惯性测量装置用于测量无人飞行器的机身的角速度和加速度，进而解算出无人飞行器的自身姿态，保证了无人飞行器在外界环境中安全导航。对于惯性测量装置而言，测量精度是最关键的指标之一。
由于无人飞行器内部的控制电路组件的功率较大，发热比较严重，风扇组件用于对控制电路组件进行散热。
但是，风扇组件通常会产生震动，从而干扰惯性测量装置，从而导致惯性侧梁装置精度下降，经常出现误判。
【发明内容】
本发明实施例的目的在于提供一种风扇组件、惯性测量组件以及无人飞行器，以解决现有技术中风扇组件对惯性测量装置的干扰较大的技术问题。
本发明实施例解决其技术问题采用以下技术方案：
在第一方面，提供一种风扇组件，安装于无人飞行器的机身，所述风扇组件包括：支架，用于与所述机身相连；固定座，安装于所述支架；风扇，安装于所述固定座；以及减震件，抵接于所述支架与所述固定座之间。
在一些实施例中，所述支架包括支架主体和由所述支架主体围成的导风槽，所述风扇位于所述导风槽内。
在一些实施例中，所述支架还包括设于所述支架主体的槽体，所述槽体的开口朝向所述导风槽，且所述槽体的所述开口与所述导风槽连通；所述固定座包括固定部和自所述固定部延伸的延伸部，所述风扇安装于所述固定部，所述延伸部插入所述槽体，所述减震件抵接于所述延伸部与所述槽体的槽壁之间。
在一些实施例中，所述风扇包括电机和与所述电机相连的扇叶，所述电机的定子与所述固定部相连。
在一些实施例中，所述延伸部设置有安装孔，所述电机的定子通过螺栓与所述安装孔相连。
在一些实施例中，所述支架还包括弯折部，所述弯折部的一端连接所述槽体，所述弯折部的另一端连接所述支架主体；
所述弯折部连接所述支架主体的另一端可相对于所述支架主体朝远离所述导风槽的方向弯折，使得所述槽体与所述延伸部相分离。
在一些实施例中，所述弯折部由弹性材质制得。
在一些实施例中，所述槽体还设置有安装部，所述安装部设置有贯通孔。
在一些实施例中，所述支架设置有安装部，所述安装部位于所述槽体背离所述导风槽的一侧，所述安装部位于所述支架背离所述导风槽的一侧，所述安装部设置有贯通孔。
在一些实施例中，所述减震件设置有收容口，所述延伸部远离所述固定部的一端被所述减震件包裹于所述收容口内，且所述延伸部远离所述固定部的一端和所述减震件均收容于所述槽体内。
在一些实施例中，所述减震件包括两个减震部，以及连接于所述两个减震部之间的连接部；所述延伸部远离所述固定部的一端设置有连接孔，所述连接部收容于所述连接孔内，所述两个减震部分别位于所述延伸部的两相对侧；所述两个减震部的任意一个远离所述连接部的一端与所述槽体的槽壁相抵，使得所述延伸部与所述槽体的槽壁相脱离。
在一些实施例中，所述延伸部的数量为多个，多个所述延伸部环绕所述固定部均匀设置。
在一些实施例中，所述延伸部的数量为三个。
在一些实施例中，所述减震件由橡胶材质制得。
在一些实施例中，所述减震件为弹簧或者弹片。
在一些实施例中，所述支架与所述固定座一体成型。
在第二方面，提供一种惯性测量组件，安装于无人飞行器，包括用于与所述无人飞行器的机身相连的安装板、设于所述安装板的惯性测量装置以及如上所述的风扇组件，所述风扇组件靠近所述惯性测量装置设置。
在第三方面，提供一种无人飞行器，包括机身、与所述机身相连的机臂，所述无人飞行器还包括如上所述的惯性测量组件。
与现有技术相比较，本发明实施例提供的无人飞行器、惯性测量组件以及风扇组件中，所述风扇组件安装于无人飞行器的机身，所述风扇组件包括：支架，用于与所述机身相连；固定座，安装于所述支架；风扇，安装于所述固定座；以及减震件，抵接于所述支架与所述固定座之间。通过将所述减震件抵接于所述支架与所述固定座之间，所述减震件可削弱风扇传递至机身的震动，对惯性测量装置的影响较小。
【附图说明】
一个或多个实施例通过与之对应的附图进行示例性说明，这些示例性说明并不构成对实施例的限定，附图中具有相同参考数字标号的元件表示为类似的元件，除非有特别申明，附图中的图不构成比例限制。
图1为本发明其中一实施例提供一种无人飞行器的立体图；
图2为图1所示的无人飞行器的爆炸视图；
图3为图2所示的无人飞行器的风扇组件的立体图；
图4为图3所示的风扇组件的后视图；
图5为图3所示的风扇组件的主视图；
图6为图5所示的风扇组件的A-A剖视图；
图7为图3所示的风扇组件的分解图；
图8为图3所示的风扇组件的右视图；
图9为图8所示的风扇组件的B-B剖视图，其中虚线部分为支架另一种状态；
图10为图3所示的风扇组件的部分拆解示意图；
图11为10所示的风扇组件的部分组装示意图；
图12为图10所示的风扇组件的另一种实现方式的部分拆解示意图；
图13为图12所示的风扇组件的减震件与固定座相装配的示意图；
图14为图13所示的风扇组件的固定座与支架相装配的示意图。
【具体实施方式】
为了便于理解本发明，下面结合附图和具体实施例，对本发明进行更详细的说明。需要说明的是，当元件被表述“固定于”另一个元件，它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件，它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”、“内”、“外”以及类似的表述只是为了说明的目的。
除非另有定义，本说明书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。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，不是用于限制本发明。本说明书所使用的术语“和/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。
此外，下面所描述的本发明不同实施例中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
请一并参阅图1和图2，为本发明其中一实施例提供的无人飞行器400，所述无人飞行器400根据重量、速度等因素，可以分为微型、轻型、小型、中型以及大型五大类，在本发明中，优选体型较小的无人飞行器400。
所述无人飞行器400包括机身300，与所述机身300相连的机臂，安装于所述机身300内的惯性测量组件200。
所述惯性测量组件200包括安装板，设于所述安装板的惯性测量装置，以及安装于所述机身的风扇组件100，所述风扇组件100靠近所述惯性测量装置设置。
所述机身300内包括由MCU等电子元器件组成的控制电路组件，该控制电路组件包括多个控制模块，如，用于控制所述动力组件工作以控制所述无人飞行器400飞行姿态的飞行控制模块，用于导航所述无人飞行器的定位模块，用于控制所述风扇组件100工作的温控模块，以及用于处理相关机载设备所获取的环境信息的数据处理模块等。为了便于说明本发明实施例，附图 仅示出与本发明实施例相关的部件。
请一并参阅图3至图7，所述风扇组件100应用在但不限于所述无人飞行器400上，例如，应用在无人船或者无人车等装置中。所述风扇组件100包括支架10，固定座20，减震件30，以及风扇40。所述风扇40安装于所述固定座20，所述固定座20安装于所述支架10，所述支架10与所述固定座20通过所述减震件30相连接。
所述支架10与所述机身300相连。
通过在风扇组件100内设置减震件30，可以有效降低风扇组件100通过所述机身300间接传递到所述惯性测量装置的震动，从而保证了所述惯性测量装置的精度。
所述支架10整体呈厚度较薄的环状，所述支架10设置有导风槽11，所述支架10的内环面形成所述导风槽11的槽壁，也即所述导风槽11为通槽。所述风扇40位于所述导风槽11内，所述导风槽11用于引导所述风扇40输出的气流朝向。需要说明的是，所述环状，可以为封闭的环，也可以为不完全封闭的不完全环，两者相比，封闭的环的强度更高，但在本发明中不作限定。
所述导风槽11的槽壁设置有插槽12，所述插槽12用于安装所述固定座20。所述插槽12的数量为多个，多个所述插槽12呈环形分布于所述导风槽11的槽壁上，较优地，多个所述插槽12均匀地分布，例如，三个所述插槽12呈品字形分布，所述固定座20插入三个所述插槽11，使得所述固定座20相对于所述支架10固定。
请一并参阅图8和图9，具体地，所述支架10包括支架主体13、弯折部14以及槽体15。所述支架主体13、所述弯折部14以及所述槽体15三者共同围成所述导风槽11的槽壁，根据实际情况，所述支架主体13也可独自围成所述导风槽11，其中，所述弯折部14的一端连接所述槽体15，所述弯折部14的另一端连接所述支架主体13，所述插槽12设置于所述槽体15上，也即所述槽体15围成所述插槽12。如图9虚线部分所示，所述弯折部14可相对于所述支架主体13朝远离所述导风槽11的方向弹性地弯折，使得所述插槽12与所述固定座20相分离，可实现所述固定座20与所述支架10较为方便地 拆装。可以理解的是，可通过在所述支架10上设置沟槽从而构成所述支架主体13、所述弯折部14以及所述槽体15，然而，根据实际情况，所述支架10可以整体都由弹性材质制得，也可以仅有所述弯折部14由弹性材质制得。
所述支架10通过螺栓与所述机身300相固定。
具体地，所述支架10设置有安装部16，所述安装部16设置有贯通孔17，所述贯通孔17用于螺栓穿过。较优地，所述安装部16设置于所述槽体15背离所述插槽12的一面。可以理解的是，根据实际情况，所述支架10也可以与所述机身300一体成型。根据实际情况，所述安装部16也可以设置于所述支架10的其他位置，例如，所述安装部16设置于所述支架主体13上，并且位于所述支架主体13背离所述导风槽11的一侧，因此，所述安装部16与所述支架10相连，并且位于所述支架背离所述导风槽11的一侧即可。
在本实施例中，所述支架10与所述固定座20为两个部件。通过将所述风扇40安装于所述固定座20，所述支架10安装于所述机身300，所述固定座20与所述支架10为两个部件，可进一步降低所述风扇40传递至所述机身10的震动。
在一些其他的实施例中，所述支架10与所述固定座20一体成型。
所述固定座20可由塑料材质制得，所述固定座20包括固定部21和延伸部22。所述固定部20朝所述导风槽11的槽壁的方向延伸有所述延伸部22。
所述固定部21呈环状，所述风扇40安装于所述固定部21，具体地，所述固定部21套设于所述风扇40。
所述延伸部22背离所述固定部21的一端插入所述插槽12。所述延伸部22的数量与所述插槽12的数量相对应，多个所述延伸部22呈环形地分布于所述固定部21的周围，每个所述延伸部22与一个所述插槽12相对应，例如，三个所述延伸部22呈品字形分布，三个所述延伸部22分别插入三个所述插槽12内。
可以理解的是，所述延伸部22与所述插槽12可以设置为任意形状的凹凸配合结构，在本实施例中，所述延伸部22的截面与所述插槽12的截面大致为矩形，在一些其他的实施例中，所述延伸部22的截面与所述插槽12的截面可以为圆形、三角形等，在本发明中不作限制。
所述延伸部22背离所述固定部21的一端的棱边设置圆弧过渡220，便于所述延伸部22插入所述插槽12内。
所述延伸部22上还设置有安装孔221，所述安装孔221用于安装所述风扇40，例如，所述风扇40通过螺栓与所述安装孔221固定连接。
所述减震件30可由具有弹性的橡胶或者塑胶制得，在一些其他的实施例中，所述减震件30为弹簧或者弹片。
所述减震件30设置于所述插槽12的槽壁与所述延伸部22之间，使得所述延伸部22与所述插槽12的槽壁相分隔。所述减震件30的数量与所述延伸部22的数量相对应，每个所述减震件30与一个相应的延伸部22相对应。
请参阅图9和图10，在本实施例中，所述减震件30设置有收容口31，所述减震件30通过所述收容口31包裹所述延伸部22背离所述固定部21的一端。所述减震件30与所述插槽12的槽壁相抵。
请参阅图12至图14，在一些其他的实施例中，所述减震件30包括两个减震部32，以及连接于所述两个减震部32之间的连接部31。所述延伸部22背离所述固定部21的一端设置有连接孔222，所述连接部31的一端穿设所述连接孔222，所述两个减震部32分别位于所述连接部31的两端处，所述减震件30可直接在所述延伸部22上注塑成型。所述两个减震部32中的任意一个均与所述插槽12的槽壁相抵，使得所述延伸部22与所述插槽12的槽壁相脱离。
所述风扇40包括电机41、扇叶42以及排线43。所述排线43的一端与所述电机41的定子相连，所述排线43的另一端与所述温控模块相连，所述扇叶42安装于所述电机41的转子。所述固定部21套设于所述电机41的定子，所述电机41的定子与所述安装孔221通过螺栓固定连接。
与现有技术相比较，本发明实施例提供的无人飞行器400、惯性测量组件200以及风扇组件100中，所述风扇组件100安装于无人飞行器400的机身300，所述风扇组件100包括：支架10，用于与所述机身300相连；固定座20，安装于所述支架10；风扇40，安装于所述固定座20；以及减震件30， 抵接于所述支架10与所述固定座20之间。通过将所述减震件30抵接于所述支架10与所述固定座20之间，所述减震件30可削弱风扇40传递至机身300的震动，对惯性测量装置的影响较小。
最后应说明的是：以上实施例仅用以说明本发明的技术方案，而非对其限制；在本发明的思路下，以上实施例或者不同实施例中的技术特征之间也可以进行组合，步骤可以以任意顺序实现，并存在如上所述的本发明的不同方面的许多其它变化，为了简明，它们没有在细节中提供；尽管参照前述实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的范围。

Claims (18)

  1. 一种风扇组件(100)，其特征在于，安装于无人飞行器(400)的机身(300)，所述风扇组件(100)包括：
    支架(10)，用于与所述机身(300)相连；
    固定座(20)，安装于所述支架(10)；
    风扇(40)，安装于所述固定座(20)；以及
    减震件(30)，抵接于所述支架(10)与所述固定座(20)之间。
  2. 根据权利要求1所述的风扇组件(100)，其特征在于，所述支架(10)包括支架主体(13)和由所述支架主体(13)围成的导风槽(11)，所述风扇(40)位于所述导风槽(11)内。
  3. 根据权利要求2所述的风扇组件(100)，其特征在于，所述支架(10)还包括设于所述支架主体(13)的槽体(15)，所述槽体(15)的开口朝向所述导风槽(11)，且所述槽体(12)的所述开口与所述导风槽(11)连通；
    所述固定座(20)包括固定部(21)和自所述固定部(21)延伸的延伸部(22)，所述风扇(40)安装于所述固定部(21)，所述延伸部(22)插入所述槽体(15)，所述减震件(30)抵接于所述延伸部(22)与所述槽体(15)的槽壁之间。
  4. 根据权利要求3所述的风扇组件(100)，其特征在于，所述风扇(30)包括电机(41)和与所述电机(41)相连的扇叶(40)，所述电机(41)的定子与所述固定部(21)相连。
  5. 根据权利要求4所述的风扇组件(100)，其特征在于，所述延伸部(22)设置有安装孔(221)，所述电机(41)的定子通过螺栓与所述安装孔(221)相连。
  6. 根据权利要求3-5中任一项所述的风扇组件(100)，其特征在于，所述支架(10)还包括弯折部(14)，所述弯折部(14)的一端连接所述槽体(15)，所述弯折部(14)的另一端连接所述支架主体(13)；
    所述弯折部(14)连接所述支架主体(13)的另一端可相对于所述支架主体(13)朝远离所述导风槽(11)的方向弯折，使得所述槽体(15)与所述延伸部(22)相分离。
  7. 根据权利要求6所述的风扇组件(100)，其特征在于，所述弯折部(14)由弹性材质制得。
  8. 根据权利要求3-7中任一项所述的风扇组件(100)，其特征在于，所述槽体(12)还设置有安装部(16)，所述安装部(16)位于所述槽体(12)背离所述导风槽(11)的一侧，所述安装部(16)设置有贯通孔(17)。
  9. 根据权利要求3-7中任一项所述的风扇组件(100)，其特征在于，所述支架(10)设置有安装部(16)，所述安装部(16)位于所述支架背离所述导风槽(11)的一侧，所述安装部(16)设置有贯通孔(17)。
  10. 根据权利要求3-9中任一项所述的风扇组件(100)，其特征在于，所述减震件(30)设置有收容口(31)，所述延伸部(22)远离所述固定部(21)的一端被所述减震件(30)包裹于所述收容口(31)内，且所述延伸部(22)远离所述固定部(21)的一端和所述减震件(30)均收容于所述槽体(15)内。
  11. 根据权利要求3-9中任一项所述的风扇组件(100)，其特征在于，所述减震件(30)包括两个减震部(32)，以及连接于所述两个减震部(32)之间的连接部(31)；
    所述延伸部(22)远离所述固定部(21)的一端设置有连接孔(222)，所述连接部(31)收容于所述连接孔(222)内，所述两个减震部(32)分别位于所述延伸部(22)的两相对侧；
    所述两个减震部(32)的任意一个远离所述连接部(31)的一端与所述槽体(15)的槽壁相抵，使得所述延伸部(22)与所述槽体(15)的槽壁相脱离。
  12. 根据权利要求3-11中任一项所述的风扇组件(100)，其特征在于，所述延伸部(22)的数量为多个，多个所述延伸部(22)环绕所述固定部(21)均匀设置。
  13. 根据权利要求12所述的风扇组件(100)，其特征在于，所述延伸部(22)的数量为三个。
  14. 根据权利要求1-13中任一项所述的风扇组件(100)，其特征在于，所述减震件(30)由橡胶材质制得。
  15. 根据权利要求1-9中任一项所述的风扇组件(100)，其特征在于，所 述减震件(30)为弹簧或者弹片。
  16. 根据权利要求1-15中任一项所述的风扇组件(100)，其特征在于，所述支架(10)与所述固定座(20)一体成型。
  17. 一种惯性测量组件(200)，安装于无人飞行器(400)，其特征在于，包括用于与所述无人飞行器(400)的机身(300)相连的安装板、设于所述安装板的惯性测量装置以及如权利要求1-16中任一项的风扇组件(100)，所述风扇组件(100)靠近所述惯性测量装置设置。
  18. 一种无人飞行器(400)，包括机身(300)、与所述机身(300)相连的机臂，其特征在于，所述无人飞行器(400)还包括权利要求17所述的惯性测量组件(200)。
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